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

특허 상세정보

Gas turbine engine having a cooling-air nacelle-cowl duct integral with a nacelle cowl

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02C-007/12   
미국특허분류(USC) 060/806; 060/785; 060/782
출원번호 UP-0616446 (2006-12-27)
등록번호 US-7665310 (2010-04-09)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    McNees Wallace & Nurick, LLC
인용정보 피인용 횟수 : 9  인용 특허 : 23
초록

A gas turbine engine includes an engine core extending along a core axis, a cooling-air delivery duct on the engine core, and a removable nacelle cowl overlying the engine core. A cooling-air nacelle-cowl duct delivers cooling air to the cooling-air delivery duct. At least a portion of the length of the cooling-air nacelle-cowl duct is integral with the nacelle cowl and not directly supported on the engine core.

대표
청구항

What is claimed is: 1. A gas turbine engine comprising: an engine core extending along a core axis; a removable nacelle cowl overlying the engine core, wherein the nacelle cowl has an inner surface facing toward the engine core and an outer surface facing away from the engine core, when the removable nacelle cowl is installed to the engine core; a cooling-air intake structure that receives cooling air through a cooling-air inlet in the nacelle cowl outer surface; a cooling-air delivery duct on the engine core; a cooling-air nacelle-cowl duct directly af...

이 특허에 인용된 특허 (23)

  1. Jones,Emlyn; Stretton,Richard G. Aeroengine nacelle. USP2006087090165.
  2. Gates Roger Jonathan,CAX. Apparatus for reducing combustor exit duct cooling. USP2001086269628.
  3. Schulze Wallace M. (West Chester OH). Auxiliary air system for gas turbine engine. USP1982094351150.
  4. Ream Jeffrey L. (Tolland CT) Bubello Robert (North Meriden CT). Buffer region for the nacelle of a gas turbine engine. USP1991055012639.
  5. Redinger ; Jr. ; Ira H. ; Sadowsky ; David ; Stripinis ; Philip S.. Clearance control for gas turbine engine. USP1978014069662.
  6. Schwarz Frederick M. (Glastonbury CT). Clearance control for gas turbine engine. USP1985074525998.
  7. Fitton David L. (South Glastonbury CT). Combined turbine power plant blade tip clearance and nacelle ventilation system. USP1984044441314.
  8. Kniat John (Glastonbury CT) Kuhlberg Joel F. (New Hartford CT) Mickey Daniel A. (Broad Brook CT). Cooling means. USP1985034504030.
  9. Beutin Bruno Albert,FRX ; Brossier Pascal Noel,FRX ; Franchet Michel Fran.cedilla.ois Raymond,FRX ; Lecordix Jean-Loic Herve,FRX ; Loubet Marc Georges,FRX. Cooling system for a turbomachine speed reducer. USP2001096282881.
  10. Laborie Daniel J. ; Mc Nulty Michael. Core compartment valve cooling valve scheduling. USP2001036202403.
  11. Griffin James G. (West Hartford CT) Schwarz Frederick M. (Glastonbury CT). External gas turbine engine cooling for clearance control. USP1981074279123.
  12. Colman Michael E. (Wakefield MA) Goeller Robert E. (Beverly MA). Gas turbine engine component cooling system. USP1986094608819.
  13. Vermejan Alexander E. (Mason OH) Daiber Paul C. (Cincinnati OH) Morton Scott C. (Cincinnati OH) Taylor Michelle L. (Cincinnati OH). Gas turbine engine fan cooled heat exchanger. USP1993125269135.
  14. Pask George (Stanton-by-Bridge GB2). Inlet for annular gas turbine combustor. USP1979124177637.
  15. Layland Michael J. (Bonita CA). Integrated engine shroud for gas turbine engines. USP1992015083426.
  16. Rodgers Joseph H. (Vernon CT) Kasprow Robert F. (Wethersfield CT). Method of operating a gas turbine engine powerplant for an aircraft. USP1996095553449.
  17. Laborie Daniel J. (Cincinnati OH) Marban Joseph R. (Springdale OH) Schulze Wallace M. (West Chester OH) Baumbick Robert J. (West Chester OH). Nacelle cooling and ventilation system. USP1994105351476.
  18. Dionne, Luc. Passive cooling system for auxiliary power unit installation. USP2005096942181.
  19. Koch William J.. Pressure augmented kiss seal. USP1999055899463.
  20. Orlando Robert J. (West Chester OH). Ramjet bypass duct and preburner configuration. USP1994055311735.
  21. Coffinberry George A. ; Leonard Gary L.. System and method of providing clean filtered cooling air to a hot portion of a gas turbine engine. USP1999075918458.
  22. Lillibridge Robert W. ; McGuire Kenneth R. ; Phillips Edward J. ; Matthews Eugene James. Turbofan engine with reduced noise. USP1999085943856.
  23. Miller Franklin E. (Cincinnati OH). Turbojet cooling system. USP1994105357742.