发明名称 |
Low observable engine inlet system |
摘要 |
A turbine engine inlet system includes a curved duct 14 to deliver air to the engine, an inlet lip 16 to smooth the entry of air flowing into the duct, a forward inlet section 18 submerged within the aircraft skin contour to provide a degree of ram recovery to the duct, and a movable air deflector 20 which is flush with the forward inlet section 18 during normal flight conditions and extended to slightly above the inlet lip 16 during icing conditions.
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申请公布号 |
US5694763(A) |
申请公布日期 |
1997.12.09 |
申请号 |
US19900507686 |
申请日期 |
1990.04.11 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
AMELIO, ARMAND F.;BARNARD, RICHARD S.;MANZOLLI, JAMES J. |
分类号 |
B64D33/02;F02C7/042;F02C7/047;F02C7/05;(IPC1-7):F02C7/055 |
主分类号 |
B64D33/02 |
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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