[특허]System and method of control for a gas turbine engine

General Electric Company

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

System and method of control for a gas turbine engine

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-001/00 F01D-021/00 F23N-005/18 F23R-003/26 F23R-003/28 F23C-009/00 F23R-003/50 F02C-007/04 F02C-007/22
출원번호	US-0599750 (2015-01-19)
등록번호	US-9863267 (2018-01-09)
발명자 / 주소	O'Dea, Dennis M. Minto, Karl Dean Huntington, Richard A. Dhanuka, Sulabh K. Mittricker, Franklin F.
출원인 / 주소	General Electric Company
대리인 / 주소	Fletcher Yoder P.C.
인용정보	피인용 횟수 : 1 인용 특허 : 529

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A system includes plurality of combustors and a distributed flow measurement system coupled to the plurality of combustors. Each combustor of the plurality of combustors includes one or more oxidant passages and one or more fuel passages. The distributed flow measurement system is configured to measure an oxidant flow rate for a respective oxidant passage of the one or more oxidant passages of the respective combustor based at least in part on an oxidant pressure drop along the respective oxidant passage, and the distributed flow measurement system is co...

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1. A system comprising: a first combustor, comprising: a plurality of first oxidant passages configured to supply a first oxidant flow to the first combustor;a plurality of first fuel passages configured to supply a first fuel flow to the first combustor;a plurality of first oxidant pressure sensors, wherein each first oxidant pressure sensor of the plurality of first oxidant pressure sensors is fluidly coupled to a respective first oxidant passage of the plurality of first oxidant passages and is configured to transmit a respective first oxidant pressure signal corresponding to a first oxidant pressure of the respective first oxidant passage; anda plurality of first fuel pressure sensors, wherein each first fuel pressure sensor of the plurality of first fuel pressure sensors is fluidly coupled to a respective first fuel passage of the plurality of first fuel passages and is configured to transmit a respective first fuel pressure signal corresponding to a first fuel pressure of the respective first fuel passage; anda controller coupled to the plurality of first oxidant pressure sensors and to the plurality of first fuel pressure sensors, wherein the controller is configured to determine a first oxidant flow rate through each first oxidant passage of the plurality of first oxidant passages based at least in part on the respective first oxidant pressure signal and a first reference oxidant pressure, and the controller is configured to determine a first fuel flow rate through each first fuel passage of the plurality of first fuel passages based at least in part on the respective first fuel pressure signal and a first reference fuel pressure. 2. The system of claim 1, wherein the first combustor comprises an annular combustor. 3. The system of claim 1, comprising a second combustor, comprising: a plurality of second oxidant passages configured to supply a second oxidant flow to the second combustor;a plurality of second fuel passages configured to supply a second fuel flow to the second combustor;a plurality of second oxidant pressure sensors, wherein each second oxidant pressure sensor of the plurality of second oxidant pressure sensors is fluidly coupled to a respective second oxidant passage of the plurality of second oxidant passages and is configured to transmit a respective second oxidant pressure signal corresponding to a second oxidant pressure of the respective second oxidant passage; anda plurality of second fuel pressure sensors, wherein each second fuel pressure sensor of the plurality of second fuel pressure sensors is fluidly coupled to a respective second fuel passage of the plurality of second fuel passages and is configured to transmit a respective second fuel pressure signal corresponding to a second fuel pressure of the respective second fuel passage;wherein the controller is configured to determine a second oxidant flow rate through each second oxidant passage of the plurality of second oxidant passages based at least in part on the respective second oxidant pressure signal and a second reference oxidant pressure, and the controller is configured to determine a second fuel flow rate through each second fuel passage of the plurality of second fuel passages based at least in part on the respective second fuel pressure signal and a second reference fuel pressure. 4. The system of claim 1, wherein the first combustor comprises a plurality of first fuel nozzles, the plurality of first fuel nozzles comprises the respective plurality of first fuel passages, and the plurality of first fuel nozzles comprises pre-mix nozzles, diffusion nozzles, or any combination thereof. 5. The system of claim 1, wherein the first reference oxidant pressure is based at least in part on a pressure of an oxidant supply system fluidly coupled to the plurality of first oxidant passages, and the first reference fuel pressure is based at least in part on a pressure of a fuel supply fluidly coupled to the plurality of first fuel passages. 6. The system of claim 1, wherein the first reference oxidant pressure is the same as the first reference fuel pressure, and the first reference oxidant pressure is based at least in part on a pressure of an oxidant supply system fluidly coupled to the plurality of first oxidant passages, a fuel supply fluidly coupled to the plurality of first fuel passages, a head end pressure, a combustor liner pressure, or a combustion chamber pressure, or any combination thereof. 7. The system of claim 1, wherein the controller is configured to control the first fuel flow to the first combustor based at least in part on the determined first oxidant flow rate and the determined first fuel flow rate to the first combustor. 8. The system of claim 1, wherein the controller is configured to control the first oxidant flow to the first combustor based at least in part on the determined first oxidant flow rate and the determined first fuel flow rate to the first combustor. 9. The system of claim 1, comprising a lambda sensor configured to measure an oxidant concentration in an exhaust gas from the first combustor, wherein the controller is configured to control at least one of the first fuel flow or the first oxidant flow to the first combustor based at least in part on the measured oxidant concentration, the determined first fuel flow rate, and the determined first oxidant flow rate. 10. The system of claim 1, comprising a gas turbine engine having the first combustor, wherein the controller is configured to control the first oxidant flow and the first fuel flow based at least in part on a target equivalence ratio between 0.95 and 1.05. 11. The system of claim 10, wherein the gas turbine engine comprises a stoichiometric exhaust gas recirculation (SEGR) gas turbine engine. 12. A system comprising: a plurality of combustors, wherein each combustor comprises one or more oxidant passages and one or more fuel passages; anda distributed flow measurement system coupled to the plurality of combustors, wherein the distributed flow measurement system is configured to measure an oxidant flow rate for a respective oxidant passage of the one or more oxidant passages of the respective combustor based at least in part on an oxidant pressure drop along the respective oxidant passage, and the distributed flow measurement system is configured to measure a fuel flow rate for a respective fuel passage of the one or more fuel passages of the respective combustor based at least in part on a fuel pressure drop along the respective fuel passage. 13. The system of claim 12, wherein each combustor of the plurality of combustors comprises: a fuel sampling manifold fluidly coupled to the one or more fuel passages of the respective combustor via one or more fuel valves or a multiple port fuel scanning valve, wherein the distributed flow measurement system is configured to control the one or more fuel valves or the multiple port fuel scanning valve to cyclically sample to the fuel sampling manifold a respective fuel flow through each fuel passage of the one or more fuel passages;a fuel manifold pressure sensor coupled to the fuel sampling manifold, wherein the fuel manifold pressure sensor is configured to sense a respective fuel pressure of the respective fuel flow sampled to the fuel sampling manifold;an oxidant sampling manifold fluidly coupled to the one or more oxidant passages of the respective combustor via one or more oxidant valves or a multiple port oxidant scanning valve, wherein the distributed flow measurement system is configured to control the one or more oxidant valves or the multiple port oxidant scanning valve to cyclically sample to the oxidant sampling manifold a respective oxidant flow through each oxidant passage of the one or more oxidant passages; andan oxidant manifold pressure sensor coupled to the oxidant sampling manifold, wherein the oxidant manifold pressure sensor is configured to sense a respective oxidant pressure of the respective oxidant flow sampled to the oxidant sampling manifold. 14. The system of claim 12, wherein the distributed flow measurement system comprises: a plurality of oxidant pressure sensors, wherein each oxidant pressure sensor of the plurality of oxidant pressure sensors is coupled to a corresponding oxidant passage of the one or more oxidant passages of each combustor of the plurality of combustors; anda plurality of fuel pressure sensors, wherein each fuel pressure sensor of the plurality of fuel pressure sensors is coupled to a corresponding fuel passage of the one or more fuel passages of each combustor of the plurality of combustors. 15. The system of claim 14, wherein the distributed flow measurement system is configured to measure the oxidant flow rate and the fuel flow rate for each combustor of the plurality of combustors without constricting an oxidant flow through the one or more oxidant passages and without constricting a fuel flow through the one or more fuel passages. 16. The system of claim 12, wherein each oxidant passage of the one or more oxidant passages comprises an oxidant flow discharge coefficient, and each fuel passage of the one or more fuel passages comprises a fuel flow discharge coefficient, wherein the distributed flow measurement system is configured to measure the oxidant flow rate for each oxidant passage of the one or more oxidant passages based at least in part on the respective oxidant flow discharge coefficient, and the distributed measurement system is configured to measure the fuel flow rate for each fuel passage of the one or more fuel passages based at least in part on the respective fuel flow discharge coefficient. 17. The system of claim 12, wherein the plurality of combustors comprises pre-mix fuel nozzles, diffusion fuel nozzles, or any combination thereof. 18. A method of operating a combustor with a controller programmed to execute control of a process comprising: conveying an oxidant flow through a plurality of oxidant passages;conveying a fuel flow through a plurality of fuel passages;measuring an oxidant pressure of the oxidant flow through each oxidant passage of the plurality of oxidant passages;measuring a fuel pressure of the fuel flow through each fuel passage of the plurality of fuel passages;determining an oxidant flow rate of the oxidant flow through each oxidant passage of the plurality of oxidant passages based at least in part on the respective oxidant pressure and a reference pressure;determining a fuel flow rate of the fuel flow through each fuel passage of the plurality of fuel passages based at least in part on the respective fuel flow and the reference pressure, wherein the reference pressure comprises a head end pressure in a head end portion of the combustor or a combustion chamber pressure in the combustor; andcontrolling a ratio of the fuel flow to the oxidant flow conveyed to the combustor based at least in part on the oxidant flow rate and the fuel flow rate. 19. The method of claim 18, comprising: determining the oxidant flow rate of the oxidant flow through each oxidant passage of the plurality of oxidant passages utilizing oxidant passage data stored in a memory; anddetermining the fuel flow rate of the fuel flow through each fuel passage of the plurality of fuel passages utilizing fuel passage data stored in the memory. 20. The method of claim 18, comprising: determining the oxidant flow rate of the oxidant flow through each oxidant passage of the plurality of oxidant passages based at least in part on an oxidant flow discharge coefficient of the respective oxidant passage; anddetermining the fuel flow rate of the fuel flow through each fuel passage of the plurality of fuel passages based at least in part on a fuel flow discharge coefficient of the respective fuel passage. 21. The method of claim 18, comprising controlling the ratio of the fuel flow to the oxidant flow to an equivalence ratio between 0.95 to 1.05. 22. The method of claim 18, comprising: measuring an oxidant concentration in an exhaust flow from the combustor; andcontrolling the ratio of the fuel flow to the oxidant flow based at least in part on the oxidant concentration. 23. The method of claim 18, comprising identifying an oxidant flow anomaly in a respective oxidant passage of the plurality of oxidant passages based at least in part on the oxidant pressure of the respective oxidant passage or identifying a fuel flow anomaly in a respective fuel passage of the plurality of fuel passages based at least in part on the fuel pressure of the respective fuel passage. 24. The method of claim 18, comprising: measuring an oxidant temperature of the oxidant flow through each oxidant passage of the plurality of oxidant passages;measuring a fuel temperature of the fuel flow through each fuel passage of the plurality of fuel passages;determining the oxidant flow rate of the oxidant flow through each oxidant passage based at least in part on the respective oxidant temperature; anddetermining the fuel flow rate of the fuel flow through each fuel passage based at least in part on the respective fuel temperature. 25. The system of claim 5, wherein the first combustor comprises: a plurality of fuel nozzles, wherein each fuel nozzle of the plurality of fuel nozzles is coupled to a respective first oxidant passage of the plurality of first oxidant passages and to a first fuel passage of the plurality of first fuel passages, wherein each fuel nozzle comprises: an oxidant pressure tap comprising a respective first oxidant pressure sensor of the plurality of first oxidant pressure sensors; anda fuel pressure tap comprising a respective first fuel pressure sensor of the plurality of first fuel pressure sensors.

이 특허에 인용된 특허 (529)

이 특허를 인용한 특허 (1)

Frey, George Frederick, Variable flow compressor of a gas turbine.

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System and method of control for a gas turbine engine

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