FIELD: aeronautical engineering; gas-turbine engines with heat addition in afterburner which are provided with propulsive jet nozzles with thrust vector changeable in direction. SUBSTANCE: method consists in delivery of air and fuel to afterburner. On the command for turning the nozzle, flow rates of air and fuel are increased at walls of swivel nozzle in incoming gas flow located on side opposite to deflection of longitudinal axis of nozzle from longitudinal axis of engine. EFFECT: reduction of temperature of nozzle walls to safe level from standpoint of their own serviceability (absence of scorching, maintenance of strength characteristics, etc) and from standpoint of their serviceability in nozzle mechanism (absence of wedging, etc). 8 cl, 2 dwg
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