Combustor with staged, axially offset combustion
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/34
F23R-003/26
F23R-003/12
F23R-003/46
F23R-003/28
F02C-003/04
출원번호
US-0411274
(2017-01-20)
등록번호
US-10006637
(2018-06-26)
발명자
/ 주소
Lee, Fei Philip
출원인 / 주소
Woodward, Inc.
대리인 / 주소
Fish & Richardson P.C.
인용정보
피인용 횟수 :
0인용 특허 :
20
초록▼
In some aspects, a gas turbine combustor assembly is arranged around a longitudinal axis. The gas turbine combustor comprises a first fuel/air mixer assembly, the mixer assembly comprising a first fuel injector and a plurality of first mixer elements, each mixer element defining an air flow passage
In some aspects, a gas turbine combustor assembly is arranged around a longitudinal axis. The gas turbine combustor comprises a first fuel/air mixer assembly, the mixer assembly comprising a first fuel injector and a plurality of first mixer elements, each mixer element defining an air flow passage therethrough having an outlet in a first plane. A second fuel/air mixer assembly comprises a second fuel injector and a plurality of second mixer elements, and each second mixer element defines an air flow passage therethrough having an outlet in a second plane, longitudinally offset from the first plane.
대표청구항▼
1. A method, comprising: supplying air without fuel at an outlet of a first fuel/air mixer assembly in a gas turbine combustor assembly; andconcurrently, burning a fuel and air mixture at an outlet of a second, adjacent fuel/air mixer assembly in the gas turbine combustor assembly, the second mixer
1. A method, comprising: supplying air without fuel at an outlet of a first fuel/air mixer assembly in a gas turbine combustor assembly; andconcurrently, burning a fuel and air mixture at an outlet of a second, adjacent fuel/air mixer assembly in the gas turbine combustor assembly, the second mixer assembly having an outlet in a second plane that is offset in the direction of a longitudinal axis of the gas turbine combustor assembly relative to a first plane of the outlet of the first fuel/air mixer assembly. 2. The method of claim 1, comprising, in response to a change in operating conditions, concurrently, while burning the fuel and air mixture at the outlet of the second fuel/air mixer assembly, burning a fuel and air mixture at the outlet of the first fuel/air mixer assembly. 3. The method of claim 2, where concurrently burning the fuel and air mixtures at the outlets of the first and second fuel/air mixer assemblies comprises directing a first flow of fuel toward the first fuel/air mixer assembly along a first set of fuel circuits and directing a second flow of fuel toward the second fuel/air mixer assembly along a second set of fuel circuits that is separate and independent of the first. 4. The method of claim 3, where the first and second flows of fuel have different flow rates. 5. The method of claim 1, where supplying air to the outlet of the first fuel/air mixer assembly comprises directing air toward a plurality of first fuel/air mixer assemblies, and where burning the fuel and air mixture at the outlet of the second fuel/air mixer comprises directing air toward a plurality of second fuel/air mixer assemblies nested in a ring with the first fuel/air mixer assemblies. 6. The method of claim 5, where the first and second fuel/air mixer assemblies are arranged in alternating order around the ring. 7. The method of claim 6, where the second fuel/air mixer assemblies are recessed relative to the first fuel/air mixer assemblies in the direction of the longitudinal axis. 8. The method of claim 1, where the second fuel/air mixer assembly comprises a plurality of second fuel/air mixer elements arranged around a center location on the longitudinal axis, and where burning the fuel and air mixture comprises directing fuel toward a fuel injector tip residing at the center location. 9. The method of claim 8, where the plurality of second fuel/air mixer elements is symmetrically arranged around the center location. 10. The method of claim 8, where the first fuel/air mixer assembly comprises a plurality of first fuel/air mixer elements, the plurality of first fuel/air mixer elements comprising a different number of mixer elements than the plurality of second fuel/air mixer elements. 11. The method of claim 1, where burning the fuel and air mixture at the outlet of the second fuel/air mixer assembly comprises forming a flame cone extending to a length in the direction of the longitudinal axis, and where the second plane is offset by a distance substantially equal to the length of the flame cone. 12. The method of claim 1, where burning the fuel and air mixture at the outlet of the second fuel/air mixer assembly comprises conveying a flow of air through converging-diverging venturi passage. 13. The method of claim 12, where burning the fuel and air mixture at the outlet of the second fuel/air mixer assembly further comprises inducing swirl in the flow of air as the air is conveyed through the converging-diverging venturi passage. 14. A method, comprising: supplying air without fuel at an outlet of a first fuel/air mixer assembly in a gas turbine combustor assembly having a longitudinal axis; andconcurrently, burning a fuel and air mixture at an outlet of a second, adjacent fuel/air mixer assembly in the gas turbine combustor assembly to form a flame cone extending to a length in a direction of the longitudinal axis, the second mixer assembly having an outlet in a second plane that is recessed in the direction relative to a first plane of the outlet of the first fuel/air mixer assembly,where the second plane is recessed relative to the first plane by a distance sufficient to at least partially shield the flame cone from airflow emanating from the outlet of the first fuel/air mixing assembly. 15. The method of claim 14, where the second plane is recessed by a distance substantially equal to the length of the flame cone. 16. The method of claim 14, comprising, in response to a change in operating conditions, concurrently, while burning the fuel and air mixture at the outlet of the second fuel/air mixer assembly, burning a fuel and air mixture at the outlet of the first fuel/air mixer assembly. 17. The method of claim 16, where concurrently burning the fuel and air mixtures at the outlets of the first and second fuel/air mixer assemblies comprises directing a first flow of fuel toward the first fuel/air mixer assembly along a first set of fuel circuits and directing a second flow of fuel toward the second fuel/air mixer assembly along a second set of fuel circuits that is separate and independent of the first. 18. The method of claim 17, where the first and second flows of fuel have different flow rates. 19. The method of claim 14, where supplying air to the outlet of the first fuel/air mixer assembly comprises directing air toward a plurality of first fuel/air mixer assemblies, and where burning the fuel and air mixture at the outlet of the second fuel/air mixer comprises directing air toward a plurality of second fuel/air mixer assemblies nested in a ring with the first fuel/air mixer assemblies. 20. The method of claim 14, where the second fuel/air mixer assembly comprises a plurality of second fuel/air mixer elements arranged around a center location on the longitudinal axis, and where burning the fuel and air mixture comprises directing fuel toward a fuel injector tip residing at the center location.
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이 특허에 인용된 특허 (20)
Hicks, Paul G.; Lee, Fei Philip, Active thermal protection for fuel injectors.
Lee Fei P. (Novi MI) Guzowski Mike (Canton MI), Fuel injector assembly with first and second fuel injectors and inner, outer, and intermediate air discharge chambers.
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