Low observable engine air inlet system

Details Low observable engine air inlet system Low observable engine air inlet system

1993-03-02

1997-12-16

Carone, Michael J.

Fluid handling

Processes

Cleaning, repairing, or assembling

137 152, 60 39092, 244 53B, B64D 3302

Patent

active

056973942

ABSTRACT:
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.

REFERENCES:
patent: 3537240 (1970-11-01), Weidinger et al.
patent: 4291530 (1981-09-01), Ballard
patent: 4397431 (1983-08-01), Ben-Porat
patent: 4406433 (1983-09-01), Radkey et al.
patent: 4655413 (1987-04-01), Genssler et al.
patent: 4836473 (1989-06-01), Aulehla et al.
patent: 4919364 (1990-04-01), John et al.
patent: 5116251 (1992-05-01), Bichler et al.

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