Two/multistage axial turbine, especially for aircraft engine, has intermediate stage sealing ring with front projection parallel to vane ring, to seal ring channel for working gas

摘要

The gas turbine incorporates an intermediate stage sealing ring (20). The ring has a section (21a) close and parallel to the vane ring (12a), with an L-shaped front projection facing the front rotor plate (8). The first inner radial leg (27a) of the projection extends mainly parallel to the plate, and its second leg (27b) extends mainly in axial direction (19) from the plate. The intermediate stage sealing ring has several passage bores (22c) on the level of the second leg, to guide the cooling air flow.