HARDWARE LIQUID COOLING SYSTEM Russian patent published in 2008 - IPC B64D47/00 H01L23/473 

FIELD: engines and pumps.

SUBSTANCE: aircraft hardware liquid cooling system incorporates a closed-circuit system circulating cooling liquid through the hardware units, a pump cut in the closed-circuit between its drain and pressure pipelines, a heat exchanger with its cooling liquid space connected to the closed-circuit line and the said space input connected to the cooling medium source. The said system is provided with a heat exchanger with cold heat carrier space inlet connected to the source of another cooling medium, while the said exchanger cooling liquid space is cut in the closed-circuit line tee connected to the said line parts with its intake and discharge pipelines. The system tee input pipeline is connected to the closed-circuit pressure line, while the tee discharge line is connected to the closed-circuit discharge pipeline. The pump, the heat exchanger and the hardware units are connected into the closed circuit in the above succession along the liquid flow. The system incorporates a three-way liquid selector valve with one inlet and two outlet branch pipes, the inlet and one of the outlet branch pipes being connected to the tee outlet pipeline. There is also a pipeline connecting the three-way valve second outlet branch pipe with the tee inlet pipeline. The said valve connects, depending upon its operating position, the tee outlet pipeline to the closed-circuit line or to the tee inlet pipeline. The flow rate and cooling liquid temperature metering means are provided for in the tee pipeline.

EFFECT: optimisation of the hardware cooling.

12 cl, 2 dwg