This paper describes an accurate, robust and efficient methodology for solving two-dimensional steady transonic turbomachinery flows. The Euler fluxes are discretized in space using a hybrid multidimensional upwind method, which, according to the local flow conditions, uses the most suitable fluctuation splitting (FS) scheme at each cell of the computational domain. The viscous terms are discretized using a standard Galerkin finite element scheme. The eddy viscosity is evaluated by means of the Spalart-Allmaras turbulence transport equation, which is discretized in space by means of a mixed FS-Galerkin approach. The equations are discretized in time using an implicit Euler scheme, the Jacobian being evaluated by two-point backward differences. The resulting large sparse linear systems are solved sequentially using a preconditioned GMRES strategy. The proposed methodology is employed to compute subsonic and transonic turbulent flows inside a high-turning turbine-rotor cascade.
An Implicit Fluctuation Splitting Scheme for Turbomachinery Flows
Contributed by the Turbomachinery Division of THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received by the ASME Turbomachinery Division, April 15, 2004; final revision, April 17, 2004. Associate Editor: D. C. Wisler.
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Bonfiglioli, A., De Palma, P., Pascazio, G., and Napolitano, M. (May 5, 2005). "An Implicit Fluctuation Splitting Scheme for Turbomachinery Flows ." ASME. J. Turbomach. April 2005; 127(2): 395–401. https://doi.org/10.1115/1.1777576
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