• 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:
    A power generation system (100) includes a generator (122, 166); a gas turbine system (102) for supplying the generator (122, 166) and comprising a turbine component (104), an integrated compressor (106) and a combustion device (108) into which air is supplied from the integrated compressor (106) and the fuel. The combustion device (108) is arranged to send hot combustion gases to the turbine component (104), and the integrated compressor (106) has a flow capacity greater than an intake capacity of at least one member among the combustion device (108) and the turbine component (104), generating an excess of airflow (200). A first control valve system (202) controls the flow of excess airflow (200) along a path of excess airflow (250) to a gas turbine system booster (102). the excess airflow (200) can be combusted with fuel and sent to the make-up gas turbine system (102).
    公开号:FR3033838A1
    申请号:FR1652330
    申请日:2016-03-18
    公开日:2016-09-23
    发明作者:Sanji Ekanayake；Thomas John Freeman；John David Memmer；Timothy Joseph Rehg；Alston Ilford Scipio
    申请人:General Electric Co；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The present invention relates generally to power generation systems, and more particularly to a power generating system comprising a compressor generating excess gas flow for a make-up gas turbine system. energy comprising a gas turbine system having a compressor which creates an excess of airflow for use by a make-up gas turbine system. Power generation systems frequently employ one or more gas turbine systems, which can be coupled to one or more steam turbine systems to produce power. A gas turbine system may include a multi-stage axial compressor having a rotary shaft. The air enters the compressor inlet and is compressed by the compressor blade stages and is discharged to a combustion device where a fuel, such as natural gas, is burned to provide a high flue gas flow. energy for driving a turbine component. In the turbine component, the energy of the hot gases is converted into work, some of which can be used to drive the integrated compressor through a rotary shaft, the remainder being available as useful work to drive a load such as a generator via a rotating shaft (for example an extension of the rotating shaft) to produce electricity. In a power generation system, several gas turbine systems can be used in parallel. In a combined cycle system, one or more steam turbine systems may also be employed with the gas turbine system (s). In this configuration, the hot exhaust gases from the gas turbine system (s) are sent to one or more Heat Recovery Steam Generators (HRSGs) 5 in heat recovery steam generators (GVRCs). Anglo-Saxon terms for creating steam, which is then sent to a steam turbine component having a separate rotary shaft or integrated with the gas turbine system (s). In all cases, the energy of the steam is converted into work, which can be used to drive a load such as a generator 10 to produce electricity. When creating a power generation system, parts of this system are configured to work together to provide a system with a desired output power. The ability to increase output power on demand and / or maintain output power in a challenging environment is a continuing challenge in the industry. For example, in very hot weather, power consumption increases, which increases the demand for energy production. Another challenge of hot weather is that as the temperature increases, the compressor flow rate decreases, which results in a decrease in the output power of the generator. An approach to increase output power (or to maintain output power, eg in hot weather) is to add components to the power generation system that can increase the airflow into the cooling device. Combustion of the gas turbine system (s). One approach to increase the airflow is to add a storage tank to supply the gas turbine combustor. However, the latter approach generally requires a separate power source for the storage tank, which is not effective.
    [0002] Another approach to increasing the airflow is to improve the compressor. Currently, the compressors have been upgraded in such a way that their throughput capacity is greater than that of their predecessors. These new higher capacity compressors are generally constructed either to accommodate new, similarly configured combustion devices or older combustion devices capable of supporting the increased capacity. One hurdle to overcome to improve existing gas turbine systems in order to employ the new 10 high capacity compressors is that there is currently no mechanism to operate high capacity compressors with systems that can not withstand increased capacity without improving other expensive parts of the system. Among these parts that it is often necessary to improve at the same time as the compressor, there may be mentioned, but not limited to, the combustion device, a gas turbine component, a generator, a transformer, an equipment switchgear, HRSG generator, steam turbine component, steam turbine control valves, etc. Therefore, although compressor improvement may be desired in theory, the additional cost of upgrading other parts makes the improvement unwise because of the additional expense involved. A first aspect of the present invention provides a power generation system, comprising: a generator; a gas turbine system for powering the generator, the gas turbine system comprising a turbine component, an integrated compressor, and a combustion device into which air from the integrated compressor and fuel are supplied, the device wherein the combustion apparatus is arranged to supply hot combustion gases to the turbine component, and the integrated compressor having a flow capacity greater than an intake capacity of at least one of the combustion device and the combustion component. turbine, which creates an excess of airflow; a makeup gas turbine system comprising an auxiliary combustion device arranged to supply hot combustion gases to a make-up turbine component thereof, the makeup turbine component being operably coupled to a auxiliary generator; and a first control valve system which controls the flow of excess airflow along an excess airflow path, wherein the excess airflow path sends the excess airflow to an inlet of the supplemental combustion device, and the supplemental combustion device burns the excess airflow with a fuel to create the hot combustion gases for the component additional turbine. A second aspect of the invention provides a method comprising the steps of: supplying a generator using a gas turbine system comprising a turbine component, an integrated compressor and a combustor into which air is supplied from of the integrated compressor and the fuel, the combustion device being arranged to send hot combustion gases to the turbine component, and the integrated compressor having a capacity of flow greater than an admission capacity of at least one of the combustion device and the turbine component, which creates an excess of airflow; supplying an auxiliary generator using a makeup gas turbine system comprising an auxiliary combustion device arranged to send hot combustion gases to a makeup turbine component of the latter, the turbine component a booster being operatively coupled to the booster generator 3033838; and extracting the excess air flow from the gas turbine system and supplying the excess airflow to an inlet of the supplemental combustion device, the auxiliary combustion device burning the excess flow air with fuel to create the hot combustion gases for the makeup turbine component. The illustrative aspects of the present disclosure are designed to solve the problems described herein and / or other unexplained problems. These and other features of the invention will become more readily apparent from the following detailed description of the various aspects of the invention taken in conjunction with the accompanying drawings which illustrate various embodiments of the invention. in which: - Figure 1 shows a schematic view of a power generation system according to embodiments of the invention; - Figure 2 shows a schematic view of a power generation system comprising an ejector according to embodiments of the invention. Note that the drawings are not to scale. The drawings are intended only to illustrate general aspects of the invention, and therefore should not be construed as limiting the scope of the invention. In the drawings, the like reference numerals represent identical elements between the drawings. As indicated above, the present invention provides an energy generating system comprising a gas turbine system having a compressor that creates an excess of airflow. Embodiments of the invention provide ways to employ excess airflow to improve the output and value of the power generation system.
    [0003] Referring to Figure 1, the proposed schematic representation shows a power generation system 100 according to embodiments of the invention. The system 100 includes a gas turbine system 102. The gas turbine system 102 may include, among other components, a turbine component 104, an integrated compressor 106 and a combustion device 108. The term "integrated compressor" 106 herein denotes a compressor 106 and a turbine component 104 which can be secured to one another, inter alia by means of a common rotary compressor / turbine shaft 110 (sometimes called rotor 110). This structure differs from many compressors which are driven separately, and which are not integral with the turbine component 104. The combustor 108 may comprise any combustion system known or further developed, generally including a combustion region. and a fuel nozzle assembly. The combustor 108 may take the form of an annular combustion system, or a cylindrical combustion system (as shown in the figures). In operation, air is supplied to the combustion device 108 from the integrated compressor 106 and a fuel, such as natural gas. Solvents may also be optionally introduced into the combustor 108, in any known or later manner.
    [0004] Air entering the integrated compressor 106 can pass into any input filter box 120 currently known or developed later. As is known, the combustor 108 is arranged to supply hot combustion gases to the turbine component 104 by combustion of the fuel and air mixture. In the turbine component 104, the energy of the hot combustion gases is converted into work, a portion of which can be used to drive the compressor 106 through the rotary shaft 110, the remainder being available as work useful for driving a load which may be, but is not limited to, a generator 122 for generating electricity, and / or another turbine via the rotary shaft 110 (or an extension of the rotary shaft 110). A starter motor 112, for example, but not limited to, a conventional starter motor or a load switched inverter motor (LCI) (shown) may also be coupled to the rotary shaft 110 for starting. of the gas turbine system 102 in any conventional manner. The turbine component 104 may comprise any turbine currently known or later developed for converting a flow of hot combustion gases into work via the rotary shaft 110. In one embodiment, the turbine system The gas 102 may include an MS7001FB model, sometimes referred to as a 7FB engine, available from General Electric Company, Greenville (United States of America). However, the present invention is not limited to a particular gas turbine system, and may be implemented in connection with other systems, for example the MS7001FA (7FA) and MS9001FA (9FA) models of the General Electric Company. Unlike conventional gas turbine system models, the integrated compressor 106 has a flow capacity greater than the inlet capacity of the turbine component 104 and / or the first combustion device 108. Indeed, the compressor 106 is an improved compressor, compared to a compressor configured to fit the combustor 108 and the turbine component 104. The term "capacitance" as used herein refers to a throughput capacity. For example, an initial compressor of the gas turbine system 102 may have a maximum flow capacity of about 487 kilograms per second (kg / s) (1.075 pounds per second (lb / s)) and the turbine component 104 can have a capacity of substantially equal maximum flow, that is to say about 487 kg / s. In this case, on the other hand, the compressor 106 has replaced the initial compressor and may have an increased maximum flow capacity, for example equal to about 544 kg / s (1200 lb / s), while the turbine component 104 continues. to have a capacity of maximum flow equal for example to 487 kg / s approximately. (If necessary, the starter motor 112 can also be improved, for example by being an LCI motor, as shown, to support the increased power requirements for starting the integrated compressor 106). Therefore, the turbine component 104 can not take advantage of the full capacity of the compressor 106, and an excess of airflow 200 is created by the compressor 106 over a maximum capacity, e.g. Likewise, the flow capacity of the integrated compressor 106 may exceed the maximum inlet capacity of the combustor 108. Similarly, the output power of the turbine component 104, exposed to the full capacity of flow rate of the integrated compressor 106, could exceed a maximum input allowed for the generator 122. Although specific illustrative flow rates have been given, it is emphasized that the flow capacities can vary greatly depending on the system of delivery. gas turbine and new built-in compressor with high capacity 106 used. As will be seen below, the present invention provides various embodiments for the power generation system 100 to use excess airflow in other parts of the power generation system 100. As can be seen in an embodiment illustrated in FIG. 1, the power generation system 100 may optionally take the form of a combined cycle power plant having a steam turbine system 160. Steam turbine system 160 may include any steam turbine arrangement currently known or further developed. In the example shown, high pressure sections 10 (HP), intermediate pressure (IP) and low pressure (LP) are shown; however, not all of them are necessary in all cases. As is known to those skilled in the art, in operation, steam enters through an inlet of the steam turbine section (s) and is channeled through static vanes, which direct the downstream steam against blades coupled to the steam turbine section (s). a rotary shaft 162 (rotor). The steam can pass through the remaining stages by impressing a force on the vanes which causes rotation of the rotary shaft 162. At least one end of the rotary shaft 162 can be connected to a load or machine such as, but without To limit this, a generator 166 and / or another turbine, for example a gas turbine system 102 or other gas turbine system. The steam for the steam turbine system 160 may be produced by one or more steam generators 168, i.e., heat recovery steam generators (HRSGs). The HRSG generator 168 may be coupled, for example, to an exhaust 172 of the gas turbine system 102. After passing through the HRSG generator 168, the flue gas stream, now devoid of heat, can be exhausted via any which emission management system 178, for example, stacks, SCRs, nitrous oxide filters, and the like. Although Figure 1 shows a combined cycle embodiment, it will be appreciated that the steam turbine system 160 including the HRSG generator 168 may be omitted. In this case, the escapement 172 would be transmitted directly to the emission management system 178 or used in other processes. The power generation system 100 may also include any control system 180 currently known or further developed to control its various components. Although shown away from the components, it is to be understood that the control system 180 is electrically coupled to all components and their respective controllable elements, eg, valves, pumps, motors, sensors, gears, controls generator, etc. Referring back to the details of the gas turbine system 102, as noted herein, the integral compressor 106 has a flow capacity greater than the inlet capacity of the turbine component 104 and / or the combustion device 108. This creates an excess of airflow 200. As shown, the excess airflow 200 can be formed by drawing air from the compressor 106. In one embodiment, a first air flow system is provided. The control valve 202 controls the flow rate of the excess airflow 200 along an excess airflow path 250 which leads to a makeup gas turbine system 272. The first control system The control valve 202 may include any number of valves required to supply the desired excess airflow 200, for example one, two (as shown) or more than two. In one embodiment, excess airflow 200 may be withdrawn from the integral compressor 106 at a discharge 204 thereof using a compressor discharge control valve 206. More specifically, the compressor discharge control valve 206 controls a first portion of excess airflow 200 taken at the discharge 204 of the integrated compressor 106. In this case, another upstream valve 210 may be omitted. In another embodiment, however, the excess airflow 200 may be withdrawn at one or more stages of the compressor 106 as required, for example at one or more locations upstream. discharge 204, at the discharge 204 and at one or more locations upstream of the discharge, etc., using appropriate associated valves and control systems. In this case, the first control valve system 202 may further include one or more upstream control valves (210) that control a second portion of the excess airflow 200 taken at one or more stages (s). ) of the integrated compressor 106 upstream of the discharge 204. Any number of upstream control valves 210 can be used in the first control valve system 202 to provide any excess airflow 200 desired to from the integrated compressor 106, that is to say with the desired pressure, the desired flow rate, the desired volume, etc. The compressor control valve 210 may be omitted when one or more other upstream control valve (s) 210 provide the desired excess airflow 200. The first control valve system 202 may also include at least one sensor 220 for measuring a flow rate of each portion of the excess airflow, each sensor 220 being operably coupled to a respective control valve or assembly control system 180. The control valve system 202 may include any industrial control currently known or later developed for the automated operation of the various control valves shown.
    [0005] The excess airflow 200 ultimately passes along an excess airflow path 250, which may include one or more pipes, leading to a makeup gas turbine system 272. Although the diagram shows an excess of airflow directed toward the make-up gas turbine system 272 in a single pipe, it is understood that the excess airflow can be directed to one or Several locations of the system 272. The makeup gas turbine system 272 may include an auxiliary combustion device 274 arranged to supply hot combustion gases to a makeup turbine component 276. The device The auxiliary combustion device 274 may comprise any form of combustion device described with respect to the combustion device 108 which is capable of utilizing the excess airflow 200 (or the increased excess gas flow rate). (Fig. 2) (described herein)) to create and supply comb In a similar manner, the makeup turbine component 276 may comprise any form of turbine component described with respect to the turbine component 104. As shown, the component The auxiliary turbine 276 is operatively coupled to an auxiliary generator 278, which may be referred to herein as an "auxiliary generator" as it may be different from the generator 122 coupled to the gas turbine system 102. The backup generator 278 may also be different from the generator 166 of the steam turbine system 160. Alternatively, the generator 274 may be the same as the generator 122 or the generator 166. In all cases, the excess flow of Air 200 (or the increased excess gas flow 270 (FIG. 2)) can be employed to generate energy through the make-up gas turbine system 272, which allows the use of the gas turbine. excess of capacity of the integrated compressor 106 3033838 13 effectively. An exhaust 280 of the makeup gas turbine system 272 may be directed to an exhaust 172 of the turbine component 104 for the purpose of creating steam in the HRSG generator 168.
    [0006] With reference to FIG. 2, the power generation system 100 may also optionally include an ejector 252 positioned in the excess airflow path 250 to utilize the excess airflow 200 as a force. The additional gas 254 forms with the excess air flow 200 an excess of the increased gas flow 270 which is transmitted to the gas turbine system. In other words, the increased excess gas flow 270 is supplied to the makeup gas turbine system 272. The increased increased gas flow 270 provides an increased total air / gas mass. to the supplemental combustion device 274, and may allow additional energy generation using the generator 278. Additional mass flow to the HRSG generator 168 via the exhaust 280 may also be considered, which increases the steam output of the generator 20 HRSG 168. The eject 252 may take the form of any pump that uses a flow of motor fluid to pump a suction fluid, i.e. additional gas 254. Here, the ejector 252 uses the excess of air stream 200 as a driving fluid for adding additional gas 254 to excess airflow 200, i.e., drawing additional gas from an additional gas source 256 along a suction side flow path 258. The additional gas source 256 can take various forms. In one embodiment, the additional gas source 256 may take the form of the input filter housing 120 of the integrated compressor 106. In all cases, the suction side flow path 258 leading to the ejector 252 may be coupled to the input filter housing 120 of the integrated compressor 106 (shown in broken lines) such that the additional gas 254 includes ambient air. Here, the additional gas 254 is in the form of ambient air. In another embodiment, the additional gas 254 may comprise ambient air from an additional gas source 256 other than the inlet filter housing 120, for example another filter housing, air directly from the environment but subsequently filtered into the flow path 258, etc. In all the aforementioned embodiments, the increased excess gas flow 270 comprises mainly air, ie it is an excess of increased airflow. However, in another embodiment, the additional gas 254 may comprise a process gas such as, but not limited to, synthesis gas from a refinery, blast furnace gas, methane from waste dumps, etc. The additional gas 254, in another embodiment, may also include the exhaust of an engine, for example a combustion engine, a diesel engine, another gas turbine system, etc. A second control valve system 260 may be placed in the suction side flow path 258 to control an additional gas flow 254 entering the ejector 252. The second control valve system 260 may include a control valve. 262 which can operate to control the amount of additional gas 254 entering the ejector 252. The second control valve system 260 may also include at least one sensor 220 for measuring an additional gas flow rate 254 in the side flow path 258, the sensor being operatively coupled to the second control valve system 260 for measuring an additional gas flow rate 254. As also shown, an exhaust 172 of the turbine component 104 may be introduced into the HRSG generator 168 for create steam for the steam turbine system 160. When the exhaust 280 of the gas turbine system Refill 272 is at least as hot as the exhaust 172 of the turbine component 104, it can be added to the exhaust 172 to more efficiently create steam in the generator HRSG 168. When the system exhaust 280 The makeup gas turbine 272 is not hotter than the exhaust 172 of the turbine component 104, it can be used to increase the mass flow to the generator HRSG 168 or elsewhere in the power generation system 100 or discharged through the emission control system 178, bypassing the HRSG generator 168. As shown, the HRSG generator 168 may also supply steam to a cogeneration steam load 170. The cogeneration steam load 170 may for example, include steam sent to a petrochemical plant, steam for district heating, steam for oil extraction in "tar sands", etc. If each control valve system 202, 260 is further investigated, each of their control valves may be positioned in any position between open and closed to provide the desired partial flow rates to the components cited. Further, while a passage to each component is shown after each control valve, it will be appreciated that other control manifolds and valves may be provided to further dispense the respective portion of the excess airflow 200 to different sub-parts, for example several inputs to the ejector 252, 3033838 16 etc. Each sensor 220 may be operably coupled to control valve system (s) 202, 260 and control system 180 to perform automated control in a known manner. Other sensors 220 for measuring the flow rate 5 can be placed wherever necessary in the power generation system 100. The control valve systems 202, 260, and thus the flow rate of the excess flow of The air 200 and the operation of the ejector 252 can be controlled using any currently known or later developed industrial control device 10 which may be part of an overall control system 180 of the production system. The control system 180 can manage the operation of all the various components of the power generation system 100 in a known manner, including the control of the control valve systems 202, 260. Power generation 100 includes a gas turbine system 102 having an integrated compressor 106 which creates an excess of airflow 200 which has several advantages over conventional systems. For example, the compressor 106 can improve the maximum power output, the base power, and the warm-weather power of the power generation system 100 at a lower cost than an improvement of all the compressors in the system, which can be very expensive when using multiple gas turbines. In addition, the embodiments of the invention reduce the relative cost of an improved compressor, i.e., the compressor 106, and further improve the economics and attractiveness of an improved compressor by providing a means of effectively consuming a greater part of the excess airflow. Further, the power generation system 100 including the integrated compressor 106 extends the operational area of the system 100 by improving the project economics in cases where any one or more of the following illustrative subsystems is underwritten. -Dimensioned: turbine component 104, generator 122, transformer (not shown), gears, HRSG generator 168, steam turbine system 160, steam turbine control valves, etc. In this way, the system 100 provides an improved case for improving a single compressor, for example in a combined cycle system with a single gas turbine and a single steam turbine (CC lx1), with respect to the case where the we do not do anything. When ejector 252 (FIG. 2) is present, the aforementioned advantages of the increased excess gas flow 270 to the makeup gas turbine system 272, such as the additional mass flow and the additional power output, can be achieved. to be considered. An additional mass flow to the HRSG generator 168 can also be achieved using the ejector 252. The terminology used herein is for the sole purpose of describing particular embodiments and is not intended to limit the invention. As used herein, the singular forms "one", "one", "the" and "the" are intended to include plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises" and / or "comprising", when used in the present description, indicate the presence of elements, integers, steps, operations, organs and / or components mentioned, but do not prevent the presence or addition of one or more other elements, integers, steps, operations, organs, components and / or groups thereof. The structures, materials, corresponding acts and equivalents of any means or steps as well as the functions herein are intended to include any structure, material, or act for performing the function in association with other cited elements. The description of the present invention has been presented for purposes of illustration and description, but is not intended to be exhaustive or limited to the description in the form described. Many modifications and variations will occur to those of ordinary skill in the art without departing from the scope and spirit of the invention. The embodiment has been chosen and described in order to best explain the principles of the invention and the practical application, and to enable others with ordinary skill in the art to understand the invention for various modes. embodiment with various modifications, appropriate for the particular use envisaged.
    [0007] 15 3033838 19 Nomenclature 100 Power Generation System 5 Gas turbine system 102 Turbine component 104 Built-in compressor 106 Combustion device 108 Rotary shaft 110 10 Starter motor 112 Input filter housing 120 Generator 122, 166 System Steam Turbine 160 Rotary Shaft 162 15 Steam Generators 168 Steam Load 170 Exhaust 172, 280 Emissions Management System 178 Control System 180 20 Air Flow 200 Control Valve System 202 Discharge Amount 204 Control Valve Discharge 206 Upstream Control Valves 210 25 Sensor 220 Excess Air Flow Path 250 Ejector 252 Additional Gas 254 Additional Gas Source 256 30 Suction Side Flow Path 258 3033838 20 Second Control Valve System 260 Control Valve 262 Excess Gas Flow Increased 270 Gas Turbine System 272 5 Auxiliary Combustion Device 274 Auxiliary Turbine Component 276 G additional generator 278
    权利要求:
    Claims (15)
    [0001]
    REVENDICATIONS1. A power generation system (100) comprising a generator (122, 166); a gas turbine system (102) for powering the generator (122, 166), the gas turbine system (102) comprising a turbine component (104), an integrated compressor (106) and a combustion device (108) ) into which air from the integrated compressor (106) and fuel is sent, the combustion device (108) being arranged to send hot combustion gases to the turbine component (104), and the integrated compressor (106) having a flow capacity greater than an intake capacity of at least one of the combustion device (108) and the turbine component (104), thereby creating an excess of airflow (200) ); A makeup gas turbine system (272) comprising an auxiliary combustion device (274) arranged to supply hot combustion gases to a makeup turbine component (276) thereof, the a makeup turbine (276) being operatively coupled to an auxiliary generator (278); and a first control valve system (202) which controls the flow of excess airflow (200) along an excess airflow path (250), wherein the path excess airflow (250) delivers the excess airflow (200) to an inlet of the auxiliary combustion device (274), and the auxiliary combustion device (274) burns excess airflow (200) with a fuel to create hot combustion gases for the makeup turbine component (276). 3033838 22
    [0002]
    An energy generating system (100) according to claim 1, wherein an exhaust (172, 280) of the turbine component (104) feeds a heat recovery steam generator (168) (HRSG) to create steam for a steam turbine system (160).
    [0003]
    The power generating system (100) of claim 2, wherein the HRSG generator also provides steam to a cogeneration steam charge (170).
    [0004]
    The power generation system (100) according to claim 1, wherein the first control valve system (202) comprises a compressor discharge control valve (206) which controls a first portion of the excess of airflow (200) taken at a discharge of the integrated compressor (106), and an upstream control valve that controls a second portion of the excess airflow (200) taken at a compressor stage integrated (106) upstream of the discharge.
    [0005]
    The power generating system (100) of claim 4, further comprising at least one sensor (220) for measuring a flow rate of each portion of the excess airflow (200), each sensor (220). ) being operably coupled to a respective control valve.
    [0006]
    The power generation system (100) of claim 4, further comprising an ejector (252) positioned in the excess airflow path (250) to utilize the excess airflow ( 200) as a driving force for increasing the excess air flow (200) with an additional gas (254), the ejector creating an increased excess gas flow (270), wherein the excess flow path of the air (250) sends the increased excess gas flow (270) to the inlet of the auxiliary combustion device (274), and the auxiliary combustion device (274) burns the excess increased gas flow (270) with a fuel to create hot combustion gases for the makeup turbine component (276).
    [0007]
    The power generation system (100) according to claim 6, wherein the ejector (252) comprises a suction side flow path (258), and further comprising a second control valve system (260). ) in the suction side flow path (258) which controls an additional gas flow (254) entering the ejector (252). 10
    [0008]
    The power generation system (100) of claim 7, further comprising a sensor (220) for measuring an additional gas flow (254) in the suction side flow path (258), the sensor (220). ) being operably coupled to the second control valve system (260). 15
    [0009]
    The power generation system (100) of claim 7, wherein the suction side flow path (258) is fluidly coupled to an input filter of the integrated compressor (106).
    [0010]
    The power generation system (100) of claim 1, wherein the generator (122, 166) is different from the booster generator (278).
    [0011]
    The power generating system (100) of claim 6, wherein the additional gas (254) comprises ambient air. 25
    [0012]
    The power generating system (100) of claim 6, wherein the additional gas (254) comprises a process gas.
    [0013]
    The power generation system (100) of claim 6, wherein the additional gas (254) comprises a synthesis gas. 3033838 24
    [0014]
    The power generating system (100) of claim 6, wherein the additional gas (254) comprises an exhaust (172, 280) from an engine.
    [0015]
    The power generation system (100) according to claim 1, further comprising an ejector (252) positioned in the excess airflow path (250) to utilize excess airflow. (200) as a motive force for increasing the excess air flow (200) with an additional gas (254), the ejector creating an increased gas flow overflow (270), wherein the excess path of the airflow (250) supplies the excess of the increased gas flow (270) to the inlet of the auxiliary combustion device (274), and the auxiliary combustion device (274) burns the excess increased gas flow (270) with a fuel to create hot combustion gases for the makeup turbine component (276).
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    US9863285B2|2018-01-09|
    JP2016176480A|2016-10-06|
    JP6877884B2|2021-05-26|
    DE102016204241A1|2016-09-22|
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    法律状态:
    2017-03-27| PLFP| Fee payment|Year of fee payment: 2 |
    2018-03-26| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-28| PLSC| Search report ready|Effective date: 20180928 |
    2020-04-17| RX| Complete rejection|Effective date: 20200309 |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/662,836|US9863285B2|2015-03-19|2015-03-19|Power generation system having compressor creating excess gas flow for supplemental gas turbine system|
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