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US 12,546,249 B1Granted
Disk engine with circumferential swirl radial combustor
AssigneeThe United States of America as represented by the Secretary of the Air Force
InventorsBrian Bohan, Marc Polanka, Bennett Staton
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Abstract
A disk engine and system configured to provide high power at a reduced axial length is disclosed herein. The disk engine includes a radial compressor, a compressor discharge manifold positioned circumferentially about compressor, a combustion chamber positioned within the discharge manifold and a radial turbine positioned radially inward of the combustion chamber.
Claims9
A disk engine comprising:
- a radial compressor;
- a compressor discharge manifold positioned circumferentially around the radial compressor;
- a combustion chamber positioned within the compressor discharge manifold;
- a primary combustion zone in a radially outer region of the combustion chamber;
- a secondary combustion zone positioned radially inward of the primary combustion zone;
- a dilution combustion zone positioned radially inward of the secondary combustion zone;
- a radial turbine positioned radially inward of all portions of the primary combustion zone, the secondary combustion zone and the dilution combustion zone of the combustion chamber;
- wherein the combustion chamber extends completely (360 degrees) around the radial compressor and the radial turbine;
- a compressor sidewall extending radially outward from the radial compressor to define one side of the disk engine;
- a turbine sidewall extending radially outward from the radial turbine to define an opposing side of the disk engine;
- and
- wherein pressurized air exits the radial compressor and traverses through the combustion chamber and into the radial turbine without passing outside of the compressor sidewall or the turbine sidewall of the disk engine.
9 more elements
Dependencies are inferred from the claim text.