FIELD: engines and pumps.
SUBSTANCE: turbine of a gas turbine engine comprises outer, inner and intermediate bodies, a stage with a nozzle block and an impeller with a circular insert above the impeller, a system of turbine cooling and bodies. A facility of radial gap regulation includes a circular insert, outer, inner and intermediate bodies. The intermediate body is made of conical shape with a radial flange. The circular insert above the impeller is fixed on intermediate and inner bodies. The circular insert is made as hollow and is filled with a heat-accumulating material. The turbine cooling system comprises a pipeline, connected via a flow rate controller and an inner pipeline with a swirling device and with holes in the front deflector and the disc.
EFFECT: efficient adjustment of radial gaps in a turbine, reliable takeoff of an aircraft with such turbine.
3 cl, 6 dwg
