FIELD: manufacture of aircraft engines; transport engineering; heat-power engineering. SUBSTANCE: gas-turbine engine includes multi-stage compressor, turbine with hollow nozzle and working blades, additional turbine whose inlet is connected with outlet of multistage compressor and outlet is connected to intermediate stage. Blade cooling system has passages of semi-closed cooling system connected at inlet to chamber after additional compressor and loop passages of open cooling system located in head and tail portions of blade fin near back and through and separated by on passage of open cooling system. EFFECT: enhanced efficiency. 2 dwg
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