作　　者： (严俊峰）; (张蒙正）; (路媛媛）;

机构地区： 西安航天动力研究所,陕西西安710100

出　　处： 《火箭推进》 2017年第4期29-33,共5页

摘　　要： 针对分层燃烧循环RBCC发动机,建立了热力学理论模型,引入压缩效率、加热比和增压比,对RBCC发动机的热力循环过程进行分析,推导了发动机热效率计算公式,探讨了热效率随不同参数的变化及其与各参数之间的关系。分析表明,压缩效率、加热比及喷管压比越高,热效率越大;存在最优增压比,可使热效率达到最高值。 A theoretical thermodynamic cycle model was set up for RBCC engine with stratified combustion（SC） cycle. The thermodynamic cycle process of RBCC engine is analyzed by importing the parameters of compression efficiency, pressure ratio and heating ratio. A computational formula of the engine＇s thermal efficiency was derived. The variation of thermal efficiency with different parameters and relationship between the parameters are deduced. The analysis results show that the higher the compression efficiency, heating ratio and nozzle pressure ratio are, the higher the thermal efficiency becomes; the pressure ratio can make the thermal efficiency reach the maximum value.

关 键 词： 分层燃烧 发动机 热力循环 热力学分析