System Design and Analysis of Hydrocarbon Scramjet with Regeneration Cooling and Expansion Cycle
- Paper number
IAC-13,C4,9,9,x16473
- Author
Dr. Wu Xianyu, College of Aerospace and Materials Engineering, National University of Defense Technology, China
- Coauthor
Mr. Chen Xuefu, China
- Coauthor
Dr. Ding Meng, College of Aerospace and Materials Engineering, National University of Defense Technology, China
- Coauthor
Prof. Shen Chibing, National University of Defense Technology, China
- Year
2013
- Abstract
A new cycle scheme of scramjet system was brought forward in this paper. For this cycle scheme, the supercritical/cracking hydrocarbon fuel with high pressure and temperature produced after regeneration cooling is used to drive turbo-pump to supply hydrocarbon fuel, and the hot hydrocarbon from the turbo exit is injected to scramjet for organizing combustion. The ethylene assistant subsystem is adopted for scramjet ignition and cold start-up. This scheme will be propitious to high performance combustion,efficiency fuel supply and long-time thermal protection with the advantage of simple configuration, light weight and high efficiency. At the same time, the scramjet system coupling of thermodynamics and dynamics is complex because of the strong coupling of combustion, flow and heat transfer. It is a challenge for scramjet system design, dynamics characteristic analysis and working mode control. The working modes of this scramjet are expatiated, and the system design and analysis of scramjet start-up is performed. This work has a benefit to study the dynamics and thermodynamics coupling problem farther.
- Abstract document
- Manuscript document
(absent)