FIELD: engines and pumps.
SUBSTANCE: proposed process consists in feed of hot gas tapped from the channel arranged downstream of turbine into channel arranged between inlet device and engine compressor in amount sufficient for maintenance of gas preset temperature at compressor inlet. Gas temperature at compressor inlet is kept constant and equal to air deceleration temperature at aircraft cruising speed. Air flow rate through engine and pressure difference at nozzle (at permanent gas temperature at compressor inlet) vary with variation of engine inlet air pressure.
EFFECT: higher fuel efficiency at high flight speeds.
3 cl, 4 dwg
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