Abstract: The invention relates to a turbine engine blade, particularly made of composite material, including: on the one hand, an airfoil (10) which exhibits: a leading edge (12), a trailing edge (14) opposite to the leading edge (12), intrados (16) and extrados (18) lateral walls which connect the leading edge (12) to the trailing edge (14), et on the other hand, a structural reinforcement (20) including a base (24) extending into two fins (26, 28) and designed to be applied to the leading edge (12) and the lateral walls (16, 18) of the airfoil (10), characterized in that the fins (26, 28) of the structural reinforcement (20) and/or the lateral walls (16, 18) of the airfoil (10) are shaped to maintain an assembly space (30) with nonzero thickness between at least one of the fins (26, 28) and the airfoil (10) when the structural reinforcement (20) is in place on the airfoil (10), said assembly space (30) extending from a free end (27, 29) of said fin (26, 28) toward the base (24) of the structural reinforcement

Abstract: A metal annular casing (16) for a turbine engine compressor, the casing having at least one annular row of radial chimneys for receiving outer cylindrical pivots of variable-pitch vanes, together with an outer cylindrical centering track (28) that is continuous or interrupted and against which runners carried by an annular ring for controlling the pitch of the vanes are to come to bear, the casing being characterized in that the track is formed by blocks (30) of plastics material fitted onto the casing and that are fastened or held on the casing.

Abstract: A variable-pitch vane for a stator stage includes an active part of the vane either side of which are positioned a radially inner platform and a radially outer platform, where the active part of the vane, which has a surface forming a convex surface, and a surface forming a concave surface, separate the platform into a part positioned on the convex side and a part positioned on the concave side. Seen along the direction of the vane's axis of rotation, the part has an outer outline superimposed on a circle, at the distance of which, and inside which, is at least a part of the outer outline of the part of the platform.

Abstract: The invention relates to a turbine engine blade, particularly made of composite material, including: on the one hand, an airfoil (10) which exhibits: a leading edge (12), a trailing edge (14) opposite to the leading edge (12), intrados (16) and extrados (18) lateral walls which connect the leading edge (12) to the trailing edge (14), et on the other hand, a structural reinforcement (20) including a base (24) extending into two fins (26, 28) and designed to be applied to the leading edge (12) and the lateral walls (16, 18) of the airfoil (10), characterized in that the fins (26, 28) of the structural reinforcement (20) and/or the lateral walls (16, 18) of the airfoil (10) are shaped to maintain an assembly space (30) with nonzero thickness between at least one of the fins (26, 28) and the airfoil (10) when the structural reinforcement (20) is in place on the airfoil (10), said assembly space (30) extending from a free end (27, 29) of said fin (26, 28) toward the base (24) of the structural reinforcement

Abstract: A variable-pitch vane for a stator stage including includes an active part of the vane either side of which are positioned a radially inner platform and a radially outer platform, where the active part of the vane, which has a surface forming a convex surface, and a surface forming a concave surface, separate the platform into a part positioned on the convex side and a part positioned on the concave side. Seen along the direction of the vane's axis of rotation, the part has an outer outline superimposed on a circle, at the distance of which, and inside which, is at least a part of the outer outline of the part of the platform.

Abstract: A gas turbine engine includes at least one compressor stage with an inner ring under variable angle stator vanes including axial keys for centering the inner ring with respect to the stator vanes, and including at least one sealing member support mounted on the inner ring. The keys include a transverse groove cooperating with a radial rib arranged transverse to the engine axis on the periphery of the support for the sealing member.

Abstract: The present invention concerns a gas turbine engine comprising at least one compressor stage with an inner ring under variable angle stator vanes comprising axial keys for centring said inner ring with respect to said stator vanes, and comprising at least one sealing member support mounted on the inner ring. It is characterized by the fact that said keys comprise a transverse groove cooperating with a radial rib arranged transverse to the engine axis on the periphery of the support for the sealing member.