22results about "Continuous jet plants" patented technology

The invention belongs to the field of detonation engines, and particularly relates to a metal-based gel propellant detonation engine which comprises an air inlet channel, a rotary detonation combustion chamber and a propellant supply system. The propellant supply system comprises a gel propellant storage box arranged in the central cylinder, a gel propelling structure connected with the gel propellant storage box and an atomizing nozzle, and the atomizing nozzle is mounted on the propellant injection structure; the propellant supply system further comprises an atomized gas storage box arranged in the combustion chamber cylinder, and the atomized gas storage box is connected with the atomizing nozzle through an atomized gas conveying channel. According to the rotary detonation engine, the metal-based gel propellant is applied to the rotary detonation engine, the energy density is superior to that of an existing gas and liquid propellant rotary detonation engine, safety is high, and thrust output is controllable. And the propellant supply system does not occupy the space outside the engine at all, and the gel propellant rotary detonation engine with a good effect is achieved under the condition that the size of the engine is not additionally increased.

The invention relates to a turbofan engine having a fixed structure, a fan, a fan casing surrounding the fan, an outer nacelle arranged around the fan casing and mounted hinged on the fixed structure, and a deployment system (250) for moving the outer nacelle from a closed position to an open position, and the deployment system has a guide rail (252) fastened around the fan casing, a slider (254) movable along the guide rail (252) and having a shoe (258), an activation system for moving the slider (254) and the shoe (258) in one direction or in the other direction along the guide rail (252) alternately, and an arm (264) having one end mounted hinged on the shoe (258) and the other end mounted hinged on the outer nacelle. Such motorized deployment system makes it possible to save space and mass of the turbofan engine.

A method for converting heat to mechanical work including providing incoming heat transfer fluid (HTF) at a first temperature to a mixing chamber, providing incoming compressed gas at a second temperature to the mixing chamber, enabling the gas and the HTF to mix, producing a gas- and- HTF mix, enabling the HTF in the gas- and- HTF mix to heat the gas and isotherma l expansion of the gas in the gas- and- HTF mix, limiting volume of the gas-and-HTF mix, thereby increasing pressure of the gas and causing acceleration of a flow of the gas-and-HTF mix, causing the gas-and-HTF mix to eject through a nozzle, thereby converting the heat of the HTF to kinetic energy, and using the kinetic energy to produce mechanical work. Related apparatus and methods are also described.

An ejector system for propelling a vehicle. The system includes a diffusing structure and a duct coupled to the diffusing structure. The duct includes a wall having openings formed therethrough and configured to introduce to the diffusing structure a primary fluid produced by the vehicle. An airfoil is positioned within the flow of the primary fluid through the openings to the diffusing structure.

The present invention belongs to the field of detonation engines, and specifically relates to a metal-based gel propellant detonation engine, comprising an air inlet, a rotating detonation combustion chamber, and a propellant supply system; the propellant supply system comprises a gel propellant tank disposed within a central cylinder, a gel propulsion structure connected to the gel propellant tank, and an atomizing nozzle, the atomizing nozzle being mounted on the propellant injection structure; the propellant supply system also comprises an atomizing gas tank disposed within the combustion chamber cylinder, the atomizing gas tank being connected to the atomizing nozzle via an atomizing gas delivery channel. The present invention proposes the application of metal-based gel propellant to a rotating detonation engine, which has an energy density superior to that of existing gas and liquid propellant rotating detonation engines, is highly safe, and has controllable thrust output. Furthermore, the propellant supply system does not occupy any space outside the engine, achieving a highly effective gel propellant rotating detonation engine without increasing the engine size.

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.

An ejector system for propelling a vehicle. The system includes a diffusing structure and a duct coupled to the diffusing structure. The duct includes a wall having openings formed therethrough and configured to introduce to the diffusing structure a primary fluid produced by the vehicle. An airfoil is positioned within the flow of the primary fluid through the openings to the diffusing structure.

Propulsion module with a jet engine, wherein the propulsion module comprises: a compressor for compressing an inlet gas prior to its entry into at least one combustion chamber of the jet engine and an electric drive for driving the compressor, wherein the electric drive is arranged outside a jet of the jet engine.

The present invention provides a rotary detonation engine based on non-equilibrium plasma detonation and gas supply, including a nozzle, a pre-detonation tube and an engine body; a combustion chamber is formed between a combustion chamber outer ring and a combustion chamber inner ring, the pre-detonation tube is installed on the combustion chamber outer ring, and one end of the pre-detonation tube is connected to the combustion chamber; a nozzle is installed at the inlet of the pre-detonation tube; a spark plug is arranged in the pre-detonation tube; a plurality of the nozzles are installed in the combustion chamber, and a plurality of the nozzles are located between the connection between one end of the pre-detonation tube and the combustion chamber and the engine cover plate; a fuel flow channel and an oxidant flow channel that are not connected to each other are arranged in the nozzle; an electrode is arranged in the wall of the fuel flow channel, and a voltage is applied on both sides of the electrode to generate non-equilibrium plasma by ionizing the fuel medium in the flow channel. The present invention can strengthen the combustion process, promote the fuel to burn out, reduce the heat loss of chemical incomplete combustion, and reduce the emission of pollutant gases.

The invention relates to the technical field of engines, and discloses a detonation engine which is characterized in that a duct cylinder, a gas collection cylinder and a spray pipe are sequentially connected, the gas collection cylinder is provided with a reducing section, and a sweepback blade fan driven by a second motor is arranged in the duct cylinder; an air injection cylinder is fixed in the spray pipe in a sealed mode, a penetrating wave channel is formed in the circumferential direction of the air injection cylinder, a wave tube is rotationally sleeved with the wave channel, and an arch-shaped scraper blade is fixed to the air injection cylinder and tangent to the inner wall of the wave tube. A guide cone is slidably arranged in the air injection barrel and connected with the air injection barrel through a spiral groove shifting fork mechanism, and the guide cone slides to drive the wave tube to rotate to achieve scraping and dust removal of the scraper. The end face of the air injection cylinder, the guide cone and the inner wall of the spray pipe define a combustion chamber, and the spray pipe is provided with a pressure detection assembly. The pressure of the combustion chamber can be accurately regulated and controlled, accumulated dust of the wave tube is actively removed, meanwhile, the combustion efficiency is improved, the heat-resistant service life is prolonged, pressure instability and dust accumulation pain points are solved, and the reliability of an engine is improved.

The present invention discloses an underwater oxygen-kerosene jet engine, comprising an outer shell component, a supply component, a combustion chamber component and a tail nozzle component; the characteristics are as follows: the outer shell component comprises an outer shell body, an upper cover plate and a lower cover plate, the two ends of the outer shell are mounting flanges, the upper cover plate and the lower cover plate are connected to the outer shell body flange by screws; the supply component comprises a kerosene supply pipe, an ignition kerosene supply pipe and an oxygen supply pipe; the combustion chamber component comprises an annular combustion chamber, a kerosene injection ring, a high-energy kerosene igniter and an oxygen-fuel secondary mixing cone; the tail nozzle component is fixed on the lower cover plate, and the tail nozzle component is a convergent nozzle with a bend in the range of 45° to 90° and an equal straight section nozzle. The present invention has a simple structure, omits a propeller device, and directly drives an underwater vehicle to sail at high speed by ejecting high-speed gas.

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.

An aerial vehicle engine is proposed which may be powered an adjustable, vortex-based virtual aerospike engine. The vehicle may also include a combustion chamber which may be coupled to the exit nozzle. The combustion chamber may include one or more gas inlets, one or more blanket inlets and one or more main inlets. The gas inlet may be configured to let in a column of gases into the combustion chamber in a direction parallel to the direction of the rocket with minimal angular velocity to prevent the column of gases from mixing with a vortex of propellants or gases. The one or more main inlets may be configured to spray fuel or oxidizer at a specific angle, where the angle may be adjustable for forming the vortex of propellants or gases. The one or more blanket inlets may be configured to spray fuel / oxidizer / (inert) coolant at a specific angle, where the angle may be adjustable and may or may form a vortex, a stagnant pocket of gases (acting as a blanket) or a stream of gases that exits through the exit nozzle. Further, the column of gases inside the combustion chamber leading up to the exit nozzle may form a virtual aerospike nozzle, the virtual aerospike nozzle may exit the gases to propel the vehicle, wherein the virtual aerospike nozzle may not require cooling.

The present invention discloses a continuous rotating detonation engine, comprising an engine body, the engine body is provided with an oxidant flow channel, comprising a first cavity, a second cavity surrounding the first cavity, and a plurality of third cavities, the first cavity is connected to an intake joint, the first cavity peripheral wall is provided with a circumferentially distributed first equalizing flow hole, the first equalizing flow hole is connected to the second cavity, a plurality of third cavities are evenly distributed along the circumference of the second cavity, the third cavity is provided with a second equalizing flow hole and a third equalizing flow hole, the second equalizing flow hole is connected to the second cavity, the engine body is also provided with a mixing chamber, and the third equalizing flow hole is connected to the mixing chamber. The present invention improves the structure of the oxidant flow channel, can improve the uniformity of oxidant distribution, and the uniformity of mixing with fuel, to ensure the combustion stability and thrust performance of the continuous rotating detonation engine.

A method for converting heat to mechanical work including providing incoming heat transfer fluid (HTF) at a first temperature to a mixing chamber, providing incoming compressed gas at a second temperature to the mixing chamber, enabling the gas and the HTF to mix, producing a gas- and- HTF mix, enabling the HTF in the gas- and- HTF mix to heat the gas and isotherma l expansion of the gas in the gas- and- HTF mix, limiting volume of the gas-and-HTF mix, thereby increasing pressure of the gas and causing acceleration of a flow of the gas-and-HTF mix, causing the gas-and-HTF mix to eject through a nozzle, thereby converting the heat of the HTF to kinetic energy, and using the kinetic energy to produce mechanical work. Related apparatus and methods are also described.

Propulsion module with a jet engine, wherein the propulsion module comprises: a compressor for compressing an inlet gas prior to its entry into at least one combustion chamber of the jet engine and an electric drive for driving the compressor, wherein the electric drive is arranged outside a jet of the jet engine.

The invention discloses a gas-liquid two-phase rotating detonation engine which comprises a combustion chamber, a combustion chamber and a detonation chamber. The oil injection ring is arranged at an inlet of the combustion chamber, the oil injection ring comprises an annular main body and a bendable metal sheet, a groove is formed in the inner side of the annular main body, an oil injection hole communicated with the groove is formed in the outer side of the annular main body, and the metal sheet is fixedly arranged on the inner side of the annular main body; the metal sheet covers a notch of the groove and forms an annular cavity with the groove in an enclosing manner, and a plurality of oil spraying holes communicated with the annular cavity are formed in the metal sheet at intervals; one end of the air inlet pipe is connected to the side, opposite to the combustion chamber, of the oil injection ring, and the other end of the air inlet pipe is used for introducing incoming flow air; and the spray pipe is arranged at an outlet of the combustion chamber. Compared with the prior art, the machining difficulty of the oil injection ring can be reduced through the structure, the machining period of the oil injection ring can be shortened, and meanwhile the yield of the oil injection ring can be increased.

An energy storage and retrieval system including an air chamber, a first air compressor operating with Heat Transfer Liquid (HTL-compressor) connected to the air chamber, a second turbine, operating with Heat Transfer Liquid (HTL-turbine) connected to the air chamber, accepting compressed air from the air chamber and producing work. Related apparatus and methods are also described.

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 provides a detonation vector propulsion scheme based on combination of multiple unit bodies. The detonation vector propulsion scheme comprises a scheme based on combination of pulse detonation engine unit bodies, a scheme based on combination of rotary detonation engine unit bodies and a scheme based on mixed combination of the pulse detonation engine unit bodies and the rotary detonation engine unit bodies. According to the scheme based on the pulse detonation engine unit body combination, a plurality of pulse detonation engine unit bodies which are symmetrically arranged are included; according to the scheme based on the rotary detonation engine unit body combination, a plurality of rotary detonation engine unit bodies which are symmetrically arranged are included; according to the scheme based on the pulse and rotary detonation engine unit body mixed combination, the rotary detonation engine unit body with the symmetrical combustion chamber channel configuration and the multiple pulse detonation engine unit bodies which are symmetrically arranged are included. When the device arranged according to the scheme works, the vector propulsion effect is achieved by changing the working state of individual engine unit bodies. The method can be applied to the fields of detonation vector propulsion and the like.