Ring for controlling a stage of variable-setting vanes for a turbine engine
a technology of variable pitch and control ring, which is applied in the direction of machines/engines, mechanical apparatus, liquid fuel engines, etc., can solve the problems of reducing the service life of the pad, destroying the threaded connection, and affecting the accuracy of the pitch, so as to limit the risk of damaging the ring and limit the direct transmission of torque
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[0033]FIG. 1 is a schematic axial sectional view of part of a high-pressure compressor 10 of a turbine engine, in particular an aircraft turbine engine, having a plurality of stages, each stage comprising an annular row of movable vanes 12 supported by the rotor (not shown) of the turbine engine and an annular row of fixed vanes 14 forming rectifiers supported by a casing 16 of the stator of the turbine engine, the angular orientation of the vanes 14 being adjustable in order to optimise the gas flow in the compressor 10.
[0034]Each vane 14 comprises a blade 18 and a radially outer cylindrical pivot 20 connected, by a disc or “plate”22 extending perpendicularly to the axis 24 of the vane, in a corresponding housing 26 of the casing 16. The radially inner surface 28 of the disc is aligned with the inner wall 30 of the casing so as not to oppose the gas flow.
[0035]The cylindrical pivot 20 of each vane 14 extends inside a radial cylindrical chamber 32 of the casing 16 and its radially o...
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