The numerical simulation and evaluation of aircraft engine axial flow turbine using numerical techniques

This research aims to improve the efficiency of an axial flow turbine by improving the boundary conditions. In the baseline paper, Sherwood number, Nusselts number for a given flow were determined. The pressure ratio was not considered in the paper. Research has been done to improve the values by considering the pressure difference which was neglected in the base line paper. Axial flow turbines expand the flow passing through it. Losses like tip losses, efficiency losses and loss on blades due to heat are high and needs to be looked after. A comprehensive literature study was carried out for the better understanding of axial flow turbines, recent developments and to analyze the control of loses.