This investigation was aimed at developing more sophisticated shock models to be incorporated in an off-design performance prediction method for transonic axial flow compressor stages for more accurate flow prediction. Primary emphasis was given to the improvement of shock models used for evaluating the shock losses, especially, at supercritical subsonic, but also at supersonic inflow conditions. The newly developed and refined methods were verified by calculating, investigating and analysing the losses of compressor cascades, as well as of a transonic axial flow compressor.
Shock Loss Model for Supercritical Subsonic Flows in Transonic Axial Flow Compressors
1987
15 pages
Report
Keine Angabe
Englisch
Jet & Gas Turbine Engines , Aerodynamics , Axial flow compressors , Supercritical flow , Transonic characteristics , Subsonic flow , Shock , Losses , Mathematical prediction , Cascades(Fluid dynamics) , Gas turbines , Power levels , West germany , Foreign technology , NATO funished , Component reports
Shock-Loss Model for Transonic and Supersonic Axial Compressors with Curved Blades
Online Contents | 1998
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