Axial-flow turbo-compressor stator blade - has profile angle to peripheral vector smaller at blade tip and root than at blade centre

摘要

The arrangement is intended for a turbo-compressor of the type having at least one stage comprising a rotor disc and a bladed stator disc whereby the diameter gradually increases in the direction of flow. Each stator blade of the same stage has the blade angle (alpha) relative to the peripheral velocity (u) varying along the radial length of the blade. The arrangement is such that the blade angle seen in the cross-sections at the top and the root of the blade at right angles to its longitudinal axis is smaller than the angle seen in the profile (9) section (c-c) in the central area of the blade.