$\require{mediawiki-texvc}$
  • 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

Engine nacelle

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64D-029/00   
미국특허분류(USC) 244/53B ; 60/2263 ; 137/151
출원번호 US-0756554 (1991-09-09)
우선권정보 GB-0025023 (1990-11-16)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 23  인용 특허 : 0
초록

A nacelle for a gas turbine engine (10) defines an air intake which is capable of meeting all the engine airflow requirements. The nacelle comprises a cowling (22), fixed upstream and in spaced apart relationship from an engine cowling (16), to define an annular passage (30) therebetween. Each of the cowlings, (22) and (16), have an air intake, (24) and (20) respectively, through which the mainstream flow of air passes into the engine (10). Depending upon the amount of airflow the engine (10) demands at different operating flight conditions air can flow ...

대표
청구항

A nacelle comprising a first cowling for a gas turbine engine, said first cowling having an air intake forward of said gas turbine engine for directing a flow of air to the gas turbine engine, and a second cowling upstream of said first cowling also having an air intake forward of the gas turbine engine, the first and second cowlings being arranged so that the air intakes in each of the cowlings are in series flow relationship with one another to allow the passage of flow of air to said gas turbine engine, the second cowling being in a spaced apart relat...

이 특허를 인용한 특허 피인용횟수: 23

  1. Devine, Michael Thomas. Adjustable size inlet system. USP20181010107196.
  2. Alvarez, Franck; Chancerelle, Emeric; Porte, Alain; Prat, Damien. Air intake arrangement for a vehicle, in particular an aircraft. USP2016089422062.
  3. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2010097797944.
  4. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014098844294.
  5. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2013018353164.
  6. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014058726632.
  7. Smith, Angus Roy; Arzoglou, Dimitris. Gas turbine engine nacelle having a symmetric flowpath. USP2016059328662.
  8. Smith, Angus Roy; Arzoglou, Dimitris. Gas turbine engine nacelle having a symmetric flowpath and design method thereof. USP2015038985507.
  9. Winter, Michael; Jain, Ashok K.. Gas turbine engine providing simulated boundary layer thickness increase. USP2011017870721.
  10. Winter, Michael; Jain, Ashok K.. Gas turbine engine system providing simulated boundary layer thickness increase. USP2012078209953.
  11. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  12. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  13. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  14. Jain, Ashok K.. Nacelle flow assembly. USP2013128596573.
  15. Jain, Ashok K.. Nacelle flow assembly. USP2012108282037.
  16. Jain, Ashok K.. Nacelle flow assembly. USP2015049004399.
  17. Zysman, Steven H.; Lord, Wesley K.; Miller, Robert M.; Atassi, Oliver V.. Passive boundary layer bleed system for nacelle inlet airflow control. USP2017059644535.
  18. Zysman, Steven H.; Lord, Wesley K.; Miller, Robert M.; Atassi, Oliver V.. Passive boundary layer bleed system for nacelle inlet airflow control. USP2014098839805.
  19. Zysman, Steven H.; Lord, Wesley K.; Miller, Robert M.; Atassi, Oliver V.. Passive boundary layer bleed system for nacelle inlet airflow control. USP2014098844553.
  20. Jain, Ashok K.; Winter, Michael. Variable contour nacelle assembly for a gas turbine engine. USP2016019228534.
  21. Jain, Ashok K.; Winter, Michael. Variable contraction ratio nacelle assembly for a gas turbine engine. USP2014058727267.
  22. Jain, Ashok K.. Variable geometry nacelle assembly for a gas turbine engine. USP2012068205430.
  23. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.