[특허]Fuel nozzle for use in a turbine engine and method of assembly

Fuel nozzle for use in a turbine engine and method of assembly 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F23R-003/28 F23D-014/64 F23D-014/62
출원번호	US-0687103 (2012-11-28)
등록번호	US-9677766 (2017-06-13)
발명자 / 주소	Abd El-Nabi, Bassam Sabry Mohammad Boardman, Gregory Allen
출원인 / 주소	GENERAL ELECTRIC COMPANY
대리인 / 주소	Darling, John P.
인용정보	피인용 횟수 : 0 인용 특허 : 32

초록 ▼

A fuel nozzle for use in a turbine engine is provided. The fuel nozzle includes a fuel injector configured to discharge a flow of fuel therefrom and a premixer tube coupled in flow communication with the fuel injector. The premixer tube is configured to receive the fuel flow and a flow of air at an upstream end of the premixer tube, wherein the fuel and air are progressively mixed as the fuel and air are channeled through the length of the premixer tube.

대표청구항 ▼

1. A fuel nozzle for use in a turbine engine comprising: a nozzle body;a liquid fuel injector configured to discharge liquid fuel therefrom; anda plurality of premixer tubes defined within and extending through said nozzle body, each of said plurality of premixer tubes coupled in flow communication with said liquid fuel injector and configured to receive a flow of liquid fuel and a flow of air at an upstream end of said plurality of premixer tubes, wherein the flow of liquid fuel and the flow of air in each premixer tube are progressively mixed as the flow of liquid fuel and the flow of air are channeled through each premixer tube, wherein said liquid fuel injector comprises a plurality of fuel spokes that each comprises a hollow tube that are straight and having a plurality of injection ports defined therein that are each configured to discharge liquid fuel therefrom, and each said injection port substantially coaxially aligns with a corresponding premixer tube centerline axis and is configured to direct a liquid fuel jet substantially axially into said corresponding premixer tube, wherein each liquid fuel jet comprises a discharge angle of 5° to 15° with respect to the corresponding premixer tube centerline axis, wherein said plurality of fuel spokes extend through said nozzle body and through said plurality of premixer tubes substantially perpendicularly with respect to the centerline axes of the plurality of premixer tubes. 2. The fuel nozzle in accordance with claim 1, wherein said fuel injector comprises: a plurality of gas fuel passages extending through said nozzle body substantially perpendicularly with respect to said plurality of premixer tube; anda plurality of as fuel injection ports defined within said nozzle body and configured to couple said plurality of gas fuel passages in flow communication with said plurality of premixer tubes. 3. The fuel nozzle in accordance with claim 1 further comprising an air plenum positioned upstream from said plurality of premixer tubes. 4. The fuel nozzle in accordance with claim 3, wherein said air plenum is configured to direct the air flow substantially axially into each of said plurality of premixer tubes. 5. The fuel nozzle in accordance with claim 1 further comprising: a heat shield coupled to a downstream end of said nozzle body; anda cooling passage extending through said nozzle body, said cooling passage configured to direct a second flow of air towards said heat shield to cool the heat shield.

이 특허에 인용된 특허 (32)

Bergt Wolfgang (Munich DT), Aerodynamic flame holder.
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Joshi Narendra D. (Cincinnati OH) Epstein Michael J. (West Chester OH) Ewbank Michael E. (Pittsburgh PA), Air fuel mixer for gas turbine combustor.
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Boardman, Gregory Allen; Melton, Patrick Benedict; Simu, Christine Elaine, Apparatus for fuel injection in a turbine engine.
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Halila, Ely Eskenazi; Anderson, Michael, Apparatus for injecting fuel into gas turbine engines.
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Manoharan, Madanmohan; Kulkarni, Rahul R.; Bathina, Mahesh, Combustor.
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Uhm, Jong Ho; Wu, Chunyang; Berry, Jonathan Dwight; Stewart, Jason Thurman, Combustor and method for conditioning flow through a combustor.
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Jeroszko Ronald A. (Hebron CT), Combustor employing serially staged pilot combustion, fuel vaporization, and primary combustion zones.
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Bland, Robert; Battaglioli, John, Combustor nozzle.
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Fitts David O. (Charlton NY), Dry low NOx multi-nozzle combustion liner cap assembly.
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Joshi Narendra D. (Cincinnati OH) Ekstedt Edward E. (Cincinnati OH), Dual fuel mixer for gas turbine combustor.
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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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Pillsbury Paul W. (Winter Springs FL) Foss David T. (Winter Park FL), Dual fuel ultra-low NOX combustor.
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Fehler Adolf (Pfaffing DT), Fuel admitting and conditioning means on combustion chambers for gas turbine engines.
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Ely E. Halila ; Stuart C. Greenfield ; Paul V. Heberling ; John D. Bibler ; John A. Kastl, Fuel air mixer for a radial dome in a gas turbine engine combustor.
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Sprouse, Kenneth M; Farhangi, Shahram; von Arx, Alan V.; Matthews, David R., Fuel injection method and apparatus for a combustor.
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Howell Stephen J. ; Cohen Joseph D., Fuel injector and multi-swirler carburetor assembly.
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Johnson, Thomas Edward; Ziminsky, Willy Steve; Lacey, Benjamin Paul; York, William David; Stevenson, Christian Xavier, Fuel nozzle assembly.
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Mandai Shigemi,JPX ; Ota Masataka,JPX ; Tanimura Satoshi,JPX ; Haruta Hideki,JPX, Gas turbine combustor.
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Mandai Shigemi,JPX ; Kawabata Hitoshi,JPX ; Nishida Koichi,JPX, Gas turbine combustor having multiple burner groups and independently operable pilot fuel injection systems.
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McWhirter Anthony (Niagara Falls CAX) Colautti Eugenio (Mississauga FL CAX) Amos David J. (Orlando FL), Gas turbine ultra low NOx combustor.
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Morenko, Oleg; Parkman, Kenneth; Phillips, Stephen, Interface between a combustor and fuel nozzle.
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Johnson, Thomas Edward; Lacy, Benjamin; Stevenson, Christian, Internal baffling for fuel injector.
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Hansel Harold R. ; Cook George E., Internal manifold fuel injection assembly for gas turbine.
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Ryan William Richard, Low Nox combustor having dual fuel injection system.
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Markowski Stanley J. (East Hartford CT) Reilly Richard S. (East Hartford CT), Low emission combustion chamber.
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Dean Anthony John, Low emissions combustor premixer.
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Davis, Jr., Lewis Berkley; Johnson, Thomas Edward; Stewart, Jason Thurman, Method and apparatus for delivery of a fuel and combustion air mixture to a gas turbine engine using fuel distribution grooves in a manifold disk with discrete air passages.
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Stalder, Marcel; Burri, Daniel; Benz, Urs, Method for operating a combustion chamber.
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Striebel ; Edmund Emil ; Koblish ; Theodore Richard ; Madden ; Thomas Joseph ; James ; Roger Halsted, Premix combustor.
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York, William David; Ziminsky, Willy Steve; Johnson, Thomas Edward; Lacy, Benjamin; Zuo, Baifang; Uhm, Jong Ho, Premixed direct injection disk.
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Matt Bernhard (Rheinheim DEX) Woringer Theo (Zurich CHX) Zouzoulas Gerassime (Dietikon CHX), Ring combustion chamber with ring burner for gas turbines.
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Uhm, Jong Ho; Johnson, Thomas Edward; Zuo, Baifang; York, William David, System and method for reducing combustion dynamics in a combustor.
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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

내보내기 구분	파일저장 인쇄 메일전송
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연합인증

Fuel nozzle for use in a turbine engine and method of assembly 원문보기

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Fuel nozzle for use in a turbine engine and method of assembly 원문보기

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연구과제 타임라인

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