TURBO COMPRESSOR Russian patent published in 2019 - IPC F04D27/02 F04D29/44 

FIELD: manufacturing technology.

SUBSTANCE: invention relates to compressor building, particularly, to axial, diagonal and axial-flow compressors of gas-turbine plants. Turbo compressor comprises housing with working and guiding vanes arranged therein, in which above working vanes ends there is an above-rotor device consisting of housing and annular grid formed by ribs and slotted channels between them. Annular cavity communicating with flow part of turbo-compressor via slot channels between annular grid forming ribs is formed between housing of above-rotor device and annular grid. Body of the above-rotor device is equipped with at least one through hole for annular cavity communication with subsequent stages of the turbo-compressor. In the body of the above-rotor device there are sealing bushings. In annular cavity above annular grid there are annular segments installed with possibility of overlapping slot-type channels of annular grid. Circular slots are made on annular segments to accommodate sealing spacers arranged above ends of annular segments to overlap clearance there between. On internal surfaces of ring segments and sealing spacers there are sealing elements from plastic material. Each annular segment is provided with a hole for a threaded bushing, and the housing of the above-rotor device and the ring segments are connected to each other by means of flexible movable elements, one end of which is rigidly fixed in the threaded bushing by an uninterrupted connection, and other end is rigidly fixed in sealing bushing by one-piece connection.

EFFECT: invention enables to reduce the negative effect of the above-rotor device in operating modes at n_Pr= 0,85…1.

5 cl, 3 dwg