This paper describes an aeroelastic analysis program for turbomachines. The program is based on the Euler/Navier-Stokes equations and is validated using experimental data and analytical and numerical results. Blade structural response is modelled using a modal representation of the blade and the work-per-cycle method is used to evaluate the stability characteristics. Non-zero inter-blade phase angle is modelled using phase-lagged periodic boundary conditions. Two phase-lagged analysis methods, time-shifted, and Fourier-decomposition have been implemented in the code and are validated by comparison to a multiple passage analysis. The time-shifted method is used for the validation of the aeroelastic analysis code. Steady and unsteady predictions obtained from TURBO-AE show good agreement with analytical and numerical results. Comparisons with experimental results are in good agreement over most of the blade surface. However, in the leading edge region where a flow separation was known to occur, the agreement was only fair.

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