CN113374597A - Self-excited detonation engine - Google Patents
Self-excited detonation engine Download PDFInfo
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- CN113374597A CN113374597A CN202110208734.9A CN202110208734A CN113374597A CN 113374597 A CN113374597 A CN 113374597A CN 202110208734 A CN202110208734 A CN 202110208734A CN 113374597 A CN113374597 A CN 113374597A
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- detonation
- pressure wave
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- pressure
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- 238000005474 detonation Methods 0.000 title claims abstract description 96
- 239000003999 initiator Substances 0.000 claims abstract description 21
- 239000007921 spray Substances 0.000 claims abstract description 21
- 239000000446 fuel Substances 0.000 claims abstract description 8
- 238000001816 cooling Methods 0.000 claims abstract description 6
- 239000007789 gas Substances 0.000 description 24
- 238000002485 combustion reaction Methods 0.000 description 23
- 238000000034 method Methods 0.000 description 12
- 230000000977 initiatory effect Effects 0.000 description 9
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 230000001902 propagating effect Effects 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000004200 deflagration Methods 0.000 description 2
- 239000002360 explosive Substances 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 239000000969 carrier Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
Images
Classifications
-
- 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
- F02K7/02—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 the jet being intermittent, i.e. pulse-jet
Abstract
The multiple self-excited detonation engines mainly comprise air inlet pipes or air inlet channels, valves (with valves or without valves), detonation chambers, detonators (negative angle devices), spray pipes, fuel supply systems, ignition systems, cooling systems, control systems and the like; the detonation chamber consists of a thrust wall, a detonation tube and a convergence tube; the initiator is a device with a plurality of (at least one) internal corners, and each internal corner corresponds to a focusing and/or converging reflection area of the detonation chamber and/or the inner wall of the spray pipe on pressure waves; the pressure wave refers to an air inlet pressure wave, an atmospheric pressure wave returned from the rear end of the spray pipe or a high-temperature and high-pressure gas pressure wave. The technical scheme adopted by the invention is as follows: the detonation is achieved by the concentration of pressure wave energy in the detonation chamber and/or the nozzle by the initiator.
Description
The technical field is as follows:
the invention relates to a plurality of self-excited detonation engines, which are suitable for fuel oil and gas carriers and equipment and are novel concept engines based on detonation combustion.
Background art:
various engines (mainly including piston engines and jet engines) at present organize combustion based on a deflagration mode; deflagration is also called slow combustion, combustion waves are transmitted at subsonic speed (about several meters to dozens of meters per second) in the combustion process, the combustion and energy release speed is low, the combustion intensity is low, constant pressure combustion is realized, and the thermal cycle efficiency is low (about 27%). Since detonation is relatively easy to implement and control, it has achieved wide application.
The detonation combustion is a combustion mode that the detonation material can detonate by being excited by the detonation wave, the detonation wave is a supersonic (about several kilometers per second) combustion wave with a compression function, the detonation wave hardly influences a wavefront mixed gas in the combustion process, the detonation combustion is close to constant volume combustion, and the thermal cycle efficiency is high (about 49%).
The engine based on detonation combustion has the advantages of high combustion and energy release speed, high combustion intensity, high thermal cycle efficiency, low fuel consumption rate, self-contained detonation wave compression function, no need of compression equipment, simple structure, small volume, light weight, high thrust-weight ratio, large specific impulse and the like.
Although the detonation engine has a plurality of advantages, the detonation engine is still in an exploration and research stage at present due to the technical defects, the true application cannot be realized, and mainly the problems of high-frequency detonation, working stability and the like are not substantially developed.
In order to overcome the defects of the prior art, the multiple self-excitation detonation engines disclosed by the invention are simple in structure, small in size, light in weight, high in thrust-weight ratio and large in specific impulse, can perform automatic high-frequency detonation, and are stable and reliable in work.
The invention content is as follows:
the multiple self-excited detonation engines mainly comprise air inlet pipes or air inlet channels, valves (with valves or without valves), detonation chambers, detonators (negative angle devices), spray pipes, fuel supply systems, ignition systems, cooling systems, control systems and the like; the detonation chamber consists of a thrust wall, a detonation tube and a convergence tube; the initiator is a device with a plurality of (at least one) internal corners, and each internal corner corresponds to a focusing and/or converging reflection area of the detonation chamber and/or the inner wall of the spray pipe on pressure waves; the pressure wave refers to an air inlet pressure wave, an atmospheric pressure wave returned from the rear end of the spray pipe or a high-temperature and high-pressure gas pressure wave.
The technical scheme adopted by the invention is as follows: the detonation is achieved by the concentration of pressure wave energy in the detonation chamber and/or the nozzle by the initiator.
Description of the drawings:
FIG. 1, FIG. 2, schematic transverse structural view of a valved detonation engine (four and six reentrant initiators, respectively)
FIG. 3, FIG. 4, schematic longitudinal structure of valvular detonation engine (adopting detonating primer with different length and length respectively)
FIG. 5, FIG. 6, longitudinal structure schematic diagram of valveless detonation engine (adopting different length and length exploders respectively)
In the figure: 1, an air inlet pipe; 2-a nozzle; 3-rotating the valve; 4-rotating valve gas inlet; 5-thrust wall (closed thrust wall in fig. 5, 6); 6-thrust wall air inlet; 7-a spark plug; 8-a detonation tube; 9-convergent tube (inner wall parabolic): 10-an exploder (the exploder is provided with a cooling hole or a fuel nozzle for cooling and cooling); 11-detonation wave; 12-spray pipe.
Connection process (fig. 3, fig. 4): the air inlet pipe 1 is connected with a thrust wall 5; the thrust wall 5 is connected with a detonation tube 8; the detonation pipe 8 is connected with the convergence pipe 9; the convergent pipe 9 is connected with a spray pipe 12; the nozzle 2 is connected with an air inlet pipe 1; the rotary valve 3 is connected with a thrust wall 5; the initiator 10 is coupled to the thrust wall 5 (fig. 3) and the longitudinal edges of the initiator 10 are coupled to the nozzles 12 (fig. 4); the spark plug 7 is coupled to a detonation tube 8.
Connection process (fig. 5, fig. 6): the air inlet pipe 1 is connected with a convergent pipe 9; the two ends of the convergent pipe 9 are respectively connected with a detonation pipe 8 and a spray pipe 12; the thrust wall 5 is connected with a detonation tube 8; the initiator 10 is coupled to the thrust wall 5 (fig. 5) and the longitudinal edges of the initiator 10 are coupled to the nozzles 12 (fig. 6); the nozzle 2 is connected with a tail nozzle 12; the spark plug 7 is connected with the detonation tube 8 or the thrust wall 5; the intake pipe 1 and the nozzle 2 may be provided at the front end of the thrust wall 5 (not shown).
The specific implementation mode is as follows:
the working cycle of the engine in fig. 3 and 4 comprises four basic processes of air intake, detonation, combustion (detonation wave propagation) and exhaust.
Firstly, air intake: firstly, opening a rotary valve, and pumping compressed air into an air inlet pipe or enabling an engine to move in the air, so that the air flowing from the air inlet pipe to a detonation chamber is provided; then the nozzle injects fuel and mixes with air in the air inlet pipe to enter the detonation chamber, and the rotary valve is closed when a proper amount of mixed gas enters.
II, detonating: when the rotary valve is closed, the spark plug ignites the mixed gas to make the mixed gas explode and generate high-temperature and high-pressure gas, pressure waves of the high-temperature and high-pressure gas are transmitted to the periphery at indoor sound velocity, part of scattered pressure waves are reflected and converged to the internal corner of the initiator through the detonation chamber, the pressure waves transmitted in the direction parallel to the axis of the convergent tube are reflected and focused to the internal corner of the initiator through the convergent tube, the pressure and the temperature of the mixed gas in the internal corner of the initiator are rapidly increased, the mixed gas is excited to explode and combust, and accordingly, explosion waves are generated.
Thirdly, combustion: the detonation wave generated by detonation propagates to the periphery at supersonic speed (about several kilometers per second), the mixed gas at the part where the detonation wave passes undergoes violent chemical reaction, and simultaneously, the high-speed energy release is accompanied, so that the pressure and the temperature of the detonation product after detonation are sharply increased (the pressure can reach 100 atmospheric pressures, and the temperature can reach 2000 ℃); and in the detonation wave propagation process, the expansion pressure of the detonation product assists in propelling the detonation wave to continue to propagate to the periphery until all the mixed gas knocks, and the detonation wave is discharged out of the detonation chamber.
Fourthly, exhausting gas: after the detonation wave is discharged, detonation products (high-temperature and high-pressure fuel gas) are sprayed out from the spray pipe (hereinafter referred to as exhaust), and thrust is generated at the same time, so that heat energy is converted into mechanical energy.
In the exhaust process, the detonation chamber forms a short-time negative pressure state due to the inertia effect of the gas flow, the rotary valve is opened at the moment, the mixed gas in the gas inlet pipe automatically enters the detonation chamber, the rotary valve is closed at proper time, and then the last working cycle process of detonation, combustion and exhaust is carried out; in this way, the engine can work continuously.
The working cycle process of the engine in fig. 5 and 6 is the same as that in fig. 3 and 4, auxiliary air intake and negative pressure forming of the detonation chamber through exhaust are also needed when the engine starts to work, and the engine enters the working cycle process of automatic air intake, detonation, combustion and exhaust. Since no mechanical valve causes part of the energy loss, a rear mechanical valve can be arranged at the air inlet pipe to prevent the energy loss.
The detonation mode of the engine is realized by reflecting, focusing and/or reflecting high-temperature and high-pressure gas pressure waves by the detonation chamber and converging the waves to the internal corner of the detonator; in addition, the detonation can be realized by the concentration of other pressure wave energy by the detonator.
Pressure-entering initiation: when the engine knocking chamber in fig. 3-6 is charged with negative pressure and the intake pressure wave has a higher energy head, the intake pressure wave propagating parallel to the axis direction of the convergent tube in fig. 3 and 4, and the reflected pressure wave propagating parallel to the axis direction of the convergent tube after being reflected by the thrust wall at the closed end in fig. 5 and 6 are reflected and focused to the internal corner of the initiator through the respective convergent tube to realize initiation; in addition, in the processes of propagation, the intake pressure wave in the figures 3-6 is scattered to the detonation chamber and/or the spray pipe, and is reflected by the detonation chamber and/or the spray pipe and converged to the internal corner of the initiator to realize initiation.
Back pressure initiation: in the engine shown in fig. 3 to 6, when the exhaust of the engine is finished, the inertially ejected gas flow makes the nozzle form a negative pressure state, so that the atmospheric pressure wave at the rear end of the nozzle returns to the detonation chamber, and after being reflected by the respective thrust wall, the reflected pressure wave propagating in the direction parallel to the axis of the convergent tube is reflected by the respective convergent tube and focused to the internal corner of the initiator to realize the initiation; in addition, the atmospheric pressure wave returned from the rear end of the spray pipe in fig. 3-6 is scattered to the spray pipe and the detonation chamber in the propagation process, and is reflected by the spray pipe and/or the detonation chamber and converged to the internal corner of the initiator to realize initiation.
And (3) spontaneous combustion initiation: in the engines of fig. 3 to 6, the mixed gas is spontaneously combusted by the high-temperature detonation tube, the convergent tube or the nozzle tube to generate high-temperature and high-pressure gas, and the detonation is realized by focusing or converging the pressure wave of the high-temperature and high-pressure gas to the internal corner of the detonator.
The location of the focused detonation in the engine of fig. 3-6 is in the reentrant corner of the parabolic axis peripheral detonator; the convergent detonation is in the internal corner of the detonators at the convergence point or line periphery.
Because the pressure wave has the characteristic of scattering, the pressure wave with different propagation directions or wave fronts adopts a thrust wall, a detonation tube, a convergent tube or a spray tube with corresponding shapes and an initiator with corresponding positions, lengths and internal corner numbers, so that the pressure wave is focused and/or converged and reflected and focused and/or reflected to the internal corner of the initiator to excite mixed gas initiation (the initiation is realized by the concentration of pressure wave energy in a detonation chamber and/or the spray tube by the initiator for short). In order to improve the success rate of detonation, a fuel nozzle can be additionally arranged in the detonator, the detonation chamber or the spray pipe, so that the mixed gas in the internal corner of the detonator reaches explosive concentration.
This type of engine is called a self-excited detonation engine, because the detonation of the mixture (explosive fuel) is automatically initiated by the collection of pressure wave energy in the detonation chamber and/or nozzle by the detonator. The thrust force generated by detonation wave generated by detonation and high-temperature and high-pressure gas generated by the detonation wave is intermittent pulse type, and belongs to the category of pulse detonation engines. In the working process, the cycle process from air inlet, detonation to combustion and exhaust is carried out quickly, the frequency is very high, and the pulse output is similar to continuous output.
Claims (2)
1. The multiple self-excited detonation engines mainly comprise air inlet pipes or air inlet channels, valves (with valves or without valves), detonation chambers, detonators (negative angle devices), spray pipes, fuel supply systems, ignition systems, cooling systems, control systems and the like; the detonation chamber consists of a thrust wall, a detonation tube and a convergence tube; the initiator is a device with a plurality of (at least one) internal corners, and each internal corner corresponds to a focusing and/or converging reflection area of the detonation chamber and/or the inner wall of the spray pipe on pressure waves; the pressure wave refers to an air inlet pressure wave, an atmospheric pressure wave returned from the rear end of the spray pipe or a high-temperature and high-pressure gas pressure wave.
2. The detonation is achieved by the concentration of pressure wave energy in the detonation chamber and/or the nozzle by the initiator.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010117916 | 2020-02-25 | ||
| CN2020101179160 | 2020-02-25 |
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| CN113374597A true CN113374597A (en) | 2021-09-10 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5937635A (en) * | 1996-11-27 | 1999-08-17 | Lockheed Martin Corporation | Pulse detonation igniter for pulse detonation chambers |
| US20050279083A1 (en) * | 2004-06-18 | 2005-12-22 | General Electric Company | Folded detonation initiator for constant volume combustion device |
| CN104500272A (en) * | 2014-11-26 | 2015-04-08 | 南京航空航天大学 | Low-flow-resistant near-wall small-space annular shock wave focusing direct priming device |
| CN107905915A (en) * | 2017-10-23 | 2018-04-13 | 西北工业大学 | A kind of pulse-knocking engine pressure anti-pass suppresses structure |
| CN110410232A (en) * | 2019-07-05 | 2019-11-05 | 华中科技大学 | A kind of shock wave focus spark knock burner and its ignition and detonation method |
| CN110541774A (en) * | 2018-05-29 | 2019-12-06 | 中国人民解放军国防科技大学 | rotary detonation ramjet engine and hypersonic aircraft |
-
2021
- 2021-02-25 CN CN202110208734.9A patent/CN113374597A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5937635A (en) * | 1996-11-27 | 1999-08-17 | Lockheed Martin Corporation | Pulse detonation igniter for pulse detonation chambers |
| US20050279083A1 (en) * | 2004-06-18 | 2005-12-22 | General Electric Company | Folded detonation initiator for constant volume combustion device |
| CN104500272A (en) * | 2014-11-26 | 2015-04-08 | 南京航空航天大学 | Low-flow-resistant near-wall small-space annular shock wave focusing direct priming device |
| CN107905915A (en) * | 2017-10-23 | 2018-04-13 | 西北工业大学 | A kind of pulse-knocking engine pressure anti-pass suppresses structure |
| CN110541774A (en) * | 2018-05-29 | 2019-12-06 | 中国人民解放军国防科技大学 | rotary detonation ramjet engine and hypersonic aircraft |
| CN110410232A (en) * | 2019-07-05 | 2019-11-05 | 华中科技大学 | A kind of shock wave focus spark knock burner and its ignition and detonation method |
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