陶瓷基复合材料高温力学性能测试系统开发  

Development of High-Temperature Mechanical Properties Testing System for Ceramic Matrix Composites

作　　者：李小可 LI Xiaoke(AECC Hunan Power Machinery Research Institute,Zhuzhou 412002)

机构地区：[1]中国航发湖南动力机械研究所,株洲412002

出　　处：《现代制造技术与装备》2025年第3期1-3,共3页Modern Manufacturing Technology and Equipment

摘　　要：针对航空发动机涡轮导向叶片所用的陶瓷基复合材料的高温力学性能测试需求,设计开发一套测试系统。该系统由温度控制、载荷施加、数据采集和控制系统4个功能模块组成,采用比例-积分-微分(Proportion Integral Differential,PID)温度控制算法和模糊控制策略,实现了1600℃高温环境下的精确测试。对C/SiC复合材料样件的测试结果表明,系统在1600℃、300 MPa工况下的温度控制精度为±2.0℃,载荷控制精度为0.95%,应变测量精度为0.98με,数据采集稳定性达99.89%,满足用于涡轮导向叶片的陶瓷基复合材料的高温力学性能评价要求。A testing system for high-temperature mechanical properties of ceramic matrix composites used in aero-engine turbine guide blades is designed and developed.The system is composed of four functional modules:temperature control,load application,data acquisition and control system.The Proportion Integral Differential(PID)temperature control algorithm and fuzzy control strategy are used to achieve accurate testing under 1600℃high temperature environment.The test results of C/SiC composites show that the temperature control accuracy of the system is±2.0℃,the load control accuracy is 0.95%,the strain measurement accuracy is 0.98με,and the data acquisition stability is 99.89%at 1600℃and 300 MPa.It meets the requirements of high temperature mechanical properties evaluation of ceramic matrix composite materials used for turbine guide blades.

关 键 词：陶瓷基复合材料 高温力学性能测试 涡轮导向叶片 航空发动机 

分 类 号：V232.2[航空宇航科学与技术—航空宇航推进理论与工程]