Analysis of Transonic Bladerows With Non-Uniform Geometry Using the Spectral Method

Abstract Turbomachinery blade rows can have non-uniform geometries due to design intent, manufacture errors or wear. When predictions are sought for the effect of such non-uniformities, it is generally case that whole assembly calculations needed. A spectral method used in this paper approximate flow fields but with significantly less computation cost. The projects perturbations geometry non-uniformity an Fourier space, and only one passage required compute corresponding a certain wave-number variation. performance on transonic demonstrated modern fan assembly. Low engine order high (e.g., “saw-tooth” pattern) examined. non-linear coupling between passage-averaged field also demonstrated. Pressure variations surface potential upstream leading edge from proposed direct solutions compared. Good agreement observed both quasi-3D full 3D cases. lumped approach deterministic fluxes further reduce computational cost method. formulated way be easily implemented into existing harmonic solver by adding extra source term potentially as efficient tool aeromechanical aeroacoustics turbomachinery rows.