33results 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 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 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 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 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 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.

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.

The invention relates to an obstructing detonation engine, which is obstructed between a combustion chamber and a gas compressor by an obstructing steel pipe and prevents detonation waves generated in the combustion chamber from generating resistance to a rotary piston rotating into a gas compression chamber, and comprises a main shaft, the obstructing detonation engine is characterized by further comprising an obstructing steel pipe, a rotary piston, a combustion chamber, an air compression chamber, an air injection channel, an air injection and exhaust channel, a fuel injection pipe, an air inlet channel, a piston inlet, a piston outlet and an exhaust pipe. High-speed airflow entering the air compression chamber is pushed by the high-speed rotating rotary piston to enter the high-speed rotating blocking steel pipe to receive fuel oil sprayed out of the fuel spray pipe to form an air-fuel mixture, then the air-fuel mixture is subjected to detonation combustion to generate detonation waves, and the detonation waves are sprayed out of the air spray channel to push an airplane where the air-fuel mixture is located to fly at a high speed. And afterwards, waste gas left in the blocking steel pipe is discharged through the air spraying and discharging channel, and the blocking steel pipe receives the air pressed in by the rotary piston again to enter the next working cycle.

The application discloses a time sequence control rotating detonation engine system combined with a turbojet engine, which comprises a turbojet engine, a shell sleeved on the periphery of the tail nozzle of the turbojet engine, a cylindrical base coaxially arranged on the inner side of the shell, and a fan-shaped detonation tube. A cover driven by an electromagnetic push rod is arranged at the top end of each detonation tube. A sequential ignition control device is arranged, and a fuel supply unit of the sequential ignition control device comprises an oil pump, a fuel coil pipe coiled in the cylindrical base, a common rail ring outside the shell, and a plurality of fuel injectors. A control unit adopts a mechanical time sequence controller, and through rotating a moving contact on an outer rotor, the mechanical time sequence controller sequentially connects static contacts on an electrode distributor, synchronously triggers electromagnetic push rods and fuel injectors of corresponding detonation tubes, and realizes multi-tube sequential cycle detonation. The application recovers exhaust heat energy to preheat fuel through a coaxial integrated structure, supplies air by using an ejecting effect, replaces a complex electronic system with a simple and reliable mechanical control, and realizes efficient, compact, wide working condition adaptation and thrust enhancement.

The invention discloses a medium channel, a rotary detonation engine outer wall and a rotary detonation engine, and relates to the technical field of rotary detonation engine active thermal protection, the medium channel comprises a first spiral section and a second spiral section which are integrated, and the space curve axis of the first spiral section and the space curve axis of the second spiral section are spiral lines; the screw pitch of the first spiral section is larger than that of the second spiral section, and the section of the first spiral section and the section of the second spiral section are rectangular and consistent in size, and the first spiral section and the second spiral section are consistent in rotating direction. The medium channel is arranged in the outer wall of the rotary detonation engine, and the outer wall of the rotary detonation engine is used for forming the rotary detonation engine. The technical prejudice in the prior art is overcome, the curve-shaped medium channel is applied to the outer wall of the rotary detonation engine, the problem that the straight channel type heat exchange effect is poor can be solved, and the problems that a dead zone is more likely to be formed by curve modeling, wall face cracking is likely to be caused, and sealing failure is likely to be caused can be solved.

The application discloses a valveless pulse jet engine quick starting device and method, which comprises a valveless pulse jet engine, an igniter, a blowing system and an oil supply system; after alcohol is filled in the alcohol tank and the engine starts, the igniter starts to work first, alcohol is pressed into the combustion chamber by fuel, the blowing system blows high-pressure air into the combustion chamber from the air inlet, and the blowing system and the igniter are closed in turn after a period of time, so that the engine can be started reliably. The method of the application can improve the starting reliability of the engine and greatly shorten the starting time of the engine by using alcohol combustion assisting preheating and high-pressure air blowing excitation.

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.

The application provides an aero-engine with knock-on afterburning chamber, comprising: a compressor, a combustion chamber, a turbine and a nozzle, the compressor and the turbine are coaxially connected, compressed air from the outlet of the compressor enters the combustion chamber, combustion gas from the outlet of the combustion chamber enters the turbine to drive the turbine to work, and the outlet gas after the turbine works enters the nozzle; the knock-on afterburning chamber is arranged in the nozzle, the knock-on afterburning chamber comprises an afterburning outer ring and an afterburning inner ring, the afterburning inner ring is coaxially sleeved in the inner cavity of the afterburning outer ring, and the annular wall of the afterburning outer ring and the annular wall of the afterburning inner ring form a knock-on ring cavity for continuous rotating knock-on combustion; the outlet gas entering the nozzle enters the knock-on ring cavity from the air inlet end of the knock-on afterburning chamber, mixes with fuel in the knock-on ring cavity and performs continuous rotating knock-on combustion. The application can effectively improve the combustion efficiency of the aero-engine and reduce fuel consumption.

A rotating detonation combustor includes a nozzle coupled to the combustor body at or near the exhaust opening to choke the exhaust opening. A rotating detonation combustor may include a diverting plate positioned radially inward of the inlet annulus and inlet channels for diverting flow of a mixture in an axial direction. A rotating detonation combustor may include a combustor body including an outer shell at least partially defining a detonation combustion chamber and extending axially from a base toward an exhaust opening of the detonation combustion chamber. The base defines a passageway in fluid communication with the detonation combustion chamber and includes an inlet annulus for axially directing a second fluid into the passageway and a plurality of inlet channels for radially directing a third fluid into at least one of the passageway or the detonation combustion chamber, and the detonation combustion chamber is free of any inner body.

The present application relates to the technical field of aero-engine, and discloses a center initiation type oblique detonation engine, which comprises a fuel injection support plate and an initiation support plate, the fuel injection support plate is fixed in a combustion chamber, a plurality of first reverse jet holes are formed on the end face of the fuel injection support plate opposite to an air inlet, a plurality of fuel injection holes are formed on the end face of the fuel injection support plate opposite to the air inlet, a first gas conveying flow channel and a fuel conveying flow channel are respectively formed in the fuel injection support plate, the initiation support plate is fixed in the combustion chamber and is arranged in parallel with the fuel injection support plate, a plurality of second reverse jet holes are formed on the end face of the initiation support plate opposite to the fuel injection holes, the initiation support plate is arranged instead of the original wedge surface, the initiation support plate and the fuel injection support plate are both subjected to thermal protection by reverse jet, the arc shock induced by the reverse jet plays a role in strengthening initiation, and the oblique detonation wave is in the center initiation, so that the boundary layer separation of the lower wall surface is avoided.