TC4钛合金空心结构风扇叶片的鸟撞动力学响应及损伤失效

张永强; 贾林

doi:10.11858/gywlxb.20220546

TC4钛合金空心结构风扇叶片的鸟撞动力学响应及损伤失效

doi: 10.11858/gywlxb.20220546

张永强,
贾林

中国航发上海商用航空发动机制造有限责任公司, 上海　201306

详细信息

作者简介:
张永强（1977－），男，硕士，高级工程师，主要从事航空发动机型号现场强度测试、航空发动机故障诊断与分析研究. E-mail：zhangyqnwpu@163.com

中图分类号: O347
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出版历程
- 收稿日期: 2022-03-23
- 修回日期: 2022-04-08
- 录用日期: 2022-04-20
- 刊出日期: 2022-10-11

Dynamic Response and Damage Failure Behavior of TC4 Titanium Alloy Hollow Fan Blade

AECC Commercial Aircraft Engine Manufacturing Co., Ltd., Shanghai 201306, China

摘要

摘要: 航空发动机是鸟撞事件中的高概率、高危部件，对风扇叶片相关抗鸟撞问题的研究具有重要意义。采用三维数字图像相关（3D-DIC）法开展了TC4钛合金空心结构风扇叶片在不同高度下的静置鸟撞试验。此外，基于Johnson-Cook动态本构模型与损伤失效理论建立了相关计算模型，较好地描述并验证了航空发动机风扇叶片在鸟撞过程中的动态变形响应过程与失效情况。结果表明：鸟撞速度的变化主要影响叶片变形的量级，而不会引起叶片特征模态的改变；在鸟撞过程中，叶根是应力/应变局域化显著区域，更容易发生损伤失效；随着鸟撞位置的提高，空心结构风扇叶片在叶根处失效断裂对应的临界鸟撞速度逐渐提高，整体结构抗鸟撞性能越好。试验结果及相应的数值模拟为TC4钛合金空心结构风扇叶片的抗鸟撞设计提供了一定的参考。
- TC4钛合金 /
- 鸟撞 /
- 风扇叶片 /
- 动力学响应 /
- 损伤失效
Abstract: Aero-engine is a high probability and high-risk component of bird strike events, which is of great significance to the study of bird strike resistance of fan blades. In this paper, based on the three-dimensional digital image correlation (DIC) in-situ strain measurement method, the static bird strike tests of TC4 titanium alloy hollow structure fan blades at different heights are carried out. In addition, a simulation model is established based on Johnson-Cook dynamic constitutive model and damage failure theory to better verify and describe the dynamic deformation response process and failure situation of aero-engine fan blades during bird strikes. It is found that the variation of bird strike velocity mainly affects the magnitude of blade deformation, but does not cause the change of blade characteristic mode. In the bird strike process, the middle root is a significant area of stress/strain localization, which is more prone to damage failure. It is found that with the increase of bird impact position, the critical bird impact velocity corresponding to the failure of the hollow fan blade at the blade root increases gradually, and the bird impact resistance of the whole structure is better. This experiment and the corresponding simulation study provide a certain reference for the anti-bird impact design of the TC4 titanium alloy hollow structure fan blade.
- TC4 titanium alloy /
- bird strike /
- fan blade /
- dynamic response /
- damage failure

HTML全文

图 1 (a) 钛合金空心风扇叶片实物及应变片、3D-DIC位移测点位置；(b) 各应变片的横纵方向分布；(c) 叶片横剖面上空心结构示意图

Figure 1. (a) Titanium alloy hollow fan blade and the position of the strain gauges and 3D-DIC displacement measuring point; (b) specific locations of the horizontal and vertical distribution of the strain gauges; (c) schematic diagram of the hollow structure along the cross section of the blade

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图 2 (a) 试验设备布置示意图及(b)部分试验设备布置现场（包括3D-DIC系统）

Figure 2. (a) Schematic diagram of the test equipment and (b) part of the test equipment layout site (including the 3D-DIC system)

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图 3 鸟撞速度为306.8 m/s、高度70%h时的图像：(a)鸟弹飞行姿态，(b)鸟撞过程俯视图，(c)～(e)撞击面

Figure 3. (a) Flight posture of the gelatin bird，(b) snapshot of the bird-strike process from the top view and (c)-(e) snapshot of the impacting surface when the bird strike velocity is 306.8 m/s and the altitude is 70%h

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图 4 叶片各测点的应变时程曲线

Figure 4. Strain history obtained by strain gauges on the blade

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图 5 TC4钛合金风扇叶片鸟撞计算模型

Figure 5. Simulation model of the TC4 titanium fanblade under the bird impact

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图 6 试验与数值模拟得到的鸟撞过程中风扇叶片两叶尖的时间-位移曲线对比

Figure 6. Comparison between experimental and numerical simulation results of time-displacement curvesof two fan blades during bird strike

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图 7 (a)～(d)当鸟撞速度为307.3 m/s、撞击高度为70%h时不同时刻总位移云图，(e) 不同鸟撞速度下叶尖的位移时程曲线

Figure 7. (a)-(d) Displacement maps under velocity of 307.3 m/s and height of 70%h at different time;(e) displacement-time history curves of leaf tip at different bird strike velocities

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图 8 鸟撞速度为157.3 m/s、不同撞击高度（10%h、30%h、50%h、70%h）下钛合金空心风扇叶片的等效应力场和等效塑性应变场分布

Figure 8. Equivalent stress and plastic strain field of the titanium hollow fan blade under different impacting heights at velocity of 157.3 m/s and different impacting height (10%h, 30%h, 50%h and 70%h), respectively

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图 9 鸟撞能量为6.64 kJ、鸟撞高度为10%h时风扇叶片的等效应变场和叶根的典型损伤断裂失效模式

Figure 9. Equivalent plastic strain of the blade and the typical failure mode along the root under a impacting energy of 6.64 kJ and height of 10%h

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表 1 不同高度下的叶片鸟撞试验结果及其对应的最大叶尖位移

Table 1. Loading conditions of the tests under different impacting heights and their corresponding maximum displacement of the blade’s tip

No.	Height position	Bird mass/kg	Ideal speed/ （m·s^–1）	Actual speed/ （m·s^–1）	Kinetic energy/kJ	Maximum displacement/mm	Whether failure
1	10%h	0.3146	158.6	163.0	4.18	24.599	No
2	30%h	0.3059	207.5	206.2	6.50	34.335	No
3	30%h	0.3142	207.5	211.9	7.05	44.206	No
4	50%h	0.3153	257.0	250.0	9.85	61.928	No
5	50%h	0.3140	257.0	263.0	10.86	86.582	No
6	50%h	0.3143	257.0	256.4	10.33	104.596	No
7	50%h	0.3119	257.0	251.3	9.85	86.220	No
8	70%h	0.3150	307.3	304.9	14.64	161.123	No
9	70%h	0.3149	307.3	306.8	14.82	162.187	No

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表 2 鸟体材料参数^[20]

Table 2. Material parameters of the gelatin bird^[20]

Density/(kg·m⁻³)	Elastic modulus/MPa	Poisson’s ratio	Yield stress/MPa	Failure strain	Tangent modulus/MPa
928	68	0.49	0.69	1.25	5

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表 3 TC4钛合金Johnson-Cook本构及损伤失效材料参数^[25-26]

Table 3. Parameters of the Johnson-Cook model for the TC4 titanium alloy^[25-26]

ρ/(kg·m⁻³)	E/GPa	μ	A₀/MPa	B₀/MPa	C	T_m/K	n
4.43×10³	135	0.33	1060	1090	0.0117	1 878	0.884

m	$\dot \varepsilon $₀/s⁻¹	D₁	D₂	D₃	D₄	D₅
1.1	4×10⁻⁴	−0.09	0.27	0.48	0.014	3.87

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表 4 不同撞击高度和撞击速度下钛合金风扇叶片的叶根同一单元的最大等效塑性应变

Table 4. Maximum equivalent plastic strain of the same element of the model under different impacting heights and velocities

Height	Maximum equivalent plastic strain
Height	3.82 kJ	6.64 kJ	10.24 kJ	14.61 kJ	19.75 kJ
10%h	6.12%	Fail	Fail	Fail	Fail
30%h	9.01%	22.78%	Fail	Fail	Fail
50%h	6.92%	15.83%	26.60%	Fail	Fail
70%h	4.67%	9.45%	11.63%	12.89%	Fail
Note: The “Fail” in the table indicates that the fan had been damaged under the corresponding loading conditions.

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