FIELD: engines and pumps.
SUBSTANCE: gas turbine engine comprises two high- and low-pressure combustion chambers, and two gas turbines arranged along gas flow, recuperative air heater, compressor, and air turbine. Second turbine at gas inlet is communicated with low-pressure combustion chamber outlet. Recuperative air heater heating gas inlet is communicated with last gas turbine outlet while heating has outlet is communicated with atmosphere. Air turbine is fitted on one shaft with compressor and has its air inlet communicated with compressor outlet via recuperative air heater air channel and its air outlet, with atmosphere. Low-pressure combustion chamber working medium inlet is communicated with recuperative air heater outlet. Second gas turbine has inlet is communicated with first gas turbine gas outlet.
EFFECT: higher efficiency at moderate gas temperatures ahead of second gas turbine and behind last gas turbine.
4 dwg
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