Technique and blade arrangement to reduce the serpentine motion of a mass particle flowing through a turbomachine

Claim 1

A multi-stage axial-flow turbo-machine, each stage thereof comprising a row of fixed blades having a concave curved configuration and an adjacent row oF movable blades having an oppositely concave curved configuration, the leading and trailing edges of said fixed blades of each stage extending along radial lines as viewed in the direction of the axis, the leading edges of said movable blades of each stage being inclined at a positive angle with respect to a radial line whereby the concave side of each movable blade faces slightly towards the axis, and the trailing edges of said movable blades of each stage being inclined at the same but negative angle with respect to a radial line, thereby to effect a reduction in the serpentine motion of a mass particle as it passes through successive stages of said multi-stage turbo-machine and which is caused by the alternating peripheral component of the flow velocity of the particle path projected cylindrically on a meridonal plane.