Turbo compressor having a surge suppressing arrangement.

摘要

A series of airfoil cross-section equidistantly spaced normally parallel vanes (20A-E) are disposed linearly across the mouth of an induction housing port (14) which lies on an essentially flat plane non-intersecting with the axis of rotation of a turbo compressor wheel (10). A control mechanism moves the vanes (20A-E) upon the compressor tending to surge so that each of the vanes is moved through an angle different from the preceeding one, whereby the airflows passing between the vanes are deflected and converge upstream of the compressor wheel (10) and swirl theretoward in the form of a single flow to impinge on the blades (18) of the wheel (10) with a uniform and reduced angle of incidence.