Orthogonal Experimental Investigation of a Gaseous Hydrogen / Gaseous Oxygen Coaxial Injector
- Paper number
IAC-07-C4.3.05
- Author
Prof. Guobiao Cai, Beijing University of Aeronautics and Astronautics, China
- Coauthor
wu zhiqi, Beijing University of Aeronautics and Astronautics, China
- Coauthor
zhenggang Du, Beijing University of Aeronautics and Astronautics, Unknown
- Coauthor
Mr. Zhenggang Du, Beijing University of Aeronautics and Astronautics, China
- Coauthor
Ms. Jin Ping, Beijing University of Aeronautics and Astronautics, China
- Coauthor
Prof. Guozhou Zhang, China
- Coauthor
Mr. Xiaowei Wang, China
- Year
2007
- Abstract
The Full-Flow Stage Combustion (FFSC) cycle engine may be applied in the next generation reusable launch vehicle. One of the key technologies required is the development of an injector that uses gaseous oxygen and gaseous hydrogen as propellants. To get the effect of injector’s design parameters on combustion performance, design of experiments according to orthogonal array was adopted to gaseous hydrogen / gaseous oxygen coaxial injector hot-firing tests. The mass flowrate, the ratio of oxidizer element pressure drop to chamber pressure, the velocity ratio of fuel to oxidizer, and the recess length of oxidizer element were selected as the test factors, and each factor varied at three different levels. As the chamber pressure was 3 MPa and mixture ratio was 6, mass flowrate varied from 0.113 to 0.339 kg/s, the ratios of oxidizer element pressure drop to chamber pressure from 6.5
- Abstract document
- Manuscript document
IAC-07-C4.3.05.pdf (🔒 authorized access only).
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