超燃冲压发动机用SCO_(2)闭式回热布雷顿循环的热电转换系统性能分析

Performance Analysis of SCO,Reheat Closed Brayton Cycle Thermoelectric Conversion System for a Scramjet Engine

针对高超声速飞行器的供电和热防护需求,本文提出了一种基于超临界二氧化碳(SCO_(2))闭式回热布雷顿循环(RCBC)的热电转换系统,建立了一个由超燃冲压发动机燃烧室、壁面冷却通道和SCO_(2),RCBC组成的耦合模型来评估系统性能。对比了燃烧室与冷却通道耦合和不耦合的差距;分析了冷却流体进人冷却通道时的进口参数对系统热防护以及供电的影响。结果表明,热电转换系统通过将部分热量转化为电能,在对发动机进行热防护的同时,可以为高超声速飞行器提供25.14kW的电能。

This study proposes a thermoelectric conversion system based on a supercritical carbon dioxide(SCO2)reheat closed Brayton cycle(RCBC)to address hypersonic flight vehicles power supply and thermal protection requirements.A coupled model consisting of the combustion chamber of a scramjet engine,a wall cooling channel,and a SCO,RCBC is established to evaluate the system performance.The study compares the difference when the combustion chamber is coupled and uncoupled to the cooling channel,analyses the influence of the coolant inlet parameters on the thermal protection and power supply of the system.The results show that the thermoelectric conversion system is capable of providing 25.14 kW electrical power to a hypersonic flight vehicle while also providing thermal protection to the engine.