41results about "Intermittent jet plants" patented technology

A system and method are disclosed for improving fuel-air mixing in the combustion chamber of pulse combustors by deflecting the pressurized fuel injected from the one or more fuel injectors at a predetermined angle towards the centerline longitudinal axis of the combustion chamber.

The invention relates to the technical field of engines, and discloses a turbine-based combined cycle engine operation method and a turbine-based combined cycle engine, and the turbine-based combined cycle engine operation method comprises the steps that a pulse detonation combustion mode is adopted in a pure turbine mode; a rotary detonation combustion mode is adopted in a pure stamping mode; a pulse detonation combustion mode is adopted in the transition mode, and meanwhile, a rotary detonation combustion mode is adopted. By utilizing the advantages of self-pressurization and high unit thrust of pulse detonation combustion, the high-speed performance is improved, and the working Mach number upper limit of a pure turbine mode is widened; by utilizing the advantages of high combustion speed, high combustion efficiency, simple structure and short length of rotary detonation combustion, the lower limit of the working Mach number of a pure stamping mode is widened. And in the transition mode, the characteristics of a pure turbine mode and a pure stamping mode are achieved at the same time, and enough thrust is provided for the aircraft.

The invention belongs to the technical field of aviation aircrafts, and particularly relates to a hybrid power engine and an aviation aircraft. The invention provides a hybrid power engine which comprises a detonation combustion chamber, a center shaft and a power generation assembly, the power generation assembly comprises a stator, an outer rotor and fourth permanent magnets, the stator is hinged to the center shaft, the outer rotor is of an annular structure, a plurality of first grooves are formed in the annular outer wall of the outer rotor, and the fourth permanent magnets are embedded in the first grooves; the fourth permanent magnet is matched with the stator for power generation; the detonation combustion chamber is arranged in the outer rotor and drives the outer rotor to rotate; the center shaft is provided with an energy storage part, and the power generation assembly is electrically connected with the energy storage part. The invention further provides an aviation aircraft comprising the hybrid power engine. According to the engine, the detonation combustion chamber combusts to drive the outer rotor to rotate to generate electricity, redundant power of the detonation combustion chamber generates electricity through the power generation assembly and then is stored in the energy storage part, waste of redundant energy is avoided, and the energy storage part can also be used for providing driving power.

The present disclosure is directed to a supersonic oblique rotating detonation wave engine (SORDE) and systems and methods for generating a supersonic oblique rotating detonation wave. The SORDE is configured to produce and sustain a supersonic oblique rotating detonation wave through the injection of fuel at supersonic speeds into an inlet air flow between Mach 1 and Mach 7. The SORDE and method include injecting fuel into the inlet air in an amount to generate an equivalence ratio of 0.2 to 2.5. Some embodiments include a plurality of fuel injector ports each having a diameter of about 0.010 inches to about 0.040 inches; an annular wedge disposed in or upstream of the detonation chamber with an angle of about 5 degrees to about 40 degrees relative to a longitudinal axis of the engine; and / or a cylindrical center body disposed in or upstream of the detonation chamber.

A method of operating a rotating detonation combustor includes providing a flow of air through an air inlet to flow into a detonation chamber, providing a flow of fuel from at least one fuel injector into the detonation chamber, mixing the flow of the fuel and the flow of the air in the detonation chamber to generate a fuel-air mixture, detonating the fuel-air mixture in the detonation chamber to generate rotating detonation waves within the detonation chamber, and controlling, during operation of the rotating detonation combustor from a first power operating state to a second power operating state, different from the first power operating state, the air inlet wall to control the flow of the air through the air inlet into the detonation chamber to control a discharge coefficient and an operating mode within the detonation chamber.

The invention provides an air inlet method, a detonation engine using the method and a rotary detonation engine, and the air inlet method comprises the steps that fuel is injected to the downstream area of a combustion device through a fuel nozzle to form a jet flow curtain, and the jet flow curtain and the combustion device are enclosed to form a closed space or a semi-closed space; the closed space or the semi-closed space is injected through the jet flow curtain, so that the closed space or the semi-closed space circularly reciprocates to form a low-pressure state to realize high-frequency air inlet; according to the detonation engine and the rotary detonation engine using the air inlet method, fuel is injected through the fuel nozzle to form a jet flow curtain, the jet flow curtain, the combustion chamber and the reflector define a closed space or a semi-closed space, and injection is conducted on the closed space or the semi-closed space through the jet flow curtain; and the closed space or the semi-closed space circularly reciprocates to form a low-pressure state so as to realize high-frequency air intake. The invention can be applied to the fields of power propulsion and rotation torque generation.

The invention relates to the technical field of aero-engines, and discloses a center detonation type oblique detonation engine which comprises a fuel injection supporting plate and a detonation supporting plate, the fuel injection supporting plate is erected and fixed in a combustion chamber, and a plurality of first reverse jet holes are formed in the end face, directly facing an air inlet channel, of the fuel injection supporting plate; a plurality of fuel injection holes are formed in the end face, back to the gas inlet channel, of the fuel injection supporting plate, and a first gas conveying flow channel and a fuel conveying flow channel are formed in the fuel injection supporting plate; the detonating supporting plate is erected and fixed in the combustion chamber and is parallel to the fuel injection supporting plate, and a plurality of second reverse jet holes are formed in the end face, directly facing the fuel injection holes, of the detonating supporting plate; the detonation supporting plate is arranged to replace an original wedge face, the detonation supporting plate and the fuel injection supporting plate both adopt reverse jet flow for thermal protection, arch shock waves formed through induction of the reverse jet flow play a role in intensifying detonation, meanwhile, oblique detonation waves are located in the center for detonation, and separation of a boundary layer of the lower wall face cannot be caused.

The invention relates to the technical field of engines, in particular to a hydrogen fuel detonation hybrid electric engine, an aircraft and a using method. A hydrogen fuel detonation hybrid electric engine includes: a hydrogen fuel cell; the gas compression assembly is connected with the hydrogen fuel cell through a line, and the gas compression assembly is used for compressing the environment gas into compressed air; and the detonation chamber is connected with the air compression assembly through a pipeline, compressed air and hydrogen flow in the detonation chamber, and the compressed air and the hydrogen are combusted in the detonation chamber to generate detonation waves. The invention provides a hydrogen fuel detonation hybrid electric engine, an aircraft and a using method, and aims to solve the problems that thrust is generated by high-temperature tail gas and compressed air generated by a hydrogen fuel cell of the hybrid electric engine, and the tail gas generated by the fuel cell is low in temperature, difficult to generate large thrust and difficult to adapt to the power requirement of the aircraft.

The invention discloses a valveless pulsating jet engine with an oval air inlet channel. The valveless pulsating jet engine is composed of a combustion chamber, the air inlet channel, a tail pipe, an oil nozzle and the like. An engine air inlet channel is of an oval flow channel structure, the air inlet channel and a tail pipe are arranged on the rear wall face of a combustion chamber, an oil nozzle is arranged on the rear half portion of the combustion chamber, and a nozzle directly faces an air inlet. The air inlet channel has the advantages that under the constraint of the limited engine section size, a circular flow channel is changed into an oval flow channel by changing the structural form of the air inlet channel, the air inlet amount of an engine is effectively increased, and therefore the thrust of the engine is improved.

A system and method for ram air intake for pulse combustion systems is disclosed that improves the ability of pulse combustions to ingest air into the inlet pipe when the pulse combustion system is moving in a direction opposite the direction the open end of the inlet pipe is facing and the system and method includes the ability to increase the thrust output from the pulse combustion system.

The invention relates to the technical field of aero-engines, and discloses a pulse detonation turbine engine which comprises an air inlet assembly, a supercharging assembly, a combustion chamber casing, a pulse detonation combustion chamber, a nozzle assembly, a transition assembly and an exhaust assembly. The first end of the pulse detonation combustion chamber is provided with a first channel and a second channel, and the second end is provided with a first exhaust channel and extends outwards from the combustion chamber casing. A two-way channel is formed between the combustion chamber casing and the pulse detonation combustion chamber, and the two-way channel is communicated with the first channel; the transition assembly is arranged at the end, close to the exhaust direction, of the pressurization assembly and communicates with the second channel. The two channels are formed between the pulse detonation combustion chamber and the combustion chamber casing, the intensity of return detonation can be effectively weakened through the cavity effect of the two channels, and then the return pressure faced by the pressurization assembly is reduced; meanwhile, after air enters the two channels through the pressurizing assembly, the wall face of the pulse detonation combustion chamber can be cooled.

A system and method are disclosed for improving fuel-air mixing in the combustion chamber of pulse combustors by deflecting the pressurized fuel injected from the one or more fuel injectors at a predetermined angle towards the centerline longitudinal axis of the combustion chamber.

The engine comprises a detonation chamber (8) for mixture combustion, a mixer (2) to receive oxygen, water vapor and fuel with a combustion rate greater than 1 meter per second, with which to form a mixture and distribute the mixture in the detonation chamber (8), a one-way valve (9) with orifices configured for mixture distribution in the detonation chamber (8), including ferromagnetic spheres (14) free to vibrate to open and close the mixture passage, an exhaust nozzle (4) of convergent-divergent configuration capable of expelling flue gases at supersonic speeds, a high-voltage circuit, a plurality of spark plugs (3) ignited by the high-voltage circuit, a gas NOx elimination circuit, a needle turbine (6), a water injection system, a fuel injection system, a control circuit for motor management and sensors for monitoring operating conditions.

To solve the problems of the complex structure of the mechanical valve type reverse transmission suppression mechanism of the air-breathing pulse detonation engine and the difficulties in valve driving and opening / closing control, the present invention proposes a pulse detonation combustion chamber with an air guiding device and an air-breathing pulse detonation engine. On the basis of the traditional pulse detonation combustion chamber, an air guiding transmission device and a transmission spring for rebounding and resetting the air guiding transmission device when it is depressurized are added to each detonation combustion device. Each air guiding transmission device is driven by a part of the energy gas led out from its corresponding detonation combustion device, compresses the transmission spring and generates an axial displacement; the output ends of all the air guiding transmission devices are cooperatively connected with the mechanical rotary valve, and convert their axial displacements into the circumferential rotation of the mechanical rotary valve. The present invention can adaptively realize the oncoming flow filling and reverse transmission isolation, without additionally arranging a driving motor, a signal acquisition unit and a motor control unit for the valve, and has a simpler structure, lower cost and higher reliability.

The application provides a knock engine, comprising: a knock power unit comprising at least two knock chambers and a transmission member, each knock chamber being provided with a reciprocating piston; one end of the transmission member being in transmission connection with a compressor, and the other end of the transmission member being connected with the pistons in the at least two knock chambers respectively, so that when the at least two knock chambers are ignited, the transmission member is driven to move through the pistons, and the compressor is driven to work; the compressor being in communication with the at least two knock chambers, and being used for providing compressed air to the at least two knock chambers. The reverse transmission energy of the knock chamber is directly utilized to drive the compressor through the piston-transmission shaft mechanism, so that the traditional turbine component is completely omitted. This fundamentally avoids the inherent contradiction that the turbine efficiency is low due to the difficulty in matching between the intermittent and non-steady-state work of the knock combustion chamber and the continuous and steady work of the turbine. The turbine is omitted, the engine structure is simplified, the manufacturing cost and the maintenance difficulty are reduced, and the working reliability of the engine is improved.

The application relates to the field of aerospace propulsion technology, and discloses a multi-mode cluster shock-absorbing pulse detonation engine with intelligent gap control; the engine comprises multiple explosion tube bodies in a concentric circle layout, a hydraulic sealing system, a fuel supply system, an electric arc igniter, an integrated thermal management system and an intelligent control system. The core lies in: the sealing reliability is ensured through intelligent dynamic gap control; a wide-range flight is adapted through multi-mode gas supply; precise ignition control is realized through multi-sensor fusion; waste heat is recycled and thrust gain is generated through integrated thermal management; and vibration and noise are inhibited through cluster detonation interference with a specific layout. The application has the dual-mode intelligent switching capability of high-frequency large thrust and low-frequency high efficiency, integrates health monitoring, and forms an advanced propulsion system solution scheme with high reliability, wide-range self-adaptation and low vibration.

A diffuser (300) may comprise an inlet (310) and an outlet (340). The inlet may comprise an arcuate shape. The outlet may comprise an annular shape. The diffuser may transition from the arcuate shape at the inlet to the annular shape at the outlet. The diffuser may comprise a radially inner wall (320) and a radially outer wall (330) disposed opposite the radially inner wall. The radially inner wall and the radially outer wall may partially define a duct.

A flywheel assembly and hoist mechanism for powering an electrical generator including a housing, a flywheel assembly positioned in the housing, a flywheel path defined for the flywheel assembly in the housing, and a hoist mechanism aligned with the flywheel path. The flywheel path is configured in such a configuration that the flywheel is returned to its point of origin with a hoist mechanism. The flywheel assembly positions at the top of the flywheel path and rotates along a downward path of the flywheel path. The flywheel assembly descends while rotating along the downward path. The rotational speed of the flywheel increases quadratically as it accelerates along the flywheel path and stores kinetic energy, which is then converted into electricity. The hoist mechanism receives the flywheel assembly and lifts the flywheel assembly back to the top of the flywheel path for continuous operation.

The present invention relates to a Flywheel Engine utilizing Flywheel with Peripheral Multiple Expanding Chambers, powered by Energies generation, each of which are used, for accommodate one or more: Compressed Air, Hydrogen / generation, Water, Steam / generation, Energies Storage and Energies Supplies (CAHWSESES), creates combinations of Energies Supplies. When combining mixing of Pressurized Air and Water suppling Aeration water, integrated in hot W ater / Solar Steam generation apparatuses, used for storing solar electricity or from grid electricity, moreover, combined with high pressure Air and Residual heat integrate Compressed Air with Residual. Water, Hydrogen generation, using Solar PV electric and Solar Thermal energies. An innovative breakthrough technology, where the energies are channeled into peripheral expanding- chambers, combined with fluid jets attached to a flywheel (CAHWS), and integrate with Electric Generator / Alternator, as well as mechanical energy output, which multiplying the energies that is exist / supplied today in the world market, defined as energies supplied from Energies Storage systems and generate various electricity and hot water generation system (e.g. about 2 times and more). Moreover, innovative Energies Storage and Energies Supplies with all mechanical systems have a lifespan of at least, 2 generations with the price lower than acid / salt batteries or lithium batteries or any other Energy storage Energy Supply, and this without the needs for chemical tanks. Innovations without the need for: 1. Heat pumps for DHWS. 2. Gas, Diesel, Mechanical combustion fossil Gasoline Engine and Electric diesel fuel generator. 3. EV / Storage Lithium batteries. 4. Mechanical elevations / lifting storage. As described, above, currently available on the world market.

The application discloses a supercritical water pulse detonation device for treating battery waste liquid, which comprises a pulse detonation chamber for oxidizing and decomposing organic pollutants by supercritical water, wherein each pulse emitter in the pulse detonation chamber is provided with a pulse emission tube, the pulse emission tube of each pulse emitter is connected to an energy-gathering ring, and a pulse detonation assembly is arranged in the pulse emitter. The application designs the supercritical water pulse detonation device for treating battery waste liquid, which can cause a violent oxidation reaction in the pulse detonation chamber, is an important component for realizing supercritical water oxidation treatment of battery waste liquid, significantly improves the degradation efficiency of organic pollutants in the battery waste liquid, reduces energy consumption, and has important environmental protection and engineering application values.

A method of operating a rotating detonation combustor (104, 104', 108, 108', 114, 114') includes providing (S702) a flow of air (80, 98) through an air inlet (154, 154') to flow into a detonation chamber (128), providing (S703) a flow of fuel (68, 102) from at least one fuel injector (160, 160') into the detonation chamber (128), mixing (S704) the flow of the fuel (68, 102) and the flow of the air (80, 98) in the detonation chamber (128) to generate a fuel-air mixture (111), detonating (S705) the fuel-air mixture (111) in the detonation chamber (128) to generate rotating detonation waves (106, 112) within the detonation chamber (128), and controlling (S706-S715), during operation of the rotating detonation combustor (104, 104', 108, 108', 114, 114') from a first power operating state to a second power operating state, different from the first power operating state, the air inlet wall (164, 164') to control the flow of the air (80, 98) through the air inlet (154, 154') into the detonation chamber (128) to control a discharge coefficient and an operating mode within the detonation chamber (128).

This invention discloses a subsonic ramjet engine based on counter-rotating rotary detonation flame stabilization ignition, belonging to the field of subsonic ramjet engine flame stabilization ignition technology. It includes an intake cooling channel, an integrated fuel supply device, and a symmetrical rotary detonation flame stabilization device. The intake cooling channel cools the engine wall temperature; the integrated fuel supply device achieves high system integration, low flow resistance loss, and lightweight and convenient design; the symmetrical rotary detonation flame stabilization device uses a counter-rotating jet to assist in creating a stable low-speed recirculation zone in the main combustion chamber, thereby achieving flame stabilization. Furthermore, the continuously operating rotary detonation generator acts as a pre-combustion tube, providing forced ignition to the main combustion chamber. This highly integrated invention effectively cools the combustion chamber wall temperature of the subsonic ramjet engine, improves combustion stability, and significantly increases the ignition success rate of the main combustion chamber, thus providing an effective technical approach for subsonic ramjet engines to operate within a wide range of conditions.

A method of operating a rotating detonation combustor includes providing a flow of air through an air inlet to flow into a detonation chamber, providing a flow of fuel from at least one fuel injector into the detonation chamber, mixing the flow of fuel and the flow of air in the detonation chamber to produce a fuel-air mixture, during operation of the rotary detonation combustor from a first power operating state to a second power operating state different from the first power operating state, the fuel-air mixture is detonated in the detonation chamber to generate a rotary detonation wave in the detonation chamber, and during operation of the rotary detonation combustor from the first power operating state to a second power operating state different from the first power operating state, the air inlet wall is controlled to control air flow into the detonation chamber through the air inlet, therefore, the emission coefficient and the operation mode in the detonation chamber are controlled.

The invention discloses an aircraft outer culvert knocking thrust increasing engine and a knocking thrust increasing method, and belongs to the technical field of engines. An aircraft outer culvert knocking and thrust increasing engine comprises an engine body, a plurality of outer culvert knocking and thrust increasing units are arranged on an outer culvert between the engine body and a cartridge receiver side by side in a circumferential array mode, and outer culvert bypass channels are arranged outside the outer culvert knocking and thrust increasing units; the outer culvert detonation thrust increasing unit comprises a main detonation pipe arranged along the axis of the engine body, an angle-adjustable flow guide ring is arranged at the air inlet end of the main detonation pipe, a pre-detonation pipe for igniting the main detonation pipe is arranged on the side wall of the air inlet end of the main detonation pipe, and an outer culvert exhaust nozzle is arranged at the air outlet end of the main detonation pipe. Gas in the outer culvert exhaust nozzle, the main combustion exhaust nozzle of the engine body and the outer culvert bypass channel is freely mixed at the tail end of the engine body. By the adoption of the aircraft outer culvert detonation thrust increasing engine and the detonation thrust increasing method, the problems that an existing detonation engine is large in air flow resistance, low in thrust-weight ratio and not compact in structure can be solved.

The invention provides a combustion technology of a fuel engine, in particular to a combustion technology of a pulse stamping combustion gathering detonation engine. The invention aims to solve the problems of incomplete combustion, low efficiency, slow combustion speed, serious atmospheric pollution and the like of the existing engine. When the combustion process of an engine applying the technology is started, mixed oil gas in the pre-combustion combustion chamber (2) is ignited firstly, pressure generated by combustion pushes pulses to stamp a piston body (8) of the combustion gathering and detonation combustion chamber to move rightwards, and air or the mixed oil gas in a right air inlet gas buffer chamber (9) is extruded to pass through a corresponding hole channel combustion gathering and detonation combustion chamber side hole set (1); and the mixed gas is quickly sprayed into a combustion gathering and detonation combustion chamber [16], the combustion pressure further pushes a pulse stamping combustion gathering and detonation combustion chamber piston body [8] to move rightwards, and the mixed gas in a right gas inlet buffer chamber [9] is forcefully extruded to quickly enter the combustion gathering and detonation combustion chamber [16], so that the combustion is quickly converted into a detonation combustion mode.

An explosion engine with its air inlet end not connected with a fixed combustion chamber, comprising an air inlet channel, a bearing, a shaft, an aircraft, characterized in that the explosion engine further comprises a machine shell, a rotary cylinder, a fixed combustion chamber, end walls at both ends of the rotary cylinder, a rotary cylinder partition, an inner circular wall of the rotary cylinder, an uninterrupted fuel injector, an igniter, a jet channel, and a gas exhaust channel; the oncoming flow entering from the air inlet channel pushes the rotor to rotate at high speed, after the rotary cylinder rotates through the position of the uninterrupted fuel injector and receives the injected fuel, the rotary cylinder continues to rotate to the position connected with the fixed combustion chamber, the explosion shock wave in the fixed combustion chamber will cause the explosive compression of the mixture of fuel and air in the rotary cylinder, so that the explosion of the mixture of fuel and air produces an explosion shock wave which is ejected from the jet channel, after the rotary cylinder rotates to the position not connected with the fixed combustion chamber, the exhaust gas remaining in the rotary cylinder is exhausted into the next working cycle.

The invention discloses a pulsating jet engine with a double-layer combustion chamber. The pulsating jet engine is composed of the double-layer combustion chamber, an air inlet channel, a tail pipe, an oil nozzle and the like. The engine combustion chamber is of a double-layer structure, the inner-layer wall face is the main structure of the engine combustion chamber, the size of the engine combustion chamber is controlled, and main combustion temperature of an engine is borne. And a certain space is formed between the outer-layer wall surface and the inner-layer wall surface for isolation. And the middle gap can be vacuumized and can also be filled with a non-metallic material with high temperature resistance and low thermal conductivity. The pulsating engine with the double-layer combustion chamber has the advantages that in the starting and working process of the engine, the heat loss of the wall face of the engine can be reduced, the temperature of fuel gas in the combustion chamber can be increased, the propelling efficiency of the engine can be improved, the working environment boundary of the engine can be widened, and the infrared stealth performance can be effectively improved.

A combustor for a rotating detonation engine includes an outer tapered wall extending along an axis; an inner tapered wall extending along the axis, wherein the inner tapered wall is positioned within the outer tapered wall to define an annular combustion chamber having an annular gap between the outer tapered wall and the inner tapered wall, wherein the outer tapered wall is moveable relative to the inner tapered wall along the axis, and wherein movement of the outer tapered wall relative to the inner tapered wall changes the annular gap of the annular combustion chamber. Obstacles can be positioned on either or both of inner and outer wall to enhance turbulence within the combustion chamber.

To obtain a flying object capable of improving propulsion performance and improving guidance accuracy to targets moving at high speeds.SOLUTION: A flying object 1, which corresponds to ground-to-air, ship-to-air, or air-to-air, comprises: a rotary detonation engine 5 with a thrust deflector 6 that controls a thrust deflection angle to change a thrust axis; a pulse detonation engine 7 with a plurality of nozzles; a seeker 2 that obtains tracking information of a target; an inertial device 3 that obtains inertial information of the flying object 1; and an autopilot 4 that calculates a thrust command and a thrust deflection angle command of the rotary detonation engine 5, which are necessary to correct an error to an expected meeting point with a target on the basis of the tracking information and the inertial information, and a nozzle thrust command of the pulse detonation engine 7, and outputs the commands to the rotary detonation engine 5 and the pulse detonation engine 7.SELECTED DRAWING: Figure 10

A diffuser (300) may comprise an inlet (310) and an outlet (340). The inlet may comprise an arcuate shape. The outlet may comprise an annular shape. The diffuser may transition from the arcuate shape at the inlet to the annular shape at the outlet. The diffuser may comprise a radially inner wall (320) and a radially outer wall (330) disposed opposite the radially inner wall. The radially inner wall and the radially outer wall may partially define a duct.