$\require{mediawiki-texvc}$
  • 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

Aircraft engine fuel system mounting assembly

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-007/224   
미국특허분류(USC) 600/393.1 ; 600/734 ; 600/736
출원번호 US-0292681 (1999-04-16)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Antonelli Terry Stout & Kraus
인용정보 피인용 횟수 : 13  인용 특허 : 10
초록

An aircraft engine assembly includes an engine, an engine control actuator responsive to flow of high pressure fuel therethrough for actuating engine controls, a fuel heat exchanger for heating fuel, a fuel controller for controlling flow of fuel in the aircraft engine assembly, a fuel pump having a low pressure section for pressurizing the fuel to a low pressure, and a high pressure section for pressurizing the fuel to a high pressure, an engine gearbox, a seal plate, and a manifold mounted on the engine gearbox and having the fuel pump and the fuel con...

대표
청구항

[ What is claimed is:] [1.] An aircraft engine assembly, comprising:an engine, having at least one engine control and having a combustion chamber with a fuel inlet;an engine control actuator responsive to flow of high pressure fuel therethrough for actuating said at least one engine control, said engine control actuator having an inlet and an outlet;a fuel heat exchanger for heating fuel, said fuel heat exchanger having an inlet and an outlet;a fuel controller for controlling flow of fuel in said aircraft engine assembly, said fuel controller having an i...

이 특허를 인용한 특허 피인용횟수: 13

  1. Bangert, Barry; Hawkins, Ralph. Aircraft engine reliability business model. USP2003116643570.
  2. Ward, Lyle; Heitz, Steven A.. Bi-metal pump gear. USP2013128613609.
  3. Suciu, Gabriel L.; Glahn, Jorn A.; Merry, Brian D.; Dye, Christopher M.. Bypass air-pump system within the core engine to provide air for an environmental control system in a gas turbine engine. USP2016079394803.
  4. Suciu, Gabriel L.; Merry, Brian D.; Glahn, Jorn A.; Dye, Christopher M.. Constant speed pump system for engine ECS loss elimination. USP2015109163562.
  5. DeFrancesco, Gregory L.; Rebours, Renaud. Dispatch critical fuel tank inerting system for aircraft. USP2012048147579.
  6. Reuter, Charles E.. Dual pump fuel flow system for a gas turbine engine and method of controlling. USP2014118893466.
  7. Anson, Bruce. Electric power generating turbine engine fuel supply system. USP2012108286432.
  8. Reuter, Charles E.; Price, Aaron V.; Haugsjaahabink, Todd; Sato, Yukinori; Wichowski, John J.. Flow control system and method for controlling two positive displacement pumps. USP2013048408233.
  9. Reuter, Charles; Dyer, Gerald P.; Haugsjaahabink, Todd; Shah, Satish. Fluid flow system for a gas turbine engine. USP2003116651441.
  10. Lorenz,William. High accuracy fuel metering system for turbine engines. USP2006026996970.
  11. Davi, Michael Alan; Chillar, Rahul Jaikaran; Black, Stephen Hugh; Herbold, John William. Quick disconnect combustion endcover. USP2016029267691.
  12. Legros, Craig R.; Finke, Aaron M.. Seal arrangement for turbomachine. USP2014128920136.
  13. Roberts, Lawrence P.. Thermal management system manifold. USP20190410253693.