Investigation of supersonic combustion of hydrocarbon fuel-riched hot gas in scramjet combustor

Due to the important of supersonic combustion of hydrocarbon fuel (such as kerosene) for hypersonic propulsion, in a supersonic air stream has been investigated the combustion of hydrocarbon fuel-riched hot gas jet. To avoid ignition problem of hydrocarbon fuel (kerosene) in supersonic air stream, the hydrocarbon. fuel has been burned partially in the subsonic combustion burner. Also, to avoid interference from the boundary layer and to understand the basic flow characteristic, the hydrocarbon fuelriched hot gas flows were ‘injected in parallel to the fi-ee’stream through a large 2dimensional nozzle. Such a reliable method for ignition and stable flame has been ‘proven at the lower air total temperature range, 880 K , 4, it is possible to leave the flow supersonic in order to avoid great pressure losses, and it becomes more better about flight M > 6, approximately. Only weak oblique shocks occur in the hypersonic inlet, but the main problem, which is supersonic combustion, then arise. In the supersonic combustion burner the residence time of the gases becomes so short, that the equilibrium of supersonic combustion can no Ion P er be assumed.