1972-02-01

Design and Development of a Small Highly Loaded, Two-Stage, Transonic Axial Compressor 720712

A small, two-stage, transonic axial compressor was selected for a 5 lb/s airflow, 0.46 lb/hp · h, sfc turboshaft engine at 2500 F turbine-inlet gas temperature. The axial compressor was configured to supercharge a single-stage centrifugal compressor to provide an overall axial/centrifugal pressure ratio of 16:1.
The axial compressor was designed, fabricated, and developed through rig testing. On final test, a pressure ratio of 3.1:1 was demonstrated at 80% efficiency with 10% surge margin.

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