Turbine engine compressor, in particular of an aeroplane turboprop or turbofan
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.
1. A turbine engine compressor comprising a stator featuring an annular casing and at least one annular row of variable-pitch vanes including:
a first vane comprising a first radially external end having a first pivot mounted in a first orifice in the casing and connected by a first linking member to a control ring capable of rotating about an axis of the casing, wherein said first linking member comprises a first end fixed to the first pivot of the first vane and a second end having a first cylindrical pin inserted in a first hole in the control ring; and
a second vane comprising a second radially external end having a second pivot mounted in a second orifice in the casing and connected by a second linking member to the control ring, wherein said second linking member comprises a third end fixed to the second pivot of the second vane and a fourth end having a second cylindrical pin inserted in a second hole in the control ring, wherein the first hole comprises a circular hole, wherein the second hole comprises an oblong hole in order to allow movement of said second cylindrical pin in said oblong hole during rotation of the control ring, wherein said oblong hole in the control ring comprises a first end located on the side of a first lateral edge of the control ring and a second end located on the side of a second lateral edge of the control ring, and wherein both ends are connected by a curved joining area featuring an inflection point.
2. A turbine engine comprising at least one turbine engine compressor according to claim 1 .