Time Resolved and Time Averaged Flow Evaluation for an Isolated Transonic Compressor Rotor.
Abstract
A 0.28-m single stage transonic fan was operated in a rotor only configuration. Overall performance was measured and radial distributions of inlet and outlet velocity were obtained using time-averaging combination temperature-pneumatic probes. These results were compared to the prediction of a finite element computer code (TURBOFEM) prediction. The blade-to-blade velocity and pressure distributions were measured using the Dual Probe Digital Sampling technique (involving two commercial semi-conductor probes of simple design). Data were obtained from hub-to-tip at both near-sonic and at supersonic inlet relative Mach numbers. The rotor losses were derived as blade-to-blade distributions and the shock losses were evaluated as components of the total loss at each radius. Based on the limited data obtained near sonic conditions, a combination of the profile loss model of Koch & Smith and shock loss model of Dunker was found to predict the measured radial loss distribution quite well. Preliminary observations of rotor shock oscillations were also reported. Keywords: Axial flow compressors, Compressor rotors, Compressor stators, Transonic flow, Turbomachinery flow fields, Transonic loss measurements, and Finite element codes.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1986
- Accession Number
- ADA166759
Entities
People
- F. Neuhoff