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<p>Shock wave generator is an effective device for mixing enhancement in scramjet combustors. This paper employs the Reynolds-averaged Navier-Stokes (RANS) numerical simulation method to investigate the effects of different parameters of a wall-mounted ramp, which serves as a shock wave generator, on cold flow, reacting flow fields and the vorticity transport within the turbulent mixing region in a strut-based scramjet combustor. The parameters examined include the ramp angle (15°, 20°, 25°, 30°) and its position (110, 130, 150&#xa0;mm). The results demonstrate that the introduction of the shock wave generator alters the shock wave distribution within the strut-based combustor, promoting rapid mixing between the hydrogen jet and the incoming air flow. In the cold flow field, volumetric expansion and diffusion are identified as the dominant mechanisms for vorticity transport in the mixing layer, whereas in the reacting flow field, the baroclinic torque and diffusion emerge as the primary mechanisms. Moreover, the shock wave generator with different structural parameters exhibit a more pronounced influence about shock wave and vorticity distribution on the reacting flow compared to the cold flow. Notably, in reacting flow field, compared to a single-sided shock wave, the simultaneous incidence of shock waves from both the upper and lower sides into the mixing layer and their interaction significantly enhances the baroclinic term and the diffusion term.</p>

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Shock Wave Generator Affected Vorticity Transport in a strut-based Scramjet Combustor

  • 期刊论文

  • 发表日期：

    2025年9月25日

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  • Yige Ouyang,
  • Qian Chen,
  • Yuling Hu

摘要

Shock wave generator is an effective device for mixing enhancement in scramjet combustors. This paper employs the Reynolds-averaged Navier-Stokes (RANS) numerical simulation method to investigate the effects of different parameters of a wall-mounted ramp, which serves as a shock wave generator, on cold flow, reacting flow fields and the vorticity transport within the turbulent mixing region in a strut-based scramjet combustor. The parameters examined include the ramp angle (15°, 20°, 25°, 30°) and its position (110, 130, 150 mm). The results demonstrate that the introduction of the shock wave generator alters the shock wave distribution within the strut-based combustor, promoting rapid mixing between the hydrogen jet and the incoming air flow. In the cold flow field, volumetric expansion and diffusion are identified as the dominant mechanisms for vorticity transport in the mixing layer, whereas in the reacting flow field, the baroclinic torque and diffusion emerge as the primary mechanisms. Moreover, the shock wave generator with different structural parameters exhibit a more pronounced influence about shock wave and vorticity distribution on the reacting flow compared to the cold flow. Notably, in reacting flow field, compared to a single-sided shock wave, the simultaneous incidence of shock waves from both the upper and lower sides into the mixing layer and their interaction significantly enhances the baroclinic term and the diffusion term.