Single-Stage Axial Compressor Stator Redesign Investigation
Abstract
The report describes the results of a program to redesign the exit stators of a 2.8:1 pressure ratio supersonic axial compressor, and to fabricate and test the redesigned stators to evaluate the effect of the redesign on the overall stage performance. This compressor is intended to serve as a boost stage in axial centrifugal compressors with overall pressure ratios of 16:1 for small gas turbine engines. The redesign was undertaken to provide an essentially cylindrical flow path aft of the rotor. This redesign eliminates an 'S' shaped duct in the exit stator assembly of the original design. The measured performance showed no improvement over the original design, and indicated a two- point degradation in efficiency. The demonstrated exit stator and duct total pressure loss at design speed and stator setting was consistent with that demonstrated by the previous exit stators. Variation in the angle setting of the adjustable stator blades caused some movement of the surge line and flow range of the compressor, but offered no improvement in peak performance relative to the design setting.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1970
- Accession Number
- AD0877209
Entities
People
- Charles Muller