Class / Patent application number | Description | Number of patent applications / Date published |
060247000 | Intermittent combustion | 37 |
20080209884 | Pulse Jet Engines - A pulse jet engine comprising a quarter wave gas resonator ( | 09-04-2008 |
20090064661 | ELECTRO-DYNAMIC SWIRLER, COMBUSTION APPARATUS AND METHODS USING THE SAME - In one embodiment, a combustion apparatus comprises: an oxidant inlet, a fuel inlet, a mixing zone configured to mix fuel and oxidant to form a mixture, a combustion zone in fluid communication with the mixing zone and configured to combust the mixture, and an outlet in fluid communication with the combustion zone. The mixing zone, the combustion zone, and/or the outlet comprises an electro-dynamic swirler configured to swirl ionized gas. The electro-dynamic swirler comprises a plurality of electrodes in electrical communication with a power source. In one embodiment, a method of creating thrust comprises: mixing a fuel and an oxidant to form a mixture, igniting the mixture to form an ignited mixture, combusting the ignited mixture to form a flame, and using the flame to create thrust, wherein the flame and/or the fuel and oxidant are electro-dynamically swirled. | 03-12-2009 |
20090120059 | SEAL FOR PULSE DETONATION ENGINE - A system of controlling airflow into a pulse detonation engine includes a rotary airflow controller valve receiving air from a high-speed inlet. An engine frame includes a plurality of detonation chambers. A sealing mechanism is between the rotary airflow controller valve and the engine frame. The sealing mechanism is associated with the engine frame and limits leakage of a gas from a first of the detonation chambers to a second of the detonation chambers. | 05-14-2009 |
20090126343 | Internal Detonation Reciprocating Engine - A method of rotating a crank shaft and in internal detonation engine are provided. The internal detonation engine comprises a deflagration to detonation transition section. The deflagration to detonation transition section is connected to a main cylinder, which houses a piston. Inducing a detonation wave from the deflagration wave and passing the detonation wave through a fluid, gives rise to high pressure and temperature in a cylinder and pushes a piston towards bottom dead center. An internal detonation reciprocating engine may be a single cylinder and may be either a two or four stroke engine. A two-stroke internal detonation reciprocating engine is similar to a four-stroke internal detonation reciprocating engine but has different valve placements. Detonations produce a more thorough combustion of the fuel and may, thereby, yield reduced emissions of carbon monoxide as compared to internal combustion engines. | 05-21-2009 |
20090139203 | METHOD AND APPARATUS FOR TAILORING THE EQUIVALENCE RATIO IN A VALVED PULSE DETONATION COMBUSTOR - A pulse detonation combustor assembly contains at least one PDC tube, a mechanical air flow valve which directs an air flow into the PDC tube, where the mechanical air flow assembly changes a rate of the air flow into the PDC tube during a fill stage of the PDC tube. The assembly also contains a fuel flow control valve which directs fuel to the PDC tube and changes the rate of the fuel flow into PDC tube. By controlling the flow of the fuel and air into the PDC tube the equivalence ratio profile of the PDC tube can be tailored and controlled. | 06-04-2009 |
20090165438 | Pulse detonation engine - The invention provides a liquid fueled pulse detonation air breathing engine. The invention also provides an embodiment of an engine which has an axial flow compressor final stage configured for momentary closure of air flow at the final stage of the compressor followed by pulse detonation combustion that powers compressor, appliances, propeller, and produce thrust. Fuel enters the configured final stage of the axial flow air compressor to allow a mixture of air and fuel before entering the engine's pulse detonation combustion chamber, also referred to as detonation canister, having an inlet opening for receiving the fuel and air mixture charge and an open end down stream to discharge the resulting combustion products. Once the fuel and air mixture enters the detonation chamber there is closure for an instant of the compressor final stage's novel stators and blades before detonation of the fuel and air mixture. Detonation is initiated by a control system at the final compressor stage closure with ignition and impulse force is provided by a resultant shock wave. The front end of the engine allows control, and provides the use of appliances such as starter, alternator, fuel pumps, timing, and propellers if attached, as well as compressed air to the pulse detonation combustion chamber or canisters. Starting the engine is accomplished by an electrical starter motor as are conventional jet engines. Fuel is injected at the final stage of the compressor for good mixing with the compressed air before being pumped into the combustion chamber or canisters. Ignition and detonation occurs immediately downstream of the final compressor stage in the combustion chamber during the closure position of the compressor final stage. Ignition and detonation of the fuel many times a second generates shock waves that travels out of the open end of the combustion chamber or canisters at supersonic speed. | 07-02-2009 |
20090320446 | Performance improvements for pulse detonation engines - A device and method for improving the performance of a pulse detonation engine. The device includes at least one of an exhaust structure and an ejector. The exhaust structure can be configured as a straight, converging or diverging nozzle device, and connected to the engine to control the flow of a primary fluid produced during a detonation reaction. The ejector is fluidly coupled to the engine, using the movement of the primary fluid to promote entrainment of a secondary fluid that can be mixed with the primary fluid. The secondary fluid can be used to increase the mass flow of the primary fluid to increase thrust, as well as be used to cool engine components. Device positioning, sizing, shaping and integration with other engine operating parameters, such as fill fraction, choice of fuel and equivalence ratio, can be used to improve engine performance. In addition to thrust augmentation and enhanced cooling, the disclosed device can be used for engine noise reduction. | 12-31-2009 |
20100043395 | PULSE DETONATION/DEFLAGRATION APPARATUS AND RELATED METHODS FOR ENHANCING DDT WAVE PRODUCTION - Pulse detonation/deflagration apparatus for providing enhanced pressure wave operating frequency and/or magnitude, and methods of increasing the frequency or the magnitude of deflagration to detonation waves, are provided. A pulse detonation/deflagration apparatus can include a main/outer pulse detonation/deflagration actuator/engine (PDA/E) with multiple smaller internal combustion chambers or tubes positioned inside the cavity of the main/outer PDA/E with each performing the function of individual PDA/Es. The output pressure waves created by the internal PDA/Es can be utilized for propulsion or for controlling large scale flows, where needed. | 02-25-2010 |
20100077725 | Piston-jet engine - The mainstream jet engine now is the turbo-jet engine. Here in this invention the turbine is replaced by a piston motor. This will increase fuel efficiency and separating the turning parts from the burning parts will benefit maintenance effort. Unlike traditional turbo-jet engine to use turbines to drive fans and compressors, this invention uses a rotary motor driven by high pressure fluid generated by separate working chambers piston engine to drive fans and compressors | 04-01-2010 |
20100077726 | PLENUM AIR PREHEAT FOR COLD STARTUP OF LIQUID-FUELED PULSE DETONATION ENGINES - A power generation system contains a compressor stage, a pre-burner stage, a combustion stage and a turbine stage. The pre-burner stage heats a portion of flow from the compressor stage to impart a higher temperature within the flow. The heated flow is directed to the combustion stage which contains at least one pulse detonation combustor. Downstream of the combustion stage is a turbine stage. In a further embodiment of the power generation system a fuel is heated prior to the combustion within the combustion stage. | 04-01-2010 |
20100186370 | PULSE DETONATION ENGINE OPERATING WITH AN AIR-FUEL MIXTURE - The invention relates to a pulse detonation engine operating with an air-fuel mixture. According to the invention, the engine ( | 07-29-2010 |
20100205932 | PARTIAL FILLING OF A PULSE DETONATION COMBUSTOR IN A PULSE DETONATION COMBUSTOR BASED HYBRID ENGINE - An engine contains at least one pulse detonation combustor having a combustion chamber and an exit nozzle coupled to and downstream of the combustion chamber. During operation of the at least one pulse detonation combustor a detonation occurs within the combustion chamber and at least one of a fuel fill fraction and purge fraction of the at least one pulse detonation combustor are utilized to offset a temperature peak of said detonation from a pressure peak of said detonation. The fuel fill fraction is defined as 1−purge fraction, and the purge fraction is the ratio of the purge time of the at least one pulse detonation combustor to a sum of the purge time of the at least one pulse detonation combustor and a fuel fill time of the at Least one pulse detonation combustor. | 08-19-2010 |
20100218481 | TWO-PULSE ROCKET MOTOR - In the two-pulse rocket motor in accordance with the present invention, the second propellant is set outside of the first propellant in a motor case, and the inner surface of the first propellant is exposed throughout the almost entire length in the axial direction of the motor case. Therefore, the initial burning area can be secured without deteriorating the performance. Also, by providing a weak part by bonding the barrier membranes or shaping slits on the barrier membrane, the breaking portion of barrier membrane and the behavior of barrier membrane after breakage can be controlled. Further, by setting an igniter charge having higher ignitability and a higher burning rate than the second propellant between the inner surface of the second propellant and the inner barrier membrane, the detachment of barrier membrane and the ignition of the second propellant can be assisted. | 09-02-2010 |
20100229529 | Timing control system for pulse detonation engines - An engine timing input system is described for pulse detonation engines that allows for accurate engine timing when rotary or cylindrical valves are used to distribute an air/fuel mixture for combustion. The invention uses a profile disk having a predetermined circumferential edge corresponding to valve position to provide for accurate engine timing. A frequency wheel is used in conjunction with the profile disk to provide a more accurate representation of valve position by partitioning the valve position into multiple pulses during each rotation of the rotary or cylindrical valve. The profile disk and frequency wheel when used with programmable timing circuitry signal fuel valve timing and ignition relative to the rotating valve. | 09-16-2010 |
20100242435 | HELICAL CROSS FLOW (HCF) PULSE DETONATION ENGINE - A helical cross flow pulse detonation engine. | 09-30-2010 |
20100242436 | MODULATION OF INLET MASS FLOW AND RESONANCE FOR A MULTI-TUBE PULSE DETONATION ENGINE SYSTEM USING PHASE SHIFTED OPERATION AND DETUNING - An engine contains a compressor stage, a plurality of pulse detonation combustors and a plurality of inlet valves, where the inlet valves direct a mass flow into the pulse detonation combustors. A control system controls at least one of a phase shift, firing frequency and a τ | 09-30-2010 |
20110030340 | PULSE DETONATION ENGINE - According to the invention, the said engine (I), which comprises at least one flame tube ( | 02-10-2011 |
20110047961 | PULSE DETONATION INLET MANAGEMENT SYSTEM - A pulse detonation combustor valve assembly is provided that includes a fixed valve portion having an inlet and a reciprocating valve portion. The valve assembly is coupled to a pulse detonation combustor. The reciprocating valve portion is exterior to the fixed valve portion and coaxially aligned with the fixed valve portion. The reciprocating valve portion is arranged to reciprocate with respect to the fixed valve portion to control inlet flow through the inlet of the valve assembly. | 03-03-2011 |
20110047962 | PULSE DETONATION COMBUSTOR CONFIGURATION FOR DEFLAGRATION TO DETONATION TRANSITION ENHANCEMENT - According to one aspect of the invention, a pulse detonation combustor chamber is provided having an ignition chamber and a detonation chamber. The cross-sectional area of the ignition chamber is greater than the cross-sectional area of the detonation chamber. A flame is generated in the ignition chamber upon ignition of a flammable mixture. The flame flows into the detonation chamber and detonates within the detonation chamber. | 03-03-2011 |
20110088370 | PULSED DETONATION ENGINE - According to the invention, the engine (I) includes a means for supplying fuel to the combustion chamber ( | 04-21-2011 |
20110126510 | PULSE DETONATION COMBUSTOR - In one embodiment, a pulse detonation combustor includes a gas discharge annulus including multiple nozzles engaged with one another via mating surfaces to support the gas discharge annulus in a circumferential direction. The pulse detonation combustor also includes multiple pulse detonation tubes extending to the nozzles. | 06-02-2011 |
20110146232 | CONTROL SYSTEM FOR A PULSE DETONATION TURBINE ENGINE - A pulse detonation turbine engine (PDTE) includes at least one controllable multi-tube pulse detonation combustor (PDC) configured to initiate firing of one or more pulse detonation tubes in response to operation of a plurality of controllable peripheral PDC components to regulate PDTE output characteristics. A control system including a programmable controller directed by algorithmic software operates to generate control inputs for the plurality of controllable peripheral PDC components in response to PDTE input conditions, such that one or more PD tube controllable inputs can be different for at least one PD tube relative to another PD tube within the multi-tube PDC, and further such that detonation timing can be different for at least one PD tube relative to another PD tube within the multi-tube PDC. | 06-23-2011 |
20120079806 | PULSE DETONATION TUBE WITH LOCAL FLEXURAL WAVE MODIFYING FEATURE - In one embodiment, a pulse detonation tube includes a continuous base tube having a substantially uniform wall thickness. The pulse detonation tube also includes a local flexural wave modifying feature configured to locally vary a flexural wave speed such that the flexural wave speed through the pulse detonation tube is different than an expected detonation wave speed, and/or to locally dissipate flexural wave energy. | 04-05-2012 |
20120102916 | Pulse Detonation Combustor Including Combustion Chamber Cooling Assembly - A pulse detonation combustor including a combustion chamber and a cooling assembly circumscribing the combustion chamber. The cooling assembly is configured to provide a flow of cooling fluid therethrough and provide cooling of the combustion chamber. The cooling assembly includes a cooling flow sleeve positioned about the combustion chamber. The cooling flow sleeve includes a plurality of circumferentially spaced apart axially extending structural members defining a plurality of flow passages therebetween. The cooling assembly is configured mechanically and thermally separate from the combustion chamber and provides axisymmetric cooling to the combustion chamber. | 05-03-2012 |
20120144798 | FLUIDIC DEFLAGRATION-TO-DETONATION INITIATION OBSTACLES - A detonation chamber and a pulse detonation combustor including a detonation chamber, wherein the detonation chamber includes a plurality of aerodynamic jets disposed adjacent an exterior of a sidewall of the detonation chamber. The detonation chamber further includes a plurality of openings formed in the sidewall of the detonation chamber, wherein each of the plurality of openings is in fluidic communication with one of the plurality of aerodynamic jets. The plurality of aerodynamic jets are adapted to create a plurality of jet flows of a fluid within the detonation chamber during a combustion cycle defining a plurality of initiation obstacles within the detonation chamber to enhance a turbulence of a fluid flow and flame acceleration through the detonation chamber. | 06-14-2012 |
20120192545 | Pulse Detonation Combustor Nozzles - The present application provides a pulse detonation engine. The pulse detonation engine may include a number of pulse detonation combustors. Each of the pulse detonation combustors may include a combustion tube and a nozzle assembly. The nozzle assembly of one or more of the pulse detonation combustors may include a diffuser therein. | 08-02-2012 |
20120311993 | MULTI-PULSE ROCKET MOTOR AND PULSE UNIT THEREOF - A pulse unit of a multi-pulse rocket motor has: a propellant in an internal-burning type or internal-end-burning type shape that is loaded within a motor case; an igniter arranged at an end surface of the propellant; a barrier membrane arranged to cover a whole of an initial burning surface of the propellant and the igniter; a forward joint arranged at a forward end of the motor case; and a rearward joint arranged at a rearward end of the motor case. The forward joint is formed so as to be connectable with the rearward joint of another pulse unit. The rearward joint is formed so as to be connectable with the forward joint of still another pulse unit. | 12-13-2012 |
20130042595 | PULSE DETONATION COMBUSTOR WITH PLENUM - A pulse detonation combustor includes at least one plenum located along the length of the pulse detonation combustor. The plenum can be located: 1) proximate an air valve; 2) between a fuel injection port and an ignition source; 3) downstream of both the fuel injection port and the ignition source; and 4) proximate an exit nozzle of the pulse detonation combustor. In addition, the pulse detonation combustor can have multiple plenums, for example, proximate the air valve and proximate the exit nozzle. The location and dimensions of the plenum can be selectively adjusted to control mechanical loading on the wall, the velocity of fluid flowing within the combustor, and the pressure generated by the pulse detonation combustor. | 02-21-2013 |
20130081376 | Pulse Detonation Engine with Variable Control Piezoelectric Fuel Injector - A pulse detonation engine including one or more fuel injectors comprising one or more piezoelectric driving stacks wherein a flow control member of each injector is driven directly by the one or more piezoelectric stacks without additional amplification means or interposing elements while a flow area of the nozzle is variably adjustable to deliver controlled flow rates in a desired flow profile to improve engine performance and reduce emissions. The pulse detonation engine configured to support variable mission and operational requirements including delivery of required thrust using specific fuel types and with power and performance of the pulse detonation engine variably adaptable. The fuel injectors associated with the pulse detonation engine configure to deliver specified flow rates with minimal linear movement of the flow control member. The injector and drive electronics configured to deliver higher frequency operation and response with increased operational stability. | 04-04-2013 |
20130145746 | VORTEX CANNON WITH ENHANCED RING VORTEX GENERATION - A vortex cannon based on pulse detonation engine comprises a combustion chamber, a fuel source, an oxidizer source, a purge gas source, a valve allowing delivery of fuel from the fuel source to the combustion chamber, a valve allowing deliver of either oxidizer or purge gas from the oxidizer and purge gas sources to the combustion chamber, an ignition source for the combustion chamber for initiating detonation of fuel and oxidizer, and a conical barrel outlet from the combustion chamber. The combustion chamber is configured for control over the detonation front. A control system provides for varying the rate and quantity of fuel and oxidizer injected to the combustion chamber for varying the frequency and strength of pulse generation. Ring vortices may be generated either in single pulses or at high rates of fire which maintain a consistent track. | 06-13-2013 |
20160025040 | GAS DYNAMIC VALVE - A flow-management system may comprise a center body impermeable to air. A conical surface of the center body may face forward. A blocking surface of the center body may be coaxial with the conical surface and may comprise an annular recess. An annular ring may be aft of the center body and fluidly coupled with the blocking surface. A tube may encase the center body and annular ring. The annular ring may comprise an air-foil shape to direct a pulse to the blocking surface. The blocking surface may comprise a central peak and a circular ridge separated by the annular recess. | 01-28-2016 |
20160053723 | ENGINE PROPULSION SYSTEM - An engine propulsion system is configured to utilize bursts of pressurized media in order to transmit mechanical energy. The engine propulsion system includes at least one cannon, wherein each cannon is configured to displace the pressurized media and further includes a firing pin casing configured to accommodate a firing pin. The firing pin is configured to transmit the mechanical energy when moved thus allowing the media to exit the cannon. | 02-25-2016 |
060248000 | Air bypass passage | 2 |
20090031701 | LIQUID COINJECTOR - A liquid coinjector is disclosed which includes a main body having an upstream pipe defining an inlet flow channel in fluid communication with a chamber portion of the body, a downstream pipe defining an outlet flow channel in fluid communication with the chamber portion, and a merging pipe in fluid communication with the chamber portion. A flexible tube supported is in the inlet flow channel of the upstream pipe. The flexible tube facilitates fluid flow from the upstream pipe to the chamber portion. At least one pressing part is positioned adjacent to the flexible tube. The at least one pressing part is movable from a first position to a second position to compress the flexible tube and close the inlet flow channel. | 02-05-2009 |
20110126511 | THRUST MODULATION IN A MULTIPLE COMBUSTOR PULSE DETONATION ENGINE USING CROSS-COMBUSTOR DETONATION INITIATION - A method and apparatus for modulating the thrust during a flight envelope of a multiple combustor chamber detonation engine using cross-combustor chamber detonation initiation are provided. The detonation combustor chambers are filled with a combustible mixture of fuel and oxidizer. The combustible mixture in one of the detonation combustor chambers is ignited by an ignition source, and the remaining detonation combustor chambers are ignited by detonation cross-firing via connectors. A controller controls the ignition source and the supply of oxidizer and fuel to the detonation combustor chambers to modulate the thrust of the engine during the flight envelope. | 06-02-2011 |
060249000 | Aerodynamic valve | 3 |
20100126140 | MILLIMETRE-SCALE ENGINE - A millimetre-scale pulse jet engine comprises an engine body that defines a combustion chamber, a fuel, an air intake, and an exhaust. The fuel inlet is arranged to inject fuel directly into the combustion chamber. The air intake and the exhaust are in fluid communication with the combustion chamber, and the combustion chamber is configured such that air from the air intake and fuel from the fuel inlet cyclically combust in the combustion chamber to produce exhaust gases. | 05-27-2010 |
20110302908 | MULTITUBE VALVELESS PULSE DETONATION ENGINE - Disclosed herein is a valveless multitube pulse detonation engine including: a plurality of detonation tubes, wherein each detonation tube comprises an independent discharge outlet, and the plurality of detonation tubes interconnected at a common air/fuel mixture intake port. In the disclosed engine, an air and fuel mixture is detonated in the detonation tubes simultaneously, and the common air/fuel mixture intake port minimizes back-pressure caused by detonating the air/fuel mixture by directing multiple reverse shock waves into one another and effectively using the back-pressures as reacting surfaces for one another and effectively reducing the effect of back flowing shock waves moving towards upstream. The detonation tubes may be non-linear, and may have independent discharges. The independent discharges may be coupled to an adapter nozzle terminating in a combined exhaust outlet. | 12-15-2011 |
20120192546 | Catalytic Converter for a Pulse Detonation Turbine Engine - The present application provides a pulse detonation turbine engine. The pulse detonation turbine engine may include one or more pulse detonation combustors to produce a flow of combustion gases, a turbine positioned downstream of the pulse detonation combustors such that the flow of combustion gases drives the turbine, and a catalytic converter positioned downstream of the pulse detonation combustors such that the flow of combustion gases passes therethrough. | 08-02-2012 |