CN115614109A - Negative pressure resistant circumferential graphite sealing structure - Google Patents
Negative pressure resistant circumferential graphite sealing structure Download PDFInfo
- Publication number
- CN115614109A CN115614109A CN202211256130.2A CN202211256130A CN115614109A CN 115614109 A CN115614109 A CN 115614109A CN 202211256130 A CN202211256130 A CN 202211256130A CN 115614109 A CN115614109 A CN 115614109A
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- Prior art keywords
- sealing
- sealing ring
- shaped chute
- groove
- negative pressure
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Links
- 238000007789 sealing Methods 0.000 title claims abstract description 139
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 title claims abstract description 26
- 229910002804 graphite Inorganic materials 0.000 title claims abstract description 26
- 239000010439 graphite Substances 0.000 title claims abstract description 26
- 238000004891 communication Methods 0.000 claims abstract description 4
- 230000007246 mechanism Effects 0.000 claims description 5
- 230000000149 penetrating effect Effects 0.000 claims description 4
- 239000003921 oil Substances 0.000 abstract description 31
- 239000010687 lubricating oil Substances 0.000 abstract description 23
- 230000009471 action Effects 0.000 abstract description 4
- 230000007774 longterm Effects 0.000 abstract description 4
- 230000000694 effects Effects 0.000 description 5
- 238000009434 installation Methods 0.000 description 4
- 238000005299 abrasion Methods 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000003756 stirring Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
-
- 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
- F01D25/18—Lubricating arrangements
- F01D25/183—Sealing means
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Sealing Devices (AREA)
Abstract
The invention relates to the technical field of aeroengine sealing, and discloses a negative pressure resistant circumferential graphite sealing structure.A sealing ring is provided with at least one C-shaped chute on the inner wall surface, the C-shaped chute comprises a communicating groove and two branch grooves, and the obliquely arranged branch grooves and the communicating groove form an oil collecting area at the downstream of the rotor in the rotation direction; one side of the C-shaped chute is a bearing cavity, the other side of the C-shaped chute is a sealing cavity, and the end face of the opening sealing ring with the C-shaped chute faces the sealing cavity. According to the invention, the branch groove of the C-shaped chute and the communication groove form an oil collection area at the downstream of the rotor in the rotation direction, and the rotor rotating at a high speed drives the leaked lubricating oil to be collected in the oil collection area under the flow guiding action of the C-shaped chute, so that the pressure of the oil collection area is increased, and the lubricating oil leaked into the sealing ring surface is returned to the bearing cavity, thereby the lubricating oil leakage of the bearing cavity can be obviously reduced under the negative pressure working condition, the sealing performance and the service life are improved, and the long-term safe and stable operation of the aero-engine is ensured.
Description
Technical Field
The invention relates to the technical field of aeroengine sealing, and discloses a negative pressure resistant circumferential graphite sealing structure.
Background
The circumferential graphite seal has the advantages of high technical maturity, good sealing performance, large allowable pressure difference, compact structure, no limitation on axial movement of a rotor and the like, is widely applied to a main shaft bearing cavity of an aircraft engine, and plays an important role in preventing lubricating oil in the bearing cavity from leaking.
When the rotor and the bearing of the aircraft engine rotate at a high speed, oil stirring and oil throwing effects can be generated, an oil-gas mixture is filled in the bearing cavity, and circumferential graphite sealing needs to be arranged between the rotor and the stator for avoiding accidents such as pollution, fire and the like caused by the fact that the oil-gas mixture leaks to the sealing cavity from the bearing cavity. One side of the circumferential graphite seal is an oil-gas environment of the bearing cavity with lower pressure, the other side of the circumferential graphite seal is pressurized air of the sealing cavity with higher pressure, and under the action of pressure difference, high-pressure air in the sealing cavity is blown into the bearing cavity to prevent lubricating oil from leaking through the circumferential graphite seal.
However, when the aircraft engine is in a transition state, a slow vehicle state or a lower state, the pressure of the bearing cavity may be greater than the pressure of the sealing cavity (i.e. a negative pressure working condition), and at this time, the lubricating oil is easy to leak.
Disclosure of Invention
The invention aims to provide a negative pressure resistant circumferential graphite sealing structure which can obviously reduce the lubricating oil leakage of a bearing cavity under the working condition of negative pressure, improve the sealing performance and prolong the service life, and ensure the long-term safe and stable operation of an aeroengine.
In order to realize the technical effects, the invention adopts the technical scheme that:
a negative pressure resistant circumferential graphite sealing structure comprises a sealing ring which can be arranged between a rotor and a stator of an aircraft engine, wherein the inner wall surface of the sealing ring is provided with at least one C-shaped chute; the C-shaped chute comprises a communicating groove and two branch grooves, the two branch grooves are obliquely arranged along the thickness direction of the sealing ring from one end surface of the sealing ring, the communicating groove penetrates and communicates the two branch grooves along the circumferential direction of the inner wall surface of the sealing ring, and the obliquely arranged branch grooves and the communicating groove form an oil collecting area.
Furthermore, the end face of the sealing ring departing from the opening of the C-shaped chute is provided with an arc-shaped groove, and the arc-shaped groove is arranged at a position close to an oil collecting area of the C-shaped chute.
Furthermore, a first groove penetrating through the end face and the communication groove is formed in a corresponding protruding area on the inner side of the C-shaped inclined groove of the sealing ring.
Furthermore, an independent groove II is formed in a corresponding protruding area of the sealing ring on the inner side of the C-shaped chute.
Furthermore, a third groove which is semi-communicated with the C-shaped chute is formed in a corresponding convex area on the inner side of the C-shaped chute by the sealing ring.
Further, the sealing ring comprises a plurality of split ring structures which are connected end to end and are hooped by a circumferential extension spring to form a ring shape; the outer wall of every split ring structure is provided with the fixed slot along circumference, and circumference extension spring is located the fixed slot.
Furthermore, the overlapping surface of the split ring structure and the adjacent split ring structure is in rectangular overlapping.
Furthermore, the sealing ring is arranged between the rotor and the stator through a sealing seat, the inner wall surface of the sealing ring is in contact with the outer wall surface of the rotor, one side of the C-shaped chute is a bearing cavity, the other side of the C-shaped chute is a sealing cavity, and the end surface of the opening sealing ring with the C-shaped chute faces the sealing cavity; be provided with in the seal receptacle and hold the chamber, the sealing ring sets up in the intracavity that holds of seal receptacle, holds the intracavity and is provided with and can carry out spacing stop gear to the sealing ring.
Further, the limiting mechanism comprises an anti-rotation pin capable of preventing the sealing ring from rotating, and a baffle plate and a clamping ring which prevent the sealing ring from being separated from the accommodating cavity.
Furthermore, a threaded sleeve is arranged on the inner wall surface of the sealing seat at a position corresponding to the sealing track of the rotor, and the threaded sleeve is in contact with the outer wall surface of the sealing track of the rotor.
Compared with the prior art, the invention has the beneficial effects that:
1. according to the invention, the branch groove of the C-shaped chute and the communicating groove form an oil collecting area at the downstream of the rotor in the rotating direction, and the rotor rotating at a high speed drives the leaked lubricating oil to be collected in the oil collecting area under the guiding action of the C-shaped chute, so that the pressure of the oil collecting area is increased, and the lubricating oil leaked into the sealing ring surface returns to the bearing cavity, thereby obviously reducing the lubricating oil leakage of the bearing cavity under the negative pressure working condition, improving the sealing performance and prolonging the service life, and ensuring the long-term safe and stable operation of the aero-engine.
2. The arrangement of the cambered surface groove can lead the lubricating oil driven by the high-speed rotor to be driven back to the bearing cavity by the cambered surface groove, and reduce the amount of the lubricating oil invading into the sealing ring surface. On the other hand, the arrangement of the cambered surface groove reduces the width of the sealing dam, namely the gap between the oil collecting area and the bearing cavity, and is favorable for the lubricating oil in the C-shaped chute to return to the bearing cavity through the smaller gap between the oil collecting area and the cambered surface groove.
3. In the invention, the corresponding convex area at the inner side of each C-shaped chute forms a functional area by arranging the first groove, the second groove or the third groove, and functional structures such as an oil guide groove or a dynamic pressure groove can be formed in the functional area, so that the oil guide effect is further enhanced, the lubricating oil leakage is reduced, or the hydrodynamic pressure is increased, the contact load is reduced, and the sealing life is prolonged.
Drawings
FIG. 1 is a schematic view of a split ring structure of a negative pressure resistant circumferential graphite seal structure in an embodiment;
FIG. 2 is a schematic structural view of a C-shaped chute in the embodiment;
FIG. 3 is a schematic view showing the rotation direction of a rotor and the inclination direction of a C-shaped chute of a corresponding sealing ring according to the embodiment;
FIG. 4 is a schematic view of a conventional seal housing structure and the installation of a seal ring in the seal housing;
FIG. 5 is a schematic view of the structure of the sealing seat and the installation of the sealing ring in the sealing seat in the embodiment;
FIG. 6 is a partially enlarged view illustrating an installation structure of an anti-rotation pin and an anti-rotation groove of a seal holder according to an embodiment of the present invention.
Wherein, 1, rotor; 2. a seal ring; 3. a communicating groove; 4. supporting a groove; 5. an oil collection area; 6. a cambered surface groove; 7. a first groove; 8. a second groove; 9. a third groove; 10. fixing grooves; 11. a circumferential extension spring; 12. rectangular lapping; 13. a sealing seat; 14. a threaded sleeve; 15. an anti-rotation pin; 16. a collar; 17. a compression spring; 18. a slot; 19. and an annular boss.
Detailed Description
The present invention will be described in further detail with reference to the following examples and accompanying drawings. It should be understood that the scope of the above-described subject matter is not limited to the following examples, and any techniques implemented based on the disclosure of the present invention are within the scope of the present invention.
Examples
Referring to fig. 1-6, a negative pressure resistant circumferential graphite sealing structure comprises a sealing ring 2 which can be arranged between a rotor 1 and a stator of an aircraft engine, wherein the inner wall surface of the sealing ring 2 is in contact with the outer wall surface of the rotor 1; at least one C-shaped chute is arranged on the inner wall surface of the sealing ring 2; the C-shaped chute comprises a communicating groove 3 and two branch grooves 4, the two branch grooves 4 are obliquely arranged along the thickness direction of the sealing ring 2 from one end surface of the sealing ring 2, the communicating groove 3 is communicated with the two branch grooves 4 in a penetrating manner along the circumferential direction of the inner wall surface of the sealing ring 2, and the obliquely arranged branch grooves 4 and the communicating groove 3 form an oil collecting area 5 at the downstream of the rotating direction of the rotor 1; one side of the C-shaped chute is a bearing cavity, the other side of the C-shaped chute is a sealing cavity, and the end face of the opening sealing ring 2 with the C-shaped chute faces the sealing cavity.
In this embodiment, when the pressure of the bearing cavity is greater than the pressure of the sealing cavity (i.e. a negative pressure working condition), the lubricating oil in the bearing cavity leaks to enter the surface of the sealing ring 2, an oil collecting area 5 is formed by the branch groove 4 of the C-shaped chute and the communicating groove 3 in the downstream of the rotation direction of the rotor 1, the rotor 1 rotating at a high speed drives the leaked lubricating oil to collect in the oil collecting area 5 under the diversion effect of the C-shaped chute, so that the pressure of the oil collecting area 5 is increased, the lubricating oil leaked to enter the surface of the sealing ring 2 returns to the bearing cavity, the lubricating oil leakage of the bearing cavity can be obviously reduced, the sealing performance and the service life are improved, and the long-term safe and stable operation of the aero-engine is ensured.
The end face, deviating from the opening of the C-shaped chute, of the sealing ring 2 is provided with an arc-shaped groove 6, and the arc-shaped groove 6 is arranged at a position close to the oil collecting area 5 of the C-shaped chute. In this embodiment, under the negative pressure operating mode, the setting of cambered surface recess 6 can make the lubricating oil that is driven by high-speed rotor 1 on the one hand be driven back to the bearing housing by cambered surface recess 6, has reduced the lubricating oil volume of invading 2 faces of sealing ring. On the other hand, the arrangement of the cambered surface groove 6 reduces the width of the sealing dam, namely the gap between the oil collecting area 5 and the bearing cavity, and is favorable for the lubricating oil in the C-shaped chute to return to the bearing cavity through the smaller gap between the oil collecting area 5 and the cambered surface groove 6.
The sealing ring 2 is provided with a groove I7 penetrating through the end face and the communicating groove 3 in a protruding area corresponding to the inner side of the C-shaped chute, an oil guide passage facing the end face of the sealing ring 2 on one side of the sealing cavity and the communicating groove 3 is added due to the arrangement of the groove I7, the oil leakage entering the sealing ring 2 is facilitated to be guided into the oil collecting area 5, and therefore the leaked oil returns to the bearing cavity more easily.
The sealing ring 2 is provided with two independent grooves 8 in the corresponding protruding region of C-shaped chute inboard, and two grooves 8 are independently located and are put in the corresponding protruding region of C-shaped chute inboard in this embodiment, are equivalent to the hydrodynamic groove, can play the effect that increases hydrodynamic pressure, alleviates contact load to promote the life of sealing ring 2.
And a third groove 9 which is semi-communicated with the C-shaped chute is arranged in a corresponding convex area on the inner side of the C-shaped chute of the sealing ring 2.
The three grooves in this embodiment have different functional emphasis, the first groove 7 mainly guides oil, the second groove 8 mainly guides oil and increases hydrodynamic pressure, and the third groove 9 mainly increases hydrodynamic pressure. It should be noted that, in this embodiment, the corresponding convex regions on the inner sides of the plurality of C-shaped chutes of the same sealing ring 2 may be individually set as any one of the first groove 7, the second groove 8, and the third groove 9, or may be used in combination with a plurality of types of functional grooves.
In this embodiment, the sealing ring 2 includes a plurality of split ring structures, which are connected end to end and are hooped by the circumferential extension spring 11 to form a ring shape; the outer wall of each split ring structure is provided with a fixing groove 10 along the circumferential direction, and a circumferential extension spring 11 is clamped in the fixing groove 10. A plurality of split ring structures are spliced into a whole ring under the action of the hoop tension of the circumferential extension spring 11, and the split ring structure plays a role in forming initial radial sealing with a runway in work.
The overlapping surface of the split ring structure and the adjacent split ring structure is a rectangular overlapping 12, and the rectangle of each split ring structure comprises a rectangular bump at one end of the split ring structure and a rectangular groove at the other end of the split ring structure and matched with the rectangular bump of the adjacent split ring structure. The overlap joint mouth structure of sealing ring 2 improves to rectangle overlap joint 12 by traditional triangle-shaped inclined plane overlap joint in this embodiment, has reduced the processing degree of difficulty, has also improved the machining precision, makes the sealed face of taking the kneck can better laminate to reduce the probability that lubricating oil leaked from the faying surface.
The sealing ring 2 is arranged between the rotor 1 and the stator through a sealing seat 13; be provided with in the seal receptacle 13 and hold the chamber, sealing ring 2 sets up in the intracavity that holds of seal receptacle 13, holds the intracavity and is provided with and can carry out spacing mechanism (generally circumferential spacing prevents that sealing ring 2 from following rotor 1 and rotating to and axial spacing prevents that sealing ring 2 from deviating from) to sealing ring 2. The sealing ring 2 is arranged in the accommodating cavity of the sealing seat 13, so that the normal work of the sealing ring 2 is ensured. The limiting mechanism in this embodiment includes an anti-rotation pin 15 that can prevent the sealing ring 2 from rotating, and a baffle and a collar 16 that prevent the sealing ring 2 from falling out of the accommodating cavity, and the installation manner of the baffle and the collar in the accommodating cavity is known to related people, and will not be described in detail.
The sealing ring 2 is provided with a slot 18 for inserting an anti-rotation pin 15, the sealing seat 13 is provided with an anti-rotation slot for inserting the anti-rotation pin 15, and the sealing ring 2 is fixed by inserting two ends of the anti-rotation pin 15 into the slot 18 and the anti-rotation slot to prevent the sealing ring from rotating along with the rotor 1; in this embodiment, the baffle plate exerts an axial thrust on the sealing ring 2 through the compression spring 17, and plays a role in forming an initial end face seal and preventing the sealing ring 2 from coming off.
During the operation of the engine, the sealing ring 2 will jump radially along the runway and generate sliding friction with the anti-rotation pin 15 on the sealing seat 13, and the abrasion amount of the part limits the service life of the circumferential graphite seal. Therefore, the anti-rotation pin 15 in this embodiment has a certain radial clearance with the anti-rotation groove on the seal holder 13, the contact surface between the anti-rotation pin 15 and the seal ring 2 may be a cylindrical surface or a plane, the cylindrical surface anti-rotation pin 15 can rotate freely, the sliding friction between the anti-rotation pin 15 and the seal ring 2 is changed into rolling friction, the plane anti-rotation pin 15 and the seal ring 2 is changed into surface contact from line contact, the abrasion loss is reduced, and the service life is prolonged. Meanwhile, the end structure of the anti-rotation pin 15 can be improved to enable the anti-rotation pin 15 to be provided with the annular boss 19, so that the anti-rotation pin 15 can be prevented from falling off from the anti-rotation groove of the sealing seat 13.
In order to enhance the oil blocking function, the conventional circumferential graphite sealing device is provided with a spiral groove (as shown in fig. 4) on a sealing seat 13; to avoid rubbing against the runway, it is necessary to maintain a large radial clearance between the spiral groove and the runway. In the present embodiment, the threaded sleeve 14 is attached to the inner wall surface of the seal holder 13 at a position corresponding to the seal raceway of the rotor 1, and the threaded sleeve 14 is in contact with the outer wall surface of the seal raceway of the rotor 1. In the embodiment, the detachable threaded sleeve 14 and the sealing seat 13 are of a split structure, the threaded sleeve 14 is arranged on the sealing seat 13 in an interference manner, and the threaded sleeve 14 is made of non-metallic materials such as graphite and rubber and is allowed to collide and rub with the runway, so that the radial clearance between the ground and the runway is small, the oil blocking function is effectively improved, and the leakage of lubricating oil is reduced; when the threaded sleeve 14 is damaged, only the threaded sleeve 14 needs to be replaced independently, and the maintenance is simple and convenient.
The present invention is not limited to the above preferred embodiments, and any modifications, equivalent substitutions and improvements made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A negative pressure resistant circumferential graphite sealing structure is characterized by comprising a sealing ring which can be arranged between a rotor and a stator of an aircraft engine, wherein the inner wall surface of the sealing ring is provided with at least one C-shaped chute; the C-shaped inclined groove comprises a communicating groove and two branch grooves, the two branch grooves are obliquely arranged along the thickness direction of the sealing ring from one end surface of the sealing ring, the communicating groove penetrates through and communicates the two branch grooves along the circumferential direction of the inner wall surface of the sealing ring, and the obliquely arranged branch grooves and the communicating groove form an oil collecting area.
2. The negative pressure resistant circumferential graphite sealing structure of claim 1, wherein an end face of the sealing ring facing away from the opening of the C-shaped chute is provided with an arc-shaped groove, and the arc-shaped groove is arranged at a position close to an oil collecting area of the C-shaped chute.
3. The negative pressure resistant circumferential graphite sealing structure of claim 1, wherein the sealing ring is provided with a first groove penetrating the end face and the communication groove in a corresponding protruding area inside the C-shaped inclined groove.
4. The negative pressure resistant circumferential graphite sealing structure of claim 1, wherein the sealing ring is provided with a second independent groove at a corresponding raised area inside the C-shaped chute.
5. The negative pressure resistant circumferential graphite sealing structure of claim 1, wherein the sealing ring is provided with a third groove in half communication with the C-shaped chute at a corresponding raised area inside the C-shaped chute.
6. The negative pressure resistant circumferential graphite seal structure of claim 1, wherein the seal ring comprises a plurality of split ring structures connected end to end and hooped by a circumferential tension spring to form a ring shape; the outer wall of each split ring structure is provided with a fixing groove along the circumferential direction, and the circumferential extension spring is located in the fixing groove.
7. The negative pressure resistant circumferential graphite seal structure of claim 6, wherein the overlapping surfaces of the split ring structure and the adjacent split ring structure are in rectangular overlapping.
8. The negative pressure resistant circumferential graphite sealing structure according to any one of claims 1 to 7, wherein the sealing ring is installed between the rotor and the stator through a sealing seat, the inner wall surface of the sealing ring is in contact with the outer wall surface of the rotor, one side of the C-shaped chute is a bearing cavity, the other side of the C-shaped chute is a sealing cavity, and the end surface of the opening sealing ring with the C-shaped chute faces the sealing cavity; the sealing device is characterized in that a containing cavity is formed in the sealing seat, the sealing ring is arranged in the containing cavity of the sealing seat, and a limiting mechanism capable of limiting the sealing ring is arranged in the containing cavity.
9. The negative pressure resistant circumferential graphite sealing structure of claim 8, wherein the limiting mechanism comprises an anti-rotation pin for preventing the sealing ring from rotating, and a baffle plate and a clamping ring for preventing the sealing ring from being removed from the accommodating cavity.
10. The circumferential graphite sealing structure with negative pressure resistance of claim 8, wherein a threaded sleeve is mounted on the inner wall surface of the sealing seat at a position corresponding to the sealing track of the rotor, and the threaded sleeve is in contact with the outer wall surface of the sealing track of the rotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211256130.2A CN115614109B (en) | 2022-10-13 | 2022-10-13 | Negative pressure-resistant circumferential graphite sealing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211256130.2A CN115614109B (en) | 2022-10-13 | 2022-10-13 | Negative pressure-resistant circumferential graphite sealing structure |
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| Publication Number | Publication Date |
|---|---|
| CN115614109A true CN115614109A (en) | 2023-01-17 |
| CN115614109B CN115614109B (en) | 2024-05-17 |
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| CN202211256130.2A Active CN115614109B (en) | 2022-10-13 | 2022-10-13 | Negative pressure-resistant circumferential graphite sealing structure |
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