FIELD: engines and pumps.
SUBSTANCE: claimed engine comprises the compressor to compress air forced from the air intake, combustion chamber to combust the fuel with the help of compressed air to produce the hit gas, and the turbine. The turbine comprises the rotor or the shaft with turbine blades for hot gas to flow there through and to expand to doe work. There are the first means for cooling of turbine blades by compressed air that include at least one separate compressor stage for compression of cooling air irrespective of the main compressor. At least one compressor stage is built in the rotor or the shaft. At least one compressor stage is arranged downstream of turbine last stage rotor blades along the flow. At least one compressor stage intakes the cooling airflow from the rotor bearing chamber and at least one compressor stage forces the main amount of compressed cooling air to the turbine last stage rotor blades for their cooling.
EFFECT: higher efficiency of cooling.
6 cl, 3 dwg
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