GAS TURBINE ENGINE AXIAL FLOW TURBINE Russian patent published in 2017 - IPC F01D11/16 F01D25/24 F01D5/20 

FIELD: engines and pumps.

SUBSTANCE: axial flow turbine of the gas turbine engine includes the outer housing with installed in it fixed blades and overrotor inserts, forming with the housing at least one pressurization cavity, connected to the cooling air supply system, the rotor with rotor blades having a profile portion limited by the concave and convex surfaces. At that the overrotor insert in its projection is perpendicular to the working blade, made in the form of a parallelogram, which two parallel sides perpendicular to the axis of the turbine rotor, have the length of 0.3…1.1 of the maximum distance between the concave surfaces of the rotor blades in their plane of rotation. The other two sides of the overrotor insert projection are inclined from the turbine rotor axis at the angle 30…80° toward the rotor blades rotation.

EFFECT: invention allows to provide small clearances at all modes, considering the error of the parts manufacture, the difference of the thermal expansions of parts and the eccentricity of the turbine rotor, while maintaining the low wear of rotor blades end faces and overrotor inserts, thus increasing the operation time of the turbine with maximum efficiency and power.

2 cl, 4 dwg