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The second method assumes points A and C have the same experimentally determined minimum-loss point for a given speed line (see Figure 3.4). D B A&C -1 0 1 2 3 4 5 Incidence (i) Minimum Loss Incidence (i*) Figure 3.4 Total Pressure Loss Versus Incidence Angle for 3-D Annular Cascade The advantage of this second method is that one can use experimental results for the minimum-loss point as the minimum-loss point for off-minimum-loss curve prediction. The disadvantage of the second method is that the inlet relative Mach numbers may be slightly different than those for the minimum-loss points one is trying to evaluate. For Rotor 1-B, the Koch and Smith model predicted a design profile loss of approximately 0.026 to 0.036 between inlet relative Mach numbers of 0.55 to 1.18. For Rotor 35, the Koch and Smith model predicted a design profile loss of approximately 0.016 to 0.021 between inlet relative Mach numbers of 0.94 to 1.4. 29 Constant Speed Line Total Pressure Loss Coefficient( ω )PDF Image | Gas Turbine Design Axial Flow Compressors
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