Patent ID: 6415595
Filing Date: 2002-07-09
Classification: B64D,F01D,F02C,Y02T

Abstract:
An integrated thermal management and coolant system for an aircraft including a turbo fan jet propulsion engine having a fan, a main engine core including a compressor and a main engine core bypass duct, comprising:a fuel reservoir; a pump for pumping fuel from the reservoir; a first heat load connected to said pump to receive fuel pumped by said pump and to be cooled by the fuel; a check valve downstream from said first heat load and upstream of a junction; at least one second heat load connected to said junction; a fuel/fan air heat exchanger having a fan air flow path in heat exchange relation with a fuel flow path having a fuel discharge end connected to said junction, said fan air flow path adapted to be connected to receive compressed air from the fan of the engine; a bleed air/fuel heat exchanger having a fuel flow path and a bleed air flow path in heat exchange relation with one another, the bleed air flow path being adapted to be connected to the main engine core to receive bleed air from the compressor thereof, said bleed air/fuel flow path being connected, at one end, to deliver fuel to said main engine core to be combusted therein and to said fuel/fan air heat exchanger to deliver fuel thereto for cooling and return to said junction; and a control valve interposed between said second heat load and said main engine core for proportioning the flow of fuel to said main engine core and said fuel/fan air heat exchanger; whereby excess fuel is recirculated without reintroduction into said fuel reservoir and fuel at a desired elevated temperature is delivered to said main engine core.