基于自适应网格加密的超声速可燃气热射流起爆详细反应数值模拟

采用块结构自适应网格加密开源程序AMROC,在高性能计算集群中,进行氢气、氧气、氮气详细反应机理的二维超声速热射流爆震起爆自适应网格精细数值模拟,研究在热射流的持续喷射作用下超声速可燃气热射流爆震起爆,以及形成的精细的爆震胞格结构.结果表明:超声速可燃气流中热射流类似气动斜劈,形成局部激波诱导燃烧.超声速可燃气中持续的热射流喷射会形成过驱爆震,并导致不规则爆震胞格的生成.热射流的扰动压缩作用对过驱爆震的形成以及不规则爆震胞格的产起着关键的作用.热射流的扰动压缩波以当地声速通过爆震波后的亚声速区域作用于爆震波,使爆震波处于持续过驱状态,并形成不规则的爆震胞格结构.

Adaptive mesh refinement-based numerical simulation of initiation in supersonic combustible mixtures using hot jet with detailed reaction model

Open-code program AMROC of block-structured adaptive mesh refinement was adopted to conduct high-resolution numerical simulation of two-dimensional detonation initiation in supersonic combustible mixtures using hot jet. Detailed chemistry mechanism of hydrogen, oxygen, argon was considered in the simulation. Detonation initiation in supersonic combustible mixtures and the formed elaborate detonation cell were investigated. Results show that the hot jet is similar with a pneumatic ramp in supersonic combustible mixtures, so as to realize shock-induced combustion. The continuous ejection of hot jet in supersonic combustible mixtures could result in forming of overdriven detonation and irregular detonation cell. The disturbance and compression function of hot jet plays an important role in the forming of overdriven detonation and its irregular detonation cell. Disturbance and compression function of hot jet propagates at local sonic velocity, yielding an impact on the forward detonation front after getting across the subsonic zone behind the detonation front. In this way overdriven detonation could be maintained to form the irregular detonation cell.