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In recent years, the effect of heat transfer in the compressors has been investigated. It shows that cooling via compressor surface can improve the overall performance of the axial compressor. In this paper, the mechanism of cooling effect on the transonic flow is studied. Casing cooling is applied in a transonic compressor rotor and a one and a half stage transonic compressor modelling the F class gas turbine first stage, respectively. Effect of cooling is numerically investigated at the neardoi:10.33737/gpps19-tc-029 fatcat:rwzudiucfvdyvh7uadwv35y7vi