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특허 상세정보

MyON담기
내보내기 페이스북 공유 카카오톡 공유

Gas turbine engine system providing simulated boundary layer thickness increase

특허상세정보
국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-003/02   
미국특허분류(USC) 060/226.1; 137/015.1
출원번호 US-0963667 (2010-12-09)
등록번호 US-8209953 (2012-07-03)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Carlson, Gaskey & Olds PC
인용정보 피인용 횟수 : 3  인용 특허 : 85
초록
▼

A gas turbine engine system for an aircraft includes a nacelle having a fan cowl with an inlet lip section and a core cowl, at least one compressor and at least one turbine, at least one combustor between the compressor and the turbine, a bleed passage, and a controller. The bleed passage includes an inlet for receiving a bleed airflow and an outlet that discharges the bleed airflow in an upstream direction from the outlet. The controller identifies an operability condition and selectively introduces the bleed airflow near a boundary layer of the inlet l...

대표
청구항
▼

1. A gas turbine engine system for an aircraft, comprising: a nacelle defined about an axis, wherein said nacelle includes a fan cowl having an inlet lip section and a core cowl disposed at least partially within said fan cowl;at least one compressor and at least one turbine positioned downstream of said at least one compressor;at least one combustor positioned between said at least one compressor and said at least one turbine;a bleed passage having an inlet that receives a bleed airflow and an outlet that discharges said bleed airflow in an upstream dir...

이 특허에 인용된 특허 (85)

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이 특허를 인용한 특허 피인용횟수: 3

  1. Sawyers-Abbott, Nigel David. Combined inlet laminar and thrust reverser cascade efflux flow control system. USP2018049951719.
  2. Richardson, Giles Anthony; MacManus, David; Sheaf, Christopher Thomas John. Intake liner for a gas turbine engine. USP2015018931252.
  3. Surply, Thierry; Bourdeau, Christophe. Turbojet nacelle and method for controlling separation in a turbojet nacelle. USP2014028640986.

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