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특허 상세정보

Pressurized nacelle compartment for active clearance controlled gas turbine engines

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-007/18   
미국특허분류(USC) 60/204 ; 60/2261 ; 60/266 ; 60/3907
출원번호 US-0472917 (1983-03-07)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 20  인용 특허 : 3
초록

Methods and apparatus for improving the thrust specific fuel consumption (TSFC) of a gas turbine engine employing an exterior active clearance control system are disclosed. The pressure within the nacelle compartment to which active clearance control air is discharged is operated under altitude cruise conditions at a level on the order of one to two and one-half pounds per square inch (1-2½psi) above the ambient atmosphere. Flow discharging from the nacelle is directed through an aft facing vent nozzle for purposes of thrust recovery.

대표
청구항

A method of operating an aircraft power plant installed on an aircraft and of the active clearance controlled type including a gas turbine engine housed within a nacelle compartment and a cooling air manifold extending around the engine including the steps of: admitting active clearance control cooling air into said nacelle compartment and discharging the air against the engine; maintaining the air pressure within said nacelle compartment at altitude cruise conditions at a level which is on the order of one to two and one-half pounds per square inch (1-2...

이 특허를 인용한 특허 피인용횟수: 20

  1. Legare, Pierre-Yves; Mah, Stephen. Active tip clearance control arrangement for gas turbine engine. USP2012018092146.
  2. Porte, Alain; Prat, Damien. Dual flow turbine engine equipped with a precooler. USP2012038141337.
  3. Porte, Alain; Prat, Damien. Dual flow turbine engine equipped with a precooler. USP2012088250852.
  4. Urban, Justin R.; Bifulco, Anthony R.. Gas turbine engine with bleed duct for minimum reduction of bleed flow and minimum rejection of hail during hail ingestion events. USP2018029890711.
  5. Khalid, Syed Jalaluddin. Gas turbine engine with ejector. USP2014098844264.
  6. Khalid, Syed Jalaluddin. Gas turbine engine with ejector. USP2013118572947.
  7. Boeck, Alexander. Method and apparatus for the cooling of jet-engine turbine casings. USP2003096625989.
  8. Chillapalli, Durga Srinivas; Kumar, Hemanth Gudibande Sathyakumar; Mondal, Bhaskar Nanda; Pal, Kishanjit; Shevakari, Sushilkumar Gulabrao; Moniz, Thomas Ory. Method and system for controlling core cowl vent area. USP20190210197007.
  9. Kumar, Hemanth Gudibande Sathyakumar; Mondal, Bhaskar Nanda; Moniz, Thomas Ory. Method and system for metallic low pressure fan case heating. USP20180910066630.
  10. Sheridan, William G.; Hasel, Karl L.. Method for setting a gear ratio of a fan drive gear system of a gas turbine engine. USP2017119816443.
  11. Murphy, Michael J.; Malecki, Robert E.. Non-circular aft nacelle cowling geometry. USP2018069995180.
  12. Murphy, Michael Joseph; Malecki, Robert E.. Non-circular aft nacelle cowling geometry. USP2015069057286.
  13. Dionne, Luc. Passive cooling system for auxiliary power unit installation. USP2003116651929.
  14. Dionne, Luc. Passive cooling system for auxiliary power unit installation. USP2017059644538.
  15. Dionne, Luc. Passive cooling system for auxiliary power unit installation. USP2005096942181.
  16. Dionne,Luc. Passive cooling system for auxiliary power unit installation. USP2008047364117.
  17. Khalid, Syed J.. Positionable ejector member for ejector enhanced boundary layer alleviation. USP2017049630706.
  18. Khan, Wasif. Reflex annular vent nozzle. USP2016059347397.
  19. Hasting, William Howard; Crall, David William; Higgins, Craig William; Krammer, Erich Alois. System and method for active clearance control. USP2016029260974.
  20. Bubello Robert (Meriden CT) Ream Jeffrey L. (Tollano CT). Ventilation system for a nacelle. USP1989054825644.