Abstract
In this study, we focus on supersonic impulse turbine designed for rocket engine and investigate feature of high efficiency turbine using Computational Fluid Dynamics (CFD) by exploring a design space which in the present study is the distance between the Nozzle and the Rotor (Nozzle-Rotor Gap). Four grids with increasing mesh densities were used for estimating the Grid Convergence Index (GCI) in order to quantify the uncertainty of the numerical results. We calculated five conditions of Nozzle-Rotor Gap which are set to 50%, 75%, 125%, 150% of the reference Nozzle-Rotor Gap. The trend of the influence of the Nozzle-Rotor Gap on T-T efficiency was obtained although the GCI uncertainty analysis showed that the trend falls within the uncertainty range. Hence an addition of another level of grid refinement is preferred in order to ascertain the presence of the trend.
