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Gas turbine engine having slim-line nacelle 원문보기

IPC분류정보
국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판)
  • F02K-001/00
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 nozz

대표청구항 ▼

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 d

이 특허에 인용된 특허 (88)

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