[특허]Optimized internal manifold heat shield attachment

Pratt & Whitney Canada Corp.

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Optimized internal manifold heat shield attachment

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-001/00 F02G-003/00
미국특허분류(USC)	060/739; 060/734
출원번호	UP-0466137 (2006-08-22)
등록번호	US-7765808 (2010-08-24)
발명자 / 주소	Fish, Jason Patel, Bhawan B.
출원인 / 주소	Pratt & Whitney Canada Corp.
대리인 / 주소	Ogilvy Renault LLP
인용정보	피인용 횟수 : 3 인용 특허 : 29

초록

A fuel manifold assembly for a gas turbine engine includes an annular fuel manifold having at least one fuel conveying passage and defining at least one slow fuel flowing location. A heat shield at least partly encloses the fuel manifold and a plurality of intermittent joints attach the heat shield to the fuel manifold. The joints are circumferentially distributed about the fuel manifold as far away from the slow flowing location as possible while maintaining the fuel manifold dynamically balanced.

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What is claimed is: 1. A fuel manifold assembly for a gas turbine engine comprising an annular fuel manifold having at least one circumferential fuel conveying passage in fluid flow communication with a fuel inlet to the fuel manifold, the fuel conveying passage defining at least one slow fuel flowing location disposed diametrically opposite to said inlet, a heat shield at least partly enclosing the fuel manifold, the heat shield comprising a front segment and a rear segment axially aft of the front segment, the front and rear heat shield segments being independently attached to the fuel manifold by front segment joints and rear segment joints respectively, the front segment joints and the rear segment joints being disposed in alternating relation about a circumference of the fuel manifold, the fuel manifold defining four equal quadrants with a center point coincident with a center of the annular fuel manifold, the slow fuel flowing location being located between a first two of the quadrants and the fuel inlet being located between a remaining two of the quadrants, and wherein one or more of the front segment joints and one or more of the rear segment joints are disposed in each of said four quadrants at circumferentially adjacent locations furthest from said slow fuel flowing location within each said quadrant. 2. The fuel manifold assembly as defined in claim 1, wherein the fuel manifold defines a first and a second half, and wherein half of the front segment joints and half of the rear segment joints are disposed in the first half of the fuel manifold and the other half of the front segment joints and the other half of the rear segment joints are disposed in the second half of the fuel manifold. 3. The fuel manifold assembly as defined in claim 2, comprising four front segment joints and four rear segment joints. 4. The fuel manifold assembly as defined in claim 1, wherein the four equal quadrants each have a mirror image differing from each other. 5. The fuel manifold assembly as defined in claim 4, wherein the fuel manifold is defined by a Cartesian coordinate system having an intersecting x-axis and y-axis with an origin concentric with a center of the fuel manifold, the Cartesian coordinate system defining a 360 degree plane, and wherein the slow fuel flowing location is at 90 degrees, the front and rear segment joints are located end to end immediately adjacent corresponding 0, 180 and 270 degree positions. 6. The fuel manifold assembly as defined in claim 1, wherein the fuel manifold comprises a circumferential lip for supporting the joints. 7. A fuel injection system for 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 slow fuel flowing location, the fuel manifold defining four equal quadrants and the slow fuel flowing location being located between two of the quadrants; an annular heat shield at least partially covering the fuel manifold about the circumference thereof, the heat shield including a front segment and a rear segment, the rear segment being axially aft of the front segment; and a plurality of intermittent joints attaching the heat shield to the fuel manifold, the plurality of intermittent joints including front segment joints and rear segment joints respectively attaching the front segments and the rear segments of the heat shield, the front segment joints and rear segment joints being circumferentially distributed about the fuel manifold in alternating relation and wherein one or more of the front segment joints and one or more of the rear segment joints are disposed in each of the four equal quadrants at circumferentially adjacent locations furthest from said slow fuel flowing location within each said quadrant. 8. The fuel manifold assembly as defined in claim 7, wherein the fuel manifold defines a first and a second half, and wherein half of the front segment joints and half of the rear segment joints are disposed in the first half of the fuel manifold and the other half of the front segment joints and the other half of the rear segment joints are disposed in the second half of the fuel manifold. 9. The fuel manifold assembly as defined in claim 8, comprising four front segment joints and four rear segment joints. 10. The fuel manifold assembly as defined in claim 7, wherein the four equal quadrants each have a mirror image differing from each other. 11. The fuel manifold assembly as defined in claim 10, wherein the fuel manifold is defined by a Cartesian coordinate system having an intersecting x-axis and y-axis with an origin concentric with a center of the fuel manifold, the Cartesian coordinate system defining a 360 degree plane and wherein the slow fuel flowing location is at 90 degrees, the front and rear segment joints are located end to end immediately adjacent corresponding 0, 180 and 270 degree positions. 12. The fuel manifold assembly as defined in claim 11, wherein the fuel manifold comprises a circumferential lip for supporting the joints. 13. A method of minimizing heat transfer from a heat shield to an internal fuel manifold of a fuel injection system in a gas turbine, the heat shield including a front segment and a rear segment axially aft of the front segment, the fuel manifold defining four equal quadrants, the method comprising the steps of: determining at least one slow fuel flowing location in a fuel conveying passage of the fuel manifold, the slow fuel flowing location being located between two of the quadrants; selecting joint locations as far away as possible from the slow fuel flowing location within each said quadrant; ensuring that the fuel injection system is -dynamically balanced with said selected joint locations; and joining the heat shield to the fuel manifold at said selected joint locations by joining the front and the rear segments independently in a alternating relation about the circumference of the fuel manifold. 14. The method as defined in claim 13, further comprising determining a minimum amount of support required for attachment of the heat shield to the fuel manifold, and selecting a minimum number of said joint locations to yield the minimum amount of support required.

이 특허에 인용된 특허 (29)

이 특허를 인용한 특허 (3)

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특허 상세정보

Optimized internal manifold heat shield attachment

초록

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이 특허에 인용된 특허 (29)

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특허 상세정보

Optimized internal manifold heat shield attachment

초록

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이 특허에 인용된 특허 (29)

이 특허를 인용한 특허 (3)

IPC 상위 출원인

과제정보

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IPC 상세정보(version : 201201)

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