FIELD: aircraft industry. SUBSTANCE: aircraft turbojet engine has air intake diffuser, main combustion chamber with exit nozzles, turbine and additional combustion chamber with nozzle and air supply channel installed in behind-the-turbine space. Air supply channel provided with air heaters is connected at inlet to compressor outlet. Wall of exit nozzle serves as wall of additional combustion chamber. EFFECT: enhanced reliability of operation. 2 dwg
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