Improvement of the Parallel Compressor Model by Consideration of Unsteady Blade Aerodynamics,
Abstract
The parallel compressor model was applied to predict compressor performance with circumferential total inlet distortion. In comparison with the experiment, however, this model gives too pessimistic results for the predicted stall line shift considering sector angles of distortion up to 120 degree. Detailed experimental evaluation of a compressor stage leads to unsteady performance effects obviously being responsible for this discrepancy. To improve the original model, the performance characteristic of the compressor was extended to account for a short time overload capability analogous to an airfoil in an unsteady flow. The governing factor of this modification will be the time-to-stall versus the time for a blade channel to pass the distorted sector. The model improvement has been demonstrated for a DFVLR and a NASA single stage transonic compressor subjected to a screen induced total pressure distortion.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1987
- Accession Number
- ADP005467
Entities
People
- M. Lecht