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Nacelle assembly having inlet bleed

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F01D-013/02   
미국특허분류(USC) 415/144; 415/175
출원번호 US-0956372 (2007-12-14)
등록번호 US-8192147 (2012-06-05)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Carlson Gaskey & Olds P.C.
인용정보 피인용 횟수 : 5  인용 특허 : 83
초록

A nacelle assembly for a turbine engine has a cowl. The cowl extends along an axis and has an exterior surface spaced from an interior surface. The interior surface forms an air inlet for directing airflow to the turbine engine. An opening is disposed on the cowl. A device for creating suction through the opening is in fluid communication with the opening. The opening removes a portion of a boundary layer flow through the cowl, thereby providing higher energy flow along the interior surface.

대표
청구항
▼

1. A nacelle assembly for a turbine engine, comprising: a cowl for a turbine engine, said cowl extending along an axis and having an exterior surface spaced from an interior surface, said interior surface forming an air inlet for directing air flow to the turbine engine;an opening disposed on said cowl;a device for creating suction through said opening, said device for creating suction in fluid communication with said opening; anda valve disposed between said opening and said device for creating suction, said valve for controlling fluid flow through said...

이 특허에 인용된 특허 (83)

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이 특허를 인용한 특허 피인용횟수: 5

  1. Fulayter, Roy D.; Smith, Crawford F.. Engine nacelle. USP20180910072511.
  2. Richardson, Giles Anthony; MacManus, David; Sheaf, Christopher Thomas John. Intake liner for a gas turbine engine. USP2015018931252.
  3. Brown, Keith T.. Modular plenum and duct system for controlling boundary layer airflow. USP2017099758240.
  4. Baruzzini, Dan J.; Miller, Daniel N.; Domel, Neal D.; Hakes, Jeff G.. Suprression of shock-induced airflow separation. USP20180810054048.
  5. Morford, Stephen A.. Turbomachine flow stability enhancement device control. USP2018049932121.

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