Centerbody for a two stream tangential entry nozzle
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0770282
(1996-12-20)
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발명자
/ 주소 |
- Kramer Stephen K.
- Hauck Peter F.
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출원인 / 주소 |
- United Technologies Corporation
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
5 인용 특허 :
2 |
초록
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A centerbody for a tangential entry fuel nozzle includes a base having at least one air supply port extending therethrough, a radially outer surface including a frustum portion and a cylindrical portion, an internal passageway which communicates with an internal chamber through a swirler, and a fuel
A centerbody for a tangential entry fuel nozzle includes a base having at least one air supply port extending therethrough, a radially outer surface including a frustum portion and a cylindrical portion, an internal passageway which communicates with an internal chamber through a swirler, and a fuel lance extending through the base, the internal chamber, and the swirler, and terminating within the second cylindrical passage.
대표청구항
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[ We claim:] [1.] A centerbody for a tangential entry fuel nozzle, comprising:a longitudinal axis,a centerbody base, said centerbody base having at least one air supply port extending therethrough,a radially outer surface including a frustum portion defining the outer surface of a frustum that is co
[ We claim:] [1.] A centerbody for a tangential entry fuel nozzle, comprising:a longitudinal axis,a centerbody base, said centerbody base having at least one air supply port extending therethrough,a radially outer surface including a frustum portion defining the outer surface of a frustum that is coaxial with the longitudinal axis and flares toward the centerbody base thereof, and a cylindrical portion which is integral with the frustum portion and defines the outer surface of a cylinder, said frustum portion between said cylindrical portion and said centerbody base,an internal passageway coaxial with the longitudinal axis and including a first cylindrical passage, a second cylindrical passage, and a tapered passage, each passage having a first end and a second end, said second cylindrical passage having a diameter greater than said first cylindrical passage, said second cylindrical passage communicating with said first cylindrical passage through said tapered passage, said first end of said tapered passage integral with said second end of said first cylindrical passage, said second end of said tapered passage integral with said first end of said second cylindrical passage, said first end of said tapered passage having a diameter equal to the diameter of the first cylindrical passage, and said second end of said tapered passage having a diameter equal to the diameter of the second cylindrical passage, each of said passages coaxial with the longitudinal axis, said first cylindrical passage includes a discharge orifice that is circular, coaxial with said axis and located at the first end of said first cylindrical passage,an internal chamber located between said centerbody base and said second end of said second cylindrical passage, said at least one air supply port communicating with said second cylindrical passage through said chamber,a swirler coaxial with the axis and is located within the chamber immediately adjacent the second end of the second cylindrical passage, anda fuel lance coaxial with said axis and extending through said centerbody base, said internal chamber, and said swirler, and terminating within said second cylindrical passage.
이 특허에 인용된 특허 (2)
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Simmons Harold C. (Richmond Heights OH) Conrad Robert R. (Chardon OH) Orav Mihkel (Euclid OH), Air-atomizing fuel nozzle.
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Girardin Pierre (St Herblain FRX) Duplan Max (Champagne au Mont d\Or FRX), High pressure snow gun.
이 특허를 인용한 특허 (5)
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Duncan, Beverly Stephenson; Benjamin, Michael Anthony; Hsiao, George Chia-Chun; Mongia, Hukam Chand, Fuel nozzle centerbody and method of assembling the same.
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Oskam, Gareth W., Gas turbine and fuel injector for the same.
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Bhagat, Reena, Late lean injection injector.
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Oskam, Gareth W., Lean direct fuel injector.
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Oskam, Gareth W., Method of operating a gas turbine engine.
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