Abstract: The invention relates to an axial compressor stator for a gas turbine, the stator having a rigid, external, annular frame and axially juxtaposed rings configured within the frame and bearing annuli of stationary vanes. The rings are defined by arcuate segments affixed to the frame. The inside walls of the arcuate segments externally define the aerodynamic conduit for the compressed gaseous fluid. The arcuate segments are brazed segments that include a honeycomb component sandwiched between an inner sheetmetal bounding the aerodynamic conduit and an outer sheetmetal. The outer sheetmetal solely connects the arcuate segments to the frame.

Abstract: The invention relates to an axial compressor stator for a gas turbine, said stator comprising a rigid, external, annular frame (2), furthermore axially juxtaposed rings (4a, 4b, 4c) configured within the frame (2) and bearing annuli of stationary vanes (5), said rings being constituted by arcuate segments (7) affixed to the frame, the inside walls of said arcuate segments externally defining the aerodynamic conduit for the compressed gaseous fluid, and this invention is characterized in that the arcuate segments (2) are brazed segments consisting of a honeycomb component (8) sandwiched between an inner sheetmetal (10) bounding the aerodynamic conduit and an outer sheetmetal (9), and in that the connection to the frame (2) is solely implemented by the outer sheetmetal (9).

Abstract: A turbine engine stator has a metal casing surrounding an envelope carrying bearings for the pivots of pivoting blades. A control mechanism for setting the position of the blades includes a radial spindle to which are transmitted the thrust forces of the gases, the envelope being advantageously formed from angular sectors of axially juxtaposed flanges or rings and which are not loaded. Therefore, the bearings are not subject to wear giving rise to gas leaks and efficiency losses. Advantageously, the envelope is made from a composite material.