An Axial Flow Research Compressor Facility Designed for Flow Measurement in Rotor Passages

Abstract

An axial-flow research compressor facility, which is designed for relative flow measurement, is described in this paper. The facility has a rotating-probe traverse mechanism which is capable of traversing hot-wire, pilot and other probes at 0.09 deg intervals across the rotor blade passage. The data transmission system includes rotating transducers, pressure transfer device, ten-channel mercury slip-ring unit, scanivalve, etc. The instrumentation includes on-line data processing capability. A brief description of probes used as well as some typical data on the rotor blade static pressure, rotor endwall flow, and rotor wake characteristics are given in the paper.