Air-assisted fuel injector for mixer assembly of a gas turbine engine combustor
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/14
F23R-003/04
출원번호
US-0188470
(2005-07-25)
등록번호
US-7464553
(2008-12-16)
발명자
/ 주소
Hsieh,Shih Yang
Hsiao,George Chia Chun
Li,Shui Chi
Mongia,Hukam Chand
출원인 / 주소
General Electric Company
대리인 / 주소
Anders,William Scott
인용정보
피인용 횟수 :
22인용 특허 :
14
초록▼
A mixer assembly for use in a combustion chamber of a gas turbine engine includes a pilot mixer, a main mixer, and a fuel manifold positioned between the pilot mixer and main mixer. The pilot mixer includes an annular pilot housing having a hollow interior and a pilot fuel nozzle mounted in the hous
A mixer assembly for use in a combustion chamber of a gas turbine engine includes a pilot mixer, a main mixer, and a fuel manifold positioned between the pilot mixer and main mixer. The pilot mixer includes an annular pilot housing having a hollow interior and a pilot fuel nozzle mounted in the housing and adapted for dispensing droplets of fuel to the hollow interior of the pilot housing. The main mixer includes: a main housing surrounding the pilot housing and defining an annular cavity; a plurality of fuel injection ports for introducing fuel into the cavity; a post member associated with and extending from each fuel injection port to an inner surface of said annular cavity, the post member including an inner passage therethrough in flow communication with the fuel injection port; a passage surrounding each post member, wherein air is provided therefrom to envelop fuel injected into the annular cavity; and, a swirler arrangement including at least one swirler positioned upstream from the fuel injection ports, wherein each swirler of the arrangement has a plurality of vanes for swirling air traveling through such swirler to mix air and the droplets of fuel dispensed by the fuel injection ports. The air through the passages is either injected substantially straight through or swirled a predetermined amount.
대표청구항▼
What is claimed is: 1. A mixer assembly for use in a combustion chamber of a gas turbine engine, comprising: (a) a pilot mixer including an annular pilot housing having a hollow interior and a pilot fuel nozzle mounted in said housing and adapted for dispensing droplets of fuel to said hollow inter
What is claimed is: 1. A mixer assembly for use in a combustion chamber of a gas turbine engine, comprising: (a) a pilot mixer including an annular pilot housing having a hollow interior and a pilot fuel nozzle mounted in said housing and adapted for dispensing droplets of fuel to said hollow interior of said pilot housing; (b) a main mixer including: (1) a main housing surrounding said pilot housing and defining an annular cavity; (2) a plurality of fuel injection ports for introducing fuel into said annular cavity; (3) a post member associated with and extending from each said fuel injection port to an inner surface of said annular cavity, said post member including an inner passage therethrough in flow communication with said fuel injection port; (4) a passage surrounding each said post member, wherein air is provided therefrom to envelop fuel injected into said annular cavity; and, (5) a swirler arrangement including at least one swirler positioned upstream from said fuel injection ports, wherein each swirler of said arrangement has a plurality of vanes for swirling air traveling through such swirler to mix air and said droplets of fuel dispensed by said fuel injection ports; and, (c) a fuel manifold positioned between said pilot mixer and said main mixer, wherein said plurality of fuel injection ports for introducing fuel into said main mixer cavity are in flow communication with said fuel manifold. 2. The mixer assembly of claim 1, wherein air flows substantially straight through said passages surrounding said post members into said annular cavity. 3. The mixer assembly of claim 1, wherein air is swirled through said passages surrounding said post members into said annular cavity. 4. The mixer assembly of claim 3, wherein air is swirled through said passages surrounding said post members at an angle of about 20�� to about 40�� with respect to an axis oriented substantially perpendicular to a centerline axis through said mixer assembly. 5. The mixer assembly of claim 3, wherein air through said passages surrounding said post members is swirled in a direction opposite air swirled by said swirler. 6. The mixer assembly of claim 1, further comprising a swirler member including: (a) a substantially planar first ring-shaped portion having a central opening therein adjacent said fuel injection port; and, (b) a second ring-shaped portion extending from said first portion and including a plurality of spaced openings formed in a side wall thereof; wherein compressed air enters said spaced openings to impart swirl to air exiting said passage surrounding said post member. 7. The mixer assembly of claim 1, further comprising a swirler member including: (a) a substantially planar ring-shaped portion having a central opening therein adjacent said fuel injection port; and, (b) a plurality of vanes extending from a top surface of said ring-shaped portion so that a passage is formed between adjacent vanes; wherein compressed air enters said passages to impart swirl to air exiting said passage surrounding said post member. 8. The mixer assembly of claim 1, wherein said passages surrounding said post members are oriented substantially coaxially around said post members. 9. The mixer assembly of claim 1, wherein a ratio of fuel through said fuel injection ports to air through said passages surrounding said post members is about 3 to about 6. 10. The mixer assembly of claim 1, further comprising openings between each said fuel injection port in flow communication with compressed air. 11. The mixer assembly of claim 1, said swirler arrangement further comprising at least one swirler oriented substantially radially to a centerline axis through said mixer assembly. 12. The mixer assembly of claim 1, said swirler arrangement further comprising at least one swirler oriented at an acute angle to a centerline axis through said mixer assembly. 13. The mixer assembly of claim 1, said swirler arrangement further comprising at least one swirler oriented substantially parallel to a centerline axis through said mixer assembly. 14. The mixer assembly of claim 1, wherein fuel droplets from said fuel injection ports are able to penetrate to a designated position within said annular cavity. 15. The mixer assembly of claim 1, further comprising a plurality of purge openings located downstream of said fuel injection ports in flow communication with compressed air. 16. The mixer assembly of claim 15, wherein said purge openings are spaced in an annular fashion around said annular cavity so as to be substantially planar. 17. The mixer assembly of claim 16, wherein said openings are located downstream of said swirler arrangement. 18. The mixer assembly of claim 1, wherein said fuel injection ports are positioned adjacent a ramp portion of said annular cavity located at an upstream end thereof. 19. The mixer assembly of claim 1, wherein compressed air is supplied to said passages surrounding said post members by means of an air cavity located between said fuel manifold and said annular cavity. 20. A mixer assembly for use in a combustion chamber of a gas turbine engine, comprising: (a) a pilot mixer including an annular pilot housing having a hollow interior and a pilot fuel nozzle mounted in said housing and adapted for dispensing droplets of fuel to said hollow interior of said pilot housing; (b) a main mixer including: (1) a main housing surrounding said pilot housing and defining an annular cavity; (2) a plurality of fuel injection ports for introducing fuel into said annular cavity; (3) a plurality of circumferentially spaced passages located in a downstream portion of said annular cavity, wherein air is provided to force a fuel/air mixture from residing along an inner surface of said annular cavity; and, (4) a swirler arrangement including at least one swirler positioned upstream from said fuel injection ports, wherein each swirler of said arrangement has a plurality of vanes for swirling air traveling through such swirler to mix air and said droplets of fuel dispensed by said fuel injection portions; and, (d) a fuel manifold positioned between said pilot mixer and said main mixer, wherein said plurality of fuel injection ports for introducing fuel into said main mixer cavity are in flow communication with said fuel manifold.
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이 특허에 인용된 특허 (14)
Arthur Wesley Johnson ; Timothy James Held ; Hukam Chand Mongia ; Michael Louis Vermeersch, Combustor mixer having plasma generating nozzle.
Harjit Singh Hura ; Paul Edward Sabla ; James Neil Cooper ; Beverly Stephenson Duncan ; Hukam Chand Mongia ; Steven Joseph Lohmueller, Fuel nozzle assembly for reduced exhaust emissions.
Falls Stephen W. (Cincinnati OH) Kress Eric J. (Loveland OH) Savelli Joseph F. (West Chester OH) Cooper James N. (Hamilton OH) Pritchard ; Jr. Byron A. (Loveland OH), Integral combustor splash plate and sleeve.
Mancini, Alfred A.; Vermeersch, Michael L.; Thomsen, Duane D.; Danis, Allen M.; Cooper, James N.; Lohmueller, Steven J.; Mongia, Hukam C., Method and apparatus to decrease combustor emissions.
Byron Andrew Pritchard, Jr. ; Allen Michael Danis ; Michael Jerome Foust ; Mark David Durbin ; Hukam Chand Mongia, Multiple annular combustion chamber swirler having atomizing pilot.
Kopp-Vaughan, Kristin; Snyder, Timothy S; Smith, Randolph J; Dai, Zhongtao, Dual fuel nozzle with swirling axial gas injection for a gas turbine engine.
Dai, Zhongtao; Cohen, Jeffrey M.; Fotache, Catalin G., Mixer assembly for a gas turbine engine having a pilot mixer with a corner flame stabilizing recirculation zone.
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