[특허]Method and apparatus for delivery of a fuel and combustion air mixture to a gas turbine engine using fuel distribution grooves in a manifold disk with discrete air passages

General Electric Company

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특허 상세정보

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Method and apparatus for delivery of a fuel and combustion air mixture to a gas turbine engine using fuel distribution grooves in a manifold disk with discrete air passages

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/22
미국특허분류(USC)	060/737; 060/740; 060/742; 060/748; 060/776
출원번호	US-0406216 (2009-03-18)
등록번호	US-8234871 (2012-08-07)
발명자 / 주소	Davis, Jr., Lewis Berkley Johnson, Thomas Edward Stewart, Jason Thurman
출원인 / 주소	General Electric Company
대리인 / 주소	Cantor Colburn LLP
인용정보	피인용 횟수 : 15 인용 특허 : 11

초록
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A nozzle has combustion air passages extending from a first, upstream end to a second, downstream end. A fuel distribution manifold is associated with the first, upstream end of the nozzle. Combustion air passages correspond to, and align with the air passages in the nozzle. Fuel distribution grooves are formed in one end of the fuel distribution manifold disk and extend from a central opening to the air passages. A fuel circuit cover closes the fuel distribution grooves to define fuel passages that extend from the central opening to the combustion air p...

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1. A nozzle assembly comprising: a nozzle having discrete combustion air passages extending from a first, upstream end to a second, downstream end;a fuel distribution manifold disk attached to the first, upstream end of the nozzle having a central opening extending therethrough and having discrete combustion air passages extending from a first, upstream end to a second, downstream end corresponding to, and in alignment with, the discrete combustion air passages in the nozzle;fuel distribution grooves located in one end of the fuel distribution manifold disk extending from the central opening to the discrete combustion air passages to define a fuel circuit;a fuel circuit cover having discrete combustion air passages extending from a first, upstream end to a second, downstream end corresponding to, and in alignment with, the discrete combustion air passages in the fuel distribution manifold disk and operable to close the fuel distribution grooves to thereby define fuel passages extending from the central opening to the discrete combustion air passages; anda fuel delivery channel in communication with the central opening and the fuel passages for delivery of fuel to the combustion air in the discrete combustion air passages. 2. The nozzle assembly claim 1, wherein the fuel distribution grooves are formed in the second, downstream end of the fuel distribution manifold disk and the fuel circuit cover is the first, upstream end of the nozzle. 3. The nozzle assembly of claim 1, wherein the fuel distribution grooves are formed in the first, upstream end of the fuel distribution manifold disk and the fuel circuit cover is configured as a second plate attached to the first, upstream end of the fuel distribution manifold disk. 4. The nozzle assembly of claim 1, wherein the discrete combustion air passages extend at an angle to a central axis of the nozzle. 5. The nozzle assembly of claim 4, wherein the angled, discrete combustion air passages are configured to impart a swirl motion to a fuel and combustion air mixture exiting the nozzle at the second, downstream end. 6. The nozzle assembly of claim 1, wherein the discrete combustion air passages extend parallel to a central axis of the nozzle. 7. The nozzle assembly of claim 6, wherein the discrete combustion air passages are configured to establish a fuel and combustion air mixture exiting the nozzle at the second, downstream end. 8. The nozzle assembly of claim 1, wherein the discrete combustion air passage outlets at the second, downstream end of the nozzle have blended edges configured to reduce flame holding at the downstream end of the nozzle. 9. A nozzle assembly comprising: a nozzle having a first series of discrete combustion air passages extending from a first, upstream end to a second, downstream end, and a second series of discrete combustion air passages extending from the first, upstream end to the second, downstream end;a first fuel distribution manifold disk attached to the first, upstream end of the nozzle having a central opening extending therethrough and having discrete combustion air passages extending from a first, upstream end to a second, downstream end corresponding to, and in alignment with both the first and the second series of discrete combustion air passages in the nozzle;first fuel distribution grooves formed in the first, upstream end of the first fuel distribution manifold disk extending from the central opening to the first series of discrete combustion air passages;a second fuel distribution manifold disk attached to the first, upstream end of the first fuel distribution manifold disk and operable to close the first fuel distribution grooves to thereby define first fuel conduits extending from the central opening to the first series of discrete combustion air passages, the second fuel distribution manifold disk having a central opening extending therethrough and having discrete combustion air passages extending from a first, upstream end to a second, downstream end corresponding to, and in alignment with both the first and the second series of discrete combustion air passages in the nozzle;second fuel distribution grooves formed in one end of the second fuel distribution manifold disk extending from the central opening to the second series of discrete combustion air passages;a fuel circuit cover attached to the first, upstream end of the second fuel distribution manifold disk and operable to close the second fuel distribution grooves to thereby define a second fuel conduit extending from the central opening to the second series of discrete combustion air passages, the fuel circuit cover having a central opening extending therethrough and having discrete combustion air passages extending from a first, upstream end to a second, downstream end corresponding to, and in alignment with, both the first and the second series of discrete combustion air passages in the second fuel distribution manifold disk; anda fuel delivery hub in communication with the central openings and the first and second fuel conduits for delivery of fuel to the combustion air in the first and second series of discrete combustion air passages. 10. The nozzle assembly of claim 9, the fuel delivery hub comprising a first fuel delivery channel for delivery of fuel to the first fuel conduit and a second fuel delivery channel for delivery of fuel to the second fuel conduit. 11. The nozzle assembly of claim 9, the first fuel delivery channel having a first fuel volume and the second fuel delivery channel having a second fuel volume. 12. The nozzle assembly of claim 9, wherein the discrete combustion air passages extend at an angle to a central axis of the nozzle. 13. The nozzle assembly of claim 12, wherein the angled, discrete combustion air passages are operable to impart a swirl motion to fuel and combustion air mixture exiting the nozzle at the second, downstream end. 14. The nozzle assembly of claim 9, wherein the discrete combustion air passages extend parallel to a central axis of the nozzle. 15. The nozzle assembly of claim 14, wherein the discrete combustion air passages are configured to establish a fuel and combustion air mixture exiting the nozzle at the second, downstream end. 16. The nozzle assembly of claim 9, wherein the discrete combustion air passage outlets at the second, downstream end of the nozzle have blended edges operable to reduce flame holding at the downstream end of the nozzle. 17. A method for delivery of a fuel and combustion air mixture comprising: delivering combustion air to a nozzle having discrete combustion air passages extending from a first, upstream end to a second, downstream end;delivering fuel through a fuel delivery channel to a fuel distribution manifold disk attached to the first, upstream end of the nozzle having a central opening extending therethrough for receipt of the fuel delivery channel, and having discrete combustion air passages extending from a first, upstream end to a second, downstream end corresponding to, and in alignment with, the discrete combustion air passages in the nozzle;channeling the fuel through fuel distribution grooves located in one end of the fuel distribution manifold disk, the fuel distribution grooves extending from the central opening to the discrete combustion air passages to define a fuel circuit;and releasing the fuel from the fuel circuit and into the discrete combustion air passages to define a fuel and combustion air mixture. 18. The method for delivery of a fuel and combustion air mixture of claim 17, further comprising; orienting the discrete combustion air passages at an angle to a central axis of the nozzle wherein the angled combustion air passages are operable to impart a swirl motion to the fuel and combustion air mixture exiting the nozzle at the second, downstream end.

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이 특허를 인용한 특허 피인용횟수: 15

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Method and apparatus for delivery of a fuel and combustion air mixture to a gas turbine engine using fuel distribution grooves in a manifold disk with discrete air passages

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Method and apparatus for delivery of a fuel and combustion air mixture to a gas turbine engine using fuel distribution grooves in a manifold disk with discrete air passages

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이 특허에 인용된 특허 (11)

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