EFFECT OF STATOR BLADE ORIENTATION ON THE PERFORMANCE OF AN AXIAL FLOW COMPRESSOR.
Abstract
A mean streamline analysis of the effect of stator blade orientation on the performance of an axial flow compressor was performed by means of a computer program. Measurements were made on a 3-stage axial flow compressor at six stator stagger angles between 23.8 deg. and 44.3 deg. for a fixed orientation of the rotor blades. Maximum efficiency and pressure ratio were measured at a stator stagger angle of 31.8 deg. Results at other blade settings showed that by varying stator stagger angle with flow rate optimum efficiencies and pressure ratios can be achieved over a wide range of operating conditions. The results of the analysis were compared with the measured results. Suggestions are made for improving the manner of adapting cascade test data to performance predictions. By applying a non-dimensional deflection coefficient it could be shown that minimum work input corresponded to maximum efficiency. The test compressor has a tip diameter of 36 in. and a hub/tip ratio of 0.6. The blading tested is of the free-vortex type with a design degree of reaction of 0.5. Tip speed was about 185 ft/sec. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1967
- Accession Number
- AD0832901
Entities
People
- Bruce Cameron Marshall
Organizations
- Naval Postgraduate School