269 results about "Afterburner" patented technology

The invention discloses a real-time early warning method for oscillation combustion of an afterburner, and the method comprises the steps: employing a network structure in which Fourier series is simplified and then the Fourier series is introduced into a Kolmogorov-Arnold network (Kolmogorov-ArnoldNetworks, KAN), proposing a Cosine Kolmogorov-Arnold network (CosKAN), and in combination with an anomaly detection idea, proposing a new algorithm which is named as an anomaly detection Kolmogorov-Arnold network (AD-KAN). Specifically, the algorithm can learn feature distribution of all normal sample points in an unsupervised manner, map the feature distribution to a high-dimensional space, and autonomously learn an early warning boundary through a minimum surrounding ellipsoid to realize early warning of afterburner oscillation combustion. In order to verify the feasibility of the method, a test is carried out on a certain type of turbofan aero-engine ground test bench, and the result shows that the AD-KAN method has excellent performance in precision, real-time performance, early warning performance and robustness. Therefore, the method has good early warning performance, and real-time early warning of aero-engine afterburner oscillation combustion can be effectively achieved.

The invention relates to the technical field of oil supply assemblies in afterburner components of aero-engines, in particular to a multi-channel distributed series finger-shaped oil supply header pipe and an afterburner. The multi-channel distributed series finger-shaped oil supply header pipe comprises a body, and a plurality of fuel oil channels are formed in the body; the upper end of the fuel oil channel penetrates through the top surface of the body; each fuel oil channel is correspondingly provided with a plurality of main fuel oil injection holes, the main fuel oil injection holes are communicated with the fuel oil channels, and the axes of the main fuel oil injection holes are perpendicular to the central axis of the body; the plurality of main fuel injection holes in each fuel channel are arranged at intervals from top to bottom; a plurality of bypass oil injection holes are formed in the position close to the main oil injection hole, and the bypass oil injection holes are communicated with the main oil injection hole through connecting holes; the main oil injection hole, the bypass oil injection hole and the connecting hole are all formed in the body.

According to the dual-fuel afterburner without the inner duct stabilizer, an oil injection rod and an air injection rod are arranged in a supporting plate with a cavity structure, an oil injection nozzle and an air injection nozzle which are communicated are formed in the wall face of the supporting plate, and cooperative combustion of gas fuel and liquid fuel is achieved. According to the afterburner, a stable ignition source is provided through the characteristic that gas fuel is easy to burn, efficient and stable combustion is achieved in cooperation with fuel injection, and therefore a traditional inner duct stabilizer is omitted, the weight of the afterburner is remarkably reduced, and weight reduction and performance optimization of the afterburner are achieved. Evaporative flame stabilizers distributed in the circumferential direction are arranged in the outer duct area to achieve stable combustion of airflow in the outer duct, and flame stability and cross flame performance are guaranteed in cooperation with the supporting plates of the inner duct and fuel gas sprayed out of the supporting plates.

The invention discloses an engine configuration using liquid hydrogen as a coolant and fuel and an overall design method, and relates to the field of aero-engines, and the engine configuration comprises an air inlet channel, a fan, a precooler, an air compressor, a main combustion chamber, a high-pressure turbine, a low-pressure turbine, a mixing chamber, an afterburner and an exhaust nozzle. Only the inner culvert airflow is cooled, on the basis of solving the difficulty of rotation limitation under the high Mach number working condition of the core engine, the problem of cooling capacity waste generated by precooling the outer culvert airflow is avoided, and the liquid hydrogen amount depends on the combustion amount needed by the main combustion chamber and the afterburner; therefore, the waste problem caused by the fact that the amount of liquid hydrogen needed by pre-cooling is larger than the amount of liquid hydrogen needed by combustion is avoided. According to the overall design of the engine, from the angle of flight / intake / launch integration, the size and performance parameters of an engine body are determined in a ground state based on the take-off task requirement of an aircraft, the size of an intake and exhaust system is determined in a cruise state based on the cruise task requirement of the aircraft, and a control rule is determined by the engine demand flow and the intake passage capture flow.

In order to solve the problem that an existing afterburner is difficult to give consideration to an efficient flame stabilizing function and low flow resistance loss, the afterburner based on the combined type pneumatic flame stabilizer comprises the combined type pneumatic flame stabilizer and a center cone, the combined type pneumatic flame stabilizer takes a support plate flame stabilizer as a carrier, and the center cone is arranged on the support plate flame stabilizer. And the pneumatic flame stabilizer is borne. Under the non-stress-application working condition, only the supporting plate flame stabilizer and the rear edge sudden-expansion type concave cavity in the center cone work, the supporting plate flame stabilizer serves as an on-duty flame stabilizer, and when the supporting plate flame stabilizer and the rear edge sudden-expansion type concave cavity work under the non-stress-application working condition, the blocking area can be effectively reduced, and the total pressure loss is reduced; and the total pressure recovery performance of the afterburner is improved. Under the stress application working condition, the supporting plate flame stabilizer, the rear edge sudden expansion type concave cavity and the pneumatic flame stabilizer act at the same time, and the low-loss and high-efficiency combustion organization mode of the afterburner is guaranteed. On the premise of meeting flame stability, the total pressure loss can be further reduced.

This invention discloses a high-disturbance spray boom structure based on plasma-excited coupled aerodynamically assisted atomization, relating to the field of afterburner technology for aero-engines. It includes: a shell with an air inlet; a fuel pipe with a fuel delivery channel; the fuel pipe extending into the shell and forming an air channel with it; a first insulating platform with a collision atomization zone and an atomization development zone; the first insulating platform is connected to the output end of the fuel pipe, and its neck has several fuel-gas atomization channels; a second insulating platform with a plasma discharge region; the second insulating platform is snapped into the first insulating platform; a high-voltage electrode located between the first and second insulating platforms; and a grounding electrode located between the second insulating platform and the shell. This invention employs the coupling of plasma excitation with aerodynamically assisted atomization and cross-collision to perform three consecutive actions on the fuel spray, thereby improving the fuel atomization performance of the high-disturbance spray boom.

The turbine-based combined ramjet engine is characterized in that the turbine-based combined ramjet engine comprises an inner culvert channel, and the inner culvert channel is provided with a core diffuser, a core engine, a low-pressure turbine, an afterburner and an injection spray pipe; the core diffuser, the core machine, the low-pressure turbine, the afterburner and the injection spray pipe are sequentially arranged in the airflow direction. The outer culvert channel surrounds the radial outer side of the inner culvert channel, the outer culvert channel is provided with a mode selection valve, an outer culvert diffuser, a ramjet combustion chamber and a single-side expansion spray pipe, and the mode selection valve, the outer culvert diffuser, the ramjet combustion chamber and the single-side expansion spray pipe are sequentially arranged in the airflow direction; the mode selection valve is used for controlling opening and closing of the outer culvert channel; and the supersonic through-flow fan is arranged on the upstream sides of the inner culvert channel and the outer culvert channel.

The invention relates to the technical field of aviation, and provides a component implicit afterburner which comprises a combustion chamber, a diffuser, a supporting plate, an inner cone, a mixer and a driving assembly, and the diffuser, the supporting plate, the inner cone, the mixer and the driving assembly are arranged in the combustion chamber; the diffuser is arranged on the top face of the supporting plate, and the diffuser and the top face of the combustion chamber form a first flow channel. The inner cone is arranged on the bottom surface of the support plate and forms a second flow channel with the bottom surface of the diffuser; the first flow channel and the second flow channel are respectively communicated with an inlet of the combustion chamber; the driving assembly is connected with the mixer and used for driving the mixer to be connected with the end, away from the inlet of the combustion chamber, of the diffuser or driving the mixer to be contained in the containing cavity, flow resistance is reduced, the mixer is prevented from being in a high-temperature environment for a long time, the service life of the mixer is prolonged, and reliability of the mixer is enhanced.

The invention discloses a waste heat utilization flue afterburning device and an afterburning method thereof, and belongs to the technical field of waste heat utilization, the waste heat utilization flue afterburning device comprises an air inlet pipe, the air inlet pipe is provided with a gas turbine air inlet and a fresh air inlet, and a fresh air adjusting valve is installed in the fresh air inlet; one end of the heating frame communicates with the air inlet pipe, and a flow equalizing plate, an afterburner and a heating pipeline are sequentially installed in the heating frame in the direction away from the air inlet pipe; the main chimney is located at the end, away from the air inlet pipe, of the heating frame and communicates with the heating frame through a communicating pipe and an air suction pipe, a first electric valve is installed in the communicating pipe, and a draught fan and a second electric valve are installed in the air suction pipe. And the waste heat boiler can be heated.

The present invention relates to a mixing device (10) for mixing at least anode exhaust gas (AEG) with cathode exhaust gas (CEG) from a fuel cell stack (110) of a fuel cell system (100), having a cathode exhaust gas line (30) with a cathode exhaust gas connection (32) for fluid-communicating connection with a cathode exhaust gas section (134) of a cathode section (130) of the fuel cell stack (110) and an anode exhaust gas line (20) with an anode exhaust gas connection (22) for fluid-communicating connection with an anode exhaust gas section (124) of an anode section (120) of the fuel cell stack (110), characterised in that the anode exhaust gas line (20) is arranged within the cathode exhaust gas line (30) and has a closed anode exhaust gas line end (24) and at least two anode exhaust gas outlets (21) into the cathode exhaust gas line (30) with outlet directions (OD) radial to the anode exhaust gas line axis (AEL) and to the cathode exhaust gas line axis (CEL), wherein, further downstream of the anode exhaust gas line end (24), the cathode exhaust gas line (30) transitions into a mixed exhaust gas line (40) with a mixed exhaust gas connection (42) for fluid-communicating connection with a burner inlet (152) of an afterburner (150) of a fuel cell system (100).

The invention relates to the technical field of aero-engines, and discloses an efficient thermal protection hybrid thermodynamic cycle combined engine and a control method thereof.The combined engine composed of an external rotary detonation engine and an internal turbine engine is adopted, and modal switching of the combined engine is achieved through an inlet adjusting valve and an adjustable exhaust nozzle; the working upper limit of a turbine engine can be effectively joined, power relay can be completed, so that a thrust gap is spanned, the structural design complexity is relatively low, the system stability is relatively high, and in a stress application rotating detonation mode, the reliability is high. Combustible mixtures sprayed by the rotary detonation engine are guided into the afterburner of the turbine engine through the afterburner diverter valve for detonation combustion, an original cooling device of the afterburner is used for thermal protection, and an outer casing is prevented from being damaged due to high temperature.

The invention discloses a design method for oil supply of a small and medium bypass ratio afterburner, which comprises the following steps of: acquiring environment index distribution of a flow field behind a mixer of the small and medium bypass ratio afterburner, and dividing a flow field area according to the environment index distribution to form n areas; the optimal residual air coefficient alpha optim and the air flow of the n areas are obtained; the optimal residual gas coefficient is the residual gas coefficient corresponding to the highest combustion efficiency under the conditions of certain temperature, pressure and oxygen content; according to the optimal residual air coefficient alpha i of the n areas and the air flow of the n areas, the stress application oil supply amount Wfi is distributed; wherein the optimal residual gas coefficient is close to the optimal residual gas coefficient alpha < optimal >. According to the technical scheme, the problems that the oil supply distribution plan of the afterburner with the small and medium bypass ratio cannot fully consider different environments of all areas of the combustion chamber, the optimal residual gas coefficients corresponding to combustion are different, and the oil supply amount of each area cannot be adaptively adjusted according to the change of the bypass ratio can be solved.

The invention discloses a main combustion chamber and afterburner integrated test platform and method, and belongs to the technical field of aero-engines. The integrated test platform comprises a main combustion chamber test section, a heat exchanger section, a back pressure valve section and an afterburner test section which are connected in sequence; the heat exchanger section comprises a heat exchange flange and a straight and straight mixing section which are coaxially connected; the heat exchange flange is provided with an air inlet pipe, an air collecting ring and a jet hole, external air is introduced into the straight mixing section through the jet hole, and the tail gas of the main combustion chamber and the external air are mixed and cooled and then input into the afterburner test section; the main combustion chamber test section and the afterburner test section are connected with the gas supply system, the oil supply system and the measurement and control system, the heat exchanger section is connected with the gas supply system and the measurement and control system, and the back pressure valve section is connected with the water supply system and used for cooperatively controlling test parameters. Decoupling between working conditions of the main combustion chamber and the afterburner is easier to realize, so that the working condition range of an integrated test of the main combustion chamber and the afterburner is widened.

To provide a cooking device capable of achieving improvement in combustibility of a grill burner and uniform grilling of an object to be cooked while improving a lamp black burning effect by an after burner.SOLUTION: An after burner is attached to the upper side of an exhaust duct in a posture in which a burning surface is directed downward. A control plate 61 is provided in a communication port between a grill chamber and the exhaust duct. The control plate 61 includes an opening part 63, a right closing part 64, a left closing part 65, a right half opening part 66, and a left half opening part 67. The opening part 63 is provided in the center of the control part 61 and opens the communication port. The right closing part 64 and the left closing part 65 are provided on both of the right and left end sides of the control plate 61, and close the communication port. The right half opening part 66 is provided between the right closing part 64 and the opening part 63, and the left half opening part 67 is provided between the left closing part 65 and the opening part 63. The right half opening part 66 and the left half opening part 67 close the lower half of the communication port and open the upper half.SELECTED DRAWING: Figure 9

The invention relates to the field of aero-engine afterburner tests, and discloses a fan-shaped afterburner inlet flow field simulation device and a control method thereof.The fan-shaped afterburner inlet flow field simulation device comprises a linkage ring, a knuckle bearing, a transmission cylinder and a servo electric cylinder, and the telescopic end of the servo electric cylinder stretches out and draws back in the axial direction of an afterburner and is used for driving the transmission cylinder to rotate through stretching out and drawing back; and the corresponding guide blades are driven by the linkage ring and the rocker arms of the other guide blades to rotate along the rotating shafts of the corresponding guide blades. Through the structural design of the servo electric cylinder and the transmission mechanism, the actual inlet flow field state of the fan-shaped afterburner is simulated, and particularly, the angle of the air inlet guide blade can be synchronously adjusted through continuous change, so that the test environment simulation of the fan-shaped afterburner with different air inlet cosine angles is realized; the fan-shaped afterburner inlet airflow cosine angle distribution is obtained, so that the test environment is closer to the real working environment, and the efficient development of the aero-engine afterburner performance test can be supported.

The invention provides a dual-fuel composite pre-cooling engine system based on jet flow / heat exchanger pre-cooling and a using method of the dual-fuel composite pre-cooling engine system, and relates to the field of aircraft engine systems. An air inlet channel, a fuel pump, a precooler, a jet device, an air compressor, a main combustion chamber, a turbine, an afterburner and an exhaust nozzle sequentially form an engine main body in the axial direction. According to the system, the characteristics of jet flow precooling and heat exchanger precooling are combined, liquid ammonia / kerosene dual-fuel layout is adopted, and a cooling working medium can realize conversion of precooling working places through a control valve according to precooling requirements, so that incoming flow air in different flight states is efficiently precooled; and the problems that a heat exchanger is large in precooling weight and flow resistance and a jet device is poor in precooling heat exchange effect are effectively solved. And finally, the system gives consideration to the simple jet flow pre-cooling structure and the high efficiency of heat exchanger pre-cooling, and the pre-cooling effect and the propelling performance of the pre-cooling engine are effectively improved.

The invention discloses a hydrogen and kerosene dual-fuel integrated support plate flame stabilizer, an afterburner and an aero-engine, and belongs to the technical field of aero-engine afterburners, the support plate flame stabilizer comprises a straight support plate body, the straight support plate body is arranged in the radial direction and is perpendicular to a flow path, and the straight support plate body is arranged in the radial direction; a plurality of hydrogen spraying holes and kerosene spraying holes are evenly distributed in the side face of the straight plate supporting plate body in the longitudinal direction, and a kerosene header pipe and a hydrogen header pipe are arranged in the straight plate supporting plate body. According to the hydrogen-kerosene dual-fuel integrated support plate flame stabilizer, the afterburner and the aero-engine, hydrogen-kerosene dual-fuel combustion can be coordinated, the combustion efficiency is improved, the temperature distribution is uniform, the structure is simple, and the weight is light.

The invention relates to the technical field of aviation, and provides an air-entraining cooling integrated assembly of an inner cone and a supporting plate diffusion oil injection stabilizer, the air-entraining cooling integrated assembly is applied to an afterburner and comprises a diffuser, a supporting plate and an inner cone which are arranged in the afterburner, the diffuser is arranged on the top face of the supporting plate, and a first flow channel is formed by the diffuser and the top face of the afterburner; the inner cone is arranged on the bottom surface of the support plate and forms a second flow channel with the bottom surface of the diffuser; the first flow channel and the second flow channel are respectively communicated with an inlet of the afterburner; and the diffuser, the support plate and the inner cone are integrally formed parts. According to the afterburner, the compactness and strength of the structure are improved, the interference and airflow separation phenomena among all parts are reduced, the flow loss in the afterburner is reduced, and therefore the performance and reliability of the whole engine are improved.

The invention discloses a rotating detonation afterburner based on centrifugal nozzle discrete injection, and belongs to the technical field of detonation propulsion. The combustion chamber comprises a gas collecting cavity, an injection unit, a centrifugal nozzle, an outer ring and an inner column, wherein an annular detonation combustion chamber is formed between the inner wall surface of the outer ring and the outer wall surface of the inner column. The centrifugal nozzles are uniformly arranged at the intersection of the gas collection cavity and the injection unit in the circumferential direction to realize primary atomization of the fuel oil; the air is accelerated by the injection unit from the air collection cavity and then is mixed with the atomized fuel oil, secondary atomization is achieved, the particle size of liquid drops is remarkably reduced, and the fuel activity and mixing uniformity are improved. The injection unit adopts a Laval nozzle profile, air is accelerated to supersonic speed in the injection unit, and pressure of a combustion chamber is prevented from being transmitted forwards. The rotary detonation engine is suitable for the high-temperature low-oxygen environment, supports the annular combustion chamber configuration and the empty cylinder combustion chamber configuration, can achieve stable rotary detonation detonation and propagation of liquid fuel and air, and provides technical support for engineering application of the rotary detonation engine.

The invention discloses a thrust augmentation type continuous detonation turbine engine. An afterburner is formed on the rear side of a rectification exhaust tail cone of the engine; the continuous detonation main combustion chamber consists of a shell and a central inner column which are coaxially arranged; a pre-explosion pipe, an air film cooling hole and a cold air mixing hole are formed in the shell; a fuel channel and a secondary air channel are arranged in the central inner column; a fuel swirler and a secondary air hole are arranged on the central inner column; the supporting plates are evenly distributed in the afterburner in the circumferential direction. A secondary inner column, a plane air ring and an annular protruding oil injection ring are arranged at the tail of the supporting plate. The annular protruding oil injection ring injects secondary fuel at high pressure in the axial direction, and the secondary fuel is mixed with tail gas of a combustion chamber for combustion. The plane air ring injects air in the axial direction, so that efficient mixing and combustion of fuel in the inner ring are achieved. According to the engine, a continuous detonation turbine engine and an afterburner are integrally designed, and the purpose of releasing a large amount of energy in a short time is achieved.

The invention discloses an afterburner adopting a gas-liquid bimodal-cross hole spray rod for oil supply, and relates to the technical field of aero-engines. Comprising a turbine located at the axis position of an inner duct in the air incoming flow direction; the mixer is arranged between the turbine and the inner duct wall body; the rectification support plates are provided with air inlet channels, and the multiple rectification support plates penetrate through the outer duct and are vertically and uniformly arranged in the circumferential direction of the inner duct; the oil injection rod is provided with an air flow channel and a fuel oil channel, and the air inlet channel is communicated with the air flow channel; and the oil injection rod is radially arranged in the rectification support plate. On the basis that the structural complexity of an afterburner of a turbine engine and a combustion chamber of a subsonic combustion ramjet engine is not increased, the atomization performance and the oil-gas mixing uniformity of fuel oil in the afterburner / ramjet combustion chamber are remarkably improved, the combustion efficiency of the engine is improved, and the combustion instability is reduced.

The present application belongs to the field of detonation turbine engine design, and is a device for separating detonation and afterburner airflow exhaust, comprising an inner nozzle, an outer nozzle, an inner regulating device, and an outer regulating device; when the detonation turbine engine is working, the high-temperature combustion gas in the afterburner combustion chamber enters the inner nozzle, the high-temperature combustion gas in the detonation combustion chamber enters the high-temperature combustion gas channel, and the outer cooling gas is divided into two streams and enters the first cooling channel and the second cooling channel respectively, cooling the wall surfaces of the outer nozzle and the inner nozzle. At the same time, the outer cooling gas in the first cooling channel and the second cooling channel enters the heat shield, so that the inner regulating device will not come into contact with the high-temperature combustion gas generated by the detonation combustion chamber, and at the same time, it is continuously cooled by the outer cooling gas, thereby minimizing the ambient temperature of the inner regulating device located in the outer high-temperature area, and effectively reducing the risk of ablation of the cylinder wall and the inner regulating device caused by the outer high-temperature area.

A PLC digital signal acquisition circuit of a nozzle force application regulator test bench comprises a communication converter ZHTX, a throttle lever servo motor drive controller SFDJ and a PLC, the communication converter ZHTX and the power supply end of the PLC are connected in parallel to a PLC power supply, the throttle lever servo motor drive controller SFDJ and the PLC power supply are connected in parallel to a power supply wiring terminal of a control cabinet, and the PLC power supply is connected in parallel to a power supply wiring terminal of the control cabinet. Analog quantity signals are collected through an RS485 serial port and converted into digital signals through a communication converter to be transmitted to an upper computer, so that the whole adjusting process can be monitored and controlled through one upper computer.

The invention belongs to the technical field of aero-engines, and particularly relates to a dual-mode afterburner outer culvert pneumatic area calculation method, which comprises the following steps: aiming at a conventional mode and an outer culvert throttling mode, respectively carrying out circulation section division on an outer culvert gas path of an afterburner; based on three-dimensional numerical simulation, resistance proportions of all sections of the outer culvert channel in the two modes are calculated respectively, and according to the resistance proportions, total pressure distribution of the outer culvert on-way channel is obtained; calculating the flow of each section based on the total pressure distribution and the given initial geometric area of each section, and iterating the final geometric area of each section meeting a flow rationality condition and an outlet static pressure balance condition according to the flow of each section; and according to the final geometric area and the flow of each section, calculating and determining the corresponding total pneumatic area of the external culvert in the two modes.

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

A kind of marine low-pressure selective catalytic reduction denitration system regeneration method utilizes marine engine supercharger front high-temperature exhaust waste heat, to heat up to ammonium bisulfate decomposition temperature point to SCR system, to realize the regeneration of SCR system.Supercharger front high-temperature exhaust gas is introduced into SCR reactor by exhaust gas bypass valve, and the flow of high-temperature exhaust gas can be changed by adjusting the opening of exhaust gas bypass valve according to the volume of catalyst in SCR reactor and the set regeneration temperature.The invention can save the traditional engine external afterburner, significantly reduce the floor area of SCR system, simplify the operation of SCR system, and realize the full utilization of engine exhaust waste heat utilization.

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.

The invention belongs to the technical field of aero-engines, and particularly relates to a dual-mode afterburner outer culvert channel system and a working method, the dual-mode afterburner outer culvert channel system comprises an outer culvert channel outer casing, an outer culvert channel inner casing and an outer culvert channel located between the outer culvert channel outer casing and the outer culvert channel inner casing, and the dual-mode afterburner outer culvert channel system further comprises a throttling device arranged at an inlet of the outer culvert channel and used for adjusting the area of the inlet of the outer culvert channel; the cold air flow dividing device is arranged on a flow dividing window of a casing in the outer culvert channel behind the throttling device and is used for adjusting the area of the flow dividing window; the driving control unit is connected with the throttling device and the cold air flow dividing device and is configured to drive the throttling device and the cold air flow dividing device to be switched between the opening state and the closing state so as to achieve different outer culvert channel circulation areas.

The invention discloses a multi-channel ion current detection circuit for an aero-engine pedestal. The multi-channel ion current detection circuit comprises a signal control box and a dual-channel real-time detection circuit, in each channel of the real-time detection circuit, the multi-gear ion current display circuit is connected to an ion current detection loop of the signal control box, and the ion current of the ion current detection loop in the signal control box is monitored in real time; in the threshold value display circuit and the multi-gear ion current threshold selection circuit which are connected in series, voltage division is realized through divider resistors which are connected in series at the front ends, adjustable resistors are connected in series on all voltage division paths, and all the voltage division paths which are connected in parallel and the adjustable resistors in the voltage division paths are connected to an ion current threshold value adjusting circuit of the signal control box. The ion current threshold value of the current threshold value adjusting circuit is set by adjusting the resistance value of the adjustable resistor in each voltage dividing path, and the voltage display of each voltage dividing resistor is realized through a voltmeter V1 connected with each voltage dividing resistor, so that the ion current threshold value set in the corresponding voltage dividing path is reflected through the display of the voltmeter V1. According to the technical scheme, the problems that an existing ionic current detection method cannot detect data of ionic current in an afterburner of an engine in real time, and the flame signal threshold value is difficult to adjust in the engine test run process are solved.

The invention belongs to the field of afterburners of aero-engines, and particularly relates to a cyclone nozzle of an afterburner. The cyclone nozzle comprises a nozzle body, a fuel oil channel and a gas channel are formed in the nozzle body, the fuel oil channel is provided with a fuel oil channel outlet, and a containing cavity located at the fuel oil channel outlet is formed in the nozzle body; the pressure difference floating seat is accommodated in the accommodating cavity; the fuel quantity control valve is fixedly installed on the nozzle body, located in the containing cavity and used for fuel flow control. The nozzle opening is formed in the nozzle main body, and the nozzle opening is communicated with the containing cavity through a nozzle opening channel; the cyclone channel is formed in the nozzle body, an air inlet of the cyclone channel is communicated with the air channel, and an air outlet of the cyclone channel is communicated with the nozzle channel.