超声速湍流燃烧G/Z方程模型验证  

Validation of G/Zequation model in supersonic turbulent combustion

作　　者：孙明波[1] 吴锦水 赵国焱[1] 

机构地区：[1]国防科技大学高超声速冲压发动机技术重点实验室,湖南长沙410073

出　　处：《热科学与技术》2015年第1期68-74,共7页Journal of Thermal Science and Technology

基　　金：国家自然科学基金资助项目(91016028);霍英东教育基金资助项目(131055)

摘　　要：为了研究超声速条件下的部分预混燃烧,引入一种基于Level set重构方法和稳态火焰面数据库的G/Z方程模型,并利用德国宇航中心的DLR支板算例对G/Z方程模型进行了验证。结果显示,超声速湍流燃烧G/Z方程模型可以捕捉到部分预混燃烧现象,数值模拟结果与实验结果吻合较好,验证了G/Z方程模型运用到超声速部分预混条件下湍流燃烧流场计算的可行性。同时,超声速湍流燃烧G/Z方程模型依赖于运用到的火焰传播速度模型与火焰面模型,模型精确度的提高有待进一步探究。A model combining level set G equation and steady flamelet Z equation was applied in supersonic partially premixed combustion in this study.The model was validated against the strut-injection supersonic combustion flow field designed by the German Aerospace Center.The predictions which captured the partially premixed combustion are in good agreement with the experimental data.Further discussions show that the combination of Gequation and steady flamelet Z equation could capture the characteristics of partially premixed combustion under supersonic condition.And it is possible to apply this method to the simulation of the partially premixed combustion under supersonic condition.However,the model accuracy depends on both the turbulent burning velocity model and the flamelet model,which requires further investigation.

关 键 词：超声速 部分预混燃烧 G方程 Z方程 

分 类 号：V435.12[航空宇航科学与技术—航空宇航推进理论与工程]