内燃波转子非定常流动和燃烧特性分析  

Analysis of Unsteady Flow and Combustion Characteristics of Combustion Wave Rotor

作　　者：巩二磊[1] 李建中[1] 韩启祥[1] 王家骅[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《南京航空航天大学学报》2013年第3期309-315,共7页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：中央高校基本科研业务费专项基金(NS2012017))资助项目;航空基金(2012ZB52029)资助项目

摘　　要：为研究内燃波转子内非定常流动和燃烧特性,在分析内燃波转子的结构和工作特点的基础上,建立了内燃波转子简化二维模型。采用数值模拟的方法,研究内燃波转子内非定常流动过程中预压缩作用对混气总压和温度的影响,冷态流动过程中混气的分布以及混气与新鲜空气接触面形状的变化。采用热射流点燃内燃波转子内形成的可燃混气,研究转子通道内燃烧特性。研究结果表明:通过内燃波转子预压缩,通道内气体的总压提高了32%,总温提高了10.4%;混气与空气接触面的扭曲变形程度受到内燃波转子作用时序和通道内的轴向速度分布影响;热射流成功点燃通道内可燃混气,实现了转子通道内可燃混气的爆震燃烧,爆震波峰值压力约2MPa,爆震波传播速度在2 600～2 800m/s范围内。In order to study the unsteady flow and combustion characteristics of combustion wave rotor, the simplified two-dimensional model is established based on the analysis of combustion wave rotor structure and working principle. The impact of pre-compression on the flow total pressure and tempera- ture is numerically simulated during the unsteady flow process occur in combustion wave rotor channel, and the gas distribution as well as the fuel-air interface shape distortion are studied. Finally, the com- bustion characteristics are researched. By the conducted pre-compression,the flow total pressure is in- creased by 32% and the total temperature by 10. 4%. The distortion of fuel-air interface is controlled by both timed sequence and channel axial velocity. Combustion in wave rotor channel is ignited by hot-jet igniter. Detonation combustion is accomplished. The peak pressure of the detonation wave approaches 2 MPa. Detonation wave propagation velocity is 2 600--2 800 m/s.

关 键 词：内燃波转子 非定常流动 等容燃烧 爆震 数值模拟 

分 类 号：V235.22[航空宇航科学与技术—航空宇航推进理论与工程]