Reduced-order models of unsteady transonic viscous flows in turbomachinery

Published

Journal Article

The proper orthogonal decomposition (POD) technique is applied in the frequency domain to obtain a reduced-order model of the unsteady flow in a transonic turbomachinery cascade of oscillating blades. The flow is described by a inviscid - viscous model, i.e. a full potential equation outer flow model and an integral equation boundary layer model. The nonlinear transonic steady flow is computed first and then the unsteady flow is determined by a small perturbation linearization about the nonlinear steady solution. Solutions are determined for a full range of frequencies and validated. The full model results and the POD method are used to construct a reduced-order model in the frequency domain. A cascade of airfoils forming the Tenth Standard Configuration is investigated to show that the reduced-order model with only 15-75 degrees of freedom accurately predicts the unsteady response of the full system with approximately 15 000 degrees of freedom. © 2000 Academic Press.

Full Text

Duke Authors

Cited Authors

  • Epureanu, BI; Dowell, EH; Hall, KC

Published Date

  • November 1, 2000

Published In

Volume / Issue

  • 14 / 8

Start / End Page

  • 1215 - 1234

International Standard Serial Number (ISSN)

  • 0889-9746

Digital Object Identifier (DOI)

  • 10.1006/jfls.2000.0320

Citation Source

  • Scopus