Optimization of the two-dimensional stator

Abstract

Gas turbine engine is mainly composed of compressor, inlet , tail nozzle, combustion chamber and turbine. The compressor pressurizes the air from the inlet into high-pressure air, which is used to mix and burn with fuel in the combustion chamber to form high-pressure gas. In this paper, numerical analysis of compressor stator performance and corresponding optimization were conducted using COMSOL Multiphysics 5.6. Firstly, an overview of compressor blade design is given. Then, the physical model and computational model are introduced and established by COMSOL. Afterwards, after the validation of the computational model, the numerical computations and results are generated and used to compare with NASA67 stator experimental data, with several key performance indicators including turning angle and loss coefficient. The polynomial expression is used to construct the blade shape/profile with different maximum thickness and its position, maximum bending and its position, trailing and leading edge angle and chord length are chosen as parameters for optimization. Then, I choose the maximum thickness and its position, maximum bending and its position, trailing and leading edge angle as the optimization parameter. Finally, we reach some conclusions of a better stator design possible for newer compressor requirements and further studies are recommended.