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the unstarted regime at constant Mach number. Konnig (1996 Pt. II) used an oblique and a normal passage shock to model the shock loss in the blades, and a method similar to Miller-Hartmann-Lewis to find the Mach number immediately upstream of the first oblique shock. Konnig then determined empirically a fictitious area ratio between the areas at the positions of the oblique and normal shocks, and used nozzle theory in order to calculate the Mach number immediately upstream of the normal shock. The third method of calculating the total off-minimum-loss is very similar to the method used to calculate minimum-loss profile loss. This time, however, diffusion factor is corrected away from minimum-loss incidence. Lieblein (1957), Swan (1961), and Konnig (1996, Pt. I) use this method of prediction, which is only applicable for subsonic inlet relative Mach numbers. Off-minimum-loss deviation angle prediction is performed almost completely empirically. The standard method is to use the minimum-loss deviation angle prediction as shown in Equation 2.16. δ =δ*+a(i−i*)2 +b(i−i*)+c (2.16) In Equation 2.16, (δ) is the off-minimum-loss deviation angle, (δ*) is the minimum-loss deviation angle, and (a), (b), and (c) are empirically determined constants. All correlations used in the current evaluation, Creveling, Lieblein (SP-36 Ch. 6, 1965), Hearsey, and Howell (1947) used a variation of this method. Because the Lieblein correlation was originally developed for a 2-D cascade, his method was modified by Jansen and Moffatt (1967) to fit a 3-D annulus. 18PDF Image | Gas Turbine Design Axial Flow Compressors
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