Min-Su KIM, Keon-Hyeong LEE, Eun-Sung LEE, Hyung-Seok HAN, Seung-Min JEONG, Bu-Kyeng SUNG, Jeong-Yeol CHOI

DOI Number: 10.60853/bmx2-wx17

Conference number: HiSST-2024-0084

Scramjet engines are critical technologies for air-breathing hypersonic vehicles, with ongoing research aimed at addressing their technical challenges. Supersonic combustion in scramjet engines necessitates rapid fuel-oxidizer mixing and flame stabilization due to the short residence time in the combustor. This study presents findings from experiments conducted using the Pusan National University Direct-Connect Scramjet Combustor (PNU-DCSC) integrated with a Micro-Pulse Detonation Engine. The experimental setup is designed for simulating flight conditions at altitudes of 20~25 km and Mach number 4.0~5.0. The results show that varying the jet-to-freestream momentum flux ratio affects fuel penetration height. Furthermore, as the fuel injection pressure increases, the combustion area expands, leading to transitions in combustion modes and flame structures. The flame-base, where peak combustion pressure forms, moves upstream, and pressure oscillations intensify.

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In Categories: 1.Events, HiSST 2024, Propulsion Systems and Components
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