GUIDE STAGE OF COMPRESSOR OF GAS-TURBINE ENGINE WITH BLADES WITH VARIABLE SETTING ANGLE, AND GAS-TURBINE ENGINE Russian patent published in 2013 - IPC F01D17/16 F04D29/56 F01D9/02 

FIELD: engines and pumps.

SUBSTANCE: guide stage of a gas-turbine engine compressor includes a row of blades with a variable setting angle. Each blade includes a bucket, an external cylindrical trunnion being a blade rotation axis and entering a seat of an external casing, and an internal cylindrical trunnion installed in a mounting place of the inner ring. The internal trunnion of each blade is arranged parallel to the blade rotation axis and at some distance from that axis and installed in the mounting seat of the ring by means of a ball hinge system. The hinge system includes a ball coupling put on the blade internal trunnion and installed into the ring mounting place. Ball coupling includes an internal element installed with possibility of axial shift to the side on the blade internal trunnion, and an external element entering the ring mounting seat. External element includes an external circular projection meant for arrangement between a radially internal end of the blade bucket and the annular projection of the inner ring.

EFFECT: invention allows providing the possibility of axial movement of an inner ring for control of a labyrinth seal located on it.

6 cl, 4 dwg