Turbine engine compressor, in particular for an aircraft turboprop engine or turbojet engine

A turbine-engine compressor, extending along a longitudinal axis, 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, each blade connected by a link to a control ring able to pivot axially with respect to the casing, each link comprising a first end fixed to the pivot of the blade and a second end mounted pivotally on the control ring, wherein pivot axes of first and second links of the at least one annular row of variable-pitch blades connected to the control ring are offset from each other along the longitudinal axis of the compressor, the second end of the second link being mounted so as to be able to slide in a recess with a complementary shape in a connecting member, the connecting member being mounted so as to be able to pivot with respect to the control ring about a radial axis so as to form a sliding pivot type connection between the second link and the control ring, wherein the recess is a hole passing through said connecting member.