C/SiC材料主被动氧化烧蚀机理及计算方法研究
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摘要
基于热化学平衡方法建立了任意比例C/SiC材料的主被动氧化烧蚀模型,开展了C/SiC材料氧化烧蚀机理的计算研究,并基于典型材料烧蚀试验结果进行了充分验证。计算结果表明,C/SiC材料的氧化烧蚀特性取决于表面温度、氧分压以及组分等因素,可能会出现主动氧化和被动氧化两种破坏机制,目前的烧蚀模型能够预测出任意比例C/SiC材料两种氧化烧蚀机制的转换过程;SiC含量对C/SiC材料的氧化烧蚀特性有明显的影响,随着SiC含量的提升,主/被动氧化转换临界分压会减小,材料的抗氧化性能越好;但当材料均处于主动氧化阶段时,SiC含量越高材料的无量纲烧蚀速率越大,材料的抗烧蚀性能减弱。
The thermochemical ablation model for the C/SiC composite is established. The active/passive ablation performance of the C/SiC composite is studied numerically. The computational results conform well with the experimental results in the published literatures. The results indicate that the oxidation and ablation characteristics of the C/SiC materials depend on the surface temperature, oxygen partial pressure and material components. Two possible failure mechanisms, active oxidation and passive oxidation, may occur. The oxidation transition process could be predicted by the current model. The mass fraction of SiC would affect the ablation performance of C/SiC composite obviously. The composite is prone to cause the passive oxidation with the increase of the SiC mass fraction.
The thermochemical ablation model for the C/SiC composite is established. The active/passive ablation performance of the C/SiC composite is studied numerically. The computational results conform well with the experimental results in the published literatures. The results indicate that the oxidation and ablation characteristics of the C/SiC materials depend on the surface temperature, oxygen partial pressure and material components. Two possible failure mechanisms, active oxidation and passive oxidation, may occur. The oxidation transition process could be predicted by the current model. The mass fraction of SiC would affect the ablation performance of C/SiC composite obviously. The composite is prone to cause the passive oxidation with the increase of the SiC mass fraction.
引文
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[10] 潘育松,徐永东,陈照峰,等. 固体火箭发动机用C/SiC导流管烧蚀性能研究[J]. 宇航学报, 2005, 26(6): 789-792. [Pan Yu-song, Xu Yong-dong, Chen Zhao-feng, et al. Analysis of the ablation properties of C/SiC diversion tube used in solid rocket motor[J]. Journal of Astronautics, 2005, 26(6): 789-792.]
[11] Williams S D, Curry D M, Chao D C, et al. Ablation analysis of the shuttle orbiter oxidation protected reinforced carbon-carbon[J]. Journal of Thermophysics and Heat Transfer, 1995, 9(3): 478-485.
[12] Balat M J H, Flamant G, Male G. Active to passive transition in the oxidation of silicon carbide at high temperature and low pressure in molecular and atomic oxygen[J]. Journal of Materials Science, 1992, 27: 697-703.
[13] Balat M J H. Determination of the active-to-passive transition in the oxidation of silicon carbide in standard and microwave-excited air[J]. Journal of the European Ceramic Society, 1996, 16: 55-62.
[14] Heuer A H, Lou V L K. Volatility diagrams for silica, silicon nitride, and silicon carbide and their application to high-temperature decomposition and oxidation[J]. Journal of the American Ceramic Society, 1990, 73: 2789-2803.
[15] Deng D Y, Luo X G, Chen S Y, et al. Calculation study of the active oxidative ablation of C/SiC[J]. Science in China Series E: Technological Sciences, 2013, 43(7): 801-806.
[2] 付前刚,张佳平,李贺军. 抗烧蚀C/C复合材料研究进展[J]. 新型碳材料, 2015, 30(2): 97-105. [Fu Qian-gang, Zhang Jia-ping, Li He-jun. Advances in the ablation resistance of C/C composites[J]. New Carbon Materials, 2015, 30(2): 97-105.]
[3] 姜贵庆,刘连元. 高速气流传热与烧蚀热防护[M]. 北京:国防工业出版社, 2003.
[4] Milos F S, Jochen M. Thermochemical ablation model for TPS materials with multiple surface constituents[R].AIAA 94-2042.
[5] Milos F S, Chen Y K. Comprehensive model for multicomponent ablation thermochemistry[R].AIAA 97-0141.
[6] Chen Y K, Milos F S. Ablation and thermal response program for spacecraft heatshield analysis[J]. Journal of Spacecraft and Rockets, 1999, 36(3): 475-483.
[7] Milos F S, Gasch M J, Prabhu D K. Conformal phenolic impregnated carbon ablator arcjet testing, ablation, and thermal response[J]. Journal of Spacecraft and Rockets, 2015, 52(3): 804-812.
[8] 邓代英,陈思员,俞继军,等. C/SiC材料主动氧化烧蚀计算研究[J]. 空气动力学学报, 2011, 29(4): 496-500. [Deng Dai-ying, Chen Si-yuan, Yu Ji-jun, et al. Calculation study of the active oxidative ablation of C/SiC[J]. Acta Aerodynamica Sinica, 2011, 29(4): 496- 500.]
[9] 国义军,桂业伟,童福林,等. C/SiC复合材料烧蚀机理和通用计算模型研究[J]. 空气动力学学报, 2012, 30(1): 34-38. [Guo Yi-jun, Gui Ye-wei, Tong Fu-lin, et al. Thermo-chemical ablation mechanisms and general relationship for C/SiC material oxidation[J]. Acta Aerodynamica Sinica, 2012, 30(1): 34-38.]
[10] 潘育松,徐永东,陈照峰,等. 固体火箭发动机用C/SiC导流管烧蚀性能研究[J]. 宇航学报, 2005, 26(6): 789-792. [Pan Yu-song, Xu Yong-dong, Chen Zhao-feng, et al. Analysis of the ablation properties of C/SiC diversion tube used in solid rocket motor[J]. Journal of Astronautics, 2005, 26(6): 789-792.]
[11] Williams S D, Curry D M, Chao D C, et al. Ablation analysis of the shuttle orbiter oxidation protected reinforced carbon-carbon[J]. Journal of Thermophysics and Heat Transfer, 1995, 9(3): 478-485.
[12] Balat M J H, Flamant G, Male G. Active to passive transition in the oxidation of silicon carbide at high temperature and low pressure in molecular and atomic oxygen[J]. Journal of Materials Science, 1992, 27: 697-703.
[13] Balat M J H. Determination of the active-to-passive transition in the oxidation of silicon carbide in standard and microwave-excited air[J]. Journal of the European Ceramic Society, 1996, 16: 55-62.
[14] Heuer A H, Lou V L K. Volatility diagrams for silica, silicon nitride, and silicon carbide and their application to high-temperature decomposition and oxidation[J]. Journal of the American Ceramic Society, 1990, 73: 2789-2803.
[15] Deng D Y, Luo X G, Chen S Y, et al. Calculation study of the active oxidative ablation of C/SiC[J]. Science in China Series E: Technological Sciences, 2013, 43(7): 801-806.