三边夹持下钛合金叶片鸟撞损伤分析和数值模拟研究

王伟灿; 罗刚; 赵朝君; 范兴超; 陈伟

doi:10.21656/1000-0887.450242

三边夹持下钛合金叶片鸟撞损伤分析和数值模拟研究

doi: 10.21656/1000-0887.450242

王伟灿^1,,
罗刚^2, ,,
赵朝君³,
范兴超³,
陈伟¹

1.
南京航空航天大学能源与动力学院, 南京 210016
2.
南京航空航天大学航空航天结构力学及控制国家重点实验室, 南京 210016
3.
中国航发四川燃气涡轮研究所, 成都 610599

(我刊编委陈伟来稿)

基金项目:

国家科技重大专项 2017-Ⅳ-0006-0043

详细信息

作者简介:
王伟灿(2000—)，男，硕士(E-mail: WWCNUAA@nuaa.edu.cn)

通讯作者:
罗刚(1980—)，男，实验师，博士(通讯作者. E-mail: luogang@nuaa.edu.cn)

中图分类号: V232.4
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- 被引次数: 0
出版历程
- 收稿日期: 2024-09-03
- 修回日期: 2024-10-07
- 刊出日期: 2025-10-01

Analysis and Numerical Simulation of Bird Impact Damages of 3-Side-Clamped Titanium Alloy Blades

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, P.R.China
2.
State Key Laboratory of Aerospace Structural Mechanics and Control for Aerospace Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, P.R.China
3.
Sichuan Gas Turbine Establishment, Aero Engine Corporation of China, Chengdu 610599, P.R.China

(Contributed by CHEN Wei, M.AMM Editorial Board)

摘要

摘要: 鸟撞发动机风扇叶片对飞机的危害性极大.为了研究叶片受鸟撞的损伤，以某型发动机风扇叶片为基础，设计夹具将叶片紧固，进行两组鸟撞叶片试验得到叶片的损伤结果.试验后使用LS-DYNA软件通过数值模拟方法对试验结果进行验证.以试验为基础建立鸟撞三边夹持叶片模型，研究四种影响叶片损伤结果的撞击工况对叶片损伤的影响.结果表明：试验工况对叶片损伤的影响根本上是鸟体传递给叶片能量的改变.随着传递能量的增大，叶片的损伤将由鼓包变为裂缝直至最后破损.通过研究叶片损伤发现在特定工况中鸟撞三边夹持叶片试验可以有效模拟部分鸟撞旋转叶片的试验.
- 风扇叶片 /
- 鸟撞 /
- 数值模拟 /
- 光滑粒子流体动力学 /
- 叶片损伤
Abstract: The damages caused by bird impacts on engine fan blades in aircraft is extremely serious. To study these damages to the blades, an experiment was conducted based on a certain type of engine fan blade clamped by fixtures on 3 sides. Then 2 groups of bird-blade impact tests were completed, and the results of blade damages were obtained. Simultaneously, the LS-DYNA software was used to numerically verify the experimental results. A 3-side-clamped blade model for bird impact was established based on the experiment to study the effects of 4 impact conditions on blade damages. The results indicate that, the effects of experimental conditions on blade damages are fundamentally due to the energy changes transmitted from the bird body to the blade. As the transmitted energy increases, the damage to the blade will change from a bulge to a crack until finally rupture. Through the study of the damages to the blade in specific impact conditions, the 3-side-clamped blade-bird impact test can effectively simulate a part of the tests on bird impacts on rotating blades.
- fan blade /
- bird impact /
- numerical simulation /
- smoothed particle hydrodynamics /
- blade damage
edited-by

edited-by
注释:

1) (我刊编委陈伟来稿)

HTML全文

图 1 叶片示意图

Figure 1. Photos of the blades

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图 2 夹具模型

Figure 2. The fixture model

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图 3 叶片夹具装配图

Figure 3. Assembly drawing of blade and fixtures

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图 4 试验设备

Figure 4. The equipment

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图 5 试验用明胶鸟

Figure 5. Gelatin bird used in the test

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图 6 高速摄影设备

Figure 6. The high-speed camera

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图 7 第Ⅰ组试验鸟体冲击过程

Figure 7. The impact process of the bird body in experiment group Ⅰ

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图 8 第Ⅰ组试验后叶片损伤图

Figure 8. Blade damage images after experiment group Ⅰ

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图 9 第Ⅱ组试验鸟体冲击过程

Figure 9. The impact process of the bird body in experiment group Ⅱ

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图 10 第Ⅱ组试验后叶片损伤图

Figure 10. Blade damage images after experiment group Ⅱ

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图 11 有限元模型

Figure 11. The finite element model

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图 12 第Ⅰ组试验数值模拟叶片损伤

Figure 12. Blade damages in numerical simulation for experiment group Ⅰ

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图 13 试验Ⅰ受撞击面表面等效应力演变过程(等效应力单位: Pa)

注为了解释图中的颜色，读者可以参考本文的电子网页版本，后同.

Figure 13. The evolution process of equivalent stresses on the impact surface in experiment Ⅰ(effective stress unit: Pa)

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图 14 第Ⅰ组试验叶片和鸟体能量变化

Figure 14. Energy changes of blades and bird bodies in experiment group Ⅰ

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图 15 第Ⅱ组试验数值模拟的叶片损伤

Figure 15. Blade damages in numerical simulation for experiment group Ⅱ

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图 16 试验Ⅱ受撞击面表面等效应力演变过程(等效应力单位: Pa)

Figure 16. The evolution process of equivalent stresses on the impact surface in experiment Ⅱ(effective stress unit: Pa)

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图 17 第Ⅱ组试验叶片和鸟体能量变化

Figure 17. Energy changes of blades and bird bodies in experiment group Ⅱ

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图 18 鸟体撞击位置

Figure 18. Positions of bird body impacts

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图 19 叶片鸟撞击损伤3种典型形式

Figure 19. The 3 typical forms of blade-bird impact damages

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图 20 叶片鼓包尺寸随撞击角度θ的变化

Figure 20. The blade bulge size changing with angle θ

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图 21 叶片鼓包尺寸随位置d的变化

Figure 21. The blade bulge size changing with position d

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图 22 叶片鼓包尺寸随鸟体质量q的变化

Figure 22. 22 The blade bulge size changing with gelatin bird mass q

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图 23 四种工况下的能量

Figure 23. Energy histograms in 4 operating conditions

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表 1 试验工况

Table 1. Test conditions

experimental group	bird type	mass/g	bird body length/mm	bird body diameter/mm	velocity/(m/s)
Ⅰ	gelatin bird	60.1	68	34	182
Ⅱ	supported gelatin bird	27.4	51.2	25.6	274

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表 2 试验后叶片损伤

Table 2. Damages to the blade after the tests

test group number	damage type	damage size
Ⅰ	bulge	1) bulge length 51 mm 2) bulge depth 10.5 mm
Ⅱ	crack	3) the 1st crack length 35 mm 4) the 2nd crack length 13 mm

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表 3 变量含义

Table 3. The meanings of variables

variable	meaning
A，B	material related constants
n	strain hardening influence coefficient
C	strain rate influence coefficient
m	temperature influence coefficient
γ	equivalent plastic strain
$ \dot{\varepsilon}^*$	relative equivalent plastic deformation rate
T^*	dimensionless temperature

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表 4 TC4叶片JC模型参数

Table 4. The JC model parameters of blade TC4

material parameter	numerical value	material parameter	numerical value
density/(kg/m³)	4 440	D₂	0.27
shear modulus/GPa	42.9	D₃	0.48
elastic modulus/GPa	115	D₄	0.014
Poisson’s ratio	0.34	D₅	3.86
A/MPa	950	C/(m/s)	5 130
B/MPa	1 080	S₁	1.028
N	0.34	S₂	0
C	0.018 2	S₃	0
M	0.767	γ₀	1.23
D₁	-0.05	A	0.17

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表 5 明胶鸟材料参数

Table 5. Material parameters of the gelatin bird

material parameter	numerical value
density/(kg/m³)	950
yield stress/Pa	20 000
shear modulus/GPa	2

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表 6 骨架材料参数

Table 6. Material parameters of the skeleton

material parameter	numerical value
density/(kg/m³)	1 300
elastic modulus/GPa	2.6
Poisson’s ratio	0.42
yield stress/MPa	38
tangent modulus/MPa	655

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表 7 40Cr材料参数

Table 7. Material parameters of 40Cr

material parameter	numerical value
density/(kg/m³)	7 830
elastic modulus/GPa	209
Poisson’s ratio	0.3
yield stress/MPa	835
tangent modulus/MPa	980

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表 8 数值模拟叶片损伤

Table 8. Blade damages in numerical simulation

test group number	damage type	damage size
Ⅰ	bulge	1) bulge length 53 mm 2) bulge depth 11 mm
Ⅱ	crack	3) the 1st crack length 41 mm 4) the 2nd crack length 15 mm

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表 9 数值模拟误差

Table 9. Numerical simulation errors

damage size	1	2	3	4
experiment/mm	51	10.5	35	13
numerical simulation/mm	53	11	41	15
error value/%	3.9	4.8	17.1	15.4

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表 10 变鸟速叶片损伤及尺寸

Table 10. Damages and sizes of blades changing with the speed

bird velocity/(m/s)	damage form	size
200	bulge	bulge length 51.9 mm, depth 10.6 mm
225	bulge	bulge length 50 mm, depth 13 mm
250	cracked bulge	bulge length 52 mm, depth 15 mm
275	cracked bulge	bulge length 52 mm, depth 17 mm
300	crack	crack length 6.2 mm
325	crack	crack length 16 mm

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表 11 叶片损伤形式与能量的关系

Table 11. The relationship between blade damage forms and energy values

energy/J	damage form
0~190	bulge
190~350	cracked bulge
above 350	crack

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