Abstract: An angular pitch control ring (8) of stator vanes (2), the rotations of which are controlled by a mechanism (6) applying a thrust tangent to the ring (8), is also moved in translation when it is displaced, making it touch the stator (2). According to the invention, one lateral region (13) on one side of the mechanism (6) is constructed to be stiffer than the other region to take account of the larger forces that the mechanism (6) must apply in a direction of movement. Application to turbomachines.

Abstract: A turbine-engine compressor, in particular for an aircraft turboprop engine or turbojet engine, comprising an annular casing and at least one annular row of variable-pitch blades, each blade comprising a radially external end comprising a pivot mounted in an orifice in the casing and connected by a link to a control ring able to pivot axially about its axis with respect to the casing. Each link comprises a first end fixed to the pivot of the blade and a second end mounted so as to be able to pivot on the control ring. The pivot axes of first and second links on the control ring are offset from each other along the axis of the compressor, the second end of the second link being mounted on the ring by a connecting member, allowing a connection of the sliding or annular linear pivot type.

Abstract: An angular pitch control ring (8) of stator vanes (2), the rotations of which are controlled by a mechanism (6) applying a thrust tangent to the ring (8), is also moved in translation when it is displaced, making it touch the stator (2). According to the invention, one lateral region (13) on one side of the mechanism (6) is constructed to be stiffer than the other region to take account of the larger forces that the mechanism (6) must apply in a direction of movement. Application to turbomachines.

Abstract: A turbine-engine compressor, in particular for an aircraft turboprop engine or turbojet engine, comprising an annular casing and at least one annular row of variable-pitch blades, each blade comprising a radially external end comprising a pivot mounted in an orifice in the casing and connected by a link to a control ring able to pivot axially about its axis with respect to the casing. Each link comprises a first end fixed to the pivot of the blade and a second end mounted so as to be able to pivot on the control ring. The pivot axes of first and second links on the control ring are offset from each other along the axis of the compressor, the second end of the second link being mounted on the ring by a connecting member, allowing a connection of the sliding or annular linear pivot type.