FIELD: engines and pumps.
SUBSTANCE: engine high-pressure turbine comprises at least one vaned disc and two radially outer chambers. One of said chambers is located at disc inlet to receive vent air flow for disc vanes from combustion chamber bottom. Second chamber is located at disc outlet. Vaned rotor disc comprises inlet and outlet circular flanges separating radially inner circular chamber accommodating disc hub. Disc inlet flange comprises means to communicate radially outer inlet chamber and radially inner chamber for disc hub ventilation. Said means comprise radial grooves made at disc inlet flange inlet surface. Said grooves make channels for air circulation between inlet flange and engine rotary part coupled with said flange.
EFFECT: decreased heat gradients in high-pressure turbine rotor and heat response of said disc.
10 cl, 2 dwg
