Flame Transition in Dual-Mode Scramjet Combustor with Oxygen Piloted Ignition

A study was conducted to investigate flame transition in dual-mode scramjet combustor with oxygen piloted ignition. The heat sink combustor model was made of stainless steel and could be divided into four segments. A strut was mounted in the center of the combustor for fuel injection and flame holding. Pressure taps were installed at the centerline of the combustor side wall with the range 0-1 MPa and its error was ±0.25% in full scale and the frequency was 500 Hz. The wall pressure distribution was used to calculate the one-dimensional (1D) Mach number distribution along the combustor based on a proposed analysis approach to obtain an estimate of the axial distribution of flow properties in dual-mode scramjet combustor. The pressure and Mach number distribution analyses showed that different combustion modes had been attained in this dual-mode combustor model.