$\require{mediawiki-texvc}$
  • 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

Propfan turbine engine

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-003/02    B64B-001/24   
미국특허분류(USC) 60/2261 ; 244/53B
출원번호 US-0662442 (1991-02-28)
우선권정보 DE-4009223 (1990-03-22)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 25  인용 특허 : 0
초록

A propfan turbine engine for an aircraft has a shroud and on the leading edge of the shroud, has one or several, preferably two, separate sector-like annular profile parts which via actuating devices can be moved from the shroud such that slots can be formed between the profile parts and the shroud. This arrangement prevents dangerous air-flow separations on the outside of the upper shroud region and on the inside of the lower shroud region at large angles of attack of the aircraft engine for both high and low power operation.

대표
청구항

A propfan turbine engine for aircraft having a shroud surrounding propfan blades, comprising: an annular leading edge of said shroud including a separate profile part forming an upper continuous annular section having an arc greater than 30°as a part of said leading edge; means for actuating coupled to said separate profile part to vary the position of said separate profile part with respect to said shroud; a single continuous annular slot-like duct formed between said profile part and said shroud when said separate profile part is in an extended positio...

이 특허를 인용한 특허 피인용횟수: 25

  1. Romano, Pascal; Bonneau, Virginie; Sensiau, Claude. Acoustically optimized air inlet. USP20180710024236.
  2. Seda, Jorge F.; Dunbar, Lawrence W.; Gliebe, Philip R.; Szucs, Peter N.; Brauer, John C.; Johnson, James E.; Moniz, Thomas; Steinmetz, Gregory T.. Aircraft engine with inter-turbine engine frame supported counter rotating low pressure turbine rotors. USP2003096619030.
  3. Jones,Anthony; Harris,Mark; Lydon,Patrick; Alexander,Eric. Combined stage single shaft turbofan engine. USP2006067055306.
  4. Seda, Jorge F.; Dunbar, Lawrence W.; Szucs, Peter N.; Brauer, John C.; Johnson, James E.. Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor. USP2004056732502.
  5. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2010097797944.
  6. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014098844294.
  7. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2013018353164.
  8. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014058726632.
  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. Todorovic, Predrag. Gas-turbine engine with telescope-type air inlet of the engine cowling (nacelle). USP2017089719421.
  12. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  13. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  14. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  15. Jain, Ashok K.. Nacelle flow assembly. USP2013128596573.
  16. Jain, Ashok K.. Nacelle flow assembly. USP2012108282037.
  17. Jain, Ashok K.. Nacelle flow assembly. USP2015049004399.
  18. Zysman, Steven H.; Lord, Wesley K.; Miller, Robert M.; Atassi, Oliver V.. Passive boundary layer bleed system for nacelle inlet airflow control. USP2017059644535.
  19. Zysman, Steven H.; Lord, Wesley K.; Miller, Robert M.; Atassi, Oliver V.. Passive boundary layer bleed system for nacelle inlet airflow control. USP2014098839805.
  20. Zysman, Steven H.; Lord, Wesley K.; Miller, Robert M.; Atassi, Oliver V.. Passive boundary layer bleed system for nacelle inlet airflow control. USP2014098844553.
  21. Moraes,Ricardo Ferreira. Turbine component with enhanced stagnation prevention and corner heat distribution. USP2006097104068.
  22. Jain, Ashok K.; Winter, Michael. Variable contour nacelle assembly for a gas turbine engine. USP2016019228534.
  23. Jain, Ashok K.; Winter, Michael. Variable contraction ratio nacelle assembly for a gas turbine engine. USP2014058727267.
  24. Jain, Ashok K.. Variable geometry nacelle assembly for a gas turbine engine. USP2012068205430.
  25. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.