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특허 상세정보

After-burning turbo-fan engine with a fixed geometry exhaust nozzle having a variable flow coefficient

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-001/28   
미국특허분류(USC) 60/204 ; ; 60/231 ; ; 60/242 ; ; 60/261
출원번호 US-0252191 (1994-06-01)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 18  인용 특허 : 0
초록

An after-burning turbo-fan engine system (10) includes turbo-fan engine (14) for producing exhaust gas (20), and jet thrust therefrom. After-burning chamber (16) receives turbo-fan exhaust and injects a controllable amount of fuel into turbo-fan exhaust to cause after burning of the turbo-fan exhaust to produce after-burned exhaust (20). Nozzle (18) associates with after-burning chamber (16) for receiving after-burned exhaust (20). Nozzle (18) has a fixed geometry. Nozzle (18) flow coefficient control mechanism (22 and 24) controls the approach of after-...

대표
청구항

A turbo-fan engine after-burning system for controlling the flow of after-burned exhaust gas from a turbo-fan engine, comprising: an after-burning chamber for receiving exhaust gas and injecting a controllable amount of fuel into said turbo-fan exhaust to cause after burning of said turbo-fan exhaust to produce after-burned exhaust; a nozzle associated with said after-burning chamber for receiving said after-burned exhaust, said nozzle having a fixed geometry including a throat area; a nozzle coefficient control comprising a compressed gas flow mechanism...

이 특허를 인용한 특허 피인용횟수: 18

  1. Dorris ; III John ; Smith David Michael ; Parekh David Espineli ; Kibens Valdis. Apparatus and methods for active flow control of a nozzle exhaust plume. USP2001106308898.
  2. Brice,David C.; Whitmire,Julia K.; Barton, deceased,Brian E.. Apparatus, method and system for gas turbine engine noise reduction. USP2007017159383.
  3. Koshoffer,John Michael. Augmenter swirler pilot. USP2008107437876.
  4. Berg, Gerald R.; Messersmith, Nathan L.; Lidstone, Gary L.; Hinkey, John. Combustion nozzle fluidic injection assembly. USP2010087775460.
  5. Bancalari, Eduardo; Wilson, Jody; Little, David A.; Fadok, Joseph. Combustion transition duct providing stage 1 tangential turning for turbine engines. USP2010057721547.
  6. Gupta,Anurag. Device for reducing jet engine exhaust noise using oscillating jets. USP2007127308966.
  7. Froemming, Kenneth W.; Lerg, Bryan H.. Exhaust nozzle apparatus and method for multi stream aircraft engine. USP2018019863366.
  8. Alhatim, Omair M.. Exhaust nozzle of a gas turbine engine. USP2016039297334.
  9. Smith, Jesse Walter. Fixed nozzle thrust augmentation system. USP2010097788899.
  10. John Michael Koshoffer. Fluidic nozzle control system. USP2002016336319.
  11. Mueller John H.. Fluidic throat exhaust nozzle. USP1999125996936.
  12. Scavo Steven. Integrated fluidic CD nozzle for gas turbine engine. USP2000026021637.
  13. Catt Jeffrey Alan ; Miller Daniel Nicholas. Method and apparatus of asymmetric injection at the subsonic portion of a nozzle flow. USP2000096112513.
  14. Miller, Daniel N.; Yagle, Patrick J.; Ginn, Kerry B.; Hamstra, Jeffrey W.. Method and apparatus of asymmetric injection into subsonic flow of a high aspect ratio/complex geometry nozzle. USP2005116962044.
  15. Miller Daniel Nicholas ; Catt Jeffrey Alan. Method and apparatus of pulsed injection for improved nozzle flow control. USP2000096112512.
  16. Segota,Darko; Finnegan, II,John W.. Method and system for regulating internal fluid flow within an enclosed or semi-enclosed environment. USP2007117296411.
  17. Weaver, Adam; Wilson, Jody. Support system for transition ducts. USP2009097584620.
  18. Alhatim, Omair M.. System of support thrust from wasted exhaust. USP2018019879636.