航空发动机转子热弯曲变形及动力学试验研究

The thermal bending deformation and dynamic test 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 show that the turbine disk with the smallest aspect ratio has the highest temperature，the largest temperature difference，and the fastest cooling rate，but the temperature difference exists for a long time. The temperature and temperature difference of the measuring point of the compressor wheel are small，and when the heat transfer of the structure is greater than the radiation and convective heat exchange with the outside world，the temperature difference disappears the fastest. The hot bending deformation of the rotor is formed by superposition of thermal expansion and flexural deformation. The disk deformation is dominated by thermal expansion，which decreases first and then rises in the temperature drop stage，and the shaft segment is dominated by flexural deformation. The critical speed of the rotor deviates after thermal bending，and the vibration increases near the first critical speed，and decreases with cooling or running time. The results can provide a basis for engine structure design and thermal bending identification.