TG800碳纤维/聚酰亚胺树脂复合材料带翻边开口圆柱壳机匣件高温气动载荷下的承载性能

杨峰; 陈玉龙; 罗旺; 史剑; 贾林江; 陈子光

doi:10.13801/j.cnki.fhclxb.20210326.001

TG800碳纤维/聚酰亚胺树脂复合材料带翻边开口圆柱壳机匣件高温气动载荷下的承载性能

doi: 10.13801/j.cnki.fhclxb.20210326.001

杨峰^{1, 3, ,},
陈玉龙^2,,
罗旺^{1, 3,},
史剑^2,,
贾林江^2,,
陈子光^4,

1.
天津航天瑞莱科技有限公司，天津 300462
2.
中国航发四川燃气涡轮研究院，成都 610500
3.
北京强度环境研究所，北京 100076
4.
华中科技大学　航空航天学院，武汉 430074

详细信息

通讯作者:
杨峰，硕士，工程师，研究方向为复合材料、强度、可靠性、试验　E-mail：yangf@relialab.com

中图分类号: TB332；V216
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出版历程
- 收稿日期: 2021-01-19
- 录用日期: 2021-03-07
- 网络出版日期: 2021-03-29
- 刊出日期: 2021-07-15

Load-bearing capability of TG800 carbon fiber/polyimide resin composite cylindrical casing with flange and window under high-temperature aerodynamic load

YANG Feng^{1, 3
, ,},
CHEN Yulong^2
,,
LUO Wang^{1, 3
,},
SHI Jian^2
,,
JIA Linjiang^2
,,
CHEN Ziguang^4
,

1.
Tianjin Aerospace Reliability Technology Co., Ltd., Tianjin 300462, China
2.
AECC Sichuan Gas Turbine Establishment, Chengdu 610500, China
3.
Beijing Institute of Structure and Environment Engineering, Beijing 100076, China
4.
School of Aerospace Engineering, Huazhong University of Science and Technology, Wuhan 430074, China

摘要

摘要: 基于航空发动机的高温气动载荷环境，对树脂传递模塑(RTM)工艺制备的TG800碳纤维/聚酰亚胺树脂复合材料带安装翻边和壳壁开口的圆柱壳机匣件开展了常温、200℃和260℃高温气动载荷下的仿真分析和承载性能试验。仿真计算得到复合材料机匣件的高应力水平发生在安装翻边和开口处。试验利用所设计的专用试验装置与机匣试验件合围成一套能够解耦内压和轴力的被试腔体结构，通过对被试腔体施加高温气体压力和机械静载联合模拟热气流载荷，相比传统的冲压胶囊加压方式，可以对机匣的翻边和开口处进行充分热压考核。常温、200℃和260℃承载试验后对机匣开口进行了无损检测，得到开口处的分层损伤区域随着载荷增大朝着正方和正圆的趋势扩大，260℃破坏试验得到TG800碳纤维/聚酰亚胺树脂复合材料机匣件的失效模式与传统金属机匣的筒体破裂不同，失效方式为安装翻边断裂。研究表明，RTM工艺TG800碳纤维/聚酰亚胺树脂复合材料结构件的力学性能在200℃以内具备良好的温度稳定性，安装翻边为复合材料机匣件在航空发动机热气流载荷下的薄弱区域，应作为机匣件减重设计的重要优化部位。
- 碳纤维 /
- 发动机机匣 /
- 高温承载试验 /
- 无损检测 /
- 失效模式
Abstract: Based on the high-temperature aerodynamic load environment of aero-engines, the high temperature resistant TG800 carbon fiber/polyimide resin composite cylindrical casing test piece, which with flanges for installation and window openings on the casing wall, prepared by the resin transfer molding (RTM) process was carried out simulation analysis and load-bearing performance test under room temperature, 200℃ and 260℃ high-temperature aerodynamic load. The simulation results show that the high stress level of the composite casing occurs at the installation flange and the window of the shell wall. In the load-bearing test, the designed special test device and the composite casing test piece are combined to form a test chamber structure that can decouple the internal pressure and the axial force during loading. By applying high-temperature gas pressure and mechanical static load to the designed special test cavity to simulate the high-temperature aerodynamic load of the aero-engine, compared with the traditional pressurization method of stamping capsule, it can achieve more realistic assessment of the casing flange and window. The non-destructive testing on the window of the casing after the load-bearing test at room temperature, 200℃ and 260℃ shows that the delamination damage area at the window expands towards a larger square and circular shape as the load increases. The failure mode of the TG800 carbon fiber/polyimide resin composite casing obtained by the 260℃ destruction test is installation flanging fracture, which is different from the failure mode of the traditional metal casing cylinder rupture. The results indicate that the mechanical properties of TG800 carbon fiber/polyimide resin composite structural components prepared by RTM process have good temperature stability within 200℃. The installation flanging is the weak area of the composite casing under the high temperature aerodynamic load of the aero engine, which is an important optimization part for the weight reduction design of the casing.
- carbon fiber /
- aero-engine casing /
- high-temperature mechanical testing /
- non-destructive testing /
- failure modes

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图 1 TG800碳纤维/聚酰亚胺树脂复合材料机匣试验件结构示意图

Figure 1. Schematic of TG800 carbon fiber/polyimide resin composite casing test piece

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图 2 插层补强的结构示意图

Figure 2. Structure diagram of intercalation reinforcement

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图 3 复合材料机匣试验件有限元模型

Figure 3. FEM model of composite casing test piece

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图 4 复合材料机匣试验件承载和破坏工况仿真结果

Figure 4. Simulation results of load-bearing and damage conditions of composite casing test pieces

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图 5 综合试验装置

Figure 5. Comprehensive loading test device

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图 6 环形加热器模型

Figure 6. Ring heater model

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图 7 TG800碳纤维/聚酰亚胺树脂复合材料机匣承载试验流程

Figure 7. Process of TG800 carbon fiber/polyimide resin composite casing load-bearing test

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图 8 TG800碳纤维/聚酰亚胺树脂复合材料机匣破坏试验流程

Figure 8. Process of TG800 carbon fiber/polyimide resin composite casing destruction test

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图 9 常温下各载荷分量作用下TG800碳纤维/聚酰亚胺树脂复合材料机匣试验件的应变数据

Figure 9. Strain data of TG800 carbon fiber/polyimide resin composite casing test piece under various load components at room temperature

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图 10 常温下不同载荷分量作用下TG800碳纤维/聚酰亚胺树脂复合材料机匣试验件的位移数据

Figure 10. Displacement data of TG800 carbon fiber/polyimide resin composite casing test piece under various load components at room temperature

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图 11 不同温度各载荷分量作用下TG800碳纤维/聚酰亚胺树脂复合材料机匣试验件的位移数据

Figure 11. Displacement data of TG800 carbon fiber/polyimide resin composite casing test piece under various load components at different temperatures

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图 12 不同温度各载荷分量作用下TG800碳纤维/聚酰亚胺树脂复合材料机匣试验件的应变数据

Figure 12. Strain data of the TG800 carbon fiber/polyimide resin composite casing test piece under various load components at different temperatures

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图 13 不同温度承载试验下TG800碳纤维/聚酰亚胺树脂复合材料机匣试验件的轴向位移数据

Figure 13. Axial displacement data of TG800 carbon fiber/polyimide resin composite casing test piece under different temperature load-bearing tests

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图 14 不同温度承载试验下TG800碳纤维/聚酰亚胺树脂复合材料机匣试验件的径向位移数据

Figure 14. Radial displacement data of TG800 carbon fiber/polyimide resin composite casing test piece under different temperature load-bearing tests

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图 15 TG800碳纤维/聚酰亚胺树脂复合材料机匣试验件在承载试验中随着载荷增大试验件开口处分层的扩展情况

Figure 15. Expansion of delamination at opening of TG800 carbon fiber/ polyimide resin composite casing test piece as load increases during load-bearing test

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图 16 TG800碳纤维/聚酰亚胺树脂复合材料机匣试验件破坏试验的失效照片

Figure 16. Failure photos of TG800 carbon fiber/polyimide resin composite casing test piece failure test

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图 17 TG800碳纤维/聚酰亚胺树脂复合材料机匣试验件破坏试验的温度载荷控制曲线

Figure 17. Temperature load control curve in failure test of TG800 carbon fiber/polyimide resin composite casing test piece

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图 18 TG800碳纤维/聚酰亚胺树脂复合材料机匣试验件破坏试验的轴向力载荷控制曲线

Figure 18. Axial force control curve in failure test of TG800 carbon fiber/polyimide resin composite casing test piece

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图 19 TG800碳纤维/聚酰亚胺树脂复合材料机匣试验件破坏试验的压力载荷控制曲线

Figure 19. Pressure load control curve in failure test of TG800 carbon fiber/polyimide resin composite casing test piece

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表 1 TG800碳纤维/聚酰亚胺树脂复合材料单层板性能参数

Table 1. Performance parameters of TG800 carbon fiber/polyimide resin composite single-layer board

Sample	Ambient	260℃
Density/(g·cm⁻³)	1.50	1.50
Poisson’s ratio ν₁₂	0.317	0.317
0° Tension strength/MPa	2213	1821
0° Tension modulus/GPa	155	155
0° Compression strength/MPa	1431	665
0° Compression modulus/GPa	144	—
90° Tension strength/MPa	39	22.5
90° Tension modulus/GPa	7.6	4
90° Compression strength/MPa	220	96.4
90° Compression modulus/GPa	8.73	—
0° Bending strength/MPa	1881	1027
0° Bending modulus/GPa	147	149
Interlayer shear strength/MPa	106	51.3
In-plan shear strength/MPa	71	34
In-plan shear modulus/GPa	4.1	2.6

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表 2 TG800碳纤维/聚酰亚胺树脂复合材料机匣试验件载荷条件

Table 2. Load condition of TG800 carbon fiber/polyimide resin composite casing test piece

Sample	Temperature T/℃	Internal pressure P/MPa	Mechanical load
Sample	Temperature T/℃	Internal pressure P/MPa	Axial load F_z/N	Torque load M_z/(N·m)
Load-bearing condition	Ambient	0.39	112978	−2975
	200	0.39	112978	−2975
	260	0.67	174100	−5475
Damage condition	260	0.67~	174100~	−5475~
Notes: The load-bearing condition is that aero-engine may occur during the flight; Damage condition is the damage test load of the aero-engine.

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