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| Analysis and test on the vibration response of an aero-engine rotor under impact load |
| NIE Weijian1,2,3, LU Yu2, TANG Guang2,3, YANG Xiaoguang1, WANG Jinshun2,3, CHEN Yanong2,3 |
| 1.School of Energy and Power Engineering, Beihang University, Beijing 102206,China；
2.AECC Hunan Aviation Powerplant Research Institute, Zhuzhou 412002,China;
3.Key Laboratory of Aero-Engine Vibration Technology, Aero Engine Corporation of China,Zhuzhou 412002,China |
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Abstract Considering the SFD nonlinear oil film force, the differential equation of motion of the rotor was established. The vibration response of rotor under impact load was decomposed into harmonic response and impact response. The finite element models of harmonic response and impact response were established respectively, and the vibration response was calculated and analyzed. Experimental study on the vibration characteristics of aero-engine rotor under vertical impact load with different pulse width was carried out on the vibration table. The instantaneous vibration response of the rotor under impact load was obtained and compared with the test results. The study shows that in a certain rang of pulse width, the vibration response of rotor decreases with the increase of pulse width. In addition, compared with the test results, the calculation error of vibration response is between 10.44%~20.00%. The study provides a method for vibration response analysis and test of rotor under impact load, and has important engineering application value.
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Received: 22 February 2023
Published: 28 November 2023
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