[특허]Flamesheet combustor dome

Flamesheet combustor dome 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F23R-003/54 F23R-003/26 F23R-003/60 F23R-003/14 F23R-003/16 F23R-003/34 F23R-003/28
출원번호	US-0038064 (2013-09-26)
등록번호	US-9752781 (2017-09-05)
발명자 / 주소	Stuttaford, Peter John Jorgensen, Stephen Hui, Timothy Chen, Yan Rizkalla, Hany Oumejjoud, Khalid
출원인 / 주소	ANSALDO ENERGIA IP UK LIMITED
대리인 / 주소	Hovey Williams LLP
인용정보	피인용 횟수 : 0 인용 특허 : 30

초록 ▼

The present invention discloses a novel apparatus and way for controlling a velocity of a fuel-air mixture entering a gas turbine combustion system. The apparatus comprises a hemispherical dome assembly which directs a fuel-air mixture along a portion of the outer wall of a combustion liner and turns the fuel-air mixture to enter the combustion liner in a manner coaxial to the combustor axis and radially outward of a pilot fuel nozzle so as to regulate the velocity of the fuel-air mixture.

대표청구항 ▼

1. A gas turbine combustor comprising: a generally cylindrical flow sleeve extending along a combustor axis;a generally cylindrical combustion liner located coaxial to and radially within the flow sleeve, the combustion liner having an inlet end and an opposing outlet end;a set of main fuel injectors positioned radially outward of the combustion liner and proximate an upstream end of the flow sleeve;a combustor dome assembly encompassing the inlet end of the combustion liner, the dome assembly extending from proximate the set of main fuel injectors to a generally hemispherical-shaped cap positioned a distance forward of the inlet end of the combustion liner and turns to extend a distance into the combustion liner, such that a first passageway and a second passageway are formed between the combustion liner and a dome assembly outer wall and a third passageway is formed between the combustion liner and a dome assembly inner wall, where the first passageway has a first radial height, the second passageway has a second radial height and the third passageway has a third radial height such that the second radial height regulates the volume of a fuel-air mixture entering the gas turbine combustor;wherein the first radial height ranges from approximately 15 millimeters to approximately 50 millimeters;wherein the second radial height ranges from approximately 10 millimeters to approximately 45 millimeters; andwherein the third radial height ranges from approximately 30 millimeters to approximately 100 millimeters, such that the first passageway tapers towards the second passageway to accelerate the fuel-air mixture to achieve adequate flashback margin velocity of 40-80 meters per second to generate a trapped vortex adjacent the combustor liner. 2. The gas turbine combustor of claim 1, further comprising a fourth passageway having a fourth height as measured between the inlet end of the combustion liner and the combustor dome assembly. 3. The gas turbine combustor of claim 1, wherein the largest height of the first passageway occurs at a region adjacent the set of main fuel injectors. 4. The gas turbine combustor of claim 1, wherein the second and third passageways are cylindrical. 5. A method of controlling a velocity of a fuel-air mixture for a gas turbine combustor comprising: directing a fuel-air mixture through a first passageway located radially outward of a combustion liner, the first passageway having a first radial height;directing the fuel-air mixture from the first passageway and into a second passageway located radially outward of the combustion liner, the second passageway having a second radial height;directing the fuel-air mixture from the second passageway into a fourth passageway in a hemispherical dome cap, thereby causing the fuel-air mixture to reverse flow direction; anddirecting the fuel-air mixture through a third passageway located within the combustion liner and into the combustion liner, the third passageway having a third radial height;wherein the first radial height ranges from approximately 15 millimeters to approximately 50 millimeters;wherein the second radial height ranges from approximately 10 millimeters to approximately 45 millimeters;wherein the third radial height ranges from approximately 30 millimeters to approximately 100 millimeters such that a ratio of the second radial height to the third radial height is approximately 0.1 to 0.5; andwherein the first passageway has a conical-shaped cross section that tapers towards the second passageway;wherein the second passageway has a cylindrical-shaped cross section; andwherein the third passageway has a cylindrical-shaped cross section. 6. The method of claim 5, wherein the second passageway contains a minimal cross sectional area between the first, second and third passageways. 7. The method of claim 5, wherein the ratio of the second radial height to the third radial height generates a trapped vortex. 8. The method of claim 5, wherein a wall of the combustion liner forms parts of the first, second and third passageways.

이 특허에 인용된 특허 (30)

Oumejjoud,Khalid; Stuttaford,Peter; Chen,Yan; Margarit Bel,Nuria; Jennings,Stephen, Apparatus and method for reducing carbon monoxide emissions.
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Buchner Horst,FRX ; Leuckel Wolfgang,DEX, Apparatus for suppressing flame/pressure pulsations in a furnace, particularly a gas turbine combustion chamber.
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Eroglu, Adnan; Stuber, Peter; Paschereit, Christian Oliver; Knoepfel, Hans Peter, Burner system with staged fuel injection and method for its operation.
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Varney, Brian A., Combustion chamber.
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Dobbeling Klaus (Nussbaumen CHX) Knopfel Hans P. (Besenburen CHX) Sattelmayer Thomas (Mandach CHX), Combustion process for atmospheric combustion systems.
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Tanimura, Satoshi; Kurihara, Kenta; Saitoh, Toshihiko; Rodriguez, Jose, Combustor.
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Tanimura, Satoshi; Kurihara, Kenta; Saitoh, Toshihiko; Rodriguez, Jose, Combustor.
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Bunker,Ronald Scott; Bailey,Jeremy Clyde; Widener,Stanley Kevin; Johnson,Thomas Edward, Combustor cooling with angled segmented surfaces.
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Parker David Marchant ; Whidden Graydon Lane ; Zolyomi Wendel, Combustor with two stage primary fuel tube with concentric members and flow regulating.
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Stuttaford,Peter; Chen,Yan, Counter swirl shear mixer.
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Puri Rahul ; Razdan Mohan K. ; Smith Duane A. ; Stansel David M., Dry low oxides of nitrogen lean premix module for industrial gas turbine engines.
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Bigelow Elwin C. (Scotia NY) Gulati Anil (Schenectady NY), Flameholder for gas turbine engine afterburner.
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Stuttaford, Peter J.; Jennings, Stephen; Green, Andrew; McMahon, Ryan; Chen, Yan; Rizkalla, Hany; Carella, John; Duraibabu, Vamsi; Spalding, Martin, Flamesheet combustor.
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Stuttaford, Peter John, Flashback suppression system for a gas turbine combustor.
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Lovett Jeffery Allan (Scotia NY), Fuel nozzle for low-NOx combustor burners.
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Corr, II,Robert Anthony; Caron,Tim; Barnes,John, Fuel-air premixing system for a catalytic combustor.
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Kawata, Yutaka; Mandai, Shigemi; Tsukuda, Yoshiaki; Akita, Eiji; Arimura, Hisato, Gas turbine and gas turbine combustor.
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Maeda Fukuo (Machida JPX) Watanabe Michio (Ayase JPX) Narabe Atsushi (Yokohama JPX) Sato Hiroya (Yokohama JPX), Gas turbine apparatus.
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Urushidani Haruo (Hitachi JPX) Kirikami Seiichi (Hitachi JPX) Sato Isao (Hitachi JPX) Shimizu Nobuo (Hitachi JPX) Arai Osamu (Hitachi JPX) Shimura Akira (Hitachi JPX) Kuroda Michio (Hitachi JPX) Koga, Gas turbine combustor and methodd of operating the same.
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Matsumoto, Kiyoshi; Oda, Takeo, Gas turbine combustor including separate fuel injectors for plural zones.
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Cowell Luke H. (San Diego CA) Roberts Peter B. (Encinitas CA), Gas turbine engine catalytic and primary combustor arrangement having selective air flow control.
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Maeda Fukuo,JPX ; Iwai Yasunori,JPX ; Sato Yuzo,JPX, Gas turbine multi-stage combustion system.
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Cihlar, David William; Melton, Patrick Benedict, Method and apparatus for mounting transition piece in combustor.
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Stuttaford,Peter; Margarit Bel,Nuria; Chen,Yan; Oumejjoud,Khalid; Jennings,Stephen, Method of operating a combustion system for increased turndown capability.
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Stuttaford,Peter J.; Jennings,Stephen; Chen,Yan, Method of operating a flamesheet combustor.
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Lacy, Benjamin Paul; Kraemer, Gilbert Otto; Varatharajan, Balachandar; Yilmaz, Ertan; Lipinski, John Joseph; Ziminsky, Willy Steve, Methods and systems to facilitate reducing NO.
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Stuttaford, Peter; Jennings, Stephen, Self-purging pilot fuel injection system.
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Toon, Ian J.; O'Dell, Stephen J.; Currin, John H.; Willis, Jeffrey D., Staged gas turbine combustion chamber with counter swirling arrays of radial vanes having interjacent fuel injection.
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Moreno Frederick E. (Los Altos CA) Joshi Narendra D. (Phoenix AZ), Staged lean premix low nox hot wall gas turbine combustor with improved turndown capability.
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Joshi Narendra D. (Phoenix AZ) Moreno Frederick E. (Los Altos CA), Staged low NOx premix gas turbine 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

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Flamesheet combustor dome 원문보기

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Flamesheet combustor dome 원문보기

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연구과제 타임라인

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