19 results about "Afterburner" patented technology

FIELD: rocket science.SUBSTANCE: invention concerns the design of a ramjet engine. The ramjet engine body is a structure consisting of several layers, including: an internal heat-protection layer made of a composite material based on a thread frame of heat-resistant fibers impregnated with an elastic polymer binder, a power body based on a high-temperature polymer composite material and an external heat-protection layer made of a composite material based on an elastic polymer binder and a finely dispersed mineral filler. Thanks to the use of layers of external and internal thermal protection, it becomes possible to use a polymer composite material for the power casing.EFFECT: reducing the labor intensity of manufacturing and weight of the product and increased energy-mass perfection of the propulsion system.1 cl, 2 dwg

This invention discloses a drag reduction and thrust reversal device, relating to the field of fluid dynamics technology. The invention includes a front drag reduction air intake assembly, an automatic rotary cutting assembly, two fluid delivery pipes, and the drag reduction and thrust reversal assembly. The automatic rotary cutting assembly is mounted on the front drag reduction air intake assembly. In this invention, the drag reduction and thrust reversal device, composed of the front drag reduction air intake assembly, the automatic rotary cutting assembly, the fluid delivery pipes, and the drag reduction and thrust reversal assembly, efficiently captures oncoming fluid through an inclined inlet at the front. A filter baffle at the inlet blocks large debris, which is then shredded and mixed by fluid-driven rotary cutting blades. The mixture is then transported through the fluid pipes to the end delivery pipes. Under the action of the tail jet pressurization device, the fluid forms a vortex and is ejected at high speed, generating reverse thrust. This converts oncoming resistance into propulsive power, directly propelling the ship forward, achieving the dual effects of drag reduction and thrust reversal, and converting drag energy into forward propulsion.

This application belongs to the field of aero-engine technology, and specifically relates to a double-layer structure afterburner heat insulation plate. The heat insulation plate is installed between the inner cone and the rear bearing cavity, isolating the rear bearing cavity from the inner cone's internal cavity. The heat insulation plate includes an inner layer, an outer layer, a skin, and a mounting edge. The mounting edge is located at the circumferential outer edge of the inner layer and has multiple circumferentially distributed through holes. The mounting edge is installed on the mounting edge of the bottom surface of the inner cone through these through holes. The outer layer is attached to the surface of the inner layer near the inner cone. The inner layer includes a spherical surface protruding into the inner cone's internal cavity. The afterburner heat insulation plate has a double-layer structure, and the cavity height is maintained by fixed supports and rivets. Heat insulation cotton is added to the double-layer cavity to enhance the heat insulation effect of the heat insulation plate.

This invention discloses a porous rectifying structure for the afterburner of a variable cycle engine, comprising a rectifying orifice plate installed in an annular channel between the turbine outlet and the flame stabilizer. The orifice plate is symmetrically arranged along its radial central axis, with the clogging area facing the turbine inflow and axially aligned with the heat shield inlet. The orifice plate height is 2 / 3 of the channel height between the central cone and the heat shield. The plate has uniformly distributed pores with an equivalent diameter of 10-20 mm along the radial direction, with a clogging ratio of 5%-25%. This invention forms a multi-stage mixing interface through the radially gradient porosity pore arrangement, promoting shear mixing of the high-temperature internal combustion gas and the external bypass gas. Simultaneously, the static pressure difference across the orifice plate drives the external bypass gas flow into the heat shield cooling channel, increasing the cooling flow rate, improving the uniformity of the upstream velocity field of the flame stabilizer, eliminating the recirculation zone inside the heat shield, reducing the thermal load on the casing wall, and controlling the total pressure loss to within 3%, achieving high-stability combustion and reliable thermal protection under a wide bypass ratio.

This invention discloses a pneumatic concave cavity flame stabilization device for an afterburner, comprising a central cylinder, an annular combustion chamber shell, a diffuser, an afterburner shell, a pneumatic concave cavity pipe, and a central cylinder connecting rod. The diffuser fixes the annular combustion chamber shell and the afterburner shell together. The central cylinder is fixed to the center of the annular combustion chamber shell via the central cylinder connecting rod. The pneumatic concave cavity pipe extends through the central cylinder into the afterburner shell. The vertical jet from the pneumatic concave cavity exhaust port of this invention can enhance the recirculation zone and stably maintain a low-speed recirculation vortex under different operating conditions, stabilizing the combustion operating range and reducing the risk of flameout. The vertical jet from the pneumatic concave cavity exhaust port of this invention can entrain fuel and air into the cavity, prolonging the fuel residence time and fundamentally improving combustion efficiency. The vertical jet from the pneumatic concave cavity exhaust port of this invention can fill the low-pressure zone at the rear edge of the cavity, reducing resistance, significantly reducing total pressure loss, and improving engine thrust efficiency.

This invention discloses a concave cavity flame stabilizer structure, its fuel injection and cooling method, and an afterburner. The structure includes a symmetrical Tesla valve, a fluid oscillator, and shape memory alloy ribs. The Tesla valve is located at the front end of the evaporation chamber of the afterburner, utilizing its unidirectional flow resistance characteristics to suppress fuel backflow caused by pressure fluctuations and ensure stable fuel supply. The fluid oscillator replaces the traditional injection hole, converting the fuel-air mixture into a high-frequency, large-scale periodic swept jet injected into the concave cavity, improving atomization, evaporation, and mixing efficiency. The shape memory alloy ribs are located on the cold side of the bottom and rear wall of the concave cavity, automatically adjusting their shape according to changes in wall temperature to achieve dynamic matching between cooling intensity and heat load. This invention, through the system integration of fuel supply, combustion, and cooling, solves the problems of fuel backflow, low atomization efficiency, and poor adaptability of the cooling system under wide operating conditions in traditional concave cavity structures, significantly improving the combustion efficiency and thermal protection reliability of the afterburner.

This invention relates to the field of aero-engine technology, and discloses an inlet swirl adjustment device and its design method for an afterburner test component. A flow divider ring is used to segment the test flow channel into an inner flow channel and an outer bypass flow channel for simulating the airflow in the inner flow channel. The remaining linkage control structures are installed in the outer bypass casing or outer bypass flow channel to reduce interference with the inner flow channel. The linkage adjustment assembly performs overall synchronous adjustment of all adjustable guide vanes, ultimately achieving adjustment of the inner airflow angle, thereby simulating the inner airflow of the afterburner and reducing testing costs and overall engine verification risks. The inlet airflow swirl adjustment device of this invention comprehensively considers the relevant requirements of total pressure recovery coefficient and airflow uniformity index, ensuring high-precision and high-stability simulation of the inner airflow of the afterburner. Furthermore, its simple structure allows for easy assembly and replacement, providing flexible support for afterburner performance testing under different operating conditions.

The application provides a rotating detonation afterburner of an aero-engine, and relates to the technical field of gas turbine engines, and specifically comprises a rotating detonation afterburner connected to an exhaust end of a casing of the engine, an air inlet of the rotating detonation afterburner is connected to an exhaust port of the casing, and an airflow injection channel is arranged on the exhaust end of the casing and / or the air inlet of the rotating detonation afterburner, the airflow injection channel is connected to an internal space and an external space of the air inlet of the rotating detonation afterburner, and when exhaust gas of the exhaust end of the engine passes through the air inlet of the rotating detonation afterburner, the air in the external space of the connection part between the rotating detonation afterburner and the casing is introduced into the rotating detonation afterburner through the airflow injection channel. Through the processing scheme, the stability of the detonation wave is stabilized, and the stability of the rotating detonation afterburner is improved.

This invention belongs to the field of aero-engine rotor design and provides a distributed support and constraint structure for high-temperature thin-walled components. The structure includes a thin-walled component for an afterburner, a thin-walled nozzle component mounted on the tail end of the afterburner thin-walled component, and a component hinge assembly installed between the outer surface of the tail nozzle thin-walled component and the tail end of the afterburner thin-walled component. An electrically controlled telescopic assembly for the thin-walled component is provided between the outer surface of the afterburner thin-walled component and the outer ring surface of the tail nozzle thin-walled component. In this invention, with the assistance of the electrically controlled telescopic assembly and the hinge assembly, the thin-walled components can be supported and constrained while simultaneously improving their fatigue resistance by reducing friction. Furthermore, the structure of the thin-walled components is non-uniformly distributed along the axial / circumferential directions, achieving a non-coordinated design effect through environmental excitation and the thin-walled components.

The application discloses a continuous detonation jet flow initiation and combustion-assisted afterburner, which comprises an outer channel case, an inner channel case, a flow regulation support plate arranged radially on the inner channel case, a center cone, a duty combustion chamber arranged on the flow regulation support plate, a V-shaped flame stabilizer arranged on the flow regulation support plate corresponding to the duty combustion chamber, a continuous detonation jet flow initiator arranged on the outer wall of the inner channel case, and a porous stationary vortex injector arranged at the jet flow outlet of the continuous detonation jet flow initiator. The inner channel utilizes continuous detonation combustion products as the conventional afterburning after the duty flame is strengthened and stabilized, and the outer channel is detonated for afterburning through the continuous detonation jet flow initiation mechanism. The continuous detonation partitioned strengthened combustion organization scheme is helpful to realize the wide-range high-efficiency low-resistance working requirement of the advanced afterburner.

This invention discloses a partially swirling afterburner, comprising an outer cylinder assembly, a central body assembly, and an oil circuit assembly. The outer cylinder assembly includes an outer casing and a shock-absorbing heat shield. The central body assembly includes an inner casing, a central cone located inside the inner casing, a rectifier support plate located between the inner casing and the central cone, an outer cavity stabilizer, and a central cavity stabilizer. The outer and central cavity stabilizers are located at the rear end of the rectifier support plate. The outer cavity stabilizer forms a protrusion from the inner casing towards the outer casing, and the central cavity stabilizer is an annular cavity disposed on the central cone. The rectifier support plate includes several direct-flow blades and several swirling blades, arranged sequentially from the inside to the outside. Through the cooperation between the outer cavity stabilizer, the central cavity stabilizer, and the partially swirling rectifier support plate, centrifugal force is used to achieve radial propagation of the cavity flame, solving the problem of difficult circumferential flame connection in traditional radial stabilizers and achieving flame connection across the entire combustion chamber cross-section.

The application relates to the field of aerospace technology, in particular to a high-Mach number ramjet engine with an afterburner. The high-Mach number ramjet engine with the afterburner comprises an aircraft body, an engine lower wall surface and an air inlet; the aircraft body is internally provided with a fuel tank; an isolation section, a first combustion chamber and a nozzle section are arranged between the aircraft body and the engine lower wall surface; the side, away from the first combustion chamber, of the isolation section is provided with the air inlet; the high-Mach number ramjet engine with the afterburner further comprises a powder fuel injection assembly and a second combustion chamber; the powder fuel injection assembly is arranged on the aircraft body, and the second combustion chamber is formed between the first combustion chamber and the nozzle section; the powder fuel injection assembly can inject metal fuel into the second combustion chamber; the metal fuel can be subjected to secondary combustion with combustion products in the second combustion chamber; and the energy generated by the secondary combustion is used to improve the thrust of the aircraft.

This application discloses a microwave-based jet engine afterburner, belonging to the field of thermomechanical technology. It includes a microwave heating mechanism, whose microwave generator comprises a cathode electron source, a heating component, a ring-shaped metal anode, an electromagnet, and a DC power supply component. The cathode electron source is located at the center of the ring-shaped metal anode. The heating component causes the cathode electron source to emit free electrons. The DC power supply component supplies power to the cathode electron source and the ring-shaped metal anode to form a DC electric field and supplies power to the electromagnet to generate a magnetic field orthogonal to the DC electric field. The strip-shaped groove within the ring-shaped metal anode serves as a microwave resonant cavity. The movement of free electrons excites microwaves, which are used to heat the exhaust gas from the engine's main combustion chamber. The microwave generator is coaxially positioned within the gas flow channel. This device replaces traditional afterburning with microwave heating, offering faster heating speed, a more compact structure, and improved thermal efficiency of the afterburner, solving the problems of easy flameout and low combustion efficiency in traditional afterburner combustion chambers.

This invention provides an integrated evaporative flame stabilizer with fuel injection and stabilization, applied to an afterburner. It includes a stabilizer cooling chamber, a stabilizer control structure, and a fuel system. This invention integrates the stabilizer, fuel system, and fuel plate into a single design. The main fuel injection rod is located within the stabilizer cooling chamber. Low-temperature airflow from the outer bypass is introduced to cool the stabilizer and the main fuel injection rod. Furthermore, the evaporative stabilizer and circumferential stabilizer are designed to work together, with high-temperature airflow introduced from the side intake channel of the evaporative stabilizer. This airflow mixes and evaporates with the fuel in the intake manifold and fuel distribution pipe. Additionally, a radial gap is provided between the fuel distribution pipe and the baffle to allow for thermal expansion of the fuel distribution pipe. This invention overcomes the shortcomings of traditional flame stabilizers, offering advantages such as a wider lean-out threshold, lower flow loss, and higher structural reliability under complex operating conditions.

A kind of afterburning type flue gas molten salt heat exchange denitration integrated device and its working mechanism, characterized by: in the upstream of flue gas molten salt heat exchanger, increase afterburning device, afterburning device is connected with flue gas molten salt heat exchanger by flue, constitutes afterburning type flue gas molten salt heat exchange denitration integrated device;Including afterburner system or afterburning device, first-stage flue gas molten salt heat exchange component, flue gas denitration component and third-stage flue gas molten salt heat exchange component.The present application can realize the function of more uniform and more efficient afterburning heat transfer in flue gas;Realize the safer ignition mode of afterburning gas or atomized afterburning gas-liquid (or gas powder) mixture outside the flue;And realize the function of more convenient monitoring of afterburning combustion;Realize the purification function of removing nitrogen oxides in flue gas;Realize the complete decoupling of heat and electricity in gas turbine power generation heat storage system, realize the function of independent external power supply, heat storage or heat supply of system.

This application relates to an afterburner with adaptive adjustment of the support plate leading edge and stabilizer, and its control method. The afterburner includes a casing, a central guide vane, an outer ring, and multiple support plates distributed circumferentially between the central guide vane and the outer ring. Each support plate includes a leading edge section and a main body section distributed sequentially along the axial direction. The main body section connects the outer ring and the central guide vane. The leading edge section is rotatably connected to the main body section. The afterburner also includes a drive mechanism connected to the leading edge section. The drive mechanism drives the leading edge section to rotate relative to the main body section to adjust the angle of the leading edge section relative to the airflow direction. This allows the leading edge section of the support plate to adapt to changes in the airflow direction, reducing the probability of the leading edge section generating a non-zero angle of attack. This reduces the likelihood of airflow separation, flow field distortion, and oscillation within the afterburner, maximizing the reduction of flow resistance loss and improving thrust and combustion stability.

The application provides a visual recognition-based engine afterburner lance injection angle measurement method and system, and relates to the technical field of fault pre-diagnosis and health management. A pressure sensor is used to monitor the thrust value at the inlet of the to-be-tested lance in real time, and the value is fed back to a proportional pressure reducing valve for PID closed-loop adjustment, so as to control the air load on the surface of fuel in the pressure control tank. The driving mode of pneumatic extrusion suppresses the fluid pulsation and pressure impact inherent in the related mechanical pump oil supply mode, thereby forming a stable laminar flow injection working condition at the to-be-tested lance. The to-be-tested lance is transported to the test position in a unified spatial posture by cooperating with a lance mounting and dismounting system, so that the physical reference of each test is consistent. The captured picture by pixel comparison of the injection angle test subsystem is no longer disturbed by shaking, and the injection angle can be objectively and quantitatively determined, so that the consistency of the measurement result is improved.

The present teachings provide designs and materials of construction for afterburners as well as methods of making the afterburners. More specifically, the afterburners of the present teachings can include a compressible, resilient refractory material such that thermal expansion of other adjacent components, for example, a fuel cell stack of a fuel cell unit, can be accommodated by the afterburner. The present teachings also provide methods of reducing contaminants in exhaust streams and / or generating heat.

The application discloses a supercritical kerosene-based anti-coking and low-blockage-ratio afterburner, and relates to the technical field of aero-engines.The supercritical kerosene-based anti-coking and low-blockage-ratio afterburner comprises a nitrogen pipeline, a normal-temperature oil circuit, a preheating oil circuit, a supercritical kerosene oil supply device formed by an afterburner oil supply circuit and a backflow oil circuit, and the like; and the afterburner is composed of an outer duct, an inner duct, a pressure atomizing nozzle, a direct injection nozzle, a center cone, an oil pipe heat insulation protective sleeve, a first kerosene superheater, a second kerosene superheater and a cavity.The application has the advantages of small flow resistance loss and no additional shaft power consumption by using supercritical kerosene jets to replace blunt body flame stabilizers and aerodynamic flame stabilizers; the mixing effect and combustion efficiency of fuel can be effectively improved by using supercritical kerosene as fuel; and the short board of easy coking of supercritical kerosene is made up by oxygen removal, superheat adjustment, nitrogen purging and the like.