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Appl. Sci. 2020, 10, 4168 18 of 26 imposed by the cycle might not allow the elimination of supersonic flows. Investigation of the total pressure losses at the rotor exit hub-to-tip surface also emphasises the efficiencies at each off-design condition. A small fraction of tip leakage losses with a pressure loss region near the hub (25% P0 loss near hub) corresponding to the better operating condition; whereas for the inefficient conditions, more pronounced shroud leakages with a proportionate value of 48% with respect to the areas of least pressure drop. Figure 12. Off-design relative Mach number distribution at mid-span from 3D CFD simulations: (a)23,550rpm&Πts =3,(b)19,268rpm&Πts =7. 3.3.4. Isolated Rotor Analysis An isolated rotor model is primarily developed for use in stress calculations but is also utilised for examination of the rotor performance without the inclusion of the stator effects. The boundary conditions are taken as dictated by the main project database of AxSTREAM with P0in = 270 bar, T0in = 1173 K at an absolute flow angle of 73.93◦ and Pout = 54.0 bar. Performance results of the rotor only model at design point are listed in Table 11. The computed total-to-static pressure drop is lower thanthedefinedvalueofwiththeCFDvalueofP0in being256bar.Themassflowrateisverycloseto the design 354.6 kg/s rate along with much better efficiencies compared to the full turbine cascade. The power output is around 14% lower than the 100 MW because of the lower pressure ratio (absence of stator means no static pressure drop there). The solution indicates that a large portion of losses arise in the stator-rotor passage and the incorrect flow conditions supplied by the nozzle. Table 11. 3D CFD performance results for the isolated rotor. Variable Unit Value Hub Tip a) 23,550 rpm/ Πts= 3 b) 19,268 rpm/ Πts= 7 Mrel [-] SS PS m ̇ kg/s W ̇ MW ηtt % ηts % ψ - φ - R - Πts - 356.3 86.38 87.80 80.46 1.21 0.423 0.406 4.75PDF Image | Radial Turbine Design for a Utility-Scale Supercritical CO2 Power
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