Combustion Instability in Lab-Scale HREs with Swirl Injectors: Pre- and Post-Chamber Effects | ||
International Conference on Aerospace Sciences and Aviation Technology | ||
Volume 21, Issue 21, September 2025, Pages 1-11 PDF (2.62 M) | ||
Document Type: Original Article | ||
DOI: 10.1088/1742-6596/3070/1/012015 | ||
Authors | ||
Mohamed Elkhshen* 1; Anwer Hashish2; Mahmoud Y. M. Ahmed3; Ahmed Farid Ayad2 | ||
1PhD student, Aerospace Engineering Department, Military Technical College, Egypt. | ||
2Associate Professor, Aerospace Engineering Department, Military Technical College, Egypt. | ||
3Professor. Aerospace Engineering Department, Military Technical College, Egypt. | ||
Abstract | ||
Combustion instability in hybrid rocket engines (HREs) remains a significant challenge, leading to pressure oscillations, vibrations, and potential engine failure. This study aims to mitigate instability while optimizing performance and safety by investigating the effects of oxidizers swirl injector, pre-combustion chamber, and post-combustion chamber lengths. Using paraffin-based fuels and oxygen, the methodology is based on experimental lab-scale firing tests to analyze the impact of these parameters on combustion dynamics. The research integrates combustion theory, fluid dynamics, and chamber design to identify optimal configurations that reduce instability and enhance fuel regression rates. The study culminates in a proposed engine design that achieves stable combustion and improved performance, offering a pathway to safer and more efficient HREs. | ||
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