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Master Thesis Report 3D Flow Simulation of the NASA Rotor 67 7.4.4 Performance Comparison of the Rotor Under Uniform and Non Uniform Inflow In this section, the performance of the rotor under both uniform and non uniform inflow will be compared. In particular, the main aspect of the performance comparison would be to look into the isentropic efficiency of the rotor, static entropy change, the total to total pressure ratio as well as the enthalpy change across the rotor. It is noted that these quantities are the mass flow averaged quantities obtained at the mid radius of the rotor. Table 7.5: Performance of the Rotor under Non Uniform Inflow Boundary Condition Ratio or Change - - - - - - 2.385 157.1 0.5814 Parameters Temperature Total Temperature Units Inlet [K] 76.6 [K] 86 Outlet 108 129 12848.1 24518.4 -191051 -169730 - -430.49 - Pressure [Pascal] 6780 10281.9 -222521 -213084 - -587.58 - Total Pressure Enthalpy Total Enthalpy Total to Total Pressure Ratio Static Entropy Total to Total Isen. Efficiency [Pascal] [m2 /s2 ] [m2/s2] - [J/kgK] - Table 7.6: Performance of the Rotor under Uniform Inflow Boundary Condition Parameters Temperature Total Temperature Pressure Total Pressure Enthalpy Total Enthalpy Total to Total Pressure Ratio Static Entropy Total to Total Isen. Efficiency Units [K] [K] [Pascal] [Pascal] [m2 /s2 ] [m2/s2] - [J/kgK] - Inlet 94.76 105 Outlet 123 144.2 Ratio or Change - - - - - - 2.15 104.691 0.627926 As seen in table 7.5 and 7.6, the effect of the non uniform inflow is an increase in entropy production and a decrease in the isentropic efficiency. For the non uniform boundary condition, the mass average total pressure at the inlet is lower as compared to the uniform boundary condition. Therefore, the outlet static pressure for both simulation cases are different. 7.5 3D Uniform Inflow Simulation Results With/Without Casing In this section of the chapter, the 3D results will be presented and discussed. In particular, the focus of the results will be on the blade loading and performance comparison of the rotor with and without a casing as well as the visualisation of the streamlines view of the meridional channel. In addition, the plot of the circumferential average total pressure at the inlet and outlet domain will be presented. 8805.63 15197.3 12608 27077.6 -204286 -175925 -193998 -154651 - -449.891 - - -345.2 - 90PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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