摘要
为满足膨胀循环液体火箭发动机高性能和高可靠的研制要求,在氢涡轮泵方案的选择上采用了径流式氢涡轮方案。通过一维热力和三维结构设计,初步验证了径流式氢涡轮应用可行性。借助于CFD分析软件,完成了该涡轮设计工况全三维粘性数值模拟,证明性能满足指标要求。通过强度优化设计和轴向力平衡两方面研究,突破了涡轮泵应用的两大技术难点。结合该涡轮介质试验及发动机热试车考核情况,得出径流式涡轮能够应用于膨胀循环发动机氢涡轮泵的结论。
In order to meet the high-performance and high reliability requirements in development of the expander cycle liquid rocket engine, the radial turbine was adopted in the scheme selection of hydrogen turbopumps. The feasibility was preliminarily verified through 1D thermal design and 3D structure design. With CFD analysis sottware, the full 3D viscosity numerical simulation was com- pleted under turbo＇ s design working conditions, proving that the performance could meet the qualifi- cation requirement. Two main technical problems in turbopump applications were solved through strength optimum design and axial force balance research. In combination with the results obtained in medium test and hot test, a conclusion that the radial turbine can be applied to the hydrogen turbopump of expander cycle engine was achieved.
出处
《火箭推进》
CAS
2012年第3期40-45,共6页
Journal of Rocket Propulsion
基金
国家"863"项目(2009AA7020512)
关键词
膨胀循环
径流式涡轮
数值仿真
强度优化
轴向力平衡
热试车
expander cycle
radial turbine
numerical simulation
strength optimization
axialforce balance
hot test
