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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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The basis for most modern shock loss models is that of Miller-Hartmann-Lewis (1961). Their model, which can be used to calculate minimum-loss shock loss, is described using Figure 2.7. A Mean Camber Line Normal Shock Approximation Figure 2.7 Schematic of Miller-Hartmann-Lewis Shock Loss Model In Figure 2.7, Mshock is equal to (Mss + Mr1) / 2, or the arithmetic average of the suction side and inlet relative Mach numbers. The suction side Mach number at point B can be found by isentropically expanding Mr1 to the angle tangent to the suction side at point B. Point A is the leading edge of the upper blade in the cascade. Point B on the suction side is found by extending the normal shock perpendicular to the mean camber line until it hits the suction side of the lower blade at Point B. The Koch and Smith minimum-loss shock loss correlation models two passage shocks, one oblique and one normal, as well as a bow shock at the leading edge. Koch 16 B Mss Mshock Mr1

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