Abstract
A high duty research compressor has been manufactured which is large enough (34-in first rotor tip diameter) to yield valid results from traverses between the blade rows. The compressor is designed to operate at a first rotor tip speed of 1390 ft/s, produce a pressure ratio of 1·88, and pass a flow of 42·3 lb/s ft2 annulus area. A brief outline of the design method is given and the measured overall performance characteristics are presented. The results from the inter-blade row traverses are compared with the design profiles as predicted by axisymmetric flow calculations. Analysis of the traverse data has produced information on blockage factors, incidence, deviation, and pressure loss which will be useful in the design of other transonic compressors.
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