$\require{mediawiki-texvc}$
  • 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

Flutter sensing system for a gas turbine engine

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-001/18   
미국특허분류(USC) 060/242; 060/226.1; 060/226.3; 415/126
출원번호 US-0346082 (2012-01-09)
등록번호 US-8646251 (2014-02-11)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Carlson, Gaskey & Olds
인용정보 피인용 횟수 : 2  인용 특허 : 20
초록

An exemplary gas turbine engine assembly includes a fan casing within a nacelle, a variable area fan nozzle. A controller is operable to move the variable area fan nozzle to influence a discharge airflow area associated with the variable area fan nozzle in response to an airfoil flutter condition. A gear train reduces a rotational speed of a fan in the gas turbine engine relative to another portion of the gas turbine engine.

대표
청구항

1. A gas turbine engine assembly, comprising: a fan casing within a nacelle;a variable area fan nozzle; anda controller is operable to move the variable area fan nozzle to influence a discharge airflow area associated with the variable area fan nozzle in response to an airfoil flutter condition, wherein a gear train reduces a rotational speed of a fan in the gas turbine engine relative to another portion of the gas turbine engine. 2. The gas turbine engine assembly of claim 1, wherein the gear train is a planetary gear train. 3. The gas turbine engine as...

이 특허에 인용된 특허 (20)

  1. Acton Elizabeth (Cambridge GB2) Cargill Alexander M. (Derby GB2) Ross Colin F. (Cambridge GB2) Eatwell Graham P. (Cambridge GB2). Active control of unsteady motion phenomena in turbomachinery. USP1991045005353.
  2. Gliebe Philip R. (Waynesville OH). Active low noise fan assembly. USP1995125478199.
  3. Gysling Daniel L. ; Feulner Matthew R. ; Eveker Kevin M.. Apparatus and method of active flutter control. USP2001036195982.
  4. Lair, Jean-Pierre. Bifurcated turbofan nozzle. USP2004116820410.
  5. Law,Chi. Geartrain coupling for a turbofan engine. USP2006047021042.
  6. Eveker, Kevin M.; Gysling, Daniel L.; Nett, Carl N.. Method and system of flutter control for rotary compression systems. USP2003066582183.
  7. Koff ; Bernard L. ; Budinger ; Raymond E. ; Johnson ; James E.. Modulating bypass variable cycle turbofan engine. USP1978034080785.
  8. Wood, Jeffrey H.; Dunne, James P.. Morphing structure. USP2010017644575.
  9. Wood,Jeffrey H; Dunne,James P. Morphing structure. USP2008037340883.
  10. Waitz Ian A. ; Brookfield John M. ; Sell Julian ; Hayden Belva J. ; Ingard K. Uno. Reduction of turbomachinery noise. USP1999126004095.
  11. Butler Lawrence (Cincinnati OH). Thrust reverser with variable nozzle. USP1997085655360.
  12. Coplin John F. (Derby GB2). Turbofan gas turbine engine. USP1989054827712.
  13. Lair,Jean Pierre. Turbofan variable fan nozzle. USP2006016983588.
  14. Barbarin Jacques M. G. (Montivilliers FRX) Lecoutre Pascal B. G. (Le Havre FRX). Turbojet engine thrust reverser with variable exhaust cross-section. USP1990054922713.
  15. Thomas William W. (Cincinnati OH) Sprunger Elmore V. (Cincinnati OH). Two-spool variable cycle engine. USP1977084043121.
  16. Duesler Paul W. ; Loffredo Constantino V. ; Prosser ; Jr. Harold T. ; Jones Christopher W.. Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems. USP1998075778659.
  17. Rey,Nancy M.; Miller,Robin M.; Tillman,Thomas G.; Rukus,Robert M.; Kettle,John L.. Variable area nozzle for gas turbine engines driven by shape memory alloy actuators. USP2006027004047.
  18. Tumavicus Julius W. (Old Saybrook CT). Variable ratio bypass gas turbine engine with flow diverter valve. USP1977104052845.
  19. Adamson ; Arthur P.. Variable thrust nozzle for quiet turbofan engine and method of operating same. USP1978014068469.
  20. McAndrews Glenn (Lebanon OH). Variable vane valve in a gas turbine. USP1993025184459.