发明名称 |
Low observable engine air inlet system |
摘要 |
A turbine engine inlet system includes a duct 14 to deliver air to the engine, inlet lips 16 and 52 to smooth the entry of air flowing into the duct, a screen 50 between the lips 52 and 16 for passage of inlet air, 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 positionable in a retracted position during normal flight, is extendable outward to a second position substantially flush with the screen 50 for maximum protection against foreign object damage (FOD), and is further extendable outward to a third position beyond the screen to provide an air bypass path when the screen is iced-over.
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申请公布号 |
US5697394(A) |
申请公布日期 |
1997.12.16 |
申请号 |
US19930020015 |
申请日期 |
1993.03.02 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
SMITH, DAVID R.;AMELIO, ARMAND F. |
分类号 |
B64D33/02;(IPC1-7):B64D33/02 |
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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