Study of cold flow pattern in a jet engine combustion chamber using three dimensional flow simulation

In this paper, we develop a numerical solution of flow for an annular gas turbine combustor. Three dimensional flow fields are considered for whole space from the compressor outlet up to turbine inlet including the inside and outside of the combustion chamber. Previous work has examined different parts of the combustor separately, using boundary conditions obtained from one-dimensional correlations. These correlations obtained with simplifications that often generate error. In this paper, the application of whole space of the combustor implies that no boundary conditions for the air inlet holes to the combustor were required. Comparison of the present numerical solution results with the experimental results indicates consistency between this study and the rest of the existent literature. We then examine the whole coupled system of an applied annular combustion chamber, simulated altogether and simultaneously. A 60 degree section of the annular combustion chamber was selected; including diffuser, swirls, liner, fuel pipes, strut and side channels and the quality of flow field was analyzed.