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.
Citation: Davis, J., "Design and Development of a Small Highly Loaded, Two-Stage, Transonic Axial Compressor," SAE Technical Paper 720712, 1972, https://doi.org/10.4271/720712. Download Citation
Author(s):
J. V. Davis
Pages: 16
Event:
National Farm, Construction, Industrial Machinery, Powerplant Meeting
ISSN:
0148-7191
e-ISSN:
2688-3627
Related Topics:
Compressors
Pressure
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