Predictions of rotor alone tones in a transonic fan using steady CFD

I. D J Dupére, W. N. Dawes, A. G. Wilson, B. J. Tester

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

    Abstract

    At transonic speeds in fans, the circumferential variation in the pressure due to shock waves and expansion fans constitutes a significant part of the sound field in the intake duct as it rotates relative to a stationary observer. Unlike low amplitude sound waves at lower speeds, the resulting waves propagate in a non-linear fashion, decaying as they propagate upstream. Since these tones are the same as the flow field which is steady relative to the blades, they are susceptible to prediction using standard steady (relative to the blades) CFD solvers. Predictions for a fan blade across a range of fan speeds and over a range of working conditions are given here with comparison with experimental measurements made on the same fan. The agreement is within 3dB in most cases, provided a sufficiently fine mesh is used all the way along the inlet duct and provided pseudo non-reflecting boundary conditions are used.
    Original languageEnglish
    Title of host publication39th Aerospace Sciences Meeting and Exhibit|39th Aerosp. Sci. Meet. Exhibit
    Publication statusPublished - 2001
    Event39th Aerospace Sciences Meeting and Exhibit 2001 - Reno, NV
    Duration: 1 Jul 2001 → …

    Conference

    Conference39th Aerospace Sciences Meeting and Exhibit 2001
    CityReno, NV
    Period1/07/01 → …

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