文献类型：期刊文献

中文题名：吸气式高超声速飞行器机体/推进一体化内外流非定常耦合方法

英文题名：Unsteady Coupling Method of Internal and External Flows for Airbreathing Hypersonic Vehicle with Airframe/Propulsion Integration

作者：何良俊 张兵 尤厚丰 王云海

第一作者：何良俊

机构：[1]合肥工业大学机械工程学院,安徽合肥230009;[2]合肥工业大学汽车与交通工程学院,安徽合肥230009;[3]贵州理工学院机械工程学院,贵州贵阳550003

第一机构：合肥工业大学机械工程学院,安徽合肥230009

年份：2020

卷号：5

期号：6

起止页码：52-59

中文期刊名：气体物理

外文期刊名：Physics of Gases

收录：CSTPCD

语种：中文

中文关键词：吸气式高超声速飞行器;超燃冲压发动机;化学非平衡流;有限速率化学反应;内外流耦合

外文关键词：airbreathing hypersonic vehicle;scramjet;chemical nonequilibrium flow;finite-rate chemical reaction;internal and external flow coupling

摘要：基于吸气式高超声速飞行器机体/推进一体化的气动布局设计方式,文章提出了一种内外流一体化流场的耦合求解方法,其中燃烧室内流场采用考虑有限速率化学反应动力学模型的一维非稳态方法求解,进气道和尾喷管外流场采用二维CFD软件计算,进气道与燃烧室在耦合界面处通过一维平均方法实现静温、静压和Mach数等参数传递.并分别以日本国家航空与航天实验室(NAL)的氢燃料燃烧室模型作为内流场验证算例,以某典型高超声速飞行器一体化模型作为内外耦合流场验证算例.研究结果表明:有限速率化学反应准一维方法能较为准确地模拟燃烧室内燃烧流场,提出的内外流场耦合方法能够有效地计算出内外流耦合效应,计算后体压力分布与理论值较接近.该方法可为超燃冲压发动机的性能快速分析和吸气式高超声速飞行器机体/推进一体化的初步分析设计提供重要参考.
Based on the aerodynamic layout design method for the airframe/propulsion integration of airbreathing hypersonic vehicles,a coupling method of the internal and external flow fields was proposed in this paper.The flow field in combustor was solved by one-dimensional unsteady method considering finite-rate chemical reaction model,and the outer flow field of inlet and tail nozzle was calculated by two-dimensional CFD software.At the coupling interface between inlet and combustor,the parameters such as static temperature,static pressure and Mach number were transferred by one-dimensional average method.The hydrogen fuel combustor model developed by the National Aeronautics and Astronautics Laboratory(NAL)of Japan was used as an example to verify the internal flow field,and the integrated model of a typical hypersonic vehicle was used as an example to verify the coupling of the internal and external flow fields.The results show that the quasi-one-dimensional method based on finite-rate chemical reaction can simulate the combustion flow field more accurately.The coupling effect of internal and external flow fields can be calculated effectively by the proposed method,and the calculated pressure distribution of the rear body is close to the theoretical value.This method can provide an important reference for the performance analysis of the scramjet and the design of the airbreathing hypersonic vehicle with airframe/propulsion inttegration.