Aeronautics and astronautics – Aircraft structure – Ice prevention
Patent
1974-12-23
1976-09-21
Blix, Trygve M.
Aeronautics and astronautics
Aircraft structure
Ice prevention
60 3909D, 165 42, 244 53B, 244 59, 244118P, B64D 1502, B64D 1308
Patent
active
039814661
ABSTRACT:
An integrated thermal anti-icing and environmental control system for a gas turbine powered aircraft uses hot high pressure bleed air from the turbine compressor to de-ice the wings and the engine air inlet, and supplies conditioned air for the aircraft cabin. In order to minimize total bleed air requirements and maximize heat recovery, bleed air exhausted from the inlet anti-icing system is passed sequentially through other systems. In this invention, the usual pre-cooler unit and the associated heat sink are eliminated and the pre-cooling function is performed within the inlet anti-icing system, preferably through the use of a double skin heat exchanger contained within the lip of the inlet. One embodiment of this system includes a closed-loop liquid anti-icing system for acoustic rings mounted in the inlet wherein the liquid is heated by passing the bleed air through a heat exchanger mounted immediately downstream of the inlet anti-icing system.
REFERENCES:
patent: 2594118 (1952-04-01), Boyd
patent: 2712727 (1955-07-01), Morley et al.
patent: 2777301 (1957-01-01), Kuhn
patent: 3341114 (1967-09-01), Larson
Blix Trygve M.
Donahue Bernard A.
Kelmachter Barry L.
Richardson Al
The Boeing Company
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