Research On Low Reaction Supersonic Compressor Stator Blade And Flow Control

In this paper, the first stage stator of a three stage low reaction compressor is studied, and the phenomenon in the flow channel is researched by using numerical simulation method in two dimensional model. This paper comprehensively analyzes aerodynamic performance impact of aspiration and blade geometry in supersonic low reaction stator, intending to solve the interference problem between boundary layer separation and shock formation in the supersonic compressor interflow.Firstly, the numerical software FINE/TURBO is introduced, and the of grid independence is verified. Grid independence confirmatory systematically analysis the flow effect of grid number and grid layout mode, providing the relatively suitable aspiration grid topology. By analyzing the boundary conditions and convergence methods, a reasonable calculation method is proposed. The calculation formula of the parameters for evaluating the performance of the compressor is presented.Then, it can be known that the boundary layer separation phenomenon occuring in pressure-expanding cascade is extremely serious under supersonic flow by the analysis of the original blade. So the necessity of using aspiration to control the separation phenomenon can be proved. The study on three aspects including the suction pressure(suction mass), suction slot position and suction slot width gives us the most appropriate aspiration scheme. When the suction slot position is located between 55% and 60%, the suction slot wid th is around 3%-5% of the axial length of blade, the maximum static pressure ratio of the stator will reach 1.82, total pressure loss coefficient will be under 0.08, suction portion is below 5%. At this time, the boundary layer separation is effectively co ntrolled, and the interference between the shock wave and the boundary layer can be alleviated.Finally, the 14-parameter method is used to construct the parametric model for the two-dimensional blade with reasonable aspiration scheme. The range and the slope of maximum thickness as well as the slope of the front/rear areas, and the radius and the width ratio of leading edge and trailing edge are analyzed and the variation law of the flow parameters and the internal shock wave mode conversion phenomena are obtained. Then the flow analysis is carried out from two aspects: the back pressure and the inlet flow angle in variable working conditions. It is found that when the back pressure increased, raising the amount of aspiration can stabilize the shock distribution in the flow channel and the shock wave structure can be more stable in negative attack angle compared with the positive one.