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Influence of Excitation Conditions on the Forced Vibration Test Response of Engine Rotor Blades |
WANG Xiaoliang1, YAO Lei2, HUANG Haihong2, WU Qiong2, DENG Ying2,3,4 |
1. Naval Military Representative Office in Beijing, Beijing 100043, China;
2. AVIC Manufacturing Technology Institute, Beijing 100024, China;
3. Aeronautical Key Laboratory for Plastic Forming Technologies, Beijing 100024, China;
4. Beijing Key Laboratory of Digital Plasticity Forming Technology and Equipment, Beijing 100024, China |
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Abstract The influence of the excitation condition on the aeroengine rotor blade response in fatigue test is studied. Numerical analysis and experiments test results show that in the rigid clamping condition, the relative relationship between the rotor blade clamping and the test device excitation load vector has no significant effect on the first-order natural frequency, mode shape and stress distribution. In the first mode shape vibration condition, the span stress component dominates the surface stress of the blade, the clamping influences the transfer function between excitation and response. There exists a clamping position, in which, minimum excitation energy is required when the vibration amplitude of blade tip reaches certain amount. The conclusion is of great significance to improve the rotor blade fatigue performance evaluation technology.
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[1] |
. CONTENTS[J]. Aeronautical Manufacturing Technology, 2023, 66(7): 6-8. |
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