Numerical solution of air-flow in a reverse flow combustion chamber of gas turbine

Reverse flow combustion chambers in gas turbines have several benefits and widely used as small turbine engines. In these turbines, the main advantage of these chambers is to decrease the length of shaft between the turbine and compressor in order to overcome the difficulties arising from the shaft at high speeds. Design of these containers for a gas turbine engine, need to expensive and frequent tests. In the past, the designers, based on the existing experiences, test results and analysis of the experimental relations were designed these chambers. But the complex geometry of these chambers was avoided from putting the measurement tools for obtain the information such as temperature, pressure and speed. In this study, the numerical solution of flow field in a reverse flow annular combustion chamber was determined and achieved results were compared with experimental solution. To analyze of flow in the outer ring, a 30 degree sector of a circle was considered. For analysis of flow in outer ring, the turbulence method and in the Liner, the RSM turbulence method was used. As you seen in this work, value of dump-gap has not effect on the shape of the profiles. At the end, the presented results were compared with experimental results.

Keywords:

reverse flow , gas turbine , combustion chamber