CN115788702A

CN115788702A - Detonation thrust engine

Info

Publication number: CN115788702A
Application number: CN202310023475.1A
Authority: CN
Inventors: 魏晶晶
Original assignee: Individual
Current assignee: Individual
Priority date: 2023-01-09
Filing date: 2023-01-09
Publication date: 2023-03-14

Abstract

The invention provides a detonation thrust engine, which relates to the technical field of engines and comprises a jet pipe group, wherein the jet pipe group comprises Laval jet pipes, the jet pipe group is formed by uniformly arranging the Laval jet pipes in a circumferential manner, one end of each Laval jet pipe is provided with a detonation pipe nozzle, and one end of each Laval jet pipe, which is far away from the detonation pipe nozzle, is fixedly provided with a detonation chamber. According to the invention, continuous pulse type injection is generated by effectively controlling continuous explosion of the detonation chambers, the air inlet duct continuously provides high-pressure air (oxygen), the shunting rotary funnel has a time sequence to distribute air (oxygen) to each group of detonation chambers, the detonation valve realizes that the gas after explosion in the detonation chambers is ejected from the Laval nozzle at the highest speed to generate thrust through a simple and effective structure, the thrust generated by explosion control becomes available energy, the working principle and the working efficiency of the internal combustion engine reach a new step of the internal combustion engine, the practicability is higher, and the progress is obvious.

Description

Detonation thrust engine

Technical Field

The invention relates to the technical field of engines, in particular to a detonation thrust engine.

Background

With the development of global aircrafts, the heat of high-speed aircrafts is increased, and the most key technology of engine technology with high efficiency, high specific impulse and large thrust-weight ratio is provided, while the traditional thrust engine at present is as follows: turbine engines, turbofan engines and turboshaft engines are internal combustion engines, but are controlled only at a combustion level, rocket engines are controlled only at a deflagration level, and the existing engines cannot meet the requirement of updating day by day, so that a new-technology engine is urgently needed to realize high-speed flight, the control level of the internal combustion engine is improved to an explosion level, and the engine is simple, reliable and durable in structure.

Disclosure of Invention

The invention aims to solve the defects in the prior art and provides a detonation thrust engine.

In order to achieve the purpose, the invention adopts the following technical scheme: the utility model provides a detonation thrust engine, includes the nozzle group, the nozzle group includes the laval spray tube, the nozzle group is to be circumference align to grid by the laval spray tube and constitutes, the one end of laval spray tube is provided with detonation tube spout, the one end fixed mounting that detonation tube spout was kept away from to the laval spray tube has the detonation chamber, the detonation chamber is the one end of circumference array at the laval spray tube, the detonation chamber is the tubulose, the one end of detonation chamber is provided with reposition of redundant personnel rotary hopper, the inlet duct is installed to the one end of reposition of redundant personnel rotary hopper, the inside of detonation chamber is provided with the detonation valve body, the detonation valve body is the individual valve.

In order to ensure that high-pressure gas in a detonation chamber is only jetted towards the Laval nozzle direction, the detonation valve body comprises a flow guide curve and a flow distribution pile, the detonation valve body is cylindrical, an air passage is formed in the surface of the detonation valve body, the air passage is formed by a plurality of annular channels, the flow distribution pile is fixedly installed in the middle of the air passage, a detonation valve inlet is formed in one end of the detonation valve body, a detonation valve outlet is formed in the position, far away from the detonation valve inlet, of the detonation valve body, the flow distribution pile is in a flat cylindrical shape, the port, towards one end of the detonation valve inlet direction, of the flow distribution pile is circular, the port, towards one end of the detonation valve outlet direction, of the flow distribution pile is in a cutter mouth shape, the flow guide curve is arranged in the detonation valve body, the outlet end of the detonation valve is in a concave arc-shaped surface, and the detonation valve inlet is formed by gathering five or more than five circular arrays.

In order to make each group of detonation chambers in the detonation chambers obtain air (oxygen) in a circulating manner, the detonation chamber circulation induction device is improved in that the shunting rotating funnel comprises a funnel frame, an induction sheet and a roller body, the shunting rotating funnel is rotatably connected with the detonation chambers, one end, away from a funnel inlet, of the shunting rotating funnel is provided with a funnel outlet, the diameter of the funnel outlet is the same as that of a detonation valve, a funnel core is arranged inside the funnel frame, a transmission fixing frame, a gear fixing piece and a pinion are sequentially arranged outside the funnel frame, the gear core comprises a transmission gear, a triangular isolation region and a funnel inlet, the induction sheet is arranged in the triangular isolation region of the funnel core, one end of the roller body is rotatably connected with the roller pile, and the roller pile and the funnel frame are fixedly mounted.

In order to ensure that the shunt rotating funnel, the detonation chamber and the air inlet duct are stably and reliably installed, the invention has the improvement that the limiting piece, the fixed screw, the funnel screw and the fixed funnel piece are installed on the outer side of the funnel frame.

In order to facilitate air inlet of the air inlet duct, the air inlet duct is improved to comprise a duct fan and a fan fixing cylinder, wherein the duct fan is circular, and the duct fan is arranged inside the fan fixing cylinder.

In order to efficiently control the rhythm of detonation actions in a detonation chamber, the invention has the improvement that one end of the triangular isolation region in the funnel core, which is close to the valve body of the detonation valve, is solid, a plurality of sensing pieces are arranged at the position of the funnel core, which is close to the inlet of the funnel, and the surface of the funnel frame is provided with a position sensor.

In order to efficiently mix fuel and air (oxygen) and ensure that the explosion completely occurs in the detonation chamber, the invention improves the method that a spark plug is arranged at the position of the detonation chamber close to the Laval nozzle, and a fuel nozzle is arranged at the position of the detonation chamber close to the outlet of the detonation valve.

Compared with the prior art, the invention has the advantages and positive effects that,

according to the invention, continuous pulse type injection is generated by effectively controlling continuous explosion of the detonation chambers, the air inlet duct continuously provides high-pressure air (oxygen), the shunting rotary funnel has a time sequence to distribute air (oxygen) to each group of detonation chambers, the detonation valve realizes that the gas after explosion in the detonation chambers is ejected from the Laval nozzle at the highest speed to generate thrust through a simple and effective structure, the thrust generated by explosion control becomes available energy, the working principle and the working efficiency of the internal combustion engine reach a new step of the internal combustion engine, the practicability is higher, and the progress is obvious.

Drawings

FIG. 1 is a schematic illustration of a detonation thrust engine according to the present disclosure;

FIG. 2 is an exploded view of an intake duct and a split flow rotary funnel of a detonation thrust engine according to the present invention;

FIG. 3 is a schematic view of a funnel core of a detonation thrust engine according to the present invention;

FIG. 4 is an exploded view of a detonation chamber of a detonation thrust engine in accordance with the present invention;

FIG. 5 is a schematic diagram of a detonation valve of a detonation thrust engine according to the present invention.

Illustration of the drawings:

1. an air intake duct; 2. a ducted fan; 3. a fan fixing cylinder; 4. a flow-dividing rotary funnel; 5. a limiting member; 6. fixing screws; 7. a roller pile; 8. a roller body; 9. a position sensor; 10. a funnel frame; 11. a transmission fixing frame; 12. a gear fixing member; 13. a pinion gear; 14. an induction sheet; 15. a funnel core; 16. a funnel inlet; 17. an outlet of the funnel; 18. a triangular isolation region; 19. a transmission gear; 20. a funnel screw; 21. fixing the funnel piece; 22. a laval nozzle; 23. a detonation chamber; 24. a detonation tube spout; 25. a spark plug; 26. a fuel nozzle; 27. a detonation valve body; 28. a detonation valve inlet; 29. shunting piles; 30. a flow guiding bent channel; 31. and (4) a detonation valve outlet.

Detailed Description

In order that the above objects, features and advantages of the present invention can be more clearly understood, the present invention will be further described with reference to the accompanying drawings and examples. It should be noted that the embodiments and features of the embodiments of the present application may be combined with each other without conflict.

In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, however, the present invention may be practiced in other ways than those specifically described herein, and thus the present invention is not limited to the specific embodiments of the present disclosure.

Example one

Referring to fig. 1-5, the present invention provides a technical solution: a detonation thrust engine comprises a jet stack, the jet stack comprises a Laval jet pipe 22, the jet stack is formed by uniformly arranging Laval jet pipes 22 in a circumference manner, one end of the Laval jet pipe 22 is provided with a detonation pipe nozzle 24, one end of the Laval jet pipe 22 far away from the detonation pipe nozzle 24 is fixedly provided with a detonation chamber 23, the detonation chamber 23 is circumferentially arranged at one end of the Laval jet pipe 22, the detonation chamber 23 is in a tubular shape, one end of the detonation chamber 23 is provided with a shunting rotating funnel 4, one end of the shunting rotating funnel 4 is provided with an air inlet duct 1, the detonation chamber 23 is internally provided with a detonation valve body 27, the detonation valve body 27 is a one-way valve, particularly, the detonation valve body 27 stops the explosive airflow flowing reversely, the detonation valve body 27 comprises a diversion bend 30 and a diversion pile 29, the detonation valve body 27 is in a cylindrical shape, the surface of the detonation valve body 27 is provided with a plurality of air ducts, the middle of the air passage is fixedly provided with a shunting pile 29, one end of the detonation valve body 27 is provided with a detonation valve inlet 28, the position of the detonation valve body 27 far away from the detonation valve inlet 28 is provided with a detonation valve outlet 31, when explosion occurs in the detonation chamber 23, high-speed deflagration gas reversely enters the air passage of the detonation valve and can be shunted by a single-edge knife edge of the shunting pile 29, the shunted gas collides with the reversely entering gas after passing through the diversion curve 30, each annular structure collides with the reversely entering gas so as to block the reverse circulation of the gas, the detonation valve can be impacted by airflow impact force at the same time, so that the explosive airflow in the detonation chamber 23 is only ejected out from the Wall nozzle at the extreme speed, the shunting pile 29 is in a flat column shape, the port of the shunting pile 29 towards one end in the direction of the detonation valve inlet 28 is in a circular shape, the port of the shunting pile 29 towards one end in the direction of the detonation valve outlet 31 is in a knife edge shape, the flow guide bend 30 is arranged inside the detonation valve body 27, the end face of the detonation valve outlet 31 is a concave arc-shaped surface, the detonation valve inlet 28 is formed by gathering five air passage circular arrays, the flow distribution rotary funnel 4 comprises a funnel frame 10, an induction sheet 14 and a roller body 8, the flow distribution rotary funnel 4 is rotatably connected with the detonation chamber 23, one end of the flow distribution rotary funnel 4, which is far away from the funnel inlet 16, is provided with a funnel outlet 17, the diameter of the funnel outlet 17 is the same as that of the detonation valve, the funnel frame 10 is internally provided with a funnel core 15, the funnel frame 10 is externally provided with a transmission fixing frame 11, a gear fixing member 12 and a pinion 13 in sequence, the gear core comprises a transmission gear 19, a triangular isolation region 18 and a funnel inlet 16, the induction sheet 14 is arranged in the triangular isolation region 18 of the funnel core 15, the induction sheet 14 is arranged in one of the triangular isolation region 18 of the funnel core 15, and other induction sheets 14 are distributed at 90 degrees on the plane of the triangular isolation region 18, the roller body 8 is a rolling auxiliary guide wheel and is arranged on the surface of the funnel frame 10 and fixed by the roller pile 7, the rotation of the funnel core 15 is guided by the roller body 8 to rotate so as to avoid overlarge friction force with the funnel frame 10, one end of the roller body 8 is rotatably connected with the roller pile 7, the roller pile 7 is fixedly arranged between the funnel frame 10, the outer side of the funnel frame 10 is provided with a limiting part 5, a fixed screw 6, a funnel screw 20 and a fixed funnel part 21 so as to fix the shunt rotating funnel 4, the detonation chamber 23 is provided with an air inlet duct 1, the air inlet duct 1 comprises a duct fan 2 and a fan fixing cylinder 3, the duct fan 2 is circular, the duct fan 2 is arranged inside the fan fixing cylinder 3, one end of a triangular isolation region inside the funnel core 15, which is close to a detonation valve body 27, is solid, a plurality of induction sheets 14 are arranged at the position of the funnel core 15, which is close to a funnel inlet 16, the surface of funnel frame 10 is provided with position sensor 9, and the position department that detonation chamber 23 is close to laval nozzle 22 is provided with spark plug 25, and the position department that detonation chamber 23 is close to detonation valve export 31 is provided with fuel nozzle 26, and funnel core 15 is close to funnel import 16 and has a plurality of response pieces 14, and there is position sensor 9 outside funnel frame 10, comes the angular velocity when funnel core 15 is rotatory of the position of the triangle-shaped isolation region of obtaining funnel core 15 and funnel export 17.

The working principle is as follows: the engine outputting continuous pulse thrust is realized by controlling continuous explosion of continuous fuel and oxygen (or air) mixture, and the engine starting process comprises the following steps: the ducted fan 2 starts the compressed air (or oxygen) to enter the shunting rotating funnel 4 first, the shunting rotating funnel 4 realizes the distribution of the air (or oxygen) to the detonation valve bodies 27 of different groups through the rotation, the air (or oxygen) is fed into the two symmetrical detonation valve bodies 27, when the air (or oxygen) passes through the position of the fuel nozzle 26, the fuel nozzle 26 sprays the fuel mixed air (oxygen), the two symmetrical detonation chambers 23 are filled with the sufficient mixture of the fuel and the air (or oxygen), when the mixture is filled in the detonation chambers 23, the sparking plug 25 ignites to explode, the detonation valve inlet 28 in the detonation chambers 23 at the moment is blocked by the triangular isolation region 18, the mixed gas in the detonation chambers 23 explodes, the high-temperature and high-pressure product gas is expanded at an extremely high speed and meets the detonation valve bodies 27 to be blocked, so that the high-temperature and high-pressure product gas is sprayed out from the laval nozzle 22 at an extremely high speed to generate huge impulse thrust, the shunting rotating funnel 4 continues to rotate, and the next group of symmetrical detonation valve bodies 27 enters the air (or oxygen), and the process is repeated: the processes of air intake, ignition and explosion are repeated all the time, once the engine is ignited and started, the rhythm of pulse thrust is determined by the rotation frequency of the shunting rotary funnel 4, if the next group of symmetrical detonation chambers 23 are residues remained in the interiors which have been worked before after explosion, the front end air (or oxygen) distributed by the shunting rotary funnel 4 plays a role of blowing out miscellaneous gas to form an isolation layer, the high-speed detonation gas reversely enters the outlet 31 of the detonation valve when the detonation valve body 27 works, the reversely entering gas passage is shunted by the single-side knife edge of the shunting pile 29, the shunted gas reversely enters the gas after passing through the diversion bend 30, and each ring-shaped structure collides with the reversely entering gas so as to block the gas passage reversely passing through the detonation valve body 27.

The above description is only a preferred embodiment of the present invention, and not intended to limit the present invention in other forms, and any person skilled in the art may apply the above modifications or changes to the equivalent embodiments with equivalent changes, without departing from the technical spirit of the present invention, and any simple modification, equivalent change and change made to the above embodiments according to the technical spirit of the present invention still belong to the protection scope of the technical spirit of the present invention.

Claims

1. A detonation thrust engine comprises a jet pipe group and is characterized in that: the spout group includes laval spray tube (22), the spout group is that circumference align to grid constitutes by laval spray tube (22), the one end of laval spray tube (22) is provided with detonation tube spout (24), the one end fixed mounting that detonation tube spout (24) were kept away from in laval spray tube (22) has detonation chamber (23), detonation chamber (23) are the one end of circumference range at laval spray tube (22), detonation chamber (23) are the tubulose, the one end of detonation chamber (23) is provided with reposition of redundant personnel rotary hopper (4), inlet duct (1) is installed to the one end of reposition of redundant personnel rotary hopper (4), the inside of detonation chamber (23) is provided with detonation valve body (27), detonation valve body (27) are the individual valve.

2. The detonation thrust engine of claim 1, wherein: the detonation valve body (27) comprises a flow guide curve (30) and a shunting pile (29), the detonation valve body (27) is cylindrical, an air passage is formed on the surface of the detonation valve body (27), the air passage is formed by a plurality of annular channels, the shunting pile (29) is fixedly installed in the middle of the air passage, a detonation valve inlet (28) is formed in one end of the detonation valve body (27), a detonation valve outlet (31) is formed in the position, away from the detonation valve inlet (28), of the detonation valve body (27), shunt pile (29) are flat column body form, shunt pile (29) present circularly towards the port of detonation valve import (28) direction one end, shunt pile (29) are unilateral sword mouth form towards the port of detonation valve export (31) direction one end, water conservancy diversion bend (30) set up the inside at detonation valve body (27), detonation valve export (31) terminal surface is the arcwall face of concavity, detonation valve import (28) are assembled by the circular array of air flue more than five or five and form.

3. The detonation thrust engine of claim 1, wherein: shunt rotary funnel (4) including funnel frame (10), response piece (14) and roller body (8), shunt rotary funnel (4) and detonation chamber (23) between rotate and be connected, the funnel export (17) has been seted up to the one end that funnel import (16) was kept away from in shunt rotary funnel (4), the diameter of funnel export (17) is the same with the diameter of detonation valve, the inside of funnel frame (10) is provided with funnel core (15), transmission mount (11), gear fixing piece (12) and pinion (13) are installed in proper order to the outside of funnel frame (10), the gear core includes drive gear (19), triangle isolation region (18) and funnel import (16), the triangle (18) in funnel core (15) are installed in response piece (14), the one end rotation of roller body (8) is connected with roller stake (7), fixed mounting between roller stake (7) and funnel frame (10).

4. The detonation thrust engine of claim 3, wherein: the limiting piece (5), the fixed screw (6), the funnel screw (20) and the fixed funnel piece (21) are installed on the outer side of the funnel frame (10).

5. The detonation thrust engine of claim 1, characterized in that: the air inlet duct (1) comprises a duct fan (2) and a fan fixing cylinder (3), the duct fan (2) is circular, and the duct fan (2) is installed inside the fan fixing cylinder (3).

6. The detonation thrust engine of claim 3, wherein: the one end that funnel core (15) inside triangle-shaped isolation region (18) are close to detonation valve body (27) is solid, the position department that funnel core (15) are close to funnel import (16) is provided with a plurality of response pieces (14), the surface of funnel frame (10) is provided with position sensor (9).

7. The detonation thrust engine of claim 1, wherein: the detonation chamber (23) is provided with a spark plug (25) at a position close to the Laval nozzle (22), and the detonation chamber (23) is provided with a fuel nozzle (26) at a position close to the outlet (31) of the detonation valve.