$\require{mediawiki-texvc}$
  • 검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
  • 검색연산자
검색연산자 기능 검색시 예
() 우선순위가 가장 높은 연산자 예1) (나노 (기계 | machine))
공백 두 개의 검색어(식)을 모두 포함하고 있는 문서 검색 예1) (나노 기계)
예2) 나노 장영실
| 두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색 예1) (줄기세포 | 면역)
예2) 줄기세포 | 장영실
! NOT 이후에 있는 검색어가 포함된 문서는 제외 예1) (황금 !백금)
예2) !image
* 검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색 예) semi*
"" 따옴표 내의 구문과 완전히 일치하는 문서만 검색 예) "Transform and Quantization"

특허 상세정보

Variable cycle propulsion system with gas tapping for a supersonic airplane, and a method of operation

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-00300   
미국특허분류(USC) 060/225; 060/263
출원번호 US-0167602 (2002-06-13)
우선권정보 FR-0007771 (2001-06-14)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Oblon, Spivak, McClelland, Maier &
인용정보 피인용 횟수 : 17  인용 특허 : 1
초록

A variable cycle propulsion system for a supersonic airplane, the system comprising at least one engine having means for producing exhaust gas and a gas exhaust nozzle for generating thrust for supersonic flight speeds, and at least one separate auxiliary propulsion assembly dissociated from said engine, having no gas generator, and capable of generating thrust for takeoff, landing, and subsonic flight speeds. The system further comprises gas flow tapping means movable between a position in which they tap off at least a fraction of the exhaust gas produc...

대표
청구항

1. A variable cycle propulsion system for a supersonic airplane, the system comprising:at least one engine comprising means for producing exhaust gas and a gas exhaust nozzle configured to generate thrust for supersonic flight speeds; a propulsion assembly dissociated from said engine, having no gas generator, and configured to generate thrust for takeoff, landing, and subsonic flight speeds; and gas flow tapping means movable between a position in which the gas flow tapping means taps off at least a portion of the exhaust gas and feeds the tapped off ex...

이 특허를 인용한 특허 피인용횟수: 17

  1. Stretton, Richard Geoffrey. Engine installation. USP2016059346551.
  2. Suciu, Gabriel L; Chandler, Jesse M; Zysman, Steven H. Free stream intake with particle separator for reverse core engine. USP2017059644537.
  3. Hutterer, Joseph A.. Fuel efficient fixed wing aircraft. USP2009067549604.
  4. Suciu, Gabriel L.; Chandler, Jesse M.. Gas turbine engine having fan rotor driven by turbine exhaust and with a bypass. USP2016059352843.
  5. Babu, Michael; Domonkos, Richard E.; Shacter, Philip. Gas turbine engine with dual fans driven about a central core axis. USP2011098015796.
  6. Suciu, Gabriel L.; Lord, Wesley K.; Dye, Christopher M.. Gas turbine engine with separate core and propulsion unit. USP2014078789354.
  7. Goutière, Vincent; Côté, Jean. Nozzle. USP2011020632359.
  8. Goutière, Vincent; Côté, Jean. Nozzle. USP2011020632360.
  9. Rice, Edward C.. Propulsive force vectoring. USP2018059976514.
  10. Vuillamy, Didier; Gazave, Robert. Rocket engine nozzle system. USP2012098266887.
  11. Rice, Edward C.; Sumner, Bradley S.. Splayed inlet guide vanes. USP20181110125622.
  12. Rice, Edward C.. System and method for a fluidic barrier on the low pressure side of a fan blade. USP2018039915149.
  13. Rice, Edward C.. System and method for creating a fluidic barrier from the leading edge of a fan blade. USP20190310233869.
  14. Lord, Wesley K.. Transverse mounted gas turbine engine. USP2014048708274.
  15. Rolt, Andrew M.. Turbofan arrangement. USP2010087770377.
  16. Rolt,Andrew M. Turbofan arrangement. USP2006097107756.
  17. Burghardt, Sascha. Turbofan jet engine with low pressure shaft passing outside of core engine. USP2017119828911.

IPC 상위 출원인