# US 12,180,887 B1 · Rotating detonation combustor and system > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,180,887 B1 - Document ID: US12180887B1 - Status: Granted - Kind: B1 - Application number: 16/686,702 - Filed: 2019-11-18 - Granted: 2024-12-31 - Earliest claimed: 2018-12-19 - Assignees: The United States of America as represented by the Secretary of the Air Force - Applicants: Government of the United States, as represented by the Secretary of the Air Force - Inventors: Michael Mcclearn; Riley Huff; John Hoke; Matthew Fotia - Web page: https://patentgrep.com/patent/US12180887B1 ## CPC - F02C 5/02: characterised by the arrangement of the combustion chamber in the chamber in the plant (combustion chambers per se F23R) - F02C 3/14: characterised by the arrangement of the combustion chamber in the plant (combustion chambers per se F23R; F02C3/205 takes precedence) - F02C 6/00: Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use - F02C 7/32: Arrangement, mounting, or driving, of auxiliaries - F02C 9/26: Control of fuel supply (F02C9/48 takes precedence; fuel valves F02C7/232) - F23R 3/10: for primary air (F23R3/06, F23R3/045 take precedence) - F23R 7/00: Intermittent or explosive combustion chambers - F05D 2220/50: for auxiliary power units (APU's) - F05D 2220/76: an electrical generator - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A rotating detonation combustor (RDC) and an associated system is disclosed herein. The RDC can be operably coupled with a vehicle to provide additional power capability over the primary motive power source. The RDC can be operated on demand to provide power to a turbine connected to an electrical power generator in some forms. The RDC can be used in stationary systems as well as moving vehicle systems. ## Claims ### Claim 1 A system comprising: a primary power source; an auxiliary power system coupled with the primary power source; a rotating detonation combustor (RDC) operable as a power source for the auxiliary power system; wherein the RDC includes: a fuel supply ring having a first face defining a first side of the RDC and a second face spaced apart from the first face; a plurality of first fuel supply passageways formed through the fuel supply ring; a baseplate connected to the second face of the fuel supply ring; a central aperture formed through the baseplate; a circular pocket formed in the baseplate around the central aperture; a plurality of second fuel passageways formed through the baseplate fluidly connected to the circular pocket; a fuel ring positioned in the circular pocket of the baseplate; a plurality of third fuel passageways formed through the fuel ring; an air inlet spacer ring connected to the baseplate on the opposite side from the fuel supply ring, the air inlet spacer ring positioned around an outer perimeter of the RDC, the air inlet spacer ring having a plurality of air inlet ports positioned circumferentially around a radial combustion chamber projecting radially inward from the outer perimeter; an air distribution ring positioned radially inward of the air inlet spacer ring, the air distribution ring having a plurality of air distribution apertures that are greater in number and smaller in size to that of the plurality of air inlet ports, a channel plate positioned radially inward of the air distribution ring, the channel plate having an arcuate aft face and a flat front face; wherein the radial combustion chamber is formed between the arcuate aft face of the channel plate and a combination of a front face wall of the baseplate and an outer wall of an inlet guide vane ring to define a substantially constant annulus area of the radial combustion chamber; and a top plate connected to each of the air spacer ring, the air distribution ring and the channel plate at the aft end of the RDC, the top plate defining an opposing second side of the RDC; and an auxiliary turbine driven by the RDC. ### Claim 2 (depends on 1) The system of claim 1, further comprising an electrical power generator connected to the auxiliary turbine. ### Claim 3 (depends on 1) The system of claim 1, further comprising positioning the RDC in a vehicle defined by one of a flight vehicle, a land vehicle and a water vessel. ### Claim 4 (depends on 1) The system of claim 1, wherein the primary motive power source includes at least one of a gas turbine engine, an internal combustion engine and an electric motor. ### Claim 5 (depends on 1) The system of claim 1, further comprising a conduit connected between the primary power source and the RDC. ### Claim 6 (depends on 5) The system of claim 5, wherein the conduit transports pressurized air from the primary power source to the RDC. ### Claim 7 (depends on 1) The system of claim 1, wherein the arcuate aft face of the channel plate extends radially inward from an inlet port of the radial combustion chamber to a nozzle port. ### Claim 8 (depends on 7) The system of claim 7, further comprising a throat ring positioned proximate the inlet port of the combustion chamber. ### Claim 9 (depends on 8) The system of claim 8, further comprising a variable fuel injection area defined by a position of the throat ring. ### Claim 10 (depends on 7) The system of claim 7, further comprising the inlet guide vane ring positioned within the nozzle port upstream of the turbine. ### Claim 11 (depends on 1) The system of claim 1, wherein a combustible fuel is stored in one of a liquid or gaseous form.