Research Of Highly Loaded Compressor Optimization Design Method

Design a compressor with highly load,highly efficiency,and wide stability margin is an important direction for the future aeroengine compressor study.However,the increase of the compressor load will improve the compressor design difficulty.The introduction of the optimized design method can greatly improve the design efficiency of the high-load compressor and improve the aerodynamic performance of the compressor.In this paper,Application research of optimization design method in highly loaded compressor has a deeply research,and the action mechanism of optimal design scheme in each link of the highly loaded compressor design has a deeply research.The aim of this paper is to establish a complete and efficient optimization design system for the future aerodynamic design of high-load compressor,to explore the limit of aerodynamic design of high-load compressor through the combination of optimization design method,and provide technical reserves for future high-load compressor aerodynamic design.Firstly,optimization design method is researched deeply.Based on the study on the standard artificial bee colony algorithm,a new improved artificial bee colony algorithm is proposed,and comparative analysis of the new improved artificial bee colony algorithm with genetic algorithm,particle swarm algorithm,differential evolution algorithm,standard artificial bee colony algorithm and quick artificial bee colony is made in the condition of low-dimension,high-dimension,and combined with CFD program.The new improved artificial bee colony(DQABC)has more advantages than other optimization algorithms based on ensuring high accuracy of solution,especially in the condition of high-dimension and complex-flow,and the convergence rate is superior to other optimization algorithms especially.Secondly,a new optimization method of two-dimensional high turning angle airfoil is proposed by using the new optimization algorithm.This optimization design method combines the numerical simulation with the cascade wind tunnel experiment resulting to design the high turning angle airfoil with high aerodynamic performance.On the basis of this optimization design method,a new optimization design method of high turning angle airfoil with wide operating range is developed,and the aerodynamic characteristics of the high turning angle airfoil with wide operating range are researched.The research finds the shape of the leading edge and the distribution of the load have an important influence on the aerodynamic performance of high turning angle airfoil with wide operating range.The shape of the airfoil leading edge can affect transitional position of the boundary layer and the accumulation of the boundary layer in the front of the airfoil.The aerodynamic configuration of moving load backword appropriately for high turning angle airfoil will achieve a great promotion on the aerodynamic performance of the large positive incidence angle,but will a little negative effect on the performance of design point.Thirdly,an optimazation design method of the high load cascade considering the endwall effect is developed.This optimization design method includes three kinds of traditional endwall modeling methods: bowed cascade,endbend cascade,and leading edge strake cascade.Two kinds of new endwall modeling methods which are bowed cascade combined with leading edge strake cascade and endbend cascade combined with leading edge strake cascade are proposed,and the flow influence of these endwall modeling methods is analyzed.The optimal bowed cascade combined with leading edge strake cascade has the excellent aerodynamic performance,and the optimal bowed cascade has the poorest aerodynamic performance,while its aerodynamic performance is far superior to the straight cascade cascade.The height of the low energy fluid radial migration and the scale of the vortex radial migration have a great effect on the aerodynamic performance.The optimal bowed cascade combined with leading edge strake cascade is superior to the other cascades in both aspects.Fourthly,three-dimensional CDFS optimization design method is developed,and the new aerodynamic design method of CDFS is proposed.In this optimization design method,the aerodynamic performance of two modes is coupling considered,and multi-working conditions composite optimization of lean and sweep under the stage environment is studied.The designed CDFS which contains outlet axial outgassing and unadjustable stator can reach the efficiency of 88.36% and stability margin of 18.5% in the single bypass mode and the efficiency of 86.66% and stability margin of 15.1% in the double bypass mode,and the CDFS stall mechanism and aerodynamic performance influence of the composite optimization of lean and sweep are studied.In the design point the performance of the CDFS rotor depends on the matching of the relative airflow angle under two modes,especially the matching of the rotor tip.In the single bypass mode the interaction of the rotor tip leakage vortex and the shock wave cause the flow instability,and in the double bypass mode large scale leakage vortex of the stator hub can cause the airflow obstruction of the stator.The aerodynamic configuration of backword sweep in the rotor hub and forword sweep in the rotor tip combined with positive bow can reduce the influence of vortex leakage and secondary leakage,and effectively improve the aerodynamic performance of the near-stall point in the single bypass mode,and The aerodynamic configuration of backword sweep in the stator hub and forword sweep in the stator tip combined with positive bow in the stator hub and negative bow in the stator tip can restrain the formation of the leakage vortex and effectively improve the stability margin of the fan in the double bypass mode.Finally,the optimization design method of the aspirated airfoil is studied comprehensively,in details,and deeply.The design of high turning angle aspirated airfoil is completed,and the optimization design result is verified by the cascade wind tunnel experiment.High subsonic aspirated airfoil with the diffusion factor of 0.72 which is the airfoil has the peak load is designed successfully.To explore the limit of aerodynamic design of high-load compressor,anultra highly loaded multi-slot aspirated airfoil with the turning angle of 75° and the diffusion factor of 0.8 is designed,and in the process of cascade wind tunnel experiment,the intermediate slot is used firstly to improve the strength of the aspirated airfoil.The aspirated airfoil optimization design method in the condition of low-Reynolds number is studied,and aerodynamic characteristic of the aspirated airfoil in the condition of low-Reynolds number is summarized simultaneous.The special phenomenon with the interaction of shock wave,boundary layer and aspiration in the supersonic aspirated airfoil is studied.