FIELD: aviation; engine cooling systems.
SUBSTANCE: invention relates to cooling systems of helicopter type aircraft engines. System includes engine cooling jacket (1), radiators communicated by supply and discharge pipelines with cooling jacket. System is equipped with individual thermostats installed at the radiator inlet or outlet. Radiators are made in the form of a row of hollow deflectors (5) of air flow located under bearing screws (14) and connected to supply and discharge pipelines in parallel.
EFFECT: higher uniformity of engine cooling at changes of its operation mode and environmental conditions, as well as reduced material consumption and power consumption for cooling.
3 cl, 4 dwg
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