Modernized Scheme of Thermal Ignition and Flame Stabilization at Flow Supersonic Speeds in Channel

For providing fuel ignition at the high supersonic flow velocity original device was developed. Main element of this device in the form of wall slotted channel has to provide the high flow temperature in the area of mixture. Numerical simulation has been performed based on solving the full averaged Navier-Stokes equations, supplemented turbulence model. The experiments were carried out in the hotshot wind tunnel 1T-302M at the mode of the attached pipe. The flow parameters at the model entrance were following: M = 2 5.8, p(o) = 12 390bar, T-o = 1170- 2930K at equivalence ratio of hydrogen from 0.6 to 1.1. Self-ignition of the hydrogen in the slotted channel has occurred at total flow temperature of 2250K at the combustor entrance. The combustion process is extended to the entire channel of the combustor. When the facility worked with decreasing parameters of the flow, combustion continued until drop of the static temperature of about 230K at the entrance of the combustor.