Turbomachinery Blade Loading Prediction Using the Panel Method
A 2D frequency domain source-doublet based potential paneling formulation is used to predict the steady and unsteady loadings on turbomachinery blades. The method employed blade-to-blade periodic boundary condition and interblade phase angles to simulate the complex blade-viscous wake interaction in a relative motion. For centrifugal turbomachines, a quasi-3D flow is calculated along the stream surfaces, using appropriate coordinate transformation and stream tube thickness variations. Results obtained from this method agreed well with measured data and other predicting methods. This method is accurate and computational efficient compared to finite difference methods. In this paper, the method of frequency domain computation is discussed. Selected results from 2D and quasi 3D flow in steady, and unsteady states are presented.
KeywordsUnsteady Pressure Turbomachinery Blade Space Shuttle Main Engine Frequency Domain Computation Subsonic Mach Number
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