| Citation: | YU Xiangyu, LIU Zhansheng, HE Peng, et al. Experimental research on thermal bow deformation and dynamics of aero-engine rotor[J]. Journal of Aerospace Power, 2025, 40（8）：20230188 doi: 10.13224/j.cnki.jasp.20230188
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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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