Dynamic stress test method for high pressure turbine rotor of the dual-rotor aero-engine
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摘要:
设计了一种基于“遥测+长跨距引线导管”的双转子涡扇发动机整机高压涡轮转子动应力测试机构,并结合轴间遥测冷却仿真设计及定制化的高温应变计，在国内完成了双转子涡扇发动机整机高压涡轮转子动应力测试，获取了整机状态下全转速范围内高压涡轮转子叶片的动应力数据。测试结果表明：该设计的动应力测试机构及其冷却方法有效解决了双转子发动机整机高压涡轮转子测试信号引出困难、信号传输稳定性差等问题，定制化的高温应变计及其安装防护技术克服了整机高压涡轮叶片上极端高温、气流冲刷、空间狭小等恶劣安装条件。该测试方法可为相关测试任务提供重要借鉴。
Abstract:A high pressure turbine rotor dynamic stress test method of “telemetry+long span lead wire pipe” was designed for the dual-rotor turbofan aero-engine in the whole engine state. Combined with the simulation design of telemetry cooling amid the dual rotor and customized high temperature strain gauge, the dynamic stress test of the high pressure turbine rotor of the dual-rotor turbofan aero-engine was completed for the first time in China, and the dynamic test data of the high pressure turbine rotor blades in the full speed range and the whole engine state were obtained. The test results showed that the test mechanism and its cooling method designed can effectively solve the problems such as the difficult test signal extraction and poor signal transmission stability of the high pressure turbine rotor in the whole dual-rotor engine, the customized high temperature strain gauge and its installation and protection technology can effectively overcome the harsh installation conditions of the high pressure turbine blades on the whole machine, such as extreme high temperature, airflow erosion and narrow space. The method proposed can provide an important reference for the relevant test tasks.
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图 3 遥测转子安装环腔结构示意图
Figure 3. Schematic diagram of the telemetry rotor installation ring cavity structure
图 5 遥测电路封装结构示意图
Figure 5. Schematic diagram of the packaging structure of the telemetry circuit
图 10 最大起飞状态遥测装置温度场云图
Figure 10. Cloud map of the temperature field of the telemetry device in the maximum take-off state
图 11 整机高压涡轮转子动应力测量试车历程图
Figure 11. Test course of dynamic stress measurement on high pressure turbine rotor in the whole engine state
图 12 最大起飞状态末高压涡轮盘组件温度场
Figure 12. Temperature field of high-pressure turbine disk assembly at the end of maximum take-off state
图 14 高涡叶片在不同径向高度截面上温度示意图
Figure 14. Temperature diagram of high vortex blade at different radial height sections
图 15 高温应变计结构及安装工艺示意图（单位：mm）
Figure 15. Schematic diagram of high temperature strain gauge structure and installation process （unit: mm）
图 16 各冷却位置实测温度示意图
Figure 16. Schematic diagram of the measured temperature at each cooling position
图 19 应变计灵敏度系数标定示意图
Figure 19. Schematic diagram of calibration diagram of gauge factor
表 1 仿真计算结果
Table 1. Simulation calculation results
压力/kPa 遥测温度/K 焊点温度/K 200 382 673 300 367 653 400 343 623 500 328 603 750 303 533 
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表 2 各温度下灵敏度系数标准差
Table 2. Standard deviation of gauge factor at each temperature
温度/K 灵敏度系数 灵敏度系数
标准差应变计1 应变计2 应变计3 应变计4 应变计5 应变计6 286.6 1.21 1.27 1.11 1.20 1.25 1.18 0.056 661.6 1.58 1.58 1.41 1.52 1.49 1.57 0.068 973.5 1.36 1.43 1.16 1.31 1.31 1.39 0.092 1193.0 1.06 1.08 0.92 1.02 0.95 1.07 0.068 1303.2 0.96 0.87 0.77 0.87 0.69 0.90 0.094 1380.2 0.46 0.46 0.23 0.35 0.52 0.31 0.110
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