Experimental research on thermal bow deformation and dynamics of aero-engine rotor
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摘要:
针对某航空发动机高压转子进行热弯曲变形及动力学试验。通过搭建空间矩阵分布式加热装置模拟发动机停机冷却时的非均匀温度环境，测试不同温度下转子温度分布、结构变形及振动特性。结果表明：长径比最小的涡轮盘温度最高，温差最大，冷却速率最快但温差却长期存在；压气机轮盘测点温度及温差均较小，且当结构传热量大于和外界的辐射及对流换热量时，温差消失最快；转子热弯曲变形由自身热膨胀及弯曲挠性变形叠加形成，轮盘变形以热膨胀为主，在温降阶段先下降后上升，轴段以挠性变形为主；转子发生热弯曲后临界转速发生偏移，在一阶临界转速附近区间振动增大，且随着冷却或运行时间增长而降低。该结果可为发动机结构设计及热弯曲识别提供依据。
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关键词:
- 转子热弯曲 /
- 空间矩阵分布式加热装置 /
- 温度分布 /
- 结构变形 /
- 振动特性
Abstract:The thermal bending deformation and dynamic tests of the high pressure rotor of an aeroengine were carried out. The temperature distribution, structural deformation and vibration characteristics of the rotor at different temperatures were tested by constructing a distributed heating device of space matrix to simulate the non-uniform temperature environment of the engine when it was shut down and cooled. The results showed that the turbine disk with the smallest aspect ratio had the highest temperature, the largest temperature difference, and the fastest cooling rate, but the temperature difference existed for a long time. The temperature and temperature difference of the measuring point of the compressor wheel was small, and when the heat transfer of the structure was greater than the radiation and convective heat exchange with the outside world, the temperature difference disappeared the fastest. The hot bending deformation of the rotor was formed by superposition of thermal expansion and flexural deformation. The disk deformation was dominated by thermal expansion, which decreased first and then rose in the temperature drop stage, and the shaft segment was dominated by flexural deformation. The critical speed of the rotor deviated after thermal bending, and the vibration increased near the first critical speed, and decreased with the cooling or running time. The results can provide a basis for engine structure design and thermal bending identification.
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图 5 工况3截面温度及温差随温度变化图
Figure 5. Diagram of temperature and temperature difference variations for each cross section in Case 3
图 6 不同工况截面温差对比图
Figure 6. Diagram of temperature difference contrast for each cross section in different cases
图 10 工况8热弯曲转子与正常转子振动对比
Figure 10. Diagram of thermal bow and normal rotor in contrast for Case 8
图 12 工况10热弯曲转子与正常转子振动对比
Figure 12. Diagram of thermal bow and normal rotor in contrast for Case 10
表 1 转子热弯曲变形试验方案
Table 1. Thermal bow deformation test scheme
工况 加热瓦温度/℃ 1 100 2 150 3 200 4 250 5 300 
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表 2 转子热弯曲动力学试验方案
Table 2. Thermal bow dynamics test scheme
工况 加热瓦温度 启动条件 6 室温 直接 7 200 ℃ 自然冷却10 min后 8 200 ℃ 自然冷却20 min后 9 200 ℃ 自然冷却30 min后 10 200 ℃ 强制冷却20 min后
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表 3 不同工况下振动对比（
2892 r/min）Table 3. Contrast of vibration in different cases（
2892 r/min）工况 S0-X
方向/μmS0-Y
方向/μmS5-X
方向/μmS5-Y
方向/μm6 63 64 102 64 7 154 147 214 186 8 91 92 142 119 9 73 75 123 94 10 65 68 107 85
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