AXIAL MULTISTAGE COMPRESSOR GUIDE VANES TURNING MECHANISM Russian patent published in 2024 - IPC F01D17/16 F04D29/56 

FIELD: engines.

SUBSTANCE: invention relates to aircraft engine building and gas turbine engines for ground application, namely to control of axial multistage compressor. Turning mechanism includes a compressor stator, synchronizing rings, adjusting rods, control levers and hinges, blades of guide vanes with possibility of their rotation; at that, levers are fixed on blades of the guide vanes. Additionally, there are two modules of control mechanisms installed on the compressor stator symmetrically relative to the motor axis X, including brackets with power drives fixed on them, with IGV and GV control levers fixed in brackets from the first to the fourth stages, as well as driving rods, lever rods and adjustment rods. Device comprises repetition arms, drive arms, with possibility of connection to leverage of control levers GV by tie-rods of levers and hinges. IGV and GV control levers from the first to the fourth stages move the synchronizing rings relative to the compressor stator in circumferential and axial directions. When the synchronizing rings move, the levers GV with the blades IGV and GV are turned from the first to the fourth stages. Between turning of blades IGV and turning of blades GV from first to fourth stage there are ratios, at which rotation of blades IGV, which is proportional to movement of power drives, is accompanied by rotation of blades GV from the first to fourth stages, which is not proportional to rotation of IGV blades.

EFFECT: proposed invention increases efficiency and gas-dynamic stability margins of axial multistage compressor at operating and throttle modes of engine operation, increases service life and reliability of aircraft engine.

6 cl, 3 dwg