与涡轮叶片一体化集成的AlN薄膜基于温度记忆效应测温技术研究

In the process of aero-engine development in China, due to the serious lack of basic data such as surface temperature of turbine blade and other high temperature components, the process of aero-engine design and manufacture in China is seriously hindered. It is urgent to develop the basic theory and monitoring method for accurate measurement of surface temperature and its distribution of aero-engine turbine blades and other high temperature components. Aiming at the research frontier of aero-engine fault diagnosis in this major research project, the basic scientific research on turbine blade surface temperature measurement is carried out. In our previous study, we found that the phase structure parameters of AlN film have memory effect on the temperature. Therefore, we innovatively proposed to deposit AlN film on the surface of turbine blade to form a temperature-sensitive film integrated with the blade surface. The temperature memory effect of the phase structure parameters of AlN ceramic film was used to explore the new monitoring method for accurate measurement of the turbine blade surface temperature and its distribution. It contributes to the core scientific problems of the perception and intelligent diagnosis and prediction principle of the state information such as the surface temperature and its distribution of the turbine blades and other high temperature components.

在我国航空发动机研制过程中，由于涡轮叶片等热端部件表面温度等基础数据的严重缺乏，严重阻碍了我国航空发动机设计研制的进程，急需开展航空发动机涡轮叶片等热端部件表面温度及其分布准确测试的基础理论和监测方法研究。本项目针对本重大研究计划中的航空发动机故障诊断研究前沿，开展涡轮叶片表面温度测量基础科学问题研究。我们前期研究发现，AlN薄膜相结构参数对温度具有记忆效应，因此，我们创新性提出在涡轮叶片表面沉积AlN薄膜形成与叶片一体化集成的温度敏感薄膜材料，利用AlN陶瓷薄膜的相结构参数的温度记忆效应，探索涡轮叶片表面温度及其分布准确测量的新方法，为涡轮叶片等热端部件表面温度及其分布等状态信息的感知与智能诊断预测原理的核心科学问题做出贡献。

本项目针对航空发动机故障诊断研究前沿，开展涡轮叶片温度测量基础科学问题研究，瞄准我国航空发动机研发重大战略需求中涡轮叶片等热端部件表面温度及其分布等核心状态信息的感知与智能诊断预测原理核心科学问题开展研究工作。利用AlN陶瓷薄膜的相结构参数的温度记忆效应，提出在涡轮叶片表面沉积AlN薄膜形成与叶片一体化集成的温度敏感薄膜材料，通过标定、判读方法和发动机相关试验应用技术研究，建立涡轮叶片表面温度及分布的AlN薄膜测温方法，实现涡轮叶片表面温度及其分布的准确测量。为航空发动机涡轮叶片表面温度及其分布的准确测量提供新的思想和方法，提升我国航空发动机故障诊断基础研究的原始创新能力和国际影响力。通过系统研究，解决了温度对AlN薄膜相结构参数影响机制和涡轮叶片表面AlN薄膜高温应力释放机制等科学问题，突破了涡轮叶片表面平坦化处理和纳米柔性自缓冲层热应力释放等关键技术，制备出了弱C轴择优取向AlN薄膜，通过标定、判读方法和软件及应用相关技术研究，建立了涡轮叶片表面温度及分布的 AlN 薄膜测温方法。判读温度范围为700-1200℃，判读误差小于5%。本项目授权国家发明专利1件，发表论文4篇，登记软件著作权1件，培养毕业硕士研究生2名，在读博士研究生1名。