CN112196631A - Labyrinth sealing structure - Google Patents
Labyrinth sealing structure Download PDFInfo
- Publication number
- CN112196631A CN112196631A CN202011063866.9A CN202011063866A CN112196631A CN 112196631 A CN112196631 A CN 112196631A CN 202011063866 A CN202011063866 A CN 202011063866A CN 112196631 A CN112196631 A CN 112196631A
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- China
- Prior art keywords
- labyrinth
- sealing
- gap
- engine
- seal
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- 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
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- 238000007789 sealing Methods 0.000 title claims abstract description 111
- 238000000576 coating method Methods 0.000 claims description 11
- 239000011248 coating agent Substances 0.000 claims description 10
- 239000007770 graphite material Substances 0.000 claims description 2
- 239000000463 material Substances 0.000 claims description 2
- 230000002035 prolonged effect Effects 0.000 abstract description 4
- 244000126211 Hericium coralloides Species 0.000 description 4
- 238000000465 moulding Methods 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 2
- 239000011247 coating layer Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 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
- 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
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
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- 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 application provides a labyrinth sealing structure, which belongs to the technical field of aero-engines and comprises a labyrinth sealing structure; the end part of the rotor is provided with a plurality of grid teeth; the sealing ring is arranged at a position, opposite to the labyrinth, of the stator, the sealing ring is provided with a plurality of sealing areas, the number of the sealing areas is the same as that of the labyrinth, each sealing area comprises a first molded surface and a second molded surface, the thickness of each sealing ring is reduced from large to small, the first molded surfaces are used for being matched with the labyrinth of the engine in a cold state to form a first labyrinth gap, and the second molded surfaces are used for being matched with the labyrinth after axial movement to form a second labyrinth gap. The labyrinth seal structure can enable the labyrinth seal to have different sealing gaps when the engine is in different working states, and improves the sealing performance of the labyrinth in a low state; meanwhile, the sealing area has a certain profile structure, so that the air circulation resistance of the sealing of the labyrinth can be further increased, the sealing performance of the labyrinth is improved, and the service life of the sealing of the labyrinth is prolonged.
Description
Technical Field
The application belongs to the technical field of aeroengines, and particularly relates to a labyrinth sealing structure.
Background
The labyrinth seal is an effective non-contact seal structure with long service life widely used on an aeroengine, and a common labyrinth seal structure is shown in figure 1. The labyrinth seal structure comprises a stator 10 and a rotor 20, the end part of the rotor 20 is provided with a labyrinth 21, a seal ring 11 is arranged in the stator 10, and the seal ring 11 and the labyrinth 21 form a sealing structure. Compared with a contact type seal, the leakage rate of the grid tooth seal is large, the theoretical leakage rate of the grid tooth seal is in direct proportion to a grid tooth gap (a grid tooth and a seal ring interval), and the grid tooth gap control is a main design criterion of the grid tooth seal.
In order to reduce sealing leakage, the smaller the comb tooth gap is, the better the comb tooth gap is, but because the comb tooth gap is influenced by factors such as accumulated tolerance, power deflection deformation and thermal deformation, and meanwhile, in order to ensure that the engine can still work normally and stably under the high-power and high-altitude state, a larger cold-state gap value is designed according to the factors in the existing design of the comb tooth gap. The cold clearance value can ensure that the base body of the engine is not abraded in a high state, but the clearance value causes larger clearance of the labyrinth compared with a low state such as slow turning of the engine, and the like, thereby causing larger leakage amount of the labyrinth in the low state and reducing the performance of the engine.
Disclosure of Invention
The present application is directed to a labyrinth seal structure that solves or reduces at least one of the problems set forth above.
In one aspect, the technical solution provided by the present application is: a labyrinth sealing structure comprises a labyrinth sealing structure body;
the end part of the rotor is provided with a plurality of grid teeth;
the sealing ring is arranged at the position, relative to the labyrinth, of the stator, the sealing ring is provided with a plurality of sealing areas, the number of the sealing areas is the same as that of the labyrinth, the sealing areas comprise a first molded surface and a second molded surface, the thickness of the sealing ring is reduced from large to small, the first molded surface is used for being matched with the labyrinth of the engine in a cold state to form a first labyrinth gap, and the second molded surface is used for being matched with the labyrinth after axial movement to form a second labyrinth gap.
In an embodiment of the application, the first profile is an inclined surface, and the inclined surface gradually reduces the thickness of the sealing ring in the axial shifting direction of the labyrinth.
In an embodiment of the present application, the second profile is a straight section, the straight section being parallel to the engine axial direction.
In one embodiment of the present application, the sealing ring is made of graphite material.
In an embodiment of the present application, the first labyrinth gap is smaller than the second labyrinth gap.
On the other hand, the technical scheme provided by the application is as follows: a labyrinth sealing structure comprises a labyrinth sealing structure body;
the end part of the rotor is provided with a plurality of grid teeth;
the sealing device comprises a stator, wherein a sealing coating is arranged on the stator relative to the labyrinth, the sealing coating is provided with a plurality of sealing areas with the same number as the labyrinth, each sealing area comprises a first molded surface and a second molded surface, the thickness of each sealing ring is reduced from the large thickness to the small thickness, the first molded surfaces are used for being matched with the labyrinth of an engine in a cold state to form a first labyrinth gap, and the second molded surfaces are used for being matched with the labyrinth after axial movement to form a second labyrinth gap.
In an embodiment of the application, the first profile is an inclined surface, and the inclined surface gradually reduces the thickness of the sealing ring in the axial shifting direction of the labyrinth.
In an embodiment of the present application, the second profile is a straight section, the straight section being parallel to the engine axial direction.
In one embodiment of the present application, the seal coating is coated with a wear resistant material.
In an embodiment of the present application, the first labyrinth gap is smaller than the second labyrinth gap.
According to the labyrinth seal structure, the certain profile surface structure is designed on the sealing ring matched with the labyrinth, so that different sealing gaps can be generated when the labyrinth seal is in different working states of an engine, and the sealing performance of the labyrinth in a low state is improved; meanwhile, the sealing area has a certain profile structure, so that the air circulation resistance of the sealing of the labyrinth can be further increased, the sealing performance of the labyrinth is improved, and the service life of the sealing of the labyrinth is prolonged.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
Fig. 1 is a schematic view of a labyrinth sealing structure in the prior art.
Fig. 2 is a schematic view of a labyrinth sealing structure of the present application.
Fig. 3 is a schematic view of a sealing area of the present application.
Fig. 4 is a schematic diagram of the relative position of the labyrinth sealing structure after axial play.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
The problem pointed out in the background art is solved, namely the problem that the grid tooth clearance is set by adopting a cold clearance value with a fixed value, so that the grid tooth clearance is too large in a low state, and the performance of an engine is further influenced. The application provides a labyrinth seal structure, through design certain profile on the ring of obturating relative with the labyrinth, can make the labyrinth seal have different clearance of obturating when the engine is in different operating condition, the performance of obturating of labyrinth when improving the little state. Meanwhile, the abradable coating has a certain profile structure, so that the air circulation resistance of the labyrinth seal can be further increased, the labyrinth seal performance is improved, and the service life of the labyrinth seal is prolonged.
As shown in fig. 2, the labyrinth sealing structure provided by the application mainly comprises a stator 30 and a rotor 40, a labyrinth 41 is arranged on the end surface of the rotor 40, a sealing ring 31 which can be matched with the labyrinth 41 is arranged at a corresponding position of the stator 30, wherein the end surface of the sealing ring 31 matched with the labyrinth 41 is provided with sealing areas with special configurations, the number of the sealing areas is the same as that of the labyrinth 41, and each sealing area is sealed with the corresponding labyrinth 41.
As shown in fig. 3, the sealing region includes a first molding surface 311 and a second region 312, and the thickness of the sealing ring at the first molding surface 311 is greater than that at the second molding surface 312. When the engine is in a cold state (the engine is not started) or a low state (the engine is in a low rotating speed, such as a slow-moving state), the grate teeth 41 and the first profile 311 are matched and sealed, and the gap between the grate teeth is the first grate tooth gap. The engine is in a high state (the engine is in a high rotating speed, the grate 41 and the second profile 312 are matched and sealed, and the gap between the two is the second grate gap.
The first profile 311 is an inclined surface, and an included angle with the end surface 313 of the sealing ring 31 on the side close to the labyrinth 41 is formed, and the first profile and the end surface form a triangular notch, so that the thickness of the sealing ring 31 from left to right is gradually reduced, and the direction is the axial moving direction of the labyrinth 41 of the rotor 40.
The second profile 312 is a straight section that is connected to the end of the first profile 311 (in the direction of the comb play). The straight section is parallel to the axis of the engine, and forms a rectangular gap with the end surface 313 of the sealing unit 31 close to one side of the grate 41, and the rectangular gap can accommodate the grate 41.
The first grid clearance formed by the grid 41 and the first molded surface 311 is smaller than the second grid clearance formed by the grid 41 and the second molded surface 312.
When the engine is in a low state, the relative position of the labyrinth 41 on the rotor 40 and the sealing ring 31 on the stator 30 is just in the position of the first profile 311, and the labyrinth clearance is H1 with a smaller value, as shown in FIG. 2. Because the rotor power deflection deformation, the thermal deformation and the like are relatively small when the engine is in a low state, the deformation of the clearance value of the grate teeth in the state is small, the grate teeth and the lining base body can not be subjected to collision and abrasion, and the use safety is ensured. For the traditional labyrinth sealing design, because the sealing rings have the same thickness, the labyrinth clearance needs to ensure the safe operation of the engine in the full state, and therefore, the corresponding labyrinth clearance is larger than the labyrinth clearance H1 in the application.
When the engine is in the high state, the rotor will generate a certain axial leap, and assuming that the rotor 40 leaps in the direction a relative to the stator 30, the changed position of the top end of the labyrinth 41 relative to the obturating ring 31 is at the second profile 312, as shown in fig. 4. At the moment, the labyrinth gap is changed from H1 to H2, and the enlarged labyrinth gap H2 can ensure that the labyrinth sealing structure still can reliably work under the high state and influenced by the factors such as dynamic deflection deformation, thermal deformation and the like, and the use safety of an engine cannot be influenced.
It should be noted that, because different rotor axial bouncing amounts correspond to different operating states of the engine, the size of the labyrinth seal gap may also be changed correspondingly with the change of the engine state.
In the above embodiment, the stator 30 is provided with the sealing ring 31, and in other embodiments, the sealing ring 31 may also be a sealing coating layer coated on the stator 30. The sealing area of the sealing coating refers to the arrangement of the sealing ring 31, which is not described in detail herein.
According to the labyrinth sealing structure, the profiles with different thicknesses are designed on the matching surface of the sealing ring, so that the clearance formed by the profiles and the labyrinth can change the labyrinth sealing clearance along with different working states of an engine, the labyrinth clearance value of the engine in a low state can be reduced, the sealing capability of the labyrinth sealing structure in the low state is improved, and the performance of the engine in the low state is ensured.
Compared with the prior art, the application has the following effects:
1) the traditional design method that the sealing rings or the sealing coatings in the labyrinth sealing structure are the same in thickness and the gap value of the labyrinth is always fixed is changed, so that the labyrinth seal can be adjusted according to different working states of the aero-engine to correspond to different sealing gaps. When the engine is in a low state, the corresponding small clearance can effectively improve the sealing performance of the labyrinth; when the engine enters a high state, the axial position of the stator relative to the rotor changes, the thickness of the sealing ring correspondingly changes, the labyrinth is positioned in a larger sealing gap, and the use safety of the high-state labyrinth can be ensured.
2) The sealing ring or the sealing coating is designed into a profile structure with non-uniform thickness, so that the air circulation resistance of the sealing of the labyrinth can be further increased, and the sealing performance of the labyrinth is improved; meanwhile, the sealing clearance of the labyrinth tooth can change along with the change of the state of the engine, so that the loss of the sealing ring or the sealing coating is reduced, the performance reduction caused by the abrasion of the sealing ring is reduced, and the service life of the labyrinth tooth is prolonged.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A labyrinth sealing structure is characterized by comprising a labyrinth sealing structure body;
the end part of the rotor is provided with a plurality of grid teeth;
the sealing ring is arranged at the position, relative to the labyrinth, of the stator, the sealing ring is provided with a plurality of sealing areas, the number of the sealing areas is the same as that of the labyrinth, the sealing areas comprise a first molded surface and a second molded surface, the thickness of the sealing ring is reduced from large to small, the first molded surface is used for being matched with the labyrinth of the engine in a cold state to form a first labyrinth gap, and the second molded surface is used for being matched with the labyrinth after axial movement to form a second labyrinth gap.
2. The labyrinth seal structure as claimed in claim 1, wherein the first profile is a bevel which causes the thickness of the seal ring in the axial float direction of the labyrinth to gradually decrease.
3. The labyrinth seal of claim 1, wherein the second profile is a straight section, the straight section being parallel to the axial direction of the engine.
4. The labyrinth seal of claim 1, wherein the seal ring is made of graphite material.
5. The labyrinth sealing structure as claimed in claim 1, wherein the first labyrinth gap is smaller than the second labyrinth gap.
6. A labyrinth sealing structure is characterized by comprising a labyrinth sealing structure body;
the end part of the rotor is provided with a plurality of grid teeth;
the sealing device comprises a stator, wherein a sealing coating is arranged on the stator relative to the labyrinth, the sealing coating is provided with a plurality of sealing areas with the same number as the labyrinth, each sealing area comprises a first molded surface and a second molded surface, the thickness of each sealing ring is reduced from the large thickness to the small thickness, the first molded surfaces are used for being matched with the labyrinth of an engine in a cold state to form a first labyrinth gap, and the second molded surfaces are used for being matched with the labyrinth after axial movement to form a second labyrinth gap.
7. The labyrinth sealing structure as claimed in claim 6, wherein the first profile is a slope, and the slope gradually reduces the thickness of the sealing ring in the axial shifting direction of the labyrinth.
8. The labyrinth sealing structure as claimed in claim 6, wherein the second profile is a straight section parallel to the axial direction of the engine.
9. The labyrinth seal structure as claimed in claim 6, wherein the seal coating is coated with a wear resistant material.
10. The labyrinth sealing structure as claimed in claim 6, wherein the first labyrinth gap is smaller than the second labyrinth gap.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011063866.9A CN112196631A (en) | 2020-09-30 | 2020-09-30 | Labyrinth sealing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011063866.9A CN112196631A (en) | 2020-09-30 | 2020-09-30 | Labyrinth sealing structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112196631A true CN112196631A (en) | 2021-01-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011063866.9A Pending CN112196631A (en) | 2020-09-30 | 2020-09-30 | Labyrinth sealing structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112196631A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113653803A (en) * | 2021-08-11 | 2021-11-16 | 中国联合重型燃气轮机技术有限公司 | Shaft seal structure and gas turbine with same |
| CN113928721A (en) * | 2021-09-24 | 2022-01-14 | 中国航发沈阳发动机研究所 | Protecting jacket for blades and comb teeth of aero-engine |
| CN114017134A (en) * | 2021-11-12 | 2022-02-08 | 中国航发沈阳发动机研究所 | Method for adjusting thermal deformation rate of casing by changing thermal capacity of casing |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110156359A1 (en) * | 2009-12-31 | 2011-06-30 | General Electric Company | Turbine engine seals |
| US20110250073A1 (en) * | 2010-04-08 | 2011-10-13 | Sudhakar Neeli | Rotor and assembly for reducing leakage flow |
| CN104895624A (en) * | 2015-05-07 | 2015-09-09 | 中国航空工业集团公司沈阳发动机设计研究所 | Comb tooth sealing structure |
| CN109505665A (en) * | 2018-12-26 | 2019-03-22 | 北京航空航天大学 | A kind of densification device based on aero-engine seal pan axial force negative feedback control |
| CN208831046U (en) * | 2018-08-14 | 2019-05-07 | 中国航发商用航空发动机有限责任公司 | Step comb tooth for gas turbines |
-
2020
- 2020-09-30 CN CN202011063866.9A patent/CN112196631A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110156359A1 (en) * | 2009-12-31 | 2011-06-30 | General Electric Company | Turbine engine seals |
| US20110250073A1 (en) * | 2010-04-08 | 2011-10-13 | Sudhakar Neeli | Rotor and assembly for reducing leakage flow |
| CN104895624A (en) * | 2015-05-07 | 2015-09-09 | 中国航空工业集团公司沈阳发动机设计研究所 | Comb tooth sealing structure |
| CN208831046U (en) * | 2018-08-14 | 2019-05-07 | 中国航发商用航空发动机有限责任公司 | Step comb tooth for gas turbines |
| CN109505665A (en) * | 2018-12-26 | 2019-03-22 | 北京航空航天大学 | A kind of densification device based on aero-engine seal pan axial force negative feedback control |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113653803A (en) * | 2021-08-11 | 2021-11-16 | 中国联合重型燃气轮机技术有限公司 | Shaft seal structure and gas turbine with same |
| CN113653803B (en) * | 2021-08-11 | 2024-06-11 | 中国联合重型燃气轮机技术有限公司 | Shaft seal structure and gas turbine with same |
| CN113928721A (en) * | 2021-09-24 | 2022-01-14 | 中国航发沈阳发动机研究所 | Protecting jacket for blades and comb teeth of aero-engine |
| CN113928721B (en) * | 2021-09-24 | 2022-11-22 | 中国航发沈阳发动机研究所 | Protecting jacket for blades and comb teeth of aero-engine |
| CN114017134A (en) * | 2021-11-12 | 2022-02-08 | 中国航发沈阳发动机研究所 | Method for adjusting thermal deformation rate of casing by changing thermal capacity of casing |
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Application publication date: 20210108 |