[특허]Internal fuel manifold having temperature reduction feature

Pratt & Whitney Canada Corp.

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특허 상세정보

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Internal fuel manifold having temperature reduction feature

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/22 F02C-007/228
미국특허분류(USC)	060/772; 060/725; 060/739
출원번호	UP-0532611 (2006-09-18)
등록번호	US-7703289 (2010-05-20)
발명자 / 주소	Rudrapatna, Nagaraja Morenko, Oleg Patel, Bhawan B.
출원인 / 주소	Pratt & Whitney Canada Corp.
대리인 / 주소	Ogilvy Renault LLP
인용정보	피인용 횟수 : 3 인용 특허 : 31

초록
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A fuel manifold assembly for a gas turbine engine comprises an annular fuel manifold and a plurality of fuel nozzles circumferentially distributed about the fuel manifold. The fuel manifold has at least one fuel conveying passage in fluid flow communication with the plurality of fuel nozzles and defines at least one location susceptible to overheating between two of the plurality of fuel nozzles. A slot extends through the fuel manifold in the susceptible location to reduce heat transfer in the fuel manifold while maintaining the fuel manifold assembly d...

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The invention claimed is: 1. A fuel manifold assembly for a gas turbine engine comprising an internal fuel manifold and a plurality of fuel nozzles circumferentially distributed about the fuel manifold, the fuel manifold being a continuously uninterrupted annular ring and having at least one fuel conveying passage in fluid flow communication with the plurality of fuel nozzles and defining at least one location susceptible to overheating between two of said fuel nozzles, the location being disposed substantially diameterically opposite from a fuel inlet to the fuel conveying passage of the fuel manifold, and wherein one or more slots extend through the fuel manifold within the susceptible location to reduce heat transfer in the fuel manifold while maintaining the fuel manifold assembly dynamically balanced, each of said one or more slots defining a closed perimeter wholly disposed between inner and outer diameters of the annular internal fuel manifold. 2. The fuel manifold assembly as defined in claim 1, wherein the susceptible location comprising an additional slot on an exposed fuel manifold surface adapted to be exposed to hot air within the gas turbine engine, the additional slot thereby reducing an area of the exposed fuel manifold surface. 3. The fuel manifold assembly as defined in claim 2, wherein the fuel manifold has a lip extending circumferentially about an inner diameter thereof, the additional slot defining a cut-out in the lip. 4. The fuel manifold assembly as defined in claim 3, wherein the additional slot has a substantially smooth inner contour. 5. The fuel manifold assembly as defined in claim 4, wherein the lip extends from a circumferential surface of the fuel manifold and the additional slot extends partially into the circumferential surface. 6. The fuel manifold assembly as defined in claim 1, wherein the fuel manifold defines a radial width extending between the inner and outer diameters, the slot having a width less than said radial width of the manifold. 7. The fuel manifold assembly as defined in claim 6, wherein the slot is located adjacent one of said fuel nozzles such as to reduce convective heat from the susceptible location within the fuel manifold to said one of the fuel nozzles. 8. The fuel manifold assembly as defined in claim 6, wherein the width of the slot is about 60% of the radial width of the fuel manifold. 9. The fuel manifold assembly as defined in claim 1, wherein the slot has a crescent shape. 10. The fuel manifold assembly as defined in claim 9, wherein the fuel manifold defines fuel nozzle receiving ports adapted for engageably receiving the fuel nozzles, and wherein a concave portion of the crescent shaped slot faces one of the fuel nozzle receiving ports. 11. The fuel manifold assembly as defined in claim 10, further comprising a pair of slots each facing respective adjacent fuel nozzle receiving ports located on opposed sides of the susceptible location defined therebetween. 12. 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 engine casing, the fuel manifold having at least one fuel conveying passage therein in fluid flow communication with a plurality of fuel injection nozzles disposed along the fuel manifold and adapted to spray fuel into the combustor, and a fuel inlet connected to the fuel manifold and providing fuel flow to the fuel conveying passage, the fuel manifold defining at least one location susceptible to overheating between two of the plurality of fuel nozzles, the location being disposed substantially diametrically opposite from the fuel inlet; an annular heat shield at least partially covering the fuel manifold about the circumference thereof; and at least one slot extending through the fuel manifold in the susceptible location to reduce heat transfer in the fuel manifold while maintaining the fuel manifold assembly dynamically balanced, the at least one slot defining a closed perimeter disposed between inner and outer diameters of the annular internal fuel manifold. 13. The fuel manifold assembly as defined in claim 12, wherein the fuel manifold has a lip extending circumferentially about an inner diameter thereof, an additional slot defining a cut-out in the lip in the susceptible location. 14. The fuel manifold assembly as defined in claim 13, wherein the heat shield is fastened to the lip for mounting to the fuel manifold, the heat shield covering the additional slot during engine operation. 15. The fuel manifold assembly as defined in claim 14, wherein the lip extends from a circumferential surface of the fuel manifold and the additional slot extends partially into the circumferential surface. 16. The fuel manifold assembly as defined in claim 12, wherein the slot is located adjacent one of said fuel nozzles such as to reduce convective heat from the susceptible location within the fuel manifold to said one of the fuel nozzles. 17. The fuel manifold assembly as defined in claim 16, wherein the fuel manifold has an inner and an outer diameter and defines a radial width extending therebetween, the slot being wholly defined within said width. 18. The fuel manifold assembly as defined in claim 17, wherein the slot has a crescent shape. 19. The fuel manifold assembly as defined in claim 18, wherein the fuel manifold defines fuel nozzle receiving ports adapted for engageably receiving the fuel nozzles, and wherein a concave portion of the crescent shaped slot faces one of the fuel nozzle receiving ports. 20. The fuel manifold assembly as defined in claim 19, wherein a pair of said slots are disposed within the susceptible location, said pair of slots being each facing respective adjacent fuel nozzle receiving ports between which the susceptible location is defined. 21. The fuel manifold assembly as defined in claim 12, wherein the susceptible location is a location of one of slow and reduced fuel flow. 22. A method of reducing heat transfer in an annular internal fuel manifold of a fuel injection system in a gas turbine, the method comprising the steps of: determining at least one location of the internal fuel manifold susceptible to overheating during engine operation, the at least one location being disposed substantially diametrically opposite from a fuel inlet to the fuel manifold; forming at least one slot within the susceptible location, the slot defining a closed perimeter disposed between inner and outer diameters of the annular internal fuel manifold; and ensuring that the fuel injection system remains dynamically balanced with said slot formed in the susceptible location of the internal fuel manifold.

이 특허에 인용된 특허 (31)

이 특허를 인용한 특허 (3)

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특허 상세정보

Internal fuel manifold having temperature reduction feature

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청구항
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이 특허에 인용된 특허 (31)

이 특허를 인용한 특허 (3)

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IPC 상세정보(version : 201201)

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특허 상세정보

Internal fuel manifold having temperature reduction feature

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이 특허에 인용된 특허 (31)

이 특허를 인용한 특허 (3)

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

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