초록 ▼

A new dual-mode ramjet combustor used for operation over a wide flight Mach number range is described. Subsonic combustion mode is usable to lower flight Mach numbers than current dual-mode scramjets. High speed mode is characterized by supersonic combustion in a free-jet that traverses the subsonic

A new dual-mode ramjet combustor used for operation over a wide flight Mach number range is described. Subsonic combustion mode is usable to lower flight Mach numbers than current dual-mode scramjets. High speed mode is characterized by supersonic combustion in a free-jet that traverses the subsonic combustion chamber to a variable nozzle throat. Although a variable combustor exit aperture is required, the need for fuel staging to accommodate the combustion process is eliminated. Local heating from shock-boundary-layer interactions on combustor walls is also eliminated.

대표청구항 ▼

1. A process for operating a dual-mode combustor, comprising the steps of: using an inlet contraction chamber to compress combustion air into a combustion air passageway;injecting fuel from said combustion air passageway into said combustion air in said combustion air passageway creating a fuel-air

1. A process for operating a dual-mode combustor, comprising the steps of: using an inlet contraction chamber to compress combustion air into a combustion air passageway;injecting fuel from said combustion air passageway into said combustion air in said combustion air passageway creating a fuel-air mixture;feeding said fuel-air mixture from said combustion air passageway into a diffusion section;igniting said fuel-air mixture in said diffusion section and combusting said fuel-air mixture in said diffusion section and in a combustion chamber, where a portion of the combusting fuel-air mixture engages a flame holder affixed to the combustion chamber to stabilize the combusting fuel-air mixture;evacuating said combusted fuel-air mixture from said combustion chamber and into a variable area nozzle throat; and,modulating and positioning said variable area nozzle throat according to an algorithm creating and controlling the position of a terminal shock within said diffusion section, said algorithm being a function of flight Mach number; andfurther comprising the step of not engaging said flame holder with said portion of the combusting fuel-air mixture in a scramjet mode, and wherein said step of modulating and positioning a variable area nozzle throat according to an algorithm creating and controlling said position of said terminal shock within said diffusion section, includes transitioning, using said algorithm, said dual-mode combustor from a ramjet mode to said scramjet mode by opening said variable area nozzle throat at a specified flight Mach number. 2. A process for operating a dual-mode combustor as claimed in claim 1 wherein said algorithm includes a discontinuity where there are two values for a specified flight Mach number. 3. A process for operating a dual-mode combustor as claimed in claim 2 wherein said fuel-air mixture and said combusted fuel-air mixture is separated into a free-jet from said combustion air passageway where a step is located to said variable area nozzle throat. 4. A process for operating a dual-mode combustor as claimed in claim 3 wherein said free-jet does not engage said subsonic diffuser, said combustion chamber or a contraction section. 5. A process for operating a dual-mode combustor as claimed in claim 4 wherein said algorithm includes said variable area nozzle position as a ratio A/Ac of the actual nozzle throat area, A, to the inlet capture area, Ac, of said contraction section, said variable area nozzle throat position varies from a ratio of about 0.8=A/Ac at about flight Mach number 2.5 in the ramjet mode to a ratio of about 0.18=A/Ac at about flight Mach number 5.0 in the ramjet mode, said nozzle throat position varies rapidly from a ratio of about 0.18=A/Ac at about flight Mach number 5.0 in the ramjet mode to a ratio of about 0.41=A/Ac at about flight Mach number 5.0 transitioning to the scramjet mode, thereafter, said nozzle throat position varies from about 0.41=A/Ac at flight Mach number 5.0 in the scramjet mode to a ratio of about 0.15=A/Ac at about flight Mach number 12 in the scramjet mode. 6. A process for operating a dual-mode combustor as claimed in claim 4, wherein said algorithm includes reducing said variable area nozzle throat from an initial value to a first value from about 2.5-5.0 flight Mach number in the ramjet mode, enlarging said open area of said variable area nozzle throat at about flight Mach number 5.0 from said first value to a second value, said second value representing a larger area than said first value, transitioning from said ramjet mode to said scramjet mode, and then, reducing said open area of said variable area nozzle throat from said second value representing the larger area to a final value from about 5.0-12.0 flight Mach number in the scramjet mode.