民航发动机风扇叶片鸟撞瞬态响应与损伤分析

史磊; 范魏冰; 张海洋; 黄颖杰; 袁堂龙; 陈泽桐

doi:10.13224/j.cnki.jasp.20250551

民航发动机风扇叶片鸟撞瞬态响应与损伤分析

doi: 10.13224/j.cnki.jasp.20250551

1.
中国民航大学中欧航空工程师学院，天津 300300
2.
中国航发沈阳发动机研究所辽宁省航空发动机冲击动力学重点实验室，沈阳 110015
3.
国家超级计算天津中心，天津 300300
4.
中国民航大学航空工程学院，天津 300300

基金项目: 国家重点研发计划（2022YFB4301001）；中央高校基本科研业务费中国民航大学专项（3122024028）

详细信息

作者简介:
史磊（1988-），男，讲师、硕士生导师，博士，主要从事轴流叶轮机械气动热力学研究。E-mail：lshi@cauc.edu.cn

中图分类号: V232.4
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出版历程
- 收稿日期: 2025-12-01
- 网络出版日期: 2026-04-20

Transient response and damage analysis of bird strike on fan blades of civil aviation engines

1.
Sino-European Institute of Aviation Engineering，Civil Aviation University of China，Tianjin 300300，China
2.
Key Laboratory of Impact Dynamics on Aero Engine，Shenyang Aeroengine Research Institute，Aeroengine Corporation of China，Shenyang 110015，China
3.
National Supercomputer Center in Tianjin，Tianjin 300300，China
4.
Aeronautical Engineering Institute，Civil Aviation University of China，Tianjin 300300，China

摘要

摘要:
通过调整鸟体撞击速度、撞击位置与发动机转速3类参数，采用显式动力学仿真方法，对 CFM56-7B 大涵道比民用涡扇发动机的风扇叶片开展瞬态鸟撞响应分析。研究结果表明：当鸟体以60、80、130 m/s撞击时，叶片在约4.2～4.3 ms出现最大Mises应力；撞击持续时间越长、轴向相对速度越小，累积损伤越严重。撞击位置改变峰值时刻与应力分布：在叶长的30%、50%、80%处撞击分别在2.6、4.1、4.2 ms出现应力峰，其中50%处产生的应力集中于叶根处；发动机转速与损伤程度呈正相关，高转速下叶片应力峰值显著增大。在鸟体质量为1.85 kg、鸟体速度为130 m/s、发动机转速为5175 r/min工况下，撞击机匣外侧对叶片与机匣的破坏远大于撞击进口整流锥，表现为周向扩散的应力集中与叶尖局部塑性破坏。
- 大涵道比风扇 /
- 鸟撞 /
- 应力 /
- 损伤 /
- 冲击动力响应
Abstract:
By adjusting three parameters—bird impact speed, impact position, and engine speed, the transient bird-strike response of the fan blades of the CFM56-7B high-bypass-ratio civil turbofan engine was analyzed by explicit-dynamics simulation. Results showed that for impact speeds of 60, 80, and 130 m/s, the peak Mises stress occurred at about 4.2—4.3 ms. Longer impact duration and smaller axial-relative velocity caused more severe cumulative damage. Impact position changed the peak moment and the stress distribution. At 30%, 50%, and 80% of blade length the stress peaks occurred at about 2.6, 4.1, and 4.2 ms, respectively. An impact at 50% blade length produced stress concentration at the blade root. Engine speed was positively correlated with the damage; peak stress increased markedly at high speeds. Under the conditions of a mass of 1.85 kg, a speed of 130 m/s, and an engine speed of 5175 r/min, the damage from a bird striking the outer casing was much greater than that from a strike on the inlet fairing. This damage presented as circumferential stress concentration and local plastic damage at the blade tip.
- high bypass ratio fan /
- bird strike /
- stress /
- damage /
- impact dynamic response

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图 1 CFM56-7B发动机主要部件

Figure 1. Main components of the CFM56-7B engine

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图 2 鸟体的几何尺寸和对应质量

Figure 2. Geometric dimensions and corresponding mass of the bird body

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图 3 鸟体网格模型图

Figure 3. Mesh model diagram of the bird body

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图 4 机匣后边缘截面

Figure 4. Rear edge cross-section of the casing

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图 5 论文中不同中鸟速度产生的叶片动态响应^[28]

Figure 5. Blade dynamic response caused by different intermediate bird speeds in the paper^[28]

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图 6 60 m/s鸟撞动态响应验证

Figure 6. 60 m/s bird strike dynamic response verification

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图 7 130 m/s鸟撞动态响应验证

Figure 7. 130 m/s bird strike dynamic response verification

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图 8 撞击碰撞鸟体流变示意图

Figure 8. Impact bird body rheological schematic diagram

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图 9 不同速度鸟撞风扇叶片变形情况

Figure 9. Deformation of fan blades when hit by birds at different speeds

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图 10 不同速度鸟撞归一化Mises应力

Figure 10. Birds colliding at different speeds normalized to Mises stress

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图 11 不同速度鸟撞归一化等效应变

Figure 11. Different speeds of birds collide to normalize the equivalent effect strain

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图 12 鸟撞击叶片位置分布

Figure 12. Distribution of bird impact on leaf positions

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图 13 不同时刻下的不同位置鸟撞结果

Figure 13. Results of bird strikes at different times and locations

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图 14 不同时刻下不同撞击位置的V-M应力分布

Figure 14. V-M stress distribution at different impact locations over time

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图 15 归一化Mises应力随时间变化

Figure 15. Normalized Mises stress variation over time

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图 16 不同时刻下不同撞击位置的叶片塑性变形

Figure 16. Plastic deformation of blades at different impact locations over time

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图 17 归一化塑性应变随时间变化

Figure 17. Normalized plastic strain changes over time

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图 18 不同时刻下的不同转速鸟撞结果

Figure 18. Bird strike results at different speeds and times

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图 19 不同转速鸟撞风扇叶片应力情况

Figure 19. Stress conditions of fan blades at different rotational speeds when struck by birds

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图 20 归一化Mises应力随时间变化

Figure 20. Normalized Mises stress variation over time

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图 21 不同转速鸟撞风扇叶片变形情况

Figure 21. Deformation of fan blades caused by birds colliding at different speeds

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图 22 归一化塑性变形随时间变化

Figure 22. Normalized plastic deformation over time

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图 23 130 m/s鸟撞进口整流锥过程

Figure 23. Process of a bird hitting the inlet cone at 130 m/s

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图 24 鸟撞整流锥发动机变形情况

Figure 24. Bird strike on the engine’s nacelle causing deformation

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图 25 130 m/s鸟撞机匣过程

Figure 25. Process of a bird hitting the receiver at 130 m/s

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图 26 鸟撞发动机机匣变形情况

Figure 26. Deformation of the engine casing caused by bird strike

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表 1 风扇增压级模型参数

Table 1. Model parameters of the fan booster stage

模型参数		数值
叶片数	风扇叶片（Fan）	24
	出口导向叶片（OGV）	76
	进口导向叶片（IGV）	108
	一级转子（Rotor 1）	74
	一级静子（Stator 1）	136
	二级转子（Rotor 2）	78
	二级静子（Stator 2）	136
	三级转子（Rotor 3）	74
	三级静子（Stator 3）	136
各级动叶叶顶间隙/mm		0.50
设计转速/（r/min）		5175

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表 2 钛合金Ti-6AL-4V和铝合金AL 7075-T6材料参数

Table 2. Material parameters of Titanium alloy Ti-6AL-4V and aluminum alloy AL 7075-T6

参数	Ti-6AL-4V	AL 7075-T6	17-4PH
密度ρ/ 10³ （kg·m³）	4.4	2.6	7.75
屈服应力A/MPa	1098	369	1000
硬化系数B/MPa	1092	684	1146
应变率系数C	0.014	0.0083	0.28

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表 3 某型发动机各部件材料属性与网格划分

Table 3. Material properties and mesh generation of each component of a certain type of engine

名称	材料	网格数	网格类型
机匣	AL 7075-T6	174634	壳网格
整流锥	AL 7075-T6	17904	体网格
风扇盘	Ti-6AL-4V	100968	体网格
分流环	AL 7075-T6	97129	壳网格
风扇叶片	Ti-6AL-4V	183820	体网格
出口导向叶片	AL 7075-T6	195548	体网格
静子叶片	17-4PH	3360	体网格
工作叶片	Ti-6AL-4V	2784	体网格

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表 4 鸟体质量要求

Table 4. Mass requirements of the bird body

吸鸟分类	数量	质量/kg	适航条款
大鸟	1	2.75	33.76 （a）
中鸟	1	1.85	33.76 （b）（1）
小鸟	1	1.15	33.76 （c）（3）

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表 5 不同鸟撞速度研究工况

Table 5. Research conditions for collision speeds of different birds

工况	鸟体质量/kg	鸟撞速度/ （m/s）	转速/ （r/min）	撞击扇叶位置
1	1.85	60	5175	80%H
2	1.85	80	5175	80%H
3	1.85	130	5175	80%H

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表 6 鸟撞扇叶位置研究工况

Table 6. Research on the working conditions of bird strikes on fan blades

工况	鸟体质量/kg	鸟撞速度/ （m/s）	转速/ （r/min）	撞击扇叶位置
1	1.85	130	5175	30%H
2	1.85	130	5175	50%H
3	1.85	130	5175	80%H

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表 7 不同转速撞击研究工况

Table 7. Impact research conditions at different rotational speeds

工况	鸟体质量/kg	鸟撞速度/ （m/s）	转速/ （r/min）	撞击扇叶位置
1	1.85	130	5175	80%H
2	1.85	130	4420	80%H
3	1.85	130	2600	80%H

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