FIELD: engines and pumps.
SUBSTANCE: aviation bypass turbojet engine comprises fan, high-pressure compressor, combustion chamber, high and low pressure turbines, mixer and afterburner and nozzle common for both circuits. Downstream the first stage of high-pressure compressor that provides for full pressure increase extent at takeoff regime of not more than πIext*=1.4…1.5, permanently open annular channel is arranged with honeycomb straightener, through which at all modes of engine operation, some air is relieved downstream stage into cocurrent flow of air in external circuit downstream fan.
EFFECT: increased extent of engine bypass-ratio and increased efficiency at non-augmented modes of operation.
1 dwg
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