考虑湿热老化的复合材料机匣包容性试验与数值分析

郑竟波; 张颖; 姜文龙; 韦林; 迟雪; 伊文昭; 刘璐璐; 陈伟

doi:10.21656/1000-0887.450289

考虑湿热老化的复合材料机匣包容性试验与数值分析

doi: 10.21656/1000-0887.450289

郑竟波^1,,
张颖¹,
姜文龙¹,
韦林²,
迟雪³,
伊文昭¹,
刘璐璐^1, ,,
陈伟¹

1.
南京航空航天大学能源与动力学院航空发动机热环境与热结构工业和信息化部重点实验室, 南京 210016
2.
中国航发四川燃气涡轮研究院, 成都 610599
3.
扬州平航航空动力技术有限公司, 江苏扬州 225100

我刊青年编委刘璐璐、编委陈伟来稿

基金项目:

国家自然科学基金 52375150

中央高校基本科研业务费 NC2022001

详细信息

作者简介:
郑竟波(2000—)，女，硕士生(E-mail: 947222529@qq.com)

通讯作者:
刘璐璐(1988—)，女，研究员，教授，博士(通讯作者. E-mail: liululu@nuaa.edu.cn)

中图分类号: O313
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- 被引次数: 0
出版历程
- 收稿日期: 2024-10-28
- 修回日期: 2024-11-23
- 刊出日期: 2025-05-01

Tests and Numerical Analyses of the Composite Casing Containment Under Hydrothermal Environment

1.
Aero-Engine Thermal Environment and Structure Key Laboratory of Ministry of Industry and Information Technology, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, P.R.China
2.
AECC Sichuan Gas Turbine Establishment, Chengdu 610599, P.R.China
3.
Yangzhou Pinghang Aviation Power Technology Co., Ltd., Yangzhou, Jiangsu 225100, P.R.China

Contributed by LIU Lulu, M.AMM Youth Editorial Board & CHEN Wei, M.AMM Editorial Board

摘要

摘要: 为获得碳纤维增强树脂基复合材料(CFRP)机匣在服役环境下的包容特性，对其分别进行了湿热老化前后的两次高速冲击弹道试验，并建立了对应的机匣吸湿率分区湿热试验仿真模型与有限元高速冲击数值仿真分析模型. 结果表明：湿热老化作用对于CFRP机匣的抗冲击能力及能量吸收能力均有显著影响. 在高速冲击下，未湿热老化机匣的抗冲击能力及能量吸收能力优于湿热老化机匣. 高速冲击下，CFRP机匣的损伤形式主要以纤维和基体的拉伸失效为主，伴随着一定数量的纤维压溃和面内剪切失效，压缩失效基本没有出现，损伤出现在冲击区域附近，并沿机匣轴向与周向扩展. 此外，吸湿层的基体拉伸失效面积显著大于未老化层的基体拉伸失效面积，验证了湿热老化作用下基体力学性能的退化.
- 航空发动机 /
- 抗冲击特性 /
- 复合材料机匣 /
- 湿热老化 /
- 弹道试验
Abstract: To obtain the inclusion characteristics of carbon fiber resin matrix composite casing in service environment, 2 high-speed impact ballistic tests were conducted before and after hygrothermal treatment, and the corresponding simulation model for the casing hygroscopicity partition hygrothermal test simulation model along with the finite element high-speed impact numerical simulation-analysis model, was established. The results show that, the hygrothermal treatment has significant effects on the impact resistance and energy absorption capacity of the carbon fiber resin matrix composite casing. Under the high-speed impact, the impact resistance and energy absorption capacity of the casing without hygrothermal treatment are better than those of the casing with hygrothermal treatment. The damage form of the casing under high-speed impact is dominated by the tensile failure of fiber and matrix, accompanied by a certain amount of fiber crush and in-plane shear failure, with little or no compression failure observed. The damage occurs in the vicinity of the impact area, and extends along the axial and circumferential direction of the casing. In addition, the tensile failure area of the matrix of the hygrothermally treated layer is significantly larger than that of the matrix of the untreated layer, which verifies the degradation of the mechanical properties of the matrix after hygrothermal treatment.
- aero-engine /
- impact behavior /
- composite casing /
- hygrothermal treatment /
- ballistic impact test
edited-by

edited-by
注释:

1) 我刊青年编委刘璐璐、编委陈伟来稿

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图 1 复合材料机匣缩比件

Figure 1. The composite casing reduced-scale test specimen

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图 2 叶片冲击机匣方式示意图

Figure 2. Schematic diagram of blade impact magazine method

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图 3 模拟叶片示意图

Figure 3. Schematic of the simulation blade

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图 4 弹体示意图

Figure 4. Schematic of the projectile

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图 5 冲击试验系统原理图

Figure 5. Schematic of the impact test system

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图 6 机匣安装示意图

Figure 6. Schematic of the casing installation

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图 7 应变片粘贴示意图

Figure 7. Schematic of the strain gauge pasting

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图 8 叶片冲击机匣过程

Figure 8. The process of the blade impacting the casing

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图 9 未吸湿机匣打靶试验后损伤形貌

Figure 9. Casing damages without hygrothermal treatment after the targeting test

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图 10 吸湿机匣打靶试验后损伤形貌

Figure 10. Casing damages with hygrothermal treatment after the targeting test

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图 11 叶片冲击吸湿机匣过程

Figure 11. The blade-impacting-casing process with hygrothermal treatment

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图 12 层合板吸湿件有限元模型

Figure 12. The finite element model diagram of the hygrothermal treatment test laminate sample

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图 13 层合板试验和仿真吸湿率对比

Figure 13. Comparison of experimental and simulated hygroscopicity of the laminate

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图 14 机匣缩比件有限元模型

Figure 14. The finite element model for the casing scale parts

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图 15 湿热试验机匣吸湿率分布云图

Figure 15. The hygroscopicity distribution of the casing in hygrothermal treatment

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图 16 机匣厚度截面吸湿率分布

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 16. The hygroscopicity distribution of the casing in hygrothermal treatment

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图 17 复合材料机匣和TC4叶片的弹道冲击有限元模型

Figure 17. The ballistic impact finite element modeling of the composite casing and TC4 blades

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图 18 未吸湿机匣等效应力云图

Figure 18. Stress nephograms of the casing without hygrothermal treatment

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图 19 吸湿机匣等效应力云图

Figure 19. Stress nephograms of the casing with hygrothermal treatment

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图 20 未吸湿机匣与吸湿机匣冲击仿真模拟叶片动能-时间曲线

Figure 20. The kinetic energy-time curves of the simulated blade impacting the casing with and without hygrothermal treatment

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图 21 吸湿机匣冲击仿真损伤变量云图

Figure 21. Damage variable nephograms of the impacted casing with hygrothermal treatment

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表 1 湿热试验数据记录

Table 1. Material mechanical properties used for TG800H/E1806

specimen	test temperature/℃	soaking hours/h	mass before test/g	mass after test/g	hygroscopicity/%
casing	85	720	3 472.95	3 514.05	1.18
laminate	85	720	68	68.64	0.94

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表 2 空气炮打靶试验记录

Table 2. Records of the air cannon targeting tests

target test	mass of blade /g	incidence velocity /(m/s)	residual speed /(m/s)	damage
casing without hygrothermal treatment	405	144	100	penetration
casing with hygrothermal treatment	403	140	105	penetration

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表 3 两次试验机匣吸收能量值

Table 3. Absorbed energy values of 2 tests respectively

target test	ΔE/J
casing without hygrothermal treatment	2 174.0
casing with hygrothermal treatment	1 727.9

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表 4 网格敏感性验证

Table 4. The mesh sensitivity verification

number	FEA element size/(mm×mm×mm)	FEA element quantity	ΔE/J
1	6×6×0.125	40 000	2 591.7
2	5×5×0.125	57 600	1 978.4
3	4×4×0.125	92 416	1 886.2
4	3×3×0.125	160 000	1 902.6

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表 5 复合材料机匣单独铺层的铺层角度

Table 5. Individual ply angles of the composite casing

number of composite layers	ply angle /(°)	number of composite layers	ply angle /(°)
1	45	17	90
2	90	18	45
3	-45	19	0
4	90	20	-45
5	0	21	90
6	90	22	45
7	-45	23	0
8	0	24	90
9	90	25	0
10	0	26	-45
11	45	27	90
12	90	28	0
13	-45	29	90
14	0	30	-45
15	45	31	90
16	90	32	45

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表 6 TG800H-12k/E1806材料参数

Table 6. Material parameters of TG800H-12k/E180

parameter	symbol	without hygrothermal treatment	with hygrothermal treatment
density	ρ/(kg/m³)	1 560	1 560
longitudinal Young’s modulus	E₁/GPa	164	167
transverse Young’s modulus	(E₂=E₃)/GPa	9.41	5.71
Poisson’s ratio	ν₁₂=ν₂₁ ν₂₃	0.3 0.3	0.3 0.3
longitudinal shear modulus	(G₁₂=G₁₃)/MPa	5 090	3 410
transverse shear modulus	G₂₃/MPa	3 700	2 480
shear strength	S/MPa	88.7	48.2
longitudinal tensile strength	X_T/MPa	2 744	2 520
longitudinal compressive strength	X_C/MPa	1 450	1 081
transverse tensile strength	Y_T/MPa	74.1	46
transverse compressive strength	Y_C/MPa	272	146
fiber shear strength	S_FS/MPa	251	251
fiber compressive strength	S_FC/MPa	350	350
strain rate constant	C₁ C₂=C₃=C₄	0.014 0.042	0.014 0.042
damage angle	φ/(°)	10	10
damage parameter	m₁=m₂ m₃=m₄	2 0.2	2 0.2

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表 7 层间材料性能参数

Table 7. Material parameters of cohesive elements

parameter	symbol	without hygrothermal treatment	with hygrothermal treatment	hygroscopicity 1%~2%
cohesive stiffness	$k_n^0 / \mathrm{GPa}$	10⁵	10⁵	10⁵
cohesive stiffness	$\left(k_s^0=k_t^0\right) / \mathrm{GPa}$	10⁵	10⁵	10⁵
critical energy release rate	$G_n^{\mathrm{C}} /\left(\mathrm{J} / \mathrm{m}^2\right)$	280	370.7	254.6
critical energy release rate	$\left(G_s^{\mathrm{C}}=G_t^{\mathrm{C}}\right) /\left(\mathrm{J} / \mathrm{m}^2\right)$	2 710	1 710	2 122
cohesive stress	$t_n^0 /\left(\mathrm{J} / \mathrm{m}^2\right)$	60	43	67.1
cohesive stress	$t_s^0=t_t^0 / \mathrm{MPa}$	103	74	115

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表 8 TC4材料参数设置(基本物理参数)

Table 8. Material parameters of TC4 (basic physical parameters)

E/GPa	ν	ρ/(kg/m³)	T_m/K	T_r/K	C_p/(J/(kg·K))
135	0.33	4 430	1 922	293	563

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表 9 TC4材料参数设置(Johnson-Cook参数)

Table 9. Material parameters of TC4 (Johnson-Cook parameters)

$\dot{\varepsilon}_0 / \mathrm{s}^{-1}$	A/MPa	B/MPa	C	n	m
4×10^－4	1 060	1 090	0.011 7	0.884	1.1

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表 10 TC4材料参数设置(Johnson-Cook失效准则参数)

Table 10. Material parameters of TC4 (Johnson-Cook failure criterion parameters)

D₁	D₂	D₃	D₄	D₅
-0.09	0.27	0.48	0.014	3.87

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表 11 TC4材料参数设置(状态方程参数)

Table 11. Material parameters of TC4 (parameters of the equation of state)

S₁	S₂	S₃	γ₀	α
1.028	0	0	1.230	0

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表 12 两次试验与仿真叶片剩余速度对比

Table 12. Comparison of blade residual velocities

casing type	impact test residual velocity	impact simulation residual velocity	inaccuracy/%
casing without hygrothermal treatment	100	109.4	9.4
casing with hygrothermal treatment	105	110.8	5.5

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参考文献(22)

[1]	陈光. 航空发动机结构设计分析[M]. 北京: 北京航空航天大学出版社, 2006: 548-551. CHEN Guang. Analysis of Aeroengine Structure Design[M]. Beijing: Beihang University Press, 2006: 548-551. (in Chinese)
[2]	United States Air Force. Engine structural integrity program: MIL2STD21783B[S]. USA: Department of Defense, 2002.
[3]	中国民用航空局. 航空发动机适航规定: CCAR—33R2[S]. 北京: 中国民用航空局, 2016. Civil Aviation Administration of China. Aviation engine air-worthiness regulations: CCAR—33R2[S]. Beijing: Civil Aviation Administration of China, 2016. (in Chinese)
[4]	HOLMES M. Carbon fibre reinforced plastics market continues growth path[J]. Reinforced Plastics, 2013, 57 (6): 24-29. doi: 10.1016/S0034-3617(13)70186-3
[5]	MARSH G. Aero engines lose weight thanks to composites[J]. Reinforced Plastics, 2012, 56 (6): 32-35. doi: 10.1016/S0034-3617(12)70146-7
[6]	MAZUMDAR S. Composites Manufacturing: Materials, Product, and Process Engineering[M]. Boca Raton: CRC Press, 2001.
[7]	沈尔明, 王志宏, 赵凤飞, 等. 风扇机匣材料应用现状与发展[J]. 航空制造技术, 2013, 56 (13): 92-95. SHEN Erming, WANG Zhihong, ZHAO Fengfei, et al. Application and development of material for aeroengine fan case[J]. Aeronautical Manufacturing Technology, 2013, 56 (13): 92-95. (in Chinese)
[8]	李佳楠, 姜亚明, 项赫, 等. 高性能纤维增强树脂基复合材料湿热老化研究进展[J]. 化工新型材料, 2024, 52 (1): 1-7. LI Jianan, JIANG Yaming, XIANG He, et al. Research progress on the hygrothermal aging of high-performance fiber reinforced resin matrix composites[J]. New Chemical Materials, 2024, 52 (1): 1-7. (in Chinese)
[9]	DEWHURST T B. The impact load on containment rings during a multiple blade shed in aircraft gas turbine engines[C]//Proceedings of the ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. Orlando, FL, USA: ASME, 1991.
[10]	RICHARDSON I J, HYDE T M, BECKER A A, et al. A three-dimensional finite element investigation of the bolt stresses in an aero-engine Curvic coupling under a blade release condition[J]. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 2000, 214 (4): 231-245. doi: 10.1243/0954410001532033
[11]	张伯熹, 宣海军, 吴荣仁. 航空发动机涡轮叶片包容模拟试验研究[J]. 机械工程师, 2006(10): 114-116. ZHANG Boxi, XUAN Haijun, WU Rongren. Research on aero-engine turbine blade containment experiment[J]. Mechanical Engineer, 2006(10): 114-116. (in Chinese)
[12]	古兴瑾. 复合材料层板高速冲击损伤研究[D]. 南京: 南京航空航天大学, 2011. GU Xingjin. Research on high velocity impact damage of composite laminates[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2011. (in Chinese)
[13]	蔡雄峰. 复合材料层合板高速冲击损伤研究[D]. 天津: 中国民航大学, 2020. CAI Xiongfeng. Research on high-speed impact damage of composite laminates[D]. Tianjin: Civil Aviation University of China, 2020. (in Chinese)
[14]	何庆, 宣海军, 刘璐璐. 某型发动机一级风扇机匣包容性数值仿真[J]. 航空动力学报, 2012, 27 (2): 295-300. HE Qing, XUAN Haijun, LIU Lulu. Numerical analysis of real aero-engine first-stage fan blade containment[J]. Journal of Aerospace Power, 2012, 27 (2): 295-300. (in Chinese)
[15]	杜长美. 三维四向编织复合材料湿热老化后低速冲击及其剩余压缩性能研究[D]. 哈尔滨: 哈尔滨理工大学, 2023. DU Changmei. Study on low-velocity impact and residual compression properties of three-dimensional four-directions braided composites after damp-heat aging[D]. Harbin: Harbin University of Science and Technology, 2023. (in Chinese)
[16]	MOKHTAR H, SICOT O, ROUSSEAU J, et al. The influence of ageing on the impact damage of carbon epoxy composites[J]. Procedia Engineering, 2011, 10 : 2615-2620. doi: 10.1016/j.proeng.2011.04.436
[17]	HOSUR M V, JAIN K, CHOWDHURY F, et al. Low-velocity impact response of carbon/epoxy laminates subjected to cold-dry and cold-moist conditioning[J]. Composite Structures, 2007, 79 (2): 300-311. doi: 10.1016/j.compstruct.2006.11.011
[18]	ZHANG C, BINIENDA W K, MORSCHER G N, et al. Experimental and FEM study of thermal cycling induced microcracking in carbon/epoxy triaxial braided composites[J]. Composites (Part A): Applied Science and Manufacturing, 2013, 46 : 34-44. doi: 10.1016/j.compositesa.2012.10.006
[19]	ATAS C, DOGAN A. An experimental investigation on the repeated impact response of glass/epoxy composites subjected to thermal ageing[J]. Composites Part B: Engineering, 2015, 75 : 127-134. doi: 10.1016/j.compositesb.2015.01.032
[20]	徐凯龙. 循环湿热作用下三维编织复合材料力学性能与抗冲击性能研究[D]. 南京: 南京航空航天大学, 2018. XU Kailong. Effect of cyclic hygrothermal aging on mechanical properties and impact resistance of three dimensional braided composites[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2018. (in Chinese)
[21]	LIU L, ZHAO Z, CHEN W, et al. An experimental investigation on high velocity impact behavior of hygrothermal aged CFRP composites[J]. Composite Structures, 2018, 204 : 645-657. doi: 10.1016/j.compstruct.2018.08.009
[22]	惠旭龙, 牟让科, 白春玉, 等. TC4钛合金动态力学性能及本构模型研究[J]. 振动与冲击, 2016, 35 (22): 161-168. HUI Xulong, MU Rangke, BAI Chunyu, et al. Dynamic mechanical property and constitutive model for TC4 titanium alloy[J]. Journal of Vibration and Shock, 2016, 35 (22): 161-168. (in Chinese)