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<p>In the past few years, the scientific community has exhibited a marked fascination with scramjet combustors employing strut injection techniques. Nevertheless, the primary challenges in designing such combustors remain their low combustion efficiency and minimal thrust force. These crucial performance indicators are significantly influenced by the combustor’s mixing efficiency. The effectiveness of mixing, in turn, is determined by the fuel injection system’s design within the combustor. A reduced mixing length inside the scramjet combustor increases scramjet combustor performance. In this context, a 2D non-reacting flow analysis is conducted numerically on a dual cavity parallel scramjet combustor with a novel twin strut injector. The governing equations are discretized with a finite volume scheme. This work studies the effect of a novel twin strut injection system (CBSC-3) on the performance of the cavity-based combustor compared to the wall injection (CBSC-1) and DLR (CBSC-2) injection systems. The results show that CBSC-3 requires a mixing length of 0.18&#xa0;m to reach 100% mixing efficiency with a total pressure loss of 26%. Whereas CBSC-1 and CBSC-2 achieved 100% mixing efficiency at mixing lengths of 0.2&#xa0;m and 0.22&#xa0;m with total pressure losses of 15% and 25%, respectively. Therefore, it is found that due to the development of favorable flow conditions inside the CBSC-3, the mixing length is reduced, and the total pressure loss is increased, which is the primary cause of the improvement in the combustion efficiency of the combustor, as found in the recent literature.</p>

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Performance Improvement of Dual-Cavity Scramjet Combustor using Novel Twin Strut Fuel Injection

  • 期刊论文

  • 发表日期：

    2025年6月7日

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  • Aabir Das,
  • Anupam Debnath,
  • Bidesh Roy

摘要

In the past few years, the scientific community has exhibited a marked fascination with scramjet combustors employing strut injection techniques. Nevertheless, the primary challenges in designing such combustors remain their low combustion efficiency and minimal thrust force. These crucial performance indicators are significantly influenced by the combustor’s mixing efficiency. The effectiveness of mixing, in turn, is determined by the fuel injection system’s design within the combustor. A reduced mixing length inside the scramjet combustor increases scramjet combustor performance. In this context, a 2D non-reacting flow analysis is conducted numerically on a dual cavity parallel scramjet combustor with a novel twin strut injector. The governing equations are discretized with a finite volume scheme. This work studies the effect of a novel twin strut injection system (CBSC-3) on the performance of the cavity-based combustor compared to the wall injection (CBSC-1) and DLR (CBSC-2) injection systems. The results show that CBSC-3 requires a mixing length of 0.18 m to reach 100% mixing efficiency with a total pressure loss of 26%. Whereas CBSC-1 and CBSC-2 achieved 100% mixing efficiency at mixing lengths of 0.2 m and 0.22 m with total pressure losses of 15% and 25%, respectively. Therefore, it is found that due to the development of favorable flow conditions inside the CBSC-3, the mixing length is reduced, and the total pressure loss is increased, which is the primary cause of the improvement in the combustion efficiency of the combustor, as found in the recent literature.