CN203347940U - Deflagration jet engine - Google Patents
Deflagration jet engine Download PDFInfo
- Publication number
- CN203347940U CN203347940U CN 201320413277 CN201320413277U CN203347940U CN 203347940 U CN203347940 U CN 203347940U CN 201320413277 CN201320413277 CN 201320413277 CN 201320413277 U CN201320413277 U CN 201320413277U CN 203347940 U CN203347940 U CN 203347940U
- Authority
- CN
- China
- Prior art keywords
- ring
- magnetic field
- jet engine
- ion generating
- electrode
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 238000004200 deflagration Methods 0.000 title abstract 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 20
- 239000007788 liquid Substances 0.000 claims abstract description 13
- 239000006200 vaporizer Substances 0.000 claims abstract description 11
- 238000005474 detonation Methods 0.000 claims description 16
- 210000000867 larynx Anatomy 0.000 claims description 13
- 238000002347 injection Methods 0.000 claims description 12
- 239000007924 injection Substances 0.000 claims description 12
- 239000002737 fuel gas Substances 0.000 claims description 11
- 239000000443 aerosol Substances 0.000 claims description 3
- 238000010304 firing Methods 0.000 claims description 3
- 239000002184 metal Substances 0.000 claims description 3
- 229920000642 polymer Polymers 0.000 claims description 3
- 239000003380 propellant Substances 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 abstract 1
- 150000002500 ions Chemical class 0.000 description 14
- 239000000567 combustion gas Substances 0.000 description 4
- 239000007789 gas Substances 0.000 description 4
- 239000007921 spray Substances 0.000 description 4
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 3
- 239000001257 hydrogen Substances 0.000 description 3
- 150000002431 hydrogen Chemical class 0.000 description 3
- 229910052739 hydrogen Inorganic materials 0.000 description 3
- 230000007935 neutral effect Effects 0.000 description 3
- 239000001301 oxygen Substances 0.000 description 3
- 229910052760 oxygen Inorganic materials 0.000 description 3
- 239000002245 particle Substances 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 230000004907 flux Effects 0.000 description 2
- 239000008187 granular material Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000003595 mist Substances 0.000 description 2
- CBENFWSGALASAD-UHFFFAOYSA-N Ozone Chemical compound [O-][O+]=O CBENFWSGALASAD-UHFFFAOYSA-N 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000005431 greenhouse gas Substances 0.000 description 1
- GPRLSGONYQIRFK-UHFFFAOYSA-N hydron Chemical compound [H+] GPRLSGONYQIRFK-UHFFFAOYSA-N 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- -1 oxonium ion Chemical class 0.000 description 1
- 238000010792 warming Methods 0.000 description 1
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- Plasma Technology (AREA)
Abstract
The utility model provides a deflagration jet engine. The deflagration jet engine comprises a liquid water vaporizer, an annular plasma arc generator, a tubular magnetic field accelerator, an ion generating combination electrode, an annular electronic igniter and a contractible gas jet tail pipe. The annular plasma arc generator is arranged at the back of the liquid water vaporizer, the tubular magnetic field accelerator is arranged at the back of the annular plasma arc generator, the ion generating combination electrode is arranged at the back of the tubular magnetic field accelerator, the annular electronic igniter is arranged at the back of the ion generating combination electrode, and the contractible gas jet tail pipe is arranged at the back of the annular electronic igniter. The deflagration jet engine has the advantages of being high in efficiency, long in service life and simple to maintain and causing no pollution to the environment and the like, is suitable for a high-technology power device and is a jet power system with water serving as a propellant.
Description
Technical field
The utility model belongs to the energy source and power field, relates in particular to a kind of detonation jet engine.
Background technique
Between global warming, melt on the iceberg, polar region, and sea level rise, and the increasing more and more severe tendency of changes of earth environment that waits in earth ozone cavity more and more needs to improve environmental protection consciousness in our life.Accordingly, the pressure aspect energy-saving and emission-reduction, minimizing greenhouse gas emission is increasing.Under this background, the new traffic tool that the environment protection type resource of take is driving source more and more becomes the existing new selection that fuel oil or colliery burning be the driving source traffic tool of take.
The model utility content
The deficiency existed for prior art, the purpose of this utility model is to provide a kind of detonation jet engine of nonstaining property exhaust emissions.
For achieving the above object, the utility model provides a kind of detonation jet engine, comprise the liquid water vaporizer, the ring-type plasma arc generator, tubulose magnetic field accelerator, ion generating combination electrode, but ring-type ignition and reducing fuel gas injection tail larynx, described ring-type plasma arc generator is arranged on the rear of described liquid water vaporizer, described tubulose magnetic field accelerator is arranged on the rear of described ring-type plasma arc generator, described ion generating combination electrode is arranged on the rear of described tubulose magnetic field accelerator, described ring-type ignition is arranged on the rear of described ion generating combination electrode, but described reducing fuel gas injection tail larynx is arranged on the rear of described ring-type ignition.
Preferably, described ion generating combination electrode is composited by ion-atmosphere guiding cone and the pipe that is looped around the described ion-atmosphere guiding cone outside, described pipe is by the spiralization of a plurality of rectangular electrode sheet, adjacent two described rectangular electrode sheet polarity are contrary, described pipe front end is communicated with tubulose magnetic field accelerator, and described pipe rear is communicated with described ring dress ignition.
Preferably, the cone ionic state aerosol diversion component of described ion-atmosphere guiding cone for being surrounded by the metal electrode film of a plurality of spirals, isolate also bondingly by insulating polymer between described electrode slices, and the polarity of adjacent two described electrode slicess is contrary.
Preferably, described ring-type ignition has a pipeline that is provided with a plurality of firing head, and described pipeline front end is communicated with described ion generating combination electrode, but described reducing fuel gas injection tail larynx is movably arranged on described rear end of pipeline.
The utility model provides a kind of detonation jet engine, has that efficiency is high, advantages such as long service life, maintenance are simple, environmentally safe, is applicable to the high-tech power equipment, and the detonation jet engine is a kind of injection power system that water is propellant agent of take.This detonation jet engine is injected plasma arc by the water particulate, the water particulate that sees through plasma arc is ionized to hydrogen ion and oxonium ion plasma state material grains, ionic state material grains after ionization through becoming after the magnetic field accelerator accelerates at a high speed, high-pressure ion group become inflammable gas light via the ring-type ignition after the ion generating utmost point remove electricity after from jet tail larynx ejection detonation gas, the reaction force that the pressurized gas ejection produces promotes body and moves.
The accompanying drawing explanation
The structural representation that Fig. 1 is the utility model detonation jet engine.
In figure: 1-liquid water vaporizer, 2-ring-type plasma arc generator, 3-tubulose magnetic field accelerator, the 4-pipe, 5-ion-atmosphere guiding cone, 6-ring-type ignition, but 7-reducing fuel gas injection tail larynx, 8-disc-shaped plasma arc, 9-accelerates magnetic flux field.
Embodiment
Below in conjunction with accompanying drawing, the utility model is described further:
Please refer to Fig. 1, the structural representation that Fig. 1 is the utility model detonation jet engine.
In a kind of embodiment, a kind of detonation jet engine that the utility model provides, comprise the liquid water vaporizer, ring-type plasma arc generator 2, tubulose magnetic field accelerator 3, ion generating combination electrode, but ring-type ignition 6 and reducing fuel gas injection tail larynx 7, described ring-type plasma arc generator 2 is arranged on the rear of described liquid water vaporizer, described tubulose magnetic field accelerator 3 is arranged on the rear of described ring-type plasma arc generator 2, described ion generating combination electrode is arranged on the rear of described tubulose magnetic field accelerator 3, described ring-type ignition 6 is arranged on the rear of described ion generating combination electrode, but described reducing fuel gas injection tail larynx 7 is arranged on the rear of described ring-type ignition 6.
Described ion generating combination electrode is composited by ion-atmosphere guiding cone 5 and the pipe 4 that is looped around described ion-atmosphere guiding cone 5 outsides, described pipe 4 is by the spiralization of a plurality of rectangular electrode sheet, adjacent two described rectangular electrode sheet polarity are contrary, described pipe 4 front ends are communicated with tubulose magnetic field accelerator 3, and described pipe 4 rears are communicated with described ring dress ignition.
The cone ionic state aerosol diversion component that described ion-atmosphere guiding cone 5 surrounds for the metal electrode film by a plurality of spirals, isolate also bondingly by insulating polymer between described electrode slices, the polarity of adjacent two described electrode slicess is contrary.
Described ring-type ignition 6 has a pipeline that is provided with a plurality of firing head, and described pipeline front end is communicated with described ion generating combination electrode, but described reducing fuel gas injection tail larynx 7 is movably arranged on described rear end of pipeline.Gas spray tail larynx 7 be a kind of can convergent-divergent jet tail mouth and adjust the equipment of jet direction, it can adjust direction and delivery pressure by the requirement of driver by the combustion gas be blown into.
The working procedure of detonation jet engine:
The first step, liquid water injects from liquid water vaporizer 1 entrance, at the interior liquid water of liquid water vaporizer 1, is vaporized into steam state granule water; Second step, steam state granule water sprays at a high speed in ring-type plasma arc generator 2, and the disc-shaped plasma arc 8 produced by ring-type plasma arc generator 2 is ionized into hydrogen, oxygen plasma state molecule; The 3rd step, hydrogen, oxygen plasma state molecule spray to tubulose magnetic field accelerator 3, the acceleration magnetic flux field 9 of tubulose magnetic field accelerator 3 interior generations is accelerated to inject in the pipe 4 of ion generating combination electrode by the ionic state molecule of suction, the ionic state particle mist particle of flowing through by ion-atmosphere guiding cone 5 water conservancy diversion is by contact and conduction, and positive and negative electrical ionic state particle mist goes the electrode effect to lose electrically to become neutral combustion gas due to difference; The 4th step, neutral combustion gas enters in the ignition pipeline, but neutral combustion gas after being lighted, from reducing fuel gas injection tail larynx 7 interior high speeds, high pressure, spray, make equipment moving thereby produce reaction force acts in the equipment body.
Wherein, ion generating combination electrode is not only removed electricity to hydrogen, oxygen plasma, also can be the powered battery of other equipment.
Above-described embodiment is only for the utility model creation example clearly is described, and not the utility model is created the restriction of embodiment.For those of ordinary skill in the field, can also make other changes in different forms on the basis of the above description.Here exhaustive without also giving all mode of executions.All any apparent variations of being extended out within spirit of the present utility model and principle or change are still among the utility model is created the protection domain of claim.
Claims (4)
1. a detonation jet engine, it is characterized in that, comprise the liquid water vaporizer, the ring-type plasma arc generator, tubulose magnetic field accelerator, ion generating combination electrode, but ring-type ignition and reducing fuel gas injection tail larynx, described ring-type plasma arc generator is arranged on the rear of described liquid water vaporizer, described tubulose magnetic field accelerator is arranged on the rear of described ring-type plasma arc generator, described ion generating combination electrode is arranged on the rear of described tubulose magnetic field accelerator, described ring-type ignition is arranged on the rear of described ion generating combination electrode, but described reducing fuel gas injection tail larynx is arranged on the rear of described ring-type ignition.
2. detonation jet engine according to claim 1, it is characterized in that, described ion generating combination electrode is composited by ion-atmosphere guiding cone and the pipe that is looped around the described ion-atmosphere guiding cone outside, described pipe is by the spiralization of a plurality of rectangular electrode sheet, adjacent two described rectangular electrode sheet polarity are contrary, described pipe front end is communicated with tubulose magnetic field accelerator, and described pipe rear is communicated with described ring dress ignition.
3. detonation jet engine according to claim 2, it is characterized in that, the cone ionic state aerosol diversion component that described ion-atmosphere guiding cone surrounds for the metal electrode film by a plurality of spirals, between described electrode slices, by insulating polymer, isolate and bonding, the polarity of adjacent two described electrode slicess is contrary.
4. according to the arbitrary described detonation jet engine of claim 1-3, it is characterized in that, described ring-type ignition has a pipeline that is provided with a plurality of firing head, described pipeline front end is communicated with described ion generating combination electrode, but described reducing fuel gas injection tail larynx is movably arranged on described rear end of pipeline.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320413277 CN203347940U (en) | 2013-07-11 | 2013-07-11 | Deflagration jet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320413277 CN203347940U (en) | 2013-07-11 | 2013-07-11 | Deflagration jet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203347940U true CN203347940U (en) | 2013-12-18 |
Family
ID=49747850
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320413277 Expired - Fee Related CN203347940U (en) | 2013-07-11 | 2013-07-11 | Deflagration jet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203347940U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108120623A (en) * | 2018-01-12 | 2018-06-05 | 西华大学 | A kind of diesel engine particulate object grading sampling device and its control method |
-
2013
- 2013-07-11 CN CN 201320413277 patent/CN203347940U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108120623A (en) * | 2018-01-12 | 2018-06-05 | 西华大学 | A kind of diesel engine particulate object grading sampling device and its control method |
| CN108120623B (en) * | 2018-01-12 | 2023-09-01 | 西华大学 | Hierarchical sampling device for exhaust particulate matters of diesel engine and control method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20160414 Address after: 101106, No. 43, national defense Road, West Town, Beijing, Tongzhou District. A53 Patentee after: Li Zengmin Address before: 101106, No. 43, national defense Road, West Town, Beijing, Tongzhou District. A53 Patentee before: JIAHAO NEW ENERGY INVESTMENT Co.,Ltd. |
|
| CX01 | Expiry of patent term |
Granted publication date: 20131218 |
|
| CX01 | Expiry of patent term | ||
| CU01 | Correction of utility model |
Correction item: Termination upon expiration of patent Correct: Revocation of Patent Expiration and Termination False: On July 28, 2023, the expiration and termination of the 39-volume 3002 patent Number: 30-02 Volume: 39 |
|
| CU01 | Correction of utility model | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20131218 |