High pressure turbine stage for e.g. turbojet engine of airplane, has split annular sealing sheet whose circumferential end parts overlap at cold and hot states, where sheet and sectorized ring are made of ceramic matrix composite material

摘要

The stage has a radial impeller rotating inside a sectorized ring carried by a casing of a turbine. The impeller includes a circumferential downstream edge anchored on an annular tab of the casing by a C-shaped lock. The lock comprises internal and external branches connected with one another by a radial wall. Circumferential end parts (54, 56) of a split annular sealing sheet (52) i.e. strip, overlap at cold and hot states, where the sheet and the ring are made of ceramic matrix composite material. The sheet is mounted between the ring and the internal branch of the lock.