Improvement of the performance and distribution of outlet combustion chamber temperature of a turbojet engine with upgraded compressor in different flight conditions

Improving available aero engines to improve the performance and reduce the cost of design and construction of the new engine, the engine designers have always desired. One of the important parts involved in the upgrade process, responsive to the engine combustion chamber that must be upgraded. In this study the combustion flow in the combustion chamber of an upgraded turbojet engine is modeled using ANSYS Fluent. The combustion chamber subject to study is simulated inlet boundary conditions for three-dimensional mass, k-ε turbulence model and PDF combustion model and the P-1 radiation model. The behavior of the combustion chamber to the original state is examined in terms of the different flights. The upgraded engine where the inlet air flow has increased compression ratio compressor, the combustor used and evaluated under the new situation. The results show that temperature distribution in the combustion chamber in terms of improved performance and improved output.