CN114810425A - Variable-thrust underwater ultrahigh-speed navigation body - Google Patents
Variable-thrust underwater ultrahigh-speed navigation body Download PDFInfo
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- CN114810425A CN114810425A CN202210447143.1A CN202210447143A CN114810425A CN 114810425 A CN114810425 A CN 114810425A CN 202210447143 A CN202210447143 A CN 202210447143A CN 114810425 A CN114810425 A CN 114810425A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/70—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using semi- solid or pulverulent propellants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T70/00—Maritime or waterways transport
- Y02T70/10—Measures concerning design or construction of watercraft hulls
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Abstract
The invention discloses a variable thrust underwater ultra-high speed navigation body, which comprises a fluidized gas source, a gas generator, a powder supply system, a water-flushed engine combustion chamber and a tail nozzle, wherein the fluidized gas source is connected with the gas generator; the head of the shell is provided with a cavitator connected with a fluidizing gas source, and the gas generator and the powder supply system are respectively communicated with a combustion chamber of the water-jet engine; the outer wall of the shell is provided with a first water inlet, the combustion chamber of the water-thrust engine is connected with the first water inlet, and the tail spray pipe is arranged at the tail part of the shell and is communicated with an outlet of the combustion chamber of the water-thrust engine. The invention is applied to the field of underwater high-overspeed propulsion and supercavitation drag reduction, realizes the active regulation of thrust by regulating the mass flow of powder fuel entering a combustion chamber, combines the supercavitation drag reduction technology with the powder fuel water-thrust engine technology to realize underwater high-speed navigation with variable thrust, has the advantages of high specific thrust, small volume, high reliability, convenient use and maintenance and the like, and can realize the technical difficulties of underwater ultrahigh-speed cruise, adjustable thrust and the like.
Description
Technical Field
The invention relates to the technical field of underwater high-overspeed propulsion and supercavitation drag reduction, in particular to a variable-thrust underwater ultrahigh-speed navigation body.
Background
With the progress of the naval vessel navigation technology, the speed advantage of the conventional underwater vehicle to the naval vessel is smaller and smaller, the combat efficiency is weakened day by day, and the development of the underwater vehicle is severely restricted.
The appearance of the ultra-high-speed underwater vehicle breaks through the conventional appearance, the head of the ultra-high-speed underwater vehicle is additionally provided with the blunt-head-shaped cavitator with a sharp edge, the surface cavitation of the vehicle is induced in the motion process, the supercavitation wrapping the whole underwater vehicle is formed, the solid-liquid boundary separation is realized, and the frictional resistance in the underwater vehicle is greatly reduced. The application of the supercavitation technology obviously reduces underwater navigation resistance on one hand, and on the other hand, due to the influence of cavitation bubble wrapping and complex multi-phase flow, the efficiency of a traditional underwater propeller propulsion system is greatly reduced, and a power device of an ultrahigh-speed underwater vehicle has the characteristic of small dependence on external flow field conditions. The water-jet engine belongs to a jet propulsion system, adopts high-metal content fuel and utilizes seawater as an oxidant, has the advantages of high energy density, simple structure, good safety and the like, can reach more than 2 times of that of the traditional solid rocket engine, and is an ideal power system of an ultrahigh-speed underwater vehicle, but the conventional solid medicine column type water-jet engine is difficult to realize the active regulation of the thrust.
The powder fuel water-thrust engine can realize active regulation of thrust by regulating the mass flow of the powder fuel entering the combustion chamber, so that the variable-thrust underwater high-speed navigation can be realized by combining the supercavitation drag reduction technology and the powder fuel water-thrust engine technology.
Disclosure of Invention
Aiming at the defects in the prior art, the invention provides a variable-thrust underwater ultrahigh-speed navigation body, which can realize the active regulation of thrust by regulating the mass flow of powder fuel entering a combustion chamber, can realize the underwater high-speed navigation with variable thrust by combining a supercavitation drag reduction technology and a powder fuel water-thrust engine technology, has the advantages of higher specific thrust, small volume, high reliability, convenient use and maintenance and the like, and can realize the technical difficulties of underwater ultrahigh-speed cruise, adjustable thrust and the like.
In order to achieve the purpose, the invention provides a variable-thrust underwater ultra-high-speed navigation body which comprises a shell, and a fluidized gas source, a gas generator, a powder supply system, a water-thrust engine combustion chamber and a tail nozzle which are arranged in the shell;
the head of the shell is provided with a cavitator, the cavitator is connected with the fluidization gas source, the gas output end of the gas generator and the powder output end of the powder supply system are respectively communicated with the inlet of the combustion chamber of the water-jet engine, and the powder output end of the powder supply system is communicated with the fluidization gas source;
the water jet engine comprises a shell, a water jet engine combustion chamber, a tail nozzle and a water jet pipe, wherein a first water inlet is formed in the outer wall of the shell, the water jet engine combustion chamber is connected with the first water inlet, and the tail nozzle is arranged at the tail of the shell and is communicated with an outlet of the water jet engine combustion chamber.
In one embodiment, the powder supply system, the gas generator and the water-thrust engine combustion chamber are sequentially arranged in the shell along the axial direction of the shell;
the fuel gas generator is connected with the combustion chamber of the water-jet engine through a heat insulation layer baffle, a high-temperature fuel gas inlet and a powder fuel inlet are formed in the heat insulation layer baffle, and a fuel gas output end of the fuel gas generator is communicated with an inlet of the combustion chamber of the water-jet engine through the high-temperature fuel gas inlet;
the gas generator is of an annular structure, a powder pipeline is connected to the powder output end of the powder supply system, and the powder pipeline penetrates through the gas generator and then is communicated with the powder fuel inlet.
In one embodiment, the powder supply system comprises a driving gas source and a powder fuel storage tank which are arranged in the shell in sequence;
the powder fuel storage tank is internally provided with a driving air source, the driving air source is communicated with one end of the powder fuel storage tank, and the other end of the powder fuel storage tank is the powder output end of the powder supply system.
In one embodiment, the pulverized fuel inlet is provided with a swirl bluff body to disperse the pulverized fuel.
In one embodiment, the aft portion of the housing is further provided with a plurality of booster engines, each of which surrounds the jet nozzle.
In one embodiment, the shell is further provided with a puncture tail rudder.
In one embodiment, a water flow controller is further arranged in the shell, and a second water inlet communicated with the inside of the water-thrust engine combustion chamber is formed in the water-thrust engine combustion chamber;
the water inlet end of the water flow controller is communicated with the first water inlet, and the water outlet end of the water flow controller is communicated with the second water inlet.
In one embodiment, the combustion chamber of the water-pressure engine comprises a double-stage water inlet cyclone and a combustion chamber main body, wherein the double-stage water inlet cyclone is arranged at the inlet end of the combustion chamber main body;
a fuel channel is arranged in the double-stage water inlet swirler, one end of the fuel channel is respectively communicated with a gas output end of the gas generator and a powder output end of the powder supply system, and the other end of the fuel channel is communicated with the combustion chamber main body;
the wall surface of the fuel channel close to the downstream is of a sandwich structure with a diversion trench;
the side part of the two-stage water inlet cyclone is provided with a plurality of first-stage rotational flow water inlet channels and second-stage rotational flow water inlet channels, the inlet end of each first-stage rotational flow water inlet channel and the inlet end of each second-stage rotational flow water inlet channel are communicated with the second water inlet, the outlet end of each first-stage rotational flow water inlet channel is communicated with the wall surface of the inlet of the fuel channel, and the outlet end of each second-stage rotational flow water inlet channel is communicated with the wall surface of the diversion trench;
the primary rotational flow water inlet channels are circumferentially distributed on the two-stage water inlet cyclone at the same angle, the secondary rotational flow water inlet channels are circumferentially distributed on the two-stage water inlet cyclone at the same angle, and the rotational direction of the primary rotational flow water inlet channels is opposite to that of the secondary rotational flow water inlet channels.
In one embodiment, the midstream section of the fuel passage is a venturi structure, or the upstream section and the midstream section of the fuel passage are venturi structures;
the diversion trench is sleeved at the tail section of the venturi structure, and the outlet of the diversion trench is flush with the outlet end of the venturi structure.
In one embodiment, the combustion chamber body is a sandwich structure having an outer wall and an inner wall;
a water inlet interlayer is arranged between the outer wall and the inner wall, and the second water inlet is arranged on the outer wall at a position corresponding to the midstream or the downstream of the combustion chamber of the water-jet engine;
the double-stage water inlet cyclone is embedded into the outer wall and then connected with the outer wall and the inner wall, and the inlet end of the first-stage rotational flow water inlet channel and the inlet end of the second-stage rotational flow water inlet channel are both positioned in the water inlet interlayer.
The variable-thrust underwater ultra-high-speed navigation body can realize underwater quick start and enter an ultra-high-speed cruise stage in a very short time; the ultra-high speed cruising can be realized through a water-flushing engine based on powdered fuel in the ultra-high speed cruising stage; the active adjustment of the thrust can be realized through water flow control and powder supply control in the ultra-high speed cruising stage; the supercavitation state can be realized in the whole navigation process, the gas in the fluidized gas source is introduced into the cavitator to realize supercavitation navigation in the initial working stage of the navigation body, and when the navigation body enters the ultrahigh-speed cruise stage, the navigation body realizes supercavitation navigation through natural cavitation. The navigation body has the advantages of high specific impulse, small volume, high reliability, convenient use and maintenance and the like, and can realize the technical difficulties of underwater ultrahigh-speed cruising, adjustable thrust and the like.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a cross-sectional view showing the overall structure of a navigation body according to an embodiment of the present invention;
FIG. 2 is a partial cross-sectional view of the water-injected engine at the inlet of the combustion chamber in an embodiment of the present invention;
FIG. 3 is an isometric view of a dual stage water inlet cyclone in an embodiment of the present invention;
FIG. 4 is an axial cross-sectional view of a dual stage water inlet cyclone in an embodiment of the present invention;
FIG. 5 is a radial cross-sectional view of a dual stage hydrocyclone in accordance with an embodiment of the present invention at the location of the primary hydrocyclone inlet passage;
FIG. 6 is a radial cross-sectional view of a dual stage hydrocyclone in accordance with an embodiment of the present invention at the location of the secondary cyclone inlet passage.
Reference numerals: the device comprises a shell 1, a fluidization gas source 2, a gas generator 3, a water-jet-propelled engine combustion chamber 4, a tail nozzle 5, a water flow controller 6, a boosting engine 7, a puncture tail vane 8, a driving gas source 9, a powder fuel storage tank 10, a cavitator 11, a ventilation and pressurization device 12, a first ventilation pipeline 13, a second ventilation pipeline 14, a heat-insulating layer baffle 15, a high-temperature gas inlet 16, a powder fuel inlet 17, a powder pipeline 18 and a piston plate 19, the device comprises a third through air pipeline 20, a fourth through air pipeline 21, a first water inlet 22, a second water inlet 23, a first water pipeline 24, a second water pipeline 25, a double-stage water inlet cyclone 26, a cyclone bluff body 27, an outer wall 28, an inner wall 29, a water inlet interlayer 30, a first-stage cyclone water inlet channel 31, a second-stage cyclone water inlet channel 32, an equal straight section 33, a venturi structure 34, a sleeve section 35, a diversion trench 36, a load part 37 and a master control cabin 38.
The implementation, functional features and advantages of the present invention will be further described with reference to the accompanying drawings.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; the connection can be mechanical connection, electrical connection, physical connection or wireless communication connection; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
Fig. 1-6 show a variable thrust underwater ultra-high speed vehicle disclosed in this embodiment, which includes a housing 1, and a fluidized gas source 2, a gas generator 3, a powder supply system, a water-thrust engine combustion chamber 4, a tail nozzle 5, a water flow controller 6, a booster engine 7, and a piercing tail vane 8, which are disposed in the housing 1, wherein the powder supply system is composed of the fluidized gas source 2, a driving gas source 9, a powder fuel storage tank 10, a powder pipeline 18, and a swirl bluff body 27. The water flow controller 6, the fluidizing gas source 2, the driving gas source 9, the powder fuel storage tank 10, the gas generator 3, the water-jet-compression engine combustion chamber 4 and the tail nozzle 5 are sequentially arranged in the shell 1 along the axial direction of the shell 1, and the outlet end of the tail nozzle 5 is positioned at the tail end of the shell 1. The number of the booster engines 7 is plural, and each booster engine 7 is wound around the jet nozzle 5 for accelerating the vehicle to a high-speed running state in a short time. The puncture tail rudder 8 is arranged at the side part of the shell 1, and the puncture tail rudder 8 can generate fluid force and moment required by motion control under water, and is an important control mechanism for underwater navigation. The variable thrust underwater super-speed navigation body utilizes the puncture tail vane 8 to penetrate through a cavity boundary to maintain a relatively stable wetting surface, so that corresponding fluid control force and torque are generated.
The fluidizing gas source 2 is a gas tank for storing fluidizing gas, the head of the shell 1 is provided with a cavitator 11, and the cavitator 11 is communicated with the fluidizing gas source 2. Specifically, a ventilation and pressurization device 12 is further arranged in the housing 1, the fluidization gas source 2 is communicated with the input end of the ventilation and pressurization device 12 through a first ventilation pipeline 13, and the ventilation and pressurization device 12 is communicated with the cavitator 11 through a second ventilation pipeline 14. Wherein, the ventilation pressurizing device 12 can adopt a booster pump. The fluidizing gas enters the ventilation and pressurization device 12 from the fluidizing gas source 2 through the first ventilation pipeline 13, so that a high-pressure state is formed in the ventilation and pressurization device 12, the high-pressure gas in the ventilation and pressurization device 12 enters the cavitator 11 through the second ventilation pipeline 14, then the fluidizing gas flows out of the cavitator 11, and then the high-speed head-on water flow outside the aircraft is evolved into supercavity.
The gas output end of the gas generator 3 and the powder output end of the powder supply system are respectively communicated with the inlet of the water-jet engine combustion chamber 4, and the powder output end of the powder supply system is connected with the fluidizing gas source 2. Specifically, the fuel gas generator is connected with the water jet engine combustion chamber 4 through a heat insulation layer baffle plate 15, a high-temperature fuel gas inlet 16 and a powder fuel inlet 17 are arranged on the heat insulation layer baffle plate 15, and a fuel gas output end of the fuel gas generator 3 is communicated with an inlet of the water jet engine combustion chamber 4 through the high-temperature fuel gas inlet 16. The gas generator 3 is of an annular structure, a powder pipeline 18 is connected to the powder output end of the powder supply system, and the powder pipeline 18 penetrates through the gas generator 3 and then is communicated with a powder fuel inlet 17. Further in particular, a piston plate 19 is slidably connected within the powder fuel tank 10. The driving gas source 9 is a gas tank storing high-pressure gas, the driving gas source 9 is communicated with one end of the powder fuel storage tank 10 through a third vent pipe 20, the other end of the powder fuel storage tank 10 is a powder output end of the powder supply system, that is, the other end of the powder fuel storage tank 10 is communicated with the fluidizing gas source 2 through a fourth vent pipe 21. The piston plate 19 divides the inside of the pulverized fuel tank 10 into two parts, one of which communicates with the third vent line 20 and the other of which stores the pulverized fuel and communicates with the powder line 18. When the powder supply system is in operation, the gas is introduced into the pulverized fuel storage tank 10 through the third vent pipe 20 by the driving gas source 9, the piston plate 19 is pushed to slide, and the pulverized fuel in the pulverized fuel storage tank 10 enters the water ramjet combustion chamber 4 through the powder pipe 18. In the process, the powder supply quantity of the powder supply system can be controlled by controlling the air outlet speed of the driving air source 9, so that the adjustable supply of the powder fuel is realized. Wherein preferably, the pulverized fuel inlet 17 is provided with a swirl bluff body 27 to disperse the pulverized fuel.
The head of the shell 1 is provided with a first water inlet 22, the water-thrust engine combustion chamber 4 is connected with the first water inlet 22, and the tail nozzle 5 is arranged at the tail of the shell 1 and is communicated with the outlet of the water-thrust engine combustion chamber 4. Specifically, a second water inlet 23 communicated with the interior of the water-thrust engine combustion chamber 4 is arranged on the water-thrust engine combustion chamber 4; the water inlet end of the water flow controller 6 is communicated with the first water inlet 22 through a first water pipeline 24, and the water outlet end of the water flow controller 6 is communicated with the second water inlet 23 through a second water pipeline 25. The water flow controller 6 can be directly realized by adopting a valve structure, and the water inflow of the combustion chamber 4 of the water ramjet engine can be controlled by controlling the valve structure, so that the adjustable supply of water is realized.
In the specific implementation process, the water-jet engine combustion chamber 4 comprises a dual-stage water inlet cyclone 26 and a combustion chamber main body with a cylindrical structure, wherein the dual-stage water inlet cyclone 26 is arranged at the inlet end of the combustion chamber main body. The two-stage water inlet swirler 26 is of a tail revolving body structure, a fuel channel which penetrates through the two-stage water inlet swirler along the circumferential direction is arranged in the two-stage water inlet swirler 26, one end of the fuel channel is connected with the heat insulation layer baffle 15 and is communicated with the high-temperature fuel gas inlet 16 and the powder fuel inlet 17, and the other end of the fuel channel is communicated with the combustion chamber main body.
The wall of the fuel passage adjacent downstream is of a sandwich construction with channels 36. Specifically, the fuel passage is composed of three sections, an upstream equal straight section 33, a midstream venturi structure 34, and a downstream quill section 35. One end of the equal straight section 33 is an inlet of a fuel channel, and the other end is communicated with the first section of the venturi structure 34; one end of the sleeve section 35 is sleeved on the tail section of the venturi structure 34, the other end of the sleeve section is an outlet of the fuel channel, the diversion groove 36 is located between the inner wall 29 of the sleeve section 35 and the outer wall 28 of the venturi structure 34, and the outlet of the diversion groove 36 is flush with the outlet end of the venturi structure 34. Of course, the straight section 33 may be omitted, i.e., both the upstream and midstream of the fuel passage may be occupied by the venturi structure 34.
The side of the double-stage water inlet cyclone 26 is provided with a plurality of first-stage rotational flow water inlet channels 31, the inlet end of each first-stage rotational flow water inlet channel 31 is circumferentially positioned on the side wall of the double-stage water inlet cyclone 26, the inlet end of each first-stage rotational flow water inlet channel 31 is communicated with the second water inlet 23, and the outlet end of each first-stage rotational flow water inlet channel 31 is communicated with the inlet wall surface (namely the wall surface of the equal straight section 33) of the fuel channel. The outlet profile of each first-stage rotational flow water inlet channel 31 is a straight-flow nozzle profile, the length direction of each first-stage rotational flow water inlet channel 31 is perpendicular to the axial direction of the water-jet engine combustion chamber 4, and each first-stage rotational flow water inlet channel 31 is circumferentially distributed on the two-stage water inlet cyclone 26 at the same offset angle.
The side of the double-stage water inlet cyclone 26 is further provided with a plurality of second-stage rotational flow water inlet channels 32, the inlet end of each second-stage rotational flow water inlet channel 32 is circumferentially located on the side wall of the double-stage water inlet cyclone 26, the inlet end of each second-stage rotational flow water inlet channel 32 is communicated with the second water inlet 23, and the outlet end of each second-stage rotational flow water inlet channel is communicated with the wall surface of the diversion trench 36 (i.e. the wall surface of the sleeve section). The outlet profile of each secondary cyclone water inlet channel 32 is a straight-flow nozzle profile, the length direction of each secondary cyclone water inlet channel 32 is perpendicular to the axial direction of the water-jet engine combustion chamber 4, and each secondary cyclone water inlet channel 32 is circumferentially distributed on the double-stage water inlet cyclone 26 at the same offset angle. Wherein, the offset direction of the first-stage rotational flow water inlet channel 31 is opposite to the offset direction of the second-stage rotational flow water inlet channel 32.
In this embodiment, the number of the first-stage rotational flow water inlet passages 31 is 8, and the 8 first-stage rotational flow water inlet passages 31 are all circumferentially arranged at an angle of 45 °, that is, the radial included angle between each first-stage rotational flow water inlet passage 31 and the two-stage water inlet cyclone 26 is 45 °. The number of the second-stage rotational flow water inlet channels 32 is equal to that of the first-stage rotational flow water inlet channels 31, the number of the second-stage rotational flow water inlet channels 32 is 8, and the 8 second-stage rotational flow water inlet channels 32 are circumferentially arranged at an angle of 45 degrees, namely, the radial included angle between each second-stage rotational flow water inlet channel 32 and the two-stage water inlet cyclone 26 is 45 degrees. The first-stage swirling flow inlet channel 31 is offset clockwise with the radial direction of the two-stage water inlet swirler 26 as a starting point, and the second-stage swirling flow inlet channel 32 is offset counterclockwise with the radial direction of the two-stage water inlet swirler 26 as a starting point.
In this embodiment, the combustion chamber body has a sandwich structure having an outer wall 28 and an inner wall 29, a water inlet sandwich 30 is provided between the outer wall 28 and the inner wall 29, and the second water inlet 23 is provided on the outer wall 28 at a position upstream or downstream of the water ramjet combustion chamber 4. The double-stage water inlet cyclone 26 is embedded into the outer wall 28 and then fixedly connected with the outer wall 28 and the inner wall 29, the inlet end of the first-stage rotational flow water inlet channel 31 and the inlet end of the second-stage rotational flow water inlet channel 32 are both positioned in the water inlet interlayer 30, and the double-stage water inlet cyclone 26, the outer wall 28 and the inner wall 29 can be integrally formed in a D printing mode.
The operation process of the combustion chamber 4 of the water-jet engine, which is composed of the double-stage water inlet cyclone 26 and the combustion chamber main body in the embodiment, is as follows:
firstly, high-temperature fuel gas generated by the fuel gas generator 3 is sprayed into a fuel channel from a high-temperature fuel gas inlet 16 to create a high-temperature environment; then, metal powder fuel generated by the powder supply system is axially sprayed into the fuel channel from the powder fuel inlet 17, so that the metal powder fuel quickly reaches the ignition temperature under the action of high-temperature fuel gas; then, spraying primary rotational flow inlet water into the upstream of the fuel channel from the second water inlet 23, the water inlet interlayer 30 and the primary rotational flow inlet channel 31 in sequence, so that the primary rotational flow inlet water is converted into steam under the action of high-temperature fuel gas, and then is mixed with metal powder fuel in the venturi tube structure 34 to be combusted, and the metal powder fuel flows backwards in an accelerated manner; and (3) spraying the secondary cyclone inflow water into the midstream of the fuel channel from the second water inlet 23, the water inlet interlayer 30 and the secondary cyclone inflow channel 32, converting the secondary cyclone inflow water into steam under the action of high-temperature fuel gas, and performing afterburning mixing with the main flow formed by the primary cyclone inflow water, the high-temperature fuel gas and the pulverized fuel at the downstream of the fuel channel in an axial cyclone mode. After the primary swirling flow water vapor and the secondary swirling flow water vapor flow out of the fuel channel, a negative pressure gradient is formed in the axial direction under the action of the centrifugal force of the swirling flow water vapor, so that the rear gas flows back to form a central backflow area in the combustion chamber body; the metal powder fuel is mixed with the primary cyclone steam and the secondary cyclone steam and then enters the central reflux area for combustion, and finally, the efficient and stable combustion of the fuel and the stamping water flow is realized.
In the specific implementation process, a load part 37 and a master control cabin 38 are further arranged in the housing 1, the load part 37 is a task load carried by the navigation body, and the master control cabin is used for controlling the operation of the whole navigation body.
As can be seen from the above, the components of the navigation device in the present embodiment are mainly divided into three parts, namely, an air ventilation system, a water flow control system, and a power system. The ventilation system mainly comprises a cavitator 11, a master control cabin 38, a ventilation pressurizing device 12 and a fluidization air source 2, the water flow control system mainly comprises the master control cabin 38 and a water flow controller 6, and the power system mainly comprises the master control cabin 38, the fluidization air source 2, a driving air source 9, a piston plate 19, a powder fuel storage tank 10, a fuel gas generator 3, a water-jet-compression engine combustion chamber 4, a long tail jet pipe 5 and a boosting engine 7.
In the ventilation system, the cavitator 11 is positioned at the head of the navigation body, the rear part of the cavitator is connected with the second ventilation pipeline 14, the front end and the side part of the ventilation and pressurization device 12 are respectively connected with the second ventilation pipeline 14 and the first ventilation pipeline 13, the first ventilation pipeline 13 conveys the gas in the fluidized gas source 2 to the ventilation and pressurization device 12, and the main control cabin 38 controls the opening and closing state of the gas flow. After the main control cabin 38 sends out a ventilation instruction, the fluidizing gas enters the ventilation and pressurization device 12 from the fluidizing gas source 2 through the first ventilation pipeline 13, so that a high-pressure state is formed in the ventilation and pressurization device 12, and the high-pressure gas in the ventilation and pressurization device 12 enters the cavitator 11 through the second ventilation pipeline 14.
In the water flow control system, the front end of a water flow controller 6 is connected with a first water pipeline 24 and a first water inlet 22 at the head part of the shell 1, and the circumferential outer side of the water flow controller 6 is connected with a second water pipeline 25. The ram water flow firstly enters the first water passage 24 from the first water inlet 22 and then flows into the water flow controller 6, the main control cabin 38 controls the water inflow entering the combustion chamber 4 of the water ramjet by adjusting the valve opening degree in the water flow controller 6, and the ram water flow adjusted by the water flow controller 6 enters the combustion chamber 4 of the water ramjet through the second water passage 25.
In the power system, a boosting engine 7 is annularly arranged outside a long tail nozzle 5, and a water-jet-pressure cruise engine consists of a fluidized gas source 2, a driving gas source 9, a piston plate 19, a powder fuel storage tank 10, a fuel gas generator 3, a water-jet-pressure engine combustion chamber 4 and the long tail nozzle 5. The fluidized gas source 2, the driving gas source 9, the piston plate 19 and the powder fuel storage tank 10 are mainly used for realizing adjustable supply of powder fuel, the gas generator 3 is mainly responsible for providing a high-temperature ignition environment for the water-thrust engine combustion chamber 4, the water-thrust engine combustion chamber 4 is responsible for mixing and burning fuel and water, and the long tail nozzle 5 is responsible for accelerating working medium generated by burning to do work and generate thrust.
The working process of the variable thrust underwater ultra-high speed navigation body in the embodiment is as follows:
in the stage from static acceleration to ultra-high speed cruising, firstly, the main control cabin 38 sends an ignition instruction to trigger the boosting engine 7 to ignite to work, the boosting engine 7 works and is responsible for accelerating the navigation body to a high-speed navigation state in a short time;
the main control cabin 38 sends an ignition instruction and then triggers a ventilation instruction, so that the fluidizing gas enters the ventilation and pressurization device 12 from the fluidizing gas source 2 through the first ventilation pipeline 13, a high-pressure state is formed in the ventilation and pressurization device 12, the high-pressure gas in the ventilation and pressurization device 3 enters the cavitator 11 through the second ventilation pipeline 14, the fluidizing gas flows out of the cavitator 11, and then the fluidizing gas is evolved into supercavitation bubbles under high-speed head-on water flow outside the aircraft;
when the navigation body reaches a high-speed cruising state under the action of the boosting engine 7, the boosting engine 7 is shut down, the powder fuel water-flushing engine is started, the master control cabin 38 closes a ventilation instruction, the ventilation cavitation is converted into natural cavitation, and under the action of the natural cavitation, the navigation body maintains a supercavitation cruising state;
after entering the high-speed state, the main control cabin 38 triggers the gas generator 3, the powder supply and water supply instructions in sequence. At the moment, high-temperature fuel gas generated by the fuel gas generator 3 enters a combustion chamber 4 of the water ramjet engine; after receiving the powder supply instruction, driving gas in the driving gas source 9 pushes the piston plate 19 to push the powder fuel forward, and simultaneously fluidizing gas in the fluidizing gas source 2 enters the powder fuel storage tank 10 to make the fluidizing gas carry the powder fuel to enter the water ramjet engine combustion chamber 4; after receiving a water supply instruction, the ram water flow in the water flow controller 6 enters the water ram engine combustion chamber 4; in a high-speed cruising state, the powder fuel is mixed and combusted with the ram water under the action of high-temperature fuel gas, and high-temperature and high-pressure gas generated by combustion is sprayed out through the tail nozzle 5 to generate thrust.
In a high-speed cruising state, the mass flow of the powdered fuel entering the combustion chamber 4 of the water ramjet engine is adjusted by adjusting the air inflow of the fluidizing air source 2 and the driving air source 9 into the powdered fuel storage tank 10, and the mass flow of the ram water flowing into the combustion chamber 4 of the water ramjet engine is adjusted by the water flow controller 6; and finally, the thrust of the powder fuel water-jet engine is adjusted by adjusting the mass flow of the powder fuel and the mass flow of the ram water flow. During the whole navigation process, the main control cabin 38 triggers a corresponding actuation instruction according to the navigation state, and then the maneuvering is carried out through puncturing the tail rudder 8.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (10)
1. A variable thrust underwater ultra-high speed navigation body is characterized by comprising a shell, and a fluidized gas source, a gas generator, a powder supply system, a water-jet engine combustion chamber and a tail jet pipe which are arranged in the shell;
the head of the shell is provided with a cavitator, the cavitator is connected with the fluidization gas source, the gas output end of the gas generator and the powder output end of the powder supply system are respectively communicated with the inlet of the combustion chamber of the water-jet engine, and the powder output end of the powder supply system is communicated with the fluidization gas source;
the water jet engine comprises a shell, a water jet pipe, a tail pipe and a tail pipe, wherein a first water inlet is formed in the outer wall of the shell, the water jet engine combustion chamber is connected with the first water inlet, and the tail pipe is arranged at the tail of the shell and communicated with an outlet of the water jet engine combustion chamber.
2. The variable-thrust underwater ultra-high-speed navigation body according to claim 1, wherein the powder supply system, the gas generator and the water-thrust engine combustion chamber are sequentially arranged in the housing along an axial direction of the housing;
the fuel gas generator is connected with the combustion chamber of the water-jet engine through a heat insulation layer baffle, a high-temperature fuel gas inlet and a powder fuel inlet are formed in the heat insulation layer baffle, and a fuel gas output end of the fuel gas generator is communicated with an inlet of the combustion chamber of the water-jet engine through the high-temperature fuel gas inlet;
the gas generator is of an annular structure, a powder pipeline is connected to the powder output end of the powder supply system, and the powder pipeline penetrates through the gas generator and then is communicated with the powder fuel inlet.
3. The variable-thrust underwater ultra-high-speed navigation body according to claim 2, wherein the powder supply system comprises a driving gas source and a powder fuel storage tank which are arranged in the housing in sequence;
the powder fuel storage tank is internally provided with a driving air source, the driving air source is communicated with one end of the powder fuel storage tank, and the other end of the powder fuel storage tank is the powder output end of the powder supply system.
4. The variable thrust underwater ultra high speed vehicle according to claim 2 or 3, wherein a swirl bluff body is provided on the pulverized fuel inlet to disperse the pulverized fuel.
5. The variable thrust underwater ultra high speed vehicle according to claim 1, 2 or 3, wherein the hull aft portion is further provided with a plurality of booster engines, each booster engine being disposed around the jet nozzle.
6. The variable thrust underwater superspeed navigation body according to claim 1, 2 or 3, wherein a puncture tail rudder is further arranged on the shell.
7. The variable-thrust underwater ultra-high-speed navigation body according to claim 1, 2 or 3, wherein a water flow controller is further arranged in the shell, and a second water inlet communicated with the inside of the combustion chamber of the water thrust engine is formed in the combustion chamber of the water thrust engine;
the water inlet end of the water flow controller is communicated with the first water inlet, and the water outlet end of the water flow controller is communicated with the second water inlet.
8. The variable-thrust underwater ultra-high-speed navigation body according to claim 7, wherein the water-thrust engine combustion chamber comprises a double-stage water-inlet cyclone and a combustion chamber main body, and the double-stage water-inlet cyclone is arranged at an inlet end of the combustion chamber main body;
a fuel channel is arranged in the double-stage water inlet swirler, one end of the fuel channel is respectively communicated with a gas output end of the gas generator and a powder output end of the powder supply system, and the other end of the fuel channel is communicated with the combustion chamber main body;
the wall surface of the fuel channel close to the downstream is of a sandwich structure with a diversion trench;
the side part of the two-stage water inlet cyclone is provided with a plurality of first-stage rotational flow water inlet channels and second-stage rotational flow water inlet channels, the inlet end of each first-stage rotational flow water inlet channel and the inlet end of each second-stage rotational flow water inlet channel are communicated with the second water inlet, the outlet end of each first-stage rotational flow water inlet channel is communicated with the wall surface of the inlet of the fuel channel, and the outlet end of each second-stage rotational flow water inlet channel is communicated with the wall surface of the diversion trench;
the primary rotational flow water inlet channels are uniformly distributed on the two-stage water inlet cyclone along the circumferential direction at the same angle, the secondary rotational flow water inlet channels are distributed on the two-stage water inlet cyclone along the circumferential direction at the same angle, and the rotational direction of the primary rotational flow water inlet channels is opposite to that of the secondary rotational flow water inlet channels.
9. The variable-thrust underwater ultra-high-speed navigation body according to claim 8, wherein the midstream section of the fuel passage is of a venturi structure, or the upstream section and the midstream section of the fuel passage are of a venturi structure;
the diversion trench is sleeved at the tail section of the venturi structure, and the outlet of the diversion trench is flush with the outlet end of the venturi structure.
10. The variable thrust underwater ultra high speed vehicle according to claim 8, wherein the combustion chamber body has a sandwich structure having an outer wall and an inner wall;
a water inlet interlayer is arranged between the outer wall and the inner wall, and the second water inlet is arranged on the outer wall at a position corresponding to the midstream or the downstream of the combustion chamber of the water-jet engine;
the double-stage water inlet cyclone is embedded into the outer wall and then connected with the outer wall and the inner wall, and the inlet end of the first-stage rotational flow water inlet channel and the inlet end of the second-stage rotational flow water inlet channel are both positioned in the water inlet interlayer.
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