Hojin CHOI, Jong-Ryul BYUN, Sangwook JIN, Jaewon KIM, Dongchang PARK

DOI Number: N/A

Conference number: HiSST-2024-283

Ignition and combustion tests of supersonic combustor were conducted with a ground test facility which simulates M4 to M6 flight conditions. In case of ambient pressure conditions at the exit of combustor, many self-ignition and stable combustion cases are shown with gaseous hydrocarbon fuel. To see the effect of separation at the exit of combustor or nozzle where flow is developed to supersonic, altitude is simulated with an air ejector. Many ignition failures and extinction of flame cases took place in the condition where self-ignition and stable combustion were possible with ambient air condition. It was shown that ignition and stable combustion existed due to the ignition source near the separation and interaction with the boundary layer by high-speed imaging and pressure measurement.

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