Aircraft anti-icing plenum

Aeronautics and astronautics – Aircraft structure – Ice prevention

Patent

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Details

60 3909D, 244 42CC, B64D 1504

Patent

active

039333272

ABSTRACT:
The leading edge of the jet engine nacelle is provided with structure to prevent the formation of ice particles at the inlet of the jet engine. The nacelle is split into leading and trailing chambers and there is a partition separating the chambers, the leading one of which includes the anti-icing apparatus. The leading chamber includes a double skin generally facing interiorly toward the jet engine and that double skin defines the nacelle therebetween which permits the passage of the hot gases which heat the outer skin from the inside thereof. Conduit means controllably pass hot exhaust gases from the jet engine to within the leading chamber from where they pass into a cell via a series of spaced apertures formed in the inner double skin. A series of spaced channels are formed between the inner and outer skins and connect the leading and trailing chambers. Those channels pass the spent heating gases into the trailing chamber which includes the structural acoustical sandwich comprising inner and outer skins separated by a layer of honeycomb core. The outer skin is apertured for acoustic purposes and the spent gases pass through those apertures and are discharged.

REFERENCES:
patent: 2514105 (1950-07-01), Thomas
patent: 2742247 (1956-04-01), Lachmann
patent: 3013641 (1961-12-01), Compton
patent: 3057154 (1962-10-01), Sherlaw et al.
patent: 3128973 (1964-04-01), Dannenberg
patent: 3566606 (1971-03-01), Mortlock
patent: 3820628 (1974-06-01), Hanson

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