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The exit static pressure was set a value 1.033 which equals to the ambient pressure plus the pressure drop in the recuperator. The rotational periodic boundary condition is imposed on the periodic boundaries. And the non-slip and adiabatic conditions were applied on all solid walls. The connection option of the stator and rotor domains is ‘stage’ which performs circumferential averaging of the fluxes through bands on the stator and rotor domain interface. A counter-rotating wall condition is specified for shroud, where a tip clearance of 4% of the blade local span was used. The low Reynolds number shear stress transport (SST) k–ω turbulence model, which predicts any flow separation with reasonable accuracy, was employed in the calculations. Both design point and off-design conditions were simulated to obtain full performance maps. Testing the performance of the designed turbine was performed using CFD. Also, one- dimensional loss models available in literature were used to account for the losses that haven’t been considered in the CFD calculations, such as volute and windage losses and the loss due scalloping the turbine rotor. This procedure gives more accurate results to predict the performance of the turbine than using one-dimensional correlations only. Figure 13 shows the performance map for the turbine at three different rotational speeds, where, the red circle represents the design point. At the design point the mass flow rate of the turbine is 0.0818 and the total to static pressure ratio is 2.827, where the shaft power output from the turbine equals 18.162 kW. Figure 14 shows the efficiency versus pressure ratio for the same two speeds, where the design point is marked by a red circle. The turbine efficiency gained when operating the turbine at the design point is 83.8%. Also it can be noticed that running the turbine with the same inlet conditions as the design point but with a higher rotational speed (140 krpm) will increase the turbine efficiency to 84.5%, meanwhile, reducing the rotational speed to (115 krpm) will reduce the turbine efficiency to 80.9%. For low expansion ratios (less than 2.2) it can be seen that for the design rotational speed (130 krpm) the efficiency drops significantly, while it increases for lower rotational speed (115 krpm). Table 6 gives the overall performance for the designed machine when running at the design point as indicated from the CFD results. Table 6: overall Performance Results Table Inlet Mass Flow Rate (kg/s) Inlet Volume Flow Rate (m3/s) Total to static Pressure Ratio Total-to-Total Isentropic Efficiency % Rotation Speed (rpm) Shaft Power (watt) Nozzle loss coefficient 0.0819 0.0861 2.827 83.8 130,000 18162 .08 14PDF Image | Optimised Radial Turbine Design D1.8
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