Research on the Radial Turbine Used in the LOX/Hydrogen Rocket Engine
- Paper number
IAC-11,C4,3,9,x9833
- Author
Mr. ZhongXiang Liu, Beijing Aerospace Propulsion Institute, China
- Coauthor
Mr. Nan Zhang, Beijing Aerospace Propulsion Institute, China
- Coauthor
Mr. XiaoMing Ye, Beijing Aerospace Propulsion Institute, China
- Coauthor
Mr. Fan Yang, Beijing Aerospace Propulsion Institute, China
- Year
2011
- Abstract
Turbopump is the key part of a LOX/LH2 rocket engine. By using a turbine to drive the pump, turbopump supplies hydrogen and oxygen to an engine at the required pressure. Nowadays, the LOX/LH2 rocket engines in service all around the world adopt axial turbine with no exception. Whatsoever, the turbine using in LOX/LH2 rocket engine has a small flux. Thus, based on theoretical analysis, adopting radial turbine can be a good idea. Recently, a radial turbine has been adopted in the development of a LOX/LH2 rocket engine. At present, several hot tests of the engine has been done. The results indicate the engine works reliably with satistied acceleration time during start transient and turbine efficiency. In this paper, some key problems on applying radial turbine to LOX/LH2 rocket engine, such as axial force, disk strength, turbine efficiency, and etc, are summarized and then solved by means of theoretial analysis, numerical simulation, and experiments. Moreover, the difference between radial and axial turbine applying to LOX/LH2 rocket engine is compared and summarized.
- Abstract document
- Manuscript document
(absent)