复合预冷吸气式火箭发动机热力循环分析  

Analysis on thermodynamic cycle characteristics of synergistic air-breathing rocket engine

作　　者：郭海波[1] 肖洪[2] 南向谊[1] 逯婉若[1] 

机构地区：[1]西安航天动力研究所,西安710100 [2]西北工业大学动力与能源学院,西安710072

出　　处：《火箭推进》2013年第3期15-20,共6页Journal of Rocket Propulsion

基　　金：国家863项目(2008AA705405)

摘　　要：采用热力学第一定律分析法分析了复合预冷吸气式火箭发动机(SABRE)的基本热力过程,得出了吸气模式和火箭模式下的理想循环功和热效率表达式,确定了影响发动机理想热力循环性能的特征参数。结果表明:吸气模式下SABRE核心机采用布雷顿循环,压气机的增压比和循环增温比是影响理想热力循环性能的关键参数;火箭模式下SABRE采用火箭发动机循环,喷管降压比和出口排气速度是影响理想热力循环性能的关键参数。氦气仅仅在发动机内通过换热器换热实现能量在各循环子系统之间的输运,而其本身并无变化,不对发动机的理想循环功和热效率产生影响。The basic thermodynamic process of synergistic air-breathing rocket engine（SABRE） is analyzed with the first law of thermodynamics method.The ideal cycle work and thermal efficiency expressions in both air-breathing mode and rocket mode were obtained.Furthermore,several characteristic parameters which affect the performance of the ideal thermodynamic cycles were determined.Results reveal that the pressune ratio of the compressor and cycle temperature ratio are the key parameters affecting the ideal thermodynamic cycle performance when SABRE core engine in air-breathing mode works in Brayton cycle,and the decompression ratio in the nozzle and exhaust velocity at nozzle outlet are the important parameters affecting the ideal thermodynamic cycle performance when the rocket engine cycle is adopted for SABRE.The helium energy transmission between all the cycle sub-systems is realized only by heat exchangers in the engine,but has no effects on ideal cycle work and thermal efficiency of SABRE.

关 键 词：复合预冷吸气式火箭发动机 热力循环 理想循环功 热效率 

分 类 号：V434.1[航空宇航科学与技术—航空宇航推进理论与工程]