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특허 상세정보

MyON담기
내보내기 페이스북 공유 카카오톡 공유

Gas turbine engine having slim-line nacelle

특허상세정보
국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-001/00   
미국특허분류(USC) 060/771; 060/226.1; 137/015.1
출원번호 US-0832254 (2010-07-08)
등록번호 US-8353164 (2013-01-15)
발명자 / 주소
  • Morford, Stephen A.
  • Larkin, Michael J.
출원인 / 주소
  • United Technologies Corporation
인용정보 피인용 횟수 : 0  인용 특허 : 88
초록
▼

A gas turbine engine system includes nacelle, a first boundary layer control device, a second boundary layer control device, at least one sensor, and a controller. The nacelle is defined about an axis and includes an inlet lip section, an inlet internal diffuser section, and a variable area fan nozzle moveable to influence a discharge airflow area of the nacelle. The first boundary layer control device is positioned near the inlet lip section and is actuable to introduce a first airflow at the inlet lip section. The second boundary layer control device i...

대표
청구항
▼

1. A gas turbine engine system, comprising: a nacelle defined about an axis and having an inlet lip section and an inlet internal diffuser section, wherein said nacelle includes a variable area fan nozzle moveable to influence a discharge airflow area of said nacelle;a first boundary layer control device positioned near said inlet lip section and actuable to introduce a first airflow at said inlet lip section;a second boundary layer control device positioned near said inlet internal diffuser section and actuable to introduce a second airflow at said inle...

이 특허에 인용된 특허 (88)

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