Centrifugal compressor for radial-flow turbine - has large mach number flow in blade channels to prevent shock waves

摘要

The compressor comprises an impeller and a diffuser with circumferential blades (vanes) of constant thickness. Between the entrance edge of each blade and its centre in a radial direction the angle between the pitch line in the longitudinal section of each blade and the tangent line to an imaginary circle drawn through any point of the pitch line from the centre of the impeller axis of rotation is equal to the entrance angle of the blades. In the remaining zone of the blade this angle varies according to a quadratic parabola. Each pair of adjacent blades are of different length.