主动冷却超燃冲压发动机最大工作马赫数评估  

Evaluation on maximum flight Mach number of active cooling scramjet

作　　者：王厚庆[1] 何国强[2] 刘佩进[2] 艾春安[1] 

机构地区：[1]第二炮兵工程学院,西安710025 [2]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2010年第4期377-381,共5页Journal of Solid Rocket Technology

摘　　要：采用主动冷却方式对超燃冲压发动机进行热防护是解决其长时间工作的有效措施。针对超燃冲压发动机燃烧室恶劣的热环境,设计了一种基于碳化硅陶瓷基复合材料的主动冷却结构,建立了发动机主动冷却结构设计的数学模型。引入发动机冷却液流量系数,从飞行器整体热防护角度出发,以发动机燃烧室主动冷却结构中冷却液的出口温度为依据来评价超燃冲压发动机可以达到的最大工作马赫数,以及分析发动机冷却液流量系数、飞行高度和燃烧室化学反应当量比对最大工作马赫数的影响。结果表明,增加冷却液流量系数、适当降低飞行高度、一定范围内提高化学反应当量比,可降低冷却液出口温度,从而提高发动机的最大工作马赫数。It is an effective measure to use active cooling structure in scramjet＇s TPS（thermal protection systems） to keep long duration engine operation.According to the severe thermal environment of scramjet,an active cooling structure based on ceramic matrix composite（CMC） was designed.The mathematical models on active cooling structure design were also developed.A factor called coolant mass flow ratio was introduced to analyze the maximum flight Mach number from the aspect of the whole vehicle＇s TPS.The exit temperature of coolant flowing through the coolant channel was used as an important baseline to evaluate the maximum flight Mach number of active cooling scramjet.Also some important factors including coolant mass flow ratio,flight altitute and combustion equivalence ratio were analyzed to study their influence on maximum flight Mach number.Results show that by enhancing coolant mass flow ratio,reducing flight height properly and increasing combustion equivalence ratio in a certain range,the exit temperature can be reduced and consequently the maximum flight Mach number can be enhanced.

关 键 词：主动冷却结构 超燃冲压发动机 吸热型碳氢燃料 最大工作马赫数 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]