FIELD: turbine construction.
SUBSTANCE: invention relates to turbine construction, namely to a system for regulating the radial clearance in gas turbine engines. Active radial clearance control system in the turbine comprises a movable ring disposed between the stator shroud liners, the turbine stator housing and the outer ring of the turbine, and pneumatic valves to supply the cooling air to the movable ring and to the shroud liners through cooling channels made in the movable ring. Movable ring has an annular ridge with through grooves radially made therein. Annular sealing rings are provided on the outer surface of the movable ring. Movable ring is connected to the turbine stator housing and the outer ring of the turbine by means of bushings inserted into the through grooves of the annular ridge of the movable ring. Axes of the bushings are parallel to the central axis of the engine. Through grooves of the movable ring are designed so that the turbine stator housing is radially contracted under thermal compression shifting along the said through grooves due to moving the bushings there through within a radially contracting rolling ring during the thermal compression.
EFFECT: simplifies and improves the reliability of the system for regulating the radial clearance between the ends (tops) of the rotor blades and the stator shroud liners when the engine rpm are lowered.
6 cl, 5 dwg
