CN114352436A - Metal powder fuel air-water cross-medium engine and control method thereof - Google Patents
Metal powder fuel air-water cross-medium engine and control method thereof Download PDFInfo
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- CN114352436A CN114352436A CN202111536392.XA CN202111536392A CN114352436A CN 114352436 A CN114352436 A CN 114352436A CN 202111536392 A CN202111536392 A CN 202111536392A CN 114352436 A CN114352436 A CN 114352436A
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Abstract
The invention provides a metal powder fuel air-water cross-medium engine and a control method thereof, wherein the engine has the capabilities of jumping water and air at multiple frequencies, flying at Ma 0-4.0 speed and working at high speed underwater. The metal powder fuel air-water cross-medium engine organically integrates air turbine rocket engine, sub-combustion ramjet engine and water-jet engine modes, can work in water and air medium through the adjustment of an engine runner, and can automatically switch the working modes according to the external environment, so that the engine has the working capacity of wide speed range and high performance.
Description
Technical Field
The invention belongs to the field of air-water cross-medium engines, and particularly relates to a metal powder fuel air-water cross-medium engine and a control method thereof.
Background
The ramjet engine is an air jet engine which works by using the deceleration and pressurization effects of high-speed air flow to complete pressurization combustion, and generally comprises an air inlet, a combustion chamber and a spray pipe. During flying, the air flow decelerates in the process of passing through the air inlet channel, the static pressure is raised, the pressurized air enters the combustion chamber to be mixed with fuel to be organized and combusted, and the generated high-temperature fuel gas is expanded and accelerated in the spray pipe and then is discharged to generate thrust.
The fuel specific impulse of the ramjet is far higher than that of the existing turbojet and compression-ignition ramjet, so that higher flight speed and flight height can be realized, and the space transportation cost is reduced.
At present, the disclosed metal fuel cross-medium engine mainly takes a solid grain as a propellant, comprises a solid stamping mode and a water stamping mode, and can only work under the supersonic speed condition, which is the inherent characteristic of the solid stamping engine, so that the flight speed range of the cross-medium engine is relatively limited; meanwhile, the adjustment capability of the solid fuel combustion in the solid fuel generator is limited, so that the adjustment range of characteristics of the engine such as thrust in the air and underwater is narrow, the engine cannot be guaranteed to work in a high specific impulse state, the range of the aircraft is influenced, and the task profile optimization of the aircraft is also influenced.
Disclosure of Invention
In order to solve the problems that an existing air-water cross-medium engine is limited in flight speed range and cannot meet requirements in performance, the invention provides a metal powder fuel air-water cross-medium engine which has the capabilities of jumping water and air in multiple frequencies, flying at Ma 0-4.0 speed and working at high speed underwater. The metal powder fuel air-water cross-medium engine organically integrates air turbine rocket engine, sub-combustion ramjet engine and water-jet engine modes, can work in water and air medium through the adjustment of an engine runner, and can automatically switch the working modes according to the external environment, so that the engine has the working capacity of wide speed range and high performance.
In order to achieve the purpose, the invention adopts the following technical scheme:
a metal powder fuel air-water cross-medium engine comprises an air inlet channel, an ATR core machine, an air inlet channel switching valve, a mixer, a combustion chamber, a water secondary jet injector, a spray pipe, a flame stabilizer, a stamping valve, a combustion chamber front valve, an air inlet channel and a fuel supply system; the air inlet channel is formed by an outer shell and an air inlet channel cone arranged at the front end in the outer shell and is used for capturing air; the air inlet channel switching valve is arranged at the front end of the ATR core machine and used for controlling air in the air inlet channel to enter the channel of the ATR core machine for combustion; the mixer is arranged at the rear end of the ATR core machine and used for mixing air and fuel gas; the combustion chamber and the spray pipe are arranged at the rear end of the outer shell and used for combusting the mixed air and fuel gas and generating thrust, and the flame stabilizer is arranged in the combustion chamber to realize fuel injection and flame stabilization; the secondary water jet injector is arranged between the combustion chamber and the spray pipe and is used for realizing the injection of seawater; the stamping valve is arranged at the rear end of the stamping flow channel and used for controlling air in the air inlet channel to enter the combustion chamber through the stamping flow channel; the combustion chamber front valve is arranged at the inlet end of the mixer and used for controlling gas in the ATR core machine to enter the mixer; the fuel supply system comprises a carbon dioxide gas cylinder, an electric explosion valve, an adjustable orifice plate and a metal powder storage tank which are sequentially connected, and the outlet of the metal powder storage tank is respectively connected with a gas generator and a combustion chamber of the ATR core machine; the carbon dioxide fluidizes the metal powder, and the flow rate of the fluidizing gas is controlled by an adjustable orifice plate; the flow rate of the metal powder is controlled by the rotation speed of a piston driving motor of the metal powder storage tank.
Further, the aircraft comprises a supercavity system and a water medium generator which are arranged on the air inlet cone, wherein the water medium generator is respectively connected with the fuel supply system and the water inlet channel, and the water medium generator and the supercavity system generate water medium supercavity which acts on the front end of the air inlet cone and is used for reducing the resistance of the aircraft.
Further, still include lubricating system, lubricating system is including the lubricating oil storage tank, lubricating pump and the lubrication pipeline that set gradually, the lubrication pipeline is connected with the lubricated oil circuit of intake duct electrohydraulic servo actuator, spray tube electrohydraulic servo actuator, ATR core machine respectively for supply lubricating oil for intake duct adjustment mechanism, ATR core machine and spray tube.
Furthermore, a filter and an energy accumulator are arranged on the lubricating pipeline, and an inflation valve is arranged on the energy accumulator.
Furthermore, an electromagnetic valve and a discharge valve are arranged on an outlet pipeline of the air inlet electrohydraulic servo actuator and the spray pipe electrohydraulic servo actuator.
Further, a filter and a pressure reducer are arranged between the electric explosion valve and the adjustable orifice plate.
Further, the spray pipe is a Laval spray pipe, and the size of the throat part of the spray pipe is adjusted according to the working condition of the engine.
Further, the metal powder in the metal powder storage tank is aluminum powder or magnesium powder.
The invention also provides a control method of the metal powder fuel air-water cross-medium engine, in an ATR (air transport reactor) working mode, the air is captured by the air inlet channel, the stamping flow channel is closed by the air inlet channel switching valve and the stamping valve, and the air enters the ATR core machine; burning fuel in a fuel gas generator of the ATR core machine to generate high-temperature fuel gas to push a turbine and a gas compressor of the ATR core machine to compress air; a front valve of the combustion chamber is opened, the compressed air and the gas after turbocharging are mixed in the mixer, the combustion is organized in the combustion chamber, and the conversion from internal energy to kinetic energy is realized through the spray pipe to generate thrust;
in a stamping working mode, air is captured by the air inlet channel, the channel of the ATR core machine is closed by the air inlet channel switching valve and the front valve of the combustion chamber, the stamping channel is opened by the stamping valve, the air enters the combustion chamber and is combusted with fuel tissues sprayed by the flame stabilizer, and the conversion of internal energy to kinetic energy is realized by gas through the spray pipe to generate thrust;
in a water-jet pressure working mode, a lip of an air inlet is closed, and a front valve and a stamping valve of a combustion chamber close an ATR core machine flow passage and a stamping flow passage; the front cone of the air inlet channel moves upstream to open the water inlet channel, and the water inlet channel captures seawater and improves the pressure of the seawater; seawater enters the combustion chamber to be combusted with fuel tissues sprayed by the flame stabilizer, and the gas realizes conversion from internal energy to kinetic energy through the spray pipe to generate thrust.
Compared with the prior art, the invention has the beneficial effects that:
1. the working speed range is wide, and the wide-range high-performance work is realized. The combined ramjet engine realizes the capability of subsonic, transonic and supersonic flight and underwater high-speed navigation by structural adjustment and pneumatic matching and one set of power system. The engine comprises an ATR mode, a sub-combustion stamping mode and a water jet stamping mode, the working Mach number range of the engine reaches 0-Ma4, the emission requirement can be reduced, and the engine can adapt to various complex task modes.
2. The engine performance is high. The engine adopts aluminum powder as a propellant, the propellant has high energy, and the engine comprises an adjustable air inlet channel, an adjustable spray pipe, an adjustable water inlet channel and a propellant adjusting system, so that the thrust and the working state of the engine can be flexibly adjusted, and the engine can work under the condition of higher specific impulse performance to the greatest extent and can improve the range of the aircraft.
3. High integration and high integration level. The ramjet combined engine has the advantages that the ATR engine with high thrust-weight ratio and high unit thrust, the ramjet engine with high altitude cruising performance and the water ram engine are highly integrated in pneumatic, structural, control and supply aspects, the three power forms are organically combined, the integrated design of thermodynamic cycle and structure is realized, the engine shares a core component and a subsystem, and the structure is compact. Meanwhile, the water inlet channel and the air inlet channel are integrated, and key components such as the air inlet channel, the spray pipe and the combustion chamber are shared, so that the overall structure is light in weight and simple in structure.
4. A unified propellant. The ramjet combined engine is different from the common ATR engine and water ram engine which respectively adopt a set of propellant system, and the invention adopts the propellant capable of reacting with air and water, thereby reducing the complexity and the structural weight of the supply system and realizing the integration of the supply system.
Drawings
FIG. 1 is a schematic structural diagram of a metal powder fuel air-water cross-medium engine according to the present invention;
FIG. 2 is a schematic structural diagram of an ATR working mode of the metal powder fuel air-water cross-medium engine;
FIG. 3 is a schematic structural diagram of a stamping mode of operation of the metal powder fuel air-water cross-medium engine according to the present invention;
FIG. 4 is a schematic structural diagram of a water-ram working mode of the metal powder fuel air-water cross-medium engine.
Reference numerals: 1-air inlet channel, 2-air inlet channel switching valve, 3-ATR core machine, 4-fuel supply system, 5-lubricating system, 6-mixer, 7-flame stabilizer, 8-combustion chamber, 9-water secondary jet injector, 10-spray pipe, 11-combustion chamber front valve, 12-water inlet channel, 13-outer shell, 14-air inlet channel cone, 15-punching flow channel, 16-front cone, 17-punching valve, 18-aqueous medium generator, 19-supercavity system, 41-carbon dioxide gas cylinder, 42-electric explosion valve, 43-adjustable orifice plate, 44-metal powder storage tank, 45-piston driving motor, 51-lubricating oil storage tank, 52-lubricating pump, 53-lubricating pipeline, 54-an air inlet electro-hydraulic servo actuator, 55-a spray pipe electro-hydraulic servo actuator, 56-a filter, 57-an energy accumulator and 58-an inflation valve.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood by those skilled in the art that these embodiments are only for explaining the technical principle of the present invention and are not intended to limit the scope of the present invention.
The invention provides a metal powder fuel air-water cross-medium engine and a control method thereof, the engine adopts gas fluidized high-energy metal powder as a propellant which reacts with water and air, and the engine has the characteristics of simple system and high density specific impulse.
As shown in fig. 1 to 4, the air-water cross-medium engine using metal powder fuel of the present invention includes an air intake duct 1, an ATR core 3, an air intake duct switching valve 2, a mixer 6, a combustion chamber 8, a water secondary jet injector 9, a nozzle 10, a flame stabilizer 7, a ram valve 17, a combustor front valve 11, an air intake duct 12, and a fuel supply system 4; the air inlet 1 is formed by an outer shell 13 and an air inlet cone 14 arranged at the front end in the outer shell 13 and used for capturing air; the ATR core machine 3 is arranged at the rear end inside the outer shell 13 and forms a stamping flow channel 15 with the outer shell 13, and the air inlet flow channel switching valve 2 is arranged at the front end of the ATR core machine 3 and is used for controlling air in the air inlet channel 1 to enter the flow channel of the ATR core machine 3 for compression pressurization and combustion; the mixer 6 is arranged at the rear end of the ATR core machine 3 and used for mixing air and fuel gas; the combustion chamber 8 and the spray pipe 10 are arranged at the rear end of the outer shell 13 and used for combusting the mixed air and fuel gas and generating thrust, and the flame stabilizer 7 is arranged in the combustion chamber 8 to realize fuel injection and flame stabilization; the secondary water jet injector 9 is arranged between the combustion chamber 8 and the spray pipe 10 and is used for realizing the injection of seawater; the stamping valve 17 is arranged at the rear end of the stamping flow channel 15 and is used for controlling the air in the air inlet channel 1 to enter the combustion chamber 8 through the stamping flow channel 15; the front valve 11 of the combustion chamber is arranged at the inlet end of the mixer 6 and is used for controlling the fuel gas in the ATR core machine 3 to enter the mixer 6; the water inlet channel 12 is arranged in the outer shell 13, one end of the water inlet channel 12 is connected with a front cone 16 of the air inlet channel cone 14, the other end of the water inlet channel is respectively connected with the mixed flow device 6 and the secondary water jet injector 9, and the front cone 16 can be moved to be opened, so that seawater enters the combustion chamber 8 through the water inlet channel 12 to be combusted.
The fuel supply system 4 comprises a carbon dioxide gas cylinder 41, an electric explosion valve 42, an adjustable pore plate 43 and a metal powder storage tank 44 which are connected in sequence, a filter and a pressure reducer are further arranged between the electric explosion valve 42 and the adjustable pore plate 43, and the outlet of the metal powder storage tank 44 is respectively connected with a gas generator and a combustion chamber 8 of the ATR core machine 3; the carbon dioxide fluidizes the metal powder, and the flow rate of the fluidizing gas is controlled by the adjustable orifice plate 43; the flow rate of the metal powder is controlled by the rotation speed of a piston driving motor 45 of the metal powder storage tank 44.
The engine of the invention adopts aluminum powder or magnesium powder fuel which can react with water and air, the carbon dioxide is used for fluidizing the aluminum powder, the flow of the fluidized gas is controlled by an adjustable orifice plate 43, and the flow of the aluminum powder is controlled by the rotating speed of a piston driving motor 45 of an aluminum powder storage tank. The mass ratio of the aluminum powder to the carbon dioxide can be adjusted by adjusting the flow of the carbon dioxide and the rotating speed of a piston driving motor 45 of the aluminum powder storage tank, so that the working condition adjustment of the gas generator and the aluminum powder content adjustment in the fuel can be realized to meet the working requirement of the engine.
The engine also comprises a supercavitation system 19 and an aqueous medium generator 18 which are arranged on the air inlet cone 14, wherein the aqueous medium generator 18 is respectively connected with the fuel supply system 4 and the water inlet channel 12, and the aqueous medium generator 18 and the supercavitation system 19 generate aqueous medium supercavitation which act on the front end of the air inlet cone 14 and are used for reducing the resistance of an aircraft.
The nozzle 10 is a laval nozzle 10, and the size of the throat is adjusted according to the working condition of the engine to enable the engine to be in high performance.
The engine also comprises a lubricating system 5, wherein the lubricating system 5 comprises a lubricating oil storage tank 51, a lubricating pump 52 and a lubricating pipeline 53 which are sequentially arranged, and the lubricating pipeline 53 is respectively connected with lubricating oil paths of an air inlet channel electrohydraulic servo actuator 54, a spray pipe electrohydraulic servo actuator 55 and the ATR core machine 3 and is used for providing lubricating oil for the air inlet channel 1 adjusting mechanism, the ATR core machine 3 and the spray pipe 10. The lubricating pipeline 53 is provided with a filter 56 and an energy accumulator 57, and the energy accumulator 57 is provided with an inflation valve 58. In addition, solenoid valves and bleed valves are provided on the outlet lines of the intake duct electro-hydraulic servo actuator 54 and the nozzle electro-hydraulic servo actuator 55.
As shown in fig. 2, in the ATR operation mode, the air intake duct 1 functions to capture air, and the air intake duct switching valve 2 and the ram valve 17 close the ram flow duct 15 to allow air to enter the ATR core 3; fuel (namely metal powder) is combusted in a fuel gas generator of the ATR core machine 3 to generate high-temperature fuel gas to push a turbine and a compressor of the ATR core machine 3 to compress air; the compressed air and the gas after turbocharging are mixed in the mixer 6 and are organized and combusted in the combustion chamber 8, and the conversion from internal energy to kinetic energy is realized through the nozzle 10 to generate thrust.
As shown in fig. 3, in the ram operation mode, the air inlet 1 plays a role of capturing air, the air inlet channel switching valve 2 and the combustor front valve 11 close the flow channel of the ATR core 3, the ram valve 17 opens the ram flow channel 15, so that air enters the combustor 8 and is combusted with the fuel tissue sprayed by the flame stabilizer 7, the flame stabilizer 7 plays a role of fuel injection and flame stabilization, and the gas realizes conversion from internal energy to kinetic energy through the spray pipe 10 to generate thrust.
As shown in fig. 4, in the water hammer operation mode, the lip of the intake port 1 is closed, and the pre-combustor valve 11 and the ram valve 17 close the flow passage and the ram flow passage 15 of the ATR core 3. A front cone 16 of the air inlet channel 1 moves upstream to open the water inlet channel 12, and the water inlet channel 12 captures seawater and improves the pressure of the seawater; seawater enters the combustion chamber 8 to be combusted with fuel tissues sprayed by the flame stabilizer 7, the flame stabilizer 7 plays roles in fuel injection and flame stabilization, and gas realizes conversion from internal energy to kinetic energy through the spray pipe 10 to generate thrust.
The engine can realize the air-water cross-medium work and has wide working speed range. The engine has the working capacity of crossing media in empty water by effectively combining an ATR engine suitable for climbing and accelerating, a ramjet engine with higher cruising specific impulse and a water-jet engine suitable for underwater high-speed cruising; the working aerial flight Mach number is 0-Ma4.0, and the underwater speed is 0-100 m/s.
The engine of the invention is highly integrated. The engine uses a fuel that reacts with both water and air and a charge gas (fluidizing gas), greatly simplifying the propulsion supply system.
The engine has high performance. The metal powder fuel is a fuel with higher calorific value in the fuel capable of reacting with water at present, has higher specific impulse compared with the traditional solid propellant and higher density specific impulse compared with the liquid propellant, has higher performance in the air and under the water of the engine, and can promote the flying range and the underwater range of the medium-crossing torpedo.
The operation modes of the metal powder fuel air-water cross-medium engine of the invention are described in detail below, and specifically include an air operation mode, a water inlet operation mode, a water under operation mode and a water outlet operation mode.
1) Aerial mode of operation
After the aircraft is separated from the airplane, the attitude is adjusted, the information processing system sends an engine propellant supply system starting instruction according to the flight state, and then sends an ignition pre-order to the engine; opening an air path of the engine, adjusting the positions of the air inlet 1 and the spray pipe 10 according to the flight state and the thrust requirement, and establishing normal air flow; the electric explosion valve 42 is detonated, carbon dioxide passes through a pressure reducer and a filter filling pipeline and a lubricating oil storage tank 51, a lubricating oil circuit lubricating pump 52 is started, the lubricating oil flow is controlled by the rotating speed of a lubricating motor, and the air inlet 1 and the spray pipe 10 are adjusted to the positions required by an ATR mode by the electro-hydraulic servo actuators of the air inlet adjusting mechanism and the spray pipe adjusting mechanism.
When the air inlet channel 1 and the spray pipe 10 are adjusted in place, a carbon dioxide main valve in front of the gas generator is opened, and an adjustable orifice plate 43 of the channel is adjusted to meet the supply flow of carbon dioxide; and opening a fluidizing gas main valve of the aluminum powder storage tank, starting the aluminum powder storage tank to drive a piston motor, and adjusting the rotating speed of the motor according to the instruction of the controller to meet the flow supply requirement of the aluminum powder. The igniter is started, carbon dioxide and aluminum powder are ignited, high-temperature gas drives a turbine of the ATR core machine 3, the ATR core machine 3 is started, the gas after the turbine is mixed with the pressurized air and is combusted, and the conversion of heat energy to kinetic energy is achieved through the spray pipe 10. In the ATR mode working process, the engine controller adjusts the rotating speed of the carbon dioxide adjustable orifice plate 43 and the aluminum powder storage tank piston driving motor 45 according to the thrust requirement and flight parameters provided by the aircraft controller to realize the working condition adjustment of the fuel gas generator; and simultaneously, electro-hydraulic servo actuators of the adjusting system of the air inlet channel 1 and the adjusting system of the spray pipe 10 adjust the profiles of the air inlet channel 1 and the spray pipe 10 in real time.
When the flight Mach number reaches Ma2.5, the engine enters a mode conversion process, the valve of the air inlet channel 1 gradually opens the stamping flow path, air simultaneously enters the ATR flow path and the stamping flow path 15, the stop valve in front of the aluminum powder path of the stamping flow path 15 is opened, the igniter is powered on, the stamping flow path 15 is ignited, when the stamping flow path 15 can normally work and provides necessary thrust, the aluminum powder path stop valve in front of the gas generator is closed firstly, carbon dioxide is blown off to the gas generator, then the carbon dioxide path stop valve is closed, and the ATR flow path is closed.
After the ram engine is relayed, cruising at a higher specific impact performance, resolving the flow of the aluminum powder by the engine according to the flight parameters provided by a flight control system, and adjusting the rotating speed of a piston driving motor 45 of the aluminum powder storage tank to realize the adjustment of the flow of the aluminum powder; meanwhile, the electro-hydraulic servo actuator adjusts the profile of the engine, so that the engine can achieve thrust required by flight and keep higher performance.
2) Working mode in water
When the aircraft reaches a preset target position or the aircraft needs to enter water, the aircraft starts to press down, and the height and the flying speed are reduced. The engine controls the mode conversion according to the flight parameters provided by the flight control system, when the flight Mach number is reduced to Ma2.7, an ATR flow path of the air inlet channel 1 is gradually opened, the gas generator is ignited, and the ATR mode is started; when the flight Mach number is reduced to Ma2.5, a front valve of an aluminum powder injector of a ram path is closed, a ram air flow channel is closed, and the ATR engine is completely relayed; the engine adjusts the working condition of the gas generator, the profile of the inlet 1 and the throat of the nozzle 10 according to the thrust required by the aircraft; before entering water, the aircraft adjusts the posture, slides on the water surface, closes the ATR engine and the gas path flow channel, simultaneously opens the water inlet channel 12, uses the sliding speed to pressurize the water, the water sprayed into the combustion chamber 8 and the aluminum powder tissue sprayed into the injector are combusted, the high temperature gas is sprayed into the water from the spray pipe 10 to generate thrust; meanwhile, the gas generated by the reaction of the aqueous medium propellant and water in the gas generator generates the supercavity, and the gas generated by the aqueous medium generator 18 generates the aqueous medium supercavity and is arranged at the cone tip, so that the resistance of the aircraft is reduced by the supercavity technology.
3) Underwater mode of operation
In the underwater cruising process, the aircraft controls the cruising depth by adjusting the posture and the airfoil surface, the thrust of the engine is controlled by adjusting the flow of aluminum powder and the supply amount of water, the flow of the aluminum powder is adjusted by the rotating speed of a piston driving motor 45 of the aluminum powder storage tank, and the water flow is adjusted by a flow resistance element arranged in the water inlet channel 12.
4) Water outlet working mode
When the aircraft needs to discharge water, the aircraft discharges water at a small angle, and a water inlet is ensured to be below the water surface and an air inlet is ensured to be above the water surface. After the aircraft is out of water, the aircraft resistance is obviously reduced, the supercavitation air supply pipe valve is closed, and the aircraft slides on the water surface for acceleration; in the process, an air path of the engine is opened, the positions of an air inlet 1 and a spray pipe 10 are adjusted according to the flight state and the thrust requirement, normal flow is established, an aluminum powder and carbon dioxide main valve in front of a gas generator is opened, a propellant enters the gas generator to generate high-temperature gas, the gas drives an ATR core machine 3 to start, and an igniter ignites a afterburning chamber; after the speed and the thrust of the aircraft meet the takeoff requirement, the aircraft takes off and is separated from the water surface, the water-jet pressure flow passage 15 is closed, and the ATR engine pushes the aircraft to climb and cruise in an accelerating mode.
In the flight process, water inlet and outlet processes can be carried out for several times, and the working processes of the engine are basically consistent. After the aircraft enters water for the last time, the aircraft carries out an attack task, the cruising depth and speed are adjusted, and the flow of aluminum powder and the inflow of water are adjusted by the engine according to instructions, so that the thrust requirement is met.
Claims (9)
1. A metal powder fuel air-water cross-medium engine is characterized in that: the device comprises an air inlet channel (1), an ATR core machine (3), an air inlet channel switching valve (2), a mixer (6), a combustion chamber (8), a secondary water jet injector (9), a spray pipe (10), a flame stabilizer (7), a stamping valve (17), a front valve (11) of the combustion chamber, an air inlet channel (12) and a fuel supply system (4);
the air inlet (1) is formed by an outer shell (13) and an air inlet cone (14) arranged at the front end in the outer shell (13) and used for capturing air;
the ATR core machine (3) is arranged at the rear end inside the outer shell (13) and forms a stamping flow channel (15) with the outer shell (13), and the air inlet flow channel switching valve (2) is arranged at the front end of the ATR core machine (3) and is used for controlling air in the air inlet channel (1) to enter the flow channel of the ATR core machine (3) for combustion;
the mixer (6) is arranged at the rear end of the ATR core machine (3) and is used for mixing air and fuel gas; the combustion chamber (8) and the spray pipe (10) are arranged at the rear end of the outer shell (13) and used for combusting mixed air and fuel gas and generating thrust, and the flame stabilizer (7) is arranged in the combustion chamber (8) to realize fuel injection and flame stabilization;
the secondary water jet injector (9) is arranged between the combustion chamber (8) and the spray pipe (10) and is used for spraying seawater;
the stamping valve (17) is arranged at the rear end of the stamping flow channel (15) and is used for controlling air in the air inlet channel (1) to enter the combustion chamber (8) through the stamping flow channel (15); the combustion chamber front valve (11) is arranged at the inlet end of the flow mixer (6) and is used for controlling gas in the ATR core machine (3) to enter the flow mixer (6);
the water inlet channel (12) is arranged in the outer shell (13), one end of the water inlet channel (12) is connected with a front cone (16) of the air inlet channel cone (14), the other end of the water inlet channel is respectively connected with the mixer (6) and the secondary water jet injector (9), and the front cone (16) can be moved to be opened, so that seawater enters the combustion chamber (8) through the water inlet channel (12) to be combusted;
the fuel supply system (4) comprises a carbon dioxide gas cylinder (41), an electric explosion valve (42), an adjustable orifice plate (43) and a metal powder storage tank (44) which are sequentially connected, and the outlet of the metal powder storage tank (44) is respectively connected with a fuel gas generator and a combustion chamber (8) of the ATR core machine (3);
the carbon dioxide fluidizes the metal powder, and the flow rate of the fluidizing gas is controlled by an adjustable orifice plate (43); the flow rate of the metal powder is controlled by a piston drive motor (45) of the metal powder storage tank (44).
2. The air-water cross-medium engine with metal powder fuel as claimed in claim 1, characterized in that: the aircraft is characterized by further comprising a supercavitation system (19) and an aqueous medium generator (18) which are arranged on the air inlet cone (14), wherein the aqueous medium generator (18) is respectively connected with the fuel supply system (4) and the water inlet channel (12), and the aqueous medium generator (18) and the supercavitation system (19) generate aqueous medium supercavitation and act on the front end of the air inlet cone (14) to reduce the resistance of the aircraft.
3. The air-water cross-medium engine with metal powder fuel as claimed in claim 1, characterized in that: still include lubricating system (5), lubricating system (5) are including lubricating oil storage tank (51), lubricating pump (52) and the lubricated pipeline (53) that set gradually, lubricated pipeline (53) are connected with the lubricated oil circuit of intake duct electric liquid servo actuator (54), spray tube electric liquid servo actuator (55), ATR core machine (3) respectively for supply air inlet duct adjustment mechanism, ATR core machine (3) and spray tube (10) and provide lubricating oil.
4. The air-water cross-medium engine with metal powder fuel as claimed in claim 3, characterized in that: the lubricating pipeline (53) is provided with a filter (56) and an energy accumulator (57), and the energy accumulator (57) is provided with an inflation valve (58).
5. The air-water cross-medium engine with metal powder fuel as claimed in claim 4, characterized in that: and the outlet pipelines of the air inlet electro-hydraulic servo actuator (54) and the spray pipe electro-hydraulic servo actuator (55) are provided with electromagnetic valves and discharge valves.
6. The air-water cross-medium engine of any one of claims 1 to 5, characterized in that: a filter and a pressure reducer are further arranged between the electric explosion valve (42) and the adjustable orifice plate (43).
7. The air-water cross-medium engine of claim 6, characterized in that: the jet pipe (10) is a Laval jet pipe, and the size of the throat part is adjusted according to the working condition of the engine.
8. The air-water cross-medium engine of claim 7, characterized in that: the metal powder in the metal powder storage box (44) is aluminum powder or magnesium powder.
9. A control method of the metal powder fuel air-water cross-medium engine according to any one of claims 1 to 8, characterized in that:
in an ATR working mode, the air inlet channel (1) captures air, the air inlet channel switching valve (2) and the stamping valve (17) close the stamping flow channel (15), and the air enters the ATR core machine (3); burning fuel in a fuel gas generator of the ATR core machine (3) to generate high-temperature fuel gas to push a turbine and a compressor of the ATR core machine (3) to compress air; a front valve (11) of the combustion chamber is opened, compressed air and gas after turbocharging are mixed in a mixer (6) and are organized and combusted in the combustion chamber (8), and conversion from internal energy to kinetic energy is realized through a spray pipe (10) to generate thrust;
in a stamping working mode, air is captured by the air inlet channel (1), the air inlet channel switching valve (2) and the combustion chamber front valve (11) close a channel of the ATR core machine (3), the stamping valve (17) opens the stamping channel (15), so that air enters the combustion chamber (8) and is combusted with fuel tissues sprayed by the flame stabilizer (7), and gas realizes conversion from internal energy to kinetic energy through the spray pipe (10) to generate thrust;
in a water-flushing working mode, a lip of the air inlet channel (1) is closed, and a front valve (11) and a stamping valve (17) of the combustion chamber close a flow channel and a stamping flow channel (15) of the ATR core machine (3); a front cone (16) of the air inlet channel (1) moves upstream to open the water inlet channel (12), and the water inlet channel (12) captures seawater and increases the pressure of the seawater; seawater enters the combustion chamber (8) to be combusted with fuel tissues sprayed by the flame stabilizer (7), and gas realizes conversion from internal energy to kinetic energy through the spray pipe (10) to generate thrust.
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| CN202111536392.XA CN114352436B (en) | 2021-12-15 | 2021-12-15 | Metal powder fuel air-water cross-medium engine and control method thereof |
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| CN114810426A (en) * | 2022-04-26 | 2022-07-29 | 中国人民解放军国防科技大学 | Two-stage water inlet cyclone combustion chamber and combustion organization method |
| CN115107968A (en) * | 2022-06-13 | 2022-09-27 | 南昌航空大学 | Low-navigation-speed underwater ramjet engine and design method thereof |
| CN115479508A (en) * | 2022-09-01 | 2022-12-16 | 华中科技大学 | Self-starting turbine water flushing combined engine based on fuel gas generator driving |
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