CN112012801A - Tooth point hook type labyrinth seal structure - Google Patents
Tooth point hook type labyrinth seal structure Download PDFInfo
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- CN112012801A CN112012801A CN202010988301.5A CN202010988301A CN112012801A CN 112012801 A CN112012801 A CN 112012801A CN 202010988301 A CN202010988301 A CN 202010988301A CN 112012801 A CN112012801 A CN 112012801A
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- labyrinth
- tooth
- sealing
- tooth tip
- seal structure
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- 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
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- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a tooth point hook type labyrinth sealing structure which comprises a sealing lining, a rotating shaft matched with the sealing lining and a labyrinth distributed on the rotating shaft, wherein the bottom of the labyrinth linearly shrinks towards a high radius direction, and a tooth point at the top is provided with an arc section inclined to form a hook shape. The labyrinth type labyrinth seal structure changes the tooth tip structure of the labyrinth seal, and compared with the conventional labyrinth seal structure, the labyrinth type labyrinth seal structure can reduce the leakage amount under the same working condition of an aero-engine due to the change of the shape of the tooth tip; and when the clearance is increased due to the change of the engine state, the vortex formed at the tooth tip is correspondingly increased, so that the increase of the actual circulation clearance is smaller than that of the physical clearance, the increase of the leakage amount can be inhibited, negative feedback is formed, and the sensitivity of the labyrinth to the clearance change is reduced.
Description
Technical Field
The invention belongs to the technical field of non-contact type rotating-static system sealing of an aero-engine, and particularly relates to a tooth tip hook type labyrinth sealing structure.
Background
Aircraft engines are the heart of aircraft and play a decisive role in aircraft performance. With the development of the modern aviation industry, the requirements of safety, reliability, maintainability and service life of an aero-engine are increasingly raised, so that the requirements of high performance of the aero-engine are urgently needed to be improved, the temperature and pressure ratio in the engine is gradually increased, the leakage of an internal flow system is increasingly serious, and the tight performance directly influences the working performance of the aero-engine, such as fuel consumption rate, flight cost, thrust-weight ratio and the like. In order to reduce leakage loss and improve the overall performance of the engine, it is important to improve the original sealing device at many positions. Domestic and foreign research shows that half of the improvement of the performance of the future aeroengine depends on the improvement of the sealing technology and the reduction of the leakage amount. Therefore, the requirement of people on a high-performance sealing structure is more and more urgent, and the improvement and development of a new sealing device have important practical value and significance for reducing the oil consumption rate and improving the efficiency of an engine.
The labyrinth seal is widely used in aeroengines as a non-contact seal structure. The labyrinth seal mainly utilizes sudden expansion and sudden contraction of a flow passage, the kinetic energy of consumed fluid is increased to increase flow resistance to limit fluid leakage, in an engine, the loss of useful energy caused by excessive leakage must be minimized to improve the effectiveness of the whole system, and the seal technical research shows that the labyrinth seal has the characteristics of high cost-benefit ratio, relatively low research and development cost, simplicity in manufacture, low maintenance cost and the like, and the improvement of the labyrinth seal performance has a remarkable effect on reducing leakage and improving the performance of the engine.
The existing modification on the sealing labyrinth structure mainly aims at the following parameters: the sealing performance of the grate obtained by the improvements on the throttling clearance, the tooth pitch, the tooth height, the tooth top thickness, the tooth number and the tooth inclination angle cannot be greatly broken through; and other special-shaped grates, such as patent of multi-bending reverse S-shaped grate aeroengine sealing structure with publication number CN106150702B and patent of publication number CN106089323A, an aeroengine grate sealing structure adopting bending windward acute-angle-shaped teeth, have good sealing effect, but in practical application, because the grate is too bent and the width of the teeth is too narrow, the problem of strength can be caused in the high-speed rotation and high-temperature environment of the aeroengine, and the special-shaped grates cannot be practically applied to the aeroengine.
Disclosure of Invention
In order to solve the problems, the invention aims to reduce the leakage amount of the labyrinth by changing the flow direction of the fluid at the tooth tip to generate the vortex at the tooth tip and increasing the range and the strength of the vortex so as to strengthen the local loss of the tooth tip and the vortex dissipation and pneumatically reducing the actual flow gap of the fluid at the tooth tip.
The invention aims to provide a tooth tip hook type labyrinth seal structure which comprises a seal lining, a rotating shaft matched with the seal lining and a labyrinth distributed on the rotating shaft, wherein the bottom of the labyrinth linearly shrinks towards a high radius direction, and a tooth tip at the top is provided with an arc section inclined to form a hook shape.
The labyrinth sealing structure provided by the invention can also have the characteristics that the matching surface of the sealing bush and the rotating shaft is provided with a step, the rotating shaft is provided with a plurality of labyrinth teeth, a labyrinth tooth cavity is formed between two adjacent labyrinth teeth, and a sealing cavity is formed between the top end of each labyrinth tooth and the top wall of the sealing bush.
The labyrinth sealing structure provided by the invention can also have the characteristic that the labyrinth is divided into a straight section and a circular section along the radial direction.
The labyrinth sealing structure provided by the invention can also have the characteristic that the height H of the straight-line section is 2.5-3.5 mm.
The labyrinth sealing structure provided by the invention can also have the characteristic that the radius R of the circular arc section is 1-2 mm.
The labyrinth sealing structure provided by the invention can also have the characteristic that the width T of the tooth top of the labyrinth is 0.5-1 mm.
The labyrinth sealing structure provided by the invention can also have the characteristic that the bend angle a of the other side of the tooth tip corresponding to the circular arc section is 150-180 degrees.
The labyrinth sealing structure provided by the invention can also have the characteristics that the size of the labyrinth tooth tip is H/R of 2.1, T is 0.8mm, and a is 170 degrees. Compared with the prior art, the invention has the following beneficial effects:
the labyrinth type labyrinth seal structure changes the tooth tip structure of the labyrinth seal, and compared with the conventional labyrinth seal structure, the labyrinth type labyrinth seal structure can reduce the leakage amount under the same working condition of an aero-engine due to the change of the shape of the tooth tip; and when the clearance is increased due to the change of the engine state, the vortex formed at the tooth tip is correspondingly increased, so that the increase of the actual circulation clearance is smaller than that of the physical clearance, the increase of the leakage amount can be inhibited, negative feedback is formed, and the sensitivity of the labyrinth to the clearance change is reduced. The invention only changes the tooth tip structure of the sealed labyrinth, reserves the tooth root and the middle part of the conventional tooth, and does not generate the problem of insufficient strength in the high rotating speed and high temperature environment of the aeroengine.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1: the axial section of the tooth tip hook type labyrinth seal structure;
FIG. 2: the tooth point structure of the tooth point hook type labyrinth seal structure is axially cut off;
FIG. 3: a tooth tip flowing schematic diagram of a conventional labyrinth sealing structure;
FIG. 4: a tooth tip flowing schematic diagram of a tooth tip hook type labyrinth seal structure; and
FIG. 5: the tooth tip hook type labyrinth seal structure is shown schematically.
Wherein: 1: a first sealed cavity; 2: the first tooth point hook type labyrinth seal structure tooth point; 3: a second sealed cavity; 4: the second tooth point hook type labyrinth seal structure tooth point; 5: a third sealing cavity; 6: the third tooth point hook type labyrinth seal structure tooth point; 7: a fourth sealed cavity; 8: a fourth tooth point hook type labyrinth seal structure tooth point; 9: a fifth sealed cavity; 10: a fifth tooth point hook type labyrinth seal structure tooth point; 11: sealing the bushing; 12: a rotating shaft; 13: conventional teeth are available.
Detailed Description
In order to make the technical means, the creation features, the achievement purposes and the effects of the invention easy to understand, the following embodiments specifically describe the tooth tip hook type labyrinth seal structure provided by the invention with reference to the accompanying drawings.
In the description of the embodiments of the present invention, it should be understood that the terms "central", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only used for convenience in describing and simplifying the description of the present invention, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to a number of indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified.
The terms "mounted," "connected," and "coupled" are to be construed broadly and may, for example, be fixedly coupled, detachably coupled, or integrally coupled; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art through specific situations.
As shown in fig. 1 to 5, the invention provides a tooth point hook type labyrinth sealing structure, which comprises a sealing bush, a rotating shaft matched with the sealing bush and a labyrinth distributed on the rotating shaft, wherein the bottom of the labyrinth linearly shrinks towards a high radius direction, and a tooth point at the top is provided with an arc section inclined to form a hook shape. The sealing bush is provided with a step on the matching surface with the rotating shaft, the rotating shaft is provided with a plurality of labyrinth teeth, a labyrinth tooth cavity is formed between every two adjacent labyrinth teeth, and a sealing cavity is formed between the top end of each labyrinth tooth and the top wall of the sealing bush.
In the working process, the arc section of the tooth tip is arranged on the windward side, a labyrinth tooth cavity is formed between the finger tips of two adjacent stages of labyrinth teeth, an interdental gap is formed between the top end of the labyrinth and the top wall of the sealing bush, when fluid flows to the tooth tip 10 of the fifth labyrinth sealing structure along the tooth tip 2 of the first labyrinth sealing structure, the fluid is confined by the first sealing cavity 1, the second sealing cavity 3, the third sealing cavity 5, the fourth sealing cavity 7 and the fifth sealing cavity 9 and flows along the tooth tip 2 of the first labyrinth sealing structure, the tooth tip 4 of the second labyrinth sealing structure, the tooth tip 6 of the third labyrinth sealing structure, the tooth tip 8 of the fourth labyrinth sealing structure and the tooth tip 10 of the fifth labyrinth sealing structure, the fluid is forced to move along the circular arc and drops on the windward side of the tooth tip, and the fluid forms vortex at the tooth tip after dropping, so that on one hand, strong vortex dissipation is caused, the kinetic energy of the fluid is consumed, and on the other hand, due to the existence of the vortex at the tooth tip, the actual circulation gap of the fluid passing through the tooth tip is reduced in the aspect of aerodynamics, and the leakage amount is reduced. Compared with the conventional tooth 13, the tooth tip windward hook type labyrinth seal structure provided by the invention has the advantage that the leakage amount is reduced by 14% under the same boundary condition compared with the conventional tooth 13.
In some embodiments of the invention, the grate is divided into a straight section and a circular section along the radial direction. In some embodiments of the present invention, the height H of the straight line segment is 2.5-3.5 mm. The radius R of the circular arc section is 1-2 mm. The width T of the tooth tip at the top of the grid tooth is 0.5-1 mm. The bent angle a of the other side of the tooth tip corresponding to the arc section is 150-180 degrees. Wherein a is the bent angle of the leeward side of the tooth tip of the comb tooth. In some embodiments of the invention, the dimension of the grid tooth tip is H/R is 2.1, T is 0.8mm, and a is 170 degrees.
In some embodiments of the invention, the tooth tip hook type labyrinth seal structure can also be applied to seal structures such as straight lines, inclined teeth and the like.
When the gap of the grate is changed, the sensitivity to the change of the gap is lower, the stability is good, and the strength of the grate is the same as that of a conventional grate.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention. The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (8)
1. The labyrinth sealing structure is characterized by comprising a sealing bush, a rotating shaft matched with the sealing bush and a labyrinth distributed on the rotating shaft, wherein the bottom of the labyrinth linearly shrinks towards a high radius direction, and a top tooth point is provided with an arc section inclined to form a hook shape.
2. The labyrinth sealing structure as claimed in claim 1, wherein the sealing bush has a step on the matching surface with the rotating shaft, the rotating shaft is provided with a plurality of labyrinth teeth, a labyrinth tooth cavity is formed between two adjacent labyrinth teeth, and a sealing cavity is formed between the top end of the labyrinth tooth and the top wall of the sealing bush.
3. The tooth tip hook type labyrinth sealing structure as claimed in claim 2, wherein the labyrinth is divided into a straight section and a circular section in a radial direction.
4. The tooth tip hook type labyrinth seal structure as claimed in claim 3, wherein the height H of the straight line section is 2.5-3.5 mm.
5. The labyrinth seal structure of the tooth point hook type as claimed in claim 4, wherein the radius R of the circular arc section is 1-2 mm.
6. The labyrinth seal structure of the tooth tip hook type as claimed in claim 5, wherein the width T of the tooth tip at the top of the labyrinth is 0.5-1 mm.
7. The labyrinth seal structure of the tooth point hook type as claimed in claim 6, wherein the bend angle a of the other side of the tooth point corresponding to the circular arc section is 150-180 °.
8. The labyrinth seal structure of the tooth tip hook type as claimed in claim 7, wherein the dimension of the tooth tip of the labyrinth is H/R of 2.1, T of 0.8mm, and a is 170 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010988301.5A CN112012801A (en) | 2020-09-18 | 2020-09-18 | Tooth point hook type labyrinth seal structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010988301.5A CN112012801A (en) | 2020-09-18 | 2020-09-18 | Tooth point hook type labyrinth seal structure |
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| Publication Number | Publication Date |
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| CN112012801A true CN112012801A (en) | 2020-12-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010988301.5A Pending CN112012801A (en) | 2020-09-18 | 2020-09-18 | Tooth point hook type labyrinth seal structure |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113685234A (en) * | 2021-08-31 | 2021-11-23 | 北京航空航天大学 | Labyrinth sealing device based on hedging principle |
| CN113685233A (en) * | 2021-08-31 | 2021-11-23 | 北京航空航天大学 | Labyrinth sealing device based on clearance reverse compensation |
| CN116150893A (en) * | 2023-04-19 | 2023-05-23 | 北京航空航天大学 | Design method of aero-engine comb tooth sealing mechanism and comb tooth sealing mechanism |
| CN116663157A (en) * | 2023-07-25 | 2023-08-29 | 中国航发四川燃气涡轮研究院 | Method for analyzing invalid air leakage of aero-engine and restraining device |
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| JP2001200937A (en) * | 2000-01-17 | 2001-07-27 | Mitsubishi Heavy Ind Ltd | Active seal of rotating machine |
| CN102322529A (en) * | 2010-05-11 | 2012-01-18 | 通用电气公司 | Crooked labyrinth seal |
| US20130149118A1 (en) * | 2011-07-04 | 2013-06-13 | Alstom Technology Ltd. | Labyrinth seals |
| CN106089323A (en) * | 2016-05-23 | 2016-11-09 | 南京航空航天大学 | A kind of use the aero-engine labyrinth gas seals structure bending acute angle type tooth windward |
| CN106150702A (en) * | 2016-09-06 | 2016-11-23 | 南京航空航天大学 | How the aero-engine of curved anti-S type comb tooth is obturaged 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 |
-
2020
- 2020-09-18 CN CN202010988301.5A patent/CN112012801A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001200937A (en) * | 2000-01-17 | 2001-07-27 | Mitsubishi Heavy Ind Ltd | Active seal of rotating machine |
| CN102322529A (en) * | 2010-05-11 | 2012-01-18 | 通用电气公司 | Crooked labyrinth seal |
| US20130149118A1 (en) * | 2011-07-04 | 2013-06-13 | Alstom Technology Ltd. | Labyrinth seals |
| CN106089323A (en) * | 2016-05-23 | 2016-11-09 | 南京航空航天大学 | A kind of use the aero-engine labyrinth gas seals structure bending acute angle type tooth windward |
| CN106150702A (en) * | 2016-09-06 | 2016-11-23 | 南京航空航天大学 | How the aero-engine of curved anti-S type comb tooth is obturaged 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 |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113685234A (en) * | 2021-08-31 | 2021-11-23 | 北京航空航天大学 | Labyrinth sealing device based on hedging principle |
| CN113685233A (en) * | 2021-08-31 | 2021-11-23 | 北京航空航天大学 | Labyrinth sealing device based on clearance reverse compensation |
| CN113685234B (en) * | 2021-08-31 | 2022-08-09 | 北京航空航天大学 | Labyrinth sealing device based on hedging principle |
| CN116150893A (en) * | 2023-04-19 | 2023-05-23 | 北京航空航天大学 | Design method of aero-engine comb tooth sealing mechanism and comb tooth sealing mechanism |
| CN116150893B (en) * | 2023-04-19 | 2023-06-16 | 北京航空航天大学 | Design method of aero-engine comb tooth sealing mechanism and comb tooth sealing mechanism |
| CN116663157A (en) * | 2023-07-25 | 2023-08-29 | 中国航发四川燃气涡轮研究院 | Method for analyzing invalid air leakage of aero-engine and restraining device |
| CN116663157B (en) * | 2023-07-25 | 2023-10-03 | 中国航发四川燃气涡轮研究院 | Method for analyzing invalid air leakage of aero-engine and restraining device |
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Application publication date: 20201201 |