CN112065511B - Injection type honeycomb bush-labyrinth sealing structure - Google Patents
Injection type honeycomb bush-labyrinth sealing structure Download PDFInfo
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- CN112065511B CN112065511B CN202010895490.1A CN202010895490A CN112065511B CN 112065511 B CN112065511 B CN 112065511B CN 202010895490 A CN202010895490 A CN 202010895490A CN 112065511 B CN112065511 B CN 112065511B
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- honeycomb
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- labyrinth
- injection hole
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- 238000002347 injection Methods 0.000 title claims abstract description 99
- 239000007924 injection Substances 0.000 title claims abstract description 99
- 238000007789 sealing Methods 0.000 title claims abstract description 34
- 238000003466 welding Methods 0.000 claims description 4
- 230000007704 transition Effects 0.000 claims description 3
- 239000012530 fluid Substances 0.000 abstract description 4
- 210000002421 cell wall Anatomy 0.000 description 3
- 208000002925 dental caries Diseases 0.000 description 3
- 238000004804 winding Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000002401 inhibitory effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
Images
Classifications
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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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- 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
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
- F01D11/06—Control thereof
-
- 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
- F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
Abstract
The invention discloses an injection type honeycomb bushing-labyrinth sealing structure which comprises a rotating shaft and a honeycomb bushing, wherein the honeycomb bushing is coaxially sleeved on the rotating shaft, an airflow channel is arranged between the honeycomb bushing and the rotating shaft, a plurality of annular sealing labyrinth arranged in an axial spaced mode are arranged on the rotating shaft, an axial injection flow channel is formed in the outer side surface of the honeycomb bushing, high-pressure gas is introduced from a sealing inlet at the front end of the injection flow channel, an injection hole is formed in the honeycomb base surface of a honeycomb cavity corresponding to a tooth tip and is communicated with the injection flow channel, the high-pressure gas is injected into the honeycomb cavity from the injection flow channel, a high-pressure area is formed in the honeycomb cavity, and deflection and streaming of tooth tip jet flow in the honeycomb grid are suppressed. According to the invention, through the injection type airflow auxiliary system, the flow structure of the honeycomb-labyrinth seal is improved, and the purpose of reducing the fluid leakage is achieved.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to an injection type honeycomb bushing-labyrinth sealing structure.
Background
In a rotating machine such as an aircraft engine, a certain gap is left between a rotating rotor part and a stator bushing, so that gas leaks between the rotating and static parts, the leakage flow can cause the flow of main flow to be reduced, the efficiency of the engine is reduced, and even the problems of blade vibration, deformation and the like can be caused, and the performance and the service life of the engine are influenced. The labyrinth seal is a non-contact dynamic seal structure which is simple in structure and reliable in performance and is applied to rotary machinery such as an aircraft engine. The special combined structure of the grid tooth and the sealing ring surface is utilized, the kinetic energy of the fluid is consumed, the flow resistance is increased, and the fluid leakage is finally reduced.
Along with the improvement of the cycle parameters of the aircraft engine, the leakage problem of a sealing system of the engine is increasingly prominent, the working condition of the labyrinth sealing is increasingly severe, and a series of problems of reduced structural rigidity, low sealing efficiency, rotor fluid excitation and the like are faced. For the traditional labyrinth seal, in order to reduce the seal leakage, the seal clearance needs to be reduced except for improving the geometric structure of the labyrinth. If the sealing gap is too large, leakage is increased, which is not beneficial to improving the efficiency of the engine. However, if the clearance is too small, the rotation of the rotor can cause the tooth tips and the stator bushing to be scraped, the service life of the engine is shortened, and even danger is generated.
Compared with the traditional labyrinth sealing, the honeycomb bushing-labyrinth combined sealing structure has good sealing characteristic and rotor dynamic characteristic, and can reduce the running clearance under the condition of ensuring the normal and stable work of an engine. The special hexagonal structure of the honeycomb can cause huge friction loss to tooth cavity jet flow, and dense high-energy vortex is generated in the honeycomb lattice, so that the flow loss is increased, and the leakage is reduced. The larger the honeycomb diameter, the more the honeycomb liner is damaging and obstructing the tooth cavity jet flow. However, at the point of the tooth tip, the honeycomb structure increases the effective gap of the tooth tip, and induces the jet of the tooth tip to pass through the gap of the tooth tip in a deflection bypass mode, which greatly increases the leakage amount of the sealing, and the deflection effect is more obvious particularly when the diameter of the honeycomb is large.
Disclosure of Invention
The invention aims to solve the problems in the background art, fully utilize the performance of a honeycomb bushing and provide a novel injection type honeycomb bushing-labyrinth sealing structure.
In order to achieve the technical purpose, the technical scheme adopted by the invention is as follows:
injection type honeycomb bush-labyrinth structure of obturating, including pivot and honeycomb bush, the coaxial cover of honeycomb bush is established in the pivot, and with the pivot between have airflow channel, the high-pressure gas of the entry of obturating can get into and flow to the export of obturating along airflow channel axial, the interior anchor ring of honeycomb bush comprises a plurality of honeycomb chambers, be provided with the annular labyrinth of obturating of a plurality of axial interval arrangements in the pivot, the prong evagination of the labyrinth of obturating stretches into airflow channel, be close to but contactless honeycomb bush interior anchor ring, wherein: the outer side surface of the honeycomb bushing is provided with an axial injection flow channel, high-pressure gas is introduced from a sealed inlet at the front end of the injection flow channel, an injection hole is formed in the honeycomb base surface of the honeycomb cavity corresponding to the tooth tip and is communicated with the injection flow channel, the high-pressure gas is injected into the honeycomb cavity from the injection flow channel, a high-pressure area is formed in the honeycomb cavity, and deflection and flow deflection of tooth tip jet flow in the honeycomb grid are suppressed.
In order to optimize the technical scheme, the specific measures adopted further comprise:
the injection flow passage reduces the size of the cross section of the flow passage of the injection flow passage by arranging the necking area at the corresponding part of the injection hole, thereby changing the pressure of high-pressure gas injected into the honeycomb cavity and enabling the high-pressure area formed in the honeycomb cavity to be only slightly higher than the impact force of deflection and streaming of tooth tip jet flow in the honeycomb grid.
The cross-sectional areas of the different necking areas are sequentially reduced along the axial direction, and the apertures of the different injection holes are sequentially reduced along the axial direction.
And one end of the injection hole, which is positioned on the base surface of the honeycomb, is arranged to be in fillet transition.
The inclined elastic piece is additionally arranged at one end, located on the honeycomb base surface, of the injection hole, one end of the inclined elastic piece is fixed on the honeycomb base surface, the other end of the inclined elastic piece is a free end, the inclined elastic piece inclines towards the straight line direction where the axis of the injection hole is located, and air flow sprayed from the injection hole impacts the inclined elastic piece to enable the inclined elastic piece to vibrate.
Two inclined elastic pieces are arranged on each injection hole and are symmetrically arranged on two sides of the injection hole, and free ends of the two inclined elastic pieces are close to each other but are not in contact with each other.
Flexible trapezoidal elastic pieces are respectively additionally arranged on the front side and the rear side of the tooth tip, and the shape of each trapezoidal elastic piece is matched with the opening shape of the honeycomb cell wall surface corresponding to the tooth tip.
The trapezoidal elastic sheet is fixedly connected with the tooth tip through welding.
The length of the neck-down region is equal to the diameter of the corresponding honeycomb cavity.
The invention has the following advantages:
1. the invention provides a novel injection honeycomb bushing-labyrinth sealing structure capable of effectively inhibiting leakage, wherein a tapered flow passage is arranged above a honeycomb bushing, high-pressure gas is introduced from the front end of a sealing inlet, an injection hole is formed in the surface of a honeycomb substrate corresponding to a tooth tip and is connected with an injection flow passage, the high-pressure gas is injected into a honeycomb cavity from the injection flow passage, a high-pressure area is formed in the honeycomb cavity, the deflection and the streaming of tooth tip jet flow in a honeycomb lattice are suppressed, and the pressure of an outlet of the injection hole is slightly higher than the pressure of jet flow in a tooth tip gap by controlling the diameter of the necking area of the injection flow passage, so that the deflection and the streaming of jet flow at the tooth tip are inhibited, and meanwhile, the jet hole airflow is not enough to flow out of the honeycomb lattice, thereby greatly reducing the leakage amount of honeycomb labyrinth sealing.
2. The invention utilizes the high pressure in front of the sealed inlet to provide energy for the injection system, and controls the injection quantity of each hole to balance the pressure of the injection flow passage and the air flow passage, thereby forming the self-adaptive injection system without external energy supply, and having simple and practical structure.
3. In consideration of gradual reduction of the sealing pressure of the labyrinth, the cross-sectional area of the necking area is sequentially reduced along the axial direction, and the aperture of the injection hole is sequentially reduced along the axial direction, so that the pressure of the outlet of the injection hole can correspond to the pressure of jet flow in the gap between the tooth tips.
4. And the round angle excess treatment is carried out at the outlet of the injection hole, so that the strength of jet flow of the injection hole is weakened, and the jet flow of the injection hole is prevented from penetrating through a vortex in the honeycomb grid.
5. Two inclined elastic pieces are additionally arranged on two sides of the outlet of the injection hole to limit the pressure of the outlet of the injection hole. Meanwhile, the energy of the injection holes is utilized to enable the inclined elastic pieces to vibrate, and disturbance and mixing in the honeycomb grids are increased.
6. Flexible trapezoidal shell fragment is respectively installed additional to both sides around the prong, further prevents to draw the jet hole efflux to flow out honeycomb check, and on the other hand restricts the deflection that the efflux is here and flows by turns, reduces leakage quantity. Meanwhile, the trapezoidal elastic sheet forms vibration waves by utilizing the energy of residual deflection airflow at the tooth tip, so that the fluctuation of jet flow at the tooth cavity position is enhanced, and the dissipation is enhanced.
Drawings
FIG. 1 is a schematic view of a conventional honeycomb bushing-labyrinth seal in use;
FIG. 2 is a schematic view of an injection honeycomb bushing-labyrinth seal structure of the present invention;
FIG. 3 is a schematic view of the injection type honeycomb bushing-labyrinth sealing structure according to the present invention in use;
FIG. 4 is a schematic view of the installation of the trapezoidal spring;
fig. 5 is a schematic structural view of the inclined spring.
The label names in the figure: the device comprises a rotating shaft 1, a honeycomb bushing 2, a honeycomb cavity 2a, an inclined elastic sheet 21, a sealing labyrinth 3, a tooth tip 31, a trapezoidal elastic sheet 32, an airflow channel 4, an injection flow channel 5, an injection hole 51 and a necking area 52.
Detailed Description
Embodiments of the present invention are described in further detail below with reference to the accompanying drawings.
The injection type honeycomb bush-labyrinth seals structure of this embodiment, including pivot 1 and honeycomb bush 2, the coaxial cover of honeycomb bush 2 is established in pivot 1, and with pivot 1 between have airflow channel 4, the high-pressure gas of the entry of obturating can get into and along the export of obturating of 4 axial flow direction of airflow channel, the interior anchor ring of honeycomb bush 2 comprises a plurality of honeycomb chamber 2a, be provided with the annular of a plurality of axial interval arrangements in the pivot 1 and obturate the labyrinth 3, the prong 31 evagination of obturate the labyrinth 3 stretches into airflow channel 4, be close to but contactless honeycomb bush 2 interior anchor ring, wherein: the outer side surface of the honeycomb lining 2 is provided with an axial injection flow channel 5, high-pressure gas is introduced from a sealing inlet at the front end of the injection flow channel 5, an injection hole 51 is formed in the honeycomb base surface of the honeycomb cavity 2a corresponding to the tooth tip 31, the injection hole 51 is communicated with the injection flow channel 5, the high-pressure gas is injected into the honeycomb cavity 2a from the injection flow channel 5, a high-pressure area is formed in the honeycomb cavity 2a, and deflection and flow winding of tooth tip jet flow in the honeycomb grid are suppressed.
In the embodiment, the injection flow passage 5 is provided with the necking area 52 at the corresponding position of the injection hole 51, so that the size of the cross section of the flow passage of the injection flow passage 5 is reduced, the pressure of high-pressure gas injected into the honeycomb cavity 2a is changed, and the high-pressure area formed in the honeycomb cavity 2a is only slightly higher than the impact force of deflection and flow winding of tooth tip jet flow in the honeycomb lattice.
In the embodiment, the cross-sectional areas of the different necking zones 52 are sequentially reduced along the axial direction, and the bore diameters of the different injection holes 51 are sequentially reduced along the axial direction.
In the embodiment, one end of the injection hole 51 on the base surface of the honeycomb is set to be in a fillet transition.
In the embodiment, the inclined elastic sheet 21 is additionally arranged at one end, located on the honeycomb base surface, of the injection hole 51, one end of the inclined elastic sheet 21 is fixed on the honeycomb base surface, the other end of the inclined elastic sheet 21 is a free end, the inclined elastic sheet 21 is inclined towards the straight line direction where the axis of the injection hole 51 is located, and airflow sprayed from the injection hole 51 impacts the inclined elastic sheet 21 to enable the inclined elastic sheet 21 to vibrate.
In the embodiment, two inclined elastic pieces 21 are installed on each injection hole 51, the two inclined elastic pieces 21 are symmetrically located on two sides of the injection hole 51, and the free ends of the two inclined elastic pieces 21 are close to each other but do not contact each other.
In the embodiment, flexible trapezoidal elastic pieces 32 are respectively additionally arranged on the front side and the rear side of the tooth tip 31, and the shape of each trapezoidal elastic piece 32 is matched with the shape of the opening of the honeycomb cell wall corresponding to the tooth tip 31.
In the embodiment, the trapezoidal elastic sheet 32 is fixedly connected with the tooth tip 31 by welding.
In an embodiment, the length of the constricted region 52 is equal to the diameter of the corresponding honeycomb cavity 2 a.
In the embodiment, as shown in fig. 2-3, an injection flow channel 5 is formed above the basal surface of the honeycomb cavity 2a, and the height of the flow channel is about the depth of the honeycomb cavity 2a, which is a sealing structure of the three-stage labyrinth-honeycomb bushing. The runner guides air from the front end of the sealing inlet and exhausts air from the rear end of the sealing outlet.
A circular injection hole 51 is formed in the honeycomb base surface corresponding to the tooth point 31, the circular injection hole 51 is connected with the upper injection flow channel 5, the outlet of the injection hole 51 is rounded, the tooth points of different stages correspond to the injection holes 51 of different diameters, the diameter of the injection hole 51 in the honeycomb cavity 2a corresponding to the tooth point of the third stage is the smallest, and the diameter of the injection hole 51 in the honeycomb cavity 2a corresponding to the tooth point of the first stage is the largest.
The injection flow passage 5 is of a special tapered structure, the height of the flow passage is about one half of the depth of the honeycomb cavity 2a, the length of the necking area 52 is equal to the diameter of the honeycomb cavity 2a, and the contraction angle is 45 degrees.
The tooth tip 31 is provided with a trapezoidal flexible elastic sheet which is connected with the tooth tip 31 in a welding mode. The spring plate is overlapped with the honeycomb cell wall surface in the top view direction, as shown in fig. 4.
The above is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above-mentioned embodiments, and all technical solutions belonging to the idea of the present invention belong to the protection scope of the present invention. It should be noted that modifications and embellishments within the scope of the invention may be made by those skilled in the art without departing from the principle of the invention.
Claims (8)
1. Injection type honeycomb bush-labyrinth seals structure, including pivot (1) and honeycomb bush (2), honeycomb bush (2) coaxial cover establish on pivot (1), and with pivot (1) between have airflow channel (4), the high-pressure gas of the entry of obturating can get into and along airflow channel (4) axial flow direction export of obturating, the interior anchor ring of honeycomb bush (2) constitute by a plurality of honeycomb chamber (2a), be provided with annular labyrinth (3) that seal that a plurality of axial interval arranged on pivot (1), prong (31) evagination of obturating labyrinth (3) stretch into airflow channel (4), be close to but not contact honeycomb bush (2) interior anchor ring, characterized by: an axial injection flow channel (5) is formed in the outer side surface of the honeycomb lining (2), high-pressure gas is introduced from a sealing inlet at the front end of the injection flow channel (5), an injection hole (51) is formed in the honeycomb base surface of the honeycomb cavity (2a) corresponding to the tooth tip (31), the injection hole (51) is communicated with the injection flow channel (5), the high-pressure gas is injected into the honeycomb cavity (2a) from the injection flow channel (5), a high-pressure area is formed in the honeycomb cavity (2a), and deflection and streaming of tooth tip jet flow in the honeycomb grid are suppressed; the injection flow channel (5) reduces the size of the cross section of the flow channel of the injection flow channel (5) at the corresponding position of the injection hole (51) by arranging a necking area (52), so that the pressure of high-pressure gas injected into the honeycomb cavity (2a) is changed, and the high-pressure area formed in the honeycomb cavity (2a) is only slightly higher than the impact force of deflection and flow bypassing of tooth tip jet flow in the honeycomb lattice.
2. The injection type honeycomb bushing-labyrinth sealing structure according to claim 1, characterized in that: the cross-sectional areas of the different necking areas (52) are sequentially reduced along the axial direction, and the hole diameters of the different injection holes (51) are sequentially reduced along the axial direction.
3. The injection type honeycomb bushing-labyrinth sealing structure according to claim 2, characterized in that: one end of the injection hole (51) positioned on the base surface of the honeycomb is set to be in fillet transition.
4. The injection type honeycomb bushing-labyrinth sealing structure according to claim 3, characterized in that: the inclined elastic sheet (21) is additionally arranged at one end, located on the honeycomb base surface, of the injection hole (51), one end of the inclined elastic sheet (21) is fixed on the honeycomb base surface, the other end of the inclined elastic sheet is a free end, the inclined elastic sheet (21) inclines towards the straight line direction where the axis of the injection hole (51) is located, and airflow sprayed from the injection hole (51) impacts the inclined elastic sheet (21) to enable the inclined elastic sheet (21) to vibrate.
5. The injection type honeycomb bushing-labyrinth sealing structure according to claim 4, characterized in that: two inclined elastic pieces (21) are installed on each injection hole (51), the two inclined elastic pieces (21) are symmetrically located on two sides of each injection hole (51), and free ends of the two inclined elastic pieces (21) are close to each other but are not in contact with each other.
6. The injection type honeycomb bushing-labyrinth sealing structure according to claim 5, characterized in that: flexible trapezoidal shrapnel (32) are respectively installed additional to both sides around prong (31), trapezoidal shrapnel (32) shape and this prong (31) correspond the opening shape of the honeycomb check wall face suit.
7. The injection type honeycomb bushing-labyrinth sealing structure as claimed in claim 6, wherein: the trapezoidal elastic sheet (32) is fixedly connected with the tooth tip (31) through welding.
8. The injection type honeycomb bushing-labyrinth sealing structure according to claim 7, characterized in that: the length of the necking area (52) is equal to the diameter of the corresponding honeycomb cavity (2 a).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010895490.1A CN112065511B (en) | 2020-08-31 | 2020-08-31 | Injection type honeycomb bush-labyrinth sealing structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010895490.1A CN112065511B (en) | 2020-08-31 | 2020-08-31 | Injection type honeycomb bush-labyrinth sealing structure |
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| CN112065511A CN112065511A (en) | 2020-12-11 |
| CN112065511B true CN112065511B (en) | 2021-10-26 |
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| CN202010895490.1A Active CN112065511B (en) | 2020-08-31 | 2020-08-31 | Injection type honeycomb bush-labyrinth sealing structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113944517B (en) * | 2021-11-10 | 2023-12-19 | 北京动力机械研究所 | Rotor sealing structure of local supercharged radial-flow turbocharging system |
| CN114151142B (en) * | 2021-11-11 | 2023-09-01 | 中国联合重型燃气轮机技术有限公司 | Seal assembly and gas turbine |
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| EP0176447A1 (en) * | 1984-09-27 | 1986-04-02 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Apparatus for the automatic control of the play of a labyrinth seal of a turbo machine |
| JP2005163693A (en) * | 2003-12-04 | 2005-06-23 | Ishikawajima Harima Heavy Ind Co Ltd | Sealing device, casing for gas turbine engine and stationary blade segment for gas turbine engine |
| 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 |
| CN106949245A (en) * | 2017-03-07 | 2017-07-14 | 西安交通大学 | It is a kind of from spin-ended convergence type rotary seal structure |
| CN110546349A (en) * | 2017-04-24 | 2019-12-06 | 赛峰航空器发动机 | Device for sealing between a rotor and a stator of a turbine engine |
| CN111140289A (en) * | 2019-12-20 | 2020-05-12 | 南京航空航天大学 | Reduce labyrinth device of obturating of gas invasion volume |
| CN111271134A (en) * | 2020-03-16 | 2020-06-12 | 南京航空航天大学 | Honeycomb-labyrinth sealing structure |
| CN111457102A (en) * | 2020-05-25 | 2020-07-28 | 西安西热节能技术有限公司 | Air-resistance type sealing structure and working method |
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2020
- 2020-08-31 CN CN202010895490.1A patent/CN112065511B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0176447A1 (en) * | 1984-09-27 | 1986-04-02 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Apparatus for the automatic control of the play of a labyrinth seal of a turbo machine |
| JP2005163693A (en) * | 2003-12-04 | 2005-06-23 | Ishikawajima Harima Heavy Ind Co Ltd | Sealing device, casing for gas turbine engine and stationary blade segment for gas turbine engine |
| 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 |
| CN106949245A (en) * | 2017-03-07 | 2017-07-14 | 西安交通大学 | It is a kind of from spin-ended convergence type rotary seal structure |
| CN110546349A (en) * | 2017-04-24 | 2019-12-06 | 赛峰航空器发动机 | Device for sealing between a rotor and a stator of a turbine engine |
| CN111140289A (en) * | 2019-12-20 | 2020-05-12 | 南京航空航天大学 | Reduce labyrinth device of obturating of gas invasion volume |
| CN111271134A (en) * | 2020-03-16 | 2020-06-12 | 南京航空航天大学 | Honeycomb-labyrinth sealing structure |
| CN111457102A (en) * | 2020-05-25 | 2020-07-28 | 西安西热节能技术有限公司 | Air-resistance type sealing structure and working method |
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| CN112065511A (en) | 2020-12-11 |
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