TURBOMACHINE OVERROTOR DEVICE

摘要

FIELD: power engineering. SUBSTANCE: invention relates to inlet stages of axial flow compressors designed for power plants and gas transfer stations. Proposed device contains ring duct wall with space outside the duct and rotor blade rim. Radial clearance is formed between peripheral ends of blades of blade rim. Holes are made in duct wall with tilting to generatrix to place through flow duct in communication with space outside the duct. Holes in duct wall are made in form of ring row of ring channels orientated in projection to axis of rotation of rotor along chords at periphery of rotor blades. Edges of slot channels located above along flow coincide with leading edges of rotor blades. Duct wall is made solid from leading edges of rotor blades above in direction of flow. Length of space outside the duct along axis of rotation of rotor is equal to axial distance between leading and trailing edges at periphery of rotor blades, and volume of slot channels is from 0.08 to 0.25 of volume of space outside the duct. EFFECT: reduced aerodynamic noise and increased efficiency of turbomachine compressor at preservation of gas dynamic stability. 5 cl, 4 dwg