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특허 상세정보

Gas turbine engine fan duct base pressure drag reduction

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-021/06   
미국특허분류(USC) 244/209 ; 244/130 ; 244/204
출원번호 US-0531734 (1990-06-01)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 22  인용 특허 : 0
초록

An aircraft is provided with an aircraft base pressure drag reduction apparatus including apparatus for ducting boundary layer air on board an aircraft wherein the air produces ram air drag, apparatus for using the air for work, and apparatus for ducting the used boundary layer air to a low pressure area of an aircraft which otherwise produces base pressure drag on the aircraft to reduce the base pressure drag that the low pressure area would otherwise produce. In a more particular embodiment of the invention the low pressure area of the aircraft is in a...

대표
청구항

An aircraft base pressure drag reduction means comprising: a means for ducting boundary layer air on board an aircraft from an aircraft nacelle, a means for using the boundary layer air as working fluid in a compressor apparatus, and a means for ducting the used air from said compressor apparatus to a low pressure area on a pylon fairing in a fan duct of an aircraft gas turbine engine which otherwise produces base pressure drag on the aircraft.

이 특허를 인용한 특허 피인용횟수: 22

  1. Liu, Xiaoliu. Cooler in nacelle with radial coolant. USP2012098266888.
  2. Retz, Kevin Matthew; Prichard, Alan Keith. Electrically conductive structure. USP2015089108387.
  3. Army, Donald E.; Peacos, Frederick; Polifka, John; Zager, Michael. Environmental control system pack pallets. USP2012038132758.
  4. Arcas Noe ; Hutto Frederick M. ; Parente Charles A.. Extended reaction acoustic liner for jet engines and the like. USP2000106135238.
  5. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014098844294.
  6. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2013018353164.
  7. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014058726632.
  8. Winter, Michael; Jain, Ashok K.. Gas turbine engine system providing simulated boundary layer thickness increase. USP2012078209953.
  9. Kupratis, Daniel B.. Gas turbine engine with intercooling turbine section and intercooling turbine section bypass. USP2015018935923.
  10. Leamy, Kevin Richard; Breig, Benjamin Paul; Epstein, Michael Jay; Parrilla, Javier Armando; Hurt, Matthew John; Brinson, Thomas Edward; Fleming, Andrew James. Jet engine cold air cooling system. USP20190410247100.
  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. Brown, Keith T.; Fowler, Frank J.; Byrne, Stuart J.; Stein, Adam. Nacelle inlet with extended outer barrel. USP2018019874228.
  18. Atassi, Oliver V.. Nacelle with porous surfaces. USP2015038974177.
  19. Bertolotti,Fabio P.. Perforated skin structure for laminar-flow systems. USP2006127152829.
  20. Pfennig Juergen,DEX ; Meister Juergen,DEX. Suction device for boundary layer control in an aircraft. USP2001046216982.
  21. Krull, Anthony; Leach, David; Kraemer, Gilbert; Myers, Geoffrey; Vert, Alexey; Frederick, Garth; Aljabari, Samer. System and method for adjusting engine parameters based on flame visualization. USP2013048432440.
  22. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.