Aeroelastic analysis of turbomachinery: Part I – phase lagged boundary condition methods

Abstract

In this two‐part paper, aeroelastic analysis of turbomachinery blade rows and phase‐lagged boundary conditions used for analysis are described. Part I of the paper describes a study of phase‐lagged boundary condition methods used for non‐zero interblade phase angle analysis. The merits of time‐shifted (direct‐store), Fourier decomposition and multiple passage methods are compared. These methods are implemented in a time marching Euler/Navier‐Stokes solver and are applied to a fan for subsonic and supersonic inflow and to a turbine geometry with supersonic exit flow. Results showed good comparisons with published results and measured data. The time‐shifted and Fourier decomposition methods compared favorably in computational costs with respect to multiple passage analysis despite a slower rate of convergence. The Fourier‐decomposition method was found to be better suited for workstation environment as it required significantly less storage, although at the expense of slightly higher computational cost. The time‐shifted method was found to be better suited for computers where fast input‐output devices are available.

Citation

Srivastava, R., Bakhle, M.A., T.G., K. and Stefko, G.L. (2004), "Aeroelastic analysis of turbomachinery: Part I – phase lagged boundary condition methods", International Journal of Numerical Methods for Heat & Fluid Flow, Vol. 14 No. 3, pp. 366-381. https://doi.org/10.1108/09615530410518002