Optimization Method And Numerical Analysis Of Axial Flow Compressor Blade Design

Blade profile design is the basis of axial flow compressor design.It is of great significance to study the optimization design method of compressor blade profile and improve the efficiency of optimization design.In this paper,two-dimensional axial compressor profile is taken as the research object to study the two-dimensional profile parameterization method.Based on the parameterization method,the blade profile optimization design method is given.In addition,the leading edge which is sensitive to the influence of blade profile performance is studied,and an asymmetric leading edge control method is proposed.Firstly,the method of superposition of mid-arc thickness was used to model the 2D profile.The distribution curves of mid-arc and thickness were constructed by NURBS equation.A 2D profile shape was controlled by 31 profile control parameters.Based on the profile modeling method,the two dimensional profile geometry analysis program and profile parametric fitting program are developed.The parametric modeling of different levels of a compressor blade is carried out.Under the condition of meeting certain error requirements,the CFD characteristics of the initial blade profile and the parametric blade profile are calculated.The results show that the modeling program can realize the parametric design of various blade profiles.Secondly,based on the parameterized modeling method in this paper,the influence of the modeling parameters used in the modeling method on the blade profile performance was studied.Subsequently,the leading edge modeling module in the modeling program was developed in depth,and the influence of leading edge shape change on blade profile performance was studied by increasing the control points and times of leading edge fitting curve.The asymmetric leading edge control method can be used to locally adjust the leading edge of the blade,and the performance of the blade can be improved by changing the local curvature near the leading edge.Then,taking a compressor stator blade as the initial blade profile,the blade modeling module,mesh division module,flow field calculation module and optimization calculation module were integrated into Isight software to optimize the variable Angle of attack of the blade profile.After numerical simulation verification,the total pressure loss coefficient of the optimized blade profile within the given Angle of attack range decreased.Finally,a sample library of leaf profile data is established by Latin hypercube random sampling and leaf profile modeling program.The flow field data of the two dimensional blades in the blade database were obtained through post-processing.The combination of POD and proxy model was used to reconstruct the flow field data of the blade,so as to realize the subsequent efficient aerodynamic optimization design of the blade.Based on this method,three proxy models are used to optimize the stator blades of a certain compressor with single objective at 0° Angle of attack,and the performance of the obtained blades is improved at 0°Angle of attack.