基于飞行数据的涡扇发动机性能模型修正技术

Turbofan Engine Performance Model Correction Technology Based on Flight Data

针对传统模型修正方法难以满足部队实际工程应用的难题,提出一种基于飞行数据的发动机性能模型修正方法。该方法将发动机高压转子慢车以上转速分为4个区域,在每个区域内采用多工作点分析方法拓展方程组,解决由于实际飞行数据过少导致发动机性能模型修正系数求解中存在的欠定问题,并使用自适应差分进化算法求解修正系数。在修正的某发动机稳态模型基础上,考虑了发动机转子惯性、容积惯性、热惯性对过渡态计算的影响,进一步建立了该发动机部件级修正的过渡态模型。修正后的模型计算结果与实际飞行数据进行对比,结果表明:稳态点计算误差在1.70%以内,过渡态计算误差在5.5%以内,满足工程精度要求。

Aiming at the difficulty that the traditional model correction method cannot meet the actual engineering application of the army,an engine model correction method based on flight data was proposed.In this method,the range above the idle speed of the high-pressure rotor of the engine was divided into four regions,and the multiple operating points analysis method was used to expand the equation system in each region,so as to solve the underdetermined problem in the calculation of the correction coefficient of the engine performance model due to too little actual flight data.The correction coefficients were solved by the adaptive differential evolution algorithm.Based on the modified steady-state model of an engine,the effects of the rotor inertia,volume inertia and thermal inertia of the engine on the calculation of the transition state were considered,and a modified transition state model of the engine component level was further established.Comparing the calculated results of the revised model with the actual flight data,the results show that the calculation error of the steady state point is within 1.70%,and the calculation error of the transition state is within 5.5%,which meets the engineering accuracy requirements.