Experimental Study on the Ignition Characteristics of Scramjet Combustor with Tandem Cavities Using Micro-Pulse Detonation Engine

This experimental investigation focused on the ignition and combustion characteristics of a tandem cavity-based scramjet combustor with side-by-side identical cavities. study utilized Pusan National University-direct connect (PNU-DCSC), which was capable simulating flight conditions at Mach number 4.0–5.0 altitudes 20–25 km using vitiated air heater (VAH). The tests were conducted under off-design point corresponding to low inlet enthalpy. It is condition in self-ignition does not occur, micro pulse detonation engine (μPDE) ignitor used. results revealed that as injection pressure gaseous hydrogen fuel (GH2) equivalence ratio increased, mode transitioned from cavity-shear layer flame jet-wake flame. Furthermore, measured wall static profiles along isolator indicated region elevated distribution caused by shock train expanded upstream higher ratios. When ignited secondary cavity, area did extend primary cavity lower ratios, while it faster Therefore, found vary based overall main position.