SABRE4氦循环分流比对设计点氢流量影响分析  

Influence of helium cycle flow ratio on SABRE4 design point hydrogen flow rate

作　　者：郑尚喆 陈玉春[1] 王治华 杜金峰 高远 黄新春 ZHENG Shangzhe;CHEN Yuchun;WANG Zhihua;DU Jinfeng;GAO Yuan;HUANG Xinchun(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China;Faculty of Engineering,University of Nottingham,Nottingham NG72RD,UK;Aero Engine Control System Institute,Aero Engine Corporation of China,Wuxi Jiangsu 214000,China)

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]诺丁汉大学机械工程学院,诺丁汉NG72RD [3]中国航发控制系统研究所,江苏无锡214000

出　　处：《航空动力学报》2024年第11期453-464,共12页Journal of Aerospace Power

摘　　要：针对协同吸气式火箭发动机(synergistic air-breathing rocket engine,SABRE),建立了基于部件法的发动机设计点热力学计算模型,分析了SABRE循环所需的最少氢质量流量(简称流量)。以节省氢流量为目的,分别在SABRE3发动机构型基础上增加了两个氦循环支路,提出了两个SABRE4简化方案,结合两种简化方案,提出了SABRE4整体方案,分析了各氦循环支路分流比对发动机设计点重要参数以及设计点氢流量的影响。结果表明:最小氢流量与通过换热器3的氦流量成正比,要减小所需氢流量,需要减少通过换热器3的氦流量;较低的氦循环支路分流比一有利于氢流量的降低,但同时增大了氦压气机设计压比,较低的氦循环支路分流比二有利于氢流量的降低,且有利于降低氦压气机设计压比,分流比一、分流比二的降低都会导致换热器接近换热限制边界;在换热器1前氦气总温不超过310 K,且氦压气机压比不大于11.0的情况下,SABRE4方案最小氢流量为SABRE3氢流量的83.3%。The thermodynamic calculation model based on component method for synergistic air-breathing rocket engine(SABRE)design point was established.The minimum hydrogen flow rate required by the engine was analyzed.To save the hydrogen flow rate,two simplified schemes of SABRE4 were proposed by adding two helium branches based on the SABRE3 configuration.Combining two simplified schemes,SABRE4 scheme was proposed.The influences of the helium branches flow ratios on engine design point parameters and hydrogen flow rate were analyzed.The results showed that:the minimum hydrogen flow rate was proportional to the helium flow rate through Heat Exchanger 3.The less helium flow rate through Heat Exchanger 3 indicated the less hydrogen flow rate required.A smaller branch one flow ratio one was conductive to reducing the hydrogen flow rate,meanwhile the required helium compressor pressure ratio was increased.A smaller branch two flow ratio two was conductive to reducing the hydrogen flow rate and the required helium compressor pressure ratio.The decrease of flow ratio one and flow ratio two caused heat exchangers to approach their limits.When the Heat Exchanger 1 inlet helium temperature was lower than 310 K and the pressure ratio of helium compressor was lower than 11.0,the minimum hydrogen flow rate of SABRE4 was 83.3%of SABRE3.

关 键 词：SABRE 氢流量 比冲 分流比 设计点 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]