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특허 상세정보

Integrated inlet fan case

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F01D-001/00   
미국특허분류(USC) 415/220; 415/182.1
출원번호 US-0211127 (2008-09-16)
등록번호 US-8092169 (2012-01-10)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Carlson, Gaskey & Olds, PC
인용정보 피인용 횟수 : 7  인용 특허 : 14

A fan section of a gas turbine engine includes nacelle inlet and a fan containment case that are integrally formed together as a single-piece component.


1. A fan section for a gas turbine engine comprising: a fan containment case formed as a single-piece structure with a nacelle inlet wherein said single-piece structure includes a fore end portion that forms said nacelle inlet and an aft end portion that forms said fan containment case, and wherein said aft end portion includes an engine case flange connector; andat least one bulkhead positioned at said fore end portion. 2. The fan section according to claim 1 wherein said single-piece structure has a radially outer circumferential surface and a radially...

이 특허에 인용된 특허 (14)

  1. Jones,Emlyn; Stretton,Richard G. Aeroengine nacelle. USP2006087090165.
  2. Porte, Alain; Batard, Herv?. Aircraft engine pod with acoustic attenuation. USP2005056896099.
  3. Harrison, Geoffrey E.. Annular acoustic panel. USP2005076920958.
  4. Dembeck Kurt M. (Vernon CT). Containment shell for a fan section of a gas turbine engine. USP1983114417848.
  5. Belanger Homer J. (Glastonbury CT) Patacca Angelo M. (Glastonbury CT). Containment structure. USP1984064452563.
  6. Porte, Alain; Lalane, Jacques. Device for connecting two tubular pieces of an aircraft turbine engine. USP2005026857669.
  7. Penda Allan R. (Amston CT). Fan blade containment assembly. USP1996015482429.
  8. Moe, Jeffrey W.; Wunsch, John J.; Sperling, Michael S.. Method and apparatus for noise abatement and ice protection of an aircraft engine nacelle inlet lip. USP2009097588212.
  9. Brodell Robert F. (Marlborough CT) Hovan Edward J. (Manchester CT) Selfors Steven T. (Somerville MA) Loffredo Constantino V. (Newington CT) Duesler Paul W. (Manchester CT). Nacelle and mounting arrangement for an aircraft engine. USP1996065524847.
  10. Costa Mark W. ; Foose Andrew S. ; Korn Nathan D. ; Kowza Jan B. ; Lopardi Wendy P. ; Welch Douglas A.. Penetration resistant fan casing for a turbine engine. USP2000056059524.
  11. Brian E. Barton. Translating independently mounted air inlet system for aircraft turbofan jet engine. USP2002016340135.
  12. Kulak Andrew C. (Hartford CT) White Richard T. (West Hartford CT). Turbofan containment structure. USP1995045409349.
  13. Dhoore Louis G. (Seattle WA) Schultz William H. (Bellevue WA). Turbofan engine having variable geometry fan duct. USP1979054155221.
  14. Readnour Jack L. (Ft. Mitchell KY) Wright Jack D. (Mason OH). Variable contour annular air inlet for an aircraft engine nacelle. USP1991035000399.