Patent ID: 8858169
Filing Date: 2014-10-14
Classification: F01D,F02C,F05D,Y02T

Abstract:
1. A high-pressure turbine of a turbomachine, comprising: at least one guide vane assembly formed by an annular row of stationary flow-stabilizing vanes and a vaned rotor rotatingly mounted downstream of the guide vane assembly, the guide vane assembly including an outer edge and an inner edge; wherein the outer edge bears axially against a line of an external casing of the turbine and the inner edge is in axial sliding connection with a line of an internal casing of the turbine, the axial sliding connection allowing the inner edge to be free along the engine axis with an axial stop formed by an axial bearing of the outer edge of the vane, wherein the line of the internal casing comprises an annular member including a plurality of axial grooves, and wherein each inner guide vane edge comprises extensions that extend towards the line of the internal casing and that are configured in hooks, one group of which is oriented in the upstream direction of the turbine and the other group of which is oriented in the downstream direction of the turbine, the hooks being interlocked in a pair of flanges fixed relative to each other, the axial sliding connection including a plurality of pins that extend radially from at least one of the flanges towards the inside of the turbine and that are housed individually in one of the axial grooves of the annular member of the line of the internal casing.