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<p>Lightweight space flights are made possible by Scramjet technology, which has been successfully tested all around the world. In order to improve the performance of this technology, researchers are constantly improvising different combustor designs by adding struts, flame holders, and turbulence inserts and modifications in the combustor area, with the motive to improve the fuel air consumption. Another additional aspect of combustor design is the fuel injection and angle of injection. To overcome the challenge of inappropriate mixing in supersonic combustor, the present study, analyses the impact of fuel injection angles ranging from 90°–30° with an increment of 15° on fluid flow characteristics and combustion performance in scramjet combustors. For the selection of the turbulence model, three different models are analyzed and compared for the static pressure variation, among all, SST k-ω model showed the maximum approximation. The computational model is incorporated with a strut and parallel cavities in the combustor and the fuel is injected with injection angle ranging between 90°–30°. The computational results indicate that initially after fuel injection, the static pressure remains uniform, which is pivotal for injection angle study. However, downstream the creation of high-temperature regions is seen significant near the cavities for 90° injection angles. Furthermore, the flow is seen deaccelerated ahead of the injectors creating high-intensity vortices and recirculation region downstream for injection angle 45° and beyond. It has been also seen that the 90° injection angles exhibit higher penetration rates than other injection angles, leading to the enhancement of the mixing efficiency. Furthermore, the highest temperature rise occurs at 90° injection, while 75° injection shows optimal mixing efficiency and combustion performance. Thus, it can be concluded that the current scramjet model operates effectively when the fuel is injected at 75° with a combustion efficiency of 93%.</p> Graphical Abstract <p></p>

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Impact of parametric changes on hybrid scramjet flow

  • 期刊论文

  • 发表日期：

    2026年4月6日

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  • Namrata Bordoloi,
  • Krishna Murari Pandey,
  • D. Sriram,
  • R. Vinothkumar,
  • V. Hari Ganesh,
  • C. Chanakyan,
  • K. Arunkumar

摘要

Lightweight space flights are made possible by Scramjet technology, which has been successfully tested all around the world. In order to improve the performance of this technology, researchers are constantly improvising different combustor designs by adding struts, flame holders, and turbulence inserts and modifications in the combustor area, with the motive to improve the fuel air consumption. Another additional aspect of combustor design is the fuel injection and angle of injection. To overcome the challenge of inappropriate mixing in supersonic combustor, the present study, analyses the impact of fuel injection angles ranging from 90°–30° with an increment of 15° on fluid flow characteristics and combustion performance in scramjet combustors. For the selection of the turbulence model, three different models are analyzed and compared for the static pressure variation, among all, SST k-ω model showed the maximum approximation. The computational model is incorporated with a strut and parallel cavities in the combustor and the fuel is injected with injection angle ranging between 90°–30°. The computational results indicate that initially after fuel injection, the static pressure remains uniform, which is pivotal for injection angle study. However, downstream the creation of high-temperature regions is seen significant near the cavities for 90° injection angles. Furthermore, the flow is seen deaccelerated ahead of the injectors creating high-intensity vortices and recirculation region downstream for injection angle 45° and beyond. It has been also seen that the 90° injection angles exhibit higher penetration rates than other injection angles, leading to the enhancement of the mixing efficiency. Furthermore, the highest temperature rise occurs at 90° injection, while 75° injection shows optimal mixing efficiency and combustion performance. Thus, it can be concluded that the current scramjet model operates effectively when the fuel is injected at 75° with a combustion efficiency of 93%.

Graphical Abstract