Three-dimensional nonreflecting boundary conditions for swirling flow in turbomachinery

Journal article

This paper discusses the implementation of nonreflecting boundary conditions for the computation of linear unsteady aerodynamic turbomachinery problems. Based on the use of precalculated far-field acoustic eigenmodes for a mean flow that is assumed to be uniform axially and circumferentially, but nonuniform in the radial direction, the method very effectively reduces the reflections and improves the convergence rate for both inviscid and viscous flows. Extension of the implementation within a generalized minimal residual method is summarized and convergence results are presented. This is the companion paper of a previous publication that addressed the numerical computation of the eigenmodes and their use for postprocessing. Copyright © 2007 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

Authors: Moinier, P; Giles, M; Coupland, J

• Publication status: Published
• Journal: JOURNAL OF PROPULSION AND POWER
• Volume: 23
• Issue: 5
• Pages: 981-986
• Publication date: 2007-01-01
• DOI: 10.2514/1.22117
• EISSN: 1533-3876
• ISSN: 0748-4658
• Language: English