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"" 따옴표 내의 구문과 완전히 일치하는 문서만 검색 예) "Transform and Quantization"

특허 상세정보

System and method for diverting boundary layer air

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64D-033/02   
미국특허분류(USC) 244/053B ; 137/015.1 ; 244/01R ; 244/130
출원번호 US-0619831 (1996-03-19)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Baker & Botts, L.L.P.
인용정보 피인용 횟수 : 17  인용 특허 : 1
초록

A diverterless engine inlet system that integrates a "bump" surface with a forward swept, aft-closing cowl to divert substantially all of the boundary layer air from the inlet. The bump includes an isentropic compression surface raised outwardly from the body of the aircraft to form a portion of the inner surface of the inlet. The cowl couples to the body of the aircraft to form the remaining surfaces of the inlet and closes against the body of the aircraft at the aft-most points of the inlet opening. The bump and the cowl work together to divert low ene...

대표
청구항

[ What is claimed is:] [1.] A system for diverting boundary layer air from an inlet for an aircraft engine comprising:a bump having a surface raised outwardly from the body of the aircraft to begin diverting the boundary layer air from the inlet prior to the boundary layer air entering the inlet, the bump beginning prior to an opening of the inlet and extending toward the rear of the inlet to form at least a portion of an inner surface of the inlet; anda cowl coupled to the body of the aircraft to define the opening of the inlet comprising;an aft-closing...

이 특허를 인용한 특허 피인용횟수: 17

  1. Silkey, Joseph S.; Wilson, Christopher D.; Dyer, Richard S.. Air induction control. USP2011077975961.
  2. Fol, Thierry; Jimenez, Philippe; Namer, Arnaud. Aircraft comprising a central fairing that adjusts the pressure on the wing structures by means of local geometric deformations. USP2012058177170.
  3. Leland, Bradley C.; Klinge, John D.; Lundy, Brian F.. Apparatus and method for processing airflow with flowfield molded hypersonic inlet. USP2012108297058.
  4. Silkey, Joseph S.; Wilson, Christopher D.; Dyer, Richard S.. Inlet distortion and recovery control system. USP2009127637455.
  5. Judas, Michael; Bichler, Bartholomaeus. Intake for an engine of an aircraft. USP2018029889945.
  6. Sato, Kazushige; Iso, Hideo; Osuka, Takeshi. Intake structure of aircraft. USP2018059975643.
  7. Conners, Timothy R.; Henne, Preston A.; Howe, Donald C.. Isentropic compression inlet for supersonic aircraft. USP2016119482155.
  8. Wik, Torsten. Method and arrangement for extending the range of fire of a fin-stabilized artillery missile. USP2005086926228.
  9. Leland, Bradley C.; Klinge, John D.; Lundy, Brian F.. Method for designing flowfield molded hypersonic inlet for integrated turbojet and ram-scramjet applications. USP2009087568347.
  10. Gruensfelder Cynthia Ann ; Wille Robert Henry. Mission adaptive inlet. USP2000076089505.
  11. Gruensfelder Cynthia Ann ; Wille Robert Henry. Mission adaptive inlet. USP2001076260567.
  12. Seidel, Gerhard E.. Separate boundary layer engine inlet. USP2003036527224.
  13. Henne, Preston A.; Conners, Timothy R.; Howe, Donald C.. Supersonic aircraft jet engine installation. USP2016059334801.
  14. Troia, Trajaen J.; Mangus, John F.. Swept gradient boundary layer diverter. USP2017099758253.
  15. Lundy,Brian F.; Klinge,John D.; Leland,Bradley C.. System, method, and apparatus for designing streamline traced, mixed compression inlets for aircraft engines. USP2007047207520.
  16. Huynh, Thuy. Variable-geometry rotating spiral cone engine inlet compression system and method. USP2014048690097.
  17. Schulein,Erich. Wing for an aircraft or spacecraft. USP2006107114685.