[특허]Gas turbine engine fuel conveying member

Pratt & Whitney Canada Corp.

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특허 상세정보

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Gas turbine engine fuel conveying member

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-001/00 F02G-003/00
미국특허분류(USC)	060/739; 060/734; 060/796; 060/800
출원번호	US-0021172 (2011-02-04)
등록번호	US-8276387 (2012-10-02)
발명자 / 주소	Prociw, Lev Alexander Shafique, Harris Fish, Jason Patel, Bhawan B.
출원인 / 주소	Pratt & Whitney Canada Corp.
대리인 / 주소	Norton Rose Canada LLP
인용정보	피인용 횟수 : 1 인용 특허 : 68

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A fuel conveying member of a gas turbine engine is described and includes a fuel manifold defining an annular fuel flow passage through a body of the fuel manifold. A plurality of fuel nozzles extend from the manifold in fluid flow communication with the annular fuel flow passage. The fuel manifold includes integral attachment lugs thereon for mounting the fuel manifold within the gas turbine engine. The attachment lugs are adapted to receive pins therein and provide a mounting mechanism which allows for thermal expansion of the fuel manifold relative to...

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1. A fuel conveying member of a gas turbine engine comprising an annular fuel manifold defining an annular fuel flow passage through a body of the fuel manifold, the manifold having a plurality of fuel nozzles extending therefrom in fluid flow communication with said annular fuel flow passage, the fuel manifold including at least two integral attachment lugs circumferentially spaced apart on an outer periphery of the annular fuel manifold for mounting the fuel manifold within the gas turbine engine, the attachment lugs each including an axially projecting flange having a radially extending and substantially circular opening defined therethrough adapted to receive pins therein and providing a mounting mechanism which allows for thermal expansion of the fuel manifold relative to a surrounding support structure to which the fuel manifold is mounted via the attachment lugs, and wherein the fuel manifold includes a radially extending fuel inlet providing fuel flow to the fuel flow passage, the fuel inlet comprising a third support for said fuel manifold. 2. The fuel conveying member of claim 1, wherein the fuel inlet is disposed at a lowermost point of the annular fuel manifold. 3. The fuel conveying member of claim 2, wherein the two attachment lugs and the fuel inlet are circumferentially equally spaced apart about the annular fuel manifold. 4. The fuel conveying member of claim 1, wherein said attachment lugs and said pins mate together to define a support for said fuel manifold which provides axial constraint while permitting radial thermal expansion of the fuel manifold. 5. The fuel conveying member of claim 1, wherein the fuel conveying member includes a heating device disposed within a body of said fuel conveying member in heat transfer communication with said fuel flow passage, such that when activated said heating device heats said fuel flow passage to a temperature sufficiently high to permit pyrolysis of carbonaceous deposits in the fuel flow passage. 6. The fuel conveying member of claim 5, wherein the body of said fuel conveying member is composed of a first heat conducting material, and wherein said heating device includes a heating element embedded in a heat conducting capsule disposed in said body of the fuel conveying member, said heat conducting capsule being composed of a second heat conducting material softer than the first heat conducting material of said body thereby providing substantially uniform heat distribution throughout said fuel conveying member. 7. A gas turbine engine including a compressor, a combustor and a turbine, comprising: a fuel manifold defining an annular fuel flow passage through a body of the fuel manifold, the body of said fuel manifold being composed of a first heat conducting material, the manifold having a plurality of fuel nozzles extending therefrom in fluid flow communication with said annular fuel flow passage, the fuel manifold being supported by a fuel inlet and integral attachment lugs thereon which mount the fuel manifold adjacent the combustor within the gas turbine engine, the integral attachment lugs each directly and matingly receiving a corresponding pin therein, the pins being engaged to a support structure surrounding the fuel manifold, the attachment lugs and the mating pins being configured for relative sliding motion therebetween such as to provide a mounting mechanism which allows for thermal expansion of the fuel manifold relative to the surrounding support structure at high temperatures. 8. The gas turbine engine as defined in claim 7, wherein the fuel manifold is an annular fuel manifold ring, the attachment lugs include two lugs on the periphery of the fuel manifold ring, the two lugs and the fuel inlet being equally spaced apart about the circumference of the fuel manifold ring. 9. The gas turbine engine as defined in claim 8, wherein the fuel inlet is disposed at a lowermost point of the annular fuel manifold ring. 10. The gas turbine engine as defined in claim 9, wherein the two attachment lugs and the fuel inlet are circumferentially equally spaced apart about the annular fuel manifold ring. 11. The gas turbine engine as defined in claim 10, wherein said lugs and said pins mate together to define a support for said fuel manifold which provides axial constraint while permitting radial thermal expansion of the fuel manifold. 12. The gas turbine engine of claim 7, wherein heating means is disposed within said fuel manifold for heating said annular fuel flow passage to a pyrolysis temperature of carbonaceous deposits in said annular fuel flow passage, said heating means including a heat conducting capsule disposed in said body of the fuel manifold, the heat conducting capsule having a heating element embedded in a second heat conducting material which is softer than the first heat conducting material of said body of the fuel manifold, thereby providing substantially uniform heat distribution throughout said fuel manifold. 13. A fuel injection system for a gas turbine engine including a compressor, a combustor and a turbine, comprising: an annular internal fuel manifold disposed adjacent the combustor within a surrounding gas generator casing, the fuel manifold having at least one fuel conveying passage therein in fluid flow communication with a plurality of fuel injection nozzles disposed about the fuel manifold and adapted to spray fuel into the combustor; anda mounting system supporting and positioning the fuel manifold relative to the combustor within said gas generator casing, the mounting system including at least two pin supports circumferentially spaced apart about the annular fuel manifold, the pin supports including ring lugs and mating pins disposed between the fuel manifold and the surrounding gas generator casing, the pins directly co-operating with the aligned ring lugs such that the ring lugs are slidingly disposed around the pin for relative sliding displacement therebetween, the pin supports providing axial constraint for the fuel manifold while permitting radially displacement thereof relative to the surrounding gas generator casing due to thermal size change. 14. The fuel injection system as defined in claim 13, wherein the fuel manifold includes a radially extending fuel inlet providing fuel flow to the fuel conveying passage, the fuel inlet comprising a third support for said fuel manifold. 15. The fuel injection system as defined in claim 14, wherein the fuel inlet is disposed at a lowermost point of the annular fuel manifold. 16. The fuel injection system as defined in claim 13, wherein the pins and the co-operating ring lugs of said pin supports are respectively engaged to the gas generator casing and the fuel manifold. 17. The fuel injection system as defined in claim 13, wherein the fuel manifold includes a heating device disposed within a body of said fuel manifold in heat transfer communication with said fuel conveying passage, such that when activated said heating device heats said fuel conveying passage to a temperature sufficiently high to permit pyrolysis of carbonaceous deposits in the fuel conveying passage. 18. The fuel conveying member of claim 17, wherein the body of said fuel manifold is composed of a first heat conducting material, and wherein said heating device includes a heating element embedded in a heat conducting capsule disposed in said body of the fuel manifold, said heat conducting capsule being composed of a second heat conducting material softer than the first heat conducting material of said body thereby providing substantially uniform heat distribution throughout said fuel conveying member. 19. An internal fuel manifold assembly for a gas turbine engine comprising: a fuel manifold ring having at least one fuel conveying passage therein in fluid flow communication with a plurality of fuel injection nozzles adapted for spraying fuel into a combustor of the gas turbine engine; anda mounting system for supporting and positioning the fuel manifold ring within the gas turbine engine, the mounting system including at least two lugs disposed on a periphery of the fuel manifold ring and a fuel inlet to the annular fuel manifold body, the lugs having a radially oriented substantially circular hole therein adapted for directly slidingly receiving a corresponding radially extending support pin therein, the lugs and the fuel inlet being equally spaced apart about the circumference of the fuel manifold ring. 20. The internal fuel manifold assembly as defined in claim 19, wherein said lug and said support pin mate together to define a support for said fuel manifold which provides axial constraint while permitting radial thermal expansion of the fuel manifold. 21. The internal fuel manifold assembly as defined in claim 19, wherein the fuel manifold ring includes a heating device disposed within a body of said fuel manifold ring in heat transfer communication with said fuel conveying passage, such that when activated said heating device heats said fuel conveying passage to a temperature sufficiently high to permit pyrolysis of carbonaceous deposits in the fuel conveying passage. 22. The fuel conveying member of claim 21, wherein the body of said fuel manifold ring is composed of a first heat conducting material, and wherein said heating device includes a heating element embedded in a heat conducting capsule disposed in said body of the fuel manifold, said heat conducting capsule being composed of a second heat conducting material softer than the first heat conducting material of said body thereby providing substantially uniform heat distribution throughout said fuel conveying member.

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Melton, Patrick Benedict, System for supporting bundled tube segments within a combustor.

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Gas turbine engine fuel conveying member

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Gas turbine engine fuel conveying member

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이 특허에 인용된 특허 (68)

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