CN114563166A - Aero-engine nacelle ventilation cooling opening grille angle test device - Google Patents
Aero-engine nacelle ventilation cooling opening grille angle test device Download PDFInfo
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- CN114563166A CN114563166A CN202011356609.4A CN202011356609A CN114563166A CN 114563166 A CN114563166 A CN 114563166A CN 202011356609 A CN202011356609 A CN 202011356609A CN 114563166 A CN114563166 A CN 114563166A
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- 238000009423 ventilation Methods 0.000 title claims abstract description 53
- 238000012360 testing method Methods 0.000 title claims abstract description 39
- 238000001816 cooling Methods 0.000 title claims abstract description 36
- 238000000034 method Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- 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
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Testing Of Engines (AREA)
Abstract
The invention relates to an angle test device for a grille of a ventilation cooling port of a nacelle of an aero-engine, which comprises: a vent base (1) having a vent; and the grating plate (3) is arranged in the vent of the vent base (1) in an angle-adjustable manner. The grating plate (3) is arranged in the vent hole of the vent hole base (1) in an angle-adjustable manner, and the air volume of the vent cooling hole of the nacelle in the process of arranging grating plates with different angles can be measured by changing the angle of the grating plate (3), so that the problem that the cost for preparing independent grating vent port test pieces with different angles in the related technology is high is solved.
Description
Technical Field
The invention relates to the field of aircraft engines, in particular to an angle test device for a grille of a ventilation cooling opening of a nacelle of an aircraft engine.
Background
The engine nacelle comprises an air inlet, a fan housing and a thrust reverser, wherein the fan housing and the engine form the fan nacelle. Various accessories and combustible liquid pipelines are arranged in the fan cabin. When the engine works, the accessories can transfer a large amount of heat into the fan cabin. If the heat cannot be dissipated in time, the temperature in the cabin can be rapidly increased, so that the accessories cannot work normally; meanwhile, when a liquid pipeline in the nacelle leaks, the liquid forms combustible steam under the action of high temperature, and if the combustible steam is not evacuated in time, a fire disaster can be caused. It is desirable to develop a ventilation cooling design for the fan compartment of the power plant. The nacelle ventilation and cooling system can cool various accessories in the fan cabin, and can provide ventilation and air exchange for the fan cabin, prevent combustible gas from gathering in the cabin and eliminate fire hazard.
The air outlet of the nacelle ventilation cooling system is generally arranged on the fan cover, and the structure form can be that the air outlet is directly opened on the skin, or the air outlet is connected to the skin of the fan cover by adopting a separate grille type air outlet. The flow coefficient of the grid type exhaust port is insensitive to the flow state of an external flow field, and the grid type exhaust port has the advantage of ensuring that the flow coefficient of the outlet of the airplane is relatively stable during the operation period, so that the grid type exhaust port is more widely applied.
The different angles of the exhaust grill have a large effect on the flow coefficient of the exhaust port. The influence trend of different grid angles on the flow coefficient of the exhaust port needs to be researched through analysis and combination tests, so that the most appropriate grid angle is designed and optimized, and the ventilation and cooling air efficiency in the fan cabin is ensured. On the other hand, the cost is higher when independent grid exhaust port test pieces with different angles are prepared.
Disclosure of Invention
The invention aims to provide an angle test device for a grille of a ventilation cooling opening of a nacelle of an aircraft engine, so as to solve the problem that the cost for preparing independent grille exhaust opening test pieces with different angles is high in the related technology.
According to one aspect of the embodiment of the invention, the angle test device for the grille of the ventilation and cooling opening of the nacelle of the aircraft engine comprises:
a vent base having a vent;
and the grating plate is arranged in the vent of the vent base in an angle-adjustable manner.
Optionally, the aircraft engine nacelle ventilation cooling opening grille angle testing device further comprises a connecting shaft, a through hole allowing the connecting shaft to pass through is formed in the ventilation opening base, and the connecting shaft passes through the through hole and is connected with the first end of the grille plate.
Optionally, the device for testing the angle of the grille of the ventilation cooling opening of the nacelle of the aircraft engine further comprises:
a plurality of first positioning portions arranged along a circumferential direction of the connecting shaft;
the second positioning part can be positioned and matched with any one of the first positioning parts to limit the grating plate at a mounting angle,
one of the first positioning part and the second positioning part is arranged on the ventilation opening base, and the other one is arranged on the connecting shaft.
Optionally, the second positioning portion is multiple.
Or,
the first positioning part comprises a first clamping groove arranged on the ventilation opening base;
the second positioning part comprises a second clamping groove arranged on the connecting shaft;
the testing device further comprises a stop block arranged in the first clamping groove and the second clamping groove.
Optionally, the vent base comprises:
the frame is enclosed to form a ventilation opening; and
the annular component is arranged on the outer side of the frame and sleeved on the connecting shaft, and the first clamping groove is formed in the annular component.
Optionally, the first locking groove penetrates through the annular component in a radial direction of the connecting shaft.
Alternatively,
the first clamping groove is arranged on the inner circumferential surface of the through hole;
the second clamping groove extends towards the ventilation opening base from the end face, located on the outer side of the ventilation opening base, of the connecting shaft along the axial direction of the connecting shaft.
Optionally, one end of the connecting shaft, which is connected with the grid plate, is provided with an external thread, and the first end of the grid plate is provided with a threaded hole matched with the external thread.
Optionally, the second end of the grid plate is connected to the vent base by a screw.
By applying the technical scheme of the invention, the grating plates are arranged in the vent of the vent base in an angle-adjustable manner, and the air volume of the nacelle can be measured by changing the angle of the grating plates when the grating plates with different angles are arranged in the ventilation cooling port, so that the problem of higher cost of preparing independent grating exhaust port test pieces with different angles in the related technology is solved.
Other features of the present invention and advantages thereof will become apparent from the following detailed description of exemplary embodiments thereof, which proceeds with reference to the accompanying drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the related art, the drawings needed to be used in the description of the embodiments or the related art will be briefly introduced below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 shows a schematic structural diagram of an aircraft engine nacelle ventilation cooling opening grille angle test device according to an embodiment of the invention;
FIG. 2 shows an enlarged view at A in FIG. 1;
FIG. 3 shows a schematic structural view of a vent base of an aircraft engine nacelle vent cooling grill angle testing apparatus according to an embodiment of the invention;
FIG. 4 shows a schematic structural view of a grid plate of an aircraft engine nacelle ventilation cooling opening grid angle test device according to an embodiment of the invention;
FIG. 5 shows a schematic structural diagram of a connecting shaft of the aircraft engine nacelle ventilation cooling opening grille angle test device of the embodiment of the invention;
FIG. 6 shows a schematic structural diagram of a stop block of an aircraft engine nacelle ventilation cooling opening grille angle test device according to an embodiment of the invention;
FIG. 7 is a schematic perspective view of another angle of an aircraft engine nacelle air cooling vent grille angle test apparatus according to an embodiment of the invention;
FIG. 8 is a schematic perspective view of an aircraft engine nacelle ventilation cooling opening grill angle testing apparatus (with the grill plates not in place) according to an embodiment of the invention; and
fig. 9 shows an enlarged view at B in fig. 8.
In the figure:
1. a vent base; 2. an annular member; 3. a grid plate; 4. a threaded hole; 5. an external thread; 6. a second positioning portion; 7. a connecting shaft; 8. a stopper; 9. a screw; 10. a first positioning portion; 11. and a through hole.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
With reference to fig. 1-2 and 7-9, the angle testing device for the grille of the air-cooling vent of the nacelle of the aircraft engine of the present embodiment includes a vent base 1 and a grille plate 3, wherein the vent base 1 is provided with a vent; the grating plate 3 is installed in the ventilation opening of the ventilation opening base 1 in an angle adjustable manner.
In this embodiment, the grating plate 3 is installed in the vent of the vent base 1 in an angle-adjustable manner, and the air volume when the grating plates with different angles are installed in the ventilation cooling port of the nacelle can be measured by changing the angle of the grating plate 3, so that the problem that the cost for preparing the independent grating vent test pieces with different angles in the related art is high is solved.
The device for testing the angle of the grille of the ventilation cooling opening of the nacelle of the aircraft engine further comprises a connecting shaft 7. As shown in fig. 3, the vent base 1 is provided with a through hole 11 for allowing the connection shaft 7 to pass therethrough, and the connection shaft 7 passes through the through hole 11 to be connected to the first end of the grill plate 3.
As shown in fig. 4, the end of the grating plate 3 is provided with a threaded hole 4. As shown in fig. 5, the first end of the connecting shaft 7 is provided with an external thread 5, and the external thread 5 is matched with the threaded hole 4 of the grid plate 3.
In some embodiments, the through hole 11 is a threaded hole, and the external thread 5 of the connecting shaft 7 is matched with the through hole 11. The parameters of the internal thread of the through hole 11 are identical to those of the threaded hole 4.
The first end of the connecting shaft 7 passes through the through hole 11 to be connected with the threaded hole 4 of the first end of the grid plate 3. The first end of the connecting shaft 7 is connected with the grating plate 3 so that the grating plate 3 can rotate along with the connecting shaft 7.
In some embodiments, the vent base 1 is provided with through holes 11 on both of opposite sides. Both ends of the grating plate 3 are provided with threaded holes 4. The threaded holes 4 at the two ends of the grating plate 3 are respectively opposite to the through holes 11 on the two sides of the ventilation opening base 1. As shown in fig. 7, the second end of the grating plate 3 is connected to the vent base 1 by a screw 9 passing through the through hole 11.
The device for testing the angle of the grille of the ventilation cooling opening of the nacelle of the aircraft engine further comprises a plurality of first positioning parts 10 and second positioning parts 6. The plurality of first positioning portions 10 are arranged side by side in the circumferential direction of the connecting shaft 7; the second positioning portion 6 can be positioned and matched with any one of the first positioning portions 10 to limit the grating plate 3 at a mounting angle.
One of the first positioning portion 10 and the second positioning portion 6 is provided on the vent base 1, and the other is provided on the connecting shaft 7. In the present embodiment, the first positioning portion 10 is provided on the vent base 1, and the second positioning portion 6 is provided on the connecting shaft 7.
In some embodiments, the second positioning portion 6 and the first positioning portion 10 are arranged in plurality along the axial direction of the connecting shaft 7, so as to position the grid plate 3 at more angles, which is beneficial to make the data of the test trials more and denser.
The first positioning portion 10 includes a first engaging groove provided in the vent base 1; the second positioning part 6 comprises a second clamping groove arranged on the connecting shaft 7; the testing device further comprises a stop block 8 arranged in the first clamping groove and the second clamping groove, and the stop block is inserted into the first clamping groove and the second clamping groove to prevent the connecting shaft 7 from rotating relative to the ventilation opening base 1, so that the grid plate 3 is limited at a specific installation angle. Fig. 6 shows a schematic structural view of the stopper 8 of the present embodiment.
The air vent base 1 comprises a frame and an annular part 2, and the frame surrounds an air vent; the annular component 2 is arranged on the outer side of the frame and sleeved on the connecting shaft 7, and the first clamping groove is formed in the annular component 2.
In the present embodiment, the through holes 11 are formed in the opposite side frames of the frame, the ring member 2 is mounted on one of the two side frames where the through holes 11 are provided, and the portion of the connecting shaft 7 extending outside the frame is fitted in the ring member 2.
The first clamping groove penetrates through the annular component 2 along the radial direction of the connecting shaft 7, the second clamping groove is formed in the circumferential surface of the connecting shaft 7, and the stop block 8 can be sequentially inserted into the first clamping groove and the second clamping groove along the radial direction of the connecting shaft 7.
In other embodiments, the first locking groove is disposed on the inner circumferential surface of the through hole 11 and extends from the outer surface of the vent base 1 toward the inside of the vent base 1; the second locking groove extends from the end surface of the connecting shaft 7, which is located on the outer side of the ventilation opening base 1, to the ventilation opening base 1 along the axial direction of the connecting shaft 7. The stopper 8 is insertable into the first and second locking grooves in the axial direction of the connecting shaft 7.
The assembly steps of the test device for the angle of the grille of the ventilating and cooling opening of the nacelle of the aircraft engine of the embodiment comprise:
the first step is as follows: the annular component 2 can be connected to any side surface of the frame of the ventilation opening base 1 in a welding mode, the annular component 2 is ensured to be aligned with the through hole 11 on the side surface of the frame, and the inner diameter of the annular component 2 is slightly larger than that of the through hole 11.
The second step is that: the grid plate 3 is placed in the middle of the ventilation opening base 1 so that the holes at the two end faces of the threaded hole 4 are aligned with the through holes 11 on the two side faces of the ventilation opening base 1. The diameter of the threaded hole 4 is consistent with that of the through hole 11. The connecting shaft 7 is then screwed into the threaded hole 4 through the through hole 11. As shown in fig. 8 and 9.
The third step: after the angle of each grid plate is adjusted to reach the target value, the stopper 8 is used for separating the first clamping groove of the annular component 2 and the second clamping groove of the connecting shaft, as shown in fig. 1 and 2.
The fourth step: a corresponding number of screws 9 are screwed into threaded holes on the other side of the vent base 1, so that the grid plate 3 and the vent base 1 are fixed relative to each other.
Finally, the gap between the grid plate 3 and the vent base 1 can be filled with putty or other materials.
The present invention is not limited to the above exemplary embodiments, and any modifications, equivalent replacements, improvements, etc. within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The utility model provides an aeroengine nacelle ventilation cooling mouth grid angle test device which characterized in that includes:
a vent base (1) having a vent;
and the grating plate (3) is arranged in the ventilation opening of the ventilation opening base (1) in an angle-adjustable manner.
2. The aircraft engine nacelle ventilation cooling opening grid angle test device according to claim 1, further comprising a connecting shaft (7), wherein a through hole (11) allowing the connecting shaft (7) to pass through is formed in the ventilation opening base (1), and the connecting shaft (7) passes through the through hole (11) and is connected with the first end of the grid plate (3).
3. The aircraft engine nacelle ventilation cooling opening grill angle testing apparatus of claim 2, further comprising:
a plurality of first positioning portions (10) arranged in a circumferential direction of the connecting shaft (7);
a second positioning part (6) which can be positioned and matched with any first positioning part (10) to limit the grating plate (3) at a mounting angle,
one of the first positioning portion (10) and the second positioning portion (6) is provided on the vent base (1), and the other is provided on the connecting shaft (7).
4. The aircraft engine nacelle ventilation cooling opening grille angle test device of claim 3, characterized in that the second positioning portion (6) is plural.
5. The aircraft engine nacelle ventilation cooling opening grille angle test apparatus of claim 3,
the first positioning part (10) comprises a first clamping groove arranged on the ventilation opening base (1);
the second positioning part (6) comprises a second clamping groove arranged on the connecting shaft (7);
the testing device also comprises a stop block (8) arranged in the first clamping groove and the second clamping groove.
6. The aircraft engine nacelle ventilation cooling grid angle test device according to claim 5, wherein the vent base (1) comprises:
a frame enclosing the vent; and
the annular component (2) is arranged on the outer side of the frame and sleeved on the connecting shaft (7), and the first clamping groove is formed in the annular component (2).
7. The aircraft engine nacelle ventilation cooling opening grille angle test device of claim 6, wherein the first clamping groove penetrates the annular component (2) in a radial direction of the connecting shaft (7).
8. The aircraft engine nacelle ventilation cooling opening grille angle test apparatus of claim 5,
the first clamping groove is arranged on the inner circumferential surface of the through hole (11);
the second clamping groove is formed in the mode that the end face, located on the outer side of the ventilation opening base (1), of the connecting shaft (7) extends towards the ventilation opening base (1) along the axial direction of the connecting shaft (7).
9. The aircraft engine nacelle ventilation cooling opening grid angle testing device of claim 2, wherein one end of the connecting shaft (7) connected with the grid plate (3) is provided with an external thread (5), and the first end of the grid plate (3) is provided with a threaded hole (4) matched with the external thread (5).
10. The aircraft engine nacelle ventilation cooling opening grill angle test device according to claim 2, wherein the second end of the grill plate (3) is connected to the vent base (1) by a screw (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011356609.4A CN114563166B (en) | 2020-11-27 | 2020-11-27 | Aeroengine nacelle ventilation cooling port grid angle test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011356609.4A CN114563166B (en) | 2020-11-27 | 2020-11-27 | Aeroengine nacelle ventilation cooling port grid angle test device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114563166A true CN114563166A (en) | 2022-05-31 |
| CN114563166B CN114563166B (en) | 2024-06-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011356609.4A Active CN114563166B (en) | 2020-11-27 | 2020-11-27 | Aeroengine nacelle ventilation cooling port grid angle test device |
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007292671A (en) * | 2006-04-27 | 2007-11-08 | Kawasaki Heavy Ind Ltd | Side wind laboratory |
| CN202256070U (en) * | 2011-07-20 | 2012-05-30 | 辽宁忠旺集团有限公司 | Pressure test device for skirt plate ventilation opening grating of motor train unit equipment cabin |
| US20120285132A1 (en) * | 2011-05-13 | 2012-11-15 | Airbus Operations (S.A.S.) | Avionic bay comprising a device for filtering cooling air for electrical equipment installed in such a bay and aircraft equipped with such a bay |
| CN104713213A (en) * | 2015-03-12 | 2015-06-17 | 珠海格力电器股份有限公司 | Air deflector, air deflector rotating structure and air conditioner comprising air deflector and air deflector rotating structure |
| CN204730424U (en) * | 2015-03-12 | 2015-10-28 | 珠海格力电器股份有限公司 | Air deflector, air deflector rotating structure and air conditioner comprising air deflector and air deflector rotating structure |
| CN205861717U (en) * | 2016-07-20 | 2017-01-04 | 国网山西省电力公司电力科学研究院 | A kind of generator amature ventilating duct wind speed tester |
| CN107757348A (en) * | 2017-11-22 | 2018-03-06 | 怡得乐电子(杭州)有限公司 | A kind of adjustable air-inlet grille for automobile of opening angle |
| EP3367009A1 (en) * | 2017-02-28 | 2018-08-29 | Soler & Palau Research, S.L. | Ventilation device |
| CN210440875U (en) * | 2019-07-26 | 2020-05-01 | 李爱兰 | Display device for education software convenient to angle regulation |
| CN210881611U (en) * | 2019-11-25 | 2020-06-30 | 昆山耀致辉机电科技有限公司 | Automobile ventilation opening device |
-
2020
- 2020-11-27 CN CN202011356609.4A patent/CN114563166B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007292671A (en) * | 2006-04-27 | 2007-11-08 | Kawasaki Heavy Ind Ltd | Side wind laboratory |
| US20120285132A1 (en) * | 2011-05-13 | 2012-11-15 | Airbus Operations (S.A.S.) | Avionic bay comprising a device for filtering cooling air for electrical equipment installed in such a bay and aircraft equipped with such a bay |
| CN202256070U (en) * | 2011-07-20 | 2012-05-30 | 辽宁忠旺集团有限公司 | Pressure test device for skirt plate ventilation opening grating of motor train unit equipment cabin |
| CN104713213A (en) * | 2015-03-12 | 2015-06-17 | 珠海格力电器股份有限公司 | Air deflector, air deflector rotating structure and air conditioner comprising air deflector and air deflector rotating structure |
| CN204730424U (en) * | 2015-03-12 | 2015-10-28 | 珠海格力电器股份有限公司 | Air deflector, air deflector rotating structure and air conditioner comprising air deflector and air deflector rotating structure |
| CN205861717U (en) * | 2016-07-20 | 2017-01-04 | 国网山西省电力公司电力科学研究院 | A kind of generator amature ventilating duct wind speed tester |
| EP3367009A1 (en) * | 2017-02-28 | 2018-08-29 | Soler & Palau Research, S.L. | Ventilation device |
| CN107757348A (en) * | 2017-11-22 | 2018-03-06 | 怡得乐电子(杭州)有限公司 | A kind of adjustable air-inlet grille for automobile of opening angle |
| CN210440875U (en) * | 2019-07-26 | 2020-05-01 | 李爱兰 | Display device for education software convenient to angle regulation |
| CN210881611U (en) * | 2019-11-25 | 2020-06-30 | 昆山耀致辉机电科技有限公司 | Automobile ventilation opening device |
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| Publication number | Publication date |
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| CN114563166B (en) | 2024-06-25 |
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