液氧/煤油发动机煤油预压涡轮泵技术  

Techniques of kerosene booster turbopump for LOX/kerosene staged combustion cycle engine

作　　者：李向阳[1] 王晓锋[1] 宣统[1] 苗旭升[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2009年第1期16-20,共5页Journal of Rocket Propulsion

摘　　要：液氧/煤油发动机采用独立的预压涡轮泵装置可减小推进剂组元贮箱的增压和提高主泵的转速,从而提高主泵的效率并降低其结构质量。以煤油预压涡轮泵为例,阐述了预压泵结构特点、轴承冷却系统及轴向力平衡装置。为提高预压泵的抗汽蚀性能和扬程,提出了变螺距变轮毂诱导轮方案,分析了流量系数、螺距及轮毂形状,并对诱导轮内流场进行了数值模拟,获得了其内部流场结构。水力试验结果表明,煤油预压泵性能稳定,在预压泵额定流量下,可使煤油主泵的入口压力提高约0.4MPa,与设计值相符。High efficiency and mass performance of the fuel main pump for LOX/kerosene engine can be obtained by the use of the individual booster turbopump （BTP） assembly, which also be good to reduce the propellant pressurization requirement and increase the main pump shaft speed. As a example for kerosene BTP, the technique approach, bearing cooling system and axial balancing system were presented. The booster pump inducer design with variable screw-pitch and hub was suggested to improve the cavitation performance and head rise characteristics. The influence of flow coefficient, pitch and hub shape was analyzed with the inner flow field of the inducer by the numerical simulation. The hydraulic test results indicated that the kerosene BTP has stable performance maps with pressure head 0.4MPa increment for the main pump inlet pressure and also agree well with the design.

关 键 词：液氧/煤油发动机 煤油预压涡轮泵 诱导轮 数值模拟 

分 类 号：V434.2[航空宇航科学与技术—航空宇航推进理论与工程]