FIELD: engines and pumps.
SUBSTANCE: cooling method of turbine work blade of gas-turbine engine includes exhaust of the cooling air from the air cavity of the combustion chamber, its transportation to the swirling assembly, made on the stator against the turbine disk, and further cooling air supply from the swirling assembly to the rotating channel of each work blade. Via the nozzles of the ring swirling assembly located along the circle tangentially with rotation in the direction of the turbine rotation and coaxially with input to the smooth channel of each blade the intermittent supply of the cooling air is ensured. As result of the periodic movement of the impact waves from the nozzles of the swirling assembly in each blade channel the forced oscillation of the cooling air are excited with frequency of the first resonant harmonics. The cooling air oscillations are created with frequency determined by the resonance conditions, air speed and wave length as per the set ratios, intensifying the heat exchange in channel between the blade and the cooling air.
EFFECT: invention increases engine economical efficiency upon keeping the reliability and increasing the engine service life.
2 cl, 10 dwg
