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ISSN Druckformat: 1948-2590
ISSN Online: 1948-2604
CALCULATION METHOD FOR UNSTEADY AERODYNAMIC BLADE ROW INTERACTION IN A MULTISTAGE TURBOMACHINE
ABSTRAKT
A mathematical model is presented for the calculation of the multistage turbomachinery tonal noise that takes into account the effects of the unsteady aerodynamic interaction in a system of several mutually rotating blade rows. The model is based on the frequency/modal spectrum analysis of turbomachinery gas flow parameter fluctuations, which allows determining the space/time structure of the perturbation field induced by the interaction of the rotor and stator blade rows. The method of tonal noise calculation is realized in the CIAM domestic three-dimensional acoustics solver (3DAS) using modern highly efficient finite-difference schemes of the numerical integration of the Euler equations for flow parameter fluctuations.
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Rossikhin Anton A, Frequency-domain method for multistage turbomachine tone noise calculation, International Journal of Aeroacoustics, 16, 6, 2017. Crossref