TURBOMACHINE AXIAL-FLOW COMPRESSOR Russian patent published in 2007 - IPC F04D29/58 

FIELD: mechanical engineering; turbomachine.

SUBSTANCE: invention relates to axial-flow compressor furnished with centripetal air takeoff device 2 in passage part 5 of compressor. Said air is designed for cooling of turbine. Compressor has two rims of working blades 4, 7 which pass radially outwards to periphery of two sequential disks 3, 6 connected by outer shell 9 provided with holes 14, and rim of fixed straightening blades 8 arranged in passage part 5 between two rims of working blades. These holes serve as air inlets of said air intake device and they open in ring groove 12 provided under clearance 13 separating inner flanges 11 of straightening blades 8 from rim of inlet disk. Said ring groove communicates with passage part through said clearance. Ring groove 12 is furnished with fixed guides 20 providing turbulent centripetal motion of air circulating in ring groove 12 in direction of rotation of compressor to reduce relative velocity of air getting into holes 14 relative to said rotating holes. Guides are provided with blade sections fastened under inner flanges 11 of straightening blades 8.

EFFECT: improved cooling of compressor.

6 cl, 6 dwg