Turbine stage for turbine engine e.g. turbojet or turbo propeller of airplane, has casing whose annular attachment radially extends towards upstream end of sectorized ring, where radial clearance is determined between casing and ring

摘要

The turbine stage has a radial-flow impeller (14) enclosed by a sectorized ring (116) made of material having thermal expansion coefficient multiple times not greater than that of a casing (12) made of metal alloy, where the casing supports the ring. The ring is provided with an upstream circumferential edge (120) axially engaged in an annular groove (24) of an annular attachment (26) of the casing. The annular attachment of the casing radially extends towards an upstream end of the ring, where radial clearance is determined between the casing and the ring. The ring is made of ceramic matrix composite.