基于试飞数据的涡轴发动机性能建模技术

为了实现军用涡轴发动机在装机状态下的虚拟预测试飞，通过罚函数法求解超定非线性方程组的最小二乘解，并采用回归分析对部件特性耦合因子进行曲线拟合，优化基准稳态模型，构建了某型涡轴发动机稳态性能计算模型；在此基础上，应用发动机加减速试飞数据，综合考虑部件容腔效应、转动部件的转子动力学和高温部件的传热效应，开发了涡轴发动机部件级过渡态性能计算模型。采用该模型对包线范围内不同工况的发动机稳态和过渡态工作过程进行了仿真预测，结果表明：与真实装机试验结果相比，发动机各工作参数的稳态预测精度在4.2%以内，过渡态预测精度在9.2%以内，满足工程精度要求。该模型能够满足虚拟预测试飞的技术需求，对涡轴发动机的设计、试飞和使用具有重要作用。

Performance Modeling Technique of Turboshaft Engine Based on Flight Experimental Data

In order to realize the virtual predictive flight test of military turboshaft engines under installed condition, the steady-state performance calculation model of turboshaft engine was constructed by solving the least square solution of overdetermined nonlinear equations with penalty function method, using regression analysis to fit the curve of the component characteristics coupling factors, and optimizing the baseline steady state model. Then considering the volume effect, rotor dynamics of rotating parts, and heat transfer effect of high temperature parts, the component-based transient performance model of the turboshaft engine was developed, with the support of the acceleration and deceleration experimental data. This model was used to simulate the steady state and transient state under some engine working conditions in the flight envelope. Compared with the real installed test results, the results show that the steady-state prediction accuracy of engine parameters is less than 4.2% and the transition state prediction accuracy is less than 9.2%. The model can meet the technical requirements of virtual predictive flight test, and plays an important role in the design, experimental and service of turboshaft engines.