Patent ID: 8087229

Claim:
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 1 ; 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 1 which is greater than 0° C.; 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 2 , and a final total temperature defined as To 2 , wherein said final total temperature is up to about 3000° C., wherein said flame stabilization means is positioned within said diverging area depending on the dimensions of said diverging area, said total temperature within said diverging area, and having a final Mach speed at said exit plane, wherein a total pressure ratio Po 2 /Po 1 of up to about 1 which is measured from said starting total pressure and said final total pressure, and said final Mach speed produced at said exit plane, wherein said final Mach speed is varied by heat addition in said diverging area by said flame stabilization means, wherein at said exit plane said final Mach speed is supersonic in a range from between about 1.5 to about 3.