Unsteady single passage methods for turbomachinery applications are becoming a more and more mature method in predicting unsteady blade-to-blade aerodynamics in a more efficient and accurate way compared to multipassage computations with scaled airfoil geometries. The outlined work presents results of a fourier-based method for phase-lagged boundary conditions using a usual conservative approach at the interfaceplane and compares it to a new characteristic treatment as well as a linearized single row approach. The new method provides results of similar accuracy with improved stability of the algorithm and faster convergence times.
Numerical Validation of Characteristic and Linearized Unsteady Boundary Conditions for Non-Integer Blade Ratios in a Non-Linear Navier Stokes Solver
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Mokulys, T, Dewhurst, SC, & Abhari, RS. "Numerical Validation of Characteristic and Linearized Unsteady Boundary Conditions for Non-Integer Blade Ratios in a Non-Linear Navier Stokes Solver." Proceedings of the ASME Turbo Expo 2005: Power for Land, Sea, and Air. Volume 6: Turbo Expo 2005, Parts A and B. Reno, Nevada, USA. June 6–9, 2005. pp. 1147-1160. ASME. https://doi.org/10.1115/GT2005-68670
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