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

특허 상세정보

Thin inlet lip design for low drag and reduced nacelle size

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64C-021/04   
미국특허분류(USC) 244/207 ; 244/053R ; 244/053B ; 600/231
출원번호 US-0020081 (1998-02-06)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Anderson
인용정보 피인용 횟수 : 26  인용 특허 : 7
초록

In accordance with the present invention, an aerodynamic turbo engine nacelle, disposable about an engine having an engine face, for mitigating boundary layer separation of intake airflow comprises an engine inlet. The engine inlet is provided with an interior surface and a curved portion. The curved portion having a leading edge. The geometry of the engine inlet is such that the ratio of the circular area defined by the diameter defined by the leading edge of the curved portion to the minimum circular area defined by the interior surface of the engine i...

대표
청구항

[ What is claimed is:] [1.] An aerodynamic turbo engine nacelle, disposable about an engine having an engine face, for mitigating boundary layer separation of intake airflow comprising:an engine inlet having an interior surface and a curved portion having a leading edge, the leading edge defining an interior surface circular area, the interior surface defining a minimum circular area, the engine inlet having a ratio of the interior surface circular area to the minimum circular area less than 1.33; anda pressurized fluid injecting device for injecting pre...

이 특허를 인용한 특허 피인용횟수: 26

  1. Hurwitz, Wayne; Ochs, Stuart S.. Active flow control for nacelle inlet. USP2015109157368.
  2. Knight, Glenn A; Maguire, Alan R; Robinson, Daniel; Bostock, George; Wilson, Mark J. Compressor tip injector. USP20181210145387.
  3. Fulayter, Roy D.; Smith, Crawford F.. Engine nacelle. USP20180910072511.
  4. Winter, Michael. Fan nacelle flow control. USP2013098529188.
  5. Cloft, Thomas G.; Wall, Sarah M.. Flow distribution system for inlet flow control. USP2010057708230.
  6. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2010097797944.
  7. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014098844294.
  8. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2013018353164.
  9. Morford, Stephen A.; Larkin, Michael J.. Gas turbine engine having slim-line nacelle. USP2014058726632.
  10. Winter, Michael; Jain, Ashok K.. Gas turbine engine providing simulated boundary layer thickness increase. USP2011017870721.
  11. Winter, Michael; Jain, Ashok K.. Gas turbine engine system providing simulated boundary layer thickness increase. USP2012078209953.
  12. Cloft, Thomas G.; Wiley, Richard H.. Integral suction device with acoustic panel. USP2010087766280.
  13. Cloft, Thomas G.; Wiley, Richard H.. Integral suction device with acoustic panel. USP2013068459597.
  14. Jain, Ashok K.; Winter, Michael. Nacelle assembly having inlet airfoil for a gas turbine engine. USP2013048408491.
  15. Haas, Martin. Nacelle assembly having inlet bleed. USP2012068192147.
  16. Haas, Martin. Nacelle assembly with turbulators. USP2012058186942.
  17. Jain, Ashok K.. Nacelle flow assembly. USP2013128596573.
  18. Jain, Ashok K.. Nacelle flow assembly. USP2012108282037.
  19. Jain, Ashok K.. Nacelle flow assembly. USP2015049004399.
  20. Gupta, Anurag; Graziosi, Paolo; Mani, Ramani. System and method for actively changing an effective flow-through area of an inlet region of an aircraft engine. USP2003126655632.
  21. Winter, Michael. Turbofan engine with variable bypass nozzle exit area and method of operation. USP2013078480350.
  22. Surply, Thierry; Bourdeau, Christophe. Turbojet nacelle and method for controlling separation in a turbojet nacelle. USP2014028640986.
  23. Jain, Ashok K.; Winter, Michael. Variable contour nacelle assembly for a gas turbine engine. USP2016019228534.
  24. Jain, Ashok K.; Winter, Michael. Variable contraction ratio nacelle assembly for a gas turbine engine. USP2014058727267.
  25. Jain, Ashok K.. Variable geometry nacelle assembly for a gas turbine engine. USP2012068205430.
  26. Jain, Ashok K.; Chaudhry, Zaffir A.. Variable shape inlet section for a nacelle assembly of a gas turbine engine. USP2013038402739.