MECHANISM OF REGULATION OF PADDLES OF THE GUIDE DEVICE OF THE STATOR MULTISTAGE COMPRESSOR OF A GAS TURBINE ENGINE Russian patent published in 2018 - IPC F01D17/16 F04D29/56 

FIELD: engines and pumps.

SUBSTANCE: invention relates to the field of aircraft engine construction, in particular to adjustable guide vanes of the stator of multi-stage compressors of multi-mode aircraft gas turbine engines. Mechanism for regulating the blades of the stator vanes of a multi-stage compressor of a gas turbine engine, mounted on the compressor housing, includes guide vanes located inside the housing with rotary vanes, on the shanks of which there are fixed pivot levers that are pivotally connected with synchronizing rings and regulating rods, a rail connected to the power drive of the rotary blades. Rail is connected directly to the rods and hinged to the compressor housing. Length of the pivoting levers at each stage of the guide vane is selected based on the radius of the synchronizing ring at the points of attachment of the ends of the levers, the distance from the point of attachment of the rail to the body to the plane in which the axes of the shanks of the pivoting vanes of the corresponding stage are located, the distance from the axis of rotation of the synchronizing ring to the point of attachment of thrust to the synchronizing ring, the angle of rotation of the blades and the angle of rotation of the rail between their extreme positions according to the ratio protected by the present invention. Rail is connected to the power drive of the rotary blades through a link and a shaft with levers.

EFFECT: invention allows to increase the reliability and efficiency of the compressor, to reduce the weight and complexity of manufacturing the device, to reduce the dimensions of the mechanism for regulating the rotary blades.

1 cl, 3 dwg