چكيده به لاتين
Aerodynamic optimization of gas turbine components has been a topic of interest for researchers in recent years. Because a small improvement in the performance of gas turbine components leads to a significant reduction in operating costs, aerodynamic optimization is of the greatest importance in aerospace and industrial applications. For this purpose, in this thesis, the aerodynamic optimization of the row of nozzle blades of the first stage of the axial turbine has been done. In order to parameterize the geometry of the nozzle blade, Bezier curves have been used to distribute the blade angles at the hub and tip of the nozzle blade. The optimization algorithm is based on artificial neural network training based on data from numerical simulations in CFX software for a certain number of nozzle geometries, generated using the Experimental Design (DOE) method. The results showed that as a result of nozzle optimization, unlike the main blade, no separation occurred in the row of nozzle blade rows
