TURBO COMPRESSOR WITH ABOVE-ROTOR DEVICE Russian patent published in 2020 - IPC F01D17/18 F04D27/02 

FIELD: power machine building.

SUBSTANCE: invention relates to power engineering and can be used in axial turbochargers for gas turbine engines and installations. Turbo compressor with above-rotor device comprises housing with above-rotor spacer and flow path. Impeller with blades is installed in the flow path inside the above-rotor spacer to form inter-blade flow channels. Circular shell ring of the above-rotor device covers the above-rotor spacer to form an annular cavity interconnected with inter-fluid flow channels by inlet holes, and with flow path-outlet openings. Control system is connected with working parameters sensors and actuators of working elements. Inlet openings of the annular cavity are made in the form of a row of slots in the above-rotor spacer of housing located in the zone of the inter-blade flow channels upstream the plane of outlet edges of the impeller blades. Outlets of annular cavity have locking elements with drive connected to control system and are made in the form of at least two rows of slit-like slots in above-rotor spacer, located in flow path zone upstream of plane of inlet edges of impeller blades. Walls of slit-like slots of outlet holes are made inclined relative to the radius of the above-rotor spacer in the downstream direction in the flow path. Each shut-off element is made in form of arc-shaped segment with seals on inner surface and tie-rod connected with drive, and is located in annular cavity of above-rotor device with possibility of overlapping by seals of slit-like slots of outlet holes. Locking elements drive is made in the form of a rotary carrier installed on external surface of annular shell of the above-rotor device with the possibility of limited rotary movement. Carrier is equipped with profiled grooves by number of locking elements and slides located in profiled slots and rigidly connected with rods of locking elements.

EFFECT: invention allows increasing operating efficiency of turbo-compressor at fractional modes at guaranteed provision of optimum value of hydrodynamic stability margin by optimization of angle of attack of air flow at input of impeller.

1 cl, 6 dwg