[특허]Gas turbine combustor including a diffusion nozzle assembly with a double cylindrical structure

Gas turbine combustor including a diffusion nozzle assembly with a double cylindrical structure 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F23R-003/30
출원번호	US-0266591 (1994-06-28)
우선권정보	JP-0157472 (1993-06-28)
발명자 / 주소	Takahara Takeshi (Yokohama JPX) Kobayashi Tadashi (Chigasaki JPX) Itoh Masao (Yokohama JPX)
출원인 / 주소	Kabushiki Kaisha Toshiba (Kawasaki JPX 03)
인용정보	피인용 횟수 : 63 인용 특허 : 0

초록 ▼

A gas turbine combustor comprises a cylindrical outer casing having one end closed by a header plate. A combustor liner provided with an inner combustion chamber which is divided into a first-stage combustion region on a side of the header plate and a second-stage combustion region formed on a downstream side of the first-stage combustion region. A first-stage fuel supply unit mounted to the header plate for injecting a first-stage fuel to the first-stage combustion region and a second-stage fuel supply unit mounted to the header plate for injecting a second-stage fuel previously mixed in a lean fuel state. The first-stage fuel supply unit includes a first-stage fuel nozzle assembly, which supplies the first-stage fuel, formed by combining a diffusion combustion nozzle and a pre-mixture combustion nozzle. The pre-mixture combustion nozzle has, at an intermediate portion thereof, a pre-mixing portion for preliminarily mixing the first-stage fuel with an air, and the pre-mixing portion having a diameter in a downstream portion thereof smaller than that of an upstream portion thereof so as to form a pre-mixed flow into a contraction flow. The pre-mixing fuel nozzle of the first stage fuel nozzle assembly is disposed so as to surround the diffusion combustion nozzle disposed in a central portion thereof.

대표청구항 ▼

A gas turbine combustor comprising: a cylindrical outer casing having one end opening closed by a header plate; a combustor liner disposed inside the outer casing and provided with an inner combustor chamber which is divided into a first-stage combustion region on a side of the header plate and a second-stage combustion region formed on a downstream side of the first-stage combustion region; and a fuel supplying means including a first-stage fuel supply means mounted to the header plate for injecting a first-stage fuel to the first-stage combustion region and a second-stage fuel supply means mounted to the header plate for injecting a second-stage fuel previously mixed in a lean fuel state, said first-stage fuel supply means comprising a first-stage fuel nozzle assembly which supplies the first-stage fuel and which is formed by combining a diffusion combustion nozzle acting as a pilot combustion nozzle and a pre-mixture combustion nozzle disposed independently from the diffusion combustion nozzle, said diffusion combustion nozzle being of a double cylindrical structure having a fuel passage portion extending in an axial direction thereof and an air passage portion formed in an outer peripheral portion of said fuel passage portion between the diffusion combustion nozzle and the pre-mixture combustion nozzle, said air passage portion being provided, on the first-stage combustion region side, with a first swirler means for imparting a swirling motion to air, and a fuel injection port for injecting fuel from the fuel passage portion, said fuel passage portion formed in said diffusion combustion nozzle being provided with a first fuel passage portion at a central portion thereof capable of supplying the first-stage fuel and a second fuel passage portion capable of supplying the first-stage fuel in a quantity different from the supply quantity through the first fuel passage portion, said first and second fuel passage portions being formed independently from each other, said pre-mixture combustion nozzle being disposed so as to concentrically surround the diffusion combustion nozzle for supplying the pre-mixture gas of air and fuel to the first-stage combustion region, said pre-mixture combustion nozzle having a double cylindrical structure having an annular fuel passage and an annular air passage surrounding the annular fuel passage, said annular air passage having an inlet side portion to which a second swirler means is disposed for causing swirling motion to the air, and a plurality of fuel injection nozzles being disposed in the annular air passage for forming an air and fuel pre-mixture region, and said second fuel supply means being provided with a plurality of fuel nozzles and a premixing portion for premixing air and fuel, and supplying the pre-mixture air and fuel to the second combustion region.

이 특허를 인용한 특허 (63)

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Melton, Patrick Benedict; Stoia, Lucas John; DiCintio, Richard Martin, Continuous combustion liner for a combustor of a gas turbine.
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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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Myers, Geoffrey D., Dual fuel combustor for a gas turbine engine including a toroidal injection manifold with inner and outer sleeves.
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Melton, Patrick Benedict; Stoia, Lucas John; DiCintio, Richard Martin, Flow sleeve assembly for a combustion module of a gas turbine combustor.
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DiCintio, Richard Martin; Melton, Patrick Benedict; Stoia, Lucas John; Willis, Christopher Paul; Pentecost, Ronnie Ray, Flow sleeve for a combustion module of a gas turbine.
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Stoia, Lucas John; DeForest, Russell Pierson; Melton, Patrick Benedict, Flowsleeve of a turbomachine component.
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Rohrssen, Robert Joseph; Cihlar, David William; Melton, Patrick Benedict; Stoia, Lucas John, Fuel delivery system with moveably attached fuel tube.
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Chen, Wei; Stoia, Lucas John; DiCintio, Richard Martin, Fuel injection assemblies in combustion turbine engines.
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William Theodore Bechtel ; David Orus Fitts ; Guy Wayne DeLeonardo, Gas only nozzle.
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William Theodore Bechtel ; David Orus Fitts ; Guy Wayne DeLeonardo, Gas only nozzle fuel tip.
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Byrne, William; Melton, Patrick Benedict; Cihlar, David William; Stoia, Lucas, Integrated late lean injection on a combustion liner and late lean injection sleeve assembly.
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Romig, Bryan Wesley; Stoia, Lucas John, System for supplying fuel to late-lean fuel injectors of a combustor.
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Melton, Patrick Benedict; Vanselow, John; DeForest, Russell; Stoia, Lucas, Systems and methods for late lean injection premixing.
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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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연합인증

Gas turbine combustor including a diffusion nozzle assembly with a double cylindrical structure 원문보기

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Gas turbine combustor including a diffusion nozzle assembly with a double cylindrical structure 원문보기

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연구과제 타임라인

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이 특허를 인용한 특허 (63)

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