热载荷下组合支承转子动力学特性分析

吴劲男; 张海彪; 刘富华; 王青山; 刘涛

doi:10.13224/j.cnki.jasp.20250560

热载荷下组合支承转子动力学特性分析

doi: 10.13224/j.cnki.jasp.20250560

吴劲男^{1, 2,},
张海彪^{1, 2},
刘富华^{1, 2},
王青山^{1, 2,*, ,},
刘涛³

1.
中南大学机电工程学院，长沙 410083
2.
中南大学极端服役性能精准制造国家重点实验室，长沙 410083
3.
中南大学土木工程学院，长沙 410075

基金项目: 国家自然科学基金（52075554）

详细信息

作者简介:
吴劲男（2001-），男，硕士生，主要从事航空发动机动力学特性研究。E-mail：wujinnan@csu.edu.cn

通讯作者:
王青山（1989-），男，教授，博士，主要从事航空发动机动力学特性研究。E-mail：qingshanwang@csu.edu.cn

中图分类号: V231.96
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- 被引次数: 0
出版历程
- 收稿日期: 2025-12-03
- 网络出版日期: 2026-04-18

Dynamic analysis of combined support rotor under thermal load

Wu Jinnan^{1, 2
,},
Zhang Haibiao^{1, 2},
Liu Fuhua^{1, 2},
Wang Qingshan^{1, 2,*
, ,},
Liu Tao³

1.
College of Mechanical and Electrical Engineering，Central South University，Changsha 410083
2.
State Key Laboratory of Precision Manufacturing for Extreme Service Performance，Central South University，Changsha 410083
3.
School of Civil Engineering，Central South University，Changsha 410075

摘要

摘要:
针对航空发动机中热载荷对组合支承转子动力学特性的影响展开研究。建立了考虑温度影响的组合支承系统模型，推导了弹性环和鼠笼弹支的刚度、阻尼随温度变化的公式。通过有限元方法构建了动力涡轮转子三维模型，结合温度场分布分析了其热变形与热应力。在此基础上，提出了组合支承-转子双向耦合模型，结合该模型和转子三维有限元模型进一步分析了热载荷下转子动力学特性的变化规律。研究结果表明，热载荷将导致临界转速小幅下降，但振动幅值只在临界转速附近变化显著。在上述研究基础上，最后搭建了转子试验台验证了理论分析的正确性。
- 热载荷 /
- 转子动力学 /
- 弹性环式组合支承 /
- 耦合系统 /
- 不平衡响应
Abstract:
The impact of thermal loads on the dynamic characteristics of a combined-support rotor system in aero-engines was investigated. A temperature-dependent model was developed for the combined-support system, deriving the formulas for the stiffness and damping of elastic rings and squirrel cage elastic supports under varying temperatures. A 3D finite element model of the power turbine rotor was developed, incorporating thermal deformation and stress analysis based on temperature field distribution. A bidirectional coupled model integrating the combined support and rotor was proposed, enabling further analysis of thermal-induced changes in rotor dynamics. Results indicated that thermal loads caused a minor reduction in critical speeds, while vibration amplitudes exhibited significant variations only near critical speed regions. Experimental validation on a rotor test rig confirmed the theoretical analysis.
- thermal load /
- rotor dynamics /
- elastic ring combined support /
- coupled system /
- unbalance response

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图 1 ERSFD组合支撑模型

Figure 1. Combined support model of ERSFD

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图 2 动力涡轮转子有限元模型

Figure 2. Finite element model of power turbine rotor

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图 3 动力涡轮转子温度场分布

Figure 3. Temperature field distribution of power turbine rotor

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图 4 组合支承-动力涡轮转子支承模型示意图

Figure 4. Schematic diagram of combined support-power turbine rotor support model

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图 5 组合支承-动力涡轮转子耦合系统建模流程

Figure 5. Modeling process of combined support-power turbine rotor coupling system

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图 6 不同情况下动力涡轮转子系统坎贝尔图

Figure 6. Campbell diagram of power turbine rotor system under different conditions

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图 7 转子各个位置的幅频曲线

Figure 7. Frequency curves at varying positions of the rotor

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图 8 1号支承处幅频曲线

Figure 8. Amplitude-frequency curve at No.1 support

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图 9 2号弹性环式组合支承处幅频曲线

Figure 9. Amplitude-frequency curve at No.2 elastic ring combined support

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图 10 不同热载荷下动力涡轮转子各位置3阶临界振幅

Figure 10. Third-order critical amplitudes at various positions of the power turbine rotor under different thermal loads

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图 11 弹性环式挤压油膜阻尼器组合支承转子系统模化实验台

Figure 11. Scaled experimental test rig for rotor system with elastic ring-type squeeze film damper combined support

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图 12 弹性环式组合支承主要零部件

Figure 12. Main components of the elastic ring type combined support

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图 13 不同油膜压力下6号组合支承处的振动响应

Figure 13. Vibration responses at the No. 6 combined support under different oil film pressures

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图 14 不同油膜压力减振幅度

Figure 14. Vibration attenuation at varying oil film pressures

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表 1 实际工程测量的关键位置温度

Table 1. Key position temperatures in actual engineering measurements

位置	温度/℃
轴承前碳密封跑道	157
动力涡轮一级盘	340
动力涡轮二级盘	300
动力涡轮轴	147
其他	147

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表 2 本文模型和实物转子临界转速对比

Table 2. Comparison between critical speeds of the present model and physical rotor

参数	实物转子	不考虑耦合系统	考虑耦合系统
1阶临界转速/ （r/min）	5320	5485.5	5413.2
偏差率/%		3.102	1.748
2阶临界转速/ （r/min）	8670	8829	8783.7
偏差率/%		1.834	1.303
3阶临界转速/ （r/min）	24950	25194	25137
偏差率/%		0.954	0.75

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表 3 不同热载荷下转子系统前三阶临界转速

Table 3. First three critical speeds of the rotor system under different thermal loads

各支承位置温度/℃	1阶临界转速/ （r/min）	2阶临界转速/ （r/min）	3阶临界转速/ （r/min）
0	5700	9000	25200
40	5550	8850	25050
80	5400	8850	25050
120	5400	8700	24900
160	5250	8700	24900
200	5100	8550	24750

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表 4 弹性环基本参数

Table 4. Basic parameters of elastic rings

参数	数值	参数	数值
内外凸台数n	8	渗油孔数/m	8
凸台对应圆心角度φ/（°）	10	渗油孔直径Φ/mm	1.5
弹性环厚度s/mm	1	弹性环径向长度L_Z/mm	15
弹性环外圈直径R₄/mm	56.5	弹性环内圈直径R₁/mm	52.5
凸台高度H/mm	0.2	滑油黏度μ/（Pa·s）	0.018

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