• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The present invention relates to an indirect fired gas turbine system comprising a combustion chamber (3) extending along a central axis of the gas turbine system, for combustion of compressed air and supplied fuel whereby flue gas is formed, a turbine (2) driven by a working medium , a compressor (1) rotatably coupled to the turbine to compress the working medium and / or air to the combustion chamber and a first heat exchanger device (8) for transferring heat between the flue gas and the working medium. The first heat exchanger device and the combustion chamber are integrally designed as a monolithic unit, the first heat exchanger device being arranged substantially within the axial extent of the combustion chamber along the central axis. The integrated design of the combustion chamber and the first heat exchanger device achieves a compact, indirectly fired gas turbine system with high efficiency.
    公开号:SE1051322A1
    申请号:SE1051322
    申请日:2010-12-15
    公开日:2012-06-16
    发明作者:Stefan Larsson；Anders Lindstroem；Hansi Kobes
    申请人:Redian Ab；
    IPC主号:
    专利说明:

    P 10-0161 2 it is incinerated together with added fuel. The hot flue gas formed by combustion is then allowed to expand through one or more turbine stages where it thereby emits its energy. The turbine stage is usually rotatably connected to the compressor stage to drive this, but the compressor stage can also be driven by a separate motor or other energy source.
    Ideally, compression and expansion are isentropic processes, ie. entropy in the system remains constant. However, due to energy losses through the compressor and the turbine in a real gas turbine, these processes are adiabatic. Compression and expansion take place so quickly that in principle there is no heat transfer to or from the working medium. When the pressure increases by compression, adiabatic heating takes place and the working medium, in this case the drawn-in ambient air, heats up. Adiabatic cooling occurs when the pressure decreases through expansion in the turbine. Parts of this emitted heat can be extracted in the form of work to drive the turbine. With higher efficiency, a larger proportion of the heat energy can be recovered.
    A microturbine is, as the name implies, a small high-speed gas turbine that exhibits lower pressure and temperature in the combustion chamber, compared to a larger gas turbine. A microturbine typically has a developed power in the range of 50-500 kW and a size of about 3 cubic meters with a total weight of 2 tons or more.
    Various fossil fuels such as natural gas (methane, propane), petrol, diesel, heating oil, LPG and digestate or non-fossil fuels such as biogas, biodiesel and E85 (a mixture of about 85% ethanol and about 15% gasoline). In practice, predominantly natural gas is used, which has the lowest emission values. Biofuels in solid form, such as wood pellets, reeds, straw or grass, have also been nominated, but are associated with the disadvantage that the flue gas and combustion products from the combustion chamber can cause contamination and fouling of the turbine blades as they pass the turbine stage, which can increase energy loss. The turbine blades also risk being exposed to chemical influences in the form of corrosion, depending on the fuel used.
    P 10-0161 Therefore, in gas turbines fired with solid biofuel, it is desirable to use a working medium, also called expansion gas or turbine air, which is separate from the flue gas. In a so-called indirectly fired work cycle, heat is transferred from the flue gas to the expansion gas by means of a heat exchanger, whereby these mediums are kept physically separated.
    WO 03/093665 describes an indirectly fired microturbine which utilizes the Brayton cycle in a gas turbine with separate circuits for flue gas and expansion gas. The combustion chamber is located at a distance from the heat exchanger, the flue gas being led from the combustion chamber to the heat exchanger where its heat is transferred to the compressed working medium from the compressor.
    Other examples of indirectly fired (micro) gas turbines are given by GB 2,402,172, FR 2,913,724 and US 2008/0041057.
    WO 02/39045 describes a directly fired gas turbine system having an annular recuperator for transferring heat between turbine exhaust gas and combustion air, with a compressor, a combustion chamber and a turbine arranged within the inner diameter of the recuperator.
    A disadvantage of the prior art is that they often have a low efficiency due to energy losses in the gas turbine system on the expansion gas and / or flue gas path from the compressor via the combustion chamber and the heat exchanger to the turbine, which contributes to lowering the efficiency.
    Another disadvantage of this type of construction is that it requires a relatively large space, which prevents integration in, for example, passenger car-type vehicles or other systems with requirements for compactness.
    There is therefore a need to develop compact, indirectly fired gas turbines with high efficiency.
    P 10-0161 Summary The object of the present invention is to provide a compact, indirectly fired gas turbine system with high efficiency, which can be used for operation of, for example, vehicles with biofuel in solid form.
    This is achieved with an indirect fired gas turbine system according to claim 1, comprising a combustion chamber for combustion of air and supplied fuel whereby flue gas is formed, a turbine driven by a working medium, a compressor rotatably coupled to the turbine to compress the turbine working medium and / or air to the combustion chamber and a first heat exchanger device for transferring heat between the flue gas and the working medium, the first heat exchanger device and the combustion chamber being integrally formed as a monolithic unit, and the first heat exchanger device being arranged substantially within the axial extent of the combustion chamber along the central axis.
    By integrating the heat exchanger and the combustion chamber in a monolithic unit, the heat losses during the passage of the flue gas from the combustion chamber to the heat exchanger can be reduced in an efficient manner. The system uses both radiant heat from the combustion chamber and convection heat in the first heat exchanger device when heating the working medium. In this way, an elevated inlet temperature of the working medium at the inlet to the turbine can be achieved.
    Likewise, a considerable reduction in the volume of the gas turbine system can be achieved, which enables installation in, for example, a vehicle, such as a passenger car or the like.
    Preferred embodiments of the invention are defined by the dependent claims.
    The present invention also relates to a vehicle comprising a gas turbine system.
    Brief description of the drawings P 10-0161 Figure 1 shows a schematic diagram of a gas turbine system according to the prior art.
    Figure 2 shows a principle sketch of the indirectly fired Brayton cycle.
    Figure 3 shows a gas turbine system according to the present invention in a perspective view.
    Figure 4 shows a longitudinal cross-section through the gas turbine system according to the present invention in a side view.
    Figure 5 shows a longitudinal cross-section through the gas turbine system according to the present invention in a perspective view.
    Detailed Description of the Invention The gas turbine system will be described in more detail below with reference to the figures. However, the invention is not to be construed as limited to the embodiment or embodiments shown in the figures and described below, but may be varied within the scope of the claims.
    In general, for all types of heating machines, which convert thermal energy (heat) to mechanical energy (work), the efficiency r is defined; as the ratio between recovered work, Woch added heat, Q: _ W 'l Q Since a real heating machine is limited due to energy losses, not the entire amount of heat added can be converted to work, but a certain amount is given to the environment as waste heat: Qin IW + Qut The efficiency then becomes: Qin _ Qut Qut nzízl-i Qin Qin P 10-0161 6 If you look at a heating machine that works between two specific temperatures, in this case a gas turbine that works after the Brayton cycle, you can deduce that the amount of heat supplied and the emitted heat emitted corresponds to the temperature of the expansion gas at the inlet and outlet of the turbine, respectively, which gives the efficiency: Tuff = 1 __ 77 Ti Thus it is understood that an increase in the temperature of the expansion gas at the turbine inlet can contribute to increasing the efficiency of the gas turbine.
    Figure 1 shows a schematic diagram of a gas turbine system according to the prior art which has a compressor 1 which is rotatably coupled to a turbine 2. The compressor 1 is usually an axial compressor consisting of a number of multi-bladed propellers which rotate on a common shaft inside a pipe. Between the propellers are fixed rings with blades that direct the air flow axially backwards towards the next propeller. Exhaust air is drawn into the compressor 1, whereby it is compressed and led to the combustion chamber 3.
    The combustion chamber 3 is also supplied with fuel from a fuel storage 6, which is combusted together with the compressed ambient air. The resulting flue gas is then led to the turbine 2 whereupon it is allowed to expand to drive the turbine's rotor.
    Through the coupling of the turbine 2 with the compressor 1, part of the recovered work is used to drive the compressor 1.
    The remaining part of the amount of energy is extracted by means of a generator 7 which is also rotatably connected to the turbine 2. Usually the generator 7 also functions as a starting engine for the gas turbine system.
    The gas turbine system may also contain other components such as air filters for the intake air to the compressor 1 or mufflers for the exhaust gas from the combustion chamber 3.
    Figure 2 illustrates the indirectly fired work cycle (Brayton cycle) in a schematic diagram. In addition to the above-mentioned components, this also includes a heat exchanger 8 for transferring heat from the flue gas from the combustion chamber 3 to the working medium of the turbine 2, also called expansion gas or turbine air. This avoids contamination of the turbine 2. The heat from the expansion gas at the turbine outlet can be recovered, by means of a recuperator where the heat is transferred by heat exchange to another medium for heating, for example water. Another possibility is to lead the exhaust gas from the turbine outlet into the flame in the combustion chamber 3 and heat the fuel before combustion. This reduces fuel consumption, as less heat needs to be supplied to the combustion chamber for a given operating temperature or power. Since the flue gas never passes the turbine 2, opportunities are opened to use e.g. solid fuel, which is otherwise associated with increased levels of polluting residues in the exhaust gases.
    Figure 3 shows a gas turbine system according to the present invention in a perspective view. The gas turbine system comprises a compressor 1 and a turbine 2 which are rotatably connected to each other by a common shaft. A generator 7 can be integrated in the inlet of the compressor 1, so that the air flow through the compressor 1 cools the stator windings of the generator 7.
    Figure 4 shows a longitudinal cross-section through the gas turbine system according to the present invention in a side view. A combustion chamber 3 extends in the axial direction along the central axis of the gas turbine system. One end of the combustion chamber 3 has a combustion chamber inlet 4 for supplying fuel from a fuel storage (not shown) in connection with the gas turbine system. In a preferred embodiment, the gas turbine system can be fired with biofuel in solid form, such as wood pellets, which is supplied to the combustion chamber 3 from a pellet storage by means of a feed screw (not shown).
    The combustion chamber 3 here has a cylindrical design, but other embodiments are also conceivable, such as a cubic, annular or irregular shape.
    At the other end of the combustion chamber 3, the flue gases from the combustion are led out through a combustion chamber outlet 5 via radially outwardly directed outlet openings 10 to a first heat exchanger device 8. The first heat exchanger device 8 is integrated with the combustion chamber 3 to form a monolithic unit. The low temperature section is designed to make maximum use of the radiant heat from the combustion chamber 3 in the radial direction to heat the expansion gas, in that the first heat exchanger device 8 is arranged substantially within the axial extent of the combustion chamber 3 along the central axis.
    Those skilled in the art will appreciate that even a construction in which a part of the first heat exchanger device 8 extends beyond the axial extent of the combustion chamber 3, for example in connection with the combustion chamber outlet 5, is within the scope of the invention. In a preferred embodiment, the first heat exchanger device 8 is arranged concentrically around the outer diameter of the combustion chamber 3 to form a compact unit.
    Figure 5 shows a longitudinal cross-section through the gas turbine system according to the present invention in a perspective view. The first heat exchanger device 8 can advantageously be designed as a convection heat exchanger where the expansion gas and the flue gas have opposite flow directions. Such a heat exchanger can consist of heat transfer ducts 11 for the flue gas in the form of several, parallel pipes longitudinally along the combustion chamber, symmetrically arranged and evenly distributed around the circumference of the combustion chamber. The cross-sectional areas of the heat transfer ducts 11 may have the same area, the heat transfer ducts 11 being completely symmetrically flow-wise for the flue gases at the outlet 5 from the combustion chamber 3. This means that the flue gas is evenly distributed between the heat transfer ducts 11 at flow rate. occurs when balancing the mass flow through the heat exchanger's ducts in an indirectly fired turbine. The flow of flue gas through the heat transfer ducts 11 is substantially axially parallel to the central axis of the gas turbine system.
    The first heat exchanger device 8 can also have a heat transfer passage 12 for the expansion gas. The expansion gas consists of compressed air from the compressor 1 which is led via a pipeline 23 to the heat transfer passage 12. This heat transfer passage 12 may be formed by a channel bounded by the outside of the outer wall 13 of the combustion chamber 3 and the outer casing 14 of the gas turbine system, and of intermediate walls 15 extending from the combustion chamber outer wall 13 to the outer casing 14 around the circumference of the combustion chamber 3 in the axial direction. The heat transfer passage 12 can thus P 10-0161 9 form a helical passage which runs at least one revolution around the circumference of the combustion chamber 3 in tangential direction. Adjacent passages are airtight to each other.
    The flow of expansion gas through the heat transfer passage 12 is substantially tangential around the central axis of the gas turbine system.
    The heat transfer ducts 11 for the flue gas intersect the partition walls 15 of the heat transfer passage 12. The contact surfaces where the heat transfer ducts 12 pipes meet the partitions 15 are airtight so that the flue gas does not come into contact with the expansion gas. On the other hand, the heat is transferred from the flue gas to the expansion gas by convection. The flue gas is led out of the first heat exchanger device 8 via flue gas outlet 22. The heated expansion gas is then passed on to the turbine 2 via a pipeline 24.
    The position temperature section is in a preferred embodiment made of 355 welded steel and adapted to increase the temperature of the expansion gas to 500-700 ° C.
    The gas turbine system can further be provided with a second heat exchanger device 9, also called high temperature section, in connection with the inlet 20 of the turbine 2.
    The outlet openings 10 of the combustion chamber can in that case be arranged in the primary side 16 of the second heat exchanger device 9, the surface of which faces the combustion chamber 3.
    On its way from the first heat exchanger device 8 to the turbine inlet 20, the expansion gas passes the secondary side 17 of the second heat exchanger device 9, the surface of which faces away from the combustion chamber 3. The secondary side 17 may be formed as a vortex chamber 19 located in front of the combustion chamber outlet 5. heat radiation center 18 where the radiant heat from the combustion chamber reaches its highest value. The vortex chamber 19 is circularly formed with an inlet 28 from the pipeline 24 located in the outer edge of the vortex chamber 19, which gives the inflowing expansion gas a substantially tangential flow direction upon entry into the vortex chamber 19. The expansion gas is circulated in the vortex chamber 19 in a helical path. Radiant heat from the combustion chamber 3 heats the vortex chamber 19, whereupon the expansion gas coats the heat transfer surface of the vortex chamber 19 several times before it enters the turbine 2 via the outlet 29 of the vortex chamber 19. It is desirable that the expansion gas has a long residence time in the vortex chamber 19. . To further extend the residence time in the vortex chamber 19, this can be provided with a central elevation 30 opposite the outlet 29, which facilitates the circulation.
    The second heat exchanger device 9 is adapted to raise the temperature of the expansion gas to 650-900 ° C, which would give an efficiency of the gas turbine system of about 20-22%. A preferred material for the high temperature section is sintered or cast ceramics, which have good thermal properties.
    The second heat exchanger device 9 can advantageously be designed as a modular component for easy attachment to the combustion chamber 3, which also facilitates replacement in the event of wear. The outer diameter of the primary side 16 of the second heat exchanger device 9 is adapted to the inner diameter of the combustion chamber 3 to form an airtight connection when joining these two components.
    When the temperature in the combustion chamber 3 amounts to about 650-1200 ° C, a temperature gradient can occur between the combustion chamber outer wall 13 and the outer casing 14 of the gas turbine system, which is in contact with the ambient temperature.
    The temperature gradient can cause deformations of the gas turbine system due to different expansion of the material in the combustion chamber outer wall 13 and / or the outer casing 14, which is preferably made of welded steel.
    To counteract deformations, the combustion chamber outer wall 13 and / or the outer casing 14 can be pleated, which provides a bellows function where the material is allowed to expand axially without leading to undesired deformation.
    The gas turbine system can further be equipped with a pipeline 25 between the outlet 21 of the turbine 2 and the inlet 4 of the combustion chamber 3. The expansion gas is thus returned to the combustion chamber 3, where it heats the supplied fuel before combustion begins. This reduces fuel consumption due to the fact that less heat needs to be supplied to the combustion chamber 3 compared to, for example, Stirling engines.
    In a preferred embodiment, the gas turbine system may further comprise means for controlling the fate of the expansion gas and / or flue gas delvis partially past the first 8 and / or the second heat exchanger device 9. This means or control may consist of one or more valves with pipelines for for example directing the expansion gas from the compressor 1 directly to the second heat exchanger device 9 or from the first heat exchanger device 8 directly to the turbine 2.
    Since the gas turbine system must be able to be integrated in a vehicle, such as a passenger car, it is of great importance that the system is sufficiently compact, and that the weight can be kept in line with traditional piston-type internal combustion engines.
    In an example with integration in a passenger car, the requirement for developed power is in the range 10-100 kW, corresponding to the power of a microturbine. The compact design with the low-temperature section designed as a monolithic unit enables an embodiment with a gas turbine in the form of a microturbine, where the size of the system is given by the length 700-1000 mm and the circumference 400-600 mm. With the prior art, such a reduction in size would entail a considerable deterioration of the efficiency, which is counteracted in the present invention by utilizing the radiant heat of the combustion chamber 3 to heat the expansion gas.
    For the size of the microturbine system, space for insulation of an additional 30-50 mm is calculated. In particular, the area enclosing the second heat exchanger device 9 in ceramics places high demands on possible surface temperature. The mass of the microturbine system is estimated at about 34 kg in this embodiment.
    The gas turbine system of the present invention is not limited to any specific size, but can be applied in a gas turbine system of the desired size and power.
    The material in the constituent components can of course be other than the above-mentioned materials which meet the requirements of the gas turbine system for strength and heat resistance, for example metals or composite materials.
    The heat transfer ducts / passages of the first heat exchanger device may be arranged so that the flue gas follows a substantially tangential flow direction around the combustion chamber and the working medium follows an axial flow direction along the combustion chamber. Other constructions are also conceivable, with both flow directions opposite in mainly tangential direction, axial direction or helical at an angle to the central axis of the gas turbine system.
    P 10-0161 13 Reference numerals OONOUCTI-ÄOONJA 11 12 13 14 16 17 18 19 21 22 23 24 26 27 28 29 Compressor Turbine Combustor Combustor Inlet combustion chamber outlet Fuel storage Generator first heat exchanger device by the heat exchanger assembly / high temperature section Outlet openings Heat transfer channel for flue gas heat exchange passage for expansion gas Outer wall Cover Partitions Primary side Secondary Heat radiation center Swirl chamber Turbine inlet Turbine outlet Flue gas outlet Pipeline (compressor-heat transfer passage) Pipeline (heat transfer passage-vortex chamber) Pipeline (turbine-combustion chamber) Compressor inlet Compressor outlet Swirl chamber inlet
    权利要求:
    Claims (1)
    [1]
    Indirect fired gas turbine system comprising: - a combustion chamber (3) extending along a central axis of the gas turbine system, for combustion of air and supplied fuel thereby forming flue gas; - a turbine (2) driven by a working medium; - a compressor (1) rotatably coupled to the turbine (2) for compressing the working medium of the turbine (2) and / or air to the combustion chamber (3); and - a first heat exchanger device (8) for transferring heat between the flue gas and the working medium, characterized in that the first heat exchanger device (8) and the combustion chamber (3) are integrally formed as a monolithic unit, the first heat exchanger device (8) being arranged substantially within the axial extent of the combustion chamber (3) along the central axis. Gas turbine system according to claim 1, wherein the combustion chamber (3) is cylindrical and the first heat exchanger device (8) is arranged concentrically around the outer diameter of the combustion chamber (3). Gas turbine system according to claim 1 or 2, wherein the first heat exchanger device (8) comprises a convection heat exchanger, through which the working medium and the flue gas have opposite flow directions. Gas turbine system according to one of the preceding claims, wherein the first heat exchanger device (8) comprises heat transfer ducts (11) for the flue gas in the form of several, longitudinal, parallel pipes, symmetrically arranged and evenly distributed around the circumference of the combustion chamber (3). Gas turbine system according to claim 4, wherein the cross-sectional area of the heat transfer ducts (11) has the same area. Gas turbine system according to any one of the preceding claims, wherein the first heat exchanger device (8) comprises a heat transfer passage (12) for the working medium of the turbine (2) in the form of a helical, substantially tangential around the circumference of the combustion chamber (3). running channel. . Gas turbine system according to any one of the preceding claims, further comprising a second heat exchanger device (9) located in front of the outlet (5) of the combustion chamber (3). . Gas turbine system according to claim 7, wherein the working medium passes the second heat exchanger device (9) just before it is led into the turbine (2) via the inlet (20) of the turbine (2). . Gas turbine system according to claim 7 or 8, wherein the second heat exchanger device (9) comprises a vortex chamber (19) with a heat transfer surface which faces away from the combustion chamber (3), the working medium coating the heat transfer surface several times before the working medium enters the turbine (2). A gas turbine system according to any one of the preceding claims, further comprising a generator (7) integrated in the inlet (26) of the compressor (1), wherein an air flow contained in the compressor (1) cools the stator windings of the generator (7). Gas turbine system according to one of the preceding claims, wherein the first heat exchanger device (8) and the combustion chamber (3) together form a low-temperature section made of welded steel. Gas turbine system according to one of the preceding claims, wherein the outer wall (13) of the combustion chamber (3) and / or the outer casing 14 of the gas turbine system are folded, forming a bellows function where the material is allowed to expand axially. Gas turbine system according to one of the preceding claims, wherein the second heat exchanger device (9) constitutes a high-temperature section made of sintered and / or cast ceramic. A gas turbine system according to any one of claims 7-12, further comprising means for regulating the gas flow partially past the first and / or the second heat exchanger device (8; 9). A gas turbine system according to any one of the preceding claims, wherein the fuel consists of biofuel in solid form. A gas turbine system according to claim 14, wherein the biofuel consists of wood pellets. Vehicle comprising a gas turbine system according to any one of claims 1-15. 15
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    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    SE1051322A|SE535434C2|2010-12-15|2010-12-15|Indirectly heated gas turbine system|SE1051322A| SE535434C2|2010-12-15|2010-12-15|Indirectly heated gas turbine system|
    US13/994,987| US9181871B2|2010-12-15|2011-12-15|Indirectly heated gas turbine system|
    BR112013015184-6A| BR112013015184B1|2010-12-15|2011-12-15|indirectly heated gas turbine system and vehicle with gas turbine system|
    JP2013544431A| JP5955858B2|2010-12-15|2011-12-15|Indirect heating gas turbine system|
    PCT/SE2011/051519| WO2012082062A1|2010-12-15|2011-12-15|Indirectly heated gas turbine system|
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