IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0653258
(2012-10-16)
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등록번호 |
US-8789375
(2014-07-29)
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발명자
/ 주소 |
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
0 인용 특허 :
34 |
초록
▼
A method of using a counterflow injection mechanism disposed in a combustion liner. The combustion liner including an outer casing comprising a plurality of openings formed along a length and configured as compressed air inlets, an inner casing having a closed rear end and a combustion outlet, and a
A method of using a counterflow injection mechanism disposed in a combustion liner. The combustion liner including an outer casing comprising a plurality of openings formed along a length and configured as compressed air inlets, an inner casing having a closed rear end and a combustion outlet, and an air circulation path extending between and along the inner and outer casings. The counterflow injection mechanism includes a fuel-air injection mechanism having fuel and air passages extending through the air circulation path and leading to fuel and air injection openings disposed at an off-center position. The method includes injecting fuel and air from the injection mechanism toward the closed rear end of the inner casing in a direction counterflow to a generally lengthwise downstream flow of combustion products in a gas turbine combustor.
대표청구항
▼
1. A method, comprising: injecting fuel and air from an injection mechanism disposed in a combustion liner of an axial gas turbine combustor, the combustion liner disposed within a combustor housing and including an outer casing comprising a plurality of openings formed along a length and configured
1. A method, comprising: injecting fuel and air from an injection mechanism disposed in a combustion liner of an axial gas turbine combustor, the combustion liner disposed within a combustor housing and including an outer casing comprising a plurality of openings formed along a length and configured as compressed air inlets, an inner casing having a closed rear end and a combustion outlet and an air circulation path extending between and along the inner and outer casings, the injection mechanism including at least one fuel injector extending through the air circulation path, the at least one fuel injector having a fuel passage leading to a fuel injection opening and an air injection assembly leading to an air passage and an air injection opening, wherein the fuel injection opening and the air injection opening are disposed at an off-center position to provide injecting of the fuel and air toward the closed rear end of the inner casing in a direction counterflow to a generally lengthwise downstream flow of combustion products in the axial gas turbine combustor. 2. The method of claim 1, wherein injecting fuel and air comprises injecting fuel and air from a plurality of flush injection regions disposed at multiple radial positions about an inner circumference of the gas turbine combustor, wherein the plurality of flush injection regions are configured flush with the inner casing of the as turbine combustor so as to not protrude into an interior of the gas turbine combustor. 3. The method of claim 1, wherein injecting fuel and air comprises injecting fuel and air from a plurality of fuel-air injection lobes disposed at multiple radial positions about an inner circumference of the gas turbine combustor. 4. The method of claim 1, wherein injecting fuel and air comprises injecting fuel and air from a plurality of cantilevered aerodynamic members disposed at multiple radial positions about an inner circumference of the gas turbine combustor. 5. The method of claim 1, wherein injecting fuel and air comprises injecting fuel and air from a plurality of fuel-air injectors oriented to converge toward a stagnation zone in the gas turbine combustor. 6. The method of claim 1, wherein injecting fuel and air comprises circulating air through a hollow annular combustion liner and injecting the air into the gas turbine combustor along with fuel. 7. The method of claim 1, wherein injecting fuel and air comprises injecting from a position within a turbine nozzle. 8. The method of claim 1, wherein injecting fuel and air comprises injecting fuel and air from a plurality of fuel-air injection disposed in a circumferential arrangement. 9. The method of claim 1, wherein injecting fuel and air comprises injecting fuel and air from a plurality of fuel-air injection mechanisms oriented in a generally converging relationship. 10. The method of claim 1, wherein injecting fuel and air comprises injecting fuel and air from a plurality of fuel-air injection mechanisms including a plurality of coaxial fuel-air openings oriented in counterflow directions, including substantially lengthwise directional portions, relative to the generally lengthwise flow axis of the axial gas turbine combustor. 11. The method of claim 1, wherein injecting fuel and air comprises injecting fuel and air from a plurality of fuel-air injection mechanisms disposed in a plurality of lobe structures, flush wall portions, cantilevered members, or airfoil structures. 12. A method, comprising: injecting fuel and air at an off-center position and in a direction counterflow to a generally lengthwise downstream flow of combustion products in a gas turbine combustor,wherein injecting fuel and air comprises injecting fuel and air from at least one fuel-air injection mechanism disposed in a combustion liner of an axial gas turbine combustor, the combustion liner disposed within a combustor housing and including an outer casing comprising a plurality of openings formed along a length and configured as compressed air inlets, an inner casing having a closed rear end and a combustion outlet, and an air circulation path extending between and along the inner and outer casings, the at least one fuel-air mechanism extending through the air circulation path, the at least one fuel-air injection mechanism having a fuel passage leading to fuel injection opening and an air injection assembly leading to an air passage and an air injection opening, wherein the fuel and air injection openings are disposed at an off-center position position to inject fuel and air toward the closed rear end of the gas turbine combustor. 13. The method of claim 12, wherein injecting fuel and air comprises injecting fuel and air from a plurality of flush injection regions disposed at multiple radial positions about an inner circumference of the gas turbine combustor, wherein the plurality of flush injection regions are configured flush with a solid inner casing of the as turbine engine so as to not protrude into an interior of the gas turbine combustor. 14. The method of claim 12, wherein injecting fuel and air comprises injecting fuel and air from a plurality of fuel-air injection lobes disposed at multiple radial positions about an inner circumference of the gas turbine combustor. 15. The method of claim 12, wherein injecting fuel and air comprises injecting fuel and air from a plurality of cantilevered aerodynamic members disposed at multiple radial positions about an inner circumference of the gas turbine combustor. 16. The method of claim 12, wherein injecting fuel and air comprises injecting fuel and air from a plurality of fuel-air injectors oriented to converge toward a stagnation zone in the gas turbine combustor. 17. A method, comprising: injecting fuel and air at an off-center position and in a counterflow direction relative to a generally lengthwise downstream flow combustion products in an a gas turbine combustor, wherein injecting fuel and air comprises injecting fuel and air from at least one fuel-air injection mechanism disposed within a combustion liner, the combustor liner disposed within a combustor housing, an air circulation path extending between and along an inner casing and an outer casing of the combustor liner and having a generally lengthwise flow axis extending from a stagnation zone at a closed rear end of the gas turbine combustor to a combustion outlet of the gas turbine combustor, the at least one fuel-air injection mechanism having a fuel passage leading to fuel injection opening and an air injection assembly leading to an air passage and an air injection opening, the outer casing comprising a plurality of openings formed along a length and configured as compressed air inlets,wherein the fuel and air injection openings are disposed at an off-center position to inject fuel and air toward a the closed rear end of the gas turbine combustor and in a direction generally counterflow to a generally lengthwise downstream flow of combustion products in the gas turbine combustor. 18. The method of claim 17, wherein injecting fuel and air comprises injecting fuel and air from a plurality of fuel-air injection mechanisms disposed in a plurality of lobe structures, flush wall portions, Of cantilevered members, or airfoil structures. 19. The method of claim 17, wherein injecting fuel and air comprises injecting fuel and air from a plurality of fuel-air injection mechanisms oriented in a generally converging relationship. 20. The method of claim 17, wherein injecting fuel and air comprises injecting fuel and air from a plurality of fuel-air injection mechanisms including a plurality of coaxial fuel-air openings oriented in counterflow directions, including substantially lengthwise directional portions, relative to the generally lengthwise flow axis of the axial gas turbine combustor.
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