$\require{mediawiki-texvc}$
  • 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

Suction generator system in an aircraft for maintaining a laminar boundary flow

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-021/06   
미국특허분류(USC) 244/209 ; 244/208 ; 244/130 ; 244/118.5
출원번호 US-0851589 (1997-05-05)
우선권정보 DE-0017952 (1996-05-04)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Fasse
인용정보 피인용 횟수 : 18  인용 특허 : 5
초록

Boundary layer air on the skin structure of an aircraft is sucked off through suction holes in the aircraft skin structure by a least one ejector pump. The ejector pump is operated by at least one of several air flow sources. One source is the excess pressure in the passenger cabin at higher altitudes. The other air flow source is tap air from at least one aircraft engine. If necessary, one or the other or both air supply sources may be utilized to operate the ejector pump or pumps.

대표
청구항

[ What is claimed is:] [1.] An aircraft comprising an aircraft cabin, a skin structure enclosing said aircraft cabin, a suction system for sucking off boundary layer air through suction holes in said skin structure, said suction system comprising at least one ejector pump (3) including an outlet port for ejected air, a suction port (15), and first and second flow inlet ports (13, 14), said system further comprising a suction duct (15A) connecting said suction port (15) to at least one respective suction hole (10A) of said suction holes, wherein said airc...

이 특허를 인용한 특허 피인용횟수: 18

  1. Schwarz, Frederick M.. Aircraft thermal management system with reduced exhaust re-ingestion. USP2010127857257.
  2. Meister, Jürgen. Aircraft with a fluid-duct-system. USP2011087988102.
  3. Meister, Juergen; Pfennig, Juergen. Boundary layer suction arrangement. USP2010117837155.
  4. Westenberger, Andreas; Arendt, Martin; Marquardt, Till; Frahm, Lars; Schrauf, Geza. Cooling system on the basis of suction of a boundary layer. USP2012068191834.
  5. Wilby, Richard. Double fuselage aircraft. USP2012048157204.
  6. Khalid, Syed Jalaluddin. Gas turbine engine with ejector. USP2014098844264.
  7. Khalid, Syed Jalaluddin. Gas turbine engine with ejector. USP2013118572947.
  8. Morris, Timothy M.; Spock, Wayne R.; Smith, Peter Gerard; Schryver, Matthew J.; Walther, Ronald S.; Gukeisen, Robert L.; Hagaman, Edward T.. Hybrid engine accessory power system. USP2014088800918.
  9. Morris, Timothy M.; Spock, Wayne R.; Smith, Peter Gerard; Schryver, Matthew J.; Walther, Ronald S.; Gukeisen, Robert L.; Hagaman, Edward T.. Hybrid engine accessory power system. USP2011077975465.
  10. Schrauf, Geza. Method and device for suctioning the boundary layer. USP2010077757994.
  11. Atassi, Oliver V.. Nacelle with porous surfaces. USP2015038974177.
  12. Bertolotti,Fabio P.. Perforated skin structure for laminar-flow systems. USP2006127152829.
  13. Khalid, Syed J.. Positionable ejector member for ejector enhanced boundary layer alleviation. USP2017049630706.
  14. Pfennig Juergen,DEX ; Meister Juergen,DEX. Suction device for boundary layer control in an aircraft. USP2001046216982.
  15. Reckzeh, Daniel; Goelling, Burkhard; Lengers, Matthias. Surface element for an aircraft, aircraft and method for improving high-lift generation on a surface element. USP2016039272772.
  16. Laugt, Paul. System for supplying an aircraft with cool air. USP2005056886782.
  17. Gariglio,Davide. Vacuum belt conveyor for plates. USP2006057036656.
  18. Reckzeh, Daniel; Goelling, Burkhard; Lengers, Matthias. Wing for an aircraft, aircraft and method for reducing aerodynamic drag and improving maximum lift. USP2016039278753.