Patent ID: 7600965
Filing Date: 2009-10-13
Classification: F01D,F02C,F04D

Abstract:
1. Flow structure for a turbocompressor of a gas turbine, having at least one ring chamber which is arranged concentrically with respect to an axis of the turbocompressor in an area of free blade/vane ends of a rotor blade ring/vane ring and is adjacent radially to a main flow channel, whereby the ring chamber is bordered by a front upstream wall, a rear downstream wall and a wall extending essentially axially, whereby baffle elements are arranged in the ring chamber and whereby the ring chamber permits flow penetration in a circumferential direction, wherein in the area of at least one of the walls, at least one opening is provided which permits flow penetration out of the ring chamber, wherein there is at least one compressor chamber to receive this emerging flow, and wherein the baffle elements on one end border flow channels running mainly in an axial direction and on another end they border at least one flow channel running in the circumferential direction, whereby the opening or each opening is provided on an upstream end of the flow channels running in the axial direction in the wall extending essentially axially.