Computations for improving the performance of a new hydrogen-oxygen rocket engine based on supermulti-jets colliding with pulse

We have previously proposed a new type of rocket engine that uses the new compressive combustion principle based on supermulti-jets colliding with pulse, which may further improve the thermal efficiency of present rocket engines. In this research, we calculate the flow inside the combustion chamber of our new rocket engine by computation in two cases of injection nozzle distributions, half-sphere and sphere-like. We used the unsteady three-dimensional compressible Navier-Stokes equation, by using a method alike the C-CUP method. Computational results showed that in the sphere-like injection nozzle distribution, combustion efficiency and the pressure of combustion chamber are higher than those in the half-sphere injection nozzle distribution.