随着吸气式高超声速飞行器飞行速域与空域的不断拓展，固体粉末超燃冲压发动机所面临的核心技术挑战已从单纯追求提高掺混燃烧效率转向更深层次的波系调控与流动控制。本文基于欧拉-拉格朗日框架构建了可压缩气固两相湍流流动数值模型与方法，研究了宽速域进气道粉末燃料预喷注流动调控机理，分析了不同来流马赫数（Ma∞=4~7）和粉末燃料输运固气比（SR=2~14）对进气道流动特性、性能表现及粉末燃料掺混过程的影响机制。通过系统分析预喷注作用下进气道波系结构与边界层的相互作用机制，发现预喷注可重构内外压缩段波系结构，在提升进气道增压性能的同时，亦导致总压恢复性能下降；通过建立输运固气比与粉末燃料掺混效率的内在关联，揭示气固两相剪切层高涡量区、尾迹高涡量区及肩部颗粒相滞止区的形成机理，并阐明上述区域内颗粒弥散特性与涡结构演化规律。

With the continuous expansion of the flight speed and altitude envelopes of air-breathing hypersonic vehicles, the core technical challenges faced by solid powder scramjets have shifted from simply pursuing improved blending combustion efficiency to deeper wave system regulation and flow control. Based on the Euler-Lagrange framework, this paper establishes a numerical model and method for compressible gas-solid two-phase turbulent flow, investigates the flow control mechanism of powder fuel pre-injection in a wide-speed-range inlet, and analyzes the influence mechanisms of different incoming flow Mach numbers (Ma∞ = 4~7) and powder fuel transport solid-gas ratios (SR = 2~14) on the flow characteristics, performance, and powder fuel mixing process of the inlet. Through a systematic analysis of the interaction mechanism between the inlet wave system structure and the boundary layer under pre-injection, it is found that pre-injection can reconstruct the wave system structures of the internal and external compression sections, which improves the inlet pressurization performance while also reducing the total pressure recovery performance. By establishing the intrinsic correlation between the transport solid-gas ratio and the mixing efficiency of powder fuel, the formation mechanisms of the high vorticity region in the gas-solid two-phase shear layer, the high vorticity region in the wake, and the particle phase stagnation region at the shoulder are revealed, and the particle dispersion characteristics and the evolution laws of the vortex structure in the above regions are clarified.