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As a result, the Koch and Smith model showed that the inlet relative Mach number does not have a significant influence on the design profile loss. Therefore, the second method of comparing experimental to simulated results was selected in order to evaluate off-minimum-loss correlations for subsonic inlet relative Mach numbers. Conversely, shock losses were found to be a strong function of inlet relative Mach number. Therefore, the first method of comparing experimental and simulated results was selected in order to evaluate off-minimum-loss correlations for supersonic inlet relative Mach numbers. 3.5 Detailed Plan Accurate testing of the correlations required experimental data for a stage. Sets of data were available for both a rotor (Rotor 1-B) and a stage (Stage 35). These data acted as control references to validate the results of the correlations. The Hearsey and Cetin correlations were coded and prepared for the CMLC and were the first correlations tested in the CMLC. After running the full range of speeds and operating conditions, the results were documented and compared with experimental data from Rotor 1-B and Stage 35. Next, an investigation of other existing correlations in the open literature was conducted. The correlations which fit the conditions of transonic axial compressors were coded and tested at the meanline. After all CMLC testing was completed, the correlation results were compared and the optimum loss and deviation correlations were determined for each speed and inlet flow condition. 30PDF Image | Gas Turbine Design Axial Flow Compressors
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