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Gas Turbine Design Axial Flow Compressors

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Gas Turbine Design Axial Flow Compressors ( gas-turbine-design-axial-flow-compressors )

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Table 4.7 contains the eight possible combinations of loss models used to obtain a total minimum-loss prediction. Table 4.7 Rotor 35 Evaluation of Minimum-Loss Prediction Experimental Koch Koch Lieblein Lieblein Swan Swan Hearsey Hearsey Total + + + + + + + + Minimum Loss Koch Miller Koch Miller Koch Miller Koch 0.122 0.181 0.177 0.140 0.067 0.087 0.090 0.086 0.018 0.021 0.021 0.044 0.017 0.029 0.027 0.008 Miller 0.137 0.089 0.044 0.006 0.1230 0.117 0.114 0.126 0.093 0.059 0.062 0.065 0.044 0.016 0.016 0.018 MEAN ERROR 0.023 0.023 0.019 The titles for the predictions contain the names of shock loss model. The second, third, and fourth rows minimum-loss results from Rotor 35’s 100%, 90%, and 70% corrected speed lines, respectively. It should be stated that the 100% and 90% corrected speed lines contained supersonic relative inlet Mach numbers, and the 70% corrected speed line contained subsonic relative inlet Mach numbers. At subsonic relative inlet Mach numbers, no shock loss model was included in the predictions. Over the entire range of corrected speeds, the combination of Hearsey profile and the Miller-Hartmann-Lewis shock loss models, and the combination of Hearsey profile and the Koch-Smith shock loss models gave predictions most comparable to Rotor 35 experimental data with mean loss errors of only 0.006 and 0.008, respectively. The next best combination was Leiblein profile and Miller-Hartmann-Lewis shock loss models, which gave a mean loss error of 0.017. Unlike for Rotor 1-B, the Koch-Smith combination of profile and shock was not very accurate, with a mean loss error of 0.023. 50 the blade profile loss model + of the table contain the total

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