考虑高压涡轮性能非确定的航空发动机鲁棒设计  

Robust optimization in aero-engine design considering uncertainty of high-pressure turbine performance

作　　者：王林 潘旭 杨锟 WANG Lin;PAN Xu;YANG Kun(Shanghai Engineering Research Center of Civil Aero Engine,Commercial Aircraft Engine Company Limited,Aero Engine Corporation of China,Shanghai 200241,China)

机构地区：[1]中国航发商用航空发动机有限责任公司上海商用飞机发动机工程技术研究中心,上海200241

出　　处：《航空动力学报》2024年第4期289-298,共10页Journal of Aerospace Power

基　　金：国家科技重大专项(HT-J2019-Ⅰ-0006-0006)。

摘　　要：为了降低制造过程中非确定性因素对航空发动机总体性能的影响,通过在设计阶段考虑高压涡轮性能的非确定性,构建鲁棒优化设计模型来优化总体性能的设计方案,使用蒙特卡洛仿真量化非确定性的影响,并开发了相应的全局优化算法进行求解。数值实验的结果验证了鲁棒设计模型的优势,与传统确定性设计方法相比,在高压涡轮性能非确定的情况下,鲁棒设计模型获得的方案能平均减少15.97%的总体性能离散程度,具有较优鲁棒性。In order to reduce the impact of uncertain factors in manufacturing on the overall performance of aero-engines,a robust design model was constructed by considering the uncertainty of highpressure turbine performance in the design stage.Monte Carlo simulation was used in this model to quantify the effect of uncertainty.A global optimization algorithm was developed to solve the robust design model.Numerical results validated the advantages of the robust design model.Its optimal solution can reduce the variability of the engine performance by an average of 15.97%,which showed better robustness in uncertain environment than the solution obtained by generic deterministic design method.

关 键 词：总体性能 非确定性 鲁棒设计 蒙特卡洛仿真 最优化 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]