Numerical Analysis Of The Flow In The Reverse Flow Type Combustor

Combustor is one of the key components in gas turbine. The geometry structure and the internal flow of the combustor is of highly complexity. CFD technique is a successful method to study the details of the flow inside the combustor. The combustor studied in this paper is a gas turbine combustor that had, in many cases, serious problems with ablation during real operations. It is crucial to study the flow inside the combustor and to obtain the details of the temperature distribution, in an attempt to solve the problem of ablation.A numerical analytic system based on the real three-dimensional geometry structure and powerful commercial software STAR-CD was established in this thesis for the study of the internal flow of the combustor. Numerical analysis was carried out for the single-phase flow, two-phase flow and the combustion simulation step by step. The main features of the flow field and temperature field were obtained. The mechanism of the ablation was explored by a close observation of the temperature distribution and the flow around the combustor.In the modeling process, every details of the real geometry were represented and the mesh was refined locally as needed. All those strict measures had safeguarded the accuracy of the simulation results. Numerical results agree well with the experimental results. The analytic system described in this thesis may provide a useful tool for the study of the problem of ablation and emission.