J051023Effects of Mach Number on Aerodynamic Losses of Rocket 'rurbopump Turbine

Abstract

A study on the effect of Mach number upon efficiency of a supersonic impulse turbine is presented. The purpose of the present work is to evaluate the accuracy of existing one dimensional loss model. Two-staged axial flow supersonic impulse turbine which was designed as Mach number of 1.3 was used as reference. By using the steady two dimensional CFD analyses, parametric studies against the major design variables were carried out. These simulation results were compared with the results that were also obtained by using the existing one dimensional loss models.