Patent ID: 6948306
Filing Date: 2005-09-27
Classification: B64G,F02K,F05D,F23R

Abstract:
1. A supersonic combustion heater apparatus capable of withstanding high enthalpy flow for operating at high Mach numbers comprising: a means for providing a high-pressure flow; a first nozzle having a throat to withstand said high pressure flow, whereby a boundary layer flow is created downstream of said first nozzle; a supersonic combustion region is located adjacent to said first nozzle, said region including a fuel injection means for ignition and an oxygen injection means for maintaining flame stabilization; and an expansion zone dimensioned and configured for withstanding high enthalpy and a supersonic combustion flow, said expansion zone is adjacent to said supersonic combustion region, said expansion zone including a second expansion nozzle, and a divergent area dimensioned and configured to withstand high enthalpy flow and a supersonic combustion flow, said divergent area is adjacent to said supersonic combustion region whereby increasing high Mach speeds are achieved as said supersonic combustion flow reaches downstream of said divergent area.