New blading concepts as used in modern transonic axial-flow compressors require improved calculation methods. Here the turbulence modelling has great influence. Therefore a quasi-three-dimensional compressor blade with subsonic inlet conditions is calculated using different turbulence models. A low-Reynolds number k-ϵ, the k-ω model and an explicit algebraic Reynolds stress model are considered in this investigation.

The results from these calculations in form of comparisons between the predicted isentropic Mach number distributions, profile losses and exit flow angles with experimental data are presented in this paper. They demonstrate the differences between the models in the prediction of the separation behavior of blade surface boundary layer especially which are introduced by shocks. For the high inlet Mach numbers the models differ also in the prediction of losses and deviation angles at design and off-design conditions.

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