抄録
This paper treats three dimensional unsteady CFD simulations of two types of supersonic turbines with different configurations, i.e. a full admission turbine and a partial admission turbine configurations respectively, for a future rocket engine. The CFD results are compared with each other from the point of view of the turbine flow pattern, loss distributions, loss mechanisms and turbine efficiency in order to determine which configuration is preferable. It is found that entropy value at the axial gap is higher in the partial admission turbine stage than that of the full admission turbine stage due to the partial admission losses. However, in the full admission turbine stage, rotor leading edge shock waves cause large separation on the rotor suction surface and large amount of entropy is created. Then, the turbine efficiency in the partial admission stage is higher than that of the full admission stage.
