IMECH-IR  > 高温气体动力学国家重点实验室
Development of zone flamelet modelfor scramjet combustor modeling
Yao W(姚卫)1,2; Fan XJ(范学军)1,2
2017
会议名称21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
会议日期March 6, 2017 - March 9, 2017
会议地点Xiamen, China
会议录名称21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
摘要To alleviate the huge computational cost in supersonic combustor modeling and to improve the accuracy of traditional unsteady flamelet model, a zone flamelet is proposed. The main idea of zone flamelet is to divide the whole turbulent combustion field into a finite number of control zones and the chemical status in each zone is represented by a single flamelet. With proper zone division, the local flow conditions can be assumed to be homogeneous, where the scattering of variables over the mixture fraction space is in controllable small, thus the representative flamelet approaches the real scalar distribution. The flamelets exchange information through flux-conserved convection when across the zone boundary, thus the flamelet variables can be transport from upstream to downstream in a flow manner. Although one additional mixture fraction is resolved, great computational cost is still saved because the zone division in physical space is much coarser than the flow simulation mesh. A simple historical statistics approach is proposed to estimate the representative temperature, in order to further alleviate the computational cost in solving the flamelet temperature equation usually with numerous sub-models for non-adiabatic terms, e.g. radiation and wall heat loss. The zone flamelet model is then applied to model a scramjet combustor operated at a flight Mach number of 6.5 and a fuel equivalence ratio of 0.8. The performance of zone flamelet model in highly non-equilibrium supersonic combustion is compared with the traditional PaSR model. © 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
关键词Combustion Cost benefit analysis Costs Mixtures Ramjet engines Supersonic aircraft Computational costs Equivalence ratios Local flow conditions Scramjet combustors Statistics approaches Supersonic combustion Supersonic combustors Turbulent combustion
ISBN号9781624104633
收录类别EI
语种英语
文献类型会议论文
条目标识符http://dspace.imech.ac.cn/handle/311007/78014
专题高温气体动力学国家重点实验室
作者单位1.Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, CAS, No.15 Beisihuanxi Road, Beijing; 100190, China;
2.School of Engineering Science, University of Chinese Academy of Science, Beijing; 100049, China
推荐引用方式
GB/T 7714
Yao W,Fan XJ. Development of zone flamelet modelfor scramjet combustor modeling[C],2017.
条目包含的文件 下载所有文件
文件名称/大小 文献类型 版本类型 开放类型 使用许可
EiCpA041.pdf(832KB)会议论文 开放获取CC BY-NC-SA浏览 下载
个性服务
推荐该条目
保存到收藏夹
查看访问统计
导出为Endnote文件
谷歌学术
谷歌学术中相似的文章
[姚卫]的文章
[范学军]的文章
百度学术
百度学术中相似的文章
[姚卫]的文章
[范学军]的文章
必应学术
必应学术中相似的文章
[姚卫]的文章
[范学军]的文章
相关权益政策
暂无数据
收藏/分享
文件名: EiCpA041.pdf
格式: Adobe PDF
所有评论 (0)
暂无评论
 

除非特别说明,本系统中所有内容都受版权保护,并保留所有权利。