turbine, process and power generation system

专利摘要:
SET OF TURBINE, PROCESS AND POWER GENERATION SYSTEM. The present invention relates to a process, together with systems for energy production, which can provide more efficient and cheaper components, originating from the control, reduction or elimination of mechanical erosion of the turbine blade (400) by erosion by particulate material or chemistry by means of gases in a combustion product stream (320). Processes, assemblies and systems may include the use of turbine blades (400), which operate at a blade speed that is significantly reduced compared to conventional turbines (400) used in typical energy production systems. The processes and systems can also make use of a recycled circulating fluid (503) to protect the turbine (400) and / or other components from perspiration. Furthermore, the recycled circulating fluid (503) can be employed to provide cleaning materials for the turbine (400).
公开号:BR112013008047B1
申请号:R112013008047-7
申请日:2011-09-20
公开日:2020-12-08
发明作者:Miles R. Palmer；Rodney John Allam；Jeremy Eron Fetvedt
申请人:Palmer Labs, Llc；8, Rivers Capital, Llc；
IPC主号:

专利说明:

FIELD OF THE INVENTION
[0001] The present invention relates to turbine and combustion components, which can be used in energy production processes and systems. The invention also provides processes for using these turbine and combustion components in energy production. BACKGROUND
[0002] Gas turbines are routinely used in energy production systems and processes, to extract energy from a flue gas stream, which is directed by the blades present in the turbine, to rotate a turbine shaft. The energy can be extracted from the rotating shaft by an electric generator, to provide energy in the form of electricity. Due to the extreme conditions (for example, high temperatures and the presence of erosive and / or corrosive materials), under which the turbines are operated in typical energy production plants (for example, coal burning power plants), the components Gas turbines are typically formed from high performance materials. Thus, gas turbines are often expensive components of energy production facilities.
[0003] Existing turbines can operate with inlet temperatures of about 1,200 ° C to about 1,400 ° C with blade temperatures of about 900 ° C to about 1,000 ° C. Thus, gas turbines, which operate in energy production facilities, typically require the use of superalloy materials to withstand high temperatures. In addition, in more advanced applications, paddle cooling is also necessary, along with the use of advanced manufacturing technology, such as directionally solidified materials, and even unique crystal paddle technology. Paddle cooling is used to help improve the turbine's temperature tolerance, and thus efficiency, but this process has been limited by the fact that only air, or in some cases, steam, has become available for cooling. The amount of air available for cooling is limited by the amount of energy available to compress and pump air, and sometimes steam through the turbine blades. Furthermore, air is typically provided at a limited pressure - for example, close to atmospheric pressure - and thus has limited thermal transfer capacity, even at high flow rates. In addition, air contains large proportions of oxygen, which is highly reactive at high temperatures, and this is another factor that tends to require turbine blade metallurgy to be limited to materials highly resistant to oxidation, such as super alloys. Thus, despite the use of advanced materials and cooling, the blades of gas turbines are still plagued by oxidative and, in some cases, steam degradation.
[0004] Even though fossil fuel sources are in exhaustion, vast reserves of coal still persist, which can be used in energy production, but the combustion of these fossil fuels results not only in pollution, but also in particulate materials, which can cause damage to components of energy production systems, particularly turbine blades. This damage originates particularly from particles in the combustion product streams, which collide with turbine blades at high speeds - for example, up to and above 600 mph (miles per hour) (268 m / s). Previous attempts to mitigate this damage have included requirements for filtration systems, for removing particulate materials from combustion product streams, before passing through the turbine, as well as the use of high-performance materials in blade construction, as mentioned above. These requirements, however, increase the cost of energy production systems. In addition, these requirements increase the complexity of energy production systems and can reduce the efficiency of energy production processes. Consequently, there is a need for an improved gas turbine blade technology that overcomes at least the limitations mentioned above in the art. SUMMARY OF THE INVENTION
[0005] The present invention provides processes, assemblies and systems for the production of energy, which can provide components of greater efficiency and lower cost arising from the control, reduction or elimination of chemical degradation of the turbine blades by air and steam and by mechanical erosion by particulate materials in a combustion product stream. Processes, assemblies and systems may comprise the use of fluid flows at higher pressure and / or turbine blades with a larger total turbine area, which provide a necessary power generation with a substantial reduction in blade speed and temperature . The invention provides, in particular, turbines, which are significantly smaller in at least one dimension and with cooler blades, compared to the turbines used in conventional energy production systems. These turbines can be particularly incorporated into an energy production process or system. For example, the process or system may be one that incorporates the use of a high recycling, high pressure, circulating or operating fluid, such as a circulating CO2 fluid. In addition, the paddle cooling technology can be combined with the blade design, operating pressure and operating speed, to allow the turbine operation to be individualized within a range of temperatures, pressures and speeds, which control, reduce or eliminate the appearance of particle collision or chemical degradation of the turbine blades. In particular, turbine blades can incorporate perspiration protection by passing a transpiration fluid (for example, the recycled operating fluid) through the turbine blades. This perspiration protection can include paddle cooling, depending on the temperature of the transpiration fluid used. Since the turbine blades can rotate at a significantly reduced speed, compared to the turbine blades in conventional energy production systems, the invention can provide a reduction in erosion, a longer blade life, and a reduction in requirements mechanical resistance of the blades. In addition, inventive turbines can operate at higher efficiency and lower temperatures, resulting in lower operating costs, longer service life and lower fuel consumption.
[0006] In a particular embodiment, an energy generation process is provided. The process may include: introducing a fuel, O2 and a circulating CO2 fluid into a combustor; burning the fuel to provide the combustion product stream comprising including the circulating CO2 fluid and a particulate material content, the combustion product stream flowing at a defined speed; and expanding the combustion product stream through a turbine, comprising several turbine blades, to generate energy and discharge a turbine discharge stream, the turbine being operated so that the turbine blades rotate at a blade speed of less than about 500 mph (223 m / s).
[0007] The process may further comprise: passing the turbine discharge stream through a filter, configured to remove substantially all of the particulate material contained in the turbine discharge stream and forming a filtered turbine discharge stream. The process may also comprise: passing the filtered turbine discharge stream through a heat exchanger, to provide a cooled turbine discharge stream; treating the cooled turbine discharge stream to extract one or more components from the turbine discharge stream; and passing the treated turbine discharge stream back through the heat exchanger, to provide a heated, recycled circulating fluid stream. The process may further comprise: directing at least a portion of the heated, recycled circulating fluid stream to the combustion. Furthermore, the process may comprise: directing at least a portion of the heated, recycled circulating fluid stream to the turbine. Also, the process may comprise: directing at least a portion of the heated, recycled circulating fluid stream to a cleaning material unit, in which the heated, recycled circulating fluid stream is combined with a cleaning material, to form a stream cleaning material, the cleaning material in the cleaning material stream being configured to remove deposits on the turbine blades from the particulate material content present in the combustion product stream.
[0008] The cleaning material stream can be introduced directly into the turbine. Furthermore, the stream of cleaning material can be combined with the stream of combustion product to form a stream of combustion product and combined cleaning material, which can be directed to the turbine. The circulating fluid can comprise CO2, which can be provided in a supercritical state. In addition, the process may include: combining the filtered turbine discharge stream with a particulate solid fuel, to form additional fuel in the form of a paste; and introducing the additional fuel to the combustor. Also, the process may include using at least part of the circulating fluid, which is recycled as a transpiration fluid. The use of circulating fluid, which is recycled as the transpiration fluid, can comprise: transpiring the transpiration fluid to an external surface of the turbine blades. The transpiration of the transpiration fluid to the outer surface of the turbine blades may comprise transpiring the transpiration fluid through a porous sintered material.
[0009] In another embodiment, an energy generation system is provided. The power generation system can comprise: a combustor configured to receive a fuel, O2 and a circulating fluid, and having at least one combustion stage, which burns the fuel and provides a stream of combustion product including the circulating fluid and a particulate material content; a turbine in fluid communication with the combustion, the turbine having an inlet to receive the combustion product stream, an outlet to release a turbine discharge stream, and several turbine blades of sufficient size, so that the turbine operates at a paddle speed of less than about 500 mph (223 m / s); and a filter to produce a filtered turbine discharge stream.
[0010] The power generation system can also comprise a heat exchanger, in fluid communication with the filter and configured to receive the filtered turbine discharge current. The power generation system may also comprise a cleaning material unit in fluid communication with the heat exchanger, the cleaning material unit being configured to combine a cleaning material with a fluid stream received from the heat exchanger, for form a stream of cleaning material. The power generation system may additionally include a flow combiner bypass, configured to combine the stream of cleaning material with the stream of combustion product, to form a stream of combustion product and combined cleaning material; and directing the stream of combustion product and cleaning material to the turbine.
[0011] The blades can comprise a porous sintered material, and the porous sintered material can be configured to direct a transpiration fluid to an external surface of the blades. The porous sintered material can define the entire outer surface of the blades. Further, the turbine may comprise a rotor, and the rotor may comprise the porous sintered material, and the porous sintered material may be configured to direct the transpiration fluid to an external surface of the rotor.
[0012] In another embodiment, an energy generation process is provided. The process may include: introducing a fuel, O2 and a circulating CO2 fluid into a combustor; burning the fuel to provide the combustion product stream comprising CO2; expanding the combustion product stream through a turbine to generate energy and discharging a turbine discharge stream; processing the turbine discharge stream to recycle at least a portion of the circulating CO2 fluid to the combustor; remove part of the circulating CO2 fluid, which is recycled; and use the recycled CO2 circulating fluid as a sweating fluid.
[0013] The use of recycled CO2 circulating fluid as the transpiration fluid may comprise transpiring the recycled CO2 circulating fluid in the turbine. The use of the recycled CO2 circulating fluid as the sweating fluid may comprise transpiring the recycled CO2 circulating fluid in the combustor. The process may further comprise directing the combustion product stream from the combustor, through a conduit, to the turbine, and using the recycled CO2 circulating fluid as the transpiration fluid can comprise transpiring the recycled CO2 circulating fluid in the conduit. The process may further comprise conditioning the recycled CO2 circulating fluid to a temperature, which is below a temperature of the combustion product stream. The process may additionally include conditioning the recycled CO2 circulating fluid to a temperature, which is substantially equal to a temperature of the combustion product stream. Also, the process may include conditioning the recycled CO2 circulating fluid to a temperature, which is greater than a temperature of the combustion product stream.
[0014] In another embodiment, an energy generation system is provided. The system may comprise: a combustor configured to receive a fuel, O2 and a CO2 circulating fluid stream, and having at least one combustion stage, which burns the fuel in the presence of the CO2 circulating fluid stream, in order to provide a combustion product stream comprising CO2; a turbine in fluid communication with the combustion, the turbine having an input for receiving the combustion product stream, an output for releasing a turbine discharge stream comprising CO2, and several turbine blades, wherein the product stream of combustion acts on the turbine blades to turn the turbine and generate energy; and one or more components configured to process the turbine discharge stream to form a recycled CO2 circulating fluid stream, wherein one or more components of the system are configured to use a portion of the recycled CO2 circulating fluid stream as a perspiration fluid.
[0015] The one or more components configured to process the turbine discharge stream, to form a circulating fluid stream of recycled CO2, may comprise a filter, a heat exchanger, a separator, and / or a compressor. The one or more components configured to use the recycled CO2 circulating fluid stream part, such as the transpiration fluid, may comprise a porous sintered material, configured to receive the transpiration fluid through it. The turbine blades can have a blade height less than about 0.275 m. The turbine may comprise less than 2,000 of the turbine blades. A ratio of a turbine length to an average blade diameter can be greater than 4.
[0016] In another embodiment, a turbine assembly is provided. The assembly may comprise several components including: a housing defining: an input configured to receive a stream of combustion product; and an exit. The components can also comprise: a rotor positioned in the housing; and several blades extending from the rotor, wherein one or more components comprise a porous sintered material, the porous sintered material configured to guide a transpiration fluid through it.
[0017] The porous sintered material can define the entire external surface of the blades. The housing can comprise the porous sintered material, and the porous sintered material is configured to guide the transpiration fluid to an internal surface of the housing. The rotor can comprise the porous sintered material, and the porous sintered material can be configured to guide the transpiration fluid to an external surface of the rotor. The rotor may comprise an annular flow diverter, configured to deflect the combustion product stream around the rotor. The assembly may further comprise an inlet conduit, coupled to the housing inlet and configured to engage an outlet of a combustion assembly and receive the stream of combustion product from it, and the inlet conduit may comprise the porous sintered material, and the porous sintered material is configured to guide the transpiration fluid to an internal surface of the inlet conduit. The housing inlet can be configured to be directly coupled to an outlet of a combustion unit. The housing inlet can be configured to receive the combustion product stream from several combustors, arranged radially with respect to a large axis defined by the rotor.
[0018] The blades can comprise the porous sintered material, the porous sintered material can be configured to guide the transpiration fluid to an external surface of the blades. The blades can further comprise at least one reinforcement element. The reinforcement element may comprise a rod, which extends through the porous sintered material on all blades. The reinforcement element can comprise a core, and the porous sintered material can extend around the core. The core can define one or more channels, configured to receive the transpiration fluid and orient it towards the porous sintered material. One or more channels can be defined in the blades, and in which the channels can be configured to receive the transpiration fluid and orient it to the porous sintered material. All blades can extend from a leading edge to a trailing edge, and the blades can be configured to define a flow of perspiration fluid at the leading edge, which is greater than a flow of perspiration fluid at the trailing edge. . All paddles can define a sweat fluid inlet area at the leading edge, which is larger than a sweat fluid inlet area at the trailing edge. All blades can define a wall thickness, which is greater at the leading edge than the trailing edge. All blades can extend from a root in the rotor to a tip, and the porous sintered material can define a porosity, which varies between the root and the tip. The porosity of the porous sintered material can be configured to define a flow of perspiration fluid at the tip, which is greater than a flow of perspiration fluid at the root. The porosity of the porous sintered material can be configured to define a flow of the transpiration fluid at the tip, which is substantially equal to the flow of the transpiration fluid at the root. The porous sintered material can define several layers, where the porosity of the layers increases from root to tip. All blades can, respectively, define an integral structure, comprising several internal ribs.
[0019] The components of the turbine assembly can also comprise several stators, in which the stators comprise the porous sintered material, and the porous sintered material can be configured to guide the transpiration fluid to an external surface of the stators. The turbine assembly may further comprise one or more seals, in which one or more of the components are configured to guide the transpiration fluid to the seals. The seals may comprise the porous sintered material.
[0020] In another embodiment, a turbine assembly is provided. The turbine assembly may further comprise a housing defining: an inlet configured to receive a stream of combustion product; and an exit. The assembly can also comprise: a rotor positioned in the housing; and several blades extending from the rotor, wherein a ratio of a length of the turbine assembly to an average diameter of the blades is greater than about 4.
[0021] The turbine blades can be less than about 0.275 m high. The turbine assembly can comprise less than 2,000 of the blades. The blades can be protected from perspiration. Furthermore, the blades comprise a porous sintered material, configured to direct a transpiration fluid to an external surface of the blades.
[0022] Other aspects and advantages of the present invention will be evident from what is presented below. BRIEF DESCRIPTION OF THE FIGURES
[0023] The invention having been described in general terms, reference will be made to the attached figures, in which:
[0024] Figure 1 provides a flow chart of a combustion cycle and a system according to an exemplary embodiment;
[0025] Figure 2 provides a flowchart of a combustion cycle and of a system according to another exemplary embodiment;
[0026] Figure 3 provides a sectional view through a combustor, according to an exemplary embodiment;
[0027] Figure 4 provides a sectional view through a turbine including an intake duct, according to an exemplary embodiment;
[0028] Figure 5 provides a longitudinal sectional view through a turbine and several combustors arranged radially, according to an exemplary embodiment;
[0029] Figure 6 provides a side sectional view through the turbine and combustion system of Figure 5;
[0030] Figure 7 provides a side sectional view including a core, according to an exemplary embodiment;
[0031] Figure 8 provides a partial sectional view through an inlet conduit, comprising first and second layers, according to an exemplary embodiment;
[0032] Figure 9 provides a partial sectional view through an inlet conduit, comprising four layers, according to an exemplary embodiment;
[0033] Figure 10 provides a sectional view between the leading and trailing edges of a turbine blade, comprising reinforcement rods, and channels configured to receive a transpiration fluid, according to an exemplary embodiment;
[0034] Figure 11 illustrates a sectional view between a leading edge and a trailing edge of a turbine blade, including integral internal ribs defining channels, configured to receive a transpiration fluid, according to an exemplary embodiment;
[0035] Figure 12 illustrates a sectional view between the tip and base elements of the turbine blade of Figure 11;
[0036] Figure 13 illustrates a perspective view of the turbine blade of Figure 11;
[0037] Figure 14 illustrates a sectional view between a leading edge and a trailing edge of a turbine blade, defining different thicknesses of material between the leading and trailing edges, according to an exemplary embodiment;
[0038] Figure 15A illustrates a partial sectional view between the roots and tips of a turbine blade, including layers of material defining different porosities between the tips and roots, according to an exemplary embodiment;
[0039] Figure 15B illustrates a partial sectional view between the roots and tips of a turbine blade, defining a porosity gradient between the roots and tips, according to an exemplary embodiment;
[0040] Figure 16 illustrates a particle trajectory calculated for a particle in a turbine, according to an exemplary embodiment;
[0041] Figure 17 provides a graphic illustration of a radial displacement distance of particulate material in a combustion product flow in a combustion, as a function of the axial displacement distance, according to an exemplary embodiment;
[0042] Figure 18 illustrates a longitudinal cross section of a conventional turbine for use in a conventional natural gas power plant; and
[0043] Figure 19 illustrates a longitudinal cross section of a turbine, according to exemplary embodiments, which is generally smaller in size than a conventional turbine. DETAILED DESCRIPTION
[0044] The present invention will be described in more detail below, with reference to various embodiments. Such embodiments are provided so that this description is comprehensive and complete and fully transmits the scope of the invention to those skilled in the art. In fact, the invention can be represented in many different ways and should not be considered as limited to the embodiments presented in this specification; instead, such embodiments are provided so that that description meets the applicable legal requirements. As used in the specification, and in the attached embodiments, the singular forms "o", "a", "one" and "one" include the associated plurals, unless the context clearly indicates otherwise.
[0045] The present invention refers, in one embodiment, to designs of turbine blades and processes for their use, which can reduce or even eliminate the erosion of turbine blades arising from chemical degradation by air or steam, or by collision of particles. The invention also provides energy production systems and processes, which can provide high-efficiency operation, while reducing or even eliminating the erosion of turbine blades from particulate material in a combustion product stream, without the prior filtration requirement. the passage through the turbine. The reduction and / or elimination of blade erosion can simplify energy production systems and increase possible feedback, as it allows turbines to process a combustion product stream with a higher total concentration of particulate material, and is, thus, beneficial in combustion processes using feedback, such as coal, which includes a relatively high concentration of particulate material in the combustion product.
[0046] The terms "particulate materials" and "particles" (including these terms in singular form), used in relation to the components of the combustion product stream, specifically cover the solid and liquid materials present in the combustion product stream , in a relatively small unit size, typically understood to be particle characteristics, specifically in relation to the overall volume of the combustion product stream. In some embodiments, the particles or particulate materials can comprise any material in the combustion product stream that is in a non-gaseous state. Liquid particulate materials can encompass materials that are liquid at the temperature of the combustion product stream, but which are solid at a temperature, which is below the temperature of the combustion product stream, such as at least 10 ° C, at least 15 ° C, at least 20 ° C, at least 30 ° C, at least 50 ° C, or at least 100 ° C below the temperature of the combustion product stream. These liquid particulate materials have a freezing point, which is at least room temperature, at least about 40 ° C, at least about 50 ° C, at least about 60 ° C, at least about 80 ° C, at least about 100 ° C, or at least about 200 ° C. In specific embodiments, liquid particles can have a freezing point falling within any combination of the temperatures listed above (for example, within the range that is at least 10% below the temperature of the combustion product stream and at least the ambient temperature ).
[0047] In particular embodiments, it can be seen in the present description that the impact damage of particles on turbine blades is related to the speed of the blades. In particular, a damage ratio from particle impact can change approximately with the blade speed cube relative to the particle speed. In this regard, the standard alternating current frequency used in the United States of America is 60 Hz. Furthermore, power generation systems typically operate synchronous alternating current generators, which operate at 1,800 rpm (30 x 60 Hz) or at 3,600 rpm (60 x 60 Hz), although it should be understood that the turbines can rotate within other rpm ranges (revolutions per minute). In this regard, other countries may employ different frequencies of standard alternating current. For example, in the United Kingdom it operates at a frequency of 50 Hz. Furthermore, generator systems can employ permanent magnet direct current generators at any speed, so that direct current is converted into alternating current having a desired frequency. . Consequently, it should be understood that the frequencies discussed in this specification are presented for example purposes only.
[0048] However, known gas turbines used in energy production systems and processes, including synchronous alternating current generators, typically operate at blade speeds of 600 mph (268 m / s) or more. At typical blade speeds on existing gas and steam turbines, the presence of very fine particulate material in a combustion product stream can cause blade erosion. The present description, however, recognized the ability to overcome the erosion of the blades by changes in the structure of the blades and in the operation, which provide lower speeds of the blades. In specific embodiments, the speed of the blades according to the present invention can be from about 20 m / s to about 340 m / s at the tip of the blade. More specifically, the speed of the blades can be below 200 m / s, below 100 m / s or from about 50 m / s to about 75 m / s. In one embodiment, the invention can provide a turbine operation at blade speed, which is about 3 times less than typical (ie, 200 mph - 89 m / s), which can result in a decrease in blade erosion rate equal to or greater than 27 times. In one embodiment, a paddle speed of 150 mph (67 m / s) - that is, a four-fold decrease in typical paddle speeds - can provide an approximately 64-fold decrease in paddle damage rate.
[0049] The ability to operate the turbine in a power generation system at a lower speed can arise from several factors, which can be represented singularly or in multiple combinations. For example, turbine blades can be designed with dimensions that can allow the speed of the blades to be slowed to a speed at which the collision of particles no longer causes erosion of the turbine blades. More specifically, the operational speed of the blades can be reduced below the critical speed, at which erosion occurs. In this respect, the speed of the blades, at any point in a blade, is provided by the following formula:
[0050] v = (rpm / 60) * 2 * π * r (formula 1)
[0051] where:
[0052] v = speed of the blades (m / s);
[0053] rpm = blade speed per minute;
[0054] π = pi; and
[0055] r = distance (m) between a rotor center and a point on the blade, at which the speed of the blades will be determined (for example, radius).
[0056] Note also that the speed of the blades at the tip of a blade is provided by the following formula:
[0057] Vt = (rpm / 60) * 2 * π * (a + b) (formula 2)
[0058] where:
[0059] v = speed of the blades (m / s);
[0060] rpm = blade speed per minute;
[0061] π = pi;
[0062] a = radius (m) of the rotor in the blade; and
[0063] b = height of the blade (m).
[0064] In this way, the maximum blade speed for all blades can be reduced by decreasing the distance in which the blades extend from the center of the rotor. As discussed below, the use of turbines having blades extending at relatively smaller radii may be permitted by employing a supercritical fluid, having relatively high fluid density and pressure, at a moderate flow rate in the turbine of the present invention. In addition, the use of a high density operating fluid in the turbine can provide a significantly reduced turbine blade temperature by improving the transpiration capacity to cool the blades.
[0065] The height of the blade (that is, the distance from a root on the outer surface of the shaft (for example, rotor) of the turbine to the tip of the turbine) is preferably less than about 0.275 m. In specific embodiments, the average blade height can be about 0.05 m to about 0.25 m, about 0.075 m to about 0.225 m, about 0.1 m to about 0.2 m, or about 0.125 about 0.175 m. In specific embodiments, the effective blade heights can vary from the turbine inlet to the turbine outlet. For example, the height of the blade at the entrance may be less than the average and increase in the direction of the exit, so that the height of the blade at the exit is greater than the average. The average blade width can be about 0.025 m to about 0.125 m, about 0.04 m to about 0.11 m, about 0.05 m to about 0.1 mm, or about 0.06 m to about 0.09 m. In other embodiments, the height and width of the blades can be of other dimensions, which provide the operation at the speed described in this specification.
[0066] Turbines and inventive operational processes can also be characterized by global turbine dimensions. For example, a turbine according to the invention can have an overall length of less than about 11 mm, less than about 10 m or less than about 9 m. In other embodiments, the overall length of the turbine can be about 6 m to about 10 m, about 6.5 m to about 9.5 m, about 7 m to about 9 m, or about 7.5 m about 8.5 m. A turbine according to the invention can have an average diameter of less than about 3.5 m, less than about 3 m, or less than about 2.5 m. In other embodiments, the average diameter of the turbine can be about 0.25 m to about 3 m, about 0.5 m to about 2 m, or about 0.5 m to about 1.5 m. The ratio of the length of the turbine to the average diameter of the turbine (i.e., the diameter of the turbine blades) can be greater than about 3.5, greater than about 4, more than about 4.5 or greater than about 5. In specific embodiments, the ratio of the length of the turbine to the average diameter of the turbine can be about 3.5 to about 7.5, about 4 to about 7, about 4.5 at about 6.5, or about 5 to about 6. The reasons mentioned above may refer, specifically, to the total length of the turbine. In some embodiments, the total length may refer to the length of the housing from inlet to outlet. In certain embodiments, the total length can refer to the distance from the housing, from the turbine blade immediately adjacent to the turbine blade inlet immediately adjacent to the outlet.
[0067] The turbines and inventive operational processes can also be characterized by an average blade radius (center of the rotor at the tip of the turbine blade). Preferably, the turbines operate with an average turbine radius of less than about 1.2 m, less than about 1.1 m, less than about 1 m, less than about 0.9 m, less than about 0.8 m, less than about 0.7, or less than about 0.6 m. The turbine blade radius can be specifically about 0.25 m to about 1 m, about 0.275 m to about 0.8 m, about 0.3 m to about 0.7 m, about 0.325 m to about 0.6 m, about 0.35 m about 0.5 m, or about 0.375 m to about 0.475 m.
[0068] In certain embodiments, a useful turbine according to the invention may have a total number of turbine blades, which is significantly less than that present in typical gas turbine systems. Specifically, inventive turbines can have less than about 3,000 blades, less than about 2,500 blades, or less than about 2,000 blades. In other embodiments, the number of blades in a turbine can be about 500 to about 2,500, about 750 to about 2,250, about 1,000 to about 2,000, or about 1,250 to about 1,750.
[0069] In some embodiments, the turbines according to the invention can provide particularly high efficiency energy production with lower blade speed per operation at significantly increased inlet pressure, and / or significantly higher outlet pressure, and / or a significantly greater pressure drop from inlet to outlet, compared to typical gas turbine power generation systems. In specific embodiments, the turbine can be operated at an inlet pressure of at least about 2.5 MPa (25 bar), at least about 5 MPa (50 bar), at least about 10 MPa (100 bar), at least about 15 MPa (150 bar), at least about 20 MPa (200 bar), or at least about 25 MPa (250 bar). In other embodiments, the inlet pressure can be about 5 MPa (50 bar) to about 50 MPa (500 bar), about 10 MPa (100 bar) to about 45 MPa (450 bar), about 15 MPa (150 bar) at about 40 MPa (400 bar), or about 20 MPa (20 bar) at about 35 MPa (350 bar).
[0070] In other embodiments, the turbine can be operated with an outlet pressure of at least about 0.5 MPa (5 bar), at least about 1 MPa (10 bar), at least about 1.5 MPa (15 bar), at least about 2 MPa (20 bar), or at least about 2.5 MPa (25 bar). The outlet pressure can be about 1 MPa (10 bar) to about 5 MPa (50 bar), about 1.5 MPa (15 bar) to about 4.5 MPa (45 bar), about 2 MPa (20 bar) at about 4 MPa (40 bar), or about 2.5 MPa (25 bar) at about 3.5 MPa (35 bar).
[0071] In other embodiments, the ratio of turbine inlet pressure to turbine outlet pressure can be at least about 6, at least about 7, at least about 8, at least about 9, or at least minus about 10. In specific embodiments, the ratio of turbine inlet pressure to turbine outlet pressure can be at least about 6 to about 15, about 7 to about 14, about 8 to about 12 , or about 9 to about 11.
[0072] In more other embodiments, the turbines according to the invention can be operated in a power generation system at a significantly increased flow density, in relation to the operation of turbines in typical energy production systems. For example, inventive turbines can be operated at a flow density of at least about 20 kg / m3, at least about 50 kg / m3, at least about 100 kg / m3, at least about 150 kg / m3 at least about 200 kg / m3, or at least about 300 kg / m3, at least about 400 kg / m3, at least about 500 kg / m3, or at least about 600 kg / m3.
[0073] Compared to the turbines according to the present invention, existing gas turbine compressors can operate with outlet pressures from about 0.1 MPa (1 bar) to about 1.5 MPa (15 bar) , with gas densities in the compressor section ranging from 1 kg / m3 to about 15 kg / m3 (considering heating by adiabatic compression). Erosion and other problems may not be serious for the compressor, due to the relatively low temperatures on it. However, in the hot section, the temperature of the gas can range from a peak of approximately 1,727 ° C to about 527 ° C. The density of the gas in the hot section can range from a rise of about 5 kg / m3 to a drop of about 0.5 kg / m3. Thus, conditions within existing turbines can vary considerably from those within turbines, in accordance with the present invention.
[0074] The use of higher pressures at lower flows and higher temperatures can increase the torque on the turbine blades. Consequently, the turbine can include items configured to reduce the torque applied to the blades. In particular, the turbine may include a greater number of blades, discs and / or stages than conventional turbines, which distribute the torque between them, to reduce the torque applied to the individual blades. Further, the blades can set an angle of attack configured to exert less force and torque on the blades. In particular, the blades can set a smaller angle to the flow through the turbine, which induces less drag and increases the lift-to-drag ratio. Consequently, these items can reduce the torque exerted on all blades, so that they can be formed from less resistant and relatively cheaper materials.
[0075] In some embodiments, blade erosion can also be controlled, reduced or eliminated by combining any of the characteristics described above with one or more blade cooling processes. Any turbine blade cooling process can be combined with the present invention, including transpiration blade cooling, as described more fully below. In this regard, transpiration cooling can be used to cool any of the various components of the turbine, combustion and related devices described in this specification. With particular regard to the turbine, the housing, the stators (for example, the stator blades), the seals, the blades (for example, the turbine blades), the rotor and various other internal components can be cooled by transpiration by, for example, the use of porous materials described in this specification. In that respect, the stators can comprise the porous sintered material, and the porous sintered material can be configured to direct the transpiration fluid to an external surface of the stators. In addition, one or more of the components of the turbine assembly can be configured to direct the transpiration fluid to the seals. The seals may comprise the porous sintered material in some embodiments. Exemplary embodiments of seals and stators, which can be cooled by perspiration, according to the embodiments of the invention, are described in the publication of US patent application 2009/0142187, which is incorporated by reference in its entirety in this report descriptive. However, several other embodiments of turbine components, combustors and related apparatus can also be cooled by perspiration according to the present invention.
[0076] Furthermore, the perspiration cooling techniques described in this specification can provide improved cooling relative to the existing perspiration cooling techniques. Current paddle cooling is typically conducted with bleed air from the turbine compressor. The air has a limited thermal capacity, due to its relatively low density (for example, 0.5 - 5 kg / m3), established by the relatively low operating pressure of the hot section of the turbine in the existing turbines, as described above. This limits thermal transfer rates. In comparison, as discussed below, the present invention provides transpiration cooling by the use of CO2, which can provide improved thermal transfer.
[0077] The thermal transfer rates for the existing embodiments of the turbines are also limited by the relatively large tension imposed on the turbine blades due to the long length of the blades, resulting in high centrifugal forces during their rotation. The cooling passages in the existing turbines must therefore be kept relatively small and must not define more than a relatively small fraction of the total cross-sectional area, to limit the reduction in longitudinal mechanical strength of the blades caused by the cooling passages.
[0078] The inventive turbines are particularly useful in energy production systems and processes, because the turbines not only provide less blade erosion, but can also significantly reduce the total cost of the turbines. In specific embodiments, the total cost of the turbines, compared to the turbines used in typical energy production systems, can be reduced by at least 20%, at least 30%, at least 40%, at least 50%, at least 60 %, at least 70%, or at least 75%, without any significant loss in electrical power output (ie, loss of less than 5%, less than 4%, less than 3%, less than 2%, less than 1 %, or less than 0.8%). Cost reductions can occur by avoiding the need for super alloys and / or other expensive materials in the blades, due, for example, to a reduction in the centrifugal forces applied to them. Furthermore, reductions in energy output can be minimized despite lower speeds of rotation by employing high turbine inlet temperatures, as well as high operating pressures in relation to existing turbine embodiments.
[0079] In specific embodiments, the present invention can comprise systems and processes for energy production, which can incorporate the present designs and operational modes of turbine blades. For example, inventive systems and processes provide energy production using a high efficiency combustor (such as a perspiration cooled combustor), optionally with an associated circulating fluid (such as a CO2 circulating fluid). Specifically, the use of a high-pressure circulating fluid (or operating fluid), which has a high CO2 recycling rate, provides the ability to direct a portion of the circulating CO2 fluid to the turbine blades for transpiration cooling.
[0080] The combination of transpiration cooling with the blade designs and operating modes of the present invention can be particularly useful, since erosion can be a function of the temperature of the turbine blade and the composition of the turbine blade. The combination of turbine blade design and operation with blade operating temperature can provide a wide range of possible blade operation speeds and blade operating temperatures, where blade erosion can be controlled, reduced or eliminated. At lower blade temperatures, erosion is less, and the speed of the blade, at which erosion begins, can be greater. The ability to select operating conditions is beneficial in that it can allow the use of metal alloys, which can resist erosion at higher blade speeds, but which would not be available for use at higher operating temperatures. In this respect, at lower temperatures, steels with high tensile strength are relatively immune to impact damage. As an example, homogeneous laminated armor, used in military vehicles, is not damaged by solid steel bullets traveling at speeds of up to 400 mph (179 m / s).
[0081] In other embodiments, however, as described more fully below, perspiration may promote protection of the blades by preventing solidification of the components of the combustion product stream (e.g., liquid ash). In these embodiments, transpiration cooling can be defined as cooling the blades (and / or other components) to a temperature below the temperature of the combustion product stream. More particularly, this cooling can be configured to have a lower limit, which is greater than the temperature at which a component of the combustion product stream (for example, liquid ash) will freeze (or solidify), and thereby , be deposited on the turbine blades. For example, the softening of the ash can start at 590 ° C, and the melting can occur at 870 ° C. Without transpiration cooling, the turbine will not need to operate much below 590 ° C, to prevent the accumulation of ash on the blades, which is too low for efficient operation. With transpiration protection, the turbine can operate above 870 ° C, in which the ash is liquid, but the liquid droplets do not touch or stick to the surface, because of the perspiration vapor layer covering substantially all surfaces that are internal to the turbine, and thus subject to contact with components of a stream flowing through the turbine (for example, the internal surface of the turbine housing, the external surfaces of the turbine blades within the turbine, etc.). In this way, perspiration protection can reduce or eliminate not only degradation, due to mechanical erosion by particle collision, but also chemical degradation, by keeping the blades cooler, and by replacing air or air / steam, such as refrigerant, with CO2, like the refrigerant, in the form of a perspiration fluid.
[0082] In some embodiments, it may be useful for the turbines to be operated at blade speeds, which are relative to the speed of the combustion product flow. In such embodiments, it may be particularly beneficial that the flow rate is significantly less than the flow rates in typical combustion processes. For example, the flow speed according to the invention can be less than about 400 mph (179 m / s), less than about 350 mph (156 m / s), less than about 300 mph (134 m / s) s), less than about 250 mph (112 m / s), less than about 200 mph (89 m / s), less than about 150 mph (67 m / s), or less than about 100 mph ( 45 m / s). The ratio of the speed of the blade to the flow rate is preferably greater than 1, greater than 1.5, greater than 2, greater than 2.5, or greater than 3. Specifically, the ratio of the speed of the tip of the shovel for the flow rate can be about 1 to about 5, about 1.5 to about 4.75, about 1.75 to about 4.5, about 2 to about 4.25, or about 2.5 to about 4.
[0083] As a result of erosion, turbines may experience degradation in performance over time (for example, due to lower efficiency and / or energy output). For example, a conventional turbine can experience operational degradation of 10% energy loss over a period of two to three years. A revision to repair the turbine can cost approximately 50% of the cost of purchasing the turbine. Consequently, over a 20-year life span, existing turbines can be overhauled a total of eight times, which can cost a total of 4 times the initial purchase price of the turbine.
[0084] This degradation may be due to erosion caused by the residual dust particles that pass through an air filtration system, positioned between the combustion and the turbine. Increasing the efficiency of removing particulate matter from filters may not be a viable option, as this can limit airflow and reduce the efficiency of the turbine. In this way, the turbines of the present invention can provide significant cost savings by minimizing or eliminating the need for overhauls, by minimizing or eliminating erosion damage. In this respect, the dissipation rate of the impact energy, associated with the collision between the particles and the blades, is approximately proportional to the cube of the relative speed between them. In this respect, the erosion of turbine blades tends to be approximately proportional to the rate of dissipation of the impact energy ("Impact Energy"), as illustrated below:
[0085] IP = kV3 / X (formula 3)
[0086] where:
[0087] IP = impact energy;
[0088] k = a variable factor based on particulate material, blade material, ambient temperature and impact angle;
[0089] V = relative speed between the turbine blades and the particles; and
[0090] X = characteristic length of the impact interaction.
[0091] By reducing the speed of the blades and providing protection by perspiration, impacts can be minimized or reduced below a threshold, in which erosion occurs, and chemical damage can also be reduced or eliminated. Consequently, the costs associated with revisions, due to erosion, can be reduced or eliminated, and thus, the turbine embodiments provided in this specification can provide significant cost savings. Furthermore, as mentioned above, by eliminating the need for the use of expensive super alloys, the turbines according to the present invention can be relatively cheaper than existing turbines.
[0092] In several known embodiments of power plants, efficiency is critically dependent on the turbine inlet temperatures. For example, intense work has been done at great cost to obtain turbine technology, for inlet temperatures as high as about 1,350 ° C. The higher the inlet temperature of the turbine, the greater the efficiency of the plant, but also the more expensive the turbine becomes, and potentially with a shorter service life. Because of the relatively high temperature of the combustion product stream, it may be beneficial for the turbine to be formed of materials capable of withstanding these temperatures. It may also be useful for the turbine to comprise a material that provides good chemical resistance to the type of secondary materials, which may be present in the combustion product stream.
[0093] In certain embodiments, the present invention can provide, in particular, the use of a cooling fluid with the turbine components. As described in more detail below, for example, inventive systems and processes provide energy production through the use of a high-efficiency fuel combustor (for example, a perspiration-cooled combustor) and an associated circulating fluid (such as a circulating fluid CO2). Specifically, a portion of the circulating fluid can be oriented towards the turbine components, particularly the turbine blades, which will be used in cooling the turbine, such as by cooling by transpiration.
[0094] For example, in some embodiments, a part of a circulating CO2 fluid can be removed from the cycle (for example, from a part of the cycle in which the circulating fluid is under conditions useful for a perspiration cooling fluid), and oriented to a turbine for cooling the components, particularly the turbine blades. The paddle cooling fluid can be discharged from holes (or perforations) in the turbine blade and be introduced directly into the turbine flow. Thus, instead of using air as the perspiration cooling fluid (which is limited in its cooling capacity, as described above, and prevented by safety concerns), the processes and systems of the invention provide for the use of very large quantities high pressure CO2, supercritical CO2, and even liquid CO2 as a means of cooling the turbine blade. This is quite useful because it increases the cooling capacity for the turbine blades for great reasons, in relation to the known blade cooling processes. The invention is particularly useful because the circulating CO2 fluid and can be present in the system in very large proportions, which allows a very large amount of cooling fluid to be moved by the turbine blades. This volumetric and / or mass flow of CO2 circulating fluid through the turbine blades not only protects the turbine blades from extreme heat, which is useful for high efficiency energy production processes, but also assists in protecting the turbine blades the corrosive and erosive effects of high temperature gases and unfiltered particulate material, which flow through the turbine through transpiration of the circulating CO2 fluid and throughout the surface of the blade. In one embodiment, transpiration cooling can provide blade temperatures of about 200 ° C to about 700 ° C, despite the significantly higher turbine inlet temperatures described above (for example, 1,350 ° C), which it can, therefore, allow the use of turbine blades comprising relatively cheaper materials than those currently employed, and / or higher turbine inlet temperatures can be employed, which can promote greater efficiency. The preceding perspiration-cooled gas turbine components can be used in any energy production process and system, where high-pressure CO2 (or other fluid that is less corrosive than air or steam, such as N2) can be made available as a circulating fluid with a high recycling ratio.
[0095] In specific embodiments, the use of a circulating CO2 fluid, as a means of cooling the turbine blade, allows the turbine blades to be manufactured from lower cost materials than the known turbine blades used in high efficiency energy production processes, because the use of the CO2 cooling medium prevents the blades in the present invention from being heated to the extreme temperatures of the surrounding combustion product stream and reduces the corrosive and erosive effects of the combustion product stream . For example, according to the present invention, turbine blades can be manufactured from a wide range of high tensile strength steels, or even relatively low cost steels. Likewise, the blades can be made of carbon composites or even materials for low temperatures, such as aluminum. Any material recognized as useful in the art for gas turbine components, even for turbines used in conditions of low temperatures and / or conditions of low erosion or corrosion, can be used to manufacture turbine components according to the present invention.
[0096] Transpiration cooling of turbine blades with a part of a circulating CO2 fluid and, according to the present invention, is still useful because it can facilitate the safe passage of combustion gases containing ash (or other particulate material and / or non-combustible material) by the turbine, without the need for a stage and an intermediate filtration component. This can greatly simplify the design of energy production facilities and expand the types of materials that can be used as the fuel source for combustion.
[0097] The use of a circulating CO2 fluid in transpiration cooling of turbine components, according to the present invention, is advantageous in relation to the thermodynamics of the energy production cycle. Due to the greatly improved cooling capacity of the circulating CO2 fluid in relation to the known transpiration media for turbine blades, it is possible to operate the combustion at higher temperatures, without limiting the thermal tolerance of the turbine. In this way, combustors capable of operating at extremely high temperatures (for example, perspiration cooled combustors) can be operated, in accordance with the present invention, very close to the maximum operating temperatures, since the flow of combustion product can be passed through the CO2-cooled turbine without damaging the turbine components. This increases the potential thermodynamic efficiency of the energy production cycle to approximately 100%.
[0098] Any combination of turbine blade design, global turbine design, and transpiration cooling of the turbine blades can be used in any energy production process, with which the blade life is desirably extended, such as the processes and systems in which combustion results in the formation of particulate matter. In some embodiments, the processes and systems can be particularly those in which a circulating fluid can be used. For example, high pressure CO2 can be made available as a circulating fluid with a high recycling ratio.
[0099] For example, a turbine, as described in this specification, can be used in a process and system in which a circulating CO2 fluid is provided in a combustor, together with a suitable fuel, any necessary oxidizer and any associated materials that can be useful for efficient combustion. These systems and processes can comprise a combustor, which operates at very high temperatures (for example, in the range of about 1,600 ° C to about 3,300 ° C, or even higher), and the presence of the circulating fluid can work to moderate the temperature of a fluid stream leaving the combustion, so that the fluid stream can be used in energy transfer for energy production. Specifically, a combustion product stream can be expanded by at least one turbine to generate energy. The expanded gas stream can be cooled to remove various components from the stream, such as water, and heat the expanded gas stream, which can be used to heat the circulating CO2 fluid. The purified circulating fluid stream can then be pressurized and heated for recycling by the combustor. Exemplary energy production systems and processes, which may incorporate the turbine blade designs of the present invention (with or without the associated blade transpiration cooling), are described in the publication of US patent application 2011/0179799, which is incorporated by reference in this specification in its entirety.
[0100] The incorporation of a turbine according to the invention in a combustion energy cycle is particularly useful in relation to the combustion of fuels, which results in a particulate component. Various types of coal can be, for example, burned in an energy production cycle, to produce a combustion stream, having a content of ash and / or other particulate material. Beneficially, when a turbine according to the invention is incorporated into the combustion cycle, the complete stream of combustion product (ie including the total particulate matter content) can be introduced into the turbine, without the need for a filtration step preliminary. This allows the use of a higher inlet temperature in the turbine, which, in turn, increases the combustion efficiency in relation to the processes requiring filtration of the combustion product, before passing through the turbine. This is possible according to the invention, since the inventive turbines can be subjected to a particle collision without significant erosion. Particulate materials can then be filtered from the stream leaving the turbine.
[0101] An embodiment of a combustion cycle, provided in accordance with the present invention, is illustrated in the flowchart of Figure 1. In the illustrated embodiment, an air separation unit 100 is provided to admit ambient air 10 and discharge an enriched stream in oxygen 120. Oxygen stream 120 may comprise oxygen having a molar purity of at least about 50%, at least about 60%, at least about 70%, at least about 80%, at least about 85 %, at least about 90%, or at least about 95%. The oxygen stream 120 can be supplied by any air separation system / technique known in the art, such as, for example, a cryogenic air separation process, or a high ionic transport membrane oxygen separation process (air) temperature can be implemented. In specific embodiments, an oxygen-rich stream can be produced by operating a separation process, in which oxygen is pressurized in the process by pumping liquid oxygen, which is efficiently heated to room temperature while maintaining refrigeration. This cryogenic pumped oxygen plant can have two air compressors, both of which are operated adiabatically without any intermediate stage cooling. In specific embodiments, it may be useful to include components useful for recovering the heat produced by the air separation unit and transferring the heat to a component of the system presently described, in which heat input may be desirable.
[0102] The cycle illustrated in Figure 1 can be useful for combustion of any fuel source that includes particulate material (eg, ash), as a component of the combustion product. Non-limiting examples of fuels, which are useful according to the invention, include various grades and types of coal, wood, oil, tar sand tar, bitumen, biomass, algae, fuel-grade solid waste, asphalt and used tires. In particular, any solid combustible material can be used in the invention, and these fuels can be particularly ground, shattered or otherwise processed to reduce the particle size, as desired. A fluidizing or filling medium can be added, if necessary, to obtain a suitable shape and satisfy the fluidity requirements for high pressure pumping. For example, with reference to Figure 1, solid fuel 15 can be passed through a grinding apparatus 200, to provide powdered fuel. In other embodiments, solid fuel 15 can be provided in a particular condition to satisfy the need for on-site grinding. In specific embodiments, solid fuel 15 can have an average particle size of about 10 μm to about 500 μm, about 25 μm to about 400 μm, or about 50 μm to about 200 μm. In other embodiments, solid fuel 15 can be described by the fact that more than 50%, 60%, 70%, 80%, 90%, 95% or 99% of the solid fuel particles have an average size of less than about 500 μm, 400 μm, 300 μm, 200 μm or 100 μm.
[0103] Solid fuel 15 can be processed properly to allow injection into a combustion device at sufficient rates and pressures above the pressure inside the combustion chamber. To provide this characteristic, solid fuel 15 can be in the form of a liquid, semi-fluid mass, gel or paste, with fluidity and viscosity suitable for room temperature or elevated temperatures. For example, solid fuel 15 can be provided at a temperature of about 30 ° C to about 500 ° C, about 40 ° C to about 450 ° C, about 50 ° C to about 425 ° C, or about 75 ° C to about 400 ° C. When solid fuel 15 is in a ground, crushed or otherwise processed condition, if the particle size is reduced appropriately, a fluidizing or pasting medium may be additional, as needed, to obtain a suitable shape and satisfy flow requirements for high pressure pumping. As illustrated, in the embodiment of Figure 1, particulate solid fuel 220, produced from solid fuel 15 by the grinding apparatus 200, can be mixed with a fluidizing substance, to provide coal in the form of a paste. In particular, particulate solid fuel 220 is combined in a mixer 250 with a side drag of CO2 562 from a circulating fluid stream of recycled CO2 561. The side drag of CO2 562 can be provided in a high density, supercritical state. In specific embodiments, the CO2 used to form the slurry can have a density of about 450 kg / m3 to about 1,100 kg / m3. More particularly, the side drag of CO2 562 can cooperate with particulate solid fuel 220 to form a slurry 255 having, for example, from about 10% by weight to about 75% by weight, or from about 25% by weight about 55% by weight of particulate coal. In addition, the side drag CO2 562, used to form the slurry 255, can be at a temperature below about 0 ° C, below about -10 ° C, below about -20 ° C, or less than about -30 ° C. In other embodiments, the side drag CO2 562, used to form the slurry, can be at a temperature of about 0 ° C to about -60 ° C, about -19 ° C to about -50 ° C, or about -18 ° C to about -40 ° C. Although the stuffing step is described in terms of using CO2 as a means of stuffing, it should be understood that other means of stuffing can be used.
[0104] Slurry 255 can be transferred from mixer 250, by means of a pump 270, to a combustion apparatus 300. In specific embodiments, combustion apparatus 300 may be a high efficiency combustion capable of substantially combustion fuel, at a relatively high combustion temperature. High temperature combustion can be particularly useful in providing substantially complete combustion of all combustible components of the fuel, and thereby maximize efficiency. In various embodiments, high temperature combustion can mean combustion at a temperature of at least about 1,000 ° C, at least about 1,200 ° C, at least about 1,500 ° C, at least about 2,000 ° C or at least about 3,000 ° C. In other embodiments, combustion at high temperature can mean combustion at a temperature of about 1,000 ° C to about 5,000 ° C, or from about 1,200 ° C to about 3,000 ° C.
[0105] In certain embodiments, the combustion apparatus 300 may be a perspirator cooled by perspiration. An example of a perspiration cooled combustor, which can be used in the invention, is described in the publication of the North American patent application 2010/0300063 and in the publication of the North American patent application 2011/0083435, the descriptions of which are incorporated herein. descriptive report by reference in its entirety. In some embodiments, a perspiration-cooled combustor, useful according to the invention, may include one or more heat exchange zones, one or more cooling fluids, and one or more perspiration fluids.
[0106] The use of a perspiration-cooled combustor according to the present invention is particularly advantageous in relation to fuel combustion relative to the known technique for energy production. For example, the use of perspiration cooling can be useful to prevent corrosion, scale and erosion in the combustion. This also allows the combustion to work in a sufficiently high temperature range to produce a complete or substantially complete combustion of the fuel that is used. These and other advantages are further described in this specification.
[0107] In a particular aspect, a perspiration-cooled combustor, useful according to the invention, may include a combustion chamber, defined at least partially by a transpiration element, in which the transpiration element is at least partially surrounded by a pressure containment element. The combustion chamber may have an inlet and an opposite outlet. The inlet part of the combustion chamber can be configured to receive the fuel containing carbon, to be burned inside the combustion chamber, at a combustion temperature, to form a combustion product. The combustion chamber can also be configured to orient the combustion product towards the outlet part. The transpiration element can be configured to guide a transpiration substance through it, towards the combustion chamber, to cushion the interaction between the combustion product and the transpiration element. In addition, the transpiration substance can be introduced into the combustion chamber to obtain a desired outlet temperature of the combustion product. In particular embodiments, the sweating substance may comprise, at least partially, the circulating fluid. The walls of the combustion chamber can be coated with a layer of porous material, through which the transpiration substance, such as CO2 and / or H2O, is oriented and flows.
[0108] The flow of the transpiration substance through that transpiration layer, and, optionally, additional provisions, can be configured to achieve a desired total outlet fluid outlet temperature of the combustion apparatus 300. In some embodiments, as further described in this specification, this temperature can be in the range of about 500 ° C to about 2,000 ° C. This flow can also serve to cool the transpiration element to a temperature below the maximum permissible operating temperature of the material forming the transpiration element. The perspiration substance can also serve to prevent the collision of any liquid or solid ash materials, or other contaminants, in the fuel, which can corrode, encrust or otherwise damage the walls. In such cases, it may be desirable to use a material for the transpiration element with reasonable thermal conductivity, so that the incident radiant heat can be conducted radially outward by the porous transpiration element, and then be intercepted by convective thermal transfer from the surfaces of the porous layer structure for the fluid passing radially inward through the transpiration layer. This configuration can allow the subsequent part of the stream, guided by the transpiration element, to be heated to a temperature in a desirable range, such as about 500 ° C to about 1,000 ° C, or about 200 ° C to about 700 ° C, while simultaneously maintaining the temperature of the porous transpiration element within the design range of the material used it. Suitable materials for the porous transpiration element may include, for example, porous ceramics, blankets of refractory metal fibers, perforated cylindrical sections, and / or layers of sintered metals or sintered metal powders. A second function of the transpiration element may be to ensure a substantially radially inward flow of transpiration fluid, as well as longitudinally along the combustion, to obtain a good mix between the transpiration fluid stream and the combustion product, while promoting a uniform axial flow along the length of the combustion chamber. A third function of the transpiration element may be to obtain a diluent fluid velocity radially inward, so as to provide damping to, or otherwise intercept, solid and / or liquid ash particles or other contaminants within the combustion products. impact of the perspiration layer surface and cause blockage, erosion, corrosion or other damage. This factor may only be of importance, for example, when combustion of a fuel, such as coal, having a residual inert non-combustible residue. The internal wall of the combustion pressure vessel, surrounding the transpiration element, can also be insulated, to isolate the high temperature transpiration fluid stream inside the combustion.
[0109] In certain embodiments, a mixing arrangement (not shown) can be provided to combine the materials to be introduced into the combustion apparatus 300, prior to such introduction. Specifically, any combination of two or three of the fuel, O2 and circulating fluid (e.g., CO2 circulating fluid) can be mixed in the optional mixing arrangement, prior to introduction into the combustion apparatus 300.
[0110] Fuel 15 introduced into the combustion apparatus 300 (such as slurry stream 255), together with O2 120 and a recycled circulating fluid 503, is burned to provide a stream of combustion product 320. In specific embodiments, the apparatus combustion 300 is a combustion-cooled combustion as described above. The combustion temperature can vary depending on specific process parameters - for example, the type of fuel used, the molar ratio of circulating fluid to carbon in the fuel, as introduced into the combustion, and / or the molar ratio of CO2 to O2 introduced into the combustor. In specific embodiments, the combustion temperature is a temperature as described above in relation to the description of the perspiration cooled by transpiration. In particularly preferred embodiments, combustion temperatures above about 1,000 ° C, as described in the present specification, can be advantageous.
[0111] It may also be useful to control the combustion temperature, so that the stream of combustion product leaving the combustion has a desired temperature. For example, it may be useful for the combustion product stream, exiting the combustion, to have a temperature of at least about 700 ° C, at least about 900 ° C, at least about 1,200 ° C, or at least about 1,600 ° C. In some embodiments, the combustion product stream may have a temperature of about 700 ° C to about 1,600 ° C, or from about 1,000 ° C to about 1,500 ° C.
[0112] Specifically, the pressure of the combustion product stream 320 can be related to the pressure of the circulating fluid, which is introduced into the combustion apparatus 300. In specific embodiments, the pressure of the combustion product stream 320 can be at least about 90% of the pressure of the circulating fluid introduced into the combustion apparatus 300.
[0113] The chemical composition of the combustion product stream 320, leaving the combustion apparatus 300, may vary, depending on the type of fuel used. Significantly, the combustion product stream will comprise the main component of the circulating fluid (e.g., CO2), which will be recycled and reintroduced into the combustion apparatus 300, or other cycles. In other embodiments, the combustion product stream 320 may comprise one or more of water vapor, SO2, SO3, HCl, NO, NO2, Hg, excess O2, N2, Air, non-combustible material and / or other particulate matter, and possibly other contaminants that may be present in the fuel, which is burned. These materials present in the combustion product stream may persist in the CO2 circulating fluid stream and, unless removed, as per the processes described in this specification.
[0114] Advantageously, according to the present invention, the combustion product stream 320 can be oriented to a turbine 400, without the need to first filter out any particulate material in the combustion product stream 320. In turbine 400, the stream combustion product 320 is expanded to generate energy (for example, through a generator 400a, to produce electricity). The turbine 400 can have an inlet to receive the combustion product stream 320 and an outlet to release a turbine discharge stream 410. Although a single turbine 400 is shown in Figure 1, it should be understood that more than a turbine can be used, the multiple turbines being connected in series, or, optionally, separated by one or more other components, such as another combustion component, a compression component, a separator component, or the like.
[0115] The turbine 400 can be, specifically, a turbine having a blade design and / or an overall design, as described otherwise in this specification. Furthermore, the turbine may incorporate transpiration cooling or other cooling technology, as described in this specification. In particular, the turbine design can be one with such low blade speed and particle collision speed, such as to allow the turbine to withstand collision without significant erosion. The transpiration cooling of the turbine can also protect against erosion of particles, by creating a layer of continuous flow barrier of the transpiration fluid, between the surface of the blade and the particulate material passing through the turbine.
[0116] Returning to Figure 1, the exemplary system and cycles further comprise a filter 5, downstream of turbine 400. The turbine discharge stream 410 can be passed through filter 5, to remove particulate materials from it. The placement of filter 5 downstream of turbine 400, instead of upstream of the turbine, is an advantageous feature of the invention, since the combustion product stream 320 can be expanded by the turbine at higher temperature and pressure, when leaving combustion apparatus 300 immediately, and in this way energy production can be maximized. The lower and cooler pressure turbine discharge stream 410 can then be filtered on the filter 5, to remove particulate materials from it as the particulate material stream 7. The filtered turbine discharge stream 420 is thereby provided substantially free of particulate matter, for further processing in the combustion cycle.
[0117] In specific embodiments, filter 5 may preferably comprise a configuration that is effective for removing substantially all particulate material present in the combustion product stream 320. Filter 5 may comprise a cyclone filter and / or a candle filter, in some embodiments, and filtration can occur from about 300 ° C to about 775 ° C in some embodiments. In particular embodiments, the removal of substantially all of the particulate material may comprise the removal of at least 95%, at least 96%, at least 97%, at least 98%, at least 99, at least 99.5%, or at least minus 99.8% by volume of the particulate material present in the combustion product stream. This efficiency of removing particulate material from the filter can be related to the particle size. For example, the mentioned percentage of particles removed may refer to the filter's ability to retain particles having a diameter of at least about 0.1 μm, at least about 0.5 μm, at least about 1 μm, at least about 5 μm, at least about 10 μm, at least about 25 μm, at least about 50 μm, at least about 100 μm, or at least about 500 μm. In one embodiment, the particles produced by combustion can be in the range of about 0.1 μm to about 100 μm, and the filter can be configured to remove substantially all particles above about 1 μm, above about 5 μm, above about 10 μm, above about 15 μm, or above about 20 μm, and reduce the total level of particulate matter to less than about 10 mg / m3, less than about 5 mg / m3, less than about 1 mg / m3, or less than about 0.5 mg / m3.
[0118] In particular embodiments (that is, in which CO2 is used as a circulating fluid), the filtered turbine discharge stream 420 can be passed through a heat exchanger unit 500 (which can be a series of heat exchangers ), to form an unprocessed recycling stream 501. That unprocessed recycling stream 501 can be passed through a cold water heat exchanger 520, to form stream 521, which is passed to a separator 540 for removing secondary components (eg H2O, SO2, SO4, NO2, NO3 and Hg), as a current 542. In specific embodiments, separator 540 may comprise a reactor, which provides contact with sufficient residence times, so that impurity can react with water to form materials (eg acids), which are easily removed. A stream of purified circulating fluid 541, from separator 540, can be passed through a compressor 550, to form stream 551, which can be further cooled with a cold water heat exchanger 560, to provide a circulating CO2 fluid of high density, supercritical 561. In certain embodiments, the purified CO2 circulating fluid 541 can be compressed at a pressure of at least about 7.5 MPa or at least about 8 MPa. A portion of the stream 561 may be withdrawn as the stream 562, for use as the fluidizing medium in the mixer 250, to form the slurry stream 255. The supercritical high density CO2 circulating fluid stream 561 is otherwise , further pressurized in the compressor 570, to form the high density, supercritical, pressurized CO2 circulating fluid stream 571. Part of the CO2 in stream 571 can be removed as stream 572 to a CO2 pipe, or other means of kidnapping. The remainder of the CO2 can proceed as the supercritical, pressurized high-density CO2 circulating fluid stream 573, which can be passed back through the heat exchanger 500 (or a series of heat exchangers), to heat the current. In specific embodiments, the fluid circulates CO2 and can be provided at a density of at least about 200 kg / m3, at least about 300 kg / m3, at least about 500 kg / m3, at least about 750 kg / m3, or at least about 1,000 kg / m3, after unloading the cold water heat exchanger 560 (and before passing through the heat exchanger unit 500 for heating). In other embodiments, the density can be from about 150 kg / m3 to about 1,100 kg / m3. The passage of current 551 through the cold water heat exchanger 560 can cool the circulating CO2 fluid and to a temperature below about 60 ° C, below about 50 ° C, or below about 30 ° C. The circulating CO2 fluid in stream 561, entering the second compressor 570, can be provided at a pressure of at least about 12 MPa. In some embodiments, the stream can be pressurized to a pressure of about 15 MPa to about 50 MPa. Any type of compressor, capable of working under the mentioned temperatures and capable of reaching the described pressures, can be used, such as a high pressure multistage pump.
[0119] The high density, supercritical, pressurized CO2 circulating fluid can leave the heat exchanger 500 as the first current 503, to be provided as the recycled circulating fluid. In some embodiments, the supercritical, pressurized, heated high-density CO2 circulating fluid can leave the heat exchanger 500 as the second recycled circulating fluid stream 504 to be provided as a transpiration fluid for the turbine blades. Preferably, the second recycled circulating fluid stream 504 can be controllable, so that the total mass or volume of circulating fluid in the stream can be increased or decreased, as required, by increasing or decreasing the protection provided by the sweating fluid . Specifically, a system according to the invention can include a flow control means, so that the second stream of recycled circulating fluid 504 can be completely interrupted, when desired. Note that in some embodiments, the recycled circulating fluid (e.g., CO2), provided to the turbine 400, can bypass the heat exchanger 500, before being provided to the turbine. In this respect, the recycled CO2 can be compressed by the compressor 570, and then a part of the circulating fluid stream 517 can bypass the heat exchanger 500 and enter the turbine 400. In this way, the CO2 (or other recycled circulating fluid) can be introduced into the turbine 400, without being heated by the heat exchanger 500. Consequently, CO2 (or other recycled circulating fluid) can be introduced into the turbine, at a temperature that is lower than the temperature of the fluid heated by the heat exchanger. In that regard, CO2 (or other recycled circulating fluid) can be introduced into the turbine at a temperature below about 300 ° C, below about 200 ° C, below about 100 ° C, below about 55 ° C, or less than about 25 ° C, and thus CO2 (or other recycled circulating fluid) can be used to cool turbine 400. To compensate for the addition of relatively cooler circulating fluid in turbine 400, the O2 can travel through heat exchanger 500 to heat O2 and then O2 can be combined with recycled circulating fluid 503, oriented towards combustion 300 to compensate for the loss in efficiency that can occur otherwise. In certain embodiments, the circulating fluid leaving the cold end of the heat exchanger (or the final heat exchanger in the series, when two or more heat exchangers are used) can have a temperature below about 200 ° C, less than about 100 ° C, less than about 75 ° C, or less than about 40 ° C.
[0120] In certain embodiments, it may therefore be useful for the heat exchanger receiving the turbine discharge current to be formed from high performance materials, designed to withstand extreme conditions. For example, the heat exchanger may comprise an INCONEL® alloy or similar material. Preferably, the heat exchanger comprises a material capable of withstanding a consistent operating temperature of at least about 700 ° C, at least about 900 ° C, or at least about 1,200 ° C. It may also be useful for one or more of the heat exchangers to comprise a material, which provides good chemical resistance to the type of secondary materials, which may be present in the combustion product stream. INCONEL® alloys are available from Special Metals Corporation, and some embodiments may include austenitic nickel and chromium based alloys. Suitable heat exchangers may include those available under the HEATRIC® trademark (available from Meggitt USA, Houston, TX).
[0121] As mentioned above, in addition to water, the circulating CO2 fluid may contain other secondary components, such as fuel-derived, combustion-derived and oxygen-derived impurities. These secondary components of the circulating CO2 fluid (often recognized as impurities or contaminants) can all be removed from the cooled CO2 circulating fluid by using appropriate processes (for example, the processes defined in the publication of US patent application 2008/0226515 and in European patent applications EP 1952874 and EP 1953486, which are incorporated in this specification by reference in their entirety). For example, SO2 and SO3 can be converted 100% to sulfuric acid, while> 95% NO and NO2 can be converted to nitric acid. Any excess O2, present in the circulating CO2 fluid, can be separated as an enriched stream for optional recycling to the combustor. Any inert gases (for example, N2 and Ar) can be vented at low pressure into the atmosphere.
[0122] As described above, an energy production cycle incorporating a turbine, which is configured according to the invention, can operate at high efficiency, in part because the combustion product stream (for example, from combustion of a solid fuel, such as coal) can be introduced directly into the turbine, without the need to first filter out the particulate material present in the combustion product stream. In particular, the configurations of the inventive turbine eliminate or greatly reduce the erosion of the blades, caused by the collision of the unburned material. Although the invention provides this valuable protection of the turbine materials, there may still occasionally be a deterioration of the turbine originating from the interaction of the turbine components with the particulate components of the combustion product stream.
[0123] For example, liquid ash grabbing and freezing (or solidifying) on the turbine blades can cause slag formation, loss of efficiency and / or loss of rotor balance. Consequently, in certain embodiments, the present invention provides for the incorporation of specific components in a combustion cycle, to relieve and / or at least partially remove the accumulation of chemical deposits from the turbine components, particularly the turbine blades. Although the accumulation of ash is exemplified in this case, it must be understood that the cleaning provided by the embodiments of the present invention will be expected to be effective in removing, at least partially or completely, any type of deposit on the turbine components, originating from materials present in the combustion product stream, particularly particulate materials. In this way, various types of ash, ash-derived material, and carbon can be removed by the cleaning provided in this case.
[0124] The accumulation of chemical deposits on the turbine components, such as turbine blades, can be prevented by the use of perspiration protection techniques. For example, as seen in Figure 1, the hot recycled operating fluid (for example, CO2) can be removed from the hot end of the heat exchanger 500, like chain 504, and transferred to turbine 400. For example, the operating fluid Hot recycled can be transferred to the turbine rotor by the turbine blades to provide transpiration protection of the turbine blades. In these embodiments, the turbine blades can be drilled if necessary, so that a hot recycled operating fluid leaves the blades along substantially the entire surface of the blades, or at least the advancing surface of the blades, that is, in the direct route of the combustion product stream entering the turbine. In specific embodiments, the largest flow of transpiration fluid out of the blades will be at the advancing edges of the blades.
[0125] The transpiration fluid can be provided at various temperatures. In some embodiments, the transpiration fluid for the turbine may be at a temperature that is within about 10%, within about 8%, within about 5%, or within approximately 2% of the current temperature combustion product entering the turbine. In these embodiments, the temperature of the transpiration fluid for the turbine can be characterized as being substantially similar to the temperature of the combustion product stream entering the turbine. In other embodiments, the turbine-oriented perspiration fluid for perspiration protection can be 15% to about 90% less, about 15% to about 60% less, about 15% to about 50% less , or about 20% to about 40% below the temperature of the combustion product stream entering the turbine. In these embodiments, the temperature of the transpiration fluid for the turbine can be characterized as being substantially below the temperature of the combustion product stream entering the turbine.
[0126] In some embodiments, the use of perspiration fluid with turbine blades can promote multiple functions. For example, transpiration fluid can be effective in protecting the turbine blades, as it can essentially prevent particulate materials in the combustion product stream from actually coming into contact with the blade surface. Instead, the protective barrier, formed by the transpiration fluid, can deflect or otherwise redirect particulate materials around the blades. The hot recycled operating fluid can also function to heat the blades, particularly the surfaces of the blades on the outlet side of the turbine. This additional heating can prevent the paddle surfaces, on the outlet side and / or on the inlet side, from cooling to a temperature at which liquid ash (or other materials that are liquid at the temperature of the combustion product stream and have a freezing point (or solidification) that is lower than the temperature of the combustion product stream, but higher than the ambient temperature) will solidify (i.e., the material's freezing temperature). This prevents liquid particles, which in fact come into contact with the surface of the turbine blade, from freezing (or solidifying), and thus depositing on the surfaces of the blades.
[0127] Perspiration protection can eliminate freezing (or solidification) of particles in some embodiments. In that regard, all ash can be maintained in melting above approximately 870 - 980 ° C in some embodiments. In other embodiments, particle freezing can be reduced in relation to identical cycles and systems, which do not incorporate perspiration protection. As the freezing of particles is reduced but not eliminated, periodic cleaning of the turbine components may be necessary. In specific embodiments, cleaning of turbine components, such as turbine blades, can be done by incorporating cleaning components into a combustion cycle or system.
[0128] The cycle shown in Figure 2 illustrates a system in which the turbine blade cleaning materials can be guided by the turbine to promote cleaning of the turbine blades. Beneficially, cleaning materials can be guided by the turbine, in parallel with the combustion product stream. In this way, cleaning can be done without interrupting the combustion cycle of energy production. In some embodiments, it may be desirable to change one or more of the cycle parameters discussed in this specification, to facilitate the cleaning process (for example, changing the temperature of the combustion product stream, to increase the ratio of recycled fluid to fuel , or similar). In embodiments in which the turbine blade is being protected by perspiration, it may be desirable to interrupt the flow of transpiration fluid, to facilitate contact of the cleaning material with the turbine blades. However, combustion and power generation can continue during the cleaning process.
[0129] With reference to Figure 2, a combustion cycle can proceed substantially as described in relation to Figure 1. In the present embodiments, however, a third stream of recycled circulating fluid 506 can leave the heat exchanger 500 and pass through a junction of cleaning material 600, in which the cleaning material is combined with the third stream of recycled circulating fluid 506, to form the cleaning material stream 610. The cleaning material junction 600 can comprise any structure, unit, or device suitable for combining the third stream of recycled circulating fluid 506 with the cleaning material, wherein the cleaning material is provided in a continuous flow or is provided in a batch. Preferably, the cleaning material junction is configured so that the cleaning material is combined and flows with the third stream of recycled circulating fluid 506. As also described above with respect to the second stream of recycled circulating fluid 504, the third stream of recycled circulating fluid 506 can be controlled so that the flow can be zero or any flow required to effectively transfer the cleaning material to the turbine.
[0130] The cleaning material can be any material effective for contacting the surface of the turbine blades, and removing, physically or chemically, the solid deposits from them. Preferably, the cleaning material comprises a material that is effective for removing deposits with minimal erosion or without it from the surfaces of the blades themselves. Solid cleaning materials can include carbon particles, alumina particles or other hard particles configured to not melt at flow temperatures. Erosion of ash, but not of blades, can occur at low impact speeds, because ash can define less fracture resistance than the blade. Liquid cleaning materials can include potassium compounds, such as potassium oxide, carbonate or hydroxide. The potassium compounds can act as a flux to lower the melting point of the ash, so that it can melt from the blades. Gaseous cleaning materials can include oxygen, which can oxidize deposits, such as carbon. Solid or liquid cleaning materials, combined with the third recycled circulating fluid stream 506, at the cleaning material junction 600, can define less than about 0.5%, less than about 0.1%, or less than about 0.01% of the total mass flow of the cleaning material stream 600, and from about 0.001% to about 0.1%, from about 0.1% to about 1%, or about 0.0001% to about 0.01% of the total mass flow of the cleaning material stream. Gaseous cleaning materials, combined with the third recycled circulating fluid stream 506, at the cleaning material junction 600, can define less than about 5%, less than about 2%, or less than about 1 % of the total mass flow of the cleaning material stream 610, and from about 0.1% to about 2%, from about 0.01% to about 1%, or from about 0.01% to about 5% of the total mass flow of the cleaning material stream. In one embodiment, the cleaning cycle can be started when the power output from generator 400a drops from about 2% to about 5%, from about 5% to about 10%, or from about 1% to about 2%. For example, the cleaning operation can be conducted from about once a week to about once every three years. The cleaning cycle can last from about five minutes to about an hour in some embodiments.
[0131] The cleaning material stream 610 can flow directly to the turbine 400. In these embodiments, the cleaning material stream can mix with the combustion product stream 320 at a common inlet to the turbine 400, or the stream of cleaning material 610 and the combustion product stream 320 can have individual entries in the turbine, so that the streams mix at an internal point in the turbine 400. In the illustrated embodiment, the cleaning material stream 610 is first mixed with the combustion product stream 320 at a flow combiner bypass 650. Thus, in a cleaning cycle, the combustion product stream and combined cleaning material 326 leaves the combiner bypass flow 650 and enters the turbine 400.
[0132] In some embodiments, continuous cleaning can be used in which some minimal flow of the third stream of recycled circulating fluid 506 can be maintained so that an amount of cleaning material is continuously introduced into the turbine. The flow of the third stream of recycled circulating fluid 506 can be adjusted up or down periodically to increase or reduce the cleaning capacity of the cycle. In other embodiments, the third recycled circulating fluid stream 506 can be closed, so that no cleaning material passes from the cleaning material junction 600 to the flow combiner diversion 650. In this operational mode, the combustion product stream 320 can bypass the flow combiner bypass 650 and pass directly to the turbine, as shown in Figure 1. Alternatively, the stream of combustion product 320 can continue to flow through the combiner bypass 650, but in the absence of a stream of Inlet cleaning 610, the stream leaving the combiner bypass 650 will essentially be the combustion product stream 320 and not the combustion product and combined cleaning material stream 326.
[0133] In embodiments in which the cleaning cycle is active, deposits or residue removed from the turbine blades can be removed from the cycle by filter 5, in the manner described in relation to Figure 1. Also, when cleaning materials are used solids, solid cleaning materials can be removed from the cycle by filter 5. In some embodiments, filter 5 can be a multi-unit filter in which a first media or filter unit is used during the normal course of the combustion cycle, and a second medium or filter unit can be used during the cleaning cycle, to collect the cleaning material and deposits from the removed blades, without unnecessarily encrusting the filter used in the normal combustion cycle. The inventive system can incorporate the appropriate devices to facilitate this switching between filters.
[0134] EXEMPLIFICATIVE ACCOMPLISHMENTS
[0135] The present invention will be described below with specific reference to the examples presented below, which are not intended to be limiting of the invention and are, instead, provided to show exemplary embodiments.
[0136] Figure 3 illustrates an exemplary embodiment of a 1000 combustor, which can be used according to the systems and processes described in this specification. The combustor 1000 can define a combustion chamber 1002, in which fuel and O2 are guided by a fuel inlet 1004 and an inlet of O2 1006. Consequently, the fuel can be burned to form a stream of combustion product 1008. The combustor 1000 may comprise a shell, comprising an outer shell 1010 and an inner shell 1012. The inner shell 1012 may comprise a transpiration material, such as a porous sintered material (e.g., a porous sintered metal material), which is configured to receive a sweat fluid 1014 and sweat the fluid through it, to define a sweat layer 1016, configured to reduce the heat incident on the housing. Transpiration fluid 1014 may be received in some embodiments via an inlet 1026, although transpiration fluid may be received from a turbine, trapped in the combustion, in some embodiments, as described below. Consequently, the combustion product stream 1000 can be configured to withstand the heat produced in the combustion chamber 1002, without employing expensive thermally resistant materials, such as super alloys, and / or the combustion can operate at higher combustion temperatures.
[0137] As described above, the combustion product stream produced by a combustor can be used to drive a turbine. In that respect, Figure 4 illustrates an exemplary embodiment of a turbine 2000. In one embodiment, turbine 2000 may include an inlet duct 2002, configured to couple with a combustion outlet (for example, combustion 1000) and directing a combustion product stream (e.g., combustion product stream 1008) to an inlet of a 2004 turbine housing. The 2000 turbine can comprise a rotor 2006, to which several blades 2008 are attached. Rotor 2006 may comprise an annular flow diverter 2010, configured to deflect the combustion product stream around the rotor. Consequently, the combustion product stream 1008 can be expanded while moving through the turbine 2000, thereby causing the blades 2008 to rotate the rotor 2006 and a driving shaft 2011 (which can be integral with the rotor, or coupled to it), before a turbine discharge current 2012 is discharged through one or more outlets 2014. In this way, turbine 2000 can drive a generator, or another device.
[0138] As further illustrated in Figure 4, the inlet duct 2002 may comprise an internal housing 2016 and an external housing 2018. Furthermore, the 2004 turbine housing 2000 may comprise an internal housing 2020 and an external housing 2022. A fluid transpiration 2024 can be guided from an inlet 2026, between the internal housings 2016, 2020 and the external housings 2018, 2022 of the intake duct 2002 and the turbine 2000. The internal housings 2016, 2020 can comprise a transpiration material such as a porous sintered material (for example, a porous sintered metallic material), which is configured to receive the transpiration fluid 2024 and transpirate the fluid through it. In this way, a transpiration layer 2028 can be defined between the combustion product stream 1008 and the inner surface of the inlet duct 2002, and a transpiration layer 2030 can be defined between the paddles 2008 and an internal surface of the inner housing 2020 , and the internal housings may be cooled or otherwise protected by the 2024 transpiration fluid. In some embodiments, the transpiration fluid provided to the turbine may also be provided to the combustion for transpiration cooling. In this respect, for example, the inlet duct can join the combustor, so that the transpiration fluid is provided to it in some embodiments. However, the transpiration fluid provided to the combustor can be additionally or alternatively, provided from a separate inlet 1026 in some embodiments.
[0139] Furthermore, the transpiration fluid 2024 can also be introduced into the turbine 2000 by a second inlet 2032, which can be defined on the driving axis 2011 in some embodiments. Consequently, the transpiration fluid 2024 can travel from the driving shaft 2011 to the rotor 2006. The rotor 2006 and / or the blades 2008 can comprise a transpiration material, such as a porous sintered material (for example, a porous sintered metal material ), which is configured to receive the transpiration fluid 2024 and transpire the fluid through it to their external surfaces. Consequently, the rotor 2006 and / or the blades can be cooled or otherwise protected from the stream of combustion product 1008 and particulate material in it by the transpiration fluid 2024.
[0140] Figures 5 and 6 illustrate an alternative embodiment of a 2000 'turbine. As illustrated, several 1000 'combustors can be configured to drive turbine 2000'. In particular, combustors 2000 'can be arranged radially with respect to the major axis, defined by rotor 2006', as shown in Figure 6. As shown in Figure 5, turbine 2000 'can be substantially similar to the embodiment of turbine 2000, illustrated in Figure 4, except that combustors 1000 'can supply combustion product streams 1008' around the circumference of the rotor 2006 '. Consequently, an annular flow diverter may be unnecessary to divert combustion product streams 1008 'around rotor 2006'. All 1000 'combustors can be substantially similar to the 1000 combustor, described above except for placing the combustors around the 2006 rotor'.
[0141] Figure 7 illustrates a side sectional view through an embodiment of a 2008A turbine blade, which can be used in the turbines described in this specification. The turbine blade 2008A can comprise an outer layer 3002 and a core 3004. Core 3004 can define a relatively mechanically resistant metal, or other material configured as a reinforcement element. A mechanically resistant metal, as used in the present invention, refers to a metal with a mechanical strength greater than 68.9 MPa (10,000 psi), greater than 137.9 MPa (20,000 psi), or greater than 206.8 MPa ( 30,000 psi), at suitable elevated temperatures, and that is chemically resistant to suitable temperatures. Examples include stainless steel alloys and alloys with a high nickel content, such as inconel, etc. Thus, the present invention allows cheaper alloys, such as stainless steel (for example, 316 stainless steel), or other alloys with lower nickel and cobalt contents, to be used instead of typical super alloys, which have nickel contents and relatively high cobalt, and are therefore expensive. In this respect, a 316 polycrystalline stainless steel can be as much as twenty times cheaper per kilogram (pound) than a polycrystalline superalloy, and two thousand times lower in cost per kilogram (pound) than single crystal superalloy paddles.
[0142] Furthermore, core 3004 can define one or more channels 3006. Channels 3006 can be configured to receive the transpiration fluid and guide it to the outer layer 3002. The outer layer 3002 can define a part, or the all of an external surface 3008 of the blade 2008A in some embodiments. Furthermore, the outer layer 3002 can comprise a porous material, such as a porous sintered metal material. Consequently, channels 3006 in core 3004 can be configured to receive transpiration fluid and guide it to the outer layer 3002. In this way, the transpiration fluid can flow through the outer layer 3002 of the turbine blade 2008A and provide a transpiration layer around the outer surface 3008 of the turbine blade, which can protect the turbine blade from heat and / or impacts with particulate matter. In this respect, it should be understood that a turbine blade and / or other components of the systems described in this specification can be protected by transpiration, meaning that a transpiration fluid is oriented to at least part of a surface of them, regardless of if perspiration cools the component. For example, a component can be protected by perspiration by a perspiration fluid, which protects a surface of the component from impact with particulate matter or other material, regardless of the temperature of the transpiration fluid. Conversely, a component can be, additionally or alternatively, protected by perspiration by a perspiration fluid, which cools the component or acts as a barrier, which reduces the heating of the component.
[0143] As described above, the transpiration fluid can be, additionally or alternatively, used in other components associated with the systems and assemblies described in this specification. In that respect, Figure 8 illustrates a sectional view through part of an inlet conduit 2002a, configured to transfer a stream of combustion product from a combustor to a turbine. The inlet conduit 2002A may comprise an inner layer 4002 and an outer layer 4004. The outer layer 4004 may comprise a crust, which may comprise a strong metal, as described above, configured to provide mechanical resistance to the inlet conduit 2002A. Furthermore, outer layer 4004 can define one or more channels 4006. Channels 4006 can be configured to receive the transpiration fluid and route it to inner layer 4002. Inner layer 4002 can define part, or all, of an inner surface 4008 of the inlet conduit 2002A in some embodiments. Furthermore, the inner layer 4002 may comprise a porous material, such as a porous sintered metal material. Consequently, channels 4006 in outer layer 4004 can be configured to receive the transpiration fluid and guide it to the inner layer 4002. In this way, the transpiration fluid can flow through the inner layer 4002 of the inner duct 2002A and provide a layer of perspiration on the inner surface 4008 of the inlet duct, heat and / or impact of particulate matter.
[0144] As illustrated in Figure 9, in an embodiment of an inlet conduit 2002B, an insulating layer 4010 and a second outer layer 4012 can be additionally provided. The insulating layer 4010 and the second outer layer 4012 may surround the inner layer 4002 and the outer layer 4004 in some embodiments. The insulating layer 4010 can insulate the inlet duct 2002B in order to retain more heat in it, which can increase the efficiency of the system in which it is employed. Furthermore, the second outer layer 4012 can provide additional mechanical strength to the inlet conduit 2002B. However, the various layers of material and the items described above can be, additionally or alternatively, used in other components of the systems and assemblies described in this specification, such as in a combustor.
[0145] Figure 10 illustrates a longitudinal sectional view through a turbine blade 2008B, according to an alternative embodiment. The 2008B turbine blade may comprise one or more reinforcement elements, such as one or more rods 5014. The rods 5014 may comprise a metallic material, or other material configured to provide mechanical strength to the turbine blade 2008B.
[0146] The turbine blade 2008B can also define one or more channels 5006. Channels 5006 can be configured to receive the transpiration fluid and guide it to the material by defining the turbine blade 2008B. In that respect, the turbine blade 2008B may comprise a porous material, such as a porous sintered metallic material. Consequently, channels 5006 on the 2008B turbine blade can be configured to receive the transpiration fluid and guide it through the turbine blade, to provide a perspiration layer on an external surface 5008 of the turbine blade, which can protect the blade from heat turbine and / or impacts with particulate material.
[0147] In some embodiments, the 2008B turbine blade can be configured to define a flow of transpiration fluid at a leading edge 5016 of the turbine blade, which is greater than a flow of transpiration fluid at a trailing edge 5018 of the turbine blade. This can provide the leading edge with greater protection, which may be desirable, since the leading edge may otherwise be more prone to particulate impacts than the rest of the turbine blade. In this respect, one or more channels 5006 on the turbine blade 2008B can define a transpiration fluid inlet area at the leading edge 5016 (see, for example, channel 5006A), which is larger than a fluid inlet area. transpiration of one or more channels at the trailing edge 5018 (see, for example, channel 5006B). Alternatively, a greater number of channels can be defined at the leading edge than at the trailing edge.
[0148] Figures 11 to 13 illustrate an alternative embodiment of a 2008C turbine blade. As illustrated, the 2008C turbine blade can define an integral structure, comprising one or more internal ribs 6020. The internal ribs 6020 can function as a reinforcement element, configured to provide mechanical resistance to the 2008C turbine blade. The internal ribs 6020 can be formed integrally with an outer layer 6002 and / or a base element 6022 of the turbine blade 2008C.
[0149] The 2008C turbine blade can include one or more channels 6006, which can be separated by internal ribs 6020. Channels 6006 can be configured to receive transpiration fluid (for example, from a rotor to which the base 6022) and guide it through the outer layer 6002. In that respect, the turbine blade 2008C may comprise a porous material, such as a porous sintered metallic material. Consequently, channels 6006 on the turbine blade 2008C can be configured to receive the transpiration fluid and guide it through the outer layer 6002 of the turbine blade, to provide a perspiration layer on an outer surface 6008 of the turbine blade, which can protect the turbine blade from heat and / or impacts with particulate matter. As further illustrated, channels 6006 on the 2008C turbine blade can define a transpiration fluid inlet area at the leading edge 6016 (see, for example, channel 6006A), which is larger than a fluid inlet area of perspiration of one or more channels not leading edge 6018 (see, for example, channel 6006B). Consequently, in some embodiments, the 2008C turbine blade can be configured to define a flow of transpiration fluid at a leading edge 6016 of the turbine blade, which is greater than a flow of transpiration fluid at a trailing edge 6018 of the turbine blade.
[0150] Figure 14 illustrates a side cross-sectional view through an additional embodiment of a 2008D turbine blade. As illustrated, the 2008D turbine blade may comprise an outer layer 7002, which defines a wall thickness at trailing edge 7018, which is greater than a wall thickness at leading edge 7016. In this respect, the 2008D turbine blade it may comprise a porous material, such as a porous sintered metal material. Consequently, the transpiration fluid can be guided by the 2008D turbine blade, so that it travels through the outer layer 7002, to provide a perspiration layer on an outer surface 7008 of the turbine blade, which can protect the heat turbine blade. and / or impacts with particulate material. Since the wall thickness of the outer layer 7002 is greater at trailing edge 7018 than at leading edge 7016, the 2008D turbine blade can define a flow of perspiration fluid at the leading edge, which is greater than one flow of perspiration fluid at the trailing edge.
[0151] Furthermore, the turbine blades, according to the various embodiments described in this specification, can define a porosity, which varies between the root and the tip of a turbine blade (see, for example, the root 6026 and the tip 6028 of the turbine blade 2008C illustrated in Figure 13). In this regard, in some embodiments, the turbine blades described in this specification can be configured to define a flow of the transpiration fluid at the tip of the turbine blade, which is greater than a flow of the transpiration fluid at the root of the blade. turbine. This can provide the turbine blades with additional protection, which may be desirable, since the tip of the turbine blade moves at a higher speed than any other point on the turbine blade.
[0152] For example, Figure 15A schematically illustrates a longitudinal sectional view through a 2008E turbine blade. As illustrated, the 2008E turbine blade defines a porosity, which differs between the 8026 root and the 8028 tip. In particular, the 2008E turbine blade is more porous at the 8028 tip than at the 8026 root, so that it is relatively more fluid. perspiration may seep from the tip of the turbine blade than from the root of the turbine blade. In that respect, the turbine blade 2008E may comprise a porous material, such as a porous sintered metallic material, configured to transpire a transpiration fluid through it, as discussed above. As illustrated, in some embodiments, the porous material can define several layers 8030A - D, in which the porosity of the layers increases from root to tip. The layers 8030A - D can be defined by different materials or by the same material, which has been sintered to varying degrees, and therefore its porosity varies. In some embodiments, the layers can be laminated together, although the layers can be attached in several other ways.
[0153] In another embodiment, as illustrated in Figure 15B, the turbine blade 2008E 'defines a porosity, which differs between the root 8026' and the tip 8028 ', as described above with respect to Figure 15B. However, as illustrated, in some embodiments, the porous material may define a porosity gradient, in which, for example, the porosity of the material increases from the root 8026 'to the tip 8028'. In this respect, the porosity of the material can vary in several places, without different layers defining different porosities in some embodiments.
[0154] Various other configurations for the turbine blades can be used. For example, in some embodiments, the turbine blades can be configured to define a flow of perspiration fluid at the leading edge, which is substantially equal to, or less than, the flow of perspiration fluid at the trailing edge of the blades. turbine. Furthermore, in some embodiments, the turbine blades can be configured to define a flow of perspiration fluid at the tip, which is substantially equal to, or less than the flow of transpiration fluid at the root of the turbine blade. Furthermore, variations in porosity between the leading edge and trailing edge can also be used to control the flow of transpiration fluid from the blades, in a similar manner as described with respect to the control of transpiration fluid between the root and the tip.
[0155] Thus, for example, the porosity of the material defining the turbine blade (or other component) can increase between the root and the tip, decrease between the root and the tip, be relatively higher or lower in the center, in relation to to the outer parts of the blade, increase or decrease from the leading edge to the trailing edge, etc. The porosity gradient or porosity layers can increase or decrease from about 10% porosity to about 90% porosity, about 25% porosity to about 75% porosity, or about 1% porosity at about 25% porosity.
[0156] Consequently, the transpiration fluid can be configured to cool and / or otherwise protect various components of the systems and assemblies described in this specification. In this respect, Figure 16 illustrates a calculated trajectory 900 for a 100 μm ash particle, relative to an outer surface 904 of a 906 turbine blade. The ash particle path 900 is modeled based on the gray particle 902 displacing initially at 75 m / s, in the direction of the turbine blade 906, with a flow of circulating CO2 fluid 908 transpiring from the outer surface 904 of the turbine blade at 2 m / s. The circulating fluid in the turbine can be at 300 bar (30 MPa) at 700 ° C. As illustrated, the transpiration fluid 908 prevents the ash particle 902 from coming into contact with the turbine blade 906. In particular, the ash particle 902 is calculated to be about 0.2 mm from the outer surface 904 of the turbine blade. turbine. Consequently, erosion of the turbine blade 906 can be prevented.
[0157] Similarly, Figure 17 illustrates an example according to the present invention of a calculated particle path 1000 for a 50 μm 1002 ash particle, relative to an internal surface 1004 of a 1006 combustor. calculated particle 1000 is modeled on the basis of the ash particle 1002 initially moving at a speed of 50 m / s, perpendicular to the internal surface 1004 of the combustion 1006, with an axial flow rate of the flue gas of about three meters per second, a flue gas composition greater than about 90% CO2, a flue gas temperature of around 1,500 ° C, a pressure of about 300 bar (30 MPa), and a radial transpiration rate of the fluid transpiration rate 1008 of about one meter per second in the radial direction (for example, perpendicular to the axial flue gas flow). As illustrated, the transpiration fluid 1008 prevents the ash particle 1002 from contacting the inner surface 1004 of the combustion 1006. The ash particle 1002 is calculated to be just 0.2 mm from the inner surface 1004 of the combustion 1006. Consequently, erosion of the internal surface 1004 of the combustion 1006 can be prevented.
[0158] Table 1 below provides several parameters for operating a natural gas gas turbine project for a conventional power plant. A cross section of this typical 1100 turbine is shown in Figure 18. As a comparison, Table 2 below provides the same parameters for operating a low speed, high pressure turbine in accordance with the present invention. A cross section of an exemplary turbine 1200, according to the invention, is shown in Figure 19. As can be seen by comparing the conventional turbine 1100 with the turbine 1200 of the present invention, the turbine of the present invention can define a diameter relatively smaller due to the turbine of the present invention employing relatively shorter 2008F turbine blades, compared to the turbine blades 1108 of the conventional turbine in some embodiments. In that regard, as shown in the tables presented below, the 2008F turbine blades of the 1200 turbine of the present invention can define a mean internal radius (that is, from the center of the rotor 2006F to the root of the turbine blade), a mean external radius (i.e., from the center of the rotor to the tip of the turbine blade) and a relatively smaller average radius (mean of the internal and external radii), compared to the turbine blades 1108 of the conventional turbine 1100 in some embodiments. Also, the turbine 1200 of the present invention can define a relatively larger length-to-diameter ratio compared to the conventional turbine 1100. Furthermore, the turbine 1200 of the present invention can include a relatively larger number of 2008F turbine blades than conventional turbine 1100. In addition, the diameter of rotor 2006F of turbine 1200 of the present invention may be smaller than the diameter of rotor 1106 of conventional turbine 1100.



[0159] Many modifications and other embodiments of the invention shown in this specification will come to mind for those skilled in the art to which the invention relates, having the benefit of the teachings presented in the description above. Therefore, it should be understood that the invention is not limited to the specific embodiments described, and that modifications and other embodiments are intended to be included within the scope of the appended claims. Although specific terms are used in this specification, they are used in a generic and descriptive sense only and not for the purpose of limitation.

权利要求:
Claims (29)
[0001]
1. Turbine assembly (400), characterized by the fact that it comprises: a plurality of components including: an enclosure defining: an inlet configured to receive a stream of combustion product (320); and an exit; a rotor positioned in the housing; and a plurality of blades extending from the rotor, wherein: the blades comprise a porous sintered material and are configured to guide a transpiration fluid to an external surface and define a flow of the transpiration fluid at a leading edge of the blades, which exceeds a flow of the transpiration fluid at a trailing edge of the paddle.
[0002]
2. A turbine assembly (400) according to claim 1, characterized by the fact that the porous sintered material defines the entire external surface of the blades.
[0003]
3. A turbine assembly (400) according to claim 1, characterized in that the casing comprises porous sintered material, and the porous sintered material is configured to guide the transpiration fluid to an internal surface of the casing, or in that the rotor comprises the porous sintered material, and the porous sintered material is configured to guide the transpiration fluid to an external surface of the rotor.
[0004]
A turbine assembly (400) according to claim 1, characterized in that the rotor comprises an annular flow diverter, configured to deflect the combustion product stream (320) around the rotor.
[0005]
5. Turbine assembly (400) according to claim 1, characterized by the fact that one or more of the following conditions is met: one or more channels are defined in the blades and the channels are configured to receive the transpiration fluid and guide the transpiration fluid for the porous sintered material; each of the blades defines a sweat fluid inlet area at the leading edge that is larger than a sweat fluid inlet area in the trailing edge; each of the blades defines a wall thickness that is greater at the trailing edge than at the leading edge; each of the blades defines, respectively, an integral structure, which comprises a plurality of internal ribs.
[0006]
Turbine assembly (400) according to claim 1 or 2, characterized in that it further comprises an inlet duct, coupled to the housing inlet and configured to be coupled to an outlet of a combustion assembly (300) and receiving the combustion product stream (320) from it, where the inlet conduit comprises the porous sintered material, and the porous sintered material is configured to guide the transpiration fluid to an internal surface of the inlet conduit.
[0007]
A turbine assembly (400) according to claim 1 or 2, characterized by the fact that the housing inlet is configured to be directly coupled to an outlet of a combustion assembly (300).
[0008]
A turbine assembly (400) according to claim 7, characterized by the fact that the housing inlet is configured to receive the combustion product stream (320) from a plurality of combustors (300), arranged radially with respect to to a large axis defined by the rotor.
[0009]
A turbine assembly (400) according to any one of claims 1 to 8, characterized in that the blades comprise at least one reinforcement element, respectively.
[0010]
A turbine assembly (400) according to claim 9, characterized by the fact that the reinforcement element comprises a rod, which extends through the porous sintered material on all blades; or where the reinforcement element comprises a core, where the porous sintered material extends around the core.
[0011]
A turbine assembly (400) according to claim 10, characterized by the fact that the core defines one or more channels, configured to receive the transpiration fluid and direct the transpiration fluid to the porous sintered material.
[0012]
Turbine assembly (400) according to claim 1, characterized in that all the blades extend from a root in the rotor to a tip, and in which the porous sintered material defines a porosity, which varies between the root and the tip.
[0013]
Turbine assembly (400) according to claim 12, characterized in that the porosity of the porous sintered material is configured to define a flow of the transpiration fluid at the tip, which is greater than a flow of the transpiration fluid at the root; or wherein the porosity of the porous sintered material is configured to define a flow of the transpiration fluid at the tip, which is substantially equal to the flow of the transpiration fluid at the root.
[0014]
Turbine assembly (400) according to claim 12, characterized in that the porous sintered material defines a plurality of layers, in which the porosity of the layers increases from root to tip.
[0015]
A turbine assembly (400) according to claim 1, characterized in that the components further comprise a plurality of stators, in which the stators comprise the porous sintered material, and the porous sintered material is configured to guide the fluid of perspiration to an external surface of the stators.
[0016]
The turbine assembly (400) according to claim 1, characterized by the fact that it also comprises one or more seals, in which one or more of the components are configured to guide the transpiration fluid to the seals.
[0017]
A turbine assembly (400) according to claim 16, characterized in that the seals comprise the porous sintered material.
[0018]
A turbine assembly (400) according to claim 1, characterized in that the ratio of a length of the turbine assembly (400) to an average blade diameter is greater than 3.5.
[0019]
A turbine assembly (400) according to claim 18, characterized in that the turbine blades (400) have a blade height of less than about 0.275 m; or where the turbine assembly (400) comprises less than about 2,000 of the blades.
[0020]
20. Energy generation process, characterized by the fact that it comprises: introducing a fuel, O2 and a circulating fluid (503) of CO2 into a combustor (300); burning a fuel to provide the combustion product stream (320) comprising CO2; expanding the combustion product stream (320) through a turbine (400), comprising a plurality of turbine blades (400) and defining a ratio of a length of the turbine (400) to an average diameter of the turbine blades (400) greater than 3.5, to generate energy and discharge a turbine discharge stream (410), in which the turbine blades (400) comprise a porous sintered material and are configured to direct a transpiration fluid to an external surface and define a flow of the transpiration fluid at a leading edge of the blades, which exceeds a flow of the transpiration fluid at a trailing edge of the paddle; processing the turbine discharge stream (410) to recycle at least a portion of the circulating fluid (503) of CO2 to the combustor (300); removing part of the circulating fluid (503) of CO2, which is recycled; and use the circulating fluid (503) of recycled CO2 as a perspiration fluid.
[0021]
21. Process according to claim 20, characterized in that using the circulating fluid (503) of recycled CO2 as the transpiration fluid comprises transpiring the circulating fluid (503) of recycled CO2 in the turbine (400) or in the combustion ( 300).
[0022]
22. Process according to claim 20, characterized by the fact that it also comprises directing the combustion product stream (320) from the combustor (300), through a duct, to the turbine (400), in which to use the circulating fluid ( 503) of recycled CO2 as the transpiration fluid comprises transpiring the circulating fluid (503) of recycled CO2 in the conduit.
[0023]
23. Process according to claim 20, characterized by the fact that it also comprises conditioning the circulating fluid (503) of recycled CO2 to change its temperature.
[0024]
24. Power generation system, characterized by the fact that it comprises: a combustor (300) configured to receive a fuel, O2 and a circulating fluid stream (503) of CO2, and having at least one combustion stage, which burns the fuel in the presence of the circulating fluid stream (503) of CO2 and provides a combustion product stream (320) comprising CO2; a turbine (400) in fluid communication with the combustion (300), the turbine (400) having an input for receiving the combustion product stream (320), an output for releasing a turbine discharge stream (410) comprising CO2, and a plurality of turbine blades (400), where a ratio of a turbine length (400) to an average diameter of the turbine blades (400) is greater than 3.5 and where the turbine blades ( 400) comprise a porous sintered material and are configured to direct a transpiration fluid to an external surface and define a flow of the transpiration fluid at a leading edge of the blades, which exceeds a flow of the transpiration fluid at a trailing edge of the Pan; one or more components configured to process the turbine discharge stream (410) to form a circulating fluid stream (503) of recycled CO2, wherein one or more system components are configured to use a portion of the circulating fluid stream (503) of recycled CO2 as a transpiration fluid.
[0025]
25. Power generation system according to claim 24, characterized by the fact that one or more components configured to process the turbine discharge stream (410), to form a circulating fluid stream (503) of recycled CO2, they comprise a filter, a heat exchanger, a separator, and a compressor.
[0026]
26. Power generation system according to claim 24, characterized in that one or more components configured to use the part of the circulating fluid stream (503) of recycled CO2, such as the transpiration fluid, comprise a sintered material porous, configured to receive the transpiration fluid through it.
[0027]
27. Power generation system according to claim 24, characterized by the fact that the turbine blades (400) have a blade height less than 0.275 m or in which the turbine (400) comprises less than 2,000 of the blades. turbine (400).
[0028]
28. Energy generation process, characterized by the fact that it comprises: introducing a fuel, O2 and a circulating fluid (503) into a combustor (300); burning the fuel in the combustion (300) to provide a combustion product stream (320), including the circulating fluid (503) and a particulate material content, the combustion product stream (320) flowing at a defined speed; and expanding the combustion product stream (320) through a turbine (400), comprising a plurality of turbine blades (400), to generate energy and discharge a turbine discharge stream (410), the turbine (400) being operated so that the turbine blades (400) rotate at a blade speed of less than 500 mph (meters per hour).
[0029]
29. Power generation system, characterized by the fact that it comprises: a combustor (300) configured to receive a fuel, O2 and a circulating fluid (503), and having at least one combustion stage, which burns the fuel and provides a combustion product stream (320) which includes the circulating fluid (503) and a particulate material content; a turbine (400) in fluid communication with the combustion (300), the turbine (400) having an input for receiving the combustion product stream (320), an output for releasing a turbine discharge stream (410), and a plurality of blades of sufficient size, so that the turbine (400) operates at a blade speed of less than 500 mph; and a filter in fluid communication with the turbine outlet (400) and configured to produce a filtered turbine discharge current (410).

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法律状态:
2018-12-26| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|

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2019-11-26| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|

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2020-09-08| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|

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2020-12-08| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 20/09/2011, OBSERVADAS AS CONDICOES LEGAIS. |

优先权:

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申请号 | 申请日 | 专利标题

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US38503910P| true| 2010-09-21|2010-09-21|

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US38504710P| true| 2010-09-21|2010-09-21|

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US61/385,039|2010-09-21|

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US61/385,047|2010-09-21|

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US201161437330P| true| 2011-01-28|2011-01-28|

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US61/437,330|2011-01-28|

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US13/236,240|US20120067054A1|2010-09-21|2011-09-19|High efficiency power production methods, assemblies, and systems|

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US13/236,240|2011-09-19|

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