摘要
热防护技术是发展高超音速的关键技术之一。为了降低冷却用燃料需求,本文提出了基于闭式Brayton循环的超燃冲压发动机冷却循环,旨在提出一个缓解超燃冲压发动机热防护压力的新方法、新思路,同时可为高超音速飞行器提供足够的电力供应。文中介绍了冷却循环的组成和工作原理,定义了评价冷却循环性能的参数,在考虑系统内、外不可逆性的基础上,完成了系统的性能分析,分析表明该冷却循环可有效地节约冷却用燃料消耗,大幅提升超燃冲压发动机热防护系统性能。
One of the main issues of hypersonic flight is the thermal protection of the overall vehicle. Cooling cycle of scramjet based on closed Brayton cycle is presented to decrease the requirement of coolant flow rate, which is a new method and a new way to mitigate the difficulty of the thermal protection of scramjet engine, and it will provide adequate electric power for the whole hypersonic vehicle. The composition and working principle are introduced, the parameter used for evaluating the cooling cycle is defined, system performance analysis is performed based on the consideration of the irreversible process. The analysis indicates that the cooling cycle could effectively save the consumption of the fuel used as coolant and improve the thermal protection system performance of scrarnjet engine.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2008年第12期1985-1989,共5页
Journal of Engineering Thermophysics
基金
国家自然科学基金(No.50306003)
