# US 2018/0023472 A1 · Engine, rotary device, power generator, power generation system, and methods of making and using the same > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2018/0023472 A1 - Document ID: US20180023472A1 - Status: Published application - Kind: A1 - Application number: 15/641,760 - Filed: 2017-07-05 - Published: 2018-01-25 - Earliest claimed: 2016-07-22 - Inventors: Brent Wei-Teh LEE - Web page: https://patentgrep.com/patent/US20180023472A1 ## CPC - F02C 3/165: {the combustion chamber contributes to the driving force by creating reactive thrust} - F01D 1/32: with pressure velocity transformation exclusively in rotor, e.g. the rotor rotating under the influence of jets issuing from the rotor, {e.g. Heron turbines (the working fluid being a combustion products F02C3/165; jet propulsion plants per se F02K)} - F01D 5/02: Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) - F01D 13/02: Working-fluid interconnection of machines or engines - F02C 5/04: the combustion chambers being formed at least partly in the turbine rotor - F02C 7/16: characterised by cooling medium - F02C 7/22: Fuel supply systems - F02C 7/36: Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) - F02K 7/005: {the engine comprising a rotor rotating under the actions of jets issuing from this rotor} - F05D 2220/32: in gas turbines - F05D 2220/76: an electrical generator - F05D 2240/242: of reaction type - F05D 2240/35: Combustors or associated equipment - F05D 2260/207: using a phase changing mass, e.g. heat absorbing by melting or boiling - F05D 2260/40: Transmission of power - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract An engine, a rotary device, a power generation system, and methods of manufacturing and using the same are disclosed. The engine includes a detonation and/or combustion chamber configured to detonate a fuel and rotate around a central rotary shaft extending from the detonation and/or combustion chamber, a fuel supply inlet configured to provide the fuel to the detonation and/or combustion chamber, at least two rotating arms extending radially from the detonation and/or combustion chamber and configured to exhaust detonation gases from detonating the fuel in the detonation and/or combustion chamber and provide a rotational thrust and/or force, the rotating arms having inner and outer walls and a nozzle at a distal end thereof, the nozzle being at or having an angle configured to provide the rotational thrust and/or force, and a plurality of cooling coils between the inner and outer walls. Alternatively, the rotary device may include a rotary disc. ## Claims ### Claim 1 An engine, comprising: a) a detonation and/or combustion chamber configured to detonate a fuel and rotate around a central rotary shaft extending from said detonation and/or combustion chamber; b) a fuel supply inlet configured to provide said fuel to said detonation and/or combustion chamber; c) at least two rotating arms extending radially from said detonation and/or combustion chamber and configured to exhaust detonation gases from detonating said fuel in said detonation and/or combustion chamber and provide a rotational thrust and/or force, each of said rotating arms having inner and outer walls and a nozzle at a distal end thereof, said nozzle being at or having an angle configured to provide said rotational thrust and/or force; and d) a plurality of cooling coils between said inner and outer walls. ### Claim 2 (depends on 1) The engine of claim 1, wherein said inner wall extends from said detonation and/or combustion chamber and has a cylindrical or a curved tubular shape, and said outer wall has a cylindrical or a curved tubular shape that matches or follows the shape of said inner wall. ### Claim 3 (depends on 1) The engine of claim 1, wherein each of said inner and outer wall comprises a metal sheet, a metal foil, or a ceramic structure, said inner wall is configured to optimize a cooling function, and said outer wall is configured to optimize an aerodynamic function. ### Claim 4 (depends on 1) The engine of claim 1, wherein said cooling coils are configured to carry a fluid through said cooling coils. ### Claim 5 (depends on 4) The engine of claim 4, wherein each of said cooling coils is configured to vaporize said fluid and expel a vapor or gas through said nozzle. ### Claim 6 (depends on 5) The engine of claim 5, wherein said fluid comprises water. ### Claim 7 (depends on 1) The engine of claim 1, further comprising a mechanical work unit configured to receive at least part of said rotational thrust and/or force. ### Claim 8 (depends on 1) The engine of claim 1, further comprising one or more wheels or cylinders, each having a plurality of buckets or cups on an inner or outer circumference thereof, wherein said buckets or cups are configured to receive the fluid expelled from the nozzles. ### Claim 9 (depends on 8) The engine of claim 8, wherein the buckets or cups are on said inner circumference, the wheel has a transmission gear on the outer circumference, the transmission gear is configured to engage with one or more external gears configured to drive an external generator or work unit. ### Claim 10 (depends on 1) The engine of claim 1, further comprising one or more aerodynamic surfaces on or over the rotating arms. ### Claim 11 An engine, comprising: a) a detonation and/or combustion chamber configured to detonate a fuel and expand a gas; b) a supply inlet configured to provide said fuel and said gas to said detonation and/or combustion chamber; and c) a first rotary disc joined to a central axle or shaft and configured to rotate around the central axle or shaft, said rotary disc having (i) an inlet configured to receive the detonated fuel and expanded gas and (ii) a plurality of nozzles at a distal edge thereof, said nozzles being oriented to expel the detonated fuel and expanded gas in a predetermined direction. ### Claim 12 (depends on 11) The engine of claim 11, further comprising a wheel or cylinder having a plurality of buckets or cups on an inner or outer circumference thereof, said plurality of buckets or cups configured to receive the fluid expelled from the nozzles. ### Claim 13 (depends on 11) The engine of claim 11, wherein the buckets or cups are on said inner circumference, the wheel further comprises a transmission gear on the outer circumference, and the transmission gear is configured to engage with one or more external gears configured to drive an external generator or work unit. ### Claim 14 (depends on 12) The engine of claim 12, further comprising a plurality of generators receiving rotational energy or torque from a plurality of said wheels or cylinders. ### Claim 15 (depends on 11) The engine of claim 11, further comprising a second rotary disc joined or affixed to said central axle or shaft and adjacent to said first rotary disc, said second rotary disc (i) having a plurality of nozzles at a distal edge thereof and (ii) being configured to rotate around the central axle or shaft and receive the expelled detonated fuel and expanded gas from said first rotary disc. ### Claim 16 (depends on 11) The engine of claim 11, further comprising a compressor at or near the supply input, said compressor is configured to compress at least the gas provided to said detonation and/or combustion chamber. ### Claim 17 (depends on 16) The engine of claim 16, wherein said compressor comprises one or more fans joined or affixed to said central axle or shaft. ### Claim 18 (depends on 11) The engine of claim 11, wherein the rotary disc comprises a plurality of dividers. ### Claim 19 A method of converting a fuel and an optional gas or vapor into mechanical energy, comprising: a) introducing the fuel into a detonation and/or combustion chamber through a fuel supply inlet; b) detonating the fuel in said detonation and/or combustion chamber; c) exhausting detonation gas(es) through a plurality of rotating arms or a rotary disc extending radially from said detonation and/or combustion chamber, each of said rotating arms having inner and outer walls and a nozzle at a distal end thereof, and said rotary disc having a plurality of nozzles at a distal end or edge thereof; d) when the detonation gas(es) are exhausted through the plurality of rotating arms, introducing a fluid into a cooling coil between each of said inner and outer walls, vaporizing the fluid to form the gas or vapor, and expelling the gas or vapor from said nozzle; e) rotating said rotating arms or said rotary disc from the exhausted detonation gas(es) and, when present, the expelled gas or vapor to generate a rotational thrust and/or force; and f) converting said rotational thrust and/or force into said mechanical work or energy. ### Claim 20 (depends on 19) The method of claim 19, wherein the method converts said fuel and said gas or vapor into mechanical energy, and comprises exhausting said detonation gas(es) through said plurality of rotating arms, introducing said fluid into said cooling coil, vaporizing the fluid to form the gas or vapor, expelling the gas or vapor from said nozzle, and rotating said rotating arms from the exhausted detonation gas(es) and the expelled gas or vapor. ### Claim 21 (depends on 19) The method of claim 19, further comprising expelling gas or vapor from said nozzles into a plurality of buckets on an outer circumference of a wheel. ### Claim 22 (depends on 19) The method of claim 19, further comprising converting rotational forces to a plurality of generators.