Full 3D relative stream surface iterative solution of the multistage transonic turbine in liquid rocket engines

A three dimension transonic flow field solver for a multistage turbine in liquid rocket engine was developed based on relative stream surface theory and streamline curvature approach. The stream surfaces were calculated with the streamline curvature approach and the full three dimension flow field was solved by stream surface iterations. The throat was located by comparison of critical mass flux. The interaction between vanes and blades was dealt with the idea of mixing plane. Loss models were adopted to calculate the influence of shock wave and viscosity. The supersonic/subsonic flow conditions in different stages were filtered by comparison of exit parameters. The solver gave accurate flow parameter distribution and performance parameters of transonic multistage turbine, thus provides a theoretical basis for improving the design and performance of liquid rocket engine turbine.