Mathematical Modelling and Analysis of an Axial Compressor Supersonic Stage Impeller

There is an evident trend to elevate pressure ratio of a single stage of a turbo compressors - axial compressors in particular. Q-3-D computer program based on wind tunnel test data was applied to research possible parameters of axial stage candidates with pressure ratio 3,0. Influence of two main design parameters on expected efficiency, periphery blade speed and flow structure was studied. Acceptable level of efficiency and inlet Mach number are expected at flow rate coefficient = 0.35 and flow deflection angle = 12 degrees. The calculation results have led to a stage candidate for further analysis and improvement by field type and CFD programs.