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双转子发动机整机高涡转子动应力测试方法

钱正纬 郭仁飞 马立强 张岩松 孙国玉

钱正纬, 郭仁飞, 马立强, 等. 双转子发动机整机高涡转子动应力测试方法[J]. 航空动力学报, 2024, 39(9):20220996 doi: 10.13224/j.cnki.jasp.20220996
引用本文: 钱正纬, 郭仁飞, 马立强, 等. 双转子发动机整机高涡转子动应力测试方法[J]. 航空动力学报, 2024, 39(9):20220996 doi: 10.13224/j.cnki.jasp.20220996
QIAN Zhengwei, GUO Renfei, MA Liqiang, et al. Dynamic stress test method for high pressure turbine rotor of the dual-rotor aero-engine[J]. Journal of Aerospace Power, 2024, 39(9):20220996 doi: 10.13224/j.cnki.jasp.20220996
Citation: QIAN Zhengwei, GUO Renfei, MA Liqiang, et al. Dynamic stress test method for high pressure turbine rotor of the dual-rotor aero-engine[J]. Journal of Aerospace Power, 2024, 39(9):20220996 doi: 10.13224/j.cnki.jasp.20220996

双转子发动机整机高涡转子动应力测试方法

doi: 10.13224/j.cnki.jasp.20220996
详细信息
    作者简介:

    钱正纬(1984-),男,高级工程师,主要从事航空发动机强度测试技术研究。E-mail:qian1984914@163.com

    通讯作者:

    郭仁飞(1988-),男,高级工程师,博士,主要从事航空发动机强度测试技术研究。E-mail:guorenfei302088@163.com

  • 中图分类号: V235.13+3

Dynamic stress test method for high pressure turbine rotor of the dual-rotor aero-engine

  • 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。

     

  • 图 1  遥测技术原理图

    Figure 1.  Principle diagram of telemetry technology

    图 2  总体测试改装示意图

    Figure 2.  Schematic diagram of overall test modification

    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 4  遥测系统示意图

    Figure 4.  Schematic diagram of telemetry system

    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 6  双层引线空气导管结构图

    Figure 6.  Structural diagram of double-layer lead air duct

    图 7  空气导管第1阶模态振型图

    Figure 7.  First mode vibration shape diagram of air duct

    图 8  空气导管当量应力分布

    Figure 8.  Air duct equivalent stress distribution

    图 9  冷却流路示意图

    Figure 9.  Schematic diagram of cooling flow diagram

    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 13  不同供气压力冷却效果图

    Figure 13.  Cooling effect diagram of different air supply pressure

    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 17  自制特种高温应变计

    Figure 17.  Homemade special high temperature strain gauge

    图 18  应变计安装展示图

    Figure 18.  Strain gauge installation display

    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

    图 20  动测坎贝尔图

    Figure 20.  Campbell diagram for dynamic stress testing

    图 21  应力最大点瀑布图

    Figure 21.  Waterfall diagram of maximum stress point

    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
    200382673
    300367653
    400343623
    500328603
    750303533
    下载: 导出CSV

    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
    286.61.211.271.111.201.251.180.056
    661.61.581.581.411.521.491.570.068
    973.51.361.431.161.311.311.390.092
    1193.01.061.080.921.020.951.070.068
    1303.20.960.870.770.870.690.900.094
    1380.20.460.460.230.350.520.310.110
    下载: 导出CSV
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  • 收稿日期:  2022-12-30
  • 网络出版日期:  2024-04-30

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