氮化铝陶瓷燃气舵仿真与试验

白澔烔; 石仲仑; 薛海峰; 蔡红明

doi:10.13224/j.cnki.jasp.20210698

氮化铝陶瓷燃气舵仿真与试验

doi: 10.13224/j.cnki.jasp.20210698

1.
南京航空航天大学航天学院，南京 211106
2.
山东科技大学电气与自动化工程学院，山东青岛 266590
3.
南京理工大学机械工程学院，南京 210094

详细信息

作者简介:
白澔烔（2001-），男，博士生，研究领域为固体火箭发动机与CFD仿真。E-mail：Baiht0201@nuaa.edu.cn

中图分类号: V433.9
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- 文章访问数: 124
- HTML浏览量: 24
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- 被引次数: 0
出版历程
- 收稿日期: 2021-12-09
- 网络出版日期: 2024-01-24

Numerical simulation and test of AlN ceramic jet vane

1.
College of Astronautics，Nanjing University of Aeronautics and Astronautics，Nanjing 211106，China
2.
College of Electrical Engineering and Automation，Shandong University of science and technology，Qingdao Shandong 266590，China
3.
School of Mechanical Engineering，Nanjing University of Science and Technology，Nanjing 210094，China

摘要

摘要:
针对弹箭燃气舵轻量化问题，设计了基于高热导率氮化铝（AlN）陶瓷材料的新型燃气舵。为考察其可行性，建立了基于流固热耦合的非定常数值模拟方法，研究了氮化铝陶瓷燃气舵在不同舵偏角下的工作过程，并基于高温下陶瓷强度预测模型分析了燃气舵的抗热震能力。加工了氮化铝陶瓷燃气舵，开展了固体火箭发动机地面静态射流试验，并通过扫描电镜分析了试验结果。研究结果表明：数值仿真与试验结果基本一致，验证了数值模拟方法的有效性；对燃烧室总温为2284 K的固体火箭发动机，氮化铝陶瓷燃气舵可承受其燃气1 s内造成的最大机械冲击和热冲击；氮化铝陶瓷由于较高的热导率（理论达320 W/（m∙K）），有远优于常规结构陶瓷的抗热震性能，是一种良好的小型燃气舵选材。
- 氮化铝陶瓷 /
- 燃气舵 /
- 热耦合 /
- 热冲击 /
- 固体火箭
Abstract:
To solve the lightweight problem of rocket jet vanes, a new jet vane based on high thermal conductivity aluminum nitride (AlN) ceramic was designed. In order to investigate its feasibility, the unsteady numerical simulation method based on fluid-solid thermal coupling was established to research the working process of aluminum nitride ceramics jet vanes under different angles, and their thermal shock resistance was analyzed based on the ceramic strength prediction model in high temperature environment. AlN ceramic jet vanes were processed for the ground static jet test of solid rocket motor at different angles, and the test results were analyzed by SEM. The research showed that, the numerical simulation results were basically consistent with the test results, which verified the effectiveness of the numerical simulation method. For the solid rocket motor with the total temperature of 2284 K, AlN ceramic jet vanes can withstand the maximum mechanical shock and thermal shock caused by the engine gas in 1s. AlN ceramic had much better high thermal conductivity (320 W∙m⁻¹∙K⁻¹ theoretical) and thermal shock resistance than other structural ceramics. AlN ceramic is a good alternative material for small jet vane.
- AlN ceramic /
- jet vane /
- thermal coupling /
- thermal shock /
- solid rocket

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图 1 三维计算模型示意图

Figure 1. 3D computational model diagram

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图 2 燃气舵坐标系图

Figure 2. Jet vane coordinate system diagram

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图 3 燃气舵舵面分区及相关术语

Figure 3. Partition and terminology of jet vane

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图 4 计算网格图

Figure 4. Computational grid diagram

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图 5 计算边界条件设置

Figure 5. Calculation boundary conditions setting diagram

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图 6 圆管温度云图对比

Figure 6. Comparison of temperature contour of cylinder

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图 7 燃气舵表面受力曲线

Figure 7. Surface force curve of jet vane

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图 8 受力峰值点处压强云图

Figure 8. Pressure contours at peak stress point

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图 9 t=0.001 s时刻流场温度云图

Figure 9. Temperature contour of flow at t=0.001 s

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图 10 氮化铝燃气舵陶瓷各剖面温度场云图

Figure 10. Temperature of AlN ceramic jet vanes in different sections

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图 11 氧化铝燃气舵陶瓷各剖面温度场云图

Figure 11. Temperature of Al₂O₃ ceramic jet vanes in different sections

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图 12 t = 0.2 s时刻1/2展长处燃气舵表面温度曲线

Figure 12. Surface temperature curve at 1/2 span of jet vanes at t = 0.2 s

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图 13 t = 0.2 s时刻燃气舵yoz平面最大主应力云图

Figure 13. Maximum principal stress contours in yoz section of jet vanes at t = 0.2 s

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图 14 0.2 s内燃气舵最大主应力及材料强度曲线

Figure 14. Maximum principal stress and material strength curve of jet vanes in 0.2 s

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图 15 1 s内燃气舵最大主应力、热应变及材料强度曲线

Figure 15. Maximum principal stress, thermal strain and material strength curve of jet vanes in 1 s

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图 16 t = 1 s时刻燃气舵1/2展长处温度曲线

Figure 16. Surface temperature curve at 1/2 span of jet vanes at t = 1 s

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图 17 t = 1 s时刻燃气舵位移量云图

Figure 17. Deformation of jet vane at t = 1 s

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图 18 试验用陶瓷燃气舵图像

Figure 18. Photograph of ceramics jet vanes for test

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图 19 发动机工作过程内弹道曲线

Figure 19. Internal ballistic curve of the motor during working process

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图 20 测试后陶瓷燃气舵图像

Figure 20. Apparent morphology ceramics jet vanes after test

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图 21 氮化铝陶瓷燃气舵上激光切割损伤

Figure 21. Laser cutting damage on AlN jet vane

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图 22 氮化铝陶瓷燃气舵断面不同位置处微观图像

Figure 22. Micro-morphology of different positions on section of AlN jet vane

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表 1 计算用陶瓷材料参数

Table 1. Parameters of ceramic materials for calculation

材料参数	高导热氮化铝AlN	高纯氧化铝Al2O3
E/GPa	$ E=E_0-BT'{\mathrm{e}}^{- （T\mathrm{_{_m}}-273.15\; \mathrm{K}） /T'}+B_1[T'-B_2 （T_{\mathrm{m}}-273.15\; \mathrm{K}） +\|T'-B_2 （T_{\mathrm{m}}-273.15\; \mathrm{K}） \|]{\mathrm{e}}^{- （T_{\mathrm{m}}-273.15\; \mathrm{K}） /T'} $
ρ/（g/cm³）	3.26	3.98
ν, B, B₁, B₂	0.23, 2.05, 0.975, 0.0129	0.22, 2.1441, 0.9278, 0.0352
E₀/GPa	314	400.3
T_m/K	2785 （升华分解）	2323
k/（W/（m∙K））	6.812×10⁻⁵T ²−2.446T+386.22	27.5−0.0289T （298～1 200 K） 1.5 （1 200～2 327 K）
c_p/（J/（kg∙K））（A₁、A₂、A₃）	A₁+A₂×10⁻³T+A₃×10⁻⁵T⁻² （787.00, 553.32, −192.78）（298～600 K）（1224.78, 28.585, −635.46）（600～1000 K）（1222.95, 9.49, −424.32）（1000～2000 K）	A₁+A₂×10⁻³T+A₃×10⁻⁵T⁻² （1018.15, 257.52, 285.20）（298～800 K）（1181.53, 97.18, −474.22）（800～2327 K）
α₁/10⁻⁶ K⁻¹	1.68ln T − 6.3239	1.93ln T − 5.3167

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表 2 陶瓷材料温度性强度参数

Table 2. Temperature-dependent strength parameters of ceramic materials

材料参数	高导热氮化铝	高纯氧化铝
σ_th/MPa	${\sigma _{{\mathrm{th}}}} = \sigma _{{\mathrm{th}}}^0{\left\{ {\displaystyle\frac{{E （T'） }}{{{E_0}}}\left[ {1 - \displaystyle\frac{{\displaystyle\int_0^{T'} {{c_p} （T） {\text{d}}T} }}{{\displaystyle\int_0^{{T_{\mathrm{m}}}} {{c_p} （T） {\text{d}}T} }}} \right]} \right\}^{{1/2}}}$
${\sigma ^0_{{\mathrm{th}}}} $/MPa	350	350

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表 3 受力峰值点处的静力学求解数据

Table 3. Static solution data at peak stress point

材料	偏角/（°）	最大主应力/MPa	最大位移/μm	安全系数
AlN	0	4.813	1.271	83.108
AlN	20	34.687	25.62	11.532
Al₂O₃	0	4.952	1.262	70.679
Al₂O₃	20	35.103	24.81	8.468

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表 4 常温下试验用陶瓷材料参数

Table 4. Parameters of ceramic materials for test at normal temperature

材料参数	高导热氮化铝AlN	高纯氧化铝Al₂O₃
E/GPa	320	300
ρ/（g/cm³）	3.3	3.7
ν	0.23	0.22
k/（W/（m∙K））	200	24
α₁/10⁻⁶ （K⁻¹）	4.6	7.5
σ_th/MPa	320	300

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