CN116378832A - Sealing structure between aeroengine casing and pipeline - Google Patents

Sealing structure between aeroengine casing and pipeline Download PDF

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Publication number
CN116378832A
CN116378832A CN202310408300.2A CN202310408300A CN116378832A CN 116378832 A CN116378832 A CN 116378832A CN 202310408300 A CN202310408300 A CN 202310408300A CN 116378832 A CN116378832 A CN 116378832A
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CN
China
Prior art keywords
cylinder
annular
pressure welding
ring
bulge
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.)
Pending
Application number
CN202310408300.2A
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Chinese (zh)
Inventor
王群
尚守堂
赵明
邓洪伟
杨胜男
王殿磊
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AECC Shenyang Engine Research Institute
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AECC Shenyang Engine Research Institute
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by AECC Shenyang Engine Research Institute filed Critical AECC Shenyang Engine Research Institute
Priority to CN202310408300.2A priority Critical patent/CN116378832A/en
Publication of CN116378832A publication Critical patent/CN116378832A/en
Pending legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/28—Arrangement of seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L3/00—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets
    • F16L3/16—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets with special provision allowing movement of the pipe
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L55/00—Devices or appurtenances for use in, or in connection with, pipes or pipe systems
    • F16L55/02—Energy absorbers; Noise absorbers
    • F16L55/033—Noise absorbers
    • F16L55/035—Noise absorbers in the form of specially adapted hangers or supports

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Joints Allowing Movement (AREA)

Abstract

The application belongs to the technical field of sealing design between aeroengine cases and pipelines, and particularly relates to a sealing structure between an aeroengine case and a pipeline, which is convenient to assemble, has a vibration reduction effect, can reduce abrasion between structures, can perform abrasion compensation, can avoid leakage, can perform axial displacement compensation, transverse displacement compensation and angular displacement compensation, can reduce the requirement on processing precision, ensures the sealing effect between the pipeline and the case, reduces the installation stress generated during installation and the thermal stress generated during the operation of the aeroengine, and can have higher service life.

Description

Sealing structure between aeroengine casing and pipeline
Technical Field
The application belongs to the technical field of sealing design between an aeroengine casing and a pipeline, and particularly relates to a sealing structure between an aeroengine casing and a pipeline.
Background
There are many pipelines to pass through the structure of the casing in the aero-engine, in order to guarantee to seal between pipeline and the casing and reduce the installation stress that produces when installing, the thermal stress that produces when aero-engine works, design corresponding seal structure.
At present, a sealing structure between an aeroengine casing and a pipeline mainly comprises the following two forms:
1) The structure of the integral ball head and sleeve sealing seat is shown in fig. 1, the sealing between the casing and the pipeline is realized by means of small clearance fit between the spherical surface of the ball head and the cylindrical surface of the sleeve, the structure has the functions of angular displacement and axial displacement compensation, but does not have the function of transverse displacement compensation, the integral ball head and the sleeve sealing seat have higher requirements on processing precision, certain leakage exists, a vibration reduction structure is not arranged between the integral ball head and the sleeve sealing seat, abrasion is easy to occur, and the leakage is aggravated after the abrasion occurs;
2) The split type movable sealing ring and sleeve sealing seat structure is characterized in that the sealing between the casing and the pipeline is realized by means of small clearance fit between the split type movable sealing ring and the sleeve sealing seat as shown in fig. 2, the split type movable sealing ring and the sleeve sealing seat have the functions of compensating transverse displacement and axial displacement angular displacement, the split type movable sealing ring, the sleeve sealing seat and the sealing seat have higher requirements on processing precision, certain leakage exists, a vibration reduction structure is not arranged between the split type movable sealing ring and the sleeve sealing seat, abrasion is easy to occur, and the leakage is aggravated after the abrasion occurs.
The present application has been made in view of the existence of the above-mentioned technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present invention, which is not necessarily prior art to the present application, and should not be used for evaluating the novelty and the creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
It is an object of the present application to provide a sealing structure between an aeroengine casing and a pipeline, which overcomes or alleviates at least one technical drawback of the known art.
The technical scheme of the application is as follows:
an aeroengine case and pipeline sealing structure, comprising:
a casing having a mounting hole thereon;
an outer support cylinder, one end of which extends into the casing from the mounting hole, the inner wall of the outer support cylinder is provided with an annular support bulge, and the outer wall of the outer support cylinder is provided with an annular mounting edge; the annular mounting edge is connected to the casing;
the inner side supporting cylinder is arranged in the outer side supporting cylinder, a radial gap is formed between the inner side supporting cylinder and the outer side supporting cylinder, and an annular limiting bulge is formed in the inner wall of one end of the inner side supporting cylinder, which faces towards the annular supporting bulge;
the lower crimping cylinder is arranged in the inner supporting cylinder, one end of the lower crimping cylinder penetrates through the annular limiting bulge and stretches into the annular supporting bulge, a radial gap exists between the lower crimping cylinder and the annular supporting bulge, and the outer wall of the other end of the lower crimping cylinder is provided with the lower annular crimping bulge;
an upper crimping barrel, one end of which extends into the inner supporting barrel, and the outer wall of which is provided with an upper annular crimping bulge;
the compression joint ring is sleeved on the periphery of the upper compression joint cylinder, is positioned in the outer support cylinder and has a radial gap with the outer support cylinder;
the sealing ring is sleeved on the periphery of the upper crimping cylinder, is positioned in the outer supporting cylinder, has a radial gap with the outer supporting cylinder and forms an annular sealing groove with the crimping ring;
the sealing ring is arranged in the annular sealing groove and positioned at the periphery of the upper compression joint cylinder;
the mounting ring is sleeved on the periphery of the upper pressure welding cylinder, a radial gap exists between the mounting ring and the upper pressure welding cylinder, and the mounting ring is connected to the casing to compress the sealing ring and the pressure welding ring;
the pipeline penetrates through the mounting ring, the upper pressure welding cylinder and the lower pressure welding cylinder;
the ball head is sleeved on the pipeline and positioned between the upper pressure welding cylinder and the lower pressure welding cylinder and is in spherical fit with the upper pressure welding cylinder and the lower pressure welding cylinder;
the two pre-tightening springs are sleeved on the periphery of the lower pressure welding cylinder, two ends of each pre-tightening spring are propped against the annular limiting bulge and the annular pressure welding bulge of the lower portion, the other pre-tightening spring is sleeved on the periphery of the upper pressure welding cylinder, two ends of each pre-tightening spring are propped against the annular pressure welding bulge and the pressure welding ring of the upper portion, so that the upper pressure welding cylinder and the lower pressure welding cylinder are tightly pressed on the ball head, the inner side supporting cylinder is tightly pressed on the annular supporting bulge, and an axial gap is reserved between the pressure welding ring and the inner side supporting cylinder.
According to at least one embodiment of the application, in the sealing structure between the aeroengine casing and the pipeline, the annular mounting edge and the mounting ring are connected to the casing through bolts.
According to at least one embodiment of the present application, in the sealing structure between the aeroengine casing and the pipeline, the sealing ring is a C-shaped metal sealing ring.
According to at least one embodiment of the present application, in the sealing structure between the aeroengine casing and the pipeline, the mounting ring is provided with an annular positioning protrusion, and the annular positioning protrusion is clamped into one end of the outer support cylinder, which is provided with an annular mounting edge.
According to at least one embodiment of the application, in the sealing structure between the aeroengine casing and the pipeline, the pipeline and the ball head are welded.
The application has at least the following beneficial technical effects:
the sealing structure between the aeroengine casing and the pipeline is convenient to assemble, has a vibration reduction effect, can reduce abrasion between structures, can perform abrasion compensation, can avoid leakage, can perform axial displacement compensation, transverse displacement compensation and angular displacement compensation, can reduce the requirement on processing precision, ensures the sealing effect between the pipeline and the casing, reduces the installation stress generated during installation and the thermal stress generated during the operation of the aeroengine, and can have a longer service life.
Drawings
FIG. 1 is a schematic view of a prior art seal arrangement for an integral ball and socket seal between an aircraft engine case and a pipeline;
FIG. 2 is a schematic view of a sealing structure of a split floating seal ring and a sleeve seal seat between a casing and a pipeline of a conventional aeroengine;
FIG. 3 is a schematic view of a seal structure between an aero-engine case and a pipeline provided in an embodiment of the present application;
fig. 4 is a schematic diagram of an assembly process of a sealing structure between an aero-engine casing and a pipeline according to an embodiment of the present application;
FIG. 5 is a schematic diagram of lateral displacement compensation of an aero-engine case and pipeline sealing structure provided by an embodiment of the present application;
FIG. 6 is a schematic diagram of axial displacement compensation of a seal structure between an aero-engine case and a pipeline according to an embodiment of the present disclosure;
FIG. 7 is a schematic view of angular displacement compensation of an aero-engine case and pipeline sealing structure provided by an embodiment of the present application;
wherein:
1-a pipeline; 2-a sealing ring; 3-mounting ring; 4-bolts; 5-pre-tightening a spring; 6-ball head; 7-an inner support cylinder; 8-a lower crimping barrel; 9-an upper crimp barrel; 10-sealing rings; 11-crimping ring; 12-an outer support cylinder; 13-casing.
For better illustration of the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the actual product size, and furthermore, the drawings are for illustrative purposes only and are not to be construed as limiting the present application.
Detailed Description
In order to make the technical solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application, not for limitation of the present application. It should be noted that, for convenience of description, only the portion relevant to the present application is shown in the drawings, and other relevant portions may refer to a general design, and without conflict, the embodiments and technical features in the embodiments may be combined with each other to obtain new embodiments.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of this application should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in this description are merely used to indicate relative directions or positional relationships, and do not imply that a device or element must have a particular orientation, be configured and operated in a particular orientation, and that the relative positional relationships may be changed when the absolute position of the object being described is changed, and thus should not be construed as limiting the present application. The terms "first," "second," "third," and the like, as used in the description herein, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the invention are not to be construed as limited in number to the precise location of at least one. As used in this description, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term and that is listed after the term and its equivalents, without excluding other elements or articles.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description herein are to be construed broadly and refer to either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The present application is described in further detail below in conjunction with fig. 1-7.
An aeroengine casing and pipeline sealing structure, as shown in fig. 3, comprises:
a casing 13 having a mounting hole thereon;
an outer support cylinder 12 having one end extending from the mounting hole into the casing 13, the inner wall of the end having an annular support projection and the outer wall of the other end having an annular mounting edge; the annular mounting edge is connected to the casing 13;
an inner support cylinder 7 which is arranged in the outer support cylinder 12, has a radial gap with the outer support cylinder 12, and has an annular limiting bulge towards the inner wall of one end of the annular support bulge;
a lower crimping barrel 8 disposed in the inner support barrel 7, one end of which extends into the annular support protrusion through the annular limit protrusion, a radial gap exists between the end and the annular support protrusion, and the outer wall of the other end is provided with a lower annular crimping protrusion;
an upper crimping barrel 9, one end of which extends into the inner support barrel 7, the outer wall of which has an upper annular crimping projection;
the compression joint ring 11 is sleeved on the periphery of the upper compression joint cylinder 9, is positioned in the outer support cylinder 12 and has a radial gap with the outer support cylinder 12;
a sealing ring 10 sleeved on the periphery of the upper pressure welding cylinder 9 and positioned in the outer supporting cylinder 12, wherein a radial gap exists between the sealing ring and the outer supporting cylinder 12, and an annular sealing groove is formed between the sealing ring and the pressure welding ring 11;
a seal ring 2 arranged in the annular seal groove and positioned at the periphery of the upper pressure welding cylinder 9;
the mounting ring 3 is sleeved on the periphery of the upper pressure welding cylinder 9, a radial gap exists between the mounting ring and the upper pressure welding cylinder 9, and is connected to the casing 13 to compress the sealing ring 10 and the pressure welding ring 11;
a pipeline 1, which penetrates through the mounting ring 3, the upper pressure welding cylinder 9 and the lower pressure welding cylinder 8;
the ball head 6 is sleeved on the pipeline 1, is positioned between the upper pressure welding cylinder 9 and the lower pressure welding cylinder 8, and is in spherical fit with the upper pressure welding cylinder 9 and the lower pressure welding cylinder 8;
the two pre-tightening springs 5, one pre-tightening spring 5 is sleeved on the periphery of the lower pressure welding barrel 8, two ends of the pre-tightening spring are propped against the annular limiting bulge and the lower annular pressure welding bulge, the other pre-tightening spring 5 is sleeved on the periphery of the upper pressure welding barrel 9, two ends of the pre-tightening spring are propped against the upper annular pressure welding bulge and the pressure welding ring 11, the upper pressure welding barrel 9 and the lower pressure welding barrel 8 are pressed on the ball head 6, the inner side supporting barrel 7 is pressed on the annular supporting bulge, and an axial gap is reserved between the pressure welding ring 11 and the inner side supporting barrel 7.
The sealing structure between the aeroengine casing and the pipeline disclosed in the above embodiment is convenient to assemble, and in a specific assembling process, as shown in fig. 4, the outer support cylinder 12 is designed to support the mounting ring 3 to compress the mounting ring 3, so that the outer support cylinder 12, the mounting ring 3, the inner support cylinder 7, the crimping ring 11 and the sealing ring 10 are in sealing contact in the axial direction, leakage can be avoided, and the pretension is performed between the annular crimping bulge on the upper and lower part of the lower crimping cylinder 8 and the annular limiting bulge on the inner support cylinder 7, and between the annular crimping bulge on the upper part of the upper crimping cylinder 9 and the crimping ring 11 by the pretension spring 5, so that the pretension spring 5 can have a vibration reduction effect, and an axial gap is reserved between the crimping ring 11 and the inner support cylinder 7, abrasion between structures can be reduced, the sealing performance of the structure can be ensured, and axial displacement compensation can be performed, as shown in fig. 5.
In the sealing structure between the aeroengine casing and the pipeline disclosed in the above embodiment, a plurality of positions are designed to have radial gaps in the radial direction, including between the inner support cylinder 7 and the outer support cylinder 12, between the compression ring 11 and the outer support cylinder 12, between the sealing ring 10 and the outer support cylinder 12, between the mounting ring 3 and the upper compression cylinder 9, etc., so that lateral displacement compensation can be performed, as shown in fig. 6.
In the sealing structure between the aeroengine casing and the pipeline disclosed by the embodiment, the ball head 6 sleeved on the pipeline 1 is designed to be in spherical surface matched contact with the upper pressure welding cylinder 9 and the lower pressure welding cylinder 8, and is clamped by utilizing the pretightening force of the two pretightening springs 5, so that angular displacement compensation can be effectively carried out.
In some alternative embodiments, in the sealing structure between the aeroengine casing and the pipeline, the annular mounting edge and the mounting ring 3 are connected to the casing 13 through bolts 4.
In some alternative embodiments, in the sealing structure between the aeroengine casing and the pipeline, the sealing ring 2 is a C-shaped metal sealing ring, which has high temperature resistance, wear resistance and easy sliding.
In some alternative embodiments, in the sealing structure between the aeroengine casing and the pipeline, the mounting ring 3 is provided with an annular positioning protrusion, and the annular positioning protrusion is clamped into one end of the outer support barrel 12 provided with an annular mounting edge for centering.
In some alternative embodiments, in the sealing structure between the aeroengine casing and the pipeline, the pipeline 1 and the ball head 6 are welded.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments illustrated in the accompanying drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the relevant technical features without departing from the principles of the present application, and those changes or substitutions will now fall within the scope of the present application.

Claims (5)

1. An aeroengine case and pipeline sealing structure, which is characterized by comprising:
a casing (13) having a mounting hole therein;
an outer support cylinder (12), one end of which extends into the casing (13) from the mounting hole, the inner wall of the end is provided with an annular support bulge, and the outer wall of the other end is provided with an annular mounting edge; the annular mounting edge is connected to the casing (13);
an inner support cylinder (7) which is arranged in the outer support cylinder (12), a radial gap is reserved between the inner support cylinder and the outer support cylinder (12), and an inner wall of one end of the inner support cylinder, which faces towards the annular support bulge, is provided with an annular limiting bulge;
a lower crimping barrel (8) is arranged in the inner supporting barrel (7), one end of the lower crimping barrel penetrates through the annular limiting bulge and stretches into the annular supporting bulge, a radial gap exists between the lower crimping barrel and the annular supporting bulge, and the outer wall of the other end of the lower crimping barrel is provided with a lower annular crimping bulge;
an upper crimping cylinder (9), one end of which extends into the inner supporting cylinder (7), and the outer wall of which is provided with an upper annular crimping bulge;
the compression joint ring (11) is sleeved on the periphery of the upper compression joint cylinder (9), is positioned in the outer support cylinder (12) and has a radial gap with the outer support cylinder (12);
the sealing ring (10) is sleeved on the periphery of the upper crimping cylinder (9), is positioned in the outer supporting cylinder (12), has a radial gap with the outer supporting cylinder (12), and forms an annular sealing groove with the crimping ring (11);
the sealing ring (2) is arranged in the annular sealing groove and positioned at the periphery of the upper compression joint cylinder (9);
the mounting ring (3) is sleeved on the periphery of the upper pressure welding cylinder (9), a radial gap exists between the mounting ring and the upper pressure welding cylinder (9), and the mounting ring is connected to the casing (13) to compress the sealing ring (10) and the pressure welding ring (11);
the pipeline (1) penetrates through the mounting ring (3), the upper pressure welding cylinder (9) and the lower pressure welding cylinder (8);
the ball head (6) is sleeved on the pipeline (1) and positioned between the upper pressure welding cylinder (9) and the lower pressure welding cylinder (8) and is in spherical fit with the upper pressure welding cylinder (9) and the lower pressure welding cylinder (8);
two pretension springs (5), one pretension spring (5) is sleeved on the periphery of the lower pressure welding cylinder (8), two ends are propped between the annular limiting bulge and the lower annular pressure welding bulge, the other pretension spring (5) is sleeved on the periphery of the upper pressure welding cylinder (9), two ends are propped between the upper annular pressure welding bulge and the pressure welding ring (11), the upper pressure welding cylinder (9) and the lower pressure welding cylinder (8) are tightly pressed on the ball head (6), the inner side supporting cylinder (7) is tightly pressed on the annular supporting bulge, and an axial gap is reserved between the pressure welding ring (11) and the inner side supporting cylinder (7).
2. The sealing structure between an aeroengine casing and a pipeline according to claim 1, wherein,
the annular mounting edge and the mounting ring (3) are connected to the casing (13) through bolts (4).
3. The sealing structure between an aeroengine casing and a pipeline according to claim 1, wherein,
the sealing ring (2) is a C-shaped metal sealing ring.
4. The sealing structure between an aeroengine casing and a pipeline according to claim 1, wherein,
the mounting ring (3) is provided with an annular positioning bulge which is clamped into one end of the outer support cylinder (12) with an annular mounting edge.
5. The sealing structure between an aeroengine casing and a pipeline according to claim 1, wherein,
the pipeline (1) and the ball head (6) are welded and connected.
CN202310408300.2A 2023-04-17 2023-04-17 Sealing structure between aeroengine casing and pipeline Pending CN116378832A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202310408300.2A CN116378832A (en) 2023-04-17 2023-04-17 Sealing structure between aeroengine casing and pipeline

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202310408300.2A CN116378832A (en) 2023-04-17 2023-04-17 Sealing structure between aeroengine casing and pipeline

Publications (1)

Publication Number Publication Date
CN116378832A true CN116378832A (en) 2023-07-04

Family

ID=86974936

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202310408300.2A Pending CN116378832A (en) 2023-04-17 2023-04-17 Sealing structure between aeroengine casing and pipeline

Country Status (1)

Country Link
CN (1) CN116378832A (en)

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