LOW OBSERVABLE ENGINE INLET SYSTEM
Assignee
UNITED TECHNOLOGIES CORPORATION, A CORP. OF DE
Filed
Apr 11, 1990
Granted
Dec 9, 1997
Location
YONKERS NY US
Abstract
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.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Sep 14, 1990
Rescinded
Apr 9, 1997
Duration
6 years, 6 months
Inventor
- 1ARMAND F. AMELIO
Record Details
- Patent number
- US 5694763
- Application
- 07507686
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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