[특허]Gas turbine engine premix injectors

Gas turbine engine premix injectors 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-001/00 F23R-003/34 F23R-003/14 F23R-003/28 F23R-003/36
출원번호	US-0639379 (2006-12-14)
등록번호	US-8881531 (2014-11-11)
발명자 / 주소	Scarinci, Thomas Young, Kenneth James
출원인 / 주소	Rolls-Royce Power Engineering Plc
대리인 / 주소	Krieg DeVault LLP
인용정보	피인용 횟수 : 0 인용 특허 : 28

초록 ▼

One embodiment is a gas turbine engine premix injector including a mixing duct, a plurality of air inlet slots leading to the duct, a plurality of gaseous fuel inlet apertures leading to the duct, a plurality of vanes positioned in the duct downstream from said air inlets, a plurality of liquid fuel

대표청구항 ▼

1. A gas turbine premix injector comprising: a mixing duct;a plurality of air inlet slots leading to said mixing duct;a plurality of gaseous fuel inlet apertures leading to said mixing duct;a plurality of members positioned in said mixing duct downstream from said plurality of gaseous fuel inlet apertures for dividing fluid flow within said mixing duct; anda plurality of liquid fuel inlet apertures positioned in said mixing duct; andwherein said air inlet slots are formed in a first surface of said mixing duct, said gaseous fuel inlet apertures are formed in a second surface of said mixing duct opposite said first surface, and the first surface and the second surface forming an annular space defined between walls having the first surface and second surface downstream of the plurality of air inlet slots. 2. The injector of claim 1 wherein said plurality of members define a plurality of vanes. 3. The injector of claim 2 wherein each of said plurality of vanes is aerodynamically shaped. 4. The injector of claim 2 wherein said mixing duct is substantially annular and the ratio of distance between adjacent slots to height of the mixing duct is between 1.5 and 3. 5. The injector of claim 2 in flow communication with a combustion chamber, wherein the length of each of said slots satisfies fLU≥1 where f is the frequency of the lowest acoustic mode of the combustion chamber, L is slot length, and U is the average velocity of air in said mixing duct at the point of slot termination. 6. The injector of claim 2 wherein said liquid fuel inlet apertures are positioned to direct a fuel jet intermediate pairs of said plurality of vanes. 7. The injector of claim 2 wherein the size and location of said liquid fuel apertures are selected such that liquid fuel jets exiting said apertures satisfy (We)(MFR)5/4≧8000 where We is the Weber number based on the diameter of the liquid fuel jet and MFR is the momentum flux ratio of the liquid fuel jet. 8. The injector of claim 1 further comprising: a second mixing duct positioned radially inward from said duct;a second plurality of air inlet slots leading to said second duct;a second plurality of gaseous fuel inlet apertures leading to said second duct;a second plurality of members positioned in said duct downstream from said air inlets;a second plurality of liquid fuel inlet apertures leading to said second duct; andwherein said plurality of members and said second plurality of members are vanes. 9. An apparatus comprising: a gas turbine engine premix injector includinga mixing duct;a plurality of air inlet slots, each of said inlet slots providing a vortex flow to said mixing duct;a plurality of fuel inlets providing fuel to said mixing duct;a plurality of vanes positioned in said mixing duct and located downstream of a generation of the vortex flow provided by the plurality of air inlet slots;a first plurality of outlet windows;said vanes directing fluid flow to said outlet windows. 10. The apparatus of claim 9 wherein said plurality of fuel inlets are liquid fuel inlets positioned to provide fuel jets intermediate said vanes. 11. The apparatus of claim 9 wherein said plurality of fuel inlets are gaseous fuel inlets defined in a surface of said mixing duct. 12. The apparatus of claim 9 wherein said plurality of fuel inlets are gaseous fuel inlets and further comprising a plurality of liquid fuel inlets. 13. The apparatus of claim 9 wherein fluid flow streams from said first plurality of outlet windows diverge from one another. 14. The apparatus of claim 9 further comprising a second plurality of outlet windows positioned radially inward from and downstream from said first plurality of outlet windows. 15. The apparatus of claim 9 wherein each of said air inlet slots generates two vortex flows within said mixing duct. 16. A gas turbine engine combustion system comprising: a premix injector including a primary stage, said primary stage including an air-fuel mixing duct, a plurality of inlet air flows to said air-fuel mixing duct, a plurality of fuel jets to said air-fuel mixing duct, and a plurality of vanes that together define a plurality of outlet windows, each outlet window providing a lean combustible fluid flow to a discrete flame associated with each window such that a plurality of discrete flames are formed, wherein each spans between downstream walls of adjacent vanes and each downstream wall having a circumferential width sufficient to create a discrete outlet flow to create the plurality of discrete flames. 17. The system of claim 16 further comprising a plurality of means for mixing fuel and air. 18. The system of claim 16 further comprising a plurality of means for routing flow to said outlet windows. 19. The system of claim 16 further comprising a plurality of means for providing a lean combustible mixture of liquid fuel and air. 20. The system of claim 16 further comprising a combustion chamber in flow communication with said premix injector. 21. The system of claim 20 wherein the premix injector further includes a secondary stage, the premix injector is flow coupled to a gas turbine engine compressor stage, and the combustion products from the primary stage and the secondary stage are flow coupled to a turbine section of a gas turbine engine.

이 특허에 인용된 특허 (28)

Joshi Narendra D. (Cincinnati OH) Epstein Michael J. (West Chester OH), Air fuel mixer for gas turbine combustor having slots at downstream end of mixing duct.
상세보기
Fglistaller Cornel (Jonen CHX) Keller Jakob (Dottikon CHX) Sattelmayer Thomas (Mandach CHX), Burner system.
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Jones Bryn (Belper GB2) Slattery Sidney E. (Foston GB2), Combustion apparatus for gas turbine engines.
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Freeman, Christopher; Day, Ivor J.; Scarinci, Thomas, Combustion chamber.
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Scarinci, Thomas; Day, Ivor J; Freeman, Christopher, Combustion chamber.
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Scarinci, Thomas; Day, Ivor J; Freeman, Christopher, Combustion chamber.
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Maghon Helmut (Mlheim/Ruhr DEX) Becker Bernard (Mlheim/Ruhr DEX), Combustion chamber apparatus for combustion installations, especially for combustion chambers of gas turbine installatio.
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Brhwiler Eduard (Nussbaumen CHX) Koch Hans (Zurich CHX), Combustion chamber of a gas turbine with pre-mixing and pre-evaporation elements.
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Chyou Yau-Pin,TWX, Combustion chamber with two-stage combustion.
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Saito Isao (Hitachi JPX) Ishibashi Yoji (Hitachi JPX) Ohmori Takashi (Hitachi JPX) Minakawa Yoshimitsu (Hitachi JPX) Kuroda Michio (Hitachi JPX), Combustor for gas turbine.
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Peter Stuttaford CA; Stephen Oliver Oikawa CA; David Edwin Cowburn CA, Diffusion mixer.
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Joshi Narendra D. (Cincinnati OH) Kress Eric J. (Loveland OH), Dual fuel mixer for gas turbine combustor.
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Wiebe, David James; Koenig, Michael Herbert; Bland, Robert, Flame-holding, single-mode nozzle assembly with tip cooling.
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Shimizu Nobuo (Hitachi JPX) Kuroda Michio (Hitachi JPX) Kirikami Seiichi (Hitachi JPX) Sato Isao (Hitachi JPX) Arai Osamu (Hitachi JPX), Fuel-air premixing device for a gas turbine.
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Ito Kazuyuki (Hitachinaka JPX) Murakami Tadayoshi (Hitachi JPX) Kobayashi Nariyoshi (Hitachinaka JPX) Azuhata Shigeru (Hitachi JPX) Moritomo Yoshikazu (Hitachi JPX), Gas turbine combustor and gas turbine.
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Inoue, Hiroshi; Koganezawa, Tomomi; Kobayashi, Nariyoshi; Ohtsuka, Masaya; Ito, Kazuyuki; Takehara, Isao, Gas turbine combustor with fuel-air pre-mixer and pre-mixing method for low NOx combustion.
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Iwai Yasunori,JPX ; Okamoto Hiroaki,JPX ; Maeda Fukuo,JPX ; Itoh Masao,JPX, Gas turbine combustor with premixing and diffusing fuel nozzles.
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Hayashi,Akinori; Inage,Shinichi; Koizumi,Hiromi; Takehara,Isao; Ito,Kazuyuki; Sasao,Toshifumi; Murata,Hidetaro, Gas turbine combustor, combustion method of the gas turbine combustor, and method of remodeling a gas turbine combustor.
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Hayes-Bradley Samantha (Buckinghamshire GB2) Toon Ian J. (Leicestershire GB2) Willis Jeffrey D. (Coventry GB2), Gas turbine engine combustion chamber.
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Maghon Helmut (Mlheim/Ruhr DEX), Hybrid burner for a pre-mixing operation with gas and/or oil, in particular for gas turbine systems.
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Ryan William Richard, Low Nox combustor having dual fuel injection system.
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Pillsbury Paul W., Multiple venturi ultra-low nox combustor.
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Bonciani Luciano (Florence ITX) Ceccherini Gianni (Sesto Fiorentino ITX) Modi Roberto (Borgo S. Lorenzo ITX), Perfected combustion system with low polluting emissions for gas turbines.
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Krockow Wolfram (Dsseldorf DEX), Pre-mixing burner with integrated diffusion burner.
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Gutmark, Ephraim; Paschereit, Christian Oliver; Weisenstein, Wolfgang, Premix burner.
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Knopfel Hans Peter,CHX ; Bolis Giacomo,CHX, Premix burner.
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Washam Roy M. (Schenectady NY) Thibault ; Jr. Bernard A. (Clifton Park NY), Swirl gutters for isolating flow fields for combustion enhancement at non-baseload operating conditions.
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Widener,Stanley Kevin, Swirler configurations for combustor nozzles and related method.
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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

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Gas turbine engine premix injectors 원문보기

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Gas turbine engine premix injectors 원문보기

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