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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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leading and trailing edges, respectively. Deviation (δ) is defined as the difference between the exit relative flow angle (β′2) and the blade exit metal angle (β′2) (see Equation 2.3). The angle formed between the chord line and the meridional axis is referred to as the stagger angle (ξ). The maximum thickness between the pressure and suction sides of the airfoil is (tmax). Although not shown in Figure 2.2, a is the distance along the chord from the leading edge of the blade to the point of maximum camber, which occurs where there is maximum displacement between the camber line and the chord line. The spacing (s) is the distance between blades in the θ direction. Equations 2.2 through 2.6 represent some blade geometry definitions as expressed in equation form: L = β􏵩 − β 􏵩 δ = β􏵪 − β 􏵪 α∗ = β􏵩 − ξ θ′= β􏵩−β􏵪 σ = FV (2.2) (2.3) (2. 4) (2.5) ( 2 . 6 ) These geometry definitions include the incidence angle (i), deviation angle (δ), angle of attack (α*), camber angle (θ′), and cascade solidity (σ). 7

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