Aerodynamic design of a high-efficiency two-stage aeronautical axial gas turbine, using free vortex and flow streamline curvature

In this study, a Matlab code has been developed to create a hybrid method for combination of free vortex (FV) and streamline curvature (SLC) methods in order to design multi-stage flow axis turbines. The achievement of this research is aerodynamic design of a high-efficiency two-stage aeronautical gas turbine with design pressure ratio of ۶.۶۸, using the developed code package. A validation on application of the hybrid method has been investigated by through ۳-D numerical flow simulation of mentioned turbine using CFX software to compare the performance parameters and flow properties at operational points. Value of performance parameters such as total outlet pressure, total outlet temperature, outlet density and outlet Mach number of the turbine obtained from the SLC method differ from that of numerical simulations results by ۱۲.۵%, ۱.۳%, ۵.۵%۵ and ۱.۲۶%, respectively. Design total to total efficiency has been chosen ۹۹.۵%, which differs from its value obtained from the hybrid method and numerical simulation by ۰.۰۳% and ۴.۸۲%, respectively. Also, the total pressure ratio resulting from the simulation differs that of design value by ۹.۹۴%.

Keywords:

Streamline curvature method , Free Vertex method , High Efficiency Axial gas turbine ۳D Design and Simulation