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Gas turbine engine variable bleed pivotal flow splitter 원문보기

IPC분류정보
국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판)
  • F02C-006/18
  • F02G-003/00
출원번호 US-0026250 (1993-03-04)
발명자 / 주소
  • Liu Hsin-Tuan (West Chester OH) Hines William R. (Montgomery OH)
출원인 / 주소
  • General Electric Company (Cincinnati OH 02)
인용정보 피인용 횟수 : 65  인용 특허 : 0

초록 ▼

The present invention provides a gas turbine engine with a circumferentially disposed plurality of pivotal flow splitters between compressor sections to bleed off flow and remove particles, particularly ice in the case of an aircraft fan-jet gas turbine engine, by pivoting the leading edge of the sp

대표청구항 ▼

A gas turbine engine driven apparatus comprising: a load means driven by a low pressure rotor of a gas turbine engine having a booster compressor drivenly connected to a low pressure turbine on said low pressure rotor; a core engine compressor downstream of said booster compressor along a core engin

이 특허를 인용한 특허 (65)

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