Fuel nozzle assembly for use as structural support for a duct structure in a combustor of a gas turbine engine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/28
F23R-003/08
F23R-003/34
F23R-003/60
F23R-003/54
출원번호
US-0566222
(2009-09-24)
등록번호
US-8991192
(2015-03-31)
발명자
/ 주소
Wiebe, David J.
Fox, Timothy A.
출원인 / 주소
Siemens Energy, Inc.
인용정보
피인용 횟수 :
1인용 특허 :
17
초록▼
A fuel nozzle assembly for use in a combustor apparatus of a gas turbine engine. An outer housing of the fuel nozzle assembly includes an inner volume and provides a direct structural connection between a duct structure and a fuel manifold. The duct structure defines a flow passage for combustion ga
A fuel nozzle assembly for use in a combustor apparatus of a gas turbine engine. An outer housing of the fuel nozzle assembly includes an inner volume and provides a direct structural connection between a duct structure and a fuel manifold. The duct structure defines a flow passage for combustion gases flowing within the combustor apparatus. The fuel manifold defines a fuel supply channel therein in fluid communication with a source of fuel. A fuel injector of the fuel nozzle assembly is provided in the inner volume of the outer housing and defines a fuel passage therein. The fuel passage is in fluid communication with the fuel supply channel of the fuel manifold for distributing the fuel from the fuel supply channel into the flow passage of the duct structure.
대표청구항▼
1. A fuel nozzle assembly in combination with a duct structure in a combustor apparatus of a gas turbine engine comprising: a duct structure comprising: an intermediate duct structure between a liner duct structure and a transition duct and defining a flow passage for combustion gases flowing from s
1. A fuel nozzle assembly in combination with a duct structure in a combustor apparatus of a gas turbine engine comprising: a duct structure comprising: an intermediate duct structure between a liner duct structure and a transition duct and defining a flow passage for combustion gases flowing from said liner duct structure to said transition duct, said intermediate duct structure being free to move axially with respect to each of said liner duct structure and said transition duct, wherein said intermediate duct structure includes a portion that has a generally constant intermediate duct diameter and said liner duct structure has a generally constant liner duct diameter generally equivalent to said intermediate duct diameter, and wherein said intermediate and liner duct structures are aligned with one another such that said intermediate and liner duct structures are generally coaxial;a fuel injection system associated with said intermediate duct structure, said fuel injection system comprising: an annular fuel manifold defining a fuel supply channel therein, said fuel supply channel in fluid communication with a source of fuel; anda plurality of fuel nozzle assemblies, each fuel nozzle assembly comprising: an outer housing coupled to said intermediate duct structure and to said fuel manifold, wherein said fuel manifold is structurally affixed to a flow sleeve, which is structurally affixed to a main engine casing, and said fuel manifold providing structural support for the fuel nozzle assembly and for said intermediate duct structure via the affixation of said fuel manifold to said flow sleeve, said outer housing structurally supporting said intermediate duct structure between said liner duct structure and said transition duct, said outer housing comprising an inner volume; anda fuel injector provided in said inner volume of said outer housing, said fuel injector defining a fuel passage therethrough, said fuel passage in fluid communication with said fuel supply channel of said fuel manifold for distributing fuel from said fuel supply channel into said flow passage of said intermediate duct structure, wherein said fuel injector extends radially inwardly from said annular manifold and passes through a corresponding opening in said intermediate duct structure. 2. The fuel nozzle assembly of claim 1, wherein said outer housing of each said fuel nozzle assembly comprises a generally cylindrical and rigid member. 3. The fuel nozzle assembly of claim 1, wherein said outer housing of each said fuel nozzle assembly is slidably received in said corresponding opening formed in said intermediate duct structure such that said outer housing of each said fuel nozzle assembly and said intermediate duct structure are movable radially independently from each other. 4. The fuel nozzle assembly of claim 3, wherein structure of said intermediate duct structure that defines each said opening engages an outer surface of said corresponding outer housing such that said intermediate duct structure and each said outer housing are movable axially and circumferentially together. 5. The fuel nozzle assembly of claim 1, wherein said outer housing of each said fuel nozzle assembly extends up to said intermediate duct structure at said corresponding opening and said fuel injector of each said fuel nozzle assembly extends radially past said corresponding outer housing and into said flow passage defined by said intermediate duct structure. 6. The fuel nozzle assembly of claim 1, wherein a distal end of said fuel injector of each said fuel nozzle assembly defines a fuel injection port in fluid communication with said fuel passage, and each said fuel injection port delivers fuel into said flow passage defined by said intermediate duct structure. 7. A combustor apparatus in a gas turbine engine comprising: a combustor device coupled to a main engine casing, said combustor device comprising: a flow sleeve for receiving pressurized air; anda liner duct structure disposed radially inwardly from said flow sleeve, said liner duct structure having an inlet, an outlet, and an inner volume, wherein said liner duct structure has a generally constant liner duct diameter;a transition duct having an inlet section and an outlet section;an intermediate duct structure disposed between said liner duct structure and said transition duct and defining a flow passage for combustion gases flowing from said liner duct structure to said transition duct, said intermediate duct structure having inlet and outlet portions, wherein said intermediate duct structure inlet portion is associated with said liner duct structure outlet such that movement is possible between said intermediate duct structure and said liner duct structure, and said intermediate duct structure outlet portion is associated with said transition duct inlet section such that movement is possible between said intermediate duct structure and said transition duct, wherein said intermediate duct structure has a portion having a constant intermediate duct diameter, said intermediate duct and liner duct diameters are generally equivalent to each other, and said intermediate and liner duct structures are aligned such that said intermediate and liner duct structures are generally coaxial; anda fuel injection system associated with said intermediate duct structure, said fuel injection system comprising: an annular fuel manifold structurally affixed to one of said flow sleeve, which is affixed to said main engine casing, and a mounting device coupled to said main engine casing, to provide structural support for said fuel injection system via the affixation of said fuel manifold to said one of said flow sleeve and said mounting device, said fuel manifold defining a fuel supply channel therein, said fuel supply channel in fluid communication with a source of fuel;a plurality of fuel nozzle assemblies, each fuel nozzle assembly comprising: an outer housing defining an inner volume and spanning between and coupled to both of said fuel manifold and said intermediate duct structure to provide structural support for said intermediate duct structure via said fuel manifold; anda fuel injector in said inner volume of said outer housing, said fuel injector defining a fuel passage therethrough, said fuel passage in fluid communication with said fuel supply channel of said fuel manifold for distributing fuel from said fuel supply channel into said flow passage of said intermediate duct structure, wherein said fuel injector extends radially inwardly from said annular manifold and passes through a corresponding opening in said intermediate duct structure. 8. The combustor apparatus of claim 7, wherein said inner volume of said liner duct structure defines a main combustion zone, and said flow passage defined by said intermediate duct structure is located downstream from said main combustion zone. 9. The combustor apparatus of claim 7, wherein said outer housing of each said fuel injector assembly is slidably received in the corresponding opening formed in said intermediate duct structure such that said outer housing of each said fuel injector assembly and said intermediate duct structure are movable radially independently from each other. 10. The combustor apparatus of claim 9, wherein structure of said intermediate duct structure that defines at least one of said openings that receives a corresponding outer housing engages an outer surface of said outer housing such that said intermediate duct structure and said outer housing are movable axially and circumferentially together. 11. A fuel injection system for use in a combustor apparatus during operation of a gas turbine engine comprising: a plurality of fuel nozzle assemblies each comprising: an outer housing defining an inner volume and attached to an annular fuel manifold that is structurally supported by an engine casing, said annular fuel manifold providing structural support for said fuel nozzle assemblies and for an intermediate duct structure via the support of said annular fuel manifold by the engine casing, said intermediate duct structure located between a liner duct structure and a transition duct and defining a flow passage for combustion gasses flowing from said liner duct structure to said transition duct, wherein said outer housing extends radially inwardly from said annular fuel manifold and is slidably received in a corresponding opening formed in said intermediate duct structure such that said outer housing and said intermediate duct structure are movable radially independently from each other, said intermediate duct structure being free to move axially with respect to each of said liner duct structure and said transition duct, wherein said annular fuel manifold defines a fuel supply channel therein in fluid communication with a source of fuel, and wherein said outer housing structurally supports said intermediate duct structure between said liner duct structure and said transition duct via said annular fuel manifold; anda fuel injector provided in said inner volume of said outer housing, said fuel injector defining a fuel passage therein, said fuel passage in fluid communication with said fuel supply channel of said annular fuel manifold for distributing fuel from said fuel supply channel into said flow passage of said intermediate duct structure. 12. The fuel injection system of claim 11, wherein structure of said intermediate duct structure that defines each said opening that receives each said outer housing engages an outer surface of each said outer housing such that said intermediate duct structure and each said outer housing are movable axially and circumferentially together. 13. The fuel injection system of claim 11, wherein said intermediate duct structure includes an outlet portion having a diameter that is generally equivalent to a diameter of an outlet of the liner duct structure. 14. The fuel injection system of claim 11, wherein each said outer housing is rigidly attached to and structurally supported by said annular fuel manifold. 15. The fuel injection system of claim 14, wherein said annular fuel manifold extends circumferentially about said intermediate duct structure. 16. The fuel injection system of claim 15, wherein said at least one outer housing comprises an annular array of outer housings. 17. The fuel injection system of claim 11, wherein said annular fuel manifold is structurally affixed to a flow sleeve, which is structurally affixed to the engine casing.
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이 특허에 인용된 특허 (17)
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