发明授权
US6148605A Method and device for reversing the thrust of very high bypass ratio
turbojet engines
有权
用于反转非常高的旁路比涡轮喷气发动机的推力的方法和装置
- 专利标题： Method and device for reversing the thrust of very high bypass ratio turbojet engines
- 专利标题（中）： 用于反转非常高的旁路比涡轮喷气发动机的推力的方法和装置
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申请号： US262345申请日： 1999-03-04
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公开(公告)号： US6148605A公开(公告)日： 2000-11-21
- 发明人: Alain Lardellier
- 申请人： Alain Lardellier
- 申请人地址： FRX Paris
- 专利权人： Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "SNECMA"
- 当前专利权人： Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "SNECMA"
- 当前专利权人地址： FRX Paris
- 优先权： FRX9802674 19980305
- 主分类号： F01D1/30
- IPC分类号： F01D1/30 ; F02C3/113 ; F02C7/36 ; F16H3/60 ; F02K3/02
摘要：
A high bypass ratio turbojet engine comprising a fan rotated by the shaft of a low pressure turbine via a speed reducer is provided with a thrust reverser device by providing the speed reducer with first and second epicyclic gear trains which are mounted in parallel between the low pressure turbine and the fan and which are arranged in such a way as to drive the fan in a first direction of rotation when the engine is operated in a direct thrust mode, and to drive the fan in the opposite direction of rotation when the engine is to be operated in the reverse thrust mode.
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