基于遗传算法寻优均匀设计航空发动机高空模拟试验研究  

Research on high altitude simulation test of aero-engine based on genetic algorithm optimization uniform design

作　　者：崔佳航 李江红[1] 赵伟[2] 翟雄飞 刘伟 陈超[1] CUI Jiahang;LI Jianghong;ZHAO Wei;ZHAI Xiongfei;LIU Wei;CHEN Chao(Northwestern Polytechnical University,Xi’an 710072,China;AECC Sichuan GAS Turbine Establishment,Chengdu 610599,China)

机构地区：[1]西北工业大学,西安710072 [2]中国燃气涡轮研究院,四川绵阳610599

出　　处：《兵器装备工程学报》2023年第9期285-289,共5页Journal of Ordnance Equipment Engineering

基　　金：中国航发四川燃气涡轮研究院稳定支持项目(GJCZ-0046-20)。

摘　　要：针对航空发动机高空模拟试验因素多、水平数多等特点,已有均匀设计表均匀性不好、效率不高,极大制约了均匀设计在航空发动机高空模拟试验领域的应用。为了提高均匀设计效率,摆脱使用表的限制,生成均匀性更好的设计表,提出了混合偏差下均匀设计构造法的整数编码遗传算法优化方法,与门限接受法进行对比,得到优化方法的均匀性更好,最后通过发动机高空台最优匹配规律模拟试验,得到寻优估计误差均小于1%,同时试验优化率达到99.923%,验证了提出的试验设计方法的高效性和准确性。At present,the number of existing uniform design tables is small,and the numbers of levels and factors of each table are small.For the characteristics of aero-engine high-altitude simulation test with many factors and levels,the uniformity of existing uniform design tables is not good and the efficiency is not high,which greatly restricts the application of uniform design in the field of aero-engine high-altitude simulation test.To improve the efficiency of uniform design and get rid of the limitation of using the table and generate a design table with better uniformity,the integer coding genetic algorithm optimization method of the uniform design construction method under mixed deviation is proposed.Compared with the threshold acceptance method,the uniformity of the optimization method is obtained better.Finally,through the simulation test of the influence of the adjustable guide vane and the optimal matching law of the engine high altitude table air start,the estimation error of the optimization search is obtained to be less than 1%,while the test optimization rate reaches 99.923%,which verifies that the test optimization rate is better than the threshold acceptance method.The design method proposed is proven to be efficient and accurate.

关 键 词：均匀设计 遗传算法 发动机高空模拟试验 好格子法 混合偏差 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]