Research On Comprehensive Parameterization And Aerodynamic Optimization For Axial Compressor Blades

As an important part of the overall compressor design,the aerodynamic design of compressor blades is a highly complex process,which relies on the designer’s long-term knowledge and experience accumulation,as well as various design tools that have been gradually developed over the past few decades.With the continuous improvement of the overall performance requirements of the compressor,it is necessary to design improved blades in the shortest time.The design of compressor blades mainly needs to solve the time cost and effectiveness of optimizing the design of driving blades.This paper develops a comprehensive parameterization method for axial compressor blades.At present,most of the existing parameterization techniques are based on pure optimization to obtain the parameterization of blades.Few studies have performed blade parameterization from a design perspective.The parametric modeling technology developed in this paper combines blade geometry,characteristics and control parameters,which is an effective breakthrough method.The parameterization method is used to fit Rotor 37 blade,and adjust its related overall characteristic variables.It can be seen that the parameterization method has high accuracy in fitting prototype blades and has a strong ability to adjust the characteristics of the blade shape.The performance optimization of multi-point cascades has been carried out.The existing blade aerodynamic design research is mostly carried out for the design conditions,and then numerical simulation is used to analyze the performance of the blade under variable conditions.This may lead to the design of the blade profile difficult to meet the performance indicators of all working conditions.In this paper,the performance of the blade profile at different working conditions is taken into account in the optimization,which helps to improve the adaptability of the optimized blade profile to variable working conditions.For the subsonic blade profile,this paper optimized the UKG30.3 blade profile,the total pressure loss coefficient of the optimized blade profile at design point was reduced from 0.0202 to 0.0162,a decrease of 19.8%;the effective inlet angle range is increased from 15.8° to 18.1°,an increase of 14.6%.At the same time,the supersonic blade profile was optimized.Single-point and multi-point optimization were performed for the PAV-1.5 pre-compression blade profile.The single-point optimization results showed that the performance was greatly improved,and the total pressure loss coefficient decreased from 0.112 to 0.099,a decrease of 11.6%;the results of multi-point optimization improved the baseline performance more significantly.The lowest total pressure loss coefficient was decreased from 0.087 to 0.072,a decrease of 17.2%,and the working range of the inlet angle was expanded by 12%,the results show that multi-point optimization has greater advantages than single-point optimization.The optimization results of the abovementioned subsonic and supersonic blades prove the feasibility of the multi-objective optimization scheme in this paper,and also verify that the parameterization method has good adaptability.Finally,the three-dimensional blade of a compressor stator is optimized.After optimization,the compressor efficiency and pressure ratio under the design point conditions are increased by 0.56% and 0.16% respectively,achieving the optimization effect,which proves the feasibility of the optimization strategy of optimizing the quasi-three-dimensional airfoil first and then performing three-dimensional stacking This method greatly reduces the high computational cost required to directly optimize the three-dimensional blades.