航空发动机多支撑附件系统振动传递路径分析

doi:10.7527/S1000-6893.2023.28303

Abstract

Abstract:

The accessory system is an important component in aero-engines， and excessive engine vibration often causes local damage to the accessory structure. Aiming at an aero-engine lubricating oil tank system supported by multiple mounting pedestals， we perform the vibration Transfer Path Analysis （TPA） of the oil tank under different flight conditions （idle， cruise， and maximum operating speed states）. Firstly， based on the basic principle of the TPA， the TPA Finite Element （FE） model of the lubricating oil tank system is established， and the TPA model validity is verified. Then， based on the measured vibration load spectrum of an aero-engine lubricating oil tank， the vibration responses of multiple target points of the oil tank are simulated and analyzed. Furthermore， based on the simulation TPA method， the contribution of the mounting pedestals to vibration response of the oil tank under different flight conditions is compared and discussed. The results show that the vibration response of the oil tank is relatively large at N₁， N₂ and 2N₁. In the idle and cruise states， the contribution of different vibration transfer directions of the mounting pedestals to the target point vibration response is Y>X>Z. At the maximum operation speed， the Y and X vibration transfer directions of different mounting pedestals have relatively large contributions to the vibration response of the target point. Finally， after reducing the transfer function and operated load of the main transfer path， the vibration response of the oil tank is reduced by 1.5 dB and 2.8 dB， respectively. The TPA analysis method used in this paper can provide guide for the dynamic design of aeroengine complex external accessory systems with multiple supports.

Key words: accessory system, Transfer Path Analysis （TPA）, simulation TPA, transfer function, inverse matrix method, dynamic design

CLC Number:

V233

Qingyu ZHU, Qingkai HAN, Weimin WANG, Zhinong JIANG. Vibration transfer path analysis of aeroengine multi-support accessory system[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(4): 628303-628303.

Figures/Tables 24

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阶次	实测/Hz	TPA/Hz	误差/%
1	45	48	6.67
2	92	87	5.43
3	115	124	7.83
4	163	166	1.84
5	225	245	8.89
6	286	270	5.59
7	318	327	2.83
8	394	374	5.08
9	429	415	3.26
10	492	471	4.27

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Vibration transfer path analysis of aeroengine multi-support accessory system

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