Abstract: The exit radial temperature profiles formed by four configurations of dilution hole design have been studied experimentally on a two-dimensional experimental combustor. According to the results the effect of different configurations of dilution hole design on combustor exit radial temperature profile shows certain regularity. A semi-empirical and semi-analytical model has been developed for predicting the exit temperature profile of gas turbine combustor.The model can predict the effect of change in dilution zone design or combustion operating conditions on the variation of combustor exit radial temperature profile based on exit temperatures meas-sured before change. The comparison of the predictions with the measurements shows excellent agreement. The model provides a quantitative design tool for adjustment of temperature profile of gas turbine combustor.