炭/陶喷管延伸段长时间抗氧化能力研究
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摘要
基于炭/陶复合材料喷管在高温下易与水蒸气发生氧化而引起烧蚀失效的现象,通过研究预制体的制备工艺以及致密化等技术途径,突破炭/陶复合材料在富水蒸气环境下长时间抗氧化技术,使面积比为7～20的工艺喷管能够经受住室压4.1MPa,混合比5.7,燃气温度2 300 K(静温)长达780 s的地面热试车考核,测得的最高外壁温度约1 800 K,试后结构基本完好,炭/陶喷管质量流失率为2.28%,为炭/陶复合材料喷管在液体火箭发动机上的工程应用奠定了基础。
In order to solve the material oxidation behavior at high temperature, the technology and systems including specific processes for manufacturing reinforcement pre-forms for composite materials and textile densification process are very important. A C/SiC-C nozzle extension at the area ratio of 7～20 has been successfully tested at sea level at a combustion-chamber pressure of 4.1 MPa,a mixture ratio of 5.7 and at temperatures of 2 300 K for the entire test duration of 780 s, the maximum wall temperatures of up to 1 800 K was determined. The nozzle with a mass loses of 2.28% was able to demonstrate its long-term stability and high chemical compatibility versus the propellants and combustion products. Based on these experiences the development of C/SiC-C nozzle extension in the field of liquid-propellant rocket engines is continued.
In order to solve the material oxidation behavior at high temperature, the technology and systems including specific processes for manufacturing reinforcement pre-forms for composite materials and textile densification process are very important. A C/SiC-C nozzle extension at the area ratio of 7～20 has been successfully tested at sea level at a combustion-chamber pressure of 4.1 MPa,a mixture ratio of 5.7 and at temperatures of 2 300 K for the entire test duration of 780 s, the maximum wall temperatures of up to 1 800 K was determined. The nozzle with a mass loses of 2.28% was able to demonstrate its long-term stability and high chemical compatibility versus the propellants and combustion products. Based on these experiences the development of C/SiC-C nozzle extension in the field of liquid-propellant rocket engines is continued.
引文
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[2]R A Ellis,J C Lee.Testing of the RL10B-2 CarbonCarnon nozzle extension[J].AIAA,1998:3363.
[3]F Jean,P Alliot.Development status of the VINCI engine for Ariane 5 upper stage[J].AIAA,2001:3553.
[4]P Alliot,F Delange,E Edeline,et al.The VINCI upper stage engine:toward the demonstration of maturity[J].A-IAA,2013:4054.
[5]陈博,张立同,成来飞,等.3D C/SiC复合材料喷管在小型固体火箭发动机中的烧蚀规律研究[J].无机材料学报,2008,23(5):938-944.
[6]Cui Hong,Li Hejun,Zhang Xiaohu,et al.The large area ratio C/C extend cone of the liquid rocket motor[J].IAC-08-C2.I.1
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