[특허]Dual fuel nozzle with swirling axial gas injection for a gas turbine engine

Dual fuel nozzle with swirling axial gas injection for a gas turbine engine 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F23R-003/12 F23R-003/14 F23R-003/28 F23R-003/36 F23D-011/10 F23C-001/08
출원번호	US-0914802 (2014-08-19)
등록번호	US-10228137 (2019-03-12)
국제출원번호	PCT/US2014/051585 (2014-08-19)
국제공개번호	WO2015/076883 (2015-05-28)
발명자 / 주소	Kopp-Vaughan, Kristin Snyder, Timothy S Smith, Randolph J Dai, Zhongtao
출원인 / 주소	United Technologies Corporation
대리인 / 주소	Bachman & LaPointe, P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 21

초록 ▼

A fuel nozzle for a combustor of a gas turbine engine includes an outer air swirler along an axis, the outer air swirler defines an outer annular air passage. An inner air swirler along the axis defines an annular fuel gas passage around the axis between the outer air swirler and the inner air swirl

대표청구항 ▼

1. A fuel nozzle for a combustor of a gas turbine engine comprising: an outer air swirler along an axis, the outer air swirler defines an outer annular air passage;an inner air swirler along the axis to define an annular fuel gas passage between the outer air swirler and the inner air swirlera multiple of vanes within the annular fuel gas passage that extend radially inward from an inner wall of the outer air swirler, each of the multiple of vanes defined by an airfoil wall surface between a leading edge and a trailing edge, the trailing edge of each of the multiple of vanes, the outer air swirler, and the inner air swirler form a multiple of skewed quadrilateral exits such that an angle of swirl from the multiple of skewed quadrilateral exits is greater than an angle of swirl from the outer annular air passage and the annular fuel gas passage;an air inflow tube along the axis within the inner air swirler, the air inflow tube defines a central air passage; anda helical inflow vane within the air inflow tube, the inner air swirler and the air inflow tube define an annular liquid passage therebetween. 2. The fuel nozzle as recited in claim 1, wherein each of the multiple of skewed slots extends radially inward from an inner wall of an outer air seal. 3. The fuel nozzle as recited in claim 2, wherein each of the multiple of vanes extend radially inward toward an outer wall of the inner air seal. 4. The fuel nozzle as recited in claim 1, wherein the annular gas passage directs one hundred (100) percent of a fuel gas through the multiple of skewed slots. 5. A method of directing a fuel gas and a liquid through a fuel nozzle and into a combustor of a gas turbine engine, comprising: directing an airflow through an outer annular air passage;directing one hundred (100) percent of the fuel gas through an annular fuel gas passage radially within the outer annular air passage;directing the liquid though an annular liquid passage radially within the annular fuel gas passage between an inner air swirler and an air inflow tube, a helical inflow vane within the air inflow tube along the axis within the inner air swirler, the air inflow tube defines a central air passage; andswirling the fuel gas through a multiple of vanes within the annular fuel gas passage that extend radially inward from an inner wall of the outer air swirler, each of the multiple of vanes defined by an airfoil wall surface between a leading edge and a trailing edge, the trailing edge of each of the multiple of vanes, the outer air swirler, and the inner air swirler form a multiple of skewed quadrilateral exits such that the angle of swirl from the multiple of skewed quadrilateral exits is greater than an angle of swirl from the outer annular air passage and the annular fuel gas passage. 6. The method as recited in claim 5, further comprising: directing an airflow through the central air passage radially within the annular liquid passage. 7. The method as recited in claim 6, further comprising: swirling the airflow within the central air passage. 8. The method as recited in claim 7, further comprising: directing the airflow through the outer annular air passage at least partially radially inward. 9. The method as recited in claim 8, further comprising: directing the liquid at least partially radially inward.

이 특허에 인용된 특허 (21)

Hsieh,Shih Yang; Hsiao,George Chia Chun; Li,Shui Chi; Mongia,Hukam Chand, Air-assisted fuel injector for mixer assembly of a gas turbine engine combustor.
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Mandai Shigemi (Takasago JPX) Satoh Nobuo (Takasago JPX) Fukue Ichiro (Takasago JPX) Tanimura Satoshi (Takasago JPX), Burner apparatus.
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Onoda Akihiro,JPX ; Iwai Yasunori,JPX, Coal gasification combined cycle power generation plant and an operating method thereof.
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Lockyer John F. ; Oskam Gareth W. ; Rawlins Douglas C., Dual fuel injection method and apparatus with multiple air blast liquid fuel atomizers.
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Madden Thomas J. (Vernon CT) Schlein Barry C. (Wethersfield CT) Wagner W. Barry (Bolton CT), Dual fuel injector.
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Beebe Kenneth W. (Galway NY) Gardy Victor R. (Shelburne VT), Dual fuel injector with premixing capability for low emissions combustion.
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Gomez Guillermo V. ; Zelina Joseph, Elliptical axial combustor swirler.
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Stratton John F. (Blackburn GB2), Fuel injector.
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Lee Fei P. (Novi MI) Guzowski Mike (Canton MI), Fuel injector assembly with first and second fuel injectors and inner, outer, and intermediate air discharge chambers.
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Bradley Jerome R. (Sterling Heights MI), Fuel injector assembly with water or auxiliary fuel capability.
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Bell Lance P.,GBX ; Munro Kevin M.,GBX, Fuel injector with purge passage.
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Lee Fei P. (Novi MI) Koblish Theodore R. (Holland MI) Bradley Jerome R. (Holland MI), Fuel purging fuel injector.
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Koizumi, Hiromi; Sekiguchi, Tatsuya; Hayashi, Akinori, Gas turbine combustor with two kinds of gas fuel supply systems.
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Willis Jeffrey D. (Coventry GB2), Gas turbine engine fuel injectors.
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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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Pelletier Robert R., Internally heatshielded nozzle.
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Pelletier Robert R., Internally heatshielded nozzle.
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Hoke James B. ; Segalman Irving ; Siskind Kenneth S. ; Smith Reid D. C., Low NOx combustor for gas turbine engine.
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Faulkner Robie L. (Alpine CA), Low NOx injector with central air swirling and angled fuel inlets.
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Harjit S. Hura, Methods and apparatus for decreasing combustor emissions.
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Pelletier Robert R. ; Patwari Kiran, Thermal gradient dispersing heatshield assembly.
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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

Dual fuel nozzle with swirling axial gas injection for a gas turbine engine 원문보기

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Dual fuel nozzle with swirling axial gas injection for a gas turbine engine 원문보기

초록 ▼

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연구과제 타임라인

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이 특허에 인용된 특허 (21)

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