Prevention of icing in the intakes of aerospace propulsors

Details Prevention of icing in the intakes of aerospace propulsors Prevention of icing in the intakes of aerospace propulsors

1989-02-17

1992-02-18

Carone, Michael J.

Power plants

Reaction motor

Liquid oxidizer

602701, 60267, 62 521, 62 12, F02K 900

Patent

active

050882805

ABSTRACT:
An air intake suitable for an aerospace propulsor comprises a duct which contains, in flow series, a first heat exchanger, a water separator, and a cryogen injector and a second heat exchanger. Air entering the intake is cooled by the first heat exchanger to cause the majority of the water vapor in the air to condense into water droplet form. The water droplets are then removed by the air flow by the water separator. The cryogenic injector reduces the air flow temperatures still further so that any remaining water in the air flow is converted to small dry ice crystals which do not block the second heat exchanger.

REFERENCES:
patent: 2920448 (1960-01-01), Coanda
patent: 3040519 (1962-06-01), Rae
patent: 3557557 (1971-01-01), Prachar
patent: 3561217 (1971-02-01), Hall
patent: 3775977 (1973-12-01), Builder et al.
patent: 4771601 (1988-04-01), Spies
patent: 4782655 (1988-11-01), Weber
patent: 4893471 (1990-01-01), Huling
patent: 5025623 (1991-06-01), Hirakoso et al.

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