火箭推进2025，Vol.51Issue(5)：22-35,14.DOI:10.3969/j.issn.1672-9374.2025.05.003
某补燃循环发动机向心和轴流涡轮方案对比研究
Comparative study on radial and axial turbine design for a certain staged combustion engine
摘要
Abstract
Staged combustion turbopump-feed liquid rocket engine has been recent trends for upper stage and space propulsion systems.Due to the lower turbine specific speed in these applications,using radial flow turbine is obviously beneficial to the turbine performance.However,related research or applications are seldom reported domestically.Aiming at using the radical flow turbine in a staged combustion liquid rocket engine,this paper presents investigations on the conceptual design of the turbine.The influence of design selection was analyzed on the aspects of turbine efficiency,flow area variation,axial force balance,impeller strength and modal frequency.Research has shown that the efficiency of radial turbine is more than 10%higher than that of axial turbine,but the efficiency and flow area have a large slope with the speed ratio.The axial force of the radial turbine changes in the opposite trend with speed ratio to that of the axial flow turbine.It is necessary to adjust the axial force direction of the oxygen pump and turbine,and adopt a different axial force balance strategy from the axial flow turbine.The structural stress of semi-open impeller is obviously lower than that of closed impeller,and it is easy to process,so it should be preferred when the aerodynamic performance meets the requirements.The natural frequency of radial vibration of radial discs is significantly higher than that of axial discs,with sufficient margin for vibration safety.关键词
向心涡轮/方案对比/涡轮效率/轴向力/结构应力Key words
radial turbine/scheme comparison/turbine efficiency/axial force/structural stress引用本文复制引用
叶树波,安近怀远,徐楠,许开富..某补燃循环发动机向心和轴流涡轮方案对比研究[J].火箭推进,2025,51(5):22-35,14.基金项目
国家重点项目 （）
