Fluidic combustion control of a solid fuel ramjet
AssigneeThe United States of America as represented by the Secretary of the Navy
InventorAllen L. Holzman
Life of this patent
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Abstract
Fluidic combustion control of a ramjet by injecting a fluid into the base recirculation region to reduce the critical injection parameter, or to shut down the ramjet without affecting the hot air flow.
Claims6
A fluidic combustion control system for a solid fuel ramjet comprising;
- a ramjet casing;
- a sustainer region in said casing lined with a solid fuel having an internal diameter D.sub.p and having a head end;
- an injector means forwardly of said sustainer region and having an internal diameter D.sub. i,
- a recirculation zone at the head end of said sustainer region and adjacent said injector means,
- said solid fuel normally having a critical injection parameter h/D.sub.p below which combustion will not be sustained where h equals 1/2 (D.sub.p -D.sub.i);
- a source of gas;
- and
- means for introducing said gas into said recirculation zone to control the combustion within said sustainer region by altering the critical injection parameter of said solid fuel.
A method for fluidic combustion control of a solid fuel ramjet having a sustainer region lined with a solid fuel having an internal diameter D.sub.p and having a head end, an injector means having an internal diameter D.sub.i and a recirculation zone at the head end of said sustainer region and adjacent said injector means, said fuel having a critical injection parameter h/D.sub.p below which combustion will not be sustained where h=1/2(D.sub.p -D.sub.i), comprising the steps of:
- supplying airflow to said injector means, and
- injecting a gas into the recirculation zone to alter the critical injection parameter of the fuel.
Dependencies are inferred from the claim text.