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특허 상세정보

Active system for wide area suppression of engine vortex

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02G-003/00   
미국특허분류(USC) 060/039.092; 244/053.B
출원번호 US-0280411 (2002-10-25)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Alston & Bird LLP
인용정보 피인용 횟수 : 18  인용 특허 : 5
초록

The active system for the wide area suppression of a ground vortex generated by the engine of an aircraft includes an actuator assembly in fluid communication with a fluid source; and, at least one nozzle assembly, including at least one movable nozzle. The movable nozzle is in fluid communication with the actuator assembly for receiving fluid from the actuator assembly. The actuator assembly controls the motion of the movable nozzle, wherein fluid is injected over a desired region relative to an inlet of the engine to disrupt the flow structure of a gro...

대표
청구항

1. An active system for the wide area suppression of a ground vortex generated by the engine of an aircraft, comprising:a) an actuator assembly in fluid communication with a fluid source; and,b) at least one nozzle assembly, including at least one movable nozzle, said at least one movable nozzle being in fluid communication with said actuator assembly for receiving fluid from said actuator assembly, said actuator assembly controlling the motion of said movable nozzle and thereby adjusting a direction of said nozzle during operation of said nozzle, wherei...

이 특허를 인용한 특허 피인용횟수: 18

  1. Shmilovich, Arvin; Carralero, Michael A.. Autonomous power generation unit for auxiliary system on an airborne platform. USP2012078232706.
  2. Owens, Lewis R.; Allan, Brian G.. Boundary-layer-ingesting inlet flow control system. USP2010087784732.
  3. Kupratis, Daniel B.. Gas turbine engine having core auxiliary duct passage. USP2013028371806.
  4. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014098844294.
  5. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2013018353164.
  6. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014058726632.
  7. Winter, Michael; Jain, Ashok K.. Gas turbine engine providing simulated boundary layer thickness increase. USP2011017870721.
  8. Winter, Michael; Jain, Ashok K.. Gas turbine engine system providing simulated boundary layer thickness increase. USP2012078209953.
  9. Corda,Stephen; Smith,Mark Stephen; Myre,David Daniel. Method for creating an aeronautic sound shield having gas distributors arranged on the engines, wings, and nose of an aircraft. USP2008087407131.
  10. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  11. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  12. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  13. Cloft, Thomas G.; Jain, Ashok K.. Nacelle compartment plenum for bleed air flow delivery system. USP2014028657567.
  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. Atassi, Oliver V.. Nacelle with porous surfaces. USP2015038974177.
  18. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.