CN110578558A - packaging type hole type damping seal with edge folding damping type holes and suitable for bidirectional rotation - Google Patents
packaging type hole type damping seal with edge folding damping type holes and suitable for bidirectional rotation Download PDFInfo
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- CN110578558A CN110578558A CN201910871543.3A CN201910871543A CN110578558A CN 110578558 A CN110578558 A CN 110578558A CN 201910871543 A CN201910871543 A CN 201910871543A CN 110578558 A CN110578558 A CN 110578558A
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- damping
- layer
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- sealing
- holes
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- 238000013016 damping Methods 0.000 title claims abstract description 69
- 230000002457 bidirectional effect Effects 0.000 title abstract description 17
- 238000004806 packaging method and process Methods 0.000 title description 3
- 238000007789 sealing Methods 0.000 claims abstract description 78
- 239000010410 layer Substances 0.000 description 67
- 230000000694 effects Effects 0.000 description 10
- 238000012423 maintenance Methods 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 5
- 230000007547 defect Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 239000012530 fluid Substances 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 230000002441 reversible effect Effects 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000011229 interlayer Substances 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000005219 brazing Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000036961 partial effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000002829 reductive effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/10—Shaft sealings
- F04D29/102—Shaft sealings especially adapted for elastic fluid pumps
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
Abstract
The integrated hole type damping seal with the edgefold damping hole is suitable for bidirectional rotation, a damping seal block is laid in a sealing area of the inner wall of a turbine mechanical stator, and the damping seal block comprises an inner liner layer, an intermediate layer and an outer layer which are overlapped from inside to outside; first through holes are uniformly distributed on the inner lining layer, and double folds are arranged on the inner side openings of the first through holes; a groove is formed in the inner wall surface of the middle layer, the groove accommodates the lining layer, second through holes are uniformly distributed in the middle layer, and the second through holes are overlapped with the first through holes in the lining layer; the outer side of the circumferential end part of the middle layer is provided with a groove for placing a sealing strip; the cross section of the outer layer is I-shaped, the top surface of the inner side is connected with the bottom surface of the outer side through the waist, the top surface is a smooth arc surface which is wider relative to the bottom surface, the top surface is tightly attached to the outer side surface of the middle layer, and the top surface, the bottom surface and the waist form a T-shaped arc clamping groove. Compared with the classical circular straight-through hole damping seal, the invention can adapt to the turbine machine which may rotate bidirectionally, not only is convenient to replace, but also can improve the sealing performance.
Description
Technical Field
The present invention relates to a shaft end sealing device suitable for use in various gas turbines, steam turbines, compressors, and other turbomachines.
Background
The increasing technical level of rotating machines, in particular turbomachines, is closely linked to the continuous improvement and structural renewal of the sealing means. Currently, the seals used for rotating and stationary parts are of a wide variety, such as: brush seals, labyrinth seals, honeycomb seals, and orifice-type damping seals, bag-type damping seals. The labyrinth seal is a sealing device which is most commonly used in turbomachinery because of relatively simple structure and low cost, and the labyrinth seal depends on a series of expansion gaps and dissipation cavities formed between seal teeth and a rotor, when leakage fluid flows through the expansion gaps, partial pressure energy is converted into speed energy, throttling and thermodynamic effects are generated by the passing fluid, and the pressure of the leakage fluid is gradually reduced to achieve the sealing effect. At present, as turbomachinery is increasingly developed towards high temperature, high rotating speed and high pressure working condition parameters, labyrinth seals are difficult to completely overcome due to the fact that rotating parts are easy to scrape or/and tooth tips are easy to fall down under the high parameter conditions, and therefore researchers and users are always searching for and developing new gap sealing technologies. In recent 20 years, the honeycomb damping seal has attracted attention and is regarded as important because of its good leakage-proof effect and excellent dynamic characteristics, and is used for sealing the shaft gap or the tooth crest gap of some turbomachines, but the honeycomb damping seal is generally made of nickel-based alloy by adopting a brazing technology, is complex to manufacture and expensive in cost, so that the popularization and the use of the honeycomb damping seal are limited, and the honeycomb damping seal is difficult to popularize on a large scale. The aluminum hole type damping seal which is considered as an excellent substitute of the honeycomb seal can well avoid the defects of the honeycomb seal. At present, the sealing structure with better leakage-resisting effect is generally considered to be a labyrinth-honeycomb combined type seal, the honeycomb component is arranged as a static part of a sealing element, the labyrinth component and a rotating shaft are made into a whole, and the labyrinth component also rotates along with the rotating shaft when the rotating shaft rotates. Under the working conditions of high rotating speed and large vibration, the labyrinth teeth of the labyrinth-honeycomb combined seal also generate lodging and abrasion, and when the labyrinth teeth are serious, the whole rotating shaft needs to be replaced, so that the maintenance amount is huge, and huge economic losses are brought, which are described in patents CN 105114629B and CN 205350364U. Along with the increasingly severe requirements of the rotary machine for adapting to working conditions, the diameter of the rotary shaft is increased, and the integral sealing structure matched with the rotary shaft is difficult to process due to the large diameter. Meanwhile, in the use site of the turbine machinery, problems of reverse rotation of a driver or process disordered opening and the like sometimes occur, so that airflow flowing into a sealing gap can reversely flow in a reverse direction, and serious standard exceeding of leakage and unit failure are caused. In a word, the existing seal can not meet the comprehensive requirements that the turbine machinery is suitable for the application occasions with high working condition parameters, is suitable for the condition of bidirectional rotating airflow, has good leakage-resistant effect, is simple and convenient to process and manufacture and the like. Therefore, based on the advantages of good leakage-proof effect, easy manufacture and low cost of the hole-type damping seal, the double effects of flow resistance and turbulence similar to labyrinth seal teeth are added on the basis of the traditional hole-type damping seal, and the container type hole-type damping seal with the folded edge damping type holes suitable for bidirectional rotation is invented and is suitable for shaft end sealing devices of various gas turbines, steam turbines, compressors and other turbomachines.
disclosure of Invention
the invention provides a container type hole-shaped damping seal with a folded edge damping hole, which is suitable for bidirectional rotation, low in cost, easy to manufacture and obviously improved in flow choking and flow disturbing effects compared with the seal, and aims to overcome the defects that the traditional labyrinth seal is easy to fall and wear, the defects that the traditional honeycomb damping seal is complicated to manufacture and high in cost and the typical defect that the traditional hole-shaped damping seal is poor in flow disturbing effect.
the technical scheme of the invention is as follows:
The collection dress formula pass damping that is fit for two-way rotatory area hem damping type hole is sealed, its characterized in that: laying a damping sealing block in a sealing area of the inner wall of the stator of the turbine machine, wherein the damping sealing block comprises an inner liner 3, an intermediate layer 2 and an outer layer 1 which are overlapped from inside to outside, one side close to a rotating shaft is taken as the inner side, the other side is taken as the outer side, and the direction of a main shaft is taken as the axial direction;
First through holes 33 are uniformly distributed on the inner liner layer 3, double folds 32 are arranged on the inner side openings of the first through holes 33, each double fold 32 comprises a rib arranged along the diameter of the inner side opening of the first through hole 33, the direction of each rib is parallel to the axial direction, two circular arc-shaped folded edges are respectively connected to two sides of each rib, and the two folded edges are tilted at the same angle;
a groove 22 is formed in the inner wall surface of the middle layer 2, the inner lining layer 3 is contained in the groove 22, second through holes 21 are uniformly distributed in the middle layer 2, and the second through holes are overlapped with first through holes 33 in the inner lining layer 3; a groove 23 for placing a sealing strip is arranged on the outer side of the circumferential end part of the middle layer 2;
The cross section of the outer layer 1 is I-shaped, the top surface 11 of the inner side is connected with the bottom surface 12 of the outer side through the waist 13, the top surface 11 is a smooth arc surface which is wider relative to the bottom surface 12, the top surface 11 is tightly attached to the outer side surface of the middle layer 2, and the top surface 11, the bottom surface 12 and the waist 13 form a T-shaped arc clamping groove.
preferably, the inner liner 3, the intermediate layer 2 and the outer layer 1 are connected together by rivets 4.
Preferably, a sealing groove 5 is formed at the end between the outer layer 1 and the groove 23 of the intermediate layer 2; and sealing strips are embedded into the sealing grooves 5 to form a sealing structure between the damping sealing blocks.
The outer layer 1 is arranged in a corresponding sealing area on a turbomachine stator by a T-shaped arc clamping groove formed by the top surface 11, the bottom surface 12 and the waist part 13.
During installation and maintenance, the sealing strips are embedded into the sealing grooves 5, and then the damping sealing blocks are placed in corresponding sealing areas of the turbine mechanical stator one by one, so that a complete shaft end sealing device is formed.
Preferably, the diameter of the first through hole 33 on the sealing surface of the lining layer 3 is set as D, the width of the rib of the first through hole 33 is t, and the relationship between t and D is: t is (1/3-1/5) D, and the width t of the folded edge 321taking the value as (D-t)/2, the distance between the highest point of the edge folding circular arc and the thickness middle plane of the first through hole 33 is delta D, and the value delta D is (1/10-1/20) D, wherein D is 1-10 mm according to the delta D and t1That is to sayto obtain the angle theta between the hem and the median plane of the thickness of the first through hole 33.
Preferably, the thickness of the inner liner layer 3 is 0.05-1.0 mm; the thickness of the middle layer 2 is 0.05-12.0 mm; the thickness of the bottom surface 12 of the outer layer 1 is 1.5-8.0 mm.
Further, the thickness range of the inner liner 3 is 0.05-0.25 mm, the thickness range of the middle layer 2 is 0.5-4.5 mm, and the thickness range of the bottom surface 12 of the outer layer 1 is 2.5-5.0 mm.
Preferably, the pattern of the first through-hole 33 is selected from one of the following: circular hole, raindrop hole, oval hole, hexagonal hole.
the working principle of the invention is as follows:
The structure is three-layer combination cartridge type pass damping seal block, because sealed shaft diameter is too big, required seal structure diameter is also great, when sealed receive wearing and tearing or collide with, often need whole maintenance to change, and is neither convenient, extravagant serious more, brings serious economic loss for the user, increases maintainer's intensity of labour and work load. Therefore, the traditional integral sealing structure is changed into an assembled combined container type hole-shaped damping sealing block, and the layers of the container type sealing block are fixedly connected together by rivets, so that seamless joint between the layers is ensured, and gas is ensured not to leak between the layers. During specific installation, the T-shaped arc clamping groove of the outer layer fixing layer of the three-layer combined container type hole-shaped damping sealing block is fixed in the sealing area of the turbine unit stator. When gas flows into a gap between the sealing stator surface and the rotating shaft from one side, part of the gas flows into the sealing hole of the middle layer sealing layer along the inner wall of the convex folded edge of the bidirectional damping type hole sealing layer with the folded edge of the lining strip because the folded edge of the bidirectional damping type hole sealing layer with the folded edge of the lining strip on the gas facing side blocks and changes the flowing direction of the gas flow, and the gas flow generates rapid speed reduction and forms strong vortex dissipation in the sealing hole; the other part of the gas flow has no retardation of the bidirectional damping type hole sealing layer with the folded edge of the lining strip, and the gas flow path is not changed, so that the gas flow continuously flows along the gap between the bidirectional damping type hole sealing layer with the folded edge of the lining strip and the rotating shaft. When the flow direction of the gas is opposite, because the two folded edges of the damping type hole of the lining layer are in a symmetrical structure, the same flow resisting effect as the above can be generated in the same way. The structure thus has the function of accommodating a bidirectional flow of the sealing air flow.
The invention has the advantages and beneficial effects that:
(1) The combination ingeniously integrates the advantages of labyrinth seal and hole type damping seal, and meanwhile, the bidirectional damping type hole seal with the folded edge on the inner liner layer is installed in the sealing area of the turbomachine stator and is soft in texture, so that the problems of collision, abrasion, lodging and the like between the bidirectional damping type hole seal and a rotating shaft under the conditions of large vibration, shaft deflection and no unbalance and the like of the labyrinth seal can be avoided; in addition, because two hems of the damping type hole of the bidirectional damping type hole sealing layer with the hems on the inner liner are of a symmetrical structure, when airflow flows to the adverse conditions caused by the process disordered opening of the unit, the reverse rotation of a driving machine and the like, the flow blocking effect of the hems cannot be influenced. Therefore, the structure has the function of adapting to bidirectional rotation or positive and negative through flow of the airflow.
(2) The traditional integral sealing structure is changed into the assembled combined container type hole-shaped damping sealing block, so that when the sealing element and the rotating shaft are scraped and rubbed, only the sealing block rubbed in the sealing structure can be replaced, and the whole sealing ring does not need to be replaced, thereby improving the maintenance efficiency of the sealing element and reducing the maintenance cost. Meanwhile, the block structure of the container type hole type damping seal suitable for the bidirectional rotating damping type hole with the folded edge can be applied to turbine machines with different shaft diameters, particularly large-shaft-diameter turbine units.
Description of the drawings:
FIG. 1 is a schematic three-dimensional structure of the present invention.
Fig. 2 is a schematic view of the structure of the inner liner of the present invention.
Fig. 3 is a schematic structural view of a first through hole of the liner layer according to the present invention.
FIG. 4 is a schematic three-dimensional structure of an interlayer of the present invention.
Fig. 5 is a schematic three-dimensional structure of the outer layer of the present invention.
Wherein: 1-an outer layer; 2-an intermediate layer; 3-an inner liner layer; 4-riveting; 5-sealing groove; 11-top surface, 12-bottom surface, 13-waist part, 14-outer layer rivet through hole; 21-a second through hole, 22-a positioning cambered surface groove and 23-a groove; 24-interlayer rivet through hole; 31-inner liner rivet through hole; 32-folding edges; 33-first via.
Detailed Description
The following further details the practice of the invention with reference to the accompanying drawings:
The technical scheme of the invention is as follows:
The packaging type hole type damping seal with the edgefold damping type hole is suitable for bidirectional rotation, a damping seal block is laid in a sealing area of the inner wall of a stator of the turbine machine, the damping seal block comprises an inner liner layer 3, an intermediate layer 2 and an outer layer 1 which are overlapped from inside to outside, one side close to a rotating shaft is the inner side, the other side is the outer side, and the direction of a main shaft is the axial direction;
First through holes 33 are uniformly distributed on the inner liner layer 3, double folds 32 are arranged on the inner side openings of the first through holes 33, each double fold 32 comprises a rib arranged along the diameter of the inner side opening of the first through hole 33, the direction of each rib is parallel to the axial direction, two circular arc-shaped folded edges are respectively connected to two sides of each rib, and the two folded edges are tilted at the same angle;
A groove 22 is formed in the inner wall surface of the middle layer 2, the inner lining layer 3 is contained in the groove 22, second through holes 21 are uniformly distributed in the middle layer 2, and the second through holes are overlapped with first through holes 33 in the inner lining layer 3; a groove 23 for placing a sealing strip is arranged on the outer side of the circumferential end part of the middle layer 2;
The cross section of the outer layer 1 is I-shaped, the top surface 11 of the inner side is connected with the bottom surface 12 of the outer side through the waist 13, the top surface 11 is a smooth arc surface which is wider relative to the bottom surface 12, the top surface 11 is tightly attached to the outer side surface of the middle layer 2, and the top surface 11, the bottom surface 12 and the waist 13 form a T-shaped arc clamping groove.
the intermediate layer 2 and the outer layer 1 are connected together by rivets 4. The rivet 4 passes through the outer layer rivet through hole 14, the middle layer rivet through hole 24 and the inner liner rivet through hole 31.
A sealing groove 5 is formed at the end part between the outer layer 1 and the groove 23 of the middle layer 2; and sealing strips are embedded into the sealing grooves 5 to form a sealing structure between the damping sealing blocks.
The outer layer 1 is arranged in a corresponding sealing area on a turbomachine stator by a T-shaped arc clamping groove formed by the top surface 11, the bottom surface 12 and the waist part 13.
during installation and maintenance, the sealing strips are embedded into the sealing grooves 5, and then the damping sealing blocks are placed in corresponding sealing areas of the turbine mechanical stator one by one, so that a complete shaft end sealing device is formed.
The diameter of the first through hole 33 on the sealing surface of the lining layer 3 is set as D, the width of the rib of the first through hole 33 is t, and the relationship between t and D is as follows: t is (1/3-1/5) D, and the width t of the folded edge 321Taking the value as (D-t)/2, the distance between the highest point of the edge folding circular arc and the thickness middle plane of the first through hole 33 is delta D, and the value delta D is (1/10-1/20) D, wherein D is 1-10 mm according to the delta D and t1The angle theta between the flange and the middle plane of the thickness of the first through hole 33 can be obtained.
The thickness of the inner liner layer 3 is 0.05-1.0 mm; the thickness of the middle layer 2 is 0.05-12.0 mm; the thickness of the bottom surface 12 of the outer layer 1 is 1.5-8.0 mm.
Further, the thickness range of the inner liner 3 is 0.05-0.25 mm, the thickness range of the middle layer 2 is 0.5-4.5 mm, and the thickness range of the bottom surface 12 of the outer layer 1 is 2.5-5.0 mm.
the shape of the first through hole 33 is selected from one of the following: circular hole, raindrop hole, oval hole, hexagonal hole.
The embodiments described in this specification are merely exemplary of implementations of the inventive concept and the scope of the present invention should not be considered limited to the embodiments described herein, but rather by the claims and their equivalents.
Claims (7)
1. The collection dress formula pass damping that is fit for two-way rotatory area hem damping type hole is sealed, its characterized in that: laying a damping sealing block in a sealing area of the inner wall of the turbine mechanical stator, wherein the damping sealing block comprises an inner liner (3), an intermediate layer (2) and an outer layer (1) which are overlapped from inside to outside, one side close to a rotating shaft is taken as the inner side, the other side is taken as the outer side, and the direction of a main shaft is taken as the axial direction;
First through holes (33) are uniformly distributed on the inner liner layer (3), double folds (32) are arranged on the inner side opening of the first through holes (33), each double fold (32) comprises a rib arranged along the diameter of the inner side opening of the first through hole (33), the direction of each rib is parallel to the axial direction, two circular arc-shaped folding edges are respectively connected to two sides of each rib, and the two folding edges are tilted at the same angle;
A groove (22) is formed in the inner wall surface of the middle layer (2), the inner lining layer (3) is contained in the groove (22), second through holes (21) are uniformly distributed in the middle layer (2), and the second through holes are overlapped with first through holes (33) in the inner lining layer (3); a groove (23) for placing a sealing strip is formed in the outer side of the circumferential end part of the middle layer (2);
The cross section of the outer layer (1) is I-shaped, the top surface (11) of the inner side is connected with the bottom surface (12) of the outer side through the waist (13), the top surface (11) is a smooth arc surface which is wider relative to the bottom surface (12), the top surface (11) is tightly attached to the outer side surface of the middle layer (2), and the top surface (11), the bottom surface (12) and the waist (13) form a T-shaped arc clamping groove.
2. a cartridge-style orifice-type damping seal with a flanged damping orifice adapted for bi-directional rotation as set forth in claim 1, wherein: the inner liner layer (3), the middle layer (2) and the outer layer (1) are connected together through rivets (4).
3. A cartridge-style orifice-type damping seal with a flanged damping orifice adapted for bi-directional rotation as set forth in claim 2, wherein: a sealing groove (5) is formed at the end part between the outer layer (1) and the groove (23) of the middle layer (2); and sealing strips are embedded into the sealing grooves (5) to form a sealing structure between the damping sealing blocks.
4. A cartridge-style orifice-type damping seal with a flanged damping orifice adapted for bi-directional rotation as set forth in claim 3 wherein: a first through hole on the sealing surface of the inner liner (3)(33) Is given as D, the width of the ribs of the first through-hole (33) is given as t, the relationship between t and D being: t is (1/3-1/5) D, and the width t of the folded edge (32)1Taking the value as (D-t)/2, the distance between the highest point of the flanging arc and the thickness middle plane of the first through hole (33) is delta D, and the value delta D is (1/10-1/20) D, wherein D is 1-10 mm according to the delta D and t1The included angle theta between the folded edge and the thickness middle plane of the first through hole (33) can be obtained.
5. A cartridge-style orifice-type damping seal with a flanged damping orifice adapted for bi-directional rotation as set forth in claim 4 wherein: the thickness of the inner liner (3) is 0.05-1.0 mm; the thickness of the middle layer (2) is 0.05-12.0 mm; the thickness of the bottom surface (12) of the outer layer (1) is 1.5-8.0 mm.
6. A cartridge-style orifice-type damping seal with a flanged damping orifice adapted for bi-directional rotation as set forth in claim 5, wherein: the thickness range of inner liner (3) is 0.05 ~ 0.25mm, intermediate level (2) thickness range is 0.5 ~ 4.5mm, the thickness range of bottom surface (12) of outer (1) is 2.5 ~ 5.0 mm.
7. A cartridge-style orifice-type damping seal with a flanged damping orifice adapted for bi-directional rotation as set forth in claim 1, wherein: the first through hole (33) is shaped so as to be selected from one of the following: circular hole, raindrop hole, oval hole, hexagonal hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910871543.3A CN110578558A (en) | 2019-10-22 | 2019-10-22 | packaging type hole type damping seal with edge folding damping type holes and suitable for bidirectional rotation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910871543.3A CN110578558A (en) | 2019-10-22 | 2019-10-22 | packaging type hole type damping seal with edge folding damping type holes and suitable for bidirectional rotation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110578558A true CN110578558A (en) | 2019-12-17 |
Family
ID=68811329
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910871543.3A Pending CN110578558A (en) | 2019-10-22 | 2019-10-22 | packaging type hole type damping seal with edge folding damping type holes and suitable for bidirectional rotation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110578558A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113775762A (en) * | 2021-08-25 | 2021-12-10 | 浙江工业大学 | Hole-type damping sealing structure with dovetail diversion trenches |
| CN113775763A (en) * | 2021-08-25 | 2021-12-10 | 浙江工业大学 | Split type air bag supporting hole type damping seal with variable hole depth |
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| CN101725375A (en) * | 2009-12-25 | 2010-06-09 | 北京化工大学 | Turbomachinery explosion-proof low-leakage damping aluminum honeycomb seal |
| CN201972955U (en) * | 2011-04-13 | 2011-09-14 | 大连理工大学 | Dynamic and static clearance wedge groove arc sealing structure for nuclear main pump |
| CN110056531A (en) * | 2019-04-29 | 2019-07-26 | 珠海格力节能环保制冷技术研究中心有限公司 | Divide valve floating ring, shaft sealing device, compressor and air conditioner |
| CN210829406U (en) * | 2019-10-22 | 2020-06-23 | 浙江工业大学 | Packaging type hole type damping seal with edge folding damping type holes and suitable for bidirectional rotation |
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2019
- 2019-10-22 CN CN201910871543.3A patent/CN110578558A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1920261A (en) * | 2005-08-22 | 2007-02-28 | 通用电气公司 | Axially adjustable sealing ring |
| CN101725375A (en) * | 2009-12-25 | 2010-06-09 | 北京化工大学 | Turbomachinery explosion-proof low-leakage damping aluminum honeycomb seal |
| CN201972955U (en) * | 2011-04-13 | 2011-09-14 | 大连理工大学 | Dynamic and static clearance wedge groove arc sealing structure for nuclear main pump |
| CN110056531A (en) * | 2019-04-29 | 2019-07-26 | 珠海格力节能环保制冷技术研究中心有限公司 | Divide valve floating ring, shaft sealing device, compressor and air conditioner |
| CN210829406U (en) * | 2019-10-22 | 2020-06-23 | 浙江工业大学 | Packaging type hole type damping seal with edge folding damping type holes and suitable for bidirectional rotation |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113775762A (en) * | 2021-08-25 | 2021-12-10 | 浙江工业大学 | Hole-type damping sealing structure with dovetail diversion trenches |
| CN113775763A (en) * | 2021-08-25 | 2021-12-10 | 浙江工业大学 | Split type air bag supporting hole type damping seal with variable hole depth |
| CN113775763B (en) * | 2021-08-25 | 2024-03-26 | 浙江工业大学 | Hole depth variable split type air bag supporting hole type damping seal |
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