Patent ID: 8087229
Filing Date: 2012-01-03
Classification: F42C

Abstract:
1. A supersonic combustion air heater apparatus comprising: a means for providing a starting pressure flow, wherein said pressure flow having a starting total pressure defined as Po a fixed geometric nozzle having a converging area, throat, and a diverging area, wherein said throat is located between said converging area and said diverging area, wherein said diverging area is downstream of said throat, wherein said pressure flow at said throat is at Mach 1; an inlet air heater upstream of said nozzle to heat said starting pressure flow to a starting temperature defined as To a flame stabilization means located in said divergent area, wherein said flame stabilization means includes a combustible fuel injector for ignition and for increasing total temperature of said pressure flow in said diverging area, wherein said diverging area having Mach speeds greater than 1; and an exit plane adjacent and downstream to said diverging area, wherein said exit plane having a final total pressure defined as Po