发明名称 |
HIGH BY-PASS RATIO TURBOJET ENGINE WITH COUNTERROTATING UPSTREAM AND DOWNSTREAM FANS |
摘要 |
A turbojet bypass engine includes an upstream fan of a conventional type and also a downstream fan arranged to rotate in the opposite direction to the upstream fan and driven by a free turbine interleaved with the low pressure turbine which drives the upstream fan. The two fans are supplied by separpate overlapping and inverleaved air flow paths which are formed largely within the nacelle structure of the engine, giving the nacelle an ovoide shape which allows such engines with a high bypass ratio to be mounted below the wings of an aircraft.
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申请公布号 |
US5058379(A) |
申请公布日期 |
1991.10.22 |
申请号 |
US19900504839 |
申请日期 |
1990.04.05 |
申请人 |
SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION |
发明人 |
LARDELLIER, ALAIN M. J. |
分类号 |
F02C3/067;F02C3/073;F02K3/065;F02K3/072;F02K3/077 |
主分类号 |
F02C3/067 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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