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특허 상세정보

Nacelle inlet with extended outer barrel

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64D-029/00    F04D-029/52    B64D-033/02    F02C-007/04   
출원번호 US-0713680 (2015-05-15)
등록번호 US-9874228 (2018-01-23)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    O'Shea Getz P.C.
인용정보 피인용 횟수 : 0  인용 특허 : 20
초록

A nacelle inlet is provided for an aircraft propulsion system. This nacelle inlet includes an outer barrel, a bulkhead and a plurality of supports. The outer barrel extends around an axis and along the axis to an aft end. The bulkhead is within and connected to the outer barrel. An aft portion of the outer barrel projects axially aftward from the bulkhead to the aft end. The supports are disposed around the axis and next to the bulkhead. The supports are configured to support the aft portion of the outer barrel.

대표
청구항

1. A nacelle inlet for an aircraft propulsion system, the nacelle inlet comprising: an outer barrel extending around an axis and along the axis to an aft end;a bulkhead within and connected to the outer barrel, wherein an aft portion of the outer barrel projects aftward axially from the bulkhead to the aft end;a plurality of supports disposed around the axis and next to the bulkhead, the supports configured to support the aft portion of the outer barrel; anda plurality of plenums for an active laminar flow control system, wherein the outer barrel is perf...

이 특허에 인용된 특허 (20)

  1. Coffinberry George A. (West Chester OH). Aircraft gas turbine engine bleed air energy recovery apparatus. USP1992085137230.
  2. Porte, Alain; Fargues, Matthieu; Marro, Martial. Aircraft nacelle comprising a reinforced connection between an air intake and a powerplant. USP2017029567905.
  3. Vauchel, Guy Bernard; Dauguet, Jean-Philippe; Beilliard, Stephane. Aircraft nacelle guidance system installation. USP2012128333344.
  4. Harrison, Geoffrey E.. Annular acoustic panel. USP2005076920958.
  5. Calder, David P.; Howarth, Graham F.. Apparatus for facilitating access to a nacelle interior. USP2015119188025.
  6. Hendricks, Gavin. Cambered aero-engine inlet. USP2013098528318.
  7. Farstad, Jerry E.. Engine assembly, acoustical liner and associated method of fabrication. USP2011017870929.
  8. Coffinberry George A. (West Chester OH). Gas turbine engine fan duct base pressure drag reduction. USP1992085141182.
  9. Lahti Daniel J. (Cincinnati OH) Yates David E. (Cincinnati OH) Mungur Parmanand (West Chester OH) Stockman Norbert O. (Batavia OH). Hybrid laminar flow nacelle. USP1991024993663.
  10. Safai, Morteza; Elangovan, Rangasamy; Khozikov, Vyacheslav. Ice protection system and method. USP2014078777163.
  11. Cloft, Thomas G.; Prihar, Ron I.; Lussier, Darin S.. Integrated inlet fan case. USP2012018092169.
  12. Meyer,Pascal J. Laminar flow nacelle for an aircraft engine. USP2006057048230.
  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. Zysman, Steven H.; Lord, Wesley K.; Miller, Robert M.; Atassi, Oliver V.. Passive boundary layer bleed system for nacelle inlet airflow control. USP2014098839805.
  17. Zysman, Steven H.; Lord, Wesley K.; Miller, Robert M.; Atassi, Oliver V.. Passive boundary layer bleed system for nacelle inlet airflow control. USP2014098844553.
  18. 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.
  19. Brian E. Barton. Translating independently mounted air inlet system for aircraft turbofan jet engine. USP2002016340135.
  20. Hughes Kevin A. (San Diego CA) Shieh Chih F. (San Diego CA). Turbine engine nacelle laminar flow control arrangement. USP1994035297765.