CN219530928U - Flame tube, engine and helicopter - Google Patents
Flame tube, engine and helicopter Download PDFInfo
- Publication number
- CN219530928U CN219530928U CN202320164164.2U CN202320164164U CN219530928U CN 219530928 U CN219530928 U CN 219530928U CN 202320164164 U CN202320164164 U CN 202320164164U CN 219530928 U CN219530928 U CN 219530928U
- Authority
- CN
- China
- Prior art keywords
- flame
- jet
- flame tube
- tube
- inner ring
- 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.)
- Active
Links
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
The utility model relates to a flame tube, an engine and a helicopter, wherein the flame tube comprises a flame inner ring and a flame outer ring, one ends of the flame inner ring and the flame outer ring are connected through a mounting plate to form an annular cavity, a plurality of mounting holes for mounting nozzles are uniformly arranged on the mounting plate around the axis of the flame tube, a plurality of jet pipes are uniformly arranged on the outer edge of each mounting hole around the axis of the flame tube, the plurality of jet pipes are spirally arranged around the axis of the mounting hole where the jet pipes are positioned, and the jet pipes are communicated with the annular cavity. The structure of the jet pipe additionally arranged at the flame tube head mounting plate can effectively replace a vortex device, lighten the weight of the flame tube and simplify the structure of an engine.
Description
Technical Field
The utility model relates to the technical field of aeroengines and gas turbines, in particular to a flame tube, an engine and a helicopter.
Background
In recent years, small aeroengines and gas turbines are research hot spots at home and abroad, and have the advantages of small volume, light weight, large output energy, high density and the like. The design of the combustor is a critical element in a gas turbine engine in which fuel or propellant is combusted to produce high temperature gas. In the annular combustion chamber, the casing and the flame tube are of an integral annular structure, so that the annular combustion chamber is compact in layout, small in windward area and high in space utilization rate, is convenient to match with the air flow of the outlet of the air compressor, reduces pressure loss, improves pneumatic efficiency, enhances combustion efficiency and reduces required cooling air quantity.
The main combustion zone of the flame tube is a main area for igniting, stabilizing flame and burning in the combustion chamber, and physicochemical reactions occurring in the main combustion zone are as follows: fuel atomization, vaporization, mixing, and combustion chemistry. The typical structure of the existing main combustion area mainly comprises a vortex device, a flame tube wall, a main combustion hole and the like, and a stable low-speed backflow area is formed under the combined action of the vortex device and the main combustion hole, so that the reliable ignition and stable combustion of the combustion chamber are ensured; the jet flow of the main combustion hole cuts off the high-temperature fuel gas, so that the main combustion is ensured to be completed in the main combustion area.
The design of the main combustion area of the existing flame tube mainly has the following defects: in order to generate the backflow zone, a swirler is generally arranged in the head area of the main combustion zone, the swirler has a complex structure and high processing precision requirement, and the swirler has high cost and can cause a large weight of the combustion chamber.
Disclosure of Invention
In order to solve the technical problems, the utility model provides a flame tube, an engine and a helicopter, which can simplify the structure of the flame tube.
In one aspect, the utility model provides a flame tube, which comprises a flame inner ring and a flame outer ring, wherein one ends of the flame inner ring and the flame outer ring are connected through a mounting plate to form an annular cavity, a plurality of mounting holes for mounting nozzles are uniformly arranged on the mounting plate around the axis of the flame tube, a plurality of jet pipes are uniformly arranged on the outer edge of each mounting hole around the axis of the flame tube, the plurality of jet pipes are spirally arranged around the axis of the mounting hole where the jet pipes are positioned, and the jet pipes are communicated with the annular cavity.
In one embodiment of the utility model, the other ends of the flame inner ring and the flame outer ring are provided with openings, one end of the flame outer ring provided with the openings is provided with a large bent pipe and a fixed ring, and one end of the flame inner ring connected with the mounting plate is provided with a fixed seat.
In one embodiment of the utility model, a jet orifice is formed within the jet tube, the jet orifice being in communication with the annular cavity.
In one embodiment of the utility model, the jet pipes at the outer edge of one mounting hole form one jet pipe group, and the spiral directions of the jet pipes of the jet pipe groups are kept consistent.
In one embodiment of the utility model, the jet pipe is angled from 15 ° to 60 ° to the mounting plate.
In one embodiment of the utility model, the jet aperture has a diameter of 2mm to 8mm.
In one embodiment of the utility model, a plurality of main combustion holes are arranged on one end of the inner flame ring and the outer flame ring, which are close to the mounting plate, and a plurality of mixing holes are arranged on one end of the inner flame ring and the outer flame ring, which are far away from the mounting plate.
In one embodiment of the utility model, the inner flame ring and the outer flame ring are provided with divergent holes, and the diameters of the divergent holes are 0.2 mm-1.0 mm.
In another aspect, an engine is provided with the flame tube.
In a further aspect, a helicopter is provided, fitted with an engine as described above.
Compared with the prior art, the flame tube technical scheme provided by the utility model has the following advantages:
(1) According to the utility model, the jet pipe is additionally arranged at the mounting plate of the head part of the flame tube, so that high-temperature fuel gas is guided by the jet pipe, a low-speed backflow area is generated in the nozzle hole area of the head part of each flame tube, the temperature uniformity in a combustion chamber is improved, the contact area of diffusion flame is increased, the combustion intensity is improved, and the influence of disturbance on flame caused by external factors is resisted, thereby playing a role in stabilizing flame, ensuring ignition, stable combustion and complete combustion, effectively replacing a swirler, reducing the weight of the flame tube and simplifying the engine structure.
(2) In the structure of the flame tube, the coaxiality of the flame tube and the turbine part can be effectively ensured by the fixing seat of the flame inner ring, the rear end positioning of the flame tube with thermal deformation can be effectively compensated by the multi-arch structure of the large bent tube on the flame tube, the vibration resistance of the flame tube can be effectively improved, and the service life of the flame tube is prolonged.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings required for the description of the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present utility model, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of the structure of a flame tube of the present utility model;
FIG. 2 is a front view of a flame tube of the present utility model;
FIG. 3 is a cross-sectional view at A-A in FIG. 2;
FIG. 4 is a schematic illustration of the recirculation zone at the jet tube of the flame tube of the present utility model.
Description of the specification reference numerals:
1. an inner flame ring; 2. a flame outer ring; 3. a mounting plate; 4. an annular cavity; 5. a mounting hole; 6. jet pipe; 7. an opening; 8. a large bent pipe; 9. a fixing ring; 10. a fixing seat; 11. jet holes; 12. a primary combustion hole; 13. and (3) blending holes.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present utility model more apparent, the technical solutions in the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model, and it is apparent that the described embodiments are only some embodiments of the present utility model, not all embodiments of the present utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Example 1
Referring to fig. 1 to 4, the flame tube of the utility model comprises a flame inner ring 1 and a flame outer ring 2, wherein one ends of the flame inner ring 1 and the flame outer ring 2 are connected through a mounting plate 3 to form an annular cavity 4, a plurality of mounting holes 5 for mounting nozzles are uniformly arranged on the mounting plate 3 around the axis of the flame tube, a plurality of jet pipes 6 are uniformly arranged on the outer edge of each mounting hole 5 around the axis of the flame tube, the plurality of jet pipes 6 are spirally arranged around the axis of the mounting hole 5 where the jet pipes 6 are positioned, and the jet pipes 6 are communicated with the annular cavity 4.
The flame tube comprises a flame inner ring 1 and a flame outer ring 2, wherein one ends of the flame inner ring 1 and the flame outer ring 2 are connected through a mounting plate 3 to form an annular cavity 4, and one end connected through the mounting plate 3 is called a flame tube head. The mounting plate 3 of the flame tube is provided with a plurality of mounting holes 5, the plurality of mounting holes 5 are arranged in a circular array around the axis of the flame tube, and are arranged at equal intervals, as shown in fig. 1 and 2, the mounting holes 5 are used for mounting a nozzle, the nozzle is used for realizing that fuel is atomized and sprayed in the annular cavity 4 of the flame tube, and the atomized and sprayed fuel is ignited in the annular cavity 4 for tissue combustion. The outer fringe of every mounting hole 5 is provided with a plurality of jet pipes 6, jet pipes 6 are linked together with annular chamber 4, as shown in fig. 1 and 2, a plurality of jet pipes 6 are arranged in circular array around the axis of mounting hole 5, the equidistance sets up, and the jet pipes 6 of every mounting hole 5 outer fringe are arranged in spiral (clockwise in fig. 1 and 2) around the axis of the mounting hole 5 that it is located, specifically, as shown in fig. 1 and 2, the jet pipes 6 of every mounting hole 5 outer fringe are arranged anticlockwise or clockwise along the mounting hole 5 axis that it belongs to, the spiral direction of jet pipes 6 is: the end of the jet pipe 6 connected with the mounting plate 3 points to the direction of the end of the jet pipe 6 far away from the mounting plate 3, and the air flow passing through the jet pipe 6 in spiral arrangement enters the annular cavity 4 to generate a backflow area so as to improve the temperature uniformity in the combustion chamber. In order to generate a backflow area, a swirler is required to be installed in the head area of a flame tube, the swirler has a complex structure and high processing precision requirement, the cost is high, and the weight of a combustion chamber is high. Further, the mounting hole 5 is communicated with the annular cavity 4, after the nozzle is mounted on the mounting hole 5, one end of the nozzle is directly positioned in the annular cavity 4, the other end of the nozzle is communicated with the oil inlet pipe, fuel is atomized and sprayed through the nozzle and then sprayed into the annular cavity 4 of the flame tube, and atomized fuel is ignited in the annular cavity 4 to be burnt. In addition, the nozzles are generally arranged in the same rotating direction in the flame tube (the nozzles are uniformly arranged in the annular cavity 4 in a clockwise or anticlockwise manner), so that the direction of the jet holes 11 at the head of the flame tube can be matched with the rotating direction of the nozzles, that is, the spiral direction of the jet tube 6 is consistent with the rotating direction of the nozzles, the fuel moves in the flame tube according to a spiral flow track (a rotational flow generated by the rotating direction of the nozzles), the fuel and the air are ensured to be mixed more uniformly, and the fuel is uniformly distributed in a combustion backflow area, so that the residence time of the fuel in the flame tube is long, the flame is stable, the combustion is complete, and the combustion efficiency is improved.
In one embodiment, the other ends of the flame inner ring 1 and the flame outer ring 2 are provided with openings 7, one end of the flame outer ring 2 provided with the opening 7 is provided with a large bent pipe 8 and a fixed ring 9, and one end of the flame inner ring 1 connected with the mounting plate 3 is provided with a fixing seat 10.
The other ends of the inner and outer flame rings 1, 2 are provided with openings 7, one end of the openings 7 being provided for connection of the cartridge to a turbine inlet guide (not shown in the figures) on the engine. The flame outer ring 2 is provided with a large bent pipe 8 and a fixed ring 9 at one end provided with an opening 7, the fixed ring 9 and the large bent pipe 8 are used for being connected with an engine casing (not shown in the figure) on an engine, the flame inner ring 1 is provided with a fixed seat 10 at one end connected with the mounting plate 3, and the fixed seat 10 is used for being connected with a combustion chamber casing (not shown in the figure) on the engine, so that the positioning connection of the flame tube and the engine is realized. The coaxiality of the flame tube and a turbine component (not shown in the figure) can be effectively ensured by the fixing seat 10 of the flame inner ring 1, the arch structure or the multi-arch structure of the flame tube large bent tube 8 is of an elastic structure, the arch part of the flame tube large bent tube can effectively counteract the thermal deformation, and the stress concentration can cause damage by adopting a rigid structure, so that the positioning of the rear end of the flame tube and the engine can be effectively realized, the vibration resistance of the flame tube can be effectively increased, and the service life of the flame tube can be prolonged.
In one embodiment, a jet hole 11 is formed in the jet pipe 6, and the jet hole 11 is communicated with the annular cavity 4.
The jet pipe 6 is tubular, so that a cylindrical jet hole 11 is formed inside the jet pipe 6, and the jet hole 11 is communicated with the annular cavity 4, so that the air flow passing through the jet hole 11 forms a backflow area in the annular cavity 4, and the temperature uniformity in the combustion chamber is improved.
In one embodiment, a plurality of jet pipes 6 at the outer edge of one mounting hole 5 form a jet pipe group, and the spiral directions of the jet pipes 6 of the plurality of jet pipe groups are kept consistent.
The outer fringe of a mounting hole 5 sets up a plurality of jet pipes 6, therefore a mounting hole 5 corresponds a plurality of jet pipes 6, the jet pipe 6 that a mounting hole 5 outer fringe corresponds forms a jet pipe group, the jet pipe 6 of every jet pipe group is the heliciform and arranges, on same flame tube, the heliciform orientation of the jet pipe 6 of a plurality of jet pipe groups keeps unanimous, i.e. the heliciform orientation of the jet pipe 6 of all jet pipe groups on same flame tube all is clockwise, or the heliciform orientation of the jet pipe 6 of all jet pipe groups on same flame tube all is anticlockwise, can improve the indoor temperature homogeneity of combustion effectively.
In one embodiment, the jet pipe 6 is at an angle of 15 ° to 60 ° to the mounting plate 3.
Specifically, the angle between the jet pipe 6 and the mounting plate 3 is 15-60 degrees; preferably 35 °; at this angle, the recirculation zone created by the air flow through jet pipe 6 is maximized and the temperature uniformity within the combustion chamber can be effectively improved.
In one embodiment, the diameter of the jet aperture 11 is 2mm to 8mm, preferably Φ4.5mm; the flow velocity of air passing through the jet hole 11 and the flow velocity of the backflow area can be considered, optimization of the confluence capability is achieved, and temperature uniformity in the combustion chamber can be effectively improved.
In one embodiment, a plurality of main combustion holes 12 are formed in the inner flame ring 1 and the outer flame ring 2 at one end near the mounting plate 3, and a plurality of mixing holes 13 are formed in the inner flame ring 1 and the outer flame ring 2 at one end far away from the mounting plate 3.
The flame inner ring 1 and the flame outer ring 2 are respectively provided with a main combustion hole 12 and a mixing hole 13, one ends of the flame inner ring 1 and the flame outer ring 2, which are close to the mounting plate 3, are provided with a plurality of main combustion holes 12, one ends of the flame inner ring 1 and the flame outer ring 2, which are far away from the mounting plate 3, are provided with a plurality of mixing holes 13, and the main combustion holes 12 and the mixing holes 13 play a role in air intake. The air inflow of the main combustion holes 12 on the flame inner ring 1 and the main combustion holes 12 on the flame outer ring 2 accounts for about 20% -40% of the total air amount of the air flow combustion chamber, and the air inflow of the mixing holes 13 on the flame inner ring 1 and the mixing holes 13 on the flame outer ring 2 accounts for about 20% -40% of the total air amount of the air flow combustion chamber. Air enters the flame tube through the main combustion hole 12 for combustion, the air passing through the blending hole 13 can be mixed with fuel gas in the flame tube, the temperature of the fuel gas is reduced, the temperature distribution at the outlet of the combustion chamber is controlled to meet the requirements of a turbine, and the flame tube can be cooled and protected.
In one embodiment, the inner flame ring 1 and the outer flame ring 2 are provided with divergent holes, and the diameters of the divergent holes are 0.2 mm-1.0 mm.
The whole flame tube is cooled by adopting a divergent hole (namely, the divergent holes are arranged on the wall surfaces of the flame inner ring 1 and the flame outer ring 2, not shown in the figure), the air inflow of the divergent holes accounts for about 10% -30% of the total air amount of the air flow combustion chamber, the aperture of the divergent hole is 0.2-1.0 mm, preferably 0.5mm, and the divergent holes are uniformly distributed on the cavity wall of the annular cavity 4 on the flame tube according to the air flow distribution design, and can play a role in cooling the cavity walls of the flame inner ring 1 and the flame outer ring 2 so as to prevent the temperature of the cavity walls of the flame outer ring 2 and the flame inner ring 1 from being too high under the combustion of fuel gas, thereby reducing the service life of the flame tube.
The working process of the fuel oil specifically comprises the following steps:
the fuel flows into a nozzle from an oil inlet pipe, and the nozzle atomizes and sprays the fuel into the annular cavity 4 of the flame tube; meanwhile, the air flow of the two channels formed by the inner casing of the casing and the flame tube casing (the flame outer ring 2) passes through the jet holes 11 on the jet tube 6, and as the jet tube 6 is in a spiral direction, the air flow passing through the jet holes 11 of each jet tube group generates a backflow area in the annular cavity 4, and the backflow area can drive the fuel sprayed by the nozzle to the annular cavity 4 to flow along with the backflow of the air, so that the fuel is distributed uniformly in the annular cavity 4, and the temperature uniformity in the combustion chamber is improved.
Example two
An engine is provided with the flame tube in the first embodiment, and the engine adopting the flame tube in the first embodiment can reduce the quality of the engine and improve the efficiency of the engine on the basis of reducing the structure of the flame tube.
Example III
A helicopter is provided with an engine in the second embodiment, and the helicopter adopting the engine in the second embodiment can reduce the quality of the engine, improve the efficiency of the engine and effectively reduce the efficiency of the helicopter on the basis of reducing the flame tube structure.
Note that the above is only a preferred embodiment of the present utility model and the technical principle applied. It will be understood by those skilled in the art that the present utility model is not limited to the particular embodiments described herein, but is capable of various obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the utility model. Therefore, while the utility model has been described in connection with the above embodiments, the utility model is not limited to the embodiments, but may be embodied in many other equivalent forms without departing from the spirit or scope of the utility model, which is set forth in the following claims.
Claims (10)
1. A flame tube, characterized in that: including flame inner ring (1) and flame outer loop (2), wherein one end of flame inner ring (1) and flame outer loop (2) is connected through mounting panel (3) and is formed annular chamber (4), on mounting panel (3) around the axis of flame tube evenly has been arranged a plurality of mounting holes (5) that are used for installing the nozzle, every the outer fringe of mounting hole (5) is around the axis of flame tube evenly has been arranged a plurality of jet pipes (6), and the axis of a plurality of jet pipes (6) around its place mounting hole (5) is the heliciform and arranges, jet pipe (6) with annular chamber (4) are linked together.
2. The flame tube of claim 1, wherein: the flame inner ring (1) and the other end of the flame outer ring (2) are provided with openings (7), one end of the flame outer ring (2) provided with the openings (7) is provided with a large bent pipe (8) and a fixed ring (9), and one end of the flame inner ring (1) connected with the mounting plate (3) is provided with a fixing seat (10).
3. The flame tube of claim 2, wherein: jet flow pipe (6) is formed with jet hole (11), jet hole (11) with annular chamber (4) are linked together.
4. A flame tube as claimed in claim 3, wherein: a plurality of jet pipes (6) at the outer edge of one mounting hole (5) form a jet pipe group, and the spiral directions of the jet pipes (6) of the jet pipe group are kept consistent.
5. The cartridge of any one of claims 1-4, wherein: the angle between the jet pipe (6) and the mounting plate (3) is 15-60 degrees.
6. A flame tube as claimed in claim 3, wherein: the diameter of the jet hole (11) is 2 mm-8 mm.
7. The flame tube of claim 1, wherein: a plurality of main combustion holes (12) are formed in one ends, close to the mounting plate (3), of the flame inner ring (1) and the flame outer ring (2), and a plurality of mixing holes (13) are formed in one ends, far away from the mounting plate (3), of the flame inner ring (1) and the flame outer ring (2).
8. The flame tube of claim 7, wherein: the flame inner ring (1) and the flame outer ring (2) are provided with divergent holes, and the diameters of the divergent holes are 0.2 mm-1.0 mm.
9. An engine comprising a flame tube as claimed in any one of claims 1 to 8.
10. A helicopter comprising the engine of claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320164164.2U CN219530928U (en) | 2023-01-28 | 2023-01-28 | Flame tube, engine and helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320164164.2U CN219530928U (en) | 2023-01-28 | 2023-01-28 | Flame tube, engine and helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219530928U true CN219530928U (en) | 2023-08-15 |
Family
ID=87628399
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320164164.2U Active CN219530928U (en) | 2023-01-28 | 2023-01-28 | Flame tube, engine and helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219530928U (en) |
-
2023
- 2023-01-28 CN CN202320164164.2U patent/CN219530928U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2405201B1 (en) | Injection nozzle for a turbomachine | |
| US7878000B2 (en) | Pilot fuel injector for mixer assembly of a high pressure gas turbine engine | |
| CN100483029C (en) | Combustion chamber of miniature gas turbine with double premixed channel using natural gas | |
| JP6196868B2 (en) | Fuel nozzle and its assembly method | |
| CN114294680B (en) | Micro-premixing combustion chamber of central grading gas turbine | |
| US20100180599A1 (en) | Insertable Pre-Drilled Swirl Vane for Premixing Fuel Nozzle | |
| JP2012017971A5 (en) | ||
| CN101769533A (en) | Method and apparatus to facilitate cooling of a diffusion tip within a gas turbine engine | |
| JP2019049253A (en) | Nozzle assembly for dual-fuel nozzle | |
| KR20180106945A (en) | Dual-fuel fuel nozzle with liquid fuel tip | |
| CN111306577B (en) | Direct-injection fan-shaped nozzle applied to afterburner concave cavity structure | |
| CN104807044A (en) | Liquefied gas combustion chamber with outlet equipped with swirling vanes | |
| JP2018536132A (en) | Fuel nozzle assembly having a premix flame stabilizer | |
| US9677766B2 (en) | Fuel nozzle for use in a turbine engine and method of assembly | |
| CN107975822B (en) | Combustion chamber of gas turbine and gas turbine using combustion chamber | |
| CN219530928U (en) | Flame tube, engine and helicopter | |
| JP7139162B2 (en) | Dual fuel fuel nozzle with gaseous and liquid fuel capabilities | |
| CN111780161B (en) | Turbine engine combustion chamber | |
| CA2597846A1 (en) | Pilot fuel injector for mixer assembly of a high pressure gas turbine engine | |
| CN109945233B (en) | Combustion chamber, atomization device thereof and aviation gas turbine engine | |
| RU89671U1 (en) | BURNER DEVICE FOR COMBUSTION CHAMBER OF A GAS-TURBINE INSTALLATION | |
| CN115264533B (en) | Natural gas coaxial staged combustion chamber adopting central ignition and combustion method | |
| RU2226652C2 (en) | Gas-turbine engine combustion chamber | |
| RU220624U1 (en) | Fuel-air burner of a gas turbine engine combustion chamber | |
| CN219510843U (en) | Combustion chamber, engine and helicopter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |