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Aerodynamic test of ﬁxed-geometry and adjustable additional blades in axial-ﬂow compressor stage

Nezym V

Transactions of the Institute of Fluid-Flow Machinery

2016

nr 132

17--28

An application of a ﬂow control equipment in a compressor has been found to give a substantial improvement in the compressor stable operational range. The experimental investigation has been performed with additional blades (of a ﬁxed-geometry and adjustable types) in an axialﬂow compressor stage. The ﬁxed-geometry type additional blades were installed in the blade-toblade duct of a rotor hub and in hub and tip zones of a guide vane. Total pressure diagrams for the stage embodiments (with and without the ﬁxed-geometry additional blades) are presented. The adjustable tip additional blades were tested in two conﬁgurations, along the full length of the rotor blade chord projection, and located only in the inlet part of the rotor blade. This experimental investigation revealed a special importance of the inlet rotor part in rotating stall occurring.