AXIAL-FLOW COMPRESSOR Russian patent published in 2016 - IPC F04D29/68 

FIELD: engines and pumps.

SUBSTANCE: invention relates to aircraft engine construction and can be used in axial compressors for perfection of aerodynamics of their flow section owing to the flow control nearby the impeller housing. A circular chamber is arranged in the housing wall of at least one stage above the impeller blades, feed channels being uniformly made from the inner side of the housing of said chamber over the entire diameter. Said channels provide the blow-out of working fluid from said circular chamber into the axial compressor radial groove at angle φ of 1-5 degrees in vertical plane relative to the housing inner surface, in horizontal plane at angle ψ relative to the front of grates of the profiles. Working fluid is fed into said circular chamber from the compressor last stages, or from whatever other source via appropriate feeder. The location of blow-out points over the blade chord and the number of feed channels for every stage define the conditions of minimization of their quantity and of working fluid flow rate given the required magnitude and direction of absolute rate correspond to the ideal design flow. The feed channels can be arranged directly in the axial compressor housing above the impeller while the circular chamber and working fluid feeder are located above the housing via u-like adapter arranged thereat.

EFFECT: higher head, efficiency and margin of gas-dynamic stability.

2 cl, 5 dwg