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<p>This study explores the enhancement of scramjet engine performance through the implementation of different strut configurations, specifically the Left Diagonal (LD) and Right Diagonal (RD) models, operating at Mach 2 with hydrogen fuel. Numerical simulations were conducted using the k–ω SST turbulence model to evaluate and compare the combustion efficiency of these configurations against a baseline model. The results indicate that both LD and RD models exhibit improved combustion efficiency between 120 and 240&#xa0;mm along the combustor length, primarily due to shock waves generated by the small strut. However, beyond 240&#xa0;mm, the LD model experiences a decline in efficiency, concluding 2.06% lower than the baseline. In contrast, the RD model maintains its advantage, achieving a 2.6% higher combustion efficiency compared to the baseline. This improvement is attributed to the enhanced turbulence and wake regions created by the strut positioned just below the divergent section of the combustor. Furthermore, analysis of hydrogen mass fraction along the combustor length reveals more effective fuel mixing in the RD model, as evidenced by its lower residual H<sub>2</sub> mass fraction compared to the LD model. The optimized strut placement in the RD configuration contributes to more stable and efficient combustion, demonstrating its potential for improving supersonic combustion performance. These findings provide valuable insights into strut-based cavity design optimization for air-breathing propulsion systems, particularly for hypersonic applications.</p>

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Performance optimization of scramjet engines with left and right diagonal strut configurations at Mach 2

  • 期刊论文

  • 发表日期：

    2025年4月10日

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  • Ritesh Mane,
  • Rohit Kumar Prasad,
  • Garima Kushwaha,
  • Shivangi Sinha,
  • Royal Madan

摘要

This study explores the enhancement of scramjet engine performance through the implementation of different strut configurations, specifically the Left Diagonal (LD) and Right Diagonal (RD) models, operating at Mach 2 with hydrogen fuel. Numerical simulations were conducted using the k–ω SST turbulence model to evaluate and compare the combustion efficiency of these configurations against a baseline model. The results indicate that both LD and RD models exhibit improved combustion efficiency between 120 and 240 mm along the combustor length, primarily due to shock waves generated by the small strut. However, beyond 240 mm, the LD model experiences a decline in efficiency, concluding 2.06% lower than the baseline. In contrast, the RD model maintains its advantage, achieving a 2.6% higher combustion efficiency compared to the baseline. This improvement is attributed to the enhanced turbulence and wake regions created by the strut positioned just below the divergent section of the combustor. Furthermore, analysis of hydrogen mass fraction along the combustor length reveals more effective fuel mixing in the RD model, as evidenced by its lower residual H2 mass fraction compared to the LD model. The optimized strut placement in the RD configuration contributes to more stable and efficient combustion, demonstrating its potential for improving supersonic combustion performance. These findings provide valuable insights into strut-based cavity design optimization for air-breathing propulsion systems, particularly for hypersonic applications.