FIELD: machine building.
SUBSTANCE: turbine of a bypass gas turbine engine comprises at least one cooled stage with a nozzle block, a rotor and a stator of the turbine. The nozzle block is made with cavities above and underneath. The turbine rotor is made with a cooled impeller and a swirling device upstream. The turbine stator comprises a turbine body, a circular insert above the turbine impeller and a system of radial gap control. The turbine body is made of two parts: front and rear, the circular insert is installed between them. The stator is made as cooled by air of the secondary circuit. The system of stator-cooling air supply is made in the form of an air intake installed in the second circuit and a flow controller with a drive, and also comprises a on-board computer and sensors of radial gap measurement. The drive of the flow controller and sensors of radial gap measurement are connected by electric connections with the on-board computer.
EFFECT: efficient control of radial gaps in a turbine at all modes, increased engine thrust in takeoff and reheat power modes, increased efficiency and reliability of a turbine.
5 cl, 15 dwg
