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: The invention relates to a wide-vectoring, axisymmetric turbojet-engine exhaust nozzle including vectoring structure (12) supporting a plurality of converging flaps (21). The vectoring structure is mounted on the downstream end of an exhaust housing (2) by means of an intermediate ring (9) which is pivotable about a first axis relative to the exhaust housing (2) and further about a second axis perpendicular to the first axis and relative to the vectoring structure (12). The converging flaps (21) hinge on the downstream end of the vectoring structure (12). A single drive ring (27) controlled by three linear actuators (28) and linked by linkrods (24) to the converging flaps (21) controls the tipping of the vectoring structure (12) and the kinematics of the flaps (21).