The Effects of Solidity, Interblade Phase Angle and Reduced Frequency on the Time-Variant Aerodynamic Response of a Compressor Stator.
Abstract
An experimental investigation was conducted to provide basic unsteady pressure distributions on a stationary vane row, with the primary source of excitation being the wakes generated from an upstream rotor. This was accomplished over a wide range of key parameters in a large-scale, low-speed, single stage compressor. The excitation, the velocity defect created by the rotor blade wakes, was measured with a crossed hot wire. The resulting time-variant aerodynamic response was measured by means of flush mounted high response pressure transducers mounted on a stator vane over a wide range in incidence angles. The dynamic data were analyzed to determine the chordwise distribution of the dimensionless dynamic pressure coefficient and aerodynamic phase lag as referenced to the transverse gust at the vane leading edge. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1980
- Accession Number
- ADA090546
Entities
People
- Robert L. Jay
- William A. Bennett
Organizations
- General Motors