基于分析法的RBCC引射模态能量利用规律  

RBCC energy utilization rule during ejector mode based on exergy analysis method

作　　者：董泽宇[1] 李大鹏 王振国[1] DONG Zeyu;LI Dapeng;WANG Zhenguo(Science and Technology on Scramjet Laboratory,College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]国防科技大学空天科学学院高超声速冲压发动机技术重点实验室,长沙410073

出　　处：《航空动力学报》2018年第7期1787-1792,共6页Journal of Aerospace Power

摘　　要：为实现RBCC(火箭基组合循环)节约燃料的目的,基于分析法,研究了引射模态下发动机典型部件和系统能量利用与转化的规律。结果表明:引射火箭在RBCC发动机主体部件中损失最大,效率最低(48%~62%);发动机效率随来流马赫数的增加而不断增大,当来流马赫数小于2.5时,增长速度缓慢;当来流马赫数大于2.5时,增长速度加快;作为一种能量经济性指标,突破了以往基于热力学第一定律的发动机性能分析的局限性,通过单一参数将进气道、引射火箭和混合室等独立部件耦合起来,可全面评价组合循环发动机能量综合利用的性能,指导发动机设计和能量优化工作。In order to achieve the purpose of saving fuel,based on the exergy analysis method,the energy utilization and conversion rule of RBCC（rocket based combined cycle）typical components and systems in ejector mode was investigated.Results showed that the ejector rocket had the largest exergy loss and the lowest exergy efficiency（48%-62%）among RBCC main parts.The exergy efficiency of RBCC engine rose with the increase of incoming flow Mach number.When the incoming flow Mach number was less than 2.5,it grew slowly.On the contrary,it went up rapidly when the incoming flow Mach number was more than 2.5.As a kind of energy efficiency indicator,exergy breaks through the limitations of the previous engine performance analysis method based on the first law of thermodynamics.The individual components like inlet,ejector rocket and mixing chamber are tightly coupled by this single parameter.It also helps to evaluate the energy comprehensive utilization characteristics of combined cycle engine and give a direction to the research on engine design and energy optimization.

关 键 词：RBCC(火箭基组合循环) 引射模态 分析法 能量利用 能量优化 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]