基于改进粒子群的航空发动机部件特性修正

Aeroengine Component Characteristic Correction Based on Improved Particle Swarm Optimization

涡桨发动机采用定转速工作方式,试车数据集中分布在几个不同转速工作状态附近。为利用大量分布不均匀的试车数据进行部件特性修正,提出一种改进参数的模拟退火粒子群算法,解决多工作点性能匹配时易陷入局部最优的问题,提高涡桨发动机部件特性修正精度。针对以往依靠经验和试错确定修正系数定义域时效率低下,且限制了算法搜索能力的问题,提出一种根据相邻等转速线确定非设计点区域修正系数上下限的方法。模型计算结果与实验数据对比表明,修正后模型各参数平均误差从3.95%降低到0.89%,最大误差从11.32%降低到2.37%,精度明显提高。

Turboprop engine adopts constant speed working mode,and the test data are distributed centrally around several different speed working states.In order to make use of a large number of unevenly distributed test data for component characteristic correction,a simulated annealing particle swarm optimization algorithm with improved parameters is proposed to solve the problem of easily falling into local optimum when performance matching at multiple working points,and improve the characteristic correction accuracy of turboprop engine components.In order to solve the problem of low efficiency and limited searching ability of the algorithm when determining the correction coefficient domain by experience and trial and error in the past,a method is proposed to determine the upper and lower limits of the correction coefficient in the region of non-design points according to adjacent equal speed lines.The comparison between the calculated results and the experimental data shows that the average error of each parameter of the modified model decreases from 3.95% to 0.89%,and the maximum error decreases from 11.32% to 2.37%.The accuracy is obviously improved.