基于伴随非等温射流理论的缝槽气膜冷却模型  

A prediction model of film-cooling adiabatic effectiveness based on cohence non-isothermal jet theory

作　　者：张弛[1] 林宇震[1] 许全宏[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力重点实验室,北京100083

出　　处：《航空动力学报》2007年第12期2006-2011,共6页Journal of Aerospace Power

摘　　要：在伴随非等温射流基础上发展了一种适用于缝槽气膜冷却绝热温比预估的数学模型.通过合理假设推导出二维壁面射流混合层核心温度分布规律,将其作为气膜绝热壁温,并考虑缝槽几何特征参数和气膜吹风比对冷却效率的影响,得到绝热温比计算公式.用试验数据对该预估模型进行拟合分析,得到了与试验数据拟合精度在±8%以内的半经验预估模型,证明该模型的可行性和应用潜力,并需要更多的试验数据对其进行验证和改进.To predict the slot film-cooing adiabatic effectiveness, a mathematic model was developed based on cohence non-isothermal jet theory. The core temperature distribution of mixing layer in 2D wall jet was deduced through reasonable assumptions,and the temperature was regarded as the adiabatic wall temperature. In addition,this influence of slot geometry parameter and film blowing ratio on the cooling effectiveness was also considered,so the adiabatic effectiveness equation was obtained. The empirical coefficients in this prediction model should be fitted to the experimental data, showing that the present prediction model has an accuracy of within ±8% to all previous experimental data. The feasibility and potential application of this model have been demonstrated, and more experimental data are required for future verification and improvement.

关 键 词：航空 航天推进系统 航空发动机 燃烧室 缝槽气膜冷却 绝热温比 伴随非等温射流模型 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]