Abstract: A stator blades of an axial turbomachine intended to be fitted on a ferrule in an annular row of identical blades. Each blade includes a platform with opposed lateral edges and a screw to the ferrule. The contour of the platform has, at each of the lateral edges, an angular profile designed to mate with the contiguous edge of the platform of an adjacent blade. This feature enables the angular position or pitch of the blade to be set. In a blade row fixed on a stator, mechanical clearances J1, J2, J3 and the fixation screws cause an average angular orientation error. The blades are made with a compensatory angle to offset the angular orientation error.

Abstract: The invention relates to a mold for injecting a layer of abradable material, such as silicone, inside an inner shroud of an axial-flow turbomachine. The mold comprises a circular wall or tubular wall extending axially and two annular walls extending radially outwardly from the axial ends of the axial wall. Each radial wall of the mold comprises an annular hook in contact with the outer surface of the shroud so as to hold the mold against the shroud. The injection pressure presses the hooks against the shroud, providing a seal. The walls form an annular molding cavity inside the inner shroud in combination with the inner shroud. The invention also relates to a method for molding an abradable layer inside the shroud with the aid of the mold. The latter is deformed by spreading apart the hooks so as to fit over the shroud.

Abstract: The invention relates to a mould for injecting a layer of abradable material, such as silicone, inside an inner shroud of an axial-flow turbomachine. The mould comprises a circular wall or tubular wall extending axially and two annular walls extending radially outwardly from the axial ends of the axial wall. Each radial wall of the mould comprises an annular hook in contact with the outer surface of the shroud so as to hold the mould against the shroud. The injection pressure presses the hooks against the shroud, providing a seal. The walls form an annular moulding cavity inside the inner shroud in combination with the inner shroud. The invention also relates to a method for moulding an abradable layer inside the shroud with the aid of the mould. The latter is deformed by spreading apart the hooks so as to fit over the shroud.

Abstract: The present application relates to the stator blades of an axial turbomachine intended to be fitted on a ferrule in an annular row of identical blades. Each blade includes a platform with opposed lateral edges and a means of attachment to the ferrule. The contour of the platform has, at each of the lateral edges, an angular profile designed to mate with the contiguous edge of the platform of an adjacent blade. This feature enables the angular position or pitch of the blade to be set. The present application also relates to a stator comprising the blade row. Mechanical clearances J1, J2 and J3 and the means of clamping cause an average angular orientation error. The blades are made with a compensatory angle to offset the angular orientation error.

Abstract: An assembly for a stator stage of a turbomachine is disclosed. The assembly includes: an outer shroud presenting a series of openings for mounting each stationary vane by welding between the edge of an opening and the outline of the platform of the vane, the outline of the outer segment of an opening surrounding, in radial projection, the outline of the inner segment thereof, the shroud not having any other holes; and at least one stationary vane with its top including a non-pierced platform received in one of the openings prior to the welding step, such that an inside face of the platform bears against a bearing face of the shroud, the outline of the platform presenting a shape that is identical to the shape of the outline of the opening.

Abstract: The invention relates to an assembly for a stator stage of a turbomachine, the assembly comprising: an outer shroud presenting a series of openings for mounting each stationary vane by welding between the edge of an opening and the outline of the platform of the vane, the outline of the outer segment of an opening surrounding, in radial projection, the outline of the inner segment thereof, the shroud not having any other holes; and at least one stationary vane with its top including a non-pierced platform received in one of said openings prior to the welding step, such that an inside face of the platform bears against a bearing face of the shroud, the outline of the platform presenting a shape that is identical to the shape of the outline of the opening. The invention is applicable to the stator stage of an axial compressor or a turbine of a turbomachine.