[특허]Gas turbine diffuser strut including a trailing edge flap and methods of assembling the same

General Electric Company

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특허 상세정보

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Gas turbine diffuser strut including a trailing edge flap and methods of assembling the same

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-025/24 F01D-025/30 F01D-009/04 F04D-029/54 F01D-005/14 F04D-029/68 B23P-019/00 F01D-025/28 B64C-023/06 F01D-025/16
출원번호	US-0681441 (2015-04-08)
등록번호	US-10151325 (2018-12-11)
발명자 / 주소	Subramaniyan, Moorthi Chengappa, Manjunath Bangalore Patel, Pradeep
출원인 / 주소	General Electric Company
대리인 / 주소	Armstrong Teasdale LLP
인용정보	피인용 횟수 : 0 인용 특허 : 51

초록

A gas turbine diffuser for use with a gas turbine power system is provided. The diffuser includes an annular inner wall and an annular outer wall circumscribing the inner wall such that a gas path is defined between the inner and outer walls. The diffuser further includes a plurality of circumferentially-spaced struts extending from the inner wall to the outer wall across the gas path. At least one of the struts has a flap.

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1. A gas turbine diffuser for use with a gas turbine power system, said gas turbine diffuser comprising: an annular inner wall;an annular outer wall circumscribing said annular inner wall such that a gas path is defined between said annular inner and annular outer walls; anda plurality of circumferentially-spaced struts extending from said annular inner wall to said annular outer wall across the gas path, wherein at least one of said plurality of circumferentially-spaced struts comprises:a root, a tip, and a span extending from said root to said tip;a leading edge;a trailing edge;a pressure side extending from said leading edge downstream to said trailing edge; anda flap immovably coupled along said pressure side, near and upstream from said trailing edge, said flap extending circumferentially from a first end coupled to said pressure side to a free end, wherein said flap extends along at least half of the respective span of said at least one of said plurality of circumferentially-spaced struts, and said flap is oriented parallel to said trailing edge. 2. A gas turbine diffuser in accordance with claim 1, wherein said at least one of said plurality of circumferentially-spaced struts comprises a substantially airfoil-shaped skin that defines said leading edge, said trailing edge, a suction side, and said pressure side. 3. A gas turbine diffuser in accordance with claim 2, wherein said at least one of said plurality of circumferentially-spaced struts has a chord extending from said leading edge to said trailing edge, said flap disposed at between 1.5% and 3.5% of the chord upstream from said trailing edge. 4. A gas turbine diffuser in accordance with claim 2, wherein said at least one of said plurality of circumferentially-spaced struts has a chord extending in an axial direction from said leading edge to said trailing edge, said flap comprising a first plate oriented substantially perpendicular to the axial direction. 5. A gas turbine diffuser in accordance with claim 4, wherein said flap comprises a second plate coupled to said first plate such that said flap forms a generally triangular shape defined by said first plate, said second plate, and said substantially airfoil-shaped skin. 6. A gas turbine diffuser in accordance with claim 1, wherein said flap extends from 0 percent of the span to 50 percent of the span. 7. A gas turbine diffuser in accordance with claim 1, wherein said flap extends from 25 percent of the span to 75 percent of the span. 8. A gas turbine diffuser in accordance with claim 1, wherein said flap extends from said root to said tip along the span. 9. A gas turbine diffuser in accordance with claim 1, wherein said flap extends from 50 percent of the span to 100 percent of the span. 10. A gas turbine comprising: a combustor;a turbine arranged in flow communication with said combustor; anda diffuser arranged in flow communication with said turbine, said diffuser comprising:an annular inner wall;an annular outer wall circumscribing said annular inner wall such that a gas path is defined between said annular inner and annular outer walls; anda plurality of circumferentially-spaced struts extending from said annular inner wall to said annular outer wall across the gas path, wherein at least one of said plurality of circumferentially-spaced struts comprises:a root, a tip, and a span extending from said root to said tip;a leading edge;a trailing edge, wherein a chord of said at least one of said plurality of circumferentially-spaced struts extends in an axial direction from said leading edge to said trailing edge;a pressure side extending from said leading edge downstream to said trailing edge; anda flap immovably coupled along said pressure side and oriented substantially perpendicular to the axial direction, said flap extending circumferentially from a first end coupled to said pressure side to a free end, wherein said flap extends along at least half of the respective span of said at least one of said plurality of circumferentially-spaced struts, and said flap is oriented parallel to said trailing edge. 11. A gas turbine in accordance with claim 10, wherein said at least one of said plurality of circumferentially-spaced struts comprises a substantially airfoil-shaped skin that defines said leading edge, said trailing edge, a suction side, and said pressure side, said flap coupled along said pressure side between 1.5% and 3.5% of the chord from said trailing edge. 12. A gas turbine in accordance with claim 10, wherein said flap extends from said root to said tip along the span. 13. A gas turbine in accordance with claim 10, wherein said flap extends from 0 percent of the span to 50 percent of the span. 14. A gas turbine diffuser in accordance with claim 10, wherein said flap extends from 25 percent of the span to 75 percent of the span. 15. A gas turbine diffuser in accordance with claim 10, wherein said flap extends from 50 percent of the span to 100 percent of the span. 16. A gas turbine diffuser for use with a gas turbine power system, said gas turbine diffuser comprising: an annular inner wall;an annular outer wall circumscribing said annular inner wall such that a gas path is defined between said annular inner and annular outer walls; anda plurality of circumferentially-spaced struts extending from said annular inner wall to said annular outer wall across the gas path, wherein at least one of said plurality of circumferentially-spaced struts comprises:a root, a tip, and a span extending from said root to said tip;a leading edge;a trailing edge;a pressure side extending from said leading edge downstream to said trailing edge; anda flap immovably coupled along said pressure side, near and upstream from said trailing edge, said flap extending circumferentially from a first end coupled to said pressure side to a free end, wherein said flap extends along at least half of the respective span of said at least one of said plurality of circumferentially-spaced struts, wherein said flap is oriented at an angle to a spanwise direction of said at least one of said plurality of circumferentially-spaced struts, and said flap is oriented parallel to said trailing edge. 17. A gas turbine diffuser in accordance with claim 16, wherein said at least one of said plurality of circumferentially-spaced struts comprises a substantially airfoil-shaped skin that defines said leading edge, said trailing edge, a suction side, and said pressure side. 18. A gas turbine diffuser in accordance with claim 17, wherein said at least one of said plurality of circumferentially-spaced struts has a chord extending from said leading edge to said trailing edge, said flap disposed at between 1.5% and 3.5% of the chord upstream from said trailing edge. 19. A gas turbine diffuser in accordance with claim 17, wherein said at least one of said plurality of circumferentially-spaced struts has a chord extending in an axial direction from said leading edge to said trailing edge, said flap comprising a first plate oriented substantially perpendicular to the axial direction. 20. A gas turbine diffuser in accordance with claim 19, wherein said flap comprises a second plate coupled to said first plate such that said flap forms a generally triangular shape defined by said first plate, said second plate, and said substantially airfoil-shaped skin.

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Gas turbine diffuser strut including a trailing edge flap and methods of assembling the same

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Gas turbine diffuser strut including a trailing edge flap and methods of assembling the same

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