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<p>Supersonic combustion in scramjet engines is limited by short residence time, inefficient mixing, and competing pressure losses. This study numerically investigates the combined influence of strut wedge angle (10°, 12°, and 14°) and a forward-slide cavity (FS12) on flow dynamics, mixing, and combustion behavior in a Mach 2.5 hydrogen-fueled combustor using RANS with finite-rate chemistry. Results show that increasing wedge angle enhances shock strength and turbulence, improving mixing but increasing pressure loss. The FS12 configuration significantly modifies the flow field by generating a stable recirculation zone, leading to earlier ignition and sustained flame stabilization. Compared to the baseline case, the cavity-assisted configuration improves combustion efficiency by 15–20% and achieves near-complete mixing at shorter axial distances. However, pressure loss increases up to ~ 0.33 for higher wedge angles. Among all cases, the 12° strut with FS12 configuration provides the optimal balance between mixing enhancement and pressure penalty. The study demonstrates that controlled shock–recirculation coupling is an effective strategy for improving scramjet combustor performance.</p>

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RuShock–recirculation synergy in scramjet combustors with the effects of strut wedge angle and cavity-assisted flame stabilization

  • 期刊论文

  • 发表日期：

    2026年7月1日

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  • K. Hema Latha,
  • S. M. D. Shehabaz,
  • S. K. Gugulothu,
  • Raju Muthyala,
  • Praveen Barmavatu,
  • G. Sailaja

摘要

Supersonic combustion in scramjet engines is limited by short residence time, inefficient mixing, and competing pressure losses. This study numerically investigates the combined influence of strut wedge angle (10°, 12°, and 14°) and a forward-slide cavity (FS12) on flow dynamics, mixing, and combustion behavior in a Mach 2.5 hydrogen-fueled combustor using RANS with finite-rate chemistry. Results show that increasing wedge angle enhances shock strength and turbulence, improving mixing but increasing pressure loss. The FS12 configuration significantly modifies the flow field by generating a stable recirculation zone, leading to earlier ignition and sustained flame stabilization. Compared to the baseline case, the cavity-assisted configuration improves combustion efficiency by 15–20% and achieves near-complete mixing at shorter axial distances. However, pressure loss increases up to ~ 0.33 for higher wedge angles. Among all cases, the 12° strut with FS12 configuration provides the optimal balance between mixing enhancement and pressure penalty. The study demonstrates that controlled shock–recirculation coupling is an effective strategy for improving scramjet combustor performance.