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특허 상세정보

Compressor comprising a plurality of cells reconstituting an annular volume of separation of flows in a turbine engine

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F01D-001/04    F01D-001/00   
미국특허분류(USC) 415/069; 415/077; 416/193.R; 416/129; 060/226.1
출원번호 UP-0465998 (2006-08-21)
등록번호 US-7618232 (2009-11-27)
우선권정보 FR-05 08656(2005-08-22)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Oblon, Spivak, McClelland, Maier & Neustadt, L.L.P.
인용정보 피인용 횟수 : 3  인용 특허 : 10
초록

This turbine engine compressor comprises a separating nose extended by inner and outer annular walls defining in cooperation an annular volume (V) of separation of a primary flow (F1) and a secondary flow (F2). This volume (V) comprises a plurality of annular segments in the form of cells separated in pairs by blades of a first fan, these blades passing through both the primary flow (F1) and the secondary flow (F2). These cells are fixed to an upstream annular collar and a downstream annular collar driven rotationally by the aforementioned blades.

대표
청구항

The invention claimed is: 1. A turbine engine compressor, comprising: a separating nose extended by an inner annular wall and an outer annular wall defining in cooperation an annular volume and the nose is configured to separate a primary flow from a secondary flow, wherein said volume comprises a plurality of annular segments in the form of cells separated in pairs by blades of a first fan, said blades of a first fan passing through both said primary flow and said secondary flow, said cells being fixed to an upstream annular collar and a downstream ann...

이 특허에 인용된 특허 (10)

  1. Orlando, Robert Joseph; Moniz, Thomas Ory; Baughman, John Lewis. Aircraft gas turbine engine having variable torque split counter rotating low pressure turbines and booster aft of counter rotating fans. USP2004076763654.
  2. Antuna Eugene J. (Springdale OH) Keck Donald F. (Fairfield OH) Roth Robert H. (Cincinnati OH) Brantley James W. (Fairfield OH) Wakeman Thomas G. (Lawrenceburg IN) Fravel Jeffrey B. (Cincinnati OH) Co. Apparatus for removably attaching a core frame to a vane frame with a stable mid ring. USP1993065222360.
  3. Seda, Jorge F.; Dunbar, Lawrence W.; Szucs, Peter N.; Brauer, John C.; Johnson, James E.. Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor. USP2004056732502.
  4. Moniz, Thomas Ory; Orlando, Robert Joseph. Counterrotatable booster compressor assembly for a gas turbine engine. USP2004056739120.
  5. Prentice, Ian Francis; Crall, David William; Busbey, Bruce Clark; Glynn, Christopher Charles; Bond, Donald Ray. Counterrotatable booster compressor assembly for a gas turbine engine. USP2003126666017.
  6. Orlando Robert J.. Gear driven booster. USP2000126158210.
  7. Taylor John B. (Cincinnati OH). High bypass ratio counterrotating gearless front fan engine. USP1989084860537.
  8. Bart,Jacques; Lacorre,Fabienne; Lebret,Yann; Le Rousseau,Vanessa; Morel,Patrick. Three-spool by-pass turbojet with a high by-pass ratio. USP2007117299621.
  9. Bart,Jacques; Beutin,Bruno; Lebret,Yann. Turbojet architecture with two fans at the front. USP2008087412819.
  10. Baughman, John Lewis; Orlando, Robert Joseph; Moniz, Thomas Ory. Variable torque split aircraft gas turbine engine counter rotating low pressure turbines. USP2004076763652.