Inyoung YANG, Sanghun LEE, Kyungjae LEE, Yangji LEE

DOI Number: XXX-YYY-ZZZ

Conference number: HiSST2024-00237

Experiment research was performed on a liquid-fueled regenerative supersonic combustor model. The model features a small inlet flowpath height, i.e. 20 mm, which is typical in many scaled experimental researches. The model inlet speed was Mach 2, and the inlet flow condition was 800 kPa(abs) of total pressure and 1,290 K of total temperature corresponding to Mach 5 flight condition. The test campaign was done at various fuel flow rate with fixed model geometry and fixed inlet flow condition. Fuel was heated by the regenerative heat exchanger before supplied to the injector. The fuel injection condition was varied with various test conditions, in the range of 1.0-1.5 MPa(abs) and 730-750 K. The transition from scramjet mode to ramjet mode was observed in the model at relatively low fuel equivalence ratio of 0.19. Mode transition at such a low fuel equivalence is addressed to the small inlet flowpath height, by which the effect of boundary layer becomes dominant in the model. The transition was detectable by the wall static pressure distribution, as well as by the direct optical observation of the flame.

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