Author(s)

Y. Noguchi, S.D. Allison, T. Shiratori

Abstract

Unsteady transonic cascade flows and the effects of turbulence models Y.Noguchi', S.D. Allison', T. Shiratoif ^School of Aeronautical Engineering University ofSalford, Greater Manchester, UK ^Department of Aerospace Engineering Tokyo Metropolitan Institute of Technology, Japan Abstract A computational study on unsteady transonic cascade flows and the effects of turbulence models are made. Both Baldwin-Lomax and Johnson-King models are used for comparison. Previous reports concerned the oscillating frequencies and pitch axes. In this report, four inter blade phase angles are tested. The results show the phase angle has less significant effects on the behaviour of the turbulence models. Johnson-King model predicts shock positions upstream of shocks predicted by Baldwin-Lomax model as previously observed. As the results, the variations in pitching moment and therefore the total work done are significant. 1 Introduction Modern jet engine fan/compressor blades may operate at transoni

Keywords