基于参数匹配的航空发动机飞行性能评估技术研究  

Research on Flight Performance Estimation of Aircraft EngineBased on Parameter Matching Technology

作　　者：刘旭[1] 任丁丁 LIU Xu;REN Dingding(Chinese Flight Test Establishment,Xi′an 710089,Shaanxi,China)

机构地区：[1]中国飞行试验研究院,陕西西安710089

出　　处：《工程与试验》2024年第2期48-51,共4页Engineering and Test

摘　　要：本文提出了一种基于参数匹配的发动机性能评估模型建立方法,在不依赖部件特性的情况下,以发动机可测截面参数作为输入,建立影响系数矩阵,利用罚函数法求解非直接测量参数的极小二范数解,建立了考虑性能衰减影响的发动机性能评估模型。以某型大涵道比涡扇发动机仿真模型为应用对象,结果显示,在全包线内的典型工作状态下,仿真数据与评估模型计算数据相对误差小于4.5%,表明性能评估模型建立方法是正确的,所建立的性能评估模型可满足工程使用要求。Based on the parameter matching technology,a gas turbine performance estimation method is developed which has the advantage that no component characteristic maps are required.Influence coefficient matrix for gas turbine engines by using gas path measurements is introduced and the performance parameters which cannot be directly measured is optimized by using the genetic algorithm and sequential unconstrained minimization technique.The developed method is applied to the performance estimation of a gas turbine running at different altitudes and Mach numbers with and without degradation by using simulated gas path measurements to test the effectiveness of the method.Taking the high bypass ratio turbofan engine as an example,the results of the investigation indicate that the model proposed in the paper are in good agreements with the simulated data,and the relative error is less than 4.5%,which shows that the performance estimation model is correct,and the method can be applied to the performance estimation of different types of gas turbine engines.

关 键 词：性能评估 大涵道比涡扇发动机 参数测量 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]