CN109184808A - Segmented turbine guider link construction, installation method and gas-turbine unit - Google Patents
Segmented turbine guider link construction, installation method and gas-turbine unit Download PDFInfo
- Publication number
- CN109184808A CN109184808A CN201811265997.8A CN201811265997A CN109184808A CN 109184808 A CN109184808 A CN 109184808A CN 201811265997 A CN201811265997 A CN 201811265997A CN 109184808 A CN109184808 A CN 109184808A
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- China
- Prior art keywords
- outer cover
- segmented
- ring
- casing
- link construction
- 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.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention provides a kind of segmented turbine guider link construction, installation method and gas-turbine units.Segmented turbine guider link construction includes segmented nozzle ring, segmented nozzle ring is divided into multiple fan-shaped sections along the circumferential direction of segmented nozzle ring, fan-shaped section includes inner ring, outer ring and at least one be set to the guide vane between inner ring and outer rings, segmented turbine guider link construction further includes the inner cavity in inner ring and the interior casing for carrying out axial limiting to inner ring and radially limiting, periphery in outer ring and the outer cover for carrying out axial limiting to outer ring and radially limiting and the periphery in outer cover and the outer casing for carrying out axial limiting to outer cover and radially limiting, multiple fan-shaped sections are combined into one by interior casing and outer cover, to improve the assembling of segmented nozzle ring.Multiple fan-shaped sections can be combined into one by interior casing and outer cover, so that segmented nozzle ring has the assembling of integral turbine guider.
Description
Technical field
The present invention relates to gas-turbine unit fields, particularly, be related to a kind of segmented turbine guider link construction,
Installation method and gas-turbine unit.
Background technique
In existing gas-turbine unit, because turbine inlet temperature level is higher and higher, to improve efficiency, reduces heat and answer
Power, improves qualification rate, and nozzle ring generallys use the design method of segmentation to reduce thermal stress.By integral turbine guider edge
Circumferentially being divided into multiple fan-shaped sections can be obtained segmented nozzle ring.
Segmented nozzle ring installs positioning usually in the following way in gas-turbine unit: each fan-shaped section
It is connect by hook or bolt with interior casing and outer casing.Regardless of segmented nozzle ring is using hook connection or spiral shell
It tethers and connects, assembling is all bad.
Summary of the invention
The present invention provides a kind of segmented turbine guider link construction, installation method and gas-turbine unit, with
Solve the problems, such as that segmented nozzle ring assembling is bad.
The technical solution adopted by the invention is as follows:
One aspect of the present invention provides a kind of segmented turbine guider link construction, including segmented nozzle ring,
Segmented nozzle ring is divided into multiple fan-shaped sections along the circumferential direction of segmented nozzle ring, fan-shaped section include inner ring, outer ring with
And at least one is set to the guide vane between inner ring and outer rings, segmented turbine guider link construction further includes in interior
The inner cavity of ring and for inner ring carry out axial limiting and radially limit interior casing, the periphery in outer ring and be used for outer ring
Carry out axial limiting and the outer cover that radially limits and periphery in outer cover and for outer cover progress axial limiting and radial direction
The outer casing of limit, multiple fan-shaped sections are combined into one by interior casing and outer cover, to improve the assembly of segmented nozzle ring
Property.
Further, outer cover uses thin walled elastic structure.
Further, multiple rigidity for reducing outer cover are offered on outer cover to ensure segmented nozzle ring in work
Make that there is radial thermal compensation ability under state and reduces the opening for the stress that outer cover generates segmented nozzle ring.
Further, the middle part of outer cover is equipped with for being contacted with outer casing so that outer casing radially limited outer cover
Positioning surface.
Further, there are be radially expanded gap between the both ends of outer cover and outer casing.
Further, outer casing is equipped with the retaining ring for carrying out axial limiting to outer cover.
Further, first for carrying out axial limiting to outer ring and radially limiting is equipped between outer cover and outer ring to stop
Mouthful；The second seam allowance for carrying out axial limiting to inner ring and radially limiting is equipped between interior casing and inner ring.
Further, interior casing includes interior casing leading portion and interior casing back segment, interior casing leading portion and interior casing back segment it
Between using being detachably connected.
Another aspect of the present invention provides a kind of segmented nozzle ring installation method, using above-mentioned segmented turbine
Guider link construction, comprising the following steps: the outer ring of each fan-shaped section is separately mounted on outer cover；Interior casing is mounted on
In the inner ring of fan-shaped section, multiple fan-shaped sections are combined into one；Outer cover is mounted on outer casing, installation is completed.
Another aspect of the present invention provides a kind of gas-turbine unit, connects including above-mentioned segmented nozzle ring
Structure.
The invention has the following advantages:
Segmented turbine guider link construction of the invention, including segmented nozzle ring, segmented turbine guiding
Device is divided into multiple fan-shaped sections, and each fan-shaped section includes inner ring, outer ring and guide vane.When segmented nozzle ring is in
When working condition, form airflow channel between inner ring and outer ring, guide vane can to the high-temperature fuel gas by airflow channel into
Row guiding.High-temperature fuel gas is in fan-shaped section in hot environment, and there are gaps between adjacent fan-shaped section, so that fan-shaped section can
The thermal stress of fan-shaped section is reduced to expand.When some fan-shaped section is damaged, it is only necessary to replace the fan of damage
Shape section improves the service life of segmented nozzle ring, reduces without replacing entire segmented nozzle ring
Cost.It is supported limit by inner ring of the interior casing to fan-shaped section, and is constrained by outer ring of the outer cover to fan-shaped section, it can
To be combined into one multiple fan-shaped sections, so that segmented nozzle ring has the assembling of integral turbine guider.It is firing
Outer cover can be installed to outer casing when gas eddy turbine general assembly, outer casing can carry out axial limiting and radial direction to outer cover
Limit, so that segmented nozzle ring firmly installs.
Other than objects, features and advantages described above, there are also other objects, features and advantages by the present invention.
Below with reference to accompanying drawings, the present invention is described in further detail.
Detailed description of the invention
The attached drawing constituted part of this application is used to provide further understanding of the present invention, schematic reality of the invention
It applies example and its explanation is used to explain the present invention, do not constitute improper limitations of the present invention.In the accompanying drawings:
Fig. 1 is the schematic diagram of the segmented turbine guider link construction of the preferred embodiment of the present invention；
Fig. 2 is the schematic diagram of the outer cover of the preferred embodiment of the present invention.
Description of symbols:
1, segmented nozzle ring；11, inner ring；12, outer ring；13, guide vane；2, interior casing；21, before interior casing
Section；22, interior casing back segment；3, outer cover；31, it is open；32, positioning surface；4, outer casing；41, retaining ring；5, it is radially expanded gap；6,
First seam allowance；7, the second seam allowance.
Specific embodiment
It should be noted that in the absence of conflict, the features in the embodiments and the embodiments of the present application can phase
Mutually combination.The present invention will be described in detail below with reference to the accompanying drawings and embodiments.
Fig. 1 is the schematic diagram of the segmented turbine guider link construction of the preferred embodiment of the present invention；Fig. 2 is that the present invention is excellent
Select the schematic diagram of the outer cover of embodiment.
As shown in Figure 1, the segmented turbine guider link construction of the present embodiment, including segmented nozzle ring 1, point
Segmentation nozzle ring 1 is divided into multiple fan-shaped sections along the circumferential direction of segmented nozzle ring 1, and fan-shaped section includes inner ring 11, outer ring
12 and at least one be set to the guide vane 13 between inner ring 11 and outer ring 12, segmented turbine guider link construction is also
Including in inner ring 11 inner cavity and for inner ring 11 carry out axial limiting and radially limit interior casing 2, be in outer ring 12
Periphery and for carrying out axial limiting and the radially outer cover 3 that limits and periphery in outer cover 3 to outer ring 12 and being used for pair
Multiple fan-shaped sections are combined into one by the outer casing 4 that outer cover 3 carries out axial limiting and radially limits, interior casing 2 and outer cover 3, with
Improve the assembling of segmented nozzle ring.Segmented turbine guider link construction of the invention, including segmented turbine
Guider 1, segmented nozzle ring 1 divide for multiple fan-shaped sections, and each fan-shaped section includes inner ring 11, outer ring 12 and guiding
Blade 13.When segmented nozzle ring 1 is in running order, airflow channel is formed between inner ring 11 and outer ring 12, is oriented to
Blade 13 can be oriented to by the high-temperature fuel gas of airflow channel.High-temperature fuel gas is in fan-shaped section in hot environment, and
There are gap between adjacent fan-shaped section, fan-shaped section is expanded to reduce the thermal stress of fan-shaped section.When a certain
When a fan-shaped section is damaged, it is only necessary to the fan-shaped section for replacing damage, without replacing entire segmented nozzle ring 1,
The service life for improving segmented nozzle ring 1, reduces costs.It is carried out by inner ring 11 of the interior casing 2 to fan-shaped section
Support limit, and the outer ring 12 of fan-shaped section is constrained by outer cover 3, multiple fan-shaped sections can be combined into one, so that
Segmented nozzle ring 1 has the assembling of integral turbine guider.It can be by outer cover 3 in gas-turbine unit general assembly
On installation to outer casing 4, outer casing 4 can carry out axial limiting and radial limit to outer cover 3, so that segmented nozzle ring
1 firmly installs.
As shown in Fig. 2, outer cover 3 uses thin walled elastic structure in the present embodiment.Thin walled elastic structure makes outer cover 3 in height
Be easier to expand to reduce the thermal stress of outer cover 3 in warm environment, and can restore after the cooling period to as former state, and will not to point
Segmentation nozzle ring 1 generates big stress.
As shown in Fig. 2, offering multiple rigidity for reducing outer cover 3 on outer cover 3 in the present embodiment to ensure segmented
Nozzle ring 1 has radial thermal compensation ability in the operating condition and reduces what outer cover 3 generated segmented nozzle ring 1
The opening 31 of stress.Opening 31 can reduce the rigidity of outer cover 3, so that outer cover 3 is easier to expand in the high temperature environment, and
Big stress will not be generated to segmented nozzle ring 1.When segmented nozzle ring 1 is radially expanded, outer cover 3 is right
The radial limit of segmented nozzle ring 1 also changes therewith, it is ensured that segmented nozzle ring 1 has in the operating condition
There is radial thermal compensation ability.Optionally, opening 31 is opened in the middle part of 32 two sides of positioning surface of outer cover 3.Optionally, be open 31 edges
The circumferential and axial uniform intervals of outer cover 3 are laid.
As depicted in figs. 1 and 2, in the present embodiment, the middle part of outer cover 3 is equipped with for contacting with outer casing 4 so that outer casing 4
The positioning surface 32 that outer cover 3 is radially limited.Positioning surface 32 is contacted with outer casing 4, so that outer casing 4 can be with contact outer cover 3
It is moved radially to limit outer cover 3.Optionally, the middle part protrusion of outer cover 3 is to form positioning surface 32.
As shown in Figure 1, there are be radially expanded gap 5 between the both ends of outer cover 3 and outer casing 4 in the present embodiment.Outer casing
4 carry out radial limit by middle part of the positioning surface 32 to outer cover 3, and are radially expanded gap 5 and make the both ends of outer cover 3 in high temperature ring
There is the space being radially expanded in border, allow outer cover 3 to bend to curved surface, to reduce thermal stress.
As shown in Figure 1, outer casing 4 is equipped with the retaining ring 41 for carrying out axial limiting to outer cover 3 in the present embodiment.It will
Outer cover 3 is mounted on outer casing 4, so that the positioning surface 32 of outer cover 3 is contacted positioning with outer casing 4, then fix by 41 block of retaining ring.
Retaining ring 41 can carry out axial limiting, 41 accurate positioning of retaining ring and convenient for disassembly and assembly to outer cover 3.
Be equipped with as shown in Figure 1, in the present embodiment, between outer cover 3 and outer ring 12 for outer ring 12 carry out axial limiting and
The first seam allowance 6 radially limited.First seam allowance 6 cooperates, accurate positioning, so that segmented nozzle ring 1 is not easy to loosen.
Outer casing 4 carries out radial limit by middle part of the positioning surface 32 to outer cover 3, and the first seam allowance 6 carries out radial limit to the both ends of outer cover 3
Position, when segmented nozzle ring 1 is radially expanded, the both ends stress of outer cover 3 is bent, and can make full use of outer cover 3
Elasticity, to reduce thermal stress.Optionally, it is equipped between interior casing 2 and inner ring 11 for carrying out axial limiting and diameter to inner ring 11
To the second seam allowance 7 of limit.Second seam allowance 7 cooperates, accurate positioning, so that segmented nozzle ring 1 is not easy to loosen.
As shown in Figure 1, in the present embodiment, interior casing 2 includes interior casing leading portion 21 and interior casing back segment 22, before interior casing
It uses and is detachably connected between section 21 and interior casing back segment 22.Interior casing 2 is designed as two sections of front and back and used to be detachably connected,
It is easily installed and dismantles segmented nozzle ring 1.Optionally, it is detachably connected be connected by screw bolts, be clamped, in grafting one
Kind.
The preferred embodiment of the present invention additionally provides a kind of segmented nozzle ring installation method, using above-mentioned segmentation
Formula turbine guider link construction, comprising the following steps: the outer ring 12 of each fan-shaped section is separately mounted on outer cover 3；It will be interior
Casing 2 is mounted in the inner ring 11 of fan-shaped section, and multiple fan-shaped sections are combined into one；Outer cover 3 is mounted on outer casing 4,
Complete installation.
The preferred embodiment of the present invention additionally provides a kind of gas-turbine unit, is oriented to including above-mentioned segmented turbine
Device connection structure.
When it is implemented, providing a kind of segmented turbine guider link construction.Segmented nozzle ring 1 and interior casing
2 and outer cover 3 be combined into " cartridge " component, including segmented nozzle ring 1, interior casing leading portion 21, interior casing back segment 22
And outer cover 3.Segmented nozzle ring 1 is first mounted in the box that interior casing 2 and outer cover 3 form, and when assembly first will segmentation
Formula nozzle ring 1 is packed on outer cover 3, then loads onto interior 2 two sections of front and back of casing to form " cartridge " component.Segmented turbine
Guider 1 and interior casing leading portion 21, interior casing back segment 22 and outer cover 3 are cooperated by Precise Flangers to be positioned.Make to be segmented in this way
Formula nozzle ring 1 has the assembling of integral turbine guider.Entirely pass through retaining ring between " cartridge " component and outer casing 4
Felt relieved between 41 axial limitings, with outer casing 4 by the positioning surface 32 at the middle part of outer cover 3,3 rear and front end of outer cover and outer casing 4 it
Between be reserved with and enough be radially expanded gap 5.Outer cover 3 is designed to thin walled elastic structure, the positioning surface contacted with outer casing 4 32
In the medium position of outer cover 3, opening 31 is circumferentially opened up in 32 two sides of positioning surface, reduces the rigidity of outer cover 3, it is ensured that segmented turbine
The radial thermal compensation ability of guider 1 in the operating condition, and outer cover 3 will not generate big answer to segmented nozzle ring 1
Power.
The segmented turbine guider link construction has the advantage that
(1) compared with linking up with connection method, segmented nozzle ring 1 is positioned using Precise Flangers, and positioning accuracy is higher；
(2) compared with bolted-on connection, the number of parts needed is few；
(3) segmented nozzle ring 1 and other parts form " cartridge " component, in gas-turbine unit general assembly
Entirely " cartridge " component assembles together, and assembling is good.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of segmented turbine guider link construction,
Including segmented nozzle ring (1), the segmented nozzle ring (1) is along the segmented nozzle ring (1)
Circumferential direction be divided into multiple fan-shaped sections, the fan-shaped section include inner ring (11), outer ring (12) and at least one be set in described
Guide vane (13) between ring (11) and the outer ring (12),
It is characterized in that,
The segmented turbine guider link construction further includes the inner cavity in the inner ring (11) and is used for the inner ring
(11) axial limiting and the interior casing (2) radially limited are carried out, is in the periphery of the outer ring (12) and for the outer ring
(12) axial limiting and the outer cover (3) radially limited are carried out and is in the periphery of the outer cover (3) and is used for the outer cover
(3) the outer casing (4) for carrying out axial limiting and radially limiting,
Multiple fan-shaped sections are combined into one by the interior casing (2) and the outer cover (3), to improve segmented turbine guiding
The assembling of device.
2. segmented turbine guider link construction according to claim 1, which is characterized in that
The outer cover (3) uses thin walled elastic structure.
3. segmented turbine guider link construction according to claim 1, which is characterized in that
Multiple rigidity for reducing the outer cover (3) are offered on the outer cover (3) to ensure the segmented turbine guiding
Device (1) has radial thermal compensation ability in the operating condition and reduces the outer cover (3) to the segmented nozzle ring (1)
The opening (31) of the stress of generation.
4. segmented turbine guider link construction according to claim 1, which is characterized in that
The middle part of the outer cover (3) is equipped with for contacting with the outer casing (4) so that the outer casing (4) is to the outer cover
(3) positioning surface (32) radially limited.
5. segmented turbine guider link construction according to claim 4, which is characterized in that
There are be radially expanded gap (5) between the both ends and the outer casing (4) of the outer cover (3).
6. segmented turbine guider link construction according to claim 1, which is characterized in that
The outer casing (4) is equipped with the retaining ring (41) for the outer cover (3) to be carried out with axial limiting.
7. segmented turbine guider link construction according to claim 1, which is characterized in that
It is equipped between the outer cover (3) and the outer ring (12) for carrying out axial limiting and radial limit to the outer ring (12)
The first seam allowance (6)；
It is equipped between the interior casing (2) and the inner ring (11) for carrying out axial limiting and radial limit to the inner ring (11)
The second seam allowance (7) of position.
8. segmented turbine guider link construction according to claim 1, which is characterized in that
The interior casing (2) includes interior casing leading portion (21) and interior casing back segment (22), the interior casing leading portion (21) and institute
It states to use between interior casing back segment (22) and be detachably connected.
9. a kind of segmented nozzle ring installation method, which is characterized in that
Using segmented turbine guider link construction according to any one of claims 1 to 8,
The following steps are included:
The outer ring (12) of each fan-shaped section is separately mounted on outer cover (3)；
Interior casing (2) is mounted in the inner ring (11) of fan-shaped section, multiple fan-shaped sections are combined into one；
The outer cover (3) is mounted on outer casing (4), installation is completed.
10. a kind of gas-turbine unit, which is characterized in that
Including segmented turbine guider link construction according to any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811265997.8A CN109184808B (en) | 2018-10-29 | 2018-10-29 | Segmented turbine nozzle connection structure, mounting method and gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811265997.8A CN109184808B (en) | 2018-10-29 | 2018-10-29 | Segmented turbine nozzle connection structure, mounting method and gas turbine engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109184808A true CN109184808A (en) | 2019-01-11 |
| CN109184808B CN109184808B (en) | 2021-08-06 |
Family
ID=64944043
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811265997.8A Active CN109184808B (en) | 2018-10-29 | 2018-10-29 | Segmented turbine nozzle connection structure, mounting method and gas turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109184808B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110219702A (en) * | 2019-04-30 | 2019-09-10 | 中国航发南方工业有限公司 | Stator blade limiting device and limit method |
| CN110617115A (en) * | 2019-10-29 | 2019-12-27 | 北京动力机械研究所 | Turbine engine guide ring assembly produced by additive manufacturing mode |
| CN111794808A (en) * | 2020-06-24 | 2020-10-20 | 中船重工龙江广瀚燃气轮机有限公司 | First-stage large meridian expansion guider casing of power turbine for fuel-drive compressor unit |
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| US20020197153A1 (en) * | 2001-06-25 | 2002-12-26 | Rogers Mark John | Segmented turbine vane support structure |
| CN101338688A (en) * | 2008-08-15 | 2009-01-07 | 中国航空动力机械研究所 | Gas-turbine unit turbine guider link construction |
| JP2009013837A (en) * | 2007-07-03 | 2009-01-22 | Hitachi Ltd | Gas turbine facility |
| CN104011333A (en) * | 2011-12-19 | 2014-08-27 | 斯奈克玛 | Turbomachine compressor guide vanes assembly |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4304522A (en) * | 1980-01-15 | 1981-12-08 | Pratt & Whitney Aircraft Of Canada Limited | Turbine bearing support |
| US20020197153A1 (en) * | 2001-06-25 | 2002-12-26 | Rogers Mark John | Segmented turbine vane support structure |
| JP2009013837A (en) * | 2007-07-03 | 2009-01-22 | Hitachi Ltd | Gas turbine facility |
| CN101338688A (en) * | 2008-08-15 | 2009-01-07 | 中国航空动力机械研究所 | Gas-turbine unit turbine guider link construction |
| CN104011333A (en) * | 2011-12-19 | 2014-08-27 | 斯奈克玛 | Turbomachine compressor guide vanes assembly |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110219702A (en) * | 2019-04-30 | 2019-09-10 | 中国航发南方工业有限公司 | Stator blade limiting device and limit method |
| CN110617115A (en) * | 2019-10-29 | 2019-12-27 | 北京动力机械研究所 | Turbine engine guide ring assembly produced by additive manufacturing mode |
| CN110617115B (en) * | 2019-10-29 | 2021-11-02 | 北京动力机械研究所 | Turbine engine guide ring assembly produced by additive manufacturing mode |
| CN111794808A (en) * | 2020-06-24 | 2020-10-20 | 中船重工龙江广瀚燃气轮机有限公司 | First-stage large meridian expansion guider casing of power turbine for fuel-drive compressor unit |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109184808B (en) | 2021-08-06 |
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