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특허 상세정보

Zero acoustic splice fan case liner

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-001/82    F02K-001/00    B64D-033/02    B64D-033/00    B64C-001/12    B64C-001/00   
미국특허분류(USC) 181/214; 181/213; 244/053.B; 244/131
출원번호 US-0899809 (2004-07-27)
등록번호 US-7328771 (2008-02-12)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Carlson, Gaskey & Olds
인용정보 피인용 횟수 : 15  인용 특허 : 19

A liner assembly for a fan case includes a noise attenuation layer covered by a face sheet. The face sheet includes openings to the underlying noise attenuation layer. The face sheet and noise attenuation layer include acoustically transparent joints. The noise attenuation layer includes a first side joined to a second side at a seam by an adhesive strip. The adhesive strip bonds the first side to the second side without filling any chambers. The face sheet includes a joint filled with an adhesive providing the desired uninterrupted surface within the fa...


What is claimed is: 1. A liner assembly for a fan case comprising: a noise attenuation layer; and a face sheet over said noise attenuation layer, said face sheet including a first plurality of openings and a joint, wherein said joint comprises a first seam comprising overlapped sides of said face sheet and an adhesive disposed over said overlapping sides, said joint including a second plurality of openings extending through said adhesive and each of said overlapped sides of said face sheet for communicating sound energy through said joint to said noise ...

이 특허에 인용된 특허 (19)

  1. Porte, Alain; Pascal, Nathalie; Thezelais, Sylvain; Rambaud, Eric. Acoustically resistive layer for an acoustical attenuation panel, panel using such a layer. USP2004086772857.
  2. Andre, Robert; Porte, Alain. Air inlet cowl for a jet engine, provided with deicing means. USP2003076585191.
  3. Hart-Smith Leonard J. (Long Beach CA). Aircraft skin lap splice. USP1994035297760.
  4. Stretton, Richard G; Udall, Kenneth F. Cowl structure for a gas turbine engine. USP2005056892526.
  5. Alain Porte FR; Stephane Viala FR. Device for discharging hot air for a jet engine air inlet cowl, with a deicing circuit. USP2002086427434.
  6. Porte Alain,FRX. Device for removing hot air for a jet engine air inlet cowl with a de-icing circuit. USP2000106131855.
  7. Wollaston Tim,GBX ; Pedwell Richard,GBX ; Bush Paul,GBX. Friction welding metal components. USP2001126328261.
  8. Wilkinson Wilfred H. (Turnditch GB2). Metal cavitated sandwich structures. USP1979074161231.
  9. Porte, Alain; Batard, Herve. Noise reduction sandwich panel, notably for aircraft turbojet engine. USP2003036536556.
  10. Anderson Robert E. (Huntington Station NY) Parente Charles A. (Oyster Bay NY). One-piece engine inlet acoustic barrel. USP1996125581054.
  11. Porte, Alain; Pascal, Nathalie; Chene, Gilles; Montetagaud, Fabienne. Process for de-icing an air intake cowling of a reaction motor and device for practicing the same. USP2003076592078.
  12. Buge, Michel; Porte, Alain; Poignonec, Jean-Marc. Process for making a panel with a protected acoustic damping layer and acoustic panel as made. USP2004116820337.
  13. Andre, Robert; Porte, Alain; Rambaud, Eric. Process for the production of an acoustively resistive layer, resistive layer thus obtained, and wall using such layer. USP2003086607625.
  14. Dublineau, Pascal; Buge, Michel; Porte, Alain. Process for the production of holes particularly micro-perforations in a composite material, device for its practice and sound damping layer constituted by said material. USP2005086923931.
  15. Porte, Alain; Lalane, Jacques. Sandwich acoustic panel. USP2003096615950.
  16. Shuttleworth Richard G. (South Windsor CT) Snyder Gene R. (Vernon CT). Sound absorbing structure. USP1981104293053.
  17. Brian E. Barton. Translating independently mounted air inlet system for aircraft turbofan jet engine. USP2002016340135.
  18. Porte, Alain. Tubular acoustic attenuation piece for an aircraft jet engine air intake. USP2004076761245.
  19. Readnour Jack L. (Ft. Mitchell KY) Wright Jack D. (Mason OH). Variable contour annular air inlet for an aircraft engine nacelle. USP1991035000399.

이 특허를 인용한 특허 피인용횟수: 15

  1. Chiou, Song; Yu, Jia; Hubert, Claude; Layland, Michael. Acoustic barrel for aircraft engine nacelle including crack and delamination stoppers. USP2010097798285.
  2. Herrera, Eric; Nesbitt, Eric H.. Acoustic panel. USP2014098820477.
  3. Porte, Alain; Lalane, Jacques; Gantie, Fabrice; Barillot-Creuzet, Jacques. Acoustic processing structure particularly adapted to the air inlet of an aircraft nacelle. USP2013048413922.
  4. Herrera, Eric; Gerken, Noel Timothy; Bauman, John Scott. Automated production of acoustic structures. USP2017069693166.
  5. Lussier, Darin S.; Robertson, Jr., Thomas J.; Costa, Mark W.; Voleti, Sreenivasa R.; Naik, Rajiv A.. Composite fan containment case assembly. USP2014038672609.
  6. Harper, Cedric B.; Humphries, Neil. Fan section. USP2013118578697.
  7. Welch, John M.; Strunk, John Thomas; Kitt, Brian R.. Method for bonding honeycomb cores. USP2012088251174.
  8. Ali, Amr; Qiu, Yuan J.. Multi-splice acoustic liner. USP2013128602156.
  9. Chiou, Song; Yu, Jia; Hubert, Claude; Layland, Michael. Reinforcement members for aircraft propulsion system components configured to address delamination of the inner fixed structure. USP2015049016042.
  10. Gerken, Noel Timothy; Herrera, Eric; Patz, Nicholas John. Septumization of cellular cores. USP2018049931825.
  11. Butler, Geoffrey Allen; Lan, Justin Honshune; Gerken, Noel T.; Duschl, Garry M.; Day, Benjamin Julius. Septumization of honeycomb sandwiches. USP2017059643392.
  12. McAuliffe, Christopher; Merritt, Brent J.. Shrouded particle separator. USP2014038679210.
  13. Chapin, Clifford O.. System for reducing stress concentrations in lap joints. USP2010127850387.
  14. Simpson, David L.. Welded lap joint with corrosive-protective structure. USP20190410252376.
  15. Costa, Mark W.; Brown, Charles; Foose, Andrew S.. Zero acoustic splice fan case liner. USP2010097797809.