- 专利标题: Air intake of a turbojet engine nacelle comprising guide vanes
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申请号: US17600539申请日: 2020-04-08
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公开(公告)号: US11614051B2公开(公告)日: 2023-03-28
- 发明人: Anthony Binder , Daniel-Ciprian Mincu
- 申请人: SAFRAN AIRCRAFT ENGINES
- 申请人地址: FR Paris
- 专利权人: SAFRAN AIRCRAFT ENGINES
- 当前专利权人: SAFRAN AIRCRAFT ENGINES
- 当前专利权人地址: FR Paris
- 代理机构: KOS IP Law LLP
- 优先权: FR1904094 20190417
- 国际申请: PCT/EP2020/060040 WO 20200408
- 国际公布: WO2020/212228 WO 20201022
- 主分类号: F02K1/66
- IPC分类号: F02K1/66 ; B64D33/02 ; F02C7/042
摘要:
Disclosed is a method for using an aircraft turbojet engine comprising an air inlet comprising a plurality of rectifier vanes, each rectifier vane being mounted such that it can move between a retracted position to assist the thrust phase and a deployed position in which the rectifier vane protrudes from the inner wall in a radially inward direction in order to rectify the reverse air flow of the inner wall to assist a thrust-reverse phase, in which method at least one rectifier vane is in the retracted position during a turbojet engine thrust phase, the method comprising, during a thrust-reverse phase of the turbojet engine, a step of moving the rectifier vane to the deployed position.