中文摘要：

考虑到目前暂无法实现机载条件下高压涡轮前温度直接、可靠的测量,提出一种用于涡扇发动机高压涡轮前温度估计的方法.基于涡扇发动机的能量守恒原理,建立高压涡轮前温度与气路参数的热力学关系,进而推导出高压涡轮前温度的6个估计模型.将各温度模型中不易测量的参数以整体的形式作为温度模型系数,并利用某涡扇发动机性能仿真模型建立温度模型系数与可测状态参数的多项式关系,最终确立高压涡轮前温度的组合估计模型.验证结果表明：组合估计方法在发动机健康及性能衰退状态下都具有较高的精度,其性能最好模型的方均根误差不超过1%.与已有线性拟合、神经网络等方法的对比也表明组合估计方法不论在精度还是性能稳定性方面都具有明显优势.

英文摘要：

Considering that direct and reliable measurement of high pressure turbine in let temperature on board is not feasible at present, a new assembled method for estimation of turbofan engine high pressure turbine inlet temperature was proposed. Based on the energy conservation principles of a turbofan engine, thermodynamic equations between high pressure turbine inlet temperature and other gas path parameters were presented, thus six esti mation models of high pressure turbine inlet temperature were derived. Unmeasured parameters of these models were defined as temperature model coefficients as a whole, which were fitted with measured engine power setting parameters using an engine performance model. Validation results show that assembled estimation models have good precision for both health and deteriorative engines, and the mean squared error of its best performance model is not above 1 %. Moreover, by comparison with linear and neural network fitting methods, the assembled estimation method has a clear advantage in precision and stability.