Full-scale Detached Eddy Simulation of kerosene fueled scramjet combustor based on skeletal mechanism
文献类型：会议论文
| 作者 | Yao W(姚卫) ; Wang J(王晶); Lu Y(陆阳); Li XP(李晓鹏); Fan XJ(范学军)
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| 出版日期 | 2015 |
| 会议名称 | 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference |
| 会议日期 | July 6, 2015 - July 9, 2015 |
| 会议地点 | Glasgow, United kingdom |
| 关键词 | Adiabatic flame temperature Combustion Directed graphs Flow separation Heat flux Kerosene Large eddy simulation Musculoskeletal system Real time systems Sensitivity analysis Spacecraft Transients |
| 中文摘要 | Large Eddy Simulation (LES) of kerosene fueled scramjet combustor is generally scare in the literature, due mainly to the formidable computational cost arisen by complex kerosene mechanism. In this study, the skeletal reduction of a detailed reaction mechanism (2185 species/8217 steps) of aviation kerosene is conducted using directed relation graph with error propagation and sensitivity analysis (DRGEPSA) method, resulting a skeletal mechanism consisting of 39 species/153 elemental reactions for China Daqing RP-3 aviation kerosene. The comparisons of adiabatic flame temperature, total heat release, ignition delay and laminar flame speed predicted by the skeletal mechanism show an overall good accordance with the original detailed reaction mechanism. Then a three-dimensional Detached Eddy Simulation (DES) modeling based on the skeletal kerosene mechanism is employed for the numerical analysis of a full-scale scramjet combustor, which has been experimentally tested in a long-time direct connect supersonic combustion test platform (abbreviated as DTZ) assembled in Chinese Academy of Sciences (CAS). Pressure and heat flux measurement systems are attached to the combustor assembly to monitor the real-time combustion performance and provide validation data for the numerical modeling. Three cases with fuel equivalence ratios from 0.8, 1.0 to 1.2 and the same crossflow conditions at Mach 2.0 are modeled. The time-averaged static pressure and heat flux are in generally good agreement with the experiment with the peak heat flux slightly underpredicted. The instantaneous and/or time-averaged pressure, momentum, temperature and turbulence fields, which are difficult to be measured, are analyzed to reveal the main flow and combustion physics, especially those related to the flame distribution and holding. The combustion is identified as in ramjet mode for the investigated cases. With the increasing of fuel equivalence ratio, the shock train propagates upstream in the isolator and the interaction between the upstream and downstream combustion assumes different patterns. © 2015, AIAA American Institute of Aeronautics and Astronautics. All rights reserved.(132 refs) |
| 收录类别 | EI |
| 语种 | 英语 |
| 源URL | [http://dspace.imech.ac.cn/handle/311007/59061]  |
| 专题 | 力学研究所_高温气体动力学国家重点实验室 |
| 推荐引用方式 GB/T 7714 | Yao W,Wang J,Lu Y,et al. Full-scale Detached Eddy Simulation of kerosene fueled scramjet combustor based on skeletal mechanism[C]. 见:20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Glasgow, United kingdom. July 6, 2015 - July 9, 2015. |
入库方式： OAI收割
来源：力学研究所
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