CN203848335U - Two-stage axial blade-type cyclone machine - Google Patents
Two-stage axial blade-type cyclone machine Download PDFInfo
- Publication number
- CN203848335U CN203848335U CN201420264412.1U CN201420264412U CN203848335U CN 203848335 U CN203848335 U CN 203848335U CN 201420264412 U CN201420264412 U CN 201420264412U CN 203848335 U CN203848335 U CN 203848335U
- Authority
- CN
- China
- Prior art keywords
- twin
- axial
- wheel hub
- hub
- cylinder
- 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
Landscapes
- Cyclones (AREA)
Abstract
The utility model discloses a two-stage axial blade-type cyclone machine which comprises a barrel, an outer hub, an inner hub and a slotted cylinder. The barrel, the outer hub, the inner hub and the slotted cylinder are coaxially arranged and sequentially sleeve one another from the outside to the inside, a plurality of outer cyclone blades are arranged in gaps between the inner wall of the barrel and the outer peripheral wall of the outer hub to form outer flow channels, and a plurality of inner cyclone blades are arranged in gaps between the inner wall of the outer hub and the outer wall surface of the inner hub to form inner flow channels; the slotted cylinder is nested in the inner hub, the diameter of the slotted cylinder is equal to the inner diameter of the inner hub, an axial center through hole is formed in the slotted cylinder, a plurality of axial through holes are peripherally formed in the slotted cylinder along the outer periphery of the center through hole and are used as axial straight through holes, and a fuel spray nozzle base is nested in the center through hole in the slotted cylinder. The two-stage axial blade-type cyclone machine has the advantages that the fuel atomizing quality can be improved by the cyclone machine, turbulent mixing can be intensified, exhaust pollution can be reduced, more importantly, the two-stage axial blade-type cyclone machine is beneficial to intensifying combustion of mainstream fuel, ignition conditions can be improved, combustion can be stabilized, and working conditions of combustion chambers can be improved.
Description
Technical field
The utility model belongs to turbulent burner field, is specifically related to a kind of twin-stage bladed axial swirler.
Background technology
Swirl flow combustion is a kind of effective means of overheavy firing, and cyclone is the important device that realizes swirl flow combustion.Cyclone is one of most important parts of swirl combustion chamber, and its performance directly has influence on combustion chamber work and performance.
Because the air-flow of strong rotation produces recirculating zone, make to enter the unburned fuel of burner inner liner and the mixture of air can be lighted smoothly.The advantage such as swirl combustion chamber has compact conformation, the length of flame is short, combustion stability good, efficiency of combustion is high and pollutant discharge amount is low.And cyclone is as one of critical component of swirl combustion chamber, and the service behaviour of combustion chamber is had to direct impact.
The tissue burning of head of combustion chamber is the aspect of a worth primary study.In decades, owing to smoldering and widening the needs of stable operation range reducing, the progression of head cyclone develops into twin-stage from single-stage.Wherein twin-stage cyclone is a kind of New type cyclone, and its main function is: (1) thus making flow rotation produce centrifugal force forms recirculating zone, improve flame stabilization performance.(2) High Rotation Speed jet increases relative velocity between air-flow and oil droplet, can improve fuel-oil atmozation quality and mixed gas and form, and improves efficiency of combustion.(3) two-stage cyclones exports different air velocities and can strengthen turbulent mixture, reduces exhaust pollution.
Figure 1 shows that a kind of twin-stage axial swirler of the prior art, air-flow can produce tangential velocity after the outer flow passage by wherein and inner flow passage in exit, and rotation direction is contrary, so just can increase the relative velocity between air-flow and oil droplet, can improve fuel-oil atmozation quality, can also occur a recirculating zone contrary with mainstream speed behind at cyclone in addition.But, this cyclone of prior art also has many weak points, such as improved atomized fuel is taken to surrounding and can not well enter central combustion zone by powerful turbulent flow, the time that gaseous mixture stops in recirculating zone is in addition shorter, is unfavorable for the stable of flame and burning efficiently.
Utility model content
The purpose of this utility model is for the deficiencies in the prior art, a kind of twin-stage bladed axial swirler is provided, it is by arranging coaxially arranged bipolar eddy flow passage and in conjunction with direct current through hole, realization improves the atomization quality of fuel oil, rotational flow strengthening burning, improve efficiency of combustion, reduce the object of exhaust pollution.
The technical solution adopted in the utility model is for achieving the above object:
A kind of twin-stage bladed axial swirler, comprises cylindrical shell, outer wheel hub, inner wheel hub and the cylinder that cracks coaxially arranged and that be set with successively from outside to inside, wherein,
Space between described cylinder inboard wall and outer wheel hub periphery wall is provided with multiple outer swirl vanes, thereby and form outer flow passage; Space between described outer wheel hub inwall and inner wheel hub outside wall surface is provided with multiple inward eddy blades, thereby and form inner flow passage; The described cylinder that cracks is sleeved in described interior ring hub and its diameter equates with the internal diameter of interior ring hub, this cylinder that cracks has axial central through hole and this and cracks cylinder along this central through hole periphery along circumferentially to having multiple axially extending bores as axial DC through hole, described in crack in cylindrical described central through hole and be set with atomizer pedestal.
As improvement of the present utility model, described outer eddy flow sharf two edges are upwards connected and fixed with cylinder inboard wall and outer wheel hub periphery wall respectively.
As improvement of the present utility model, described outer eddy flow sharf to end face respectively with the two end faces of atomizer pedestal in same plane.
As improvement of the present utility model, the blade tilt of described outer swirl vane is 45 °
As improvement of the present utility model, described inward eddy sharf two edges are upwards connected and fixed with outer wheel hub internal perisporium face and inner wheel hub periphery wall respectively.
As improvement of the present utility model, described inward eddy blade axial end respectively with the two end faces of atomizer pedestal in same plane.
As improvement of the present utility model, the blade tilt of described inward eddy blade sheet is 30 °.
As improvement of the present utility model, described outer swirl vane is 12.
As improvement of the present utility model, described inward eddy blade is 12.
As improvement of the present utility model, described in the cylindrical direct current hole count of cracking of cracking be six.
The twin-stage bladed axial swirler efficiently cracking of the present utility model is by reasonably arranging section direct current hole pass into direct current wind of the surrounding at cyclone center, the area of recirculating zone obviously strengthens, reduce recirculating zone negative pressure, weaken the filling effect of main flow, reduced the turbulence intensity of wake flow, made to move after the point of main flow, cause recirculating zone elongated, thereby increase fuel oil in the time of staying of recirculating zone, improve atomizing effect, and then overheavy firing; Particularly a small amount of mist of oil forms a flame on duty that is difficult for extinguishing in the recirculating zone of high temperature, low speed, has strengthened the stabilizing power of flame and has improved efficiency of combustion.Due to the reduction of turbulence intensity, fluid loss also can reduce to some extent.Simultaneously near burner inner liner wall place, but temperature with cyclone combustion chamber, direct current hole lower than the temperature without cyclone combustion chamber, direct current hole, cooling very favourable to combustion chamber wall surface like this.
Compared with traditional twin-stage cyclone combustion chamber, the twin-stage bladed axial swirler combustion chamber intermediate fuel oil atomizing effect efficiently cracking is better, and ignition temperature is higher, and the area of high temperature is also obviously bigger than normal, therefore large with the Rong Qianggeng of cyclone combustion chamber, direct current hole, the efficiency of burning is also higher.In addition, with compared with cyclone combustion chamber, direct current hole, in cyclone exit, move backward some with the high temperature section of cyclone combustion chamber, direct current hole, avoided like this cyclone and nozzle to be burned.The utility model has been realized overheavy firing by this design, makes flame stabilization simultaneously, and has obtained higher efficiency of combustion.
Brief description of the drawings
Fig. 1 is the three-dimensional structure diagram of twin-stage axial swirler in prior art;
Fig. 2 is the part-structure figure of the twin-stage bladed axial swirler of the utility model embodiment;
Fig. 3 is the three-dimensional structure diagram of the twin-stage bladed axial swirler of the utility model embodiment.
Detailed description of the invention
Below in conjunction with accompanying drawing, detailed description of the invention of the present utility model is described further.It should be noted that at this, be used for helping to understand the utility model for the explanation of these embodiments, but do not form restriction of the present utility model.In addition,, in each embodiment of described the utility model, involved technical characterictic just can combine mutually as long as do not form each other conflict.
As Fig. 2, shown in 3, the utility model provides a kind of axial blade formula twin-stage cyclone with direct current hole, comprise barrel 1, outer shroud hub 3, interior ring hub 5, atomizer pedestal 6, cylinder 7 cracks, several outer swirl vane 2 and inward eddy blades 4, described several outer swirl vanes 2 are evenly arranged in the outer flow passage 9 forming between barrel 1 and outer shroud hub 3, if described inward eddy blade 4 all and be arranged between outer shroud hub 3 and interior ring hub 5 and form in inner flow passage 10, the described cylinder 7 that cracks is sleeved in interior ring hub 5, the diameter of cylinder 7 of cracking preferably equates with the internal diameter of interior ring hub 5, described atomizer pedestal 6 solids are in the center axially extending bore of cylinder 7 that cracks, described barrel 1, outer shroud hub 3, interior ring hub 5, atomizer pedestal 6 and the cylinder 7 that cracks have identical central axis 8.
Preferably, described outer swirl vane 2 is 12, but the quantity of the external swirl vane of the utility model is not construed as limiting.12 outer swirl vanes 2 of the present embodiment are evenly arranged between barrel 1 and outer shroud hub 3, and outer swirl vane 2 is around central axis 8 radial locations.One side of each outer swirl vane 2 is all connected with barrel 1, and opposite side is all connected with outer shroud hub 3.The intersection of blade and barrel 1 and blade and outer shroud hub 3 outer peripheral faces forms two space curves.
Preferably, described inward eddy blade 4 is 12, but the quantity of the internal swirl vane of the utility model is not construed as limiting.12 inward eddy blades 4 of the present embodiment are evenly arranged between outer shroud hub 3 and interior ring hub 5, and inward eddy blade 4 is around central axis 8 radial locations.One side of each inward eddy blade 4 is all connected with outer shroud hub 3, and opposite side is all connected with interior ring hub 5.
Preferably, the both ends of the surface of outer swirl vane 2 and inward eddy blade 4 respectively with the two end faces of atomizer pedestal 6 in same plane.
Preferably, described in the crack direct current hole of cracking of cylinder 7 be six, six direct current holes are evenly distributed in the surrounding of the cylinder 7 that cracks.Can certainly select according to actual needs more or less direct current hole.
Preferably, the blade tilt of described outer swirl vane 2 and inward eddy 4 reaches 45 ° and 30 °, and the airflow inlet speed angle of described outer swirl vane 2 is 90 °, and air stream outlet speed angle is 45 °, the airflow inlet speed angle of described inward eddy blade 4 is 90 °, and air stream outlet speed angle is-30 °.But in the utility model, the blade tilt of external swirl vane 2 and inward eddy 4 is not limited to the occurrence of above-described embodiment, can specifically select according to actual needs.
The utility model, in the situation that keeping existing structure substantially constant, along circumferentially evenly beating some direct currents hole, is introduced a certain amount of direct current wind around the cylinder 7 that cracks.Direct current wind add the adverse pressure gradient that has changed recirculating zone, so just changed the form of recirculating zone, the improvement that brings a series of performances.
The twin-stage bladed axial swirler efficiently cracking of the present utility model is in reasonably crack direct current hole pass into direct current wind of arranging section of the surrounding at cyclone center, this part air-flow can be carried a small amount of mist of oil secretly and enter recirculating zone burning, contributes to the combustion intensification of main flow fuel.Can make flame draw close to center adding of centre wind simultaneously, eliminate the lower problem of center temperature producing because of backflow, can improve ignition condition, smooth combustion, improves the working condition of combustion chamber.In addition the swirling eddy entering in inside and outside eddy flow passage also can better blending fuel oil and air, strengthen turbulent mixture, swirl strength is stronger, this effect that just makes centre wind add is more obvious, therefore not only improve fuel-oil atmozation quality and mixed gas and form, and further improve ignition condition, smooth combustion, improve efficiency of combustion, reduce exhaust pollution.
The above is preferred embodiment of the present utility model, but the utility model should not be confined to the disclosed content of this embodiment and accompanying drawing.Do not depart from the equivalence or the amendment that under spirit disclosed in the utility model, complete so every, all fall into the scope of the utility model protection.
Claims (10)
1. a twin-stage bladed axial swirler, comprises cylindrical shell (1), outer wheel hub (3), inner wheel hub (5) and the cylinder that cracks (7) coaxially arranged and that be set with successively from outside to inside, wherein,
Space between described cylindrical shell (1) inwall and outer wheel hub (3) periphery wall is provided with multiple outer swirl vanes (2), thereby and form outer flow passage; Space between described outer wheel hub (3) inwall and inner wheel hub (5) outside wall surface is provided with multiple inward eddy blades (4), thereby and form inner flow passage; The described cylinder that cracks (7) is sleeved in described inner wheel hub (5) and its diameter equates with the internal diameter of inner wheel hub (5), this cylinder that cracks (7) has axial central through hole and this cylinder that cracks (7) along this central through hole periphery along circumferentially to having multiple axially extending bores as axial DC through hole, described in crack in the described central through hole of cylinder (7) and be set with atomizer pedestal (6).
2. a kind of twin-stage bladed axial swirler according to claim 1, wherein, the two edges on described outer swirl vane (2) is axial are connected and fixed with cylindrical shell (1) inwall and outer wheel hub (3) periphery wall respectively.
3. a kind of twin-stage bladed axial swirler according to claim 2, wherein, described outer swirl vane (2) axial end respectively with the axial two end faces of atomizer pedestal (6) in same plane.
4. a kind of twin-stage bladed axial swirler according to claim 3, wherein, the blade tilt of described outer swirl vane (2) is 45 °.
5. according to a kind of twin-stage bladed axial swirler described in any one in claim 1-4, wherein, the two edges of described inward eddy blade (4) on are axially connected and fixed with outer wheel hub (3) internal perisporium face and inner wheel hub (5) periphery wall respectively.
6. a kind of twin-stage bladed axial swirler according to claim 5, wherein, described inward eddy blade (4) axial end respectively with the axial two end faces of atomizer pedestal (6) in same plane.
7. a kind of twin-stage bladed axial swirler according to claim 6, wherein, the blade tilt of described inward eddy blade (4) is 30 °.
8. according to a kind of twin-stage bladed axial swirler described in any one in claim 1-4, wherein, described outer swirl vane (2) is 12.
9. according to a kind of twin-stage bladed axial swirler described in any one in claim 1-4, wherein, described inward eddy blade (4) is 12.
10. according to a kind of twin-stage bladed axial swirler described in any one in claim 1-4, wherein, described in the crack direct current hole count of cracking of cylinder (7) be six.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420264412.1U CN203848335U (en) | 2014-05-22 | 2014-05-22 | Two-stage axial blade-type cyclone machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420264412.1U CN203848335U (en) | 2014-05-22 | 2014-05-22 | Two-stage axial blade-type cyclone machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203848335U true CN203848335U (en) | 2014-09-24 |
Family
ID=51561345
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420264412.1U Expired - Fee Related CN203848335U (en) | 2014-05-22 | 2014-05-22 | Two-stage axial blade-type cyclone machine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203848335U (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105042594A (en) * | 2015-07-21 | 2015-11-11 | 广东摩德娜科技股份有限公司 | Energy-saving burner for stirring and mixing fuel at high speed |
| CN105716113A (en) * | 2016-02-06 | 2016-06-29 | 中国科学院工程热物理研究所 | Double-cyclone premixing burner |
| CN106895397A (en) * | 2017-01-12 | 2017-06-27 | 华中科技大学 | A kind of rich or poor bimodal inner and outer ring reflux formula axle stream cyclone burner |
| CN108151063A (en) * | 2017-12-14 | 2018-06-12 | 西北工业大学 | A kind of tiny engine combustion chamber evaporation tube structure with cyclone |
| CN108392973A (en) * | 2018-05-11 | 2018-08-14 | 郭明春 | A kind of desulfuration absorbing tower spiral-flow plate-type collaboration dedusting tower integrated with desulfurization synergistic |
| CN108758692A (en) * | 2018-03-08 | 2018-11-06 | 西北工业大学 | A kind of standing vortex burning chamber with cyclone |
| CN109210573A (en) * | 2018-08-10 | 2019-01-15 | 江苏大学 | A kind of Novel variable-section aeroengine combustor buring room |
| CN109404349A (en) * | 2018-11-08 | 2019-03-01 | 中国船舶重工集团公司第七〇九研究所 | Spiral-flow type jet pump |
| CN110440286A (en) * | 2019-07-26 | 2019-11-12 | 中国航发沈阳发动机研究所 | It is a kind of for premixing the swirl-flow devices of fuel gas |
| CN110822478A (en) * | 2019-11-08 | 2020-02-21 | 哈尔滨工程大学 | Variable geometry swirler with adjustable swirl angle |
| CN111520751A (en) * | 2020-04-08 | 2020-08-11 | 西北工业大学 | Double-stage swirler and centrifugal nozzle integrated structure |
| CN111780163A (en) * | 2020-06-23 | 2020-10-16 | 江苏大学 | Swirler with continuously adjustable outlet airflow strength |
| CN111927629A (en) * | 2020-07-10 | 2020-11-13 | 西安增材制造国家研究院有限公司 | Evaporation tube structure for engine combustion chamber, combustion chamber device and preparation method |
| CN113739151A (en) * | 2021-08-16 | 2021-12-03 | 江苏大学 | Double-pipe bidirectional cyclone burner |
-
2014
- 2014-05-22 CN CN201420264412.1U patent/CN203848335U/en not_active Expired - Fee Related
Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105042594B (en) * | 2015-07-21 | 2017-11-28 | 广东摩德娜科技股份有限公司 | A kind of Energy saving burning nozzle of high-speed stirred fuel combination |
| CN105042594A (en) * | 2015-07-21 | 2015-11-11 | 广东摩德娜科技股份有限公司 | Energy-saving burner for stirring and mixing fuel at high speed |
| CN105716113A (en) * | 2016-02-06 | 2016-06-29 | 中国科学院工程热物理研究所 | Double-cyclone premixing burner |
| CN105716113B (en) * | 2016-02-06 | 2019-03-12 | 中国科学院工程热物理研究所 | Bispin premix burner |
| CN106895397B (en) * | 2017-01-12 | 2019-01-15 | 华中科技大学 | A kind of rich or poor bimodal inner and outer ring reflux formula axis stream cyclone burner |
| CN106895397A (en) * | 2017-01-12 | 2017-06-27 | 华中科技大学 | A kind of rich or poor bimodal inner and outer ring reflux formula axle stream cyclone burner |
| CN108151063A (en) * | 2017-12-14 | 2018-06-12 | 西北工业大学 | A kind of tiny engine combustion chamber evaporation tube structure with cyclone |
| CN108758692A (en) * | 2018-03-08 | 2018-11-06 | 西北工业大学 | A kind of standing vortex burning chamber with cyclone |
| CN108392973A (en) * | 2018-05-11 | 2018-08-14 | 郭明春 | A kind of desulfuration absorbing tower spiral-flow plate-type collaboration dedusting tower integrated with desulfurization synergistic |
| CN109210573A (en) * | 2018-08-10 | 2019-01-15 | 江苏大学 | A kind of Novel variable-section aeroengine combustor buring room |
| CN109210573B (en) * | 2018-08-10 | 2023-08-18 | 江苏大学 | Novel variable cross-section aeroengine combustion chamber |
| CN109404349A (en) * | 2018-11-08 | 2019-03-01 | 中国船舶重工集团公司第七〇九研究所 | Spiral-flow type jet pump |
| CN109404349B (en) * | 2018-11-08 | 2023-08-25 | 中国船舶重工集团公司第七一九研究所 | Spiral-flow type jet pump |
| CN110440286A (en) * | 2019-07-26 | 2019-11-12 | 中国航发沈阳发动机研究所 | It is a kind of for premixing the swirl-flow devices of fuel gas |
| CN110822478A (en) * | 2019-11-08 | 2020-02-21 | 哈尔滨工程大学 | Variable geometry swirler with adjustable swirl angle |
| CN110822478B (en) * | 2019-11-08 | 2020-11-03 | 哈尔滨工程大学 | Variable geometry swirler with adjustable swirl angle |
| CN111520751A (en) * | 2020-04-08 | 2020-08-11 | 西北工业大学 | Double-stage swirler and centrifugal nozzle integrated structure |
| CN111780163A (en) * | 2020-06-23 | 2020-10-16 | 江苏大学 | Swirler with continuously adjustable outlet airflow strength |
| CN111927629A (en) * | 2020-07-10 | 2020-11-13 | 西安增材制造国家研究院有限公司 | Evaporation tube structure for engine combustion chamber, combustion chamber device and preparation method |
| CN113739151A (en) * | 2021-08-16 | 2021-12-03 | 江苏大学 | Double-pipe bidirectional cyclone burner |
| CN113739151B (en) * | 2021-08-16 | 2024-03-19 | 江苏大学 | Double-tube bidirectional cyclone burner |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203848335U (en) | Two-stage axial blade-type cyclone machine | |
| RU2570989C2 (en) | Gas turbine combustion chamber axial swirler | |
| CN108072053B (en) | Rotational flow atomization device | |
| CN103196159B (en) | Annular grading trapped vortex combustor | |
| CN104676650B (en) | Reverse flow combustor allowing wider range of stable running | |
| CN108844098B (en) | Combustor head based on volute structure | |
| CN108151069B (en) | Main combustion zone radial flow combustion chamber and oil-gas mixing method | |
| CN107559881A (en) | A kind of main combustion stage uses the low pollution combustor head construction of angular injection nozzle | |
| CN105705866B (en) | Nozzle, burner and gas turbine | |
| CN105041539A (en) | Multilevel rotational flow combined type air atomized fuel nozzle device and control method thereof | |
| CN205065799U (en) | A flame holder for combustion chamber and combustion chamber thereof | |
| CN104534515B (en) | Gas-turbine combustion chamber head construction | |
| CN107726364B (en) | Evaporation tube combustion chamber | |
| CN109539314A (en) | A kind of novel radial swirler with wave blade | |
| CN104373962A (en) | Blade type air inlet swirl nozzle for combustion chamber of gas turbine | |
| CN106016364B (en) | A kind of gas turbine dry low pollution combustor unit two divides swirl-flow premixed burner noz(zle) | |
| CN102384489A (en) | Small-sized annular combustion chamber with high-capacity heat intensity | |
| CN106524154B (en) | A kind of classification combustion gas low NO | |
| CN107327872A (en) | A kind of oblique spray ring stream toroidal combustion chamber | |
| CN105588144B (en) | Flame smooth combustion apparatus and flame smooth burning method for gas-turbine combustion chamber | |
| CN103266922A (en) | Turbine stator blade with interstage combustor | |
| CN104566472B (en) | A kind of nozzle and gas turbine | |
| CN203586284U (en) | Axial blade type cyclone with direct flow holes | |
| CN110440290B (en) | Micro-mixing nozzle for gas turbine | |
| CN113464982A (en) | Center staged combustion chamber based on self-excitation sweep oscillation fuel nozzle |
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: 20160819 Address after: 5, building 999, block A, overseas talent building, 430000 hi tech Avenue, East Lake hi tech Development Zone, Hubei, Wuhan Patentee after: WUHAN HUAWU AVIATION TECHNOLOGY Co.,Ltd. Address before: 430074 Hubei Province, Wuhan city Hongshan District Luoyu Road No. 1037 Patentee before: Huazhong University of Science and Technology |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210104 Address after: No.1, 20th floor, R & D building / unit 1, modern service industry base, Science Park, Huazhong University of science and technology, No.13-1, daxueyuan Road, Donghu New Technology Development Zone, Wuhan City, Hubei Province, 430000 Patentee after: Wuhan Huazhong Science and technology large Industry Group Co.,Ltd. Address before: 5 / F, block a, overseas talents building, 999 Gaoxin Avenue, Donghu hi tech Development Zone, Wuhan City, Hubei Province, 430000 Patentee before: WUHAN HUAWU AVIATION TECHNOLOGY Co.,Ltd. |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140924 |