CN109519280B - Turboprop direct-injection hybrid multistage-power underwater high-speed propeller and control method - Google Patents
Turboprop direct-injection hybrid multistage-power underwater high-speed propeller and control method Download PDFInfo
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- CN109519280B CN109519280B CN201811558476.1A CN201811558476A CN109519280B CN 109519280 B CN109519280 B CN 109519280B CN 201811558476 A CN201811558476 A CN 201811558476A CN 109519280 B CN109519280 B CN 109519280B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/26—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being solid or pulverulent, e.g. in slurry or suspension
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
- F02C3/305—Increasing the power, speed, torque or efficiency of a gas turbine or the thrust of a turbojet engine by injecting or adding water, steam or other fluids
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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
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
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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
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
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- Combustion & Propulsion (AREA)
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- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
- Output Control And Ontrol Of Special Type Engine (AREA)
Abstract
The invention discloses a turboprop direct-injection hybrid multistage power underwater high-speed propeller and a control method thereof, wherein the turboprop direct-injection hybrid multistage power underwater high-speed propeller comprises a low-speed section engine, an acceleration section engine and a high-speed section engine, aiming at different combat guidelines, a water-flushing high-metal content propellant engine and a high-metal content solid rocket engine are combined, a turbine power output device is assisted, and by reasonably designing a charging mode, the charging amount and the water-flushing amount are adjusted to meet the requirements of a system on propulsion power at different navigation speeds, so that the limitation of single navigation speed of a traditional underwater vehicle is broken through, and two typical motion states of conventional low-speed cruising and high-speed striking which is seven times of the conventional speed can be realized in the same navigation.
Description
Technical Field
The invention belongs to the technical field of underwater vehicle power, and particularly relates to a turboprop direct-injection hybrid multistage-power underwater high-speed propeller and a control method.
Background
At present, various states of naval force are protected around ocean equity, new combat requirements are aimed, novel equipment development is actively developed, and great progress is made in the aspects of surface ships, submarine equipment, new concept and new technology and the like. Under the current situation, the role of an underwater high-efficiency offensive weapon in a modern battlefield is increasingly important. The killing principle of the underwater weapon is to break the keel of the other side, so that the underwater weapon is high in concealment, good in penetration effect and high in hit rate; the diversification of tactics can be enhanced, and the attack effect is improved. However, in the construction of underwater operation platforms, various countries are generally troubled by the problem of low efficiency of power systems, and energy and power systems are a main technical difficulty that the current aircraft is limited in military application. The development and utilization of new energy are broken through, the cruising ability of the weapon is improved, and the development of a navigation body towards high compatibility and modularization is an important current task.
Among various available energy sources, the high-calorific-value energy of metal fuel is valued by various countries, and particularly, part of oxidant required by the metal combustion process can be served by an aqueous medium introduced in a working environment, so that the feasibility and the convenience of the metal fuel are proved, the metal fuel is utilized in the existing weapon models, and the potential of the metal fuel is worthy of being deeply explored. However, in the existing aircraft power system, the speed is single, the speed conversion is difficult to realize, and the flexibility required by battle operation is lacked.
Disclosure of Invention
In view of the above, the present invention provides a turboprop direct-injection hybrid multistage power underwater high-speed propeller and a control method thereof, which can meet the requirements of systems for propulsion power at different sailing speeds, and the propeller has the characteristics of compact structure and light weight, and can achieve the general goal of flexible combat.
A turboprop direct-injection hybrid multistage power underwater high-speed vehicle comprises a low-speed section engine, an acceleration section engine and a high-speed section engine which are sequentially connected;
the high-speed section engine comprises a high-speed section water inlet buffer chamber (1), a high-speed section primary water injection pipeline (2), water-thrust metal fuel (3), a high-speed section secondary water injection pipeline (4), a high-speed section combustion chamber (21) and a high-speed section spray pipe (5);
the accelerating section engine comprises an accelerating section baffle (6), a solid propellant (7), an accelerating section combustion chamber (22) and an accelerating section spray pipe (8);
the low-speed section engine comprises a speed section baffle (10), a low-speed section water inlet buffer chamber (11), a water pump (12), a low-speed section primary water injection pipeline (13), a low-speed section secondary water injection pipeline (14), a turbine (17), a speed changer (18), a propeller (19), water-jet metal fuel (20) and a low-speed section combustion chamber (23);
one end of the high-speed section combustion chamber (21) is closed, and the outer end surface of the high-speed section combustion chamber is connected with the high-speed section water inlet buffer chamber (1); the other end is open and connected with a high-speed section spray pipe (5); the side, close to the high-speed section water inlet buffer chamber (1), of the water stamping metal fuel (3) is cast in a high-speed section combustion chamber (21); the high-speed section primary water injection pipeline (2) and the high-speed section secondary water injection pipeline (4) are respectively provided with a plurality of pipelines and coated on the outer surface of the high-speed section combustion chamber (21); one end of the high-speed section primary water injection pipeline (2) and one end of the high-speed section secondary water injection pipeline (4) are communicated with the high-speed section engine buffer chamber 1, the other end of the high-speed section primary water injection pipeline extends into an internal cavity of the high-speed section combustion chamber (21), an interface of the high-speed section primary water injection pipeline (2) connected into the high-speed section combustion chamber (21) is closer to a combustion surface of the water-jet-pressing metal fuel (3), one side of the accelerating section baffle (6) is connected with the high-speed section spray pipe (5) through an explosion bolt, and the high-speed section spray pipe (5); the other side of the accelerating section baffle (6) is fixedly connected to the end part of one side of the accelerating section combustion chamber (22); the other side opening end of the accelerating section combustion chamber (22) is connected with an accelerating section spray pipe (8); a plurality of hollow cylindrical solid propellant grains (7) are cast in the accelerating section combustion chamber (22);
one side surface of the low-speed section baffle (10) is connected with the accelerating section spray pipe (8) through an explosion bolt, and the other side surface is connected with the low-speed section water inlet buffer chamber (11); one end of the low-speed section combustion chamber (23) is a mixed combustion chamber cavity, a plurality of even number of charge pipes communicated with the mixed combustion chamber cavity extend from the edge of the end part, and the charge pipes are filled with water-flushed metal fuel (20); all the charge pipes surround a circle to form a cavity, and the outer diameter of the cavity is the same as that of the combustion chamber (22) of the acceleration section; an accelerating section spray pipe (8) of the accelerating section engine and a low-speed section water inlet buffer chamber (11), a water pump (12), a low-speed section primary water injection pipeline (13) and a low-speed section secondary water injection pipeline (14) in the low-speed section engine are accommodated in the cavity; each medicine filling pipe is at least provided with a low-speed primary water injection pipeline (13), and the low-speed primary water injection pipeline (13) is arranged along the outer surface of the medicine filling pipe; the cavity of the mixing combustion chamber is connected with a turbine (17) through a pipeline; the turbine (17) is connected with a propeller (19) through a transmission (18);
the low-speed section water inlet buffer chamber (11) is divided into two small buffer chambers, and the first small buffer chamber is connected with a low-speed section baffle (10) and is provided with a water inlet (9); the first small buffer chamber is connected with a water inlet of the water pump (12), and a water outlet of the water pump (12) is communicated with the second small buffer chamber; one end of a low-speed section primary water injection pipeline (13) is communicated with the second small buffer chamber, and the other end of the low-speed section primary water injection pipeline is communicated with the medicine filling pipe; one end of the low-speed section secondary water injection pipeline (14) is communicated with the second small buffer chamber, the other end of the low-speed section secondary water injection pipeline is communicated to the mixed combustion chamber of the low-speed section combustion chamber (23), and the interface is positioned at the middle shaft of the low-speed section combustion chamber (23).
Preferably, the low-speed section primary water injection pipeline (13) is communicated to the positions of different lengths of the medicine loading pipe through more than two connectors.
Preferably, the fast section engine, the accelerating section engine and the high speed section engine are respectively connected with the aircraft shell.
Preferably, the high-speed section combustion chamber (21) is connected with the high-speed section spray pipe (5) through threads.
Preferably, the high-speed section primary water injection pipeline (2) and the high-speed section secondary water injection pipeline (4) are arranged on the outer surface of the high-speed section combustion chamber (21) at intervals.
Preferably, the power of the water pump (12) is provided by a battery (15).
Preferably, the water supply of the water pump (12) to the second small buffer chamber is controlled by a flow valve (16).
A control method of a turboprop direct-injection hybrid multistage power underwater high-speed vehicle comprises the following steps:
(1) starting a low-speed section engine, and igniting water in a charging pipe by using an ignition device to impact metal fuel (20); after the fuel is burnt to a set temperature, a water pump (12) is started, water in the external environment is introduced into a low-speed section water inlet buffer chamber (11) through an external water inlet (9), a low-speed section primary water injection pipeline (13) is started, the reaction of the low-speed section primary water injection pipeline and water-pressing metal fuel (20) is promoted, and water stamping combustion is realized; then, a low-speed section secondary water injection pipeline (14) is opened, secondary mixing is carried out on the environment water injection and the fuel gas generated by combustion of the water-jet-pressing metal fuel (20), and a driving force is output through a high-speed section spray pipe (5);
(2) after the water-jet-pressing metal fuel (20) at the low-speed section is completely burnt out, starting an explosion bolt device for connecting a low-speed baffle plate (10) and an accelerating section spray pipe (8), abandoning a low-speed section engine device, and starting an accelerating section engine; after the engine at the accelerating section works, the solid propellant grain (7) is ignited, and the fuel gas generated by combustion is discharged outwards through a nozzle (8) at the accelerating section to generate driving force;
(3) after the solid propellant grain (7) in the accelerating section engine is burnt out, an explosion bolt device which is connected with a baffle plate (6) of the accelerating section and a spray pipe (5) of the high-speed section is started, the accelerating section engine is abandoned, and the high-speed section engine is started;
after the high-speed section engine works, an ignition device in the water-thrust metal fuel (3) is started to ignite the fuel gas, after the fuel gas reaches a set temperature, a water inlet of the high-speed section water inlet buffer chamber (1) is opened, water in the external environment is introduced, and a primary water injection pipeline (2) is started to react with the water-thrust metal fuel (3) in a high-speed section combustion chamber (21), so that water-thrust combustion is realized, and heat is released; then, a secondary water injection pipeline (4) is opened, the environmental water is mixed with the fuel gas generated by the combustion of the water-jet-pressing metal fuel (3) for the second time, and the fuel gas is discharged outwards through a high-speed section spray pipe (5) to generate a driving force; and after the high-speed section water-jet pressure metal fuel (3) is completely burnt out, the propeller finishes all work.
Preferably, after the low-speed engine is started, the ignition device in each charge pipe is sequentially started in a symmetrical mode to ignite the water in the charge pipes to press the metal fuel (20).
The invention has the following beneficial effects:
the invention provides a turboprop direct-injection hybrid multistage power underwater high-speed propeller and a control method thereof, aiming at different operational guidelines, a water-thrust high-metal content propellant engine and a high-metal content solid rocket engine are combined, a turbine power output device is used for assistance, the charge amount and the water-punching amount are adjusted by reasonably designing a charge mode to meet the requirements of a system on propulsion power at different navigation speeds, the limitation of single navigation speed of a traditional underwater vehicle is broken through, and two typical motion states of conventional low-speed cruising and high-speed striking which is seven times of the conventional speed can be realized in the same navigation range.
The turboprop direct-injection hybrid multistage power underwater high-speed propeller provided by the invention can quickly finish high-efficiency switching between low-speed sailing speed and high-speed sailing speed, and can ensure sailing stability in the switching process.
In the low-speed working stage of the aircraft, the novel power propulsion mode of combining the water-thrust metal fuel propellant and the turbine propeller output device is adopted, so that high-temperature gas generated by combustion of the solid propellant can be fully utilized, and the overall work doing efficiency of the system is greatly improved.
After the low-speed engine finishes working, the low-speed working mechanism is thrown out through devices such as explosive bolts, and meanwhile, the accelerating engine is started to work. After the acceleration section works, the acceleration section working mechanism is thrown out through devices such as explosive bolts, and meanwhile, the high-speed section engine is started to work.
In the high-speed working stage of the navigation body, the water-thrust metal fuel propellant is adopted, and the high pressure formed by the high-speed movement of the navigation body is utilized to introduce the environmental water, so that the autonomous water-thrust combustion is realized. The mixed gas generated by combustion is discharged out of the combustion chamber in a direct injection mode through the Laval nozzle, so that strong thrust is generated, and quick target striking can be realized.
The three engines related in the turboprop direct-injection hybrid multistage power underwater high-speed propeller are connected in sequence structurally, work sequentially after starting, the space arrangement is reasonable, the optimal design of the multistage propeller in the minimum space is realized, the multi-task operation work under complex conditions can be completed, and the fighting performance of an underwater weapon system can be greatly improved.
Drawings
FIG. 1 is a shaft view of a turboprop direct-injection hybrid multistage power underwater high-speed propeller.
FIG. 2 is a top view of a turboprop direct-injection hybrid multistage power underwater high-speed propeller
Fig. 3 is a sectional view of a turboprop direct-injection hybrid multistage power underwater high-speed propeller.
FIG. 4 is a distribution diagram of the charge in the combustion chamber in the low velocity section.
FIG. 5 is a distribution diagram of the charge in the combustion chamber of the acceleration section.
FIG. 6 is a low speed section engine shaft view.
Fig. 7 is an engine shaft view of the acceleration section.
FIG. 8 is a high speed section engine shaft view.
The device comprises a high-speed section water inlet buffer chamber, a 2-high-speed section primary water injection pipeline, a 3-water pressure metal fuel, a 4-high-speed section secondary water injection pipeline, a 5-high-speed section spray pipe, a 6-acceleration section baffle, a 7-solid propellant grain, an 8-acceleration section spray pipe, a 9-water inlet, a 10-low-speed section baffle, a 11-low-speed section water inlet buffer chamber, a 12-water pump, a 13-low-speed section primary water injection pipeline, a 14-low-speed section secondary water injection pipeline, a 15-battery, a 16-flow valve, a 17-turbine, an 18-speed changer, a 19-propeller, a 20-small water pressure metal fuel, a 21-high-speed section combustion chamber, a 22-acceleration section combustion chamber and a 23-low-speed section combustion chamber, wherein the high-speed section.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
As shown in fig. 1-3, the multi-stage power underwater high-speed propeller mainly comprises a high-speed engine, an accelerating engine and a low-speed engine. The high-speed section engine mainly comprises a high-speed section water inlet buffer chamber 1, a high-speed section primary water injection pipeline 2, a water-thrust metal fuel 3, a high-speed section secondary water injection pipeline 4, a high-speed section combustion chamber 21 and a high-speed section spray pipe 5; the accelerating section engine mainly comprises an accelerating section baffle 6, a solid propellant grain 7, an accelerating section combustion chamber 22 and an accelerating section spray pipe 8; the low-speed section engine mainly comprises a low-speed section engine external water inlet 9, a low-speed section baffle 10, a low-speed section water inlet buffer chamber 11, a special water pump 12, a low-speed section primary water injection pipeline 13, a low-speed section secondary water injection pipeline 14, a battery 15, a flow valve 16, a turbine 17, a transmission 18, a propeller 19, a end-burning type water-flushing metal fuel 20 and a low-speed section combustion chamber 23. The high-speed section is sequentially connected with the acceleration section, the acceleration section is sequentially connected with the low-speed section, and the three parts are respectively connected with the aircraft shell through bolts.
As shown in fig. 8, one end of the high-speed combustion chamber 21 is closed, and the high-speed water inlet buffer chamber 1 is connected to the outer end surface; the other end is opened and is connected with a high-speed section spray pipe 5 through threads; the water stamping metal fuel 3 is cast in the high-speed section combustion chamber 21 close to one side of the high-speed section water inlet buffer chamber 1; the high-speed section primary water injection pipeline 2 and the high-speed section secondary water injection pipeline 4 are respectively provided with a plurality of pipelines which are arranged at intervals and are coated on the outer surface of the high-speed section combustion chamber 21 in a half way; the high-speed section primary water injection pipeline 2 and the high-speed section secondary water injection pipeline 4 are communicated with one end of the high-speed section engine buffer chamber 1, the other end of the high-speed section engine buffer chamber all extends into an inner cavity of the high-speed section combustion chamber 21, but an interface of the high-speed section primary water injection pipeline 2 connected into the high-speed section combustion chamber 21 is closer to a combustion surface of the water-jet metal fuel 3, and an interface of the high-speed section secondary water injection pipeline 4 is close to the rear part of the high-speed section combustion chamber 21.
As shown in fig. 5 and 7, one side of the accelerating section baffle 6 is connected with the high-speed section spray pipe 5 through an explosion bolt to seal the high-speed section spray pipe 5; the diameter of the accelerating section baffle 6 is the same as that of the accelerating section combustion chamber 22; the other side of the acceleration section baffle 6 is welded to one side end part of the acceleration section combustion chamber 22; the other side opening end of the accelerating section combustion chamber 22 is connected with an accelerating section spray pipe 8; in order to control the combustion of the engine propellant at a set combustion speed, ensure the uniform combustion in the combustion chamber and provide working power under the design requirement, a tubular charging mode is adopted, and a plurality of solid propellant grains 7 are cast in the combustion chamber 22 of the acceleration section; the grain 7 is a hollow cylinder structure, the central axis is parallel to the central axis of the combustion chamber 22 of the accelerating section; the solid propellant grain 7 is embedded with metal wires to improve the thrust thereof.
As shown in fig. 3, 4 and 6, one side surface of the low-speed section baffle 10 is connected with the acceleration section spray pipe 8 through an explosion bolt, and the other side surface is connected with the low-speed section water inlet buffer chamber 11; one end of the low-speed section combustion chamber 23 is a mixed combustion chamber cavity, a plurality of even number of charge pipes communicated with the mixed combustion chamber cavity extend from the edge of the end part, and the charge pipes are filled with water-stamped metal fuel 20; all the charge pipes surround a circle to form a cavity, and the outer diameter of the cavity is the same as that of the combustion chamber 22 of the accelerating section, so that a streamline whole is formed in appearance; an accelerating section spray pipe 8 of the accelerating section engine and a low-speed section water inlet buffer chamber 11, a water pump 12, a low-speed section primary water injection pipeline 13, a low-speed section secondary water injection pipeline 14, a battery 15 and a flow valve 16 in the low-speed section engine are accommodated in the cavity; each medicine filling pipe is at least provided with a low-speed primary water injection pipeline 13, and the low-speed primary water injection pipeline 13 is arranged along the outer surface of the medicine filling pipe; the installation space of the structure can be saved, and the size of the whole propeller is reduced. The cavity of the mixed combustion chamber is connected with a turbine 17 through a pipeline; turbine 17 is connected to propeller 19 through transmission 18.
The low-speed section water inlet buffer chamber 11 is divided into two small buffer chambers, and the first small buffer chamber is connected with a low-speed section baffle 10 and is provided with a water inlet 9; the first small buffer chamber is connected with the water inlet of the water pump 12, and the water outlet of the water pump 12 is communicated with the second small buffer chamber; one end of the low-speed section primary water injection pipeline 13 is communicated with the second small buffer chamber, and the other end is communicated with the medicine loading pipe; one end of the low-speed section secondary water injection pipeline 14 is communicated with the second small buffer chamber, the other end of the low-speed section secondary water injection pipeline is communicated to the mixed combustion chamber of the low-speed section combustion chamber 23, and the interface is positioned at the middle shaft of the combustion chamber 23.
The working principle of the device is as follows:
after receiving a starting instruction of the aircraft, the turboprop direct-injection hybrid multistage power underwater high-speed propeller sequentially starts the low-speed section engine, the accelerating section engine and the high-speed section engine to propel the aircraft to change from a low-speed cruising state to a high-speed striking state until fuel is burnt out to complete all work.
In a low-speed engine, the working efficiency of gas is improved by using a turbine propeller device, and the overall power is improved; in the acceleration section, the stability of the navigation body in the acceleration process is ensured through reasonable design of the charge form and the propellant components; and the high-speed section adopts water to flush and press metal fuel to improve the navigation speed.
Summarizing the operation method of the turboprop direct-injection hybrid multistage power underwater high-speed propeller, provided by the invention, comprises the following steps:
(1) starting the low-speed engine; the low-speed section combustion chamber 23 consists of a plurality of even small-sized grains and a shared mixed combustion chamber cavity, and each small-sized grain is filled with small-sized water-flushing metal fuel 20 and is provided with an ignition device. After the system is started, the ignition devices in the branch explosive columns are sequentially started in a symmetrical mode to ignite the corresponding water-thrust metal fuel 20. After the fuel burns to a certain temperature, the special water pump 12 is started, water in the external environment is introduced into the low-speed section water inlet buffer chamber 11 through the external water inlet 9, the low-speed section primary water injection pipeline 13 is started to promote the reaction of the low-speed section primary water injection pipeline and the water-impact metal fuel 20, the water-impact combustion is realized, and heat is released. And then, a secondary water injection pipeline 14 at a low-speed section is started, so that the environmental water is secondarily mixed with the fuel gas generated by burning the water-thrust metal fuel 20, the total fuel gas quantity is increased, and the work capacity of the system is improved. The total water intake of the system is monitored by means of a flow valve 16. All the combustion gas is delivered to a propeller 19 through a turbine 17 and a transmission 18, and the propeller is pushed to rotate and outputs pushing force.
(2) After the water-jet pressure metal fuel 20 in the low-speed section is completely burnt out, an explosion bolt device for connecting the low-speed baffle plate 10 and the accelerating section spray pipe 8 is started, the low-speed section engine device is abandoned, and the accelerating section engine is started.
(3) After the engine at the accelerating section works, an ignition device in the solid propellant 7 with high metal content is started to ignite the propellant to promote the combustion of the propellant, and fuel gas generated by the combustion is discharged outwards through a spray pipe 8 at the accelerating section to generate driving force.
(4) After the solid propellant 7 with high metal content in the accelerating section is burnt out, an explosion bolt device which is connected with the baffle 6 of the accelerating section and the spray pipe 5 of the high-speed section is started, an engine device of the accelerating section is abandoned, and an engine of the high-speed section is started.
(5) After the high-speed section engine works, an ignition device in the water-thrust metal fuel 3 is started to ignite the fuel gas, after the fuel gas reaches a certain temperature, a water inlet of the high-speed section water inlet buffer chamber 1 is opened, water in the external environment is introduced, and the primary water injection pipeline 2 is started to react with the water-thrust metal fuel 3 in the high-speed section combustion chamber 21, so that water-thrust combustion is realized, and heat is released. And then, a secondary water injection pipeline 4 is opened, so that the environmental water is mixed with the fuel gas generated by burning the water-jet pressure metal fuel 3 for the second time, the total amount of the fuel gas is increased, and the working capacity is improved. All fuel gas is discharged outwards through the high-speed section spray pipe 5 to generate driving force and maintain high-speed movement of the aircraft. And after the high-speed section water-jet pressure metal fuel 3 is completely combusted, the propeller finishes all work.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A turboprop direct-injection hybrid multistage power underwater high-speed vehicle is characterized by comprising a low-speed section engine, an acceleration section engine and a high-speed section engine which are sequentially connected;
the high-speed section engine comprises a high-speed section water inlet buffer chamber (1), a high-speed section primary water injection pipeline (2), a high-speed section water-flushing metal fuel (3), a high-speed section secondary water injection pipeline (4), a high-speed section combustion chamber (21) and a high-speed section spray pipe (5);
the accelerating section engine comprises an accelerating section baffle (6), a solid propellant grain (7), an accelerating section combustion chamber (22) and an accelerating section spray pipe (8);
the low-speed section engine comprises a speed section baffle (10), a low-speed section water inlet buffer chamber (11), a water pump (12), a low-speed section primary water injection pipeline (13), a low-speed section secondary water injection pipeline (14), a turbine (17), a speed changer (18), a propeller (19), low-speed section water-pressure metal fuel (20) and a low-speed section combustion chamber (23);
one end of the high-speed section combustion chamber (21) is closed, and the outer end surface of the high-speed section combustion chamber is connected with the high-speed section water inlet buffer chamber (1); the other end is open and connected with a high-speed section spray pipe (5); the high-speed section water-jet metal fuel (3) is cast in the high-speed section combustion chamber (21) close to one side of the high-speed section water-inlet buffer chamber (1); the high-speed section primary water injection pipeline (2) and the high-speed section secondary water injection pipeline (4) are respectively provided with a plurality of pipelines and coated on the outer surface of the high-speed section combustion chamber (21); the high-speed section primary water injection pipeline (2) is communicated with one end of the high-speed section secondary water injection pipeline (4) to form a high-speed section water inlet buffer chamber (1), the other end of the high-speed section secondary water injection pipeline extends into an inner cavity of the high-speed section combustion chamber (21), and an interface of the high-speed section primary water injection pipeline (2) connected into the high-speed section combustion chamber (21) is closer to a combustion surface of the high-speed section water-jet metal fuel (3);
one side of the accelerating section baffle (6) is connected with the high-speed section spray pipe (5) through an explosion bolt to seal the high-speed section spray pipe (5); the other side of the accelerating section baffle (6) is fixedly connected to the end part of one side of the accelerating section combustion chamber (22); the other side opening end of the accelerating section combustion chamber (22) is connected with an accelerating section spray pipe (8); a plurality of hollow cylindrical solid propellant grains (7) are cast in the accelerating section combustion chamber (22);
one side surface of the low-speed section baffle (10) is connected with the accelerating section spray pipe (8) through an explosion bolt, and the other side surface is connected with the low-speed section water inlet buffer chamber (11); one end of the low-speed section combustion chamber (23) is a mixed combustion chamber cavity, a plurality of even number of charge pipes communicated with the mixed combustion chamber cavity extend from the edge of the end part, and the charge pipes are filled with low-speed section water-flushing metal fuel (20); all the charge pipes surround a circle to form a cavity, and the outer diameter of the cavity is the same as that of the combustion chamber (22) of the acceleration section; an accelerating section spray pipe (8) of the accelerating section engine and a low-speed section water inlet buffer chamber (11), a water pump (12), a low-speed section primary water injection pipeline (13) and a low-speed section secondary water injection pipeline (14) in the low-speed section engine are accommodated in the cavity; each medicine filling pipe is at least provided with a low-speed primary water injection pipeline (13), and the low-speed primary water injection pipeline (13) is arranged along the outer surface of the medicine filling pipe; the cavity of the mixing combustion chamber is connected with a turbine (17) through a pipeline; the turbine (17) is connected with a propeller (19) through a transmission (18);
the low-speed section water inlet buffer chamber (11) is divided into two small buffer chambers, and the first small buffer chamber is connected with a low-speed section baffle (10) and is provided with a water inlet (9); the first small buffer chamber is connected with a water inlet of the water pump (12), and a water outlet of the water pump (12) is communicated with the second small buffer chamber; one end of a low-speed section primary water injection pipeline (13) is communicated with the second small buffer chamber, and the other end of the low-speed section primary water injection pipeline is communicated with the medicine filling pipe; one end of the low-speed section secondary water injection pipeline (14) is communicated with the second small buffer chamber, the other end of the low-speed section secondary water injection pipeline is communicated to the mixed combustion chamber of the low-speed section combustion chamber (23), and the interface is positioned at the middle shaft of the low-speed section combustion chamber (23).
2. The turboprop direct-injection hybrid multistage-power underwater high-speed vehicle as claimed in claim 1, characterized in that the low-speed stage primary water injection pipeline (13) is communicated to the charge pipe at different lengths through more than two interfaces.
3. The turboprop direct-injection hybrid multistage-power underwater high-speed vehicle as claimed in claim 1, wherein the low-speed stage engine, the acceleration stage engine and the high-speed stage engine are respectively connected to the vehicle hull.
4. The turboprop direct-injection hybrid multistage power underwater high-speed vehicle according to claim 1, characterized in that said high-speed section combustion chamber (21) is screwed to the high-speed section nozzle (5).
5. The turboprop direct-injection hybrid multistage-power underwater high-speed vehicle as claimed in claim 1, characterized in that the high-speed stage primary water injection line (2) and the high-speed stage secondary water injection line (4) are arranged on the outer surface of the high-speed stage combustion chamber (21) at a spacing.
6. The turboprop direct-injection hybrid multistage-powered underwater high-speed vehicle as claimed in claim 1, characterized in that the power of the water pump (12) is provided by a battery (15).
7. The turboprop direct-injection hybrid multistage powered underwater high-speed vehicle according to claim 1, characterized in that the water supply of the water pump (12) to the second small buffer chamber is controlled by a flow valve (16).
8. The method for controlling the turboprop direct-injection hybrid multistage-powered underwater high-speed vehicle as claimed in claim 1, characterized in that it comprises the following steps:
(1) starting a low-speed section engine, and igniting low-speed section water in a charging pipe by adopting an ignition device to press metal fuel (20); after the fuel is burnt to a set temperature, a water pump (12) is started, water in the external environment is introduced into a low-speed section water inlet buffer chamber (11) through an external water inlet (9), a low-speed section primary water injection pipeline (13) is started, the reaction between the low-speed section primary water injection pipeline and the low-speed section water impact metal fuel (20) is promoted, and water impact burning is realized; then, a secondary water injection pipeline (14) at the low-speed section is opened, the environment water is secondarily mixed with fuel gas generated by combustion of the water-jet-pressing metal fuel (20) at the low-speed section, and a driving force is output through a high-speed section spray pipe (5);
(2) after the water-jet-pressing metal fuel (20) at the low-speed section is completely burnt out, starting an explosion bolt device for connecting a low-speed baffle plate (10) and an accelerating section spray pipe (8), abandoning a low-speed section engine device, and starting an accelerating section engine; after the engine at the accelerating section works, the solid propellant grain (7) is ignited, and the fuel gas generated by combustion is discharged outwards through a nozzle (8) at the accelerating section to generate driving force;
(3) after the solid propellant grain (7) in the accelerating section engine is burnt out, an explosion bolt device which is connected with a baffle plate (6) of the accelerating section and a spray pipe (5) of the high-speed section is started, the accelerating section engine is abandoned, and the high-speed section engine is started;
after the high-speed section engine works, an ignition device in the high-speed section water-jet metal fuel (3) is started to ignite the high-speed section water-jet metal fuel, after fuel gas reaches a set temperature, a water inlet of the high-speed section water-inlet buffer chamber (1) is opened, water in the external environment is introduced, and a primary water injection pipeline (2) is started to react with the high-speed section water-jet metal fuel (3) in a high-speed section combustion chamber (21), so that water-jet combustion is realized, and heat is released; then a secondary water injection pipeline (4) is opened, the environmental inlet water and the fuel gas generated by combustion of the high-speed section water-jet metal fuel (3) are secondarily mixed, and the fuel gas is discharged outwards through a high-speed section spray pipe (5) to generate a driving force; and after the high-speed section water-jet pressure metal fuel (3) is completely burnt out, the propeller finishes all work.
9. The method for controlling the turboprop direct-injection hybrid multistage-power underwater high-speed vehicle as claimed in claim 8, wherein after the low-speed engine is started, the ignition devices in the charge pipes are sequentially started in a symmetrical manner to ignite the low-speed stage water-thrust metal fuel (20) inside the charge pipes.
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| CN110107426B (en) * | 2019-05-08 | 2020-08-14 | 中国航空发动机研究院 | Cross-medium aircraft power device based on interstage combustion chamber and turbine water-air sharing |
| CN110107401A (en) * | 2019-05-08 | 2019-08-09 | 中国航空发动机研究院 | Across medium flight device power device based on empty water flow passage compact layout |
| CN111734550B (en) * | 2020-06-15 | 2022-07-15 | 哈尔滨工程大学 | Built-in multistage thrust underwater power system and control method thereof |
| CN111749814B (en) * | 2020-06-15 | 2022-06-17 | 哈尔滨工程大学 | Cross-medium dual-mode ramjet based on metal fuel and control method |
| CN112918650B (en) * | 2021-03-26 | 2023-01-24 | 河南科技学院 | Instantaneous acceleration system and method for autonomous underwater vehicle |
| CN114408145B (en) * | 2021-12-09 | 2023-04-07 | 哈尔滨工程大学 | Preheating type water inlet ramjet engine structure and control method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7194852B1 (en) * | 2005-01-07 | 2007-03-27 | Krishnan Vinu B | Propulsion from combustion of solid propellant pellet-projectiles |
| RU2461728C2 (en) * | 2010-12-03 | 2012-09-20 | Федеральное государственное унитарное предприятие "Научно-исследовательский институт полимерных материалов" | Solid-propellant rocket engine |
| CN104481696A (en) * | 2014-12-05 | 2015-04-01 | 南昌航空大学 | Contra-rotating outer framework water-air dual-purpose engine |
| CN105370439A (en) * | 2015-12-01 | 2016-03-02 | 北京航空航天大学 | Spiral-flow type water-ramjet engine |
| CN107792360A (en) * | 2017-11-29 | 2018-03-13 | 周锦宇 | Water air double-used aircraft |
| CN108791792A (en) * | 2018-06-15 | 2018-11-13 | 西南科技大学 | A kind of hydroreactive metal fuel eddy flow punching press marine propuision system |
-
2018
- 2018-12-19 CN CN201811558476.1A patent/CN109519280B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7194852B1 (en) * | 2005-01-07 | 2007-03-27 | Krishnan Vinu B | Propulsion from combustion of solid propellant pellet-projectiles |
| RU2461728C2 (en) * | 2010-12-03 | 2012-09-20 | Федеральное государственное унитарное предприятие "Научно-исследовательский институт полимерных материалов" | Solid-propellant rocket engine |
| CN104481696A (en) * | 2014-12-05 | 2015-04-01 | 南昌航空大学 | Contra-rotating outer framework water-air dual-purpose engine |
| CN105370439A (en) * | 2015-12-01 | 2016-03-02 | 北京航空航天大学 | Spiral-flow type water-ramjet engine |
| CN107792360A (en) * | 2017-11-29 | 2018-03-13 | 周锦宇 | Water air double-used aircraft |
| CN108791792A (en) * | 2018-06-15 | 2018-11-13 | 西南科技大学 | A kind of hydroreactive metal fuel eddy flow punching press marine propuision system |
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