Liang Xiaorui, Cheng Wenhua, Li Shuang, Hu Dan, Tan Qiulin
State Key Laboratory of Dynamic Measurement Technology, North University of China, Taiyuan, 030051, China.
Key Laboratory of Micro/nano Devices and Systems, Ministry of Education, North University of China, Tai Yuan, 030051, China.
Heliyon. 2024 Sep 25;10(19):e38417. doi: 10.1016/j.heliyon.2024.e38417. eCollection 2024 Oct 15.
As aero-engines operate under extreme conditions such as high temperatures and speeds, the effectiveness of the engine tends to decrease. Therefore, real-time vibration monitoring of such structures is essential to ensure flight safety. However, the sensors used in the control system are prone to interference, thus leading to ineffective monitoring and eventually reducing the service life of the equipment. Therefore, in this study, a shear vibration sensor for real-time structural monitoring at 750 °C is designed and produced using a Langasite (LGS) crystal. Further, the high-temperature performance of the sensor is examined in the frequency, acceleration, and temperature ranges of 80-1000 Hz, 0.5-5g, and 30-750 °C, respectively. Its linearity is less than 1 %, which meets the application requirements of high-temperature piezoelectric vibration sensors. The average sensitivity of the sensor over the entire temperature range is 0.074 V/g. The sensor has good viability and can be used for testing in high-temperature environment applications as the sensitivity fluctuates by less than 2 % at different temperature points when applied to the same frequency. Furthermore, a temperature-vibration cross-decoupling approach is proposed to determine the acceleration value following temperature demodulation. The highest inaccuracy with respect to the reference acceleration is 4.54 %. Sensors also have a small size, are easy to install, and can maintain high reliability in harsh environments, playing an essential role in health assessment, fault prediction, and diagnosis of engines and other components. Therefore, the developed LGS acceleration sensor offers a promising alternative for real-time monitoring of structures in high-temperature environments, including aero-engines.
由于航空发动机在高温和高速等极端条件下运行，发动机的效率往往会降低。因此，对这类结构进行实时振动监测对于确保飞行安全至关重要。然而，控制系统中使用的传感器容易受到干扰，从而导致监测无效并最终缩短设备的使用寿命。因此，在本研究中，使用硅酸镓镧（LGS）晶体设计并制作了一种用于750°C实时结构监测的剪切振动传感器。此外，分别在80 - 1000Hz、0.5 - 5g和30 - 750°C的频率、加速度和温度范围内对该传感器的高温性能进行了测试。其线性度小于1%，满足高温压电振动传感器的应用要求。该传感器在整个温度范围内的平均灵敏度为0.074V/g。该传感器具有良好的适用性，在应用于相同频率时，由于灵敏度在不同温度点的波动小于2%，因此可用于高温环境应用测试。此外，还提出了一种温度 - 振动交叉解耦方法来确定温度解调后的加速度值。相对于参考加速度的最高误差为4.54%。该传感器尺寸小、易于安装，并且在恶劣环境中能够保持高可靠性，在发动机及其他部件的健康评估、故障预测和诊断中发挥着重要作用。因此，所开发的LGS加速度传感器为包括航空发动机在内的高温环境下结构的实时监测提供了一种很有前景的替代方案。
