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Master Thesis Report 3D Flow Simulation of the NASA Rotor 67 7.5.4 Performance Comparison of the Rotor Under Uniform Inflow with/without Casing In this section, the performance of the rotor under uniform inflow for the case with and without casing will be presented. 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. quantities obtained at the mid radius of Table 7.7: Performance of the Rotor Parameters Temperature Total Temperature Pressure Total Pressure Enthalpy Total Enthalpy Total to Total Pressure Ratio Static Entropy Total to Total Isen. Efficiency It is noted that these quantities are the mass flow averaged the rotor. The results are presented in table 7.7 and 7.8. (with casing) under Uniform Inflow Boundary Condition Units [K] [K] [Pascal] [Pascal] [m2 /s2 ] [m2 /s2 ] Inlet 94.76 105 8805.63 12608 -204286 -193998 Outlet Ratio or Change 123 - 144.2 - 15197.3 - 27077.6 - -175925 - -154651 - --- 2.15 [J/kgK] -449.891 -345.2 104.691 - - - 0.627926 Table 7.8: Performance of the Rotor (without casing) 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 ] Inlet 77.4 86 8723.38 12607.2 -221715 -213082 Outlet Ratio or Change 104.43 - 125 - 15227.7 - 29052.3 - -194573 - -174221 - - - - 2.304 [J/kgK] -650.358 -511.3 139.06 - - - 0.58484 From the above table, it can be seen that the case of a rotor without the casing experienced a reduction in the isentropic efficiency despite having a slightly higher pressure ratio for the same inlet and outlet boundary conditions used in the simulation. As seen in the plot of the circumferential averaged total pressure versus normalized span, it can be inferred that the loss in efficiency and gain in entropy is due to the lower total pressure at the tip of the blade as a result of tip vortex formation. 95PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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