Aircraft engine inlet cowl anti-icing system

Details Aircraft engine inlet cowl anti-icing system Aircraft engine inlet cowl anti-icing system

1988-10-03

1992-02-18

Casaregola, Louis J.

Power plants

Combustion products used as motive fluid

With safety device

244134R, F02C 7047

Patent

active

050882775

ABSTRACT:
A system is provided for preventing and removing ice accumulation from the leading edges of an inlet cowl of an aircraft gas turbine engine. High pressure, high temperature air, preferrably from a port on the engine compressor, is provided to an annular duct located within an annular chamber formed at the leading edge of the inlet cowl. A plurality of air ejector nozzles are spaced about the air duct and function to direct anti-icing air at a supersonic velocity toward the forward inboard surface of the inlet cowl and create a swirling air mass within the annular chamber.

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patent: 4688745 (1987-08-01), Rosenthal
patent: 4738416 (1988-04-01), Birbragher

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