COMPRESSOR AND GAS-TURBINE ENGINE WITH OPTIMISED EFFICIENCY Russian patent published in 2015 - IPC F04D29/52 F04D29/68 F01D11/08 

FIELD: motors and pumps.

SUBSTANCE: axial compressor (10) of the gas-turbine engine comprises a housing (12) which has an inner wall forming an aerodynamic base surface for the channel for the passage of gas, and in which an impeller (14) is mounted, having radial blades (18). The annular recess is formed on the inner wall of the housing. The recess shape in the direction away from the area located upstream to the area located downstream, is determined by three surfaces, the surface located upstream, respectively, the middle surface and the surface located downstream, and the said surfaces are substantially conical. The surface located upstream extends in the direction in the upstream direction from the front edges of the blades. The middle surface is substantially parallel to the said aerodynamic base surface. The surface located downstream extends in the downstream direction, at least until the rear edges of the blades. Connection area between the middle surface and the surface located downstream is located at a distance from the front edges of the blades (18) ranging from 30% to 80%, and preferably in the range from 50% to 65% of the length of the blades (18) in the axial direction.

EFFECT: achievement of decrease in turbulence and increase in the efficiency of the compressor.

13 cl, 5 dwg