摘要
旋转爆震发动机环形燃烧室的设计是影响发动机性能的关键因素,研究爆震波通过环形通道的传播过程能够为燃烧室设计提供有力指导。为了对这一传播过程及其传播模式进行系统研究,采用流场阴影观测方法,对爆震波通过环形通道的传播现象进行试验观测,并结合通道内外壁面的影响对其传播模式进行详细划分,依次分析各传播模式的形成机制及速度特性。研究结果表明,爆震波的传播模式可按照波面是否发生解耦划分为不稳定传播模式和稳定传播模式,根据马赫干的变化情况又可细分为马赫干增长型、平稳型和衰减型;爆震波在不稳定传播模式下会出现明显的速度亏损,而在稳定传播模式下速度较为平稳;外壁面附近波面呈现一定的过驱度,且过驱度随马赫干的衰减而增大;随着初始压力的增大,爆震波实现稳定传播的能力增强,且使马赫干呈现增长—平稳—衰减的转换趋势,而壁面曲率半径与通道宽度比的增大会使马赫干呈现衰减—平稳—增长的变化规律。
The design of the annular combustion chamber is a key factor affecting the performance of a rotating detonation engine.Studying the propagation process of the detonation wave through the annular channel can provide a powerful guide for the design of the combustion chamber.In order to systematically study this propagation process and its propagation mode,the flow field shadow observation method is used to experimentally observe the propagation of detonation wave through the annular channel,and the propagation mode is divided in detail based on the influence of the inner and outer walls of the channel.The formation mechanism and velocity characteristics of each propagation mode are analyzed.The research results indicate that the propagation mode of detonation wave can be divided into unstable and stable propagation modes according to whether the wave front is decoupled.While considering the change of the Mach-stem,the propagation mode can be subdivided into Mach-stem growing type,steady type and decaying type.In the unstable propagation mode,the wave velocity experiences obvious attenuation while the velocity is relatively steady in the stable propagation mode,the detonation wave front near the outer wall is overdriven,and the overdriven degree increases with the attenuation of the Mach-stem.With the increase of the initial pressure,the ability of the detonation wave in realizing stable propagation is enhanced,and the Mach-stem shows a growing-steady-decaying transition trend,while the increase of the ratio of the wall curvature radius to the channel width makes the Mach-stem present a decaying-steady-growing transition law.
作者
袁雪强
蒋露欣
张多
刘世杰
YUAN Xueqiang;JIANG Luxin;ZHANG Duo;LIU Shijie(Science and Technology on Scramjet Laboratory,National University of Defense Technology,Changsha 410073,China)
出处
《火箭推进》
CAS
2021年第6期101-110,共10页
Journal of Rocket Propulsion
基金
国家级重点实验室基金项目(6142704200101)。
关键词
旋转爆震发动机
环形通道
传播模式
试验研究
波系结构
速度分布
rotating detonation engine
annular channel
propagation mode
experimental study
wave structure
velocity distribution
