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Appl. Sci. 2018, 8, 2038 Appl. Sci. 2018, 8, x FOR PEER REVIEW 4 of 16 Appl. Sci. 2018, 8, x FOR PEER REVIEW 4 of 17 4 of 17 1.2 1 1 0.8 0 0.6 0 0.4 0 0.1 0.1 0.2 0.2 0.3 0.4 0.5 .2 1 85 .8 .6 .4 82.2 85.2 82.2 85.8 85 85 85.8 80.2 83 83 54 80 88 .2 8181 .2 80.8 70.5 54 90.4 88.4 82 86.2 7 8882 85.6 78 88 85 887.1 867.2 85.6 82.8 87.1 87 84.682.8 84 84.683 84 83 82.7 82 82 80.8 85 85.585.683 83 82 85.585.6 84.5 8279.8 82.7 82.3 90.4 8888 86 88.4 82.3 80.8 80.8 84 84 76 8684 84 80 80 76 82 87 85.6 82.4 85.6 84.6 80.6 60.2 60.2 84.5 79.8 83.6 75.4 74.5 84.6 80.680.6 80.6 83.6 75.4 74.5 77.5 74 77.5 7 0.5 7 8 .4 4 62.9 67 67 72 72 62.9 0.3 0.4 Flow coefficient [-] Flow coefficient [-] 0.5 Figure 2. Correlation of loading and flow coefficients for radial inflow turbine [26,28]. Figure 2. Correlation of loading and ffllow coefffiicients for radial inflflow turbine [26,28]. FiFgiugruer3e3shsohwowstshtehecocnovnevnetniotinoanlaflloflwowchcahratrotfotfhtehmemeaenanlinliendeedseigsingnprporcoecsess.sI.tIsttsatratrstwswithithaadedseisgingn Figure 3 shows the conventional flowchart of the mean line design process. It starts with a design vevcetcotro(rψ(,ψφ,φn,)nan)danadnainitinailtgiaulegsuseosfsthoeftohtealt-otota-ls-ttaot-iscteaftfiiciefnficcyieηnc,ythηen, tchaelcnulcatlecsutlhateegsetohmeegteroicmaentdric ts ts ts vector (ψ , φ , n ) and an initial guess of the total-to-static efficiency η , then calculates the geometric flow features for both nozzle and rotor, and after that iterates the efficiency using well-established and flow features for both nozzle and rotor, and after that iterates the efficiency using well- and flow features for both nozzle and rotor, and after that iterates the efficiency using well- loss models until a convergence criterion has been achieved. The feasibility check makes sure that the established loss models until a convergence criterion has been achieved. The feasibility check makes established loss models until a convergence criterion has been achieved. The feasibility check makes design output satisfies the application nature and constraints. sure that the design output satisfies the application nature and constraints. sure that the design output satisfies the application nature and constraints. It should be noted that the total-to-static efficiency is initially estimated based on Figure 2 after It should be noted that the total-to-static efficiency is initially estimated based on Figure 2 after It should be noted that the total-to-static efficiency is initially estimated based on Figure 2 after the loading coefficient and the flow coefficient are set, but the initial total-to-static efficiency cannot the loading coefficient and the flow coefficient are set, but the initial total-to-static efficiency cannot the loading coefficient and the flow coefficient are set, but the initial total-to-static efficiency cannot influence the final result, but only the iteration steps. Therefore, the final result is only decided by the influence the final result, but only the iteration steps. Therefore, the final result is only decided by the influence the final result, but only the iteration steps. Therefore, the final result is only decided by the loading coefficient, the flow coefficient, and the rotor rotational speed. loading coefficient, the flow coefficient, and the rotor rotational speed. loading coefficient, the flow coefficient, and the rotor rotational speed. In addition, there are two kinds of calculations in the process of stator and rotor calculation in In addition, there are two kinds of calculations in the process of stator and rotor calculation in In addition, there are two kinds of calculations in the process of stator and rotor calculation in Figure 3. The first one is the calculation of main geometry size and aerodynamic parameter according Figure 3. The first one is the calculation of main geometry size and aerodynamic parameter according Figure 3. The first one is the calculation of main geometry size and aerodynamic parameter according to the loading coefficient, flow coefficient, and rotor rotational speed. The second one is the calculation to the loading coefficient, flow coefficient, and rotor rotational speed. The second one is the to the loading coefficient, flow coefficient, and rotor rotational speed. The second one is the of various energy losses according to the result of the first step. calculation of various energy losses according to the result of the first step. calculation of various energy losses according to the result of the first step. FiFgiugruer3e.3F.lFolwowchcahratrotfotfhtehme meaenanlinliendeedseigsingnprporcoecsess.s. Figure 3. Flowchart of the mean line design process. For radial inflow turbines, seven kinds of losses are considered in the mean line design procedure, For radial inflow turbines, seven kinds of losses are considered in the mean line design For radial inflow turbines, seven kinds of losses are considered in the mean line design and they are nozzle loss, rotor incidence loss, rotor passage loss, rotor tip clearance loss, rotor trailing procedure, and they are nozzle loss, rotor incidence loss, rotor passage loss, rotor tip clearance loss, procedure, and they are nozzle loss, rotor incidence loss, rotor passage loss, rotor tip clearance loss, Loading coefficient [-] Loading coefficient [-]PDF Image | Design and Optimization Approach for Radial Inflow Turbines
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