METHOD OF DISPERSION OF GAS TURBINE ENGINE COMPRESSION STAGE AND STAGE OF DISPERSION FOR APPLICATION Russian patent published in 2016 - IPC F04D29/44 

FIELD: machine building.

SUBSTANCE: invention can be used in centrifugal compressors. Disclosed are nonaxisymmetric shapes in the flow direction and in tangential direction. According to the implementation version, the stage of dispersion of radial or combined centrifugal axial compressor of gas turbine engine comprises a wheel formed by two disks (9), between which in the centrifugal manner or inclined from the centre to the periphery the gaseous substance flows. Grid blades (60) are located between disks (9) to direct the gaseous substance movement between front edges (6a) of those blades (60) from the centre side and rear edges from the periphery side. At least one of disks (9) has inboard side (9i) containing at least zone (Z1, Z2) with alternating curvature with recess (91) and convexity (92), between two adjacent blades (60), at least in one of two essentially perpendicular directions, namely in the direction of flow (F) along blades (60) and in the inter-blade tangential direction.

EFFECT: invention is aimed at implementation of the air flow by installation of a disc of optimised shape.

9 cl, 9 dwg