涡扇发动机高压涡轮前温度组合估计方法

发布时间：2018-08-02 16:30

【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.
[Abstract]:Considering that it is not possible to measure directly and reliably the front temperature of high pressure turbine under airborne condition, a method for estimating the front temperature of high pressure turbine in turbofan engine is presented. Based on the energy conservation principle of turbofan engine, the thermodynamic relationship between the front temperature of high pressure turbine and the gas path parameters is established, and six estimation models of the front temperature of high pressure turbine are deduced. The parameters which are not easy to measure in each temperature model are taken as the temperature model coefficients in the form of a whole, and the polynomial relationship between the temperature model coefficients and the measurable state parameters is established by using a turbofan engine performance simulation model. Finally, the combined estimation model of the front temperature of high pressure turbine is established. The results show that the combined estimation method has high accuracy under the condition of engine health and performance decline, and the square mean root error of the best performance model is less than 1. The comparison with the existing methods such as linear fitting and neural network also shows that the combined estimation method has obvious advantages in terms of accuracy and performance stability.
【作者单位】：海军航空工程学院飞行器工程系;中国人民解放军91331部队;
【基金】：国家自然科学基金(51505492,51375490) 泰山学者工程专项经费海军航空工程学院研究生创新基金
【分类号】：V235.13

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