Numerical Simulation of Hydrogen-Air Combustion Reaction Flows in Propulsion Systems
- Paper number
IAC-09.C4.8.1
- Author
Dr. Pan Sha, National University of Defense Technology, China
- Coauthor
Prof. Hua Li, National University of Defense Technology, China
- Coauthor
Mr. Dinghua Feng, National University of Defense Technology, China
- Coauthor
Mr. Kangping Zhang, National University of Defense Technology, China
- Coauthor
Dr. Zhengyu Tian, College of Aerospace and Materials Engineering, National University of Defense Technology, China
- Year
2009
- Abstract
Research on combustion reaction flow is vital for the propulsion system. But Investigation for combustion is difficult in that it involved species, reaction, chemical kinetics and other complicated factors. Numerical simulation with CFD(Computational Fluid Dynamic) technology is cheaper and timesaver method compared with experiment. In this study, calculation of chemically reacting combustion flows has been presented. Jameson scheme and LU-SGS implicit method were used to resolve chemical non-equilibrium NS equation. Seven species, eight equations Finite-rate chemistry model were used to calculate reaction between hydrogen and oxygen. Chemical source in equations was conducted implicitly to remove stiffness and accelerate convergence. The study considers two cases. The first is subsonic reacting shear layer, which often occurred in the combustor of liquid-propellant rocket. The second is combustion of premixed H2-air supersonic flow in a ramped duct, which occurred in the scramjet combustor. Numerical results were presented, and flow field was discussed all of which showed that calculation had credibility. The numerical method could be used to the further engineering application.
- Abstract document
- Manuscript document
IAC-09.C4.8.1.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.