A low speed centrifugal compressor facility is described. The purpose of this facility is to obtain detailed flow field measurements for computational fluid dynamic code assessment and flow physics modelling in support of Army and NASA efforts to advanced small gas turbine engine technology. The facility is heavily instrumented with pressure and temperature probes, both in the stationary and rotating frames of reference, and has provisions for flow visualization and ...
A two-stage, baseline configuration, low-speed, axial-flow research compressor was designed, built and tested at design flow. The design, fabrication and data acquisition and reduction details are described. Time- averaged, spatially detailed and overall flow and aerodynamic performance data for design flow operation of the compressor are presented and discussed. (Author)
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