Experimental investigation of losses and secondary flow in an axial compressor stage
Abstract
A detailed investigation of a three-dimensional flow using both stationary and rotating pressure probes has been carried out in a low speed axial compressor stage. At the casing of a rotor row there is secondary flow produced by the relative motion of the annular wall to rotor blade tip and the tip clearance flow. At the hub a channel vortex can be observed. The value of the loss coefficient of both rotor and stator rows determined from conventional pressure probe data is affected by flow unsteadiness. This effect has been considered in detail. As a result, the probes should be dynamically calibrated. The rotor and stator blade elements loss at mid-span approximately equals two-dimensional cascade loss, when the data of probes exposed to strong flow unsteadiness have been corrected.
- Publication:
-
Forschung im Ingenieurwesen
- Pub Date:
- 1985
- Bibcode:
- 1985F&I....51...33C
- Keywords:
-
- Axial Flow;
- Compressor Efficiency;
- Pressure Measurement;
- Secondary Flow;
- Three Dimensional Flow;
- Turbocompressors;
- Losses;
- Pressure Distribution;
- Rotor Blades;
- Stator Blades;
- Unsteady Flow;
- Fluid Mechanics and Heat Transfer