In this study, a one-dimensional empirical model was developed and integrated with a commercial network solver to predict flow distributions and pressure losses for the combustion chamber of a commercial gas turbine aero engine. The need for such a model arose from practical problems being experienced on the particular gas turbine combustor considered. Results obtained showed that our simplified model is capable of predicting, with reasonable accuracy, the same trends as more detailed numerical models. The advantage, however, is the model’s rapid execution, which allows design modifications and parametric studies to be conducted more simply than before. Moreover, the data obtained from the one-dimensional analysis were also used as boundary conditions for a more detailed three-dimensional model. The results were compared with the measured temperature distribution on the combustor outlet plane, and overall good agreement was obtained.