Abstract: A cooking device includes a frame forming a cooking chamber; a door opening and closing the cooking chamber; a burner cover disposed in the cooking chamber; and a burner located in the burner cover, the burner generating a flame, wherein the burner cover is provided with a first hole providing a path through which air flows, and the frame is provided with a second hole communicating with the first hole, the second hole providing a path through which the air flows.

Abstract: A cooking device includes a frame forming a cooking chamber; a door opening and closing the cooking chamber; a burner cover disposed in the cooking chamber; and a burner located in the burner cover, the burner generating a flame, wherein the burner cover is provided with a first hole providing a path through which air flows, and the frame is provided with a second hole communicating with the first hole, the second hole providing a path through which the air flows.

Abstract: A pulse combustor system for efficiently operating a pulse combustor. The pulse combustor system includes the pulse combustor and a duct. The pulse combustor has a combustion chamber defining an internal space, a conduit having a first end in fluid communication with the internal space and a second end in fluid communication with an environment outside of the pulse combustor system, and a fuel injector configured to inject fuel into the internal space of the combustion chamber. The duct has two openings, with one opening disposed adjacent to the second end of the conduit. The pulse combustor system has an average operating frequency, and the duct has a length that is about one quarter of a wavelength corresponding to the average operating frequency. The pulse combustor and the duct each has a central longitudinal axis, and the two axes are substantially aligned.

Abstract: A cooking device includes a frame forming a cooking chamber; a door opening and closing the cooking chamber; a burner cover disposed in the cooking chamber; and a burner located in the burner cover, the burner generating a flame, wherein the burner cover is provided with a first hole providing a path through which air flows, and the frame is provided with a second hole communicating with the first hole, the second hole providing a path through which the air flows.

Abstract: A hybrid jet engine, including a front cowling having a tubular shape, a rear cowling having a tubular shape and connected to the front cowling, a central core disposed within the front cowling and the rear cowling, a shaft disposed longitudinally within the central core, a plurality of main fan blades disposed at a first end of the shaft at the front cowling, a plurality of auxiliary fan blades disposed at a second end of the shaft at the rear cowling, at least one aerodynamic stabilizer disposed on a surface of the central core to extend therefrom, and at least one Tesla one way valve disposed on the surface of the central core to receive the ram air and to provide the ram air to the plurality of auxiliary fan blades.

Abstract: A pulse combustor system for reducing noise and/or vibration levels. The system includes a pulse combustor including a combustion chamber, an inlet pipe, an exhaust pipe, and a first fuel injector for injecting fuel into the combustion chamber. The pulse combustor has a fundamental oscillation mode and one or more additional oscillation modes. The system includes at least one pressure sensor for measuring a pressure inside the fuel combustor and/or a at least one fluid velocity sensor for measuring fluid velocity at the inlet pipe or at the exhaust pipe. A controller adjusts a rate of fuel supply to the pulse combustor if the measured pressure and/or the measured velocity is above a predetermined threshold value to reduce excitation of the one or more additional oscillation modes.

Abstract: A cooking device includes a frame forming a cooking chamber; a door opening and closing the cooking chamber; a burner cover disposed in the cooking chamber; and a burner located in the burner cover, the burner generating a flame, wherein the burner cover is provided with a first hole providing a path through which air flows, and the frame is provided with a second hole communicating with the first hole, the second hole providing a path through which the air flows.

Abstract: 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.

Abstract: The present specification generally relates to improvements to combustors such as burners and engines. In one aspect, the specification presents an acoustically enhanced ejector system which can be used as part of an intake system for a combustor. In another aspect, the specification teaches the use of a combustor combustion chamber as an oscillator to magnify a harmonic frequency of a pulsating frequency of the combustor. In still other aspects, the specification presents a combustion chamber having an inlet with a plurality of tangentially spaced apertures, and an in-line intake system connected to the apertures.

Abstract: In one embodiment, a pulse detonation engine includes a resonator configured to fluidly couple to an air flow path upstream of a pulse detonation tube. The pulse detonation engine also includes a controller configured to receive signals indicative of an operating frequency of an air valve disposed at an upstream end of the pulse detonation tube, and to adjust a geometric configuration of the resonator in response to the signals.

Abstract: 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.

Abstract: Improvements to combustors such as burners and engines are provided. In one aspect, the specification presents an acoustically enhanced ejector system which can be used as part of an intake system for a combustor. In another aspect, the specification teaches the use of a combustor combustion chamber as an oscillator to magnify a harmonic frequency of a pulsating frequency of the combustor. In still other aspects, the specification presents a combustion chamber having an inlet with a plurality of tangentially spaced apertures, and an in-line intake system connected to the apertures.

Abstract: 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.

Abstract: A dual mode combustor of a gas turbine engine contains at least one dual mode combustor device having a combustion chamber, a fuel air mixing element, a high frequency solenoid valve and a fuel injector. During a first mode of operation the dual mode combustor device operates in a steady, constant pressure deflagration mode, receiving its fuel from the fuel injector. In a second mode of operation the dual mode combustor device operates in a pulse detonation mode, receiving its fuel from the high frequency solenoid valve.

Abstract: Pulse detonation combustors of valveless construction. One valveless pulse detonation combustor, having a tube with a closed end and an open end, is constructed with a flame accelerator within the tube, adjacent the open end. A valveless, apertured flow restrictor is positioned between the flame accelerator and the closed end of the tube. A sparking device is positioned within the tube, between the flow restrictor and the flame accelerator. Valveless fuel and air ports are positioned between the flow restrictor and the closed end of the tube. Substantially right-angle manifold passageways are in communication with each of the ports.

Abstract: 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.

Abstract: The present invention provides a statically starting and operating ramjet engine system. The system includes a pumping ejector coupled to a ramjet engine upstream of the ramjet inlet. A subsonic converging nozzle is placed in fluid communication between the pumping ejector and ramjet inlet. The pumping ejector ejects a primary fluid into the ramjet inlet to entrain a secondary fluid and create a mixed flow with sufficient momentum and internal energy to achieve characteristic speed. The converging nozzle provides a characteristic cross section necessary for the mixed flow to achieve characteristic speed as it moves through the nozzle, thereby producing a standing shock wave at the point of maximum convergence of the nozzle and creating sonic conditions at the inlet of the ramjet engine.

Abstract: A two-stage pulse detonation system includes a pre-combustor and a geometric resonator connected via a converging-diverging nozzle to the pre-combustor to create a high temperature and high pressure conditions in the resonator in order to create optimal conditions for detonation initiation. A mixture of a fuel and a gas is burned in the pre-combustor and is passed through the nozzle into the geometric resonator, where the burned mixture is detonated. The detonation propagates through the resonator exit nozzle thus generating thrust.

Abstract: A pulse combustion device has a number of combustors with upstream bodies and downstream nozzles. Coupling conduits provide communication between the combustors. For each given combustor this includes a first communication between a first location upstream of the nozzle thereof and a first location along the nozzle of another. There is second communication between a second location upstream of the nozzle and a second communication between a second location upstream of the nozzle of a second other combustor and a second nozzle location along the nozzle of the given combustor.

Abstract: A pulse detonation engine (10) is provided with an aerovalve (14) for controlling the pressure of injected propellants (Ox, Fuel) in an open-ended detonation chamber (26). The propellants are injected at such pressure and velocity, and in a direction generally toward a forward thrust wall end (16) of the detonation chamber (26), an aerovalve (14) is formed which effectively inhibits or prevents egress of the propellant from the detonation chamber (26). A shock wave (34) formed by the injected propellant acts, after reflection by the thrust wall end (16) and in combination with the aerovalve (14), to compress and conserve, or increase, the pressure of the injected propellant. Carefully timed ignition (28) effects a detonation pulse under desired conditions of maintained, or increased, pressure. Termination of the propellant injection serves to “open” the aerovalve (14), and exhaust of the combusted propellants occurs to produce thrust.

Abstract: The present invention reveals a method and apparatus for more efficiently injecting a primary fluid flow in a fluid ejector used to pump lower velocity fluid from a secondary source. In one embodiment, the primary fluid flow is a pulsed or unsteady fluid flow contained within an inner nozzle situated within a secondary flow field. This secondary fluid flow is bounded within the walls of an ejector or shroud. The secondary and primary fluid flows meet within the ejector shroud section wherein the secondary fluid flow is entrained by the primary fluid flow. The geometry of the ejector shroud section where the primary and secondary fluids mix is such as to allow the beginning of primary injector pulse to be synchronized with an acoustic wave moving upstream through the ejector initiated by the exiting of the previous pulse from the ejector shroud. The ejector's geometric properties are determined by the acoustic properties, frequency, duty cycle, and amplitude, of the pulsed primary fluid flow.

Abstract: A self-starting, self-aspirating valveless jet engine comprising a combustor tube, a multiple tube intake duct, a flame holder, and a fuel supply means. High throttle capability has been achieved through the use of an intake duct consisting of multiple tubes, the intake duct being located on a common longitudinal axis with the combustor tube, and the inlet mouth of each intake tube in the intake duct facing forward in the direction of flight. A unique intake duct design succeeds in blocking all backflow of combustion gases during the combustion cycle, permitting the intake duct to be mounted facing the direction of flight. Intake tube inlet mouths that face forward in the direction of flight, maximize capture of ram air during flight, providing more air in the fuel to raise the fuel feed rate with a resulting increase in thrust. Blocking of all backflow gases increases thrust in another way, by increasing the buildup of pressure in the combustion chamber during the combustion process.

Abstract: A miniture liquid-fueled turbojet engine for powering remote control model aeroplane or light pilotless aircraft includes a plural number of tiny pressure-swirl type atomizers for thoroughly atomizing liquid fuel and a V-gutter flame holder. High combustion efficiency and satisfactory outlet temperature pattern factor can be obtained in the present combustion system of the engine. This is because the system possesses the characteristics such as fine spray of liquid fuel, long residence time of fuel droplets, efficient flame holding mechanism and good mixing in the dilution region. As a result, safety and maneuverability of the present engine can be enhanced in comparison with the engines of prior art.

Abstract: A self starting valved pulse jet particularly adapted to power pilotless aircraft in the subsonic speed range. This invention is somewhat related to my U.S. Pat. No. 3,823,554. The device continues to utilize a substantially cylindrical combustion chamber, a reduction cone and exhaust tube. The multiplicity of reverse flow air and fuel inlet tubes projecting through the reduction cone into the combustion chamber have been modified so each air and fuel inlet utilizes two tubes axially aligned with each other. The aft tube diameter is less than the forward tube. An opening between the tubes permits gas to flow to and from an annular plenum chamber surrounding the air inlet tubes. The plenum chamber also houses an equal number of shrouded valve assemblies in its outer wall. The small aft tube of the air and fuel inlet secures and penetrates through the aft annular wall of the plenum chamber.

Abstract: A thermally driven gas resonance device includes a resonance tube (3) which expands in cross-section along its length from one end to the other, a heat source (2) located at the one end of the resonance tube, and an igniter (14) to trigger oscillations in a gas in the tube. The heat source (2) is preferably a pulsed heat source having a repetition frequency corresponding to a resonant frequency of the gas tube (3). The mechanical energy produced in the oscillating gas may be used to operate a pressure swing gas separator by including a bed (16) of molecular sieve material in the other end of the tube (3). Alternatively, the mechanical energy may be used to drive a heat pump (19). In this case a heat sink (21) is located at the other end of the tube (3), a regenerator (20) is also located adjacent the other end, and ports (8) on the side of the regenerator (20) towards the heat source (2) effect heat exchange between the gas in the resonance tube (3) and a source of low grade heat.

Abstract: Combustion supporting air in the resonator tube of a pulse jet engine is cyclically compressed by combustion and discharged through a decelerating passage of a diffuser in a tail section of the engine to internally pressurize an afterbody preceding atmospheric dishcarge of the combustion products through nozzle passages, followed by primary refill with air from the pressurized afterbody and secondary refill by reentry of external air. The nozzle passages are formed in angularly spaced, rearwardly diverging vane formations of the tail section projecting from a protective casing directing ram air intake into orifice openings formed in a rear end portion of the diffuser to regulate afterbody pressurization under control of ram pressure created by forward propulsion of the engine.

Abstract: A device for controlling the rate of fuel generation in a solid fuel ramjet ngine having a translating tube within the fuel grain and air inlet for continuously changing the distribution of air over the fuel grain in response to air mass flow. The distribution of air effects the aerodynamic shear interaction between the air and solid fuel which causes a change in burn rate.

Abstract: The physical size of an inlet plenum (2) for a cluster of pulse combustors (1) may be reduced while maintaining a tuned condition for noise cancellation by constructing the plenum with an annular chamber (8) having internal baffles (20, 21) which make the acoustic path length through the annular plenum (2) substantially larger than its circumference.

Abstract: A thrust augmenting fluid rectifier for a pulsed combustor comprising ducting having a converging inlet section, a flow redirecting section and a diffuser section, the inlet of the ducting being spaced upstream from the combustor inlet to define a thrust augmentor utilizing the backflow from the combustor inlet as primary fluid. In one embodiment the rectifier ducting extends rearwardly to a chamber that combines it with the combustor outlet. Substantial pressure gain is obtainable making the invention suitable for gas turbine applications.