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특허 상세정보

Low noise aeroengine inlet system

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-007/045    F02C-007/042    F02K-003/06   
출원번호 US-0463031 (2014-08-19)
등록번호 US-9957889 (2018-05-01)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Norton Rose Fulbright Canada
인용정보 피인용 횟수 : 0  인용 특허 : 26
초록

An aeroengine is provided with a splitter apparatus disposed in a section of an inlet duct. The splitter apparatus can be actuated from a stowed position to a deployed position to allow splitter(s) to selectively move from out of the inlet flow to a position extending into the inlet duct to divide the inlet flow into multiple passages.

대표
청구항

1. An aeroengine comprising an inlet duct for directing an air flow from an inlet opening to a compressor rotor, and an inlet splitter apparatus disposed within a section of the inlet duct and having at least one splitter plate pivotally mounted to a wall of the inlet duct about an axis substantially parallel to a direction of the air flow, the at least one splitter plate being pivotally moveable between a deployed position in which the at least one splitter plate extends from the wall of the inlet duct into the inlet duct to expose both sides of the pla...

이 특허에 인용된 특허 (26)

  1. Krojer Hubert (Kippenhausen DT). Air intake with deflecting device against foreign objects impinging in the initial direction of air flow at engine nacel. USP1977094047911.
  2. Hogeboom William H. ; Bielak Gerald W.. Aircraft engine acoustic liner. USP1998075782082.
  3. Porte, Alain; Batard, Herv?. Aircraft engine pod with acoustic attenuation. USP2005056896099.
  4. Schwarz, Frederick M.. Aircraft thermal management system with reduced exhaust re-ingestion. USP2010127857257.
  5. Raimbault, Vincent; Cormerais, Mickael; Champion, Arnaud. Anti-noise device for the air intake conduit of a supercharged internal combustion engine. USP2012108276707.
  6. Dougherty Robert P. (Bellevue WA). Apparatus and method for reducing noise emissions from a gas turbine engine inlet. USP1997125702231.
  7. Frustie, Valerie; Duprieu, Bernard; Gantie, Fabrice. Coating for acoustic treatment integrating the function of frost treatment with hot air. USP2011057938224.
  8. Arnold Michael J. (Bangor GB5). Composite structural component. USP1994055315820.
  9. Winter, Michael. Fan nacelle flow control. USP2013098529188.
  10. Ball William H. (Mercer Island WA). Flush inlet for supersonic aircraft. USP1984084463772.
  11. Flatman Richard J. (Derby GB2). Gas turbine engine. USP1989114881367.
  12. Prasad, Dilip; Feng, Jinzhang; Sabnis, Jayant S.. Gas turbine engine inlet with noise reduction features. USP2012108286654.
  13. Chee Wan T. (Bellevue WA). Inlet cowl attachment for jet engine. USP1985084534167.
  14. Sanders,Bobby W.; Weir,Lois J.. Low sonic boom inlet for supersonic aircraft. USP2006057048229.
  15. Moe, Jeffrey W.; Wunsch, John J.; Sperling, Michael S.. Method and apparatus for noise abatement and ice protection of an aircraft engine nacelle inlet lip. USP2009097588212.
  16. Gruensfelder Cynthia Ann ; Wille Robert Henry. Mission adaptive inlet. USP2000076089505.
  17. Wilson, Robert Samuel. Noise attenuation panel. USP2003086609592.
  18. Farquhar Bannister W. (Bellevue WA) Sloan Denis (Bellevue WA). Noise suppression refracting inlet for jet engines. USP1980034192336.
  19. Derue Anicet (Aix-en-Provence FR). Ram air intakes of rotary-wing aircraft turbine engines. USP1976123998048.
  20. Ayle, Earl; Burchett, Rickey L.. Splicing of curved acoustic honeycomb. USP2013118579076.
  21. Norris Richard M. (Stratford CT) Murphy Joseph P. (Newtown CT). Swinging door particle separator and deicing system. USP1981024250703.
  22. Dhoore Louis G. (Seattle WA) Schultz William H. (Bellevue WA). Turbofan engine having variable geometry fan duct. USP1979054155221.
  23. Tedstone, Donald J.. Vane fairing for inertial separator. USP1982084346860.
  24. Sargisson ; Donald Farley. Variable area inlet for a gas turbine engine. USP1978024075833.
  25. Readnour Jack L. (Ft. Mitchell KY) Wright Jack D. (Mason OH). Variable contour annular air inlet for an aircraft engine nacelle. USP1991035000399.
  26. Kechely,Roy Eric. Variable fluid intake with ramp and inflatable bag. USP2008097429018.