Combustion Modelling of JP10 in a Scramjet Engine
This paper introduces a new concept of thermal cracking of aviation fuels using a porous media reactor (PMR). In this process thermal partial oxidation (TPOX) is achieved inside a porous bed where the heavy JP10 is broken down into a lighter molecules. A numerical modelling of the combustion of the decomposed JP10 injected in a scramjet engine is carried out. The results highlight the importance of selecting an appropriate chemistry, combustion and turbulence-chemistry interaction models. The superiority of using multistep chemistry and the eddy-dissipation concept, over fast-chemistry models, in predicting flow and flame characteristics is demonstrated. Overall, the TPOX-PMR approach offers a potential solution for achieving a stable burning of JP10 fuel in scramjet engines. However further design optimisation of the fuel injector is required.
supersonic combustion CFD hypersonic vehicles.
Farid C. Christo
Institute for Sustainable Systems and Technologies University of South AustraliaMawson Lakes, Adelaide, 5095 Australia
国际会议
2011年亚太航空航天技术学术会议(APISAT 2011)
澳大利亚
英文
1-10
2011-02-28（万方平台首次上网日期，不代表论文的发表时间）