突加不平衡下航空发动机转子动态响应与载荷传递

刘继军; 李益萱; 李凯翔; 姜永平; 刘小川

doi:10.13224/j.cnki.jasp.20250193

突加不平衡下航空发动机转子动态响应与载荷传递

doi: 10.13224/j.cnki.jasp.20250193

中国飞机强度研究所强度与结构完整性全国重点实验室，西安 710065

详细信息

作者简介:
刘继军（1981-），男，高级工程师，硕士，研究方向为结构动力学。E-mail：liujijun0514@163.com

中图分类号: V231.1；O327
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出版历程
- 收稿日期: 2025-04-21
- 网络出版日期: 2025-11-06

Dynamic response and load transfer characteristics of aero-engine rotor system under sudden unbalance

National Key Laboratory of Strength and Structural Integrity，Aircraft Strength Research Institute of China，Xi’an 710065，China

摘要

摘要:
航空发动机转子叶片突加不平衡（如叶片飞脱）会引发剧烈的瞬态冲击，严重影响飞行安全。针对大涵道比涡扇发动机低压转子系统，设计了一种可模拟大不平衡量（900 g·cm，6000 r/min）的地面实验平台，结合数值仿真与实验验证，研究了突加不平衡条件下的转子动态响应与载荷传递特性。基于Timoshenko梁理论建立了转子系统的有限元动力学模型，分析了不平衡量与转速变化对系统位移及外传力的影响规律。研究结果表明：在远离临界转速的风车工况区间（1140～1440 r/min），转子系统的位移和外传力瞬态响应均显著增大，其中外传力的动力学放大系数均值达1.2，远高于位移响应的1.03～1.04；不平衡量与转速变化对稳态响应呈近似线性影响，但对瞬态冲击效应的放大程度影响有限。研究为航空发动机突加不平衡实验的安全设计及适航验证提供了理论依据，建议采用1.2的动力学放大系数修正稳态外传力以准确评估瞬态载荷。
- 动力学系数 /
- 突加不平衡 /
- 转子系统动力学 /
- 动不平衡实验台 /
- 叶片飞脱
Abstract:
Sudden unbalance events (e.g., blade-off) in aero-engine rotor systems can induce severe transient impacts, significantly threatening flight safety. Focusing on the low-pressure rotor system of a high-bypass turbofan engine, a ground test platform capable of simulating large unbalance conditions (900 g·cm, 6000 r/min) was designed. Through numerical simulations and test validation, the dynamic response and load transfer characteristics under sudden unbalance were investigated. A finite element dynamics model of the rotor system was established based on Timoshenko beam theory, and the effects of unbalance and rotational speed on displacement and external force transmission were analyzed. The results revealed that within the windmilling speed range (1140—1440 r/min, far from critical rotational speeds), both displacement and external force responses exhibited significant transient amplification, with mean dynamic amplification factors of 1.2 for external force and 1.03—1.04 for displacement. Unbalance and rotational speed variations showed approximately linear effects on steady-state responses but limited influence on transient amplification. This research could provide theoretical support for the safety design and airworthiness verification of sudden unbalance tests, and a dynamic amplification factor of 1.2 should be recommended to correct steady-state external forces for accurate transient load assessment.
- dynamic amplification factor /
- sudden unbalance /
- rotor system dynamics /
- unbalanced test rig /
- blade loss

HTML

图 1 动不平衡实验平台

Figure 1. Unbalanced test platform

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图 2 支座与传感器设计

Figure 2. Support and sensor design

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图 3 通过第2阶临界转速

Figure 3. Passing the second critical rotational speed

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图 4 不同转速/平衡量下的稳态位移

Figure 4. Steady state displacement at different rotational speeds/balances

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图 5 典型柔性支撑的圆盘转子结构

Figure 5. Typical flexible supported disk rotor structure

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图 6 转子系统Campbell图

Figure 6. Campbell diagram of rotor system

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图 7 不同不平衡量下风扇盘轴心轨迹

Figure 7. Axis trajectory of fan disk under different unbalances

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图 8 风扇振幅及其动力学系数随不平衡量的关系

Figure 8. Relationship between fan amplitude and its dynamic amplification factors with unbalance

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图 9 不同不平衡量下转子系统外传力

Figure 9. External force of rotor system under different unbalances

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图 10 外传力及其动力学系数随不平衡量的关系

Figure 10. Relationship between external force and its dynamic amplification factors with unbalance

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图 11 不同转速下风扇轴心轨迹

Figure 11. Fan axis trajectory at different rotational speeds

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图 12 风扇振幅及其动力学系数随转速的关系

Figure 12. Relationship between fan amplitude and its dynamic amplification factors with rotational speed

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图 13 不同转速下转子系统外传力

Figure 13. External force of rotor system at different rotational speeds

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图 14 外传力及其动力学系数随转速的关系

Figure 14. Relationship between external force and its dynamic amplification factors with rotational speed

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表 1 分析和实验结果比较

Table 1. Comparison of analysis and test results

阶数临界转速/（r/min）误差/%

模型分析实验

1 1720 1770 2.9

2 2720 2695 0.9

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