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Figures 10 and 11 show the velocity triangles at rotor inlet and exit respectively. These figures compare the CFD results with those obtained from the one-dimensional design process. The velocity triangles in figure 11 are defined at Root Mean Square (RMS) radius of the rotor outlet. Based on the CFD results, the number of nozzle guide vanes was increased to 15 to achieve the required mass flow rate. The incidence angle at the rotor inlet was reduced to prevent flow separation at the suction side of the rotor blades. The difference between mean-line design and CFD results shown in figure 10, results from these modifications and the inherent assumptions of the mean line design process. At the rotor exit (figure11), larger difference can be observed between the CFD results and the meanline results which are related to the assumption made in the preliminary design method. W (m/s) Preliminary results CFD results C (m/s) U (m/s) U (m/s) = 499 C (m/s) = 467 W (m/s) = 135 U (m/s) = 499 C (m/s) = 497 W (m/s) = 142.5 Figure 10: velocity triangle at rotor inlet resulted from preliminary design and CFD results. W (m/s) Preliminary results CFD results C (m/s) U (m/s) U (m/s) = 299 C (m/s) = 125 W (m/s) = 261 U (m/s) = 229 C (m/s) = 216 W (m/s) = 311 Figure 11: velocity triangle at rotor outlet resulted from preliminary design and CFD results defined at RMS radius. 12PDF Image | Optimised Radial Turbine Design D1.8
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