CN114991883B - Radial multilayer brush silk brush formula seal structure - Google Patents
Radial multilayer brush silk brush formula seal structure Download PDFInfo
- Publication number
- CN114991883B CN114991883B CN202210574132.XA CN202210574132A CN114991883B CN 114991883 B CN114991883 B CN 114991883B CN 202210574132 A CN202210574132 A CN 202210574132A CN 114991883 B CN114991883 B CN 114991883B
- Authority
- CN
- China
- Prior art keywords
- brush
- wire
- layer
- clamping plate
- annular
- Prior art date
- 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.)
- Active
Links
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
- F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/28—Arrangement of seals
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Sealing Devices (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a brush type sealing structure of radial multi-layer brush wires, which structurally comprises inner and outer layer brush wires, wherein the brush wires have a certain interference quantity and generate elastic force to resist rigidifying effect and hysteresis effect caused by friction force between the brush wires and a rear baffle plate. The air entering the sealing gap flows along the wall surface of the stator, and then flows along the wall surface direction of the rear clamping plate after being blocked by the rear clamping plate, so that radial closing force and thrust are generated, the friction between the brush wires and the rear clamping plate is overcome, and a pressure chamber is formed in the brush wires of the inner layer by the air, so that the internal and external pressure difference is reduced, and the deformation is reduced. The other strand of the air flows out from the gap between the rear clamping plate and the rotor along the axial direction near the wall surface of the rotor, and the tensile force and the elastic force of the brush wires generated by the fixation of the front section of the brush wires and the blocking of the brush wires of the inner layer counteract part of the axial aerodynamic force of the air flow, so that the axial deformation of the brush wires is limited. The sealing structure plays roles of a damper, reducing friction, low hysteresis, reducing actual leakage clearance and reducing the axial size of the sealing device.
Description
Technical Field
The invention belongs to the field of brush type sealing, and relates to a brush type sealing structure, in particular to a radial multi-layer brush type sealing structure which is applied between a rotor and a stator of an impeller rotary machine such as an aeroengine, a gas turbine or a steam turbine and reduces actual leakage clearance by utilizing brush wire deformation.
Background
Brush seal technology has been widely used as a substitute for labyrinth seals in aircraft engines, gas turbines, and steam turbines, and single stage brush seals have proven inadequate for achieving the desired sealing effect, and therefore multi-stage seals are often employed. At present, the multistage brush type seal is mainly of a cantilever structure and is arranged in axial multistage, and the pressure of each stage of brush wires is sequentially reduced. Research shows that the pressure drop in the multi-stage brush wires mainly occurs in the brush wires of the last stage, and the deformation of the brush wires of the last stage can not be effectively restrained when the total pressure drop is larger. The friction between the brush filaments and the rear splint produces stiffening and hysteresis effects. When the rotating shaft is eccentric or the load between the rotating shaft and the brush wire changes, the brush wire cannot immediately follow or recover.
Disclosure of Invention
First, the present invention solves the problems
The invention aims to provide a brush type sealing structure of radial multi-layer brush wires, which aims to reduce the axial size of a sealing device, reduce the actual gap between the rotating stator and a rotor and reduce air leakage and improve the closing effect by adopting the radial multi-layer brush wires, fixing two ends of each layer of brush wires on the sealing device, connecting the front and rear stages of the multi-stage brush wires, reducing the axial size of the sealing device by utilizing the space between the multi-stage brush wires, overcoming leakage flow aerodynamic force by utilizing fixed points and brush wire elastic force, reducing deformation and friction and enhancing the closing effect by utilizing the space between the multi-stage brush wires and reducing the axial size of the sealing device and utilizing the fixed points and the brush wire elastic force.
(II) the technical proposal adopted by the invention for solving the technical problems
A radial multi-layer brush type sealing structure for the space between rotor and stator of rotary vane machine is composed of an annular front clamping plate, an annular middle clamping plate, an annular back clamping plate and multi-layer brush wires,
an annular first wire brushing groove plate is fixedly arranged between the front clamping plate and the middle clamping plate, an annular second wire brushing groove plate is fixedly arranged between the rear clamping plate and the middle clamping plate, and annular protrusions which are basically positioned in the middle in the axial direction are respectively arranged on the inner walls of the first wire brushing groove plate and the second wire brushing groove plate;
the multi-layer annular brush wire comprises an annular outer brush wire layer and an annular inner brush wire layer which is positioned in the outer brush wire layer in the radial direction, the cross sections of the outer brush wire layer and the inner brush wire layer are approximately U-shaped, wherein,
the front axial fixed point of each brush wire in the outer brush wire layer is clamped and fixed in an annular groove formed between the annular bulge of the first brush wire groove plate and the front clamping plate, and the rear axial fixed point of each brush wire in the outer brush wire layer is clamped and fixed in an annular groove formed between the annular bulge of the second brush wire groove plate and the rear clamping plate;
the front axial fixing point of each brush wire in the inner brush wire layer is clamped and fixed in an annular groove formed between the annular protrusion of the first brush wire groove plate and the middle clamping plate, and the rear axial fixing point of each brush wire in the inner brush wire layer is clamped and fixed in an annular groove formed between the annular protrusion of the second brush wire groove plate and the middle clamping plate.
According to the radial multi-layer brush wire brush type sealing structure for the rotor and the stator of the impeller rotary machine, the brush wires with the two fixed ends are adopted in the radial direction, so that the brush wires are connected in the front and rear stages, the space between the brush wires at each stage is fully utilized, and the axial size of the sealing device is reduced. The brush silk both ends are fixed on the stator, are equivalent to the two-stage brush silk front and back level and link to each other, and the brush silk front end is fixed to front splint and intermediate lamella, and the brush silk rear end is fixed to intermediate lamella and backplate, has utilized the space between the multistage brush silk of tradition, reduces sealing device axial dimension.
Preferably, each brush wire in the outer brush wire layer and the inner brush wire layer is uniformly distributed in a circumferential dislocation mode, and a circumferential dislocation angle beta exists between the front fixed point and the rear fixed point of each brush wire in the axial direction so as to effectively absorb circumferential deflection caused by rotor movement.
Further, the circumferential dislocation angle beta is between 0 and 60 degrees.
Further, the brush filaments in the outer and inner brush filament layers are mounted at different circumferential offset angles β.
Preferably, the connecting line between the front and rear fixed points of each wire brushing shaft is called a wire brushing string, a circumferential crossing angle gamma exists between the wire brushing string of the outer wire brushing layer and the wire brushing string of the inner wire brushing layer, and the circumferential crossing angle gamma is between 0 and 90 degrees.
Preferably, the outer brush wire layer adopts thick brush wires, and the inner brush wire layer adopts thin brush wires. The outer brush silk layer adopts thick brush silk for bear the eccentric pressure that brings with rotatory of rotor, interior brush silk layer adopts thin brush silk for play the repair effect to the clearance of outer brush silk, interior brush silk in situ forms the pressure chamber, and the inlayer is contactless with the rotor, and the offset is little, thereby the inlayer can reduce outer axial deflection, and the contact of the outer first half of inlayer can make brush silk combine inseparabler, makes deformation for beneficial deformation.
Preferably, the top surfaces of the annular protrusions on the inner walls of the first wire brushing groove plate and the second wire brushing groove plate are basically kept flush with the inner wall mounting surfaces of the front clamping plate, the middle clamping plate and the rear clamping plate on the left side and the right side of the first wire brushing groove plate and the second wire brushing groove plate.
Preferably, the inner wall of the rear clamping plate is also provided with an annular bulge for guiding air flow, so that the rear clamping plate has the effect of guiding air flow besides clamping the brush wires.
In the radial multi-layer brush wire brush type sealing structure used between the rotor and the stator of the impeller rotating machine, brush wires have a certain interference quantity, and elastic force is generated to resist rigidization effect and hysteresis effect caused by friction force between the brush wires and the rear baffle plate. The gas entering the sealing gap is regarded as two streams, one stream of gas moves along the wall surface of the stator after meeting the blocking of the rear clamping plate along the wall surface direction of the rear clamping plate, radial closing force and thrust are generated, the friction between the brush wires and the rear clamping plate is overcome, and the air forms a pressure chamber inside the brush wires at the inner layer, so that the pressure difference between the inside and the outside is reduced, and the deformation is reduced. The other air flows out through the gap between the rear clamping plate and the rotor along the axial direction near the wall surface of the rotor, and the tensile force and the elastic force of the brush wires generated by the fixation of the front section of the brush wires and the blocking of the brush wires of the inner layer counteract part of the axial aerodynamic force of the air flow, so that the axial deformation of the brush wires is limited. By the mode, the sealing device plays roles of a damper, reducing friction, reducing hysteresis, reducing actual leakage clearance and reducing the axial size of the sealing device.
The invention relates to a radial multi-layer wire brushing type sealing structure used between a rotor and a stator of an impeller rotary machine, which has the working principle that: the brush type seal adopts radial multi-layer brush wires, both ends of each layer of brush wires are fixed on the sealing device, and the tensile force generated by the fixed points and the elastic force of the brush wires weaken the axial aerodynamic force of air flow and prevent the axial deformation. Therefore, the friction force between the brush wires and the rear baffle is reduced, and rigidization effect and hysteresis effect are effectively inhibited. Meanwhile, the brush filaments are arranged more tightly under the action of the tensile force. In the radial direction, the elastic force of the brush wire plays a role in spring damping when the rotor is eccentric, so that the rotating shaft can follow the rotating shaft in time when the rotating shaft is deformed, the blowing-closing effect is enhanced, and the actual gap is reduced. The brush wires are distributed in radial multiple layers, the inner layer and the outer layer are crossed, thick brush wires are used at the outer layer to help absorb circumferential deflection caused by rotor movement, thin brush wires are used at the inner layer, a gap between the outer layer brush wires is subjected to a stitching effect, actual gaps are reduced, and radial thrust is provided.
(III) compared with the prior art, the invention has obvious technical effects
According to the radial multi-layer brush wire brush type sealing structure for the impeller rotary machine rotor and the stator, the axial aerodynamic force is restrained through the tensile force and the elastic force generated by the brush wire mounting structure, the brush wires are not excessively deformed, so that the axial deformation and the radial deformation are beneficial deformation, friction between the brush wires and the rear baffle is reduced, rigidization effect and hysteresis effect are effectively restrained, space is fully utilized in the axial direction to reduce the axial size of the sealing device, and the layered structure of the brush wires in the radial direction plays a role in spring damping and gap supplementing.
Drawings
FIG. 1 is a schematic illustration in partial cross-section of a radial multi-layer brush seal structure for use between a rotor and stator of an impeller rotating machine of the present invention in a free state;
FIG. 2 is a schematic diagram of the radial multi-layer brush seal structure of the present invention in operation between a rotor and stator of an impeller rotating machine;
FIG. 3 is a schematic view of circumferential misalignment angle in a radial multi-layer brush seal structure for use between a rotor and stator of an impeller rotating machine of the present invention;
FIG. 4 is an axial schematic view of a radial multi-layer brush seal structure for use between a rotor and stator of an impeller rotating machine of the present invention;
FIG. 5 is a schematic radial cross-sectional view of a radial multi-layer brush seal structure for use between a rotor and stator of an impeller rotating machine of the present invention;
FIG. 6 is an axial schematic view of the inner and outer arrangement of the radial multi-layer brush seal structure for use between the rotor and stator of an impeller rotating machine of the present invention;
reference numerals illustrate:
front splint 1, middle splint 2, back splint 3, outer brush silk layer 4, interior brush silk layer 5, brush silk frid 6.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention become more apparent, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are intended to be illustrative of the invention and should not be construed as limiting the invention in any way. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in fig. 1-6, the radial multi-layer brush type sealing structure for the rotor and stator of the impeller rotary machine is used for reducing the axial size of a sealing device, reducing the actual gap between the stator and rotor of the impeller rotary machine (such as an aero-engine, a gas turbine or a steam turbine and the like) and reducing the air leakage. The invention relates to a radial multi-layer wire brushing brush type sealing structure used between a rotor and a stator of an impeller rotary machine, which comprises an annular front clamping plate 1, an annular middle clamping plate 2, an annular rear baffle plate 3, an outer wire brushing layer 4 and an inner wire brushing layer 5 which are fixedly arranged on a stator part and are arranged along the axial direction front and back.
An annular first wire brushing groove plate 6 is fixedly arranged between the front clamping plate 1 and the middle clamping plate 2, an annular second wire brushing groove plate 6 is fixedly arranged between the rear clamping plate 3 and the middle clamping plate 2, and annular bulges which are basically positioned in the middle in the axial direction are respectively arranged on the inner walls of the first wire brushing groove plate 6 and the second wire brushing groove plate 6; the annular inner wire brushing layer 5 is positioned inside the outer wire brushing layer 4 in the radial direction, and the cross sections of the outer wire brushing layer 4 and the inner wire brushing layer 5 are approximately U-shaped.
The front axial fixed point of each brush wire in the outer brush wire layer 4 is clamped and fixed in an annular groove formed between the annular bulge of the first brush wire groove plate 6 and the front clamping plate 1, and the rear axial fixed point of each brush wire in the outer brush wire layer 4 is clamped and fixed in an annular groove formed between the annular bulge of the second brush wire groove plate 6 and the rear clamping plate 3; the front axial fixing point of each brush wire in the inner brush wire layer 5 is clamped and fixed in an annular groove formed between the annular bulge of the first brush wire groove plate 6 and the middle clamping plate 2, and the rear axial fixing point of each brush wire in the inner brush wire layer 5 is clamped and fixed in an annular groove formed between the annular bulge of the second brush wire groove plate 6 and the middle clamping plate 2.
The invention relates to a radial multi-layer brush type sealing structure used between a rotor and a stator of an impeller rotary machine, which has the working principle that: the outer wire brushing layer 4 and the inner wire brushing layer 5 are circumferentially and uniformly distributed on the wire brushing groove plate 6, and the front end and the rear end of the axial direction of the brush wires are respectively fixed by the front clamping plate 1, the middle clamping plate 2 and the rear baffle plate 3. Compared with the traditional axial multistage brush type seal, the axial dimension of the sealing device is reduced by fully utilizing the space between the multistage brush wires. The connecting line of the front fixed point and the rear fixed point of the brush wire is called a string, and the connecting line is uniformly distributed on the sealing ring in a circumferential dislocation mode, an dislocation angle beta exists, the dislocation angle beta is between 0 and 60 degrees, and circumferential deflection caused by rotor movement is effectively absorbed. The inner-stage brush wires and the outer-stage brush wires are installed at different dislocation angles beta, the strings of the two-stage brush wires have an intersection angle gamma, and the intersection angle gamma is between 0 and 90 degrees. The outer stage adopts thick brush wires, bears the pressure caused by rotor eccentricity and friction generated by rotation, and the inner stage adopts thin brush wires, so that the gap between the outer stage brush wires is repaired.
The radial multi-layer brush wire brush type sealing structure for the impeller rotating machinery rotor and the stator can be regarded as two air flows flowing through the sealing transposition, one air flow flows along the wall surface of the stator, flows along the radial direction of the wall surface of the stator when encountering the rear baffle, turns to pass through the outlet, flows out of the outlet together with the axial air flow, and forms a pressure cavity in the inner layer brush wire, the inner layer brush wire is not contacted with the rotor, the circumferential offset is small, and the overall deformation is small. The radial flow generates thrust to the brush wires, and can overcome the friction between the rear baffle and the brush wires. The other air flow flows to the gap outlet along the wall surface of the rotor through the brush wires to generate axial aerodynamic force, the air flow enables the brush wires to generate axial deformation, the brush wires are restrained by the tensile force of the fixed point and the elastic force of the brush wires and blocked by the brush wires at the inner layer, the brush wires are restrained from deforming, and the inner layer brush wires and the outer layer brush wires are in closer contact under the action of the restrained deformation. In addition, as the deformation is reduced, the friction between the brush wire and the rear baffle is reduced, the low hysteresis effect is achieved, the actual leakage gap of the brush wire is reduced, and the spring damping effect is formed on the vibration of the rotor.
The foregoing has shown and described the basic principles, principal features and advantages of the invention. It will be appreciated by those skilled in the art that the present invention is not limited by the foregoing examples, which are described in the foregoing specification merely illustrative of the principles of the invention. The present invention is subject to various changes and modifications without departing from the spirit and scope thereof, and such changes and modifications fall within the scope of the invention as hereinafter claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
The present invention is not described in detail in part as being well known to those skilled in the art.
Claims (4)
1. A radial multi-layer brush type sealing structure for the space between rotor and stator of rotary vane machine is composed of an annular front clamping plate, an annular middle clamping plate, an annular back clamping plate and multi-layer brush wires,
an annular first wire brushing groove plate is fixedly arranged between the front clamping plate and the middle clamping plate, an annular second wire brushing groove plate is fixedly arranged between the rear clamping plate and the middle clamping plate, and annular protrusions which are basically positioned in the middle in the axial direction are respectively arranged on the inner walls of the first wire brushing groove plate and the second wire brushing groove plate;
the multi-layer annular brush wire comprises an annular outer brush wire layer and an annular inner brush wire layer which is positioned in the outer brush wire layer in the radial direction, the cross sections of the outer brush wire layer and the inner brush wire layer are approximately U-shaped, wherein,
the front axial fixed point of each brush wire in the outer brush wire layer is clamped and fixed in an annular groove formed between the annular bulge of the first brush wire groove plate and the front clamping plate, and the rear axial fixed point of each brush wire in the outer brush wire layer is clamped and fixed in an annular groove formed between the annular bulge of the second brush wire groove plate and the rear clamping plate;
the front axial fixing point of each brush wire in the inner brush wire layer is clamped and fixed in an annular groove formed between the annular bulge of the first brush wire groove plate and the middle clamping plate, and the rear axial fixing point of each brush wire in the inner brush wire layer is clamped and fixed in an annular groove formed between the annular bulge of the second brush wire groove plate and the middle clamping plate;
each brush wire in the outer brush wire layer and the inner brush wire layer is uniformly distributed in a circumferential dislocation mode, and a circumferential dislocation angle exists between the front fixed point and the rear fixed point of each brush wire in the axial directionβThe circumferential offset angleβThe brush filaments in the outer brush filament layer and the inner brush filament layer are installed at different circumferential dislocation angles beta;
the connecting line between the front and rear fixed points of each brush wire in the axial direction is called a brush wire string, and a circumferential crossing angle exists between the brush wire string of the outer brush wire layer and the brush wire string of the inner brush wire layerγThe circumferential crossing angleγBetween 0 DEG and 90 deg.
2. The radial multi-layer brush seal of claim 1 wherein the outer brush filaments are thick and the inner brush filaments are thin.
3. The radial multi-layered wire brush seal structure according to claim 1, wherein the top surfaces of the annular protrusions on the inner walls of the first wire brush groove plate and the second wire brush groove plate are substantially flush with the inner wall mounting surfaces of the front clamping plate, the middle clamping plate and the rear clamping plate on the left and right sides thereof.
4. The radial multi-layer brush type seal structure according to claim 1, wherein an annular protrusion for guiding air flow is further provided on an inner wall of the rear clamping plate, so that the rear clamping plate has an effect of guiding air flow in addition to clamping brush filaments.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210574132.XA CN114991883B (en) | 2022-05-24 | 2022-05-24 | Radial multilayer brush silk brush formula seal structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210574132.XA CN114991883B (en) | 2022-05-24 | 2022-05-24 | Radial multilayer brush silk brush formula seal structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114991883A CN114991883A (en) | 2022-09-02 |
| CN114991883B true CN114991883B (en) | 2023-08-11 |
Family
ID=83028921
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210574132.XA Active CN114991883B (en) | 2022-05-24 | 2022-05-24 | Radial multilayer brush silk brush formula seal structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114991883B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5752805A (en) * | 1995-07-28 | 1998-05-19 | Mtu Motoren- Und Turbinen-Union | Brush seal for turbo-engines |
| CN105649685A (en) * | 2015-12-31 | 2016-06-08 | 沈阳航空航天大学 | Combined type brush sealing structure with radially adjustable brush wire bundle |
| CN108757055A (en) * | 2018-05-24 | 2018-11-06 | 西安交通大学 | A kind of labyrinth seal structure with brush seal item |
| CN109209520A (en) * | 2018-09-13 | 2019-01-15 | 中国科学院工程热物理研究所 | A kind of centripetal turbine back cavity leakage stream loss inhibition sealing technique |
| CN208996771U (en) * | 2018-09-04 | 2019-06-18 | 昆明理工大学 | A kind of low abrasion labyrinth-brush composite seal device |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9322287B2 (en) * | 2014-06-03 | 2016-04-26 | General Electric Company | Brush seal for turbine |
| CN111663963B (en) * | 2020-05-14 | 2021-06-04 | 复旦大学 | Multistage brush type sealing structure capable of adjusting final-stage pressure drop |
-
2022
- 2022-05-24 CN CN202210574132.XA patent/CN114991883B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5752805A (en) * | 1995-07-28 | 1998-05-19 | Mtu Motoren- Und Turbinen-Union | Brush seal for turbo-engines |
| CN105649685A (en) * | 2015-12-31 | 2016-06-08 | 沈阳航空航天大学 | Combined type brush sealing structure with radially adjustable brush wire bundle |
| CN108757055A (en) * | 2018-05-24 | 2018-11-06 | 西安交通大学 | A kind of labyrinth seal structure with brush seal item |
| CN208996771U (en) * | 2018-09-04 | 2019-06-18 | 昆明理工大学 | A kind of low abrasion labyrinth-brush composite seal device |
| CN109209520A (en) * | 2018-09-13 | 2019-01-15 | 中国科学院工程热物理研究所 | A kind of centripetal turbine back cavity leakage stream loss inhibition sealing technique |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114991883A (en) | 2022-09-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8191374B2 (en) | Two-shaft gas turbine | |
| US9695704B2 (en) | High damping labyrinth seal with helicoidal and helicoidal-cylindrical mixed pattern | |
| US20110280715A1 (en) | Curved labyrinth seals | |
| CN104204418B (en) | For the labyrinth sealing of turbo machine | |
| US20120027582A1 (en) | Floating packing ring assembly | |
| US20190085725A1 (en) | Lube system for geared turbine section | |
| US20180223994A1 (en) | Radial coverage piston ring groove arrangement | |
| US11371380B2 (en) | Variable guide vane assembly and vane arms therefor | |
| JP6632206B2 (en) | Face seal with local elastohydrodynamic pad | |
| US10837301B2 (en) | Structure for multi-stage sealing of turbine | |
| US20120121411A1 (en) | Labyrinth Seals for Turbomachinery | |
| CN105723134B (en) | Sealing system with two rows complementation potted component | |
| US20130266427A1 (en) | Sealing system for a turbomachine | |
| CN114991883B (en) | Radial multilayer brush silk brush formula seal structure | |
| US8632075B2 (en) | Seal assembly and method for flowing hot gas in a turbine | |
| CN103291379B (en) | Turbine | |
| WO2011055666A1 (en) | Axial flow turbine | |
| US20160290511A1 (en) | Shaft seal and method for producing same | |
| US9470101B2 (en) | Turbomachine | |
| WO2021201828A1 (en) | Rotary machine seal assemblies and method | |
| WO2002099253A1 (en) | Gas turbine | |
| JP6106439B2 (en) | Near flow path seal with axial flexible arm | |
| JP5221760B2 (en) | Reduction method of thermal load of outer housing for turbomachine | |
| US11408511B2 (en) | Circumferential seal assembly | |
| CN114991884B (en) | Arch brush wire brush type sealing structure for reducing actual gap by utilizing brush wire deformation |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |