C/SiC陶瓷基复合材料燃烧室壁厚设计与验证

Wall thickness design of combustion chamber for C/SiC composites rocket engine

C/SiC复合材料发动机具有重量轻、工作温度高等优势,已成为下一代高性能发动机的重要发展方向,其中C/SiC复合材料燃烧室的强度与壁厚设计是发动机设计的关键技术之一。本文以薄壳理论和第四强度理论为基础,以环向拉伸强度为基础数据,推导了C/SiC复合材料燃烧室壁厚计算公式,并对某型号发动机燃烧壁厚进行了计算。未验证计算结果准确性,利用复合材料燃烧室试件的爆破试验对计算结果进行了验证,并对根据计算结果研制的C/SiC复合材料燃烧室进行了热试车考核验证。本文提出的研究计算方法与结果对其他C/SiC复合材料燃烧室的壁厚设计具有指导意义。

Carbon fibers reinforced silicon carbide composites （C/SiC） are the most promising materials for next generation rocket engine components due to their unique properties, such as low densities and extremely high temperature resistance. The intensity and wall thickness design of C/SiC composites combustion chamber is one of the key tasks for rocket engine design. Based on the thin shell theory and the fourth intensity theory, this research deduced an ideal thickness calculation formula for composites chamber, which was used to calculate the wall thickness of a certain type of rocket engine combustion chamber. The validity of the formula was checked through subscale C/SiC tube by burst-test and thrust chamber by hot fire test. The formula and results proposed in this paper can be widely applied to the design of the wall thickness of C/SiC composites combustion chamber.