Abstract: Disclosed is a compressor of a dual-flow aircraft turboshaft engine extending longitudinally along an axis X, the compressor comprising a low-pressure compressor, a high-pressure compressor and an intermediate casing axially connecting the low-pressure compressor and the high-pressure compressor, the high-pressure compressor comprising an inlet guide stator comprising a retaining ring, an outer high-pressure compressor casing and a plurality of vanes, the compressor comprising an immobilising device comprising at least one first member secured to the intermediate casing and at least one second member secured to the retaining ring and configured to cooperate with the first member in order to prevent tangential movement while allowing axial movement and radial movement of the retaining ring relative to the intermediate casing according to the axis X.

Abstract: Disclosed is a compressor of a dual-flow aircraft turboshaft engine extending longitudinally along an axis X, the compressor comprising a low-pressure compressor, a high-pressure compressor and an intermediate casing axially connecting the low-pressure compressor and the high-pressure compressor, the high-pressure compressor comprising an inlet guide stator comprising a retaining ring, an outer high-pressure compressor casing and a plurality of vanes, the compressor comprising an immobilising device comprising at least one first member secured to the intermediate casing and at least one second member secured to the retaining ring and configured to cooperate with the first member in order to prevent tangential movement while allowing axial movement and radial movement of the retaining ring relative to the intermediate casing according to the axis X.

Abstract: Variable-pitch blade control ring (44) for a turbine engine, including an annular body (42) configured to be mounted so as to be rotatable about an annular casing (16) of the turbine engine. The body links to levers (34) for connecting to the vanes. The ring has a mechanism for guiding in an axial and/or helical direction, supported by the body. The mechanism includes at least one substantially radial finger (60, 62) for axial abutment on at least one first surface (72, 74) of the casing and for sliding on the surface.

Abstract: An assembly for controlling variable pitch vanes in a turbine engine, the assembly comprising an actuating ring surrounding a casing of the turbine engine and connected by rods to variable pitch vanes. The actuating ring is configured to rotate around the casing. The assembly further includes a passive element including a first end sliding connected to a second end. The first end is connected by a sliding pivoting link on the actuating ring, and the second end is connected by a ball-joint link to the casing.

Abstract: Variable-pitch blade control ring (44) for a turbine engine, comprising an annular body (42) configured to be mounted so as to be rotatable about an annular casing (16) of the turbine engine, said body comprising means (46) for linking to levers (34) for connecting to said vanes, characterised in that said ring further comprises first means (60, 62, 64) for guiding in an axial and/or helical direction, which means are supported by said body and comprise at least one substantially radial finger (60, 62) comprising means (62) for axial abutment on at least one first surface (72, 74) of said casing and for sliding on said surface.