TURBOMACHINE IMPROVED HIGH-PRESSURE TURBINE, ASSOCIATED GUIDE VANES SECTOR AND ASSOCIATED AIRCRAFT ENGINE

摘要

The invention relates to a novel solution for mounting a guide vane assembly for a turbomachine turbine, formed of an annular row of fixed flow-stabilizing vanes. According to the invention, the outer edge (11) of the guide vane assembly is axially supported on the extension of the external casing (5, 50) of the turbine, and the inner edge (10) of the guide vane assembly is in sliding axial connection (LG) with the extension of the internal casing (3, 30) of the turbine, the axial sliding connection (LG) allowing the inner edge (10) to be free along the motor axis while the axial stop is achieved by axial contact of the outer edge of the vane.