Calculation of the internal flow for turbine of liquid rocket engine based on the theory of S₁, S₂ stream surface

The theory of S₁ and S₂ stream surface was applied to calculate and analyze the internal transonic flow field for a two-stage axial turbine used in turbo pump for liquid rocket engine. Streamline curvature method was used for calculation. The interaction between the stator and the rotor was dealt with the idea of mixing plane, and then the unsteady problem was simplified to the steady problem. The influence of viscosity was corrected by several loss coefficients. The result of calculation describes the internal flow of the turbine well and provides a theoretical basis for improving the design and performance of the turbine.