Abstract In this study, the flow field at the end section of a turbojet engine consisting of an axial flow turbine and its exhaust nozzle is investigated. The purpose of this study is to investigate the flow in an axial flow turbine (stator blade row and rotor blade row) as well as the converged exhaust nozzle in a turbojet engine using ANSYS commercial software. At first, the stator and rotor blade geometries of axial flow turbine in ANSYS CFX and the nozzle cut section geometry in ANSYS fluent are separately meshed. Meshing has been reduced to eight steps to obtain resolved independence from the network. After applying boundary conditions and solving the flow field, important flow characteristics are extracted and their diagrams are plotted. The Fano equation was developed for the output nozzle and the Mach number during the nozzle was coded by MATLAB software and compared with the Mach number obtained from the three-dimensional nozzle analysis. Using the shape functions, the geometry of the nozzle is modified and the problem resolved again. The efficiency of the exhaust nozzle was eva‎luated at each stage with the modified nozzle. After modification, it was observed that the nozzle with the PCS shape function has the highest efficiency compared to the original. The deformation of the exhaust nozzle with PCS shape functions increases the total efficiency by 0.24% compared to the initial state and also increases the turbine efficiency by 0.42%.

ابوالحسن عسگرشمسي