Optimal Design Of Compressor Blade Based On Digital-Model Parameteraztion

In the design process of the compressor,there is a time consuming problem of repeatedly modifying the number of modules and generating the calculation grid.Based on the advantage of parameterized expression of digital module and the attempt of combining industrial design with computer aided design,a software for compressor blade design and optimization is designed.The main contents of this paper are divided into the following four aspects:First,according to the relevant background knowledge,it can be seen that the one-dimensional design and through-flow design can obtain the data of the axial compressor blades and blades.Therefore,the leaf type first uses any polynomial method to obtain the mid-arc,and then uses the direct parameterization method to obtain the leaf-type number model;the leaf blade is numerically modeled using the stacking-line-curve parameterization method.Secondly,the key computational techniques in the compressor design process are studied.The one-dimensional calculation uses flow continuity equations,energy equations,the first law of thermodynamics and the generalized Bernoulli equation.The throughflow calculation uses the curvature streamline method.The calculation results show that the total pressure ratio and total efficiency of the primary axial compressor are 1.4848 and 83.35%.When the full three-dimensional calculation of the compressor is performed,the required quality is better.The grid is produced by the customized O-type topology,which can not only ensure the quality of the calculation grid,but also facilitate the optimization of the grid quality.Using single-channel calculation in grid computing can greatly shorten the grid generation time and calculation time,and the calculation accuracy and the full-ring calculation gap is smaller.thridly,genetic algorithm is used to optimize one-dimensional design.One-dimensional design adopts total pressure ratio and total efficiency as targets,and flow coefficient,total inlet pressure coefficient,inlet guide vane coefficient,and load coefficient as design parameters.When the design parameters take 1.01,0.96,0.96,and 0.32,respectively,The total pressure ratio and the total efficiency increase the most;At the same time,the design of circulation flow design,the derailment angle,the rotor blade efficiency,the leading edge radius and the trailing edge radius are selected as the design parameters,and the design parameters are selected as 2%,1%,and 0.96 resp-ectively.At 10%,5%,the total pressure ratio and total efficiency increase the most.Finally,relying on the existing technical reserves of the China Aero-dynamics Research and Development Center,using programming language C++to implement one-dimensional design data and flow design input,through-flow design data and parametric digital-analog generation,digital analogue and grid generation,etc.The interface functions,thus completing the main functions of the Aeroengine Design/Assessment System Software Platform(AIFS),namely the automation design and optimization of the compressor blades.The numerical calculation of the compressor blades that survived the software results in good aerodynamic performance and good robustness of the software.