Al20Si/Gr耗散防热材料氧—乙炔和发动机燃烧室烧蚀性能研究
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摘要
本文通过专利技术(ZL200810064995.2)制备得Al20Si/Gr耗散防热材料,其中基体为多孔石墨,耗散剂为Al20Si。利用万能电子试验机测试了常温和高温弯曲强度、压缩强度。采用氧-乙炔烧蚀试验和超燃冲压发动机燃烧室烧蚀试验考察了Al20Si/Gr耗散防热材料在不同烧蚀时间和不同冷却条件下的烧蚀行为,通过SEM、XRD、EDS等分析测试手段对烧蚀后材料的表面形貌及微区成分,表面及内部的物相组成进行了分析,进而探讨了Al20Si/Gr耗散防热材料在烧蚀过程中陶瓷膜的形成过程、体积烧蚀效应及耐烧蚀机理。
Al20Si/Gr耗散防热材料的常温弯曲强度较基体提高了3.5倍,常温压缩强度较基体提高了1.3倍。在20-1000℃内,随着温度的升高,Al20Si/Gr耗散防热材料的弯曲强度逐渐下降;压缩强度先下降后上升,750℃时降至最低,1000℃时又升至175MPa。
在氧-乙炔烧蚀条件下,Al20Si/Gr耗散防热材料60s一次烧蚀时线烧蚀率为5.0×10~(-3)mm/s,60s二次烧蚀的线烧蚀率较之降低了60%,较石墨基体降低了两个数量级。烧蚀表面分为中心区、过渡区和边缘区。烧蚀时间超过30s,中心区出现烧蚀坑,改变了气流方向,使得过渡区中出现明显大颗粒金属氧化物,边缘区由网状金属氧化物构成。Al20Si/Gr耗散防热材料的体积烧蚀效应为:从材料表面至背部,物相组成呈梯度分布,依次为:C+Al_2O_3+SiO_2,C+Al_4SiC4,C+Al_4SiC4+SiC+Al_4C_3,C+SiC+Al_4C_3,C+Si+Al+Al_4C_3。
耗散防热材料的抗烧蚀机理主要体现在以下几个方面:第一,烧蚀过程中耗散剂的熔化吸热;第二,陶瓷膜的热阻隔和氧阻隔效应;第三,陶瓷膜对气流冲刷的缓冲作用。
发动机燃烧室烧蚀温度约为800℃,表面形成的保护膜提高了材料的耐气流冲刷性,材料内部相组成为Al、Si和C,距烧蚀面越近,Al和Si含量越低。
In this thesis, Al20Si/Gr transpiring coolant materials were prepared by a patent technology(ZL200810064995.2). Porous graphite was used as matrix and Al20Si was used as refrigerant. The composite was denoted by Al20Si/Gr. The flexural strength and compression strength under room temperature and high temperature were tested by multi-purpose electronic testing machines. The behavior of Al20Si/Gr transpiring coolant materials under different ablation time and cooling condition was studied by oxygen-ethane torch heating test and ramjet combustor heating test. The surface morphology and microzone component after ablation were researched by scanning electron microscope(SEM) and energy spectrometer. The surface and inner phase composition were studied by X-ray diffraction(XRD). After that, the forming process of metal oxides film, the effect of volume ablation and the ablation mechanism were disscussed.
The experiment results showed that the flexural strength and compression strength of Al20Si/Gr transpiring coolant materials under room temterature were 3.5 times and 1.3 times more than that of graphite matrix respectively. With the temperature increasing, the flexural strength of Al20Si/Gr transpiring coolant materials decreased gradually. The compression strength got its minimum value at 750℃, and rebounded to 175MPa at 1000℃.
Under the oxygen-ethane torch heating condition, the linear ablation rate of Al20Si/Gr transpiring coolant materials was 5.0×10~(-3)mm/s, the linear ablation rate of twice~(-3)0s-ablation was 60% than that of once-60s-ablation, which was two orders of magnitude lower than that of the graphite matrix. The ablation surface morphology could be divided into three parts: central ablation area, transition region and marginal zone. As the ablation time increased to 30s, pits emerged in the central ablation area, which played an important part on the forming process of metal oxides film. Large particle metal oxides appeared in transition region. The marginal zone was made up of reticular metal oxides. During the forming process of the metal oxides film, the metal melted and absorb the heat. The metal oxides film firstly could prevent the heat transfer and oxygen transfer and then decrease the scouring effect of airflow. These three effects together increased the ablation properties of Al20Si/Gr transpiring coolant materials. During typical ablation process, the phase composition was C+Al_2O_3+SiO_2 , C+Al4SiC_4 ,C+Al4SiC_4+SiC+Al4C_3,C+SiC+Al4C_3,C+Si +Al4C_3 in sequence from surface to tail. The linear ablation rate of twice-30s-ablation was much lower than that of once-60s-ablation. The surface phase composition under twice-30s-ablation was C+Al_2O_3+ Al4SiC_4.
With low-temperature, the ramjet combustor heating condition was quite different from the oxygen-ethane torch heating condition. The protective film increased the air flow scouring resistence of Al20Si/Gr transpiring coolant materials. The inner phase composition was Al、Si and C. The content of Al and Si decreased as the decreasing of the distance from ablation surface.
Al20Si/Gr耗散防热材料的常温弯曲强度较基体提高了3.5倍,常温压缩强度较基体提高了1.3倍。在20-1000℃内,随着温度的升高,Al20Si/Gr耗散防热材料的弯曲强度逐渐下降;压缩强度先下降后上升,750℃时降至最低,1000℃时又升至175MPa。
在氧-乙炔烧蚀条件下,Al20Si/Gr耗散防热材料60s一次烧蚀时线烧蚀率为5.0×10~(-3)mm/s,60s二次烧蚀的线烧蚀率较之降低了60%,较石墨基体降低了两个数量级。烧蚀表面分为中心区、过渡区和边缘区。烧蚀时间超过30s,中心区出现烧蚀坑,改变了气流方向,使得过渡区中出现明显大颗粒金属氧化物,边缘区由网状金属氧化物构成。Al20Si/Gr耗散防热材料的体积烧蚀效应为:从材料表面至背部,物相组成呈梯度分布,依次为:C+Al_2O_3+SiO_2,C+Al_4SiC4,C+Al_4SiC4+SiC+Al_4C_3,C+SiC+Al_4C_3,C+Si+Al+Al_4C_3。
耗散防热材料的抗烧蚀机理主要体现在以下几个方面:第一,烧蚀过程中耗散剂的熔化吸热;第二,陶瓷膜的热阻隔和氧阻隔效应;第三,陶瓷膜对气流冲刷的缓冲作用。
发动机燃烧室烧蚀温度约为800℃,表面形成的保护膜提高了材料的耐气流冲刷性,材料内部相组成为Al、Si和C,距烧蚀面越近,Al和Si含量越低。
In this thesis, Al20Si/Gr transpiring coolant materials were prepared by a patent technology(ZL200810064995.2). Porous graphite was used as matrix and Al20Si was used as refrigerant. The composite was denoted by Al20Si/Gr. The flexural strength and compression strength under room temperature and high temperature were tested by multi-purpose electronic testing machines. The behavior of Al20Si/Gr transpiring coolant materials under different ablation time and cooling condition was studied by oxygen-ethane torch heating test and ramjet combustor heating test. The surface morphology and microzone component after ablation were researched by scanning electron microscope(SEM) and energy spectrometer. The surface and inner phase composition were studied by X-ray diffraction(XRD). After that, the forming process of metal oxides film, the effect of volume ablation and the ablation mechanism were disscussed.
The experiment results showed that the flexural strength and compression strength of Al20Si/Gr transpiring coolant materials under room temterature were 3.5 times and 1.3 times more than that of graphite matrix respectively. With the temperature increasing, the flexural strength of Al20Si/Gr transpiring coolant materials decreased gradually. The compression strength got its minimum value at 750℃, and rebounded to 175MPa at 1000℃.
Under the oxygen-ethane torch heating condition, the linear ablation rate of Al20Si/Gr transpiring coolant materials was 5.0×10~(-3)mm/s, the linear ablation rate of twice~(-3)0s-ablation was 60% than that of once-60s-ablation, which was two orders of magnitude lower than that of the graphite matrix. The ablation surface morphology could be divided into three parts: central ablation area, transition region and marginal zone. As the ablation time increased to 30s, pits emerged in the central ablation area, which played an important part on the forming process of metal oxides film. Large particle metal oxides appeared in transition region. The marginal zone was made up of reticular metal oxides. During the forming process of the metal oxides film, the metal melted and absorb the heat. The metal oxides film firstly could prevent the heat transfer and oxygen transfer and then decrease the scouring effect of airflow. These three effects together increased the ablation properties of Al20Si/Gr transpiring coolant materials. During typical ablation process, the phase composition was C+Al_2O_3+SiO_2 , C+Al4SiC_4 ,C+Al4SiC_4+SiC+Al4C_3,C+SiC+Al4C_3,C+Si +Al4C_3 in sequence from surface to tail. The linear ablation rate of twice-30s-ablation was much lower than that of once-60s-ablation. The surface phase composition under twice-30s-ablation was C+Al_2O_3+ Al4SiC_4.
With low-temperature, the ramjet combustor heating condition was quite different from the oxygen-ethane torch heating condition. The protective film increased the air flow scouring resistence of Al20Si/Gr transpiring coolant materials. The inner phase composition was Al、Si and C. The content of Al and Si decreased as the decreasing of the distance from ablation surface.
引文
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