Experimental Investigations on Shock Losses of Transonic and Supersonic Compressor Cascades,
Abstract
The losses of transonic and supersonic compressor bladings are due to viscous effects and due to entropy rises in shock waves arising in the entrance regions and passages of the blades. Depending on inlet Mach number, inlet flow angle and back pressure the shock loss level reaches 40 to 70 percent of the overall losses. Most of the loss prediction models in use consider viscous and shock losses separately. However, very few quantitative experimental data of shock losses are available to verify these models. In this paper a separation of the viscous and shock losses is performed by the analysis of wake measurements behind some compressor cascades. The cascade tests have been performed in the inlet Mach number range from 0.8 to 1.7. Detailed information is presented about the shock structure and the region of shock boundary layer interaction in the blade passage of a supersonic cascade obtained with the aid of laser anemometry.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1987
- Accession Number
- ADP005513
Entities
People
- H. A. Schreiber