Abstract: An assembly including a propeller blade and a pitch adjustment system for setting the pitch of the blade. A root of the blade has a bulb and the pitch adjustment system for setting the pitch of the blade includes a cup having an upper opening; —a retaining ring, which extends around the bulb, is restricted at least in terms of axial movement towards the opening relative to the cup and has a bearing face to inhibit axial movement of the root towards the opening The pitch adjustment system being further includes a lower seat for the root to engage the cup, the seat and/or the retaining ring being mounted so as to be capable of axial translation relative to the cup by at least one clamping mechanism.

Abstract: An assembly including a propeller blade and a pitch adjustment system for setting the pitch of the blade. A root of the blade has a bulb and the pitch adjustment system for setting the pitch of the blade includes a cup having an upper opening; a retaining ring, which extends around the bulb, is restricted at least in terms of axial movement towards the opening relative to the cup and has a bearing face to inhibit axial movement of the root towards the opening The pitch adjustment system being further includes a lower seat for the root to engage the cup, the seat and/or the retaining ring being mounted so as to be capable of axial translation relative to the cup by at least one clamping mechanism.

Abstract: The invention relates to a de-icing device designed to supply de-icing air to a turbomachine separation nozzle extending along a longitudinal axis, the turbomachine comprising:—the separation nozzle which is designed to be positioned downstream from a turbomachine fan and comprises an internal casing and an external casing which form a separation between a primary flow vein for a primary stream and a secondary flow vein for a secondary stream, said streams issuing from the fan, the internal casing and the external casing defining an inter-vein space;—turbomachine guide vanes designed to be secured by screws to the internal casing such that the screws extend into the inter-vein space, the de-icing device being intended to be positioned in the inter-vein space and comprising—an air inlet;—an air outlet;—a plurality of channels extending from the air inlet toward the air outlet; the channels being arranged in relation to one another such that they are designed to extend from the air inlet toward the air outlets,

Abstract: A turbine engine compressor includes a stator featuring an annular casing and at least one annular row of variable-pitch vanes, wherein each vane comprises a radially external end having a pivot mounted in an orifice in the casing and connected by a linking member to an control ring capable of pivoting axially in relation to the casing, where the linking member comprises a first end fixed to the pivot of the vane and a second end having a pin inserted in a hole in the control ring, where at least one of the holes in the control ring serves for insertion of the pins of the linking members, is oblong in shape and extends in the circumferential direction in order to allow movement of the pin in the oblong hole, during rotation of the control ring.

Abstract: The invention relates to a turbine engine compressor, in particular of an aeroplane turboprop or turbofan, comprising a stator featuring an annular casing and at least one annular row of variable-pitch vanes, wherein each vane comprises a radially external end having a pivot mounted in an orifice in the casing and connected by a linking member to an control ring (38) capable of pivoting axially in relation to the casing, wherein said linking member comprises a first end fixed to the pivot of the vane and a second end having a pin inserted in a hole (52, 58) in the control ring (38), characterised in that one (58) at least of the holes (52, 58) in the control ring (38) serving for insertion of the pins of the linking members, is oblong in shape and extends in the circumferential direction in order to allow movement of the pin in said oblong hole (58), during rotation of the control ring (38).

Abstract: A turbomachine compressor or turbine including annular anti-wear shims mounted against hooks of a stator, each shim being substantially of channel-section defining an annular groove for engaging on a hook, the shim mounted against the downstream hook bearing axially via its middle annular wall on the stator, or on the casing, and one of its side walls includes a bearing device at its end remote from the middle annular wall for bearing against the casing or the stator, respectively, which bearing device is elastically deformable in an axial direction so as to urge the stator upstream.

Abstract: A device for guiding pivoting of variable-pitch vanes in a turbomachine, each vane having a pivot formed by a cylindrical axial shank which is guided in a cylindrical chimney of the casing and in a cylindrical orifice of a stationary element which surrounds the outside of the casing and which is centered and fixed relative thereto. The invention improves pivotal guidance of variable-pitch vanes.

Abstract: A device for guiding pivoting of variable-pitch vanes in a turbomachine, each vane having a pivot formed by a cylindrical axial shank which is guided in a cylindrical chimney of the casing and in a cylindrical orifice of a stationary element which surrounds the outside of the casing and which is centered and fixed relative thereto. The invention improves pivotal guidance of variable-pitch vanes.