摘要
在全流量补燃循环发动机系统动力平衡模型的基础上,研究了氢发汗冷却流量、燃烧室压力和燃烧室混合比对发动机系统参数的影响规律.研究结果表明:在发动机推力和喷管扩张比保持恒定时,①随着氢发汗冷却流量的增加,燃料泵扬程大幅度增大,氧化剂泵扬程小幅度减小;②当燃烧室压力在20MPa之前,泵的扬程增加与燃烧室压力的增加近似成线性;而在20MPa之后,燃烧室压力的增加很小,导致泵的扬程增加很大,燃烧室压力不宜超过20MPa;③随着燃烧室混合比的增加,燃料泵扬程呈线性增大,氧化剂泵扬程开始以较大幅度减小,之后以小幅度减小;因此燃烧室混合比不宜过小,取7左右较为合适.这些研究结果为全流量补燃循环发动机系统参数设计提供了合理的选择范围.
Based on the full flow staged combustion（FFSC） cycle engine balance m odel,three parameters were selected for the engine system design,such as hydroge n transpiration cooling mass flow rate,combustion chamber pressure and combustio n chamber mixture ratio.These results show that,when the thrust and nozzle expan sion ratio are kept constant：（1） with the increase of hydrogen transpiration coo ling mass flow rate,the fuel pump lift ascends rapidly and the oxidizer pump lif t falls down;（2） with the increase of combusion chamber pressure,the pump lift a scends linearly before combustion chamber pressure at 20 MPa and rapidly after 2 0 MPa,so 20 MPa is recommended for combustion chamber pressure;（3） with the incr ease of combustion chamber mixture ratio,the fuel pump lift ascends linearly,the oxidizer pump lift reduces rapidly and then slowly,so seven is recommended for combustion chamber mixture ratio.The effects of these design parameters on engin e system parameters offer a reasonable range for engine system design.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2011年第2期435-441,共7页
Journal of Aerospace Power
基金
国家高技术研究发展计划项目
