IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0489533
(2006-07-20)
|
등록번호 |
US-8096130
(2012-01-17)
|
발명자
/ 주소 |
|
출원인 / 주소 |
- Pratt & Whitney Canada Corp.
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
4 인용 특허 :
30 |
초록
▼
A gas turbine engine fuel conveying member in fluid flow communication with at least one fuel nozzle, the fuel conveying member having at least first and second member portions sealingly engaged to one another, and means for conveying fuel defined at a junction between the first and second member po
A gas turbine engine fuel conveying member in fluid flow communication with at least one fuel nozzle, the fuel conveying member having at least first and second member portions sealingly engaged to one another, and means for conveying fuel defined at a junction between the first and second member portions. The means for conveying fuel is defined by at least part of two different walls of each of the first and second member portions.
대표청구항
▼
1. A gas turbine engine fuel injection assembly comprising: an internal fuel manifold being annular and extending around a central axis, the fuel manifold having a plurality of fuel nozzles disposed about a circumference thereof, each of said fuel nozzles being in fluid flow communication with at le
1. A gas turbine engine fuel injection assembly comprising: an internal fuel manifold being annular and extending around a central axis, the fuel manifold having a plurality of fuel nozzles disposed about a circumference thereof, each of said fuel nozzles being in fluid flow communication with at least two fuel conduits defined within the fuel manifold such that the fuel conduits of the fuel manifold deliver fuel flow to any one or more of the fuel nozzles at their respective circumferentially spaced apart locations about the annular fuel manifold, the fuel manifold comprising first and second ring portions cooperating to provide a manifold body and to define therebetween the at least two fuel conduits;wherein the first ring portion includes a first circumferentially-extending inner surface including a plurality of first walls cooperating to define a plurality of channels defined in the first circumferentially-extending inner surface, and the second ring portion includes a second circumferentially-extending inner surface including a plurality of second walls cooperating to define a plurality of channels defined in the second circumferentially-extending inner surface, the first and second circumferentially-extending inner surfaces sealingly engaging one another about their respective circumferences at least three separate sealing locations on each ring portion, at least two of said three sealing locations being radially offset from each other so that said sealingly engaged first and second circumferentially-extending inner surfaces define a step, the said sealing locations being disposed between adjacent said channels, the channels of each said ring portion and the at least three sealing locations cooperating to define the at least two fuel conduits within the manifold body; andwherein the at least two fuel conduits being sealingly separated from one another to provide independent fuel feeds to each of the fuel nozzles, an intermediate one of the at least three locations being disposed between the at least two fuel conduits, the ring portions being joined by a braze at said intermediate location in a manner preventing fuel leakage from one fuel conduit to another. 2. The fuel conveying member as defined in claim 1, wherein each of the fuel conduits is defined by at least part of two of the first walls and at least part of two of the second walls. 3. The fuel conveying member as defined in claim 1, wherein each of the first walls extends substantially perpendicularly to each one of the subsequent, immediately adjacent and contacting one of the first walls, and each of the second walls extends substantially perpendicularly to each one of the subsequent, immediately adjacent and contacting one of the second walls. 4. The fuel conveying member as defined in claim 1, wherein each of the locations is defined by one of at least two non-subsequent ones of the first walls which are not in contact with each other and sealingly engaged to a respective one of two-non-subsequent ones of the second walls which are also not in contact with each other. 5. The fuel conveying member as defined in claim 1, wherein the first and second ring portions are concentric, the first and second inner surfaces being sealingly engaged along a full circumference thereof. 6. The fuel conveying member as defined in claim 1, wherein the first and second ring portions are concentric, the first and second circumferentially-extending inner surfaces having a radially facing sealing interface. 7. The fuel conveying member as defined in claim 1, wherein the first and second walls are straight. 8. The fuel conveying member as defined in claim 1, wherein the fuel conduits and locations are axially spaced apart from one another within the manifold body. 9. The fuel conveying member as defined in claim 1, wherein all of said sealing locations are radially offset from each other. 10. A gas turbine engine fuel injection system comprising: an annular internal fuel manifold extending around a central axis and a plurality of fuel nozzles disposed about a circumference of the fuel manifold, each of said fuel nozzles being in fluid flow communication with the fuel manifold such that the fuel conduits of the fuel manifold deliver fuel flow to any one or more of the fuel nozzles at their respective circumferentially spaced apart locations about the fuel manifold, the fuel manifold comprising: at least first and second ring portions sealingly engaged to one another about their respective circumferences at least three separate sealing locations, the three sealing locations being axially spaced apart; andmeans for conveying fuel defined at a junction between the first and second ring portions, the means for conveying fuel providing at least two least two independent fuel conduits defined within the fuel manifold to deliver fuel flow to any one or more of the fuel nozzles and being defined by at least part of two different walls of each of the first and second ring portions, and wherein the independent fuel conduits are sealingly enclosed by said at least three separate sealing locations, the three sealing locations including at least one central seal and two outer seals, the central seal extending continuously between the fuel conduits to seal against fluid flow communication from one conduit to another, and including a brazed joint between the first and second ring portions at a location between the two sealed fuel conduits, and the outer seals extending continuously between the first and second ring portions on opposed axial outer edges of the fuel manifold to sealing enclose the fuel conduits, at least two of said sealing locations being radially offset from each other to define a step in said first and second ring portions which are sealingly engaged to form the fuel manifold. 11. The gas turbine engine fuel injection system as defined in claim 10, wherein the at least part of the two different walls include at least part of two adjacent walls of each of the first and second ring portions defining a first one of the conduits and at least part of two other adjacent walls of each of the first and second ring portions defining a second one of the conduits. 12. The gas turbine engine fuel injection system as defined in claim 10, wherein the two different walls are adjacent. 13. The gas turbine engine fuel injection system as defined in claim 10, wherein all of said sealing locations are radially offset from each other.
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