16results about "Intermittent jet plants" patented technology

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.

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.

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.

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.

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.

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.

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 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 field of hypersonic aerodynamics and intelligent control technology, especially to a bulge assisted oblique detonation wave initiation intelligent control method based on a feedforward neural network, which is used for the design and control of high-performance propulsion systems such as scramjet engines and oblique detonation wave thrusters. Wave structure data under different bulge geometric parameters and inflow conditions are obtained through numerical simulation technology. Image processing technology is used to extract feature parameters, label wave structure types, and construct sample data sets. A multi-layer feedforward neural network is used to train the samples, and the optimal network structure is selected through cross-validation to establish a nonlinear mapping model between the bulge geometric parameters and the wave structure categories. The neural network is used to quickly identify and predict the wave structure under unknown conditions, and the probability distribution is output to evaluate the confidence. According to the wave structure category and the control rule library, the height, length, position or inclination angle of the bulge is adjusted to realize real-time intelligent control of the oblique detonation wave system.

The invention discloses a small valveless pulsating jet engine which comprises a combustion chamber, an air inlet, a resonance tube, an exhaust nozzle and a rectifying ring. The rear end face of the combustion chamber is connected with air inlets and resonant tubes; the outlet direction of the air inlet faces behind the engine; the front end of the resonance tube is connected with the combustion chamber; and the rectifying ring is mounted at a nozzle of the exhaust nozzle. The pulsating jet engine is simple in structure, free of movable parts, stable in work in the flying process and high in thrust efficiency.