CN111379628A - Sealing assembly for gas turbine and gas turbine - Google Patents
Sealing assembly for gas turbine and gas turbine Download PDFInfo
- Publication number
- CN111379628A CN111379628A CN201811628421.3A CN201811628421A CN111379628A CN 111379628 A CN111379628 A CN 111379628A CN 201811628421 A CN201811628421 A CN 201811628421A CN 111379628 A CN111379628 A CN 111379628A
- Authority
- CN
- China
- Prior art keywords
- section
- seal
- inner peripheral
- peripheral surface
- fingertip
- 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.)
- Pending
Links
Images
Classifications
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (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 invention discloses a sealing assembly for a gas turbine and the gas turbine, wherein the sealing assembly comprises a sealing ring, the sealing ring comprises a first section and a second section which are sequentially connected along the axial direction of the sealing ring, the cross-sectional area of the inner peripheral outline of the first section is larger than that of the inner peripheral outline of the second section, the length of the first section along the axial direction of the sealing ring is smaller than that of the second section along the axial direction of the sealing ring, at least one of the inner peripheral surface of the first section and the inner peripheral surface of the second section is provided with a fingertip sealing part, and the fingertip sealing part and a rotator are spaced along the radial direction of the sealing ring. The sealing component for the gas turbine is not easy to wear and long in service life, and improves the sealing effect.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a sealing assembly for a gas turbine and the gas turbine.
Background
In a gas turbine, the interstage of the turbine disk is usually sealed to prevent the gas of the main flow channel from invading into the interior of the turbine chamber, and the gas turbine is guaranteed to move normally and efficiently. In external air extraction from a certain stage of the compressor, most of air flow enters the inside of the static blade, one part of the air flow entering the inside of the static blade cools the static blade of the turbine, the other part of the air flow flows to the static blade sealing ring and is divided into two parts of air flow which flow forwards and backwards along the axial direction, and the two parts of air flow respectively pass through the sealing parts on the static blade sealing ring and then seal the air leaked from the main flow channel.
In the related art, the seal member on the vane seal ring is often in the form of a labyrinth seal, a brush seal, or a brush seal and a labyrinth seal. However, a gap is left between the seal tooth of the labyrinth seal and the surface of the rotating shaft, the leakage amount is large, and under the influence of the radial motion of the surface of the rotating shaft, the seal tooth is easy to wear, so that the leakage amount is increased and even the seal fails; although the leakage amount of the brush seal is small relative to the labyrinth seal, the brush wire is in contact with the surface of the rotating shaft, the brush wire is easy to wear in the rotating process of the rotating shaft, the sealing gap is enlarged, the leakage amount is enlarged, and meanwhile, the problems of heat generation, hysteresis effect and the like along with the wear are solved, and the sealing effect is poor.
Disclosure of Invention
The present invention is directed to solving, at least to some extent, one of the technical problems in the related art. Therefore, the invention provides a sealing assembly for a gas turbine, which is not easy to wear, has long service life and improves the sealing effect.
The invention also provides a gas turbine.
A seal assembly for a gas turbine engine, the gas turbine engine including a stator and a rotor, the static body surrounds the rotating body, the sealing assembly comprises a sealing ring, the sealing ring is arranged between the static body and the rotating body, and the peripheral surface of the sealing ring is connected with the static body, the sealing ring comprises a first section and a second section which are sequentially connected along the axial direction of the sealing ring, the cross-sectional area of the inner peripheral profile of the first section is greater than the cross-sectional area of the inner peripheral profile of the second section, and the length of the first section in the axial direction of the seal ring is smaller than the length of the second section in the axial direction of the seal ring, at least one of the inner peripheral surface of the first section and the inner peripheral surface of the second section is provided with a fingertip seal member, and the fingertip seal member is spaced from the rotor in the radial direction of the seal ring.
According to the sealing assembly for the gas turbine, provided by the embodiment of the invention, the fingertip sealing part is arranged on the inner surface of the sealing ring, so that the sealing assembly is not easy to wear, the service life is long, and the sealing effect is improved.
In some embodiments, the fingertip sealing members are provided on an inner peripheral surface of the first section and an inner peripheral surface of the second section.
In some embodiments, the inner peripheral surface of the first segment is provided with one fingertip seal member, the inner peripheral surface of the second segment is provided with a plurality of fingertip seal members, and the plurality of fingertip seal members on the inner peripheral surface of the second segment are arranged at intervals in the axial direction of the seal ring.
In some embodiments, a labyrinth seal part is further provided on the inner peripheral surface of the second section, the labyrinth seal part being spaced from the fingertip seal part in the axial direction of the seal ring.
In some embodiments, the inner peripheral surface of the first section and the inner peripheral surface of the second section are respectively provided with one of the fingertip seal parts, and one of the fingertip seal parts on the inner peripheral surface of the second section is spaced apart from the labyrinth seal part in the axial direction of the seal ring.
In some embodiments, the fingertip seal member is provided on an inner peripheral surface of the first section, and the inner peripheral surface of the second section is provided with a labyrinth seal member.
In some embodiments, the fingertip seal member is provided on an inner peripheral surface of the second segment, and the inner peripheral surface of the first segment is provided with a brush seal member.
In some embodiments, the fingertip seal member has a plurality of fingertip seal members spaced apart in an axial direction of the seal ring.
In some embodiments, the inner circumferential surface of the second section is further provided with a labyrinth seal part, and the labyrinth seal part and the fingertip seal part are arranged at intervals along the axial direction of the seal ring.
A gas turbine according to an embodiment of the second aspect of the invention includes: a turbine disk, the turbine disk being rotatable; the first movable blade and the second movable blade are arranged at the outer edge of the turbine wheel disc; a turbine stator vane surrounding the turbine disk and located between the first and second movable blades; the sealing assembly is the sealing assembly in any one of the embodiments, and the sealing ring is coaxially arranged with the turbine disk and the turbine stationary blade.
Drawings
FIG. 1 is a schematic block diagram of a gas turbine according to an embodiment of the present invention.
FIG. 2 is a schematic structural view of a seal assembly according to one embodiment of the present invention.
Fig. 3 is a schematic structural view of a seal assembly according to another embodiment of the present invention.
Fig. 4 is a schematic structural view of a seal assembly according to yet another embodiment of the present invention.
FIG. 5 is a schematic structural view of a seal assembly according to yet another embodiment of the present invention.
Fig. 6 is a schematic structural view of a seal assembly according to yet another embodiment of the present invention.
Reference numerals:
the turbine blade assembly includes a stator (turbine vane) 1, a rotor (turbine disk) 2, a seal assembly 3, a seal ring 31, a first segment 311, a second segment 312, a fingertip seal member 32, a labyrinth seal member 33, a brush seal member 34, a first rotor blade 4, and a second rotor blade 5.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced device or component must have a particular orientation, be constructed and operated in a particular orientation, and are not to be considered limiting of the invention.
A gas turbine and a seal assembly for a gas turbine according to an embodiment of the present invention will be described with reference to fig. 1 to 6.
As shown in fig. 1, a gas turbine according to an embodiment of the present invention includes a stationary body 1, a rotor 2, and a seal assembly 3, the stationary body 1 surrounding the rotor 2, the seal assembly 3 surrounding between the stationary body 1 and the rotor 2, and the seal assembly 3 being attached to the stationary body 1. It will be appreciated that an external air flow may enter the seal assembly 3 through the stator 1, wherein a portion of the air flow exits from the first port of the seal assembly 3 and another portion of the air flow exits from the second port of the seal assembly 3 to respectively perform the sealing function.
A seal assembly 3 for a gas turbine according to an embodiment of the present invention is described below.
As shown in fig. 1 to 6, the seal assembly 3 includes a seal ring 31, the seal ring 31 is surrounded between the stationary body 1 and the rotor 2, and an outer circumferential surface of the seal ring 31 is connected to the stationary body 1.
The seal ring 31 includes a first segment 311 and a second segment 312 that are arranged in this order in the axial direction (the left-right direction shown in fig. 1) of the seal ring 31, and the first segment 311 and the second segment 312 are connected. Wherein the cross-sectional area of the inner peripheral profile of the first section 311 is greater than the cross-sectional area of the inner peripheral profile of the second section 312. In other words, as shown in fig. 1, the first section 311 and the second section 312 are sequentially disposed from left to right and connected to each other, the first section 311 has a central hole penetrating the first section 311 in the left-right direction, the second section 312 has a central hole penetrating the second section 312 in the left-right direction, the cross-sectional area of the central hole of the first section 311 is larger than that of the central hole of the second section 312, and the first section 311 and the second section 312 are coaxially arranged. In the description of the present invention, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implying any number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature.
The length of the first segment 311 in the axial direction (the left-right direction shown in fig. 1) of the seal ring 31 is smaller than the length of the second segment 312 in the axial direction of the seal ring 31. In other words, as shown in fig. 1, the length of the first segment 311 in the left-right direction is shorter than the length of the second segment 312 in the left-right direction.
At least one of the inner peripheral surface of the first segment 311 and the inner peripheral surface of the second segment 312 is provided with a fingertip seal member 32, and the fingertip seal member 32 is spaced apart from the rotor 2 in the radial direction of the seal ring 31. It will be appreciated that the fingertip sealing member 32 is a non-contact fingertip seal.
It will be appreciated that external air flow may enter the seal ring 31 through the stator 1, wherein a portion of the air flow exits the first port of the seal ring 31 through the first section 311, and another portion of the air flow exits the second port of the seal ring 31 through the second section 312 to perform sealing functions, respectively.
According to the seal assembly 3 for a gas turbine of the embodiment of the present invention, when the seal air flows through the fingertip seal members 32 on the seal ring 31, the high pressure fingertip pieces and the low pressure fingertip pieces of the fingertip seal members 32 are staggered and stacked in the axial direction of the seal ring 31, so that the axial leakage caused by the circumferential gap between the fingertip pieces can be prevented. The structure of the bottom of the low-pressure fingertip sheet sealing shoe of the fingertip sealing part 32 can generate fluid pressure between the sealing shoe and the rim of the rotor 2 by means of fluid pressure or high-speed rotation of the rotor, float the sealing shoe, form a fluid film between the sealing shoe and the rim of the rotor 2, and reduce abrasion between the sealing shoe of the fingertip sealing part 32 and the rim of the rotor 2. Therefore, the seal ring 31 with the noncontact fingertip seal has the characteristics of low leakage, low abrasion, and long life. Therefore, the fingertip seal member 32 is provided on the inner surface of the seal ring 31, so that the fingertip seal member is less likely to be worn, has a long service life, and improves the sealing effect.
In addition, compared with a labyrinth seal, the non-contact fingertip seal has a small leakage amount, and compared with a brush seal, the process is simple and the cost is low. Because the sealing type is non-contact and the sealing type is not in contact with the rotating body, the friction and the abrasion do not exist under the normal operation condition, and the heating value is small. And moreover, the surface of the runway which is coupled with the fingertips does not need to be sprayed with a wear-resistant coating, so that the risk of falling off of the coating is avoided.
In some alternative embodiments, as shown in fig. 2-3, fingertip sealing members 32 are provided on the inner peripheral surface of the first section 311 and the inner peripheral surface of the second section 312. In other words, the inner peripheral surface of the first section 311 and the inner peripheral surface of the second section 312 are both provided with the fingertip seal members 32.
In some specific embodiments, as shown in fig. 2, the inner circumferential surface of the first section 311 is provided with one fingertip seal member 32, the inner circumferential surface of the second section 312 is provided with a plurality of fingertip seal members 32, and the plurality of fingertip seal members 32 on the inner circumferential surface of the second section 312 are arranged at intervals in the axial direction of the seal ring 31. It will be appreciated that the invention is not so limited, for example the inner periphery of the first section 311 and the inner periphery of the second section 312 are each provided with a fingertip sealing member 32. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In some specific embodiments, as shown in fig. 3, a labyrinth seal part 33 is further provided on the inner peripheral surface of the second section 312, and the labyrinth seal part 33 is spaced from the fingertip seal part 32 in the axial direction of the seal ring 31.
Further, an inner peripheral surface of the first section 311 and an inner peripheral surface of the second section 312 are provided with one fingertip seal part 32, respectively, and the one fingertip seal part 32 on the inner peripheral surface of the second section 312 is spaced apart from the labyrinth seal part 33 in the axial direction of the seal ring 31. For example, in the embodiment shown in fig. 3, the right end of the first section 311 is connected to the left end of the second section 312, the inner peripheral surface of the first section 311 is provided with one fingertip seal member 32, and the inner peripheral surface of the second section 312 is provided with a labyrinth seal member 33 and one fingertip seal member 32, wherein the fingertip seal member 32 and the labyrinth seal member 33 are arranged in this order from left to right and spaced apart from each other.
In other alternative embodiments, as shown in fig. 4, the fingertip seal member 32 is provided on the inner peripheral surface of the first section 311, and the inner peripheral surface of the second section 312 is provided with the labyrinth seal member 33. In other words, as shown in fig. 4, only the inner peripheral surface of the first segment 311 is provided with the fingertip seal member 32, and the inner peripheral surface of the second segment 312 is provided with the labyrinth seal member 33 without the fingertip seal member 32.
Specifically, as shown in fig. 4, the labyrinth seal member 33 is distributed over the inner peripheral surface of the second section 312 in the axial direction of the second section 312.
In still other alternative embodiments, as shown in fig. 5-6, fingertip seal members 32 are provided on the inner peripheral surface of the second section 312, and the inner peripheral surface of the first section 311 is provided with a brush seal member 34. In other words, as shown in fig. 5 and 6, only the inner peripheral surface of the second segment 312 is provided with the fingertip seal member 32, and the inner peripheral surface of the first segment 311 is provided with the brush seal member 34 without the fingertip seal member 32.
In some specific embodiments, as shown in fig. 5, the inner peripheral surface of the second section 312 is further provided with a labyrinth seal part 33, and the labyrinth seal part 33 and the fingertip seal part 32 are arranged at intervals in the axial direction (the left-right direction shown in fig. 1 and 4) of the seal ring 31. In other words, as shown in fig. 5, the second section 312 is provided with the fingertip seal member 32 and the labyrinth seal member 33, and the fingertip seal member 32 and the labyrinth seal member 33 are spaced apart from each other in the left-right direction. The tip seal member 32 and the labyrinth seal member 33 may be arranged in this order from left to right on the inner peripheral surface of the second section 312, or the tip seal member 32 and the labyrinth seal member 33 may be arranged in this order from right to left on the inner peripheral surface of the second section 312.
In some specific embodiments, as shown in fig. 6, the fingertip seal members 32 are plural, and the plural fingertip seal members 32 are spaced apart in the axial direction of the seal ring 31. In other words, the inner peripheral surface of the second segment 312 is provided with a plurality of fingertip seal members 32, and the plurality of fingertip seal members 32 are arranged at intervals from each other in the left-right direction. For example, in the embodiment shown in fig. 6, the inner peripheral surface of the second segment 312 is provided with two fingertip seal members 32, and the two fingertip seal members 32 are arranged in this order from left to right and spaced apart from each other.
It is understood that the inner peripheral surface of the second section 312 may also be provided with a labyrinth seal part 33 and a plurality of fingertip seal parts 32, wherein the labyrinth seal part 33 may be provided between two adjacent fingertip seal parts 32 and spaced apart from each fingertip seal part 32, or spaced apart from a plurality of fingertip seal parts 32.
The sealing assembly for the gas turbine adopts a mode that a non-contact fingertip seal is matched with other forms of seals. The problem that the clearance between the sealing teeth of the labyrinth seal and the surface of the rotating shaft is large is solved, the contact between the bottom end of the seal and the rotating body is reduced, and the dynamic sealing performance is excellent. Therefore, the sealing leakage amount is effectively controlled, the problems of friction, abrasion and heating in the operation process are solved, the reliability of the interstage seal of the rotating body is improved, and the service life of the interstage seal of the rotating body is prolonged. Meanwhile, compared with a brush type seal, the non-contact fingertip seal has the advantages that the number of flexible units is greatly reduced, the processing and manufacturing process is relatively simple, and the processing and manufacturing cost can be greatly reduced.
A gas turbine according to another embodiment of the present invention is described below with reference to fig. 1.
As shown in fig. 1, the gas turbine according to the embodiment of the present invention includes a turbine stationary blade 1, a turbine disk 2, a seal assembly 3, a first movable blade 4 and a second movable blade 5, wherein the turbine disk 2 is rotatable, the first movable blade 4 and the second movable blade 5 are provided at an outer edge of the turbine disk 2 (a rim of the turbine disk 2), that is, the first movable blade 4 and the second movable blade 4 are both connected to an outer circumferential surface of the turbine disk 2. The turbine vanes 1 surround the turbine disk 2 and are located between the first blades 4 and the second blades 5.
The seal assembly 3 is arranged between the turbine disk 2 and the turbine stator blade 1 and is connected with the turbine stator blade 1. Specifically, the seal ring 31 is provided coaxially with the turbine disk 2 and the turbine vane 1, and gaps are provided between the turbine vane 1 and the first movable blade 4 and between the turbine vane 1 and the second movable blade 5. As shown in fig. 1, after the external air flows through the turbine vane 1 into the sealing ring 31, a part of the air flows through the first section 311, flows out from the left port of the sealing ring 31, and flows to the gap between the turbine vane 1 and the first blade 4 to seal the gap; another part of the air flows out of the right end port of the seal ring 31 through the second segment 312 and flows to the gap between the turbine vane 1 and the second movable blade 5 to seal the gap.
The seal assembly 3 includes a seal ring 31 and a fingertip seal member 32, wherein the seal ring 31 is surrounded between the turbine disk 2 and the turbine stationary blade 1, and the outer peripheral surface of the seal ring 31 is connected to the turbine stationary blade 1. The sealing ring 31 includes a first section 311 and a second section 312 which are arranged in sequence from left to right and connected to each other, the first section 311 has a central hole penetrating the first section 311 in a left-right direction, the second section 312 has a central hole penetrating the second section 312 in a left-right direction, a cross-sectional area of the central hole of the first section 311 is larger than a cross-sectional area of the central hole of the second section 312, and the first section 311 and the second section 312 are coaxially arranged. The length of the first segment 311 in the left-right direction is shorter than the length of the second segment 312 in the left-right direction.
Wherein in the embodiment shown in fig. 2, there are three fingertip seal members 32, one fingertip seal member 32 is provided at the inner peripheral surface of the first section 311, two fingertip seal members 32 are provided at the inner peripheral surface of the second section 312, and the two fingertip seal members 32 at the inner peripheral surface of the second section 312 are spaced apart in the left-right direction.
In the embodiment shown in fig. 3, the inner peripheral surface of the first section 311 is provided with one fingertip seal member 32, the inner peripheral surface of the second section 312 is provided with one fingertip seal member 32 and one labyrinth seal member 33, and the fingertip seal member 32 and the labyrinth seal member 33 are spaced apart from each other in the left-right direction.
In the embodiment shown in fig. 4, the inner peripheral surface of the first section 311 is provided with a fingertip seal member 32, the inner peripheral surface of the second section 312 is provided with a labyrinth seal member 33, and the labyrinth seal member 33 spreads over the inner peripheral surface of the second section 312 in the left-right direction.
In the embodiment shown in fig. 5, the inner peripheral surface of the first section 311 is provided with a brush seal member 34, the inner peripheral surface of the second section 312 is provided with a fingertip seal member 32 and a labyrinth seal member 33, and the fingertip seal member 32 and the labyrinth seal member 33 are arranged in this order from left to right and spaced apart from each other.
In the embodiment shown in fig. 6, the inner peripheral surface of the first section 311 is provided with one brush seal member 34, and the inner peripheral surface of the second section 312 is provided with two fingertip seal members 32 spaced apart in the left-right direction.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; may be mechanically coupled, may be electrically coupled or may be in communication with each other; they may be directly connected or indirectly connected through intervening media, or they may be interconnected within two members or in an interactive relationship between two members, unless expressly defined otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (10)
1. A seal assembly for a gas turbine engine, said gas turbine engine including a stator and a rotor, said stator surrounding said rotor, it is characterized in that the sealing component comprises a sealing ring which is arranged between the static body and the rotating body, and the peripheral surface of the sealing ring is connected with the static body, the sealing ring comprises a first section and a second section which are sequentially connected along the axial direction of the sealing ring, the cross-sectional area of the inner peripheral profile of the first section is greater than the cross-sectional area of the inner peripheral profile of the second section, and the length of the first section in the axial direction of the seal ring is smaller than the length of the second section in the axial direction of the seal ring, at least one of the inner peripheral surface of the first section and the inner peripheral surface of the second section is provided with a fingertip seal member, and the fingertip seal member is spaced from the rotor in the radial direction of the seal ring.
2. The seal assembly for a gas turbine according to claim 1, wherein said fingertip seal members are provided on an inner peripheral surface of said first section and an inner peripheral surface of said second section.
3. The seal assembly for a gas turbine according to claim 2, wherein an inner peripheral surface of said first section is provided with one of said fingertip seal members, an inner peripheral surface of said second section is provided with a plurality of said fingertip seal members, and said fingertip seal members on the inner peripheral surface of said second section are arranged at intervals in an axial direction of said seal ring.
4. The seal assembly for a gas turbine according to claim 2, wherein a labyrinth seal member is further provided on an inner peripheral surface of the second section, the labyrinth seal member being spaced from the fingertip seal member in an axial direction of the seal ring.
5. The seal assembly for a gas turbine according to claim 4, wherein an inner peripheral surface of said first section and an inner peripheral surface of said second section are provided with one of said fingertip seal members, respectively, and one of said fingertip seal members on the inner peripheral surface of said second section is spaced from said labyrinth seal member in an axial direction of said seal ring.
6. The seal assembly for a gas turbine according to claim 1, wherein said fingertip seal member is provided on an inner peripheral surface of said first section, and an inner peripheral surface of said second section is provided with a labyrinth seal member.
7. The seal assembly for a gas turbine according to claim 1, wherein said fingertip seal member is provided on an inner peripheral surface of said second segment, and an inner peripheral surface of said first segment is provided with a brush seal member.
8. The seal assembly for a gas turbine according to claim 7, wherein said fingertip seal members are plural in number, and plural are spaced apart in an axial direction of said seal ring.
9. The seal assembly for a gas turbine according to claim 7, wherein an inner peripheral surface of said second section is further provided with a labyrinth seal member, said labyrinth seal member and said fingertip seal member being arranged at a spacing in an axial direction of said seal ring.
10. A gas turbine engine, comprising:
a turbine disk, the turbine disk being rotatable;
the first movable blade and the second movable blade are arranged at the outer edge of the turbine wheel disc;
a turbine stator vane surrounding the turbine disk and located between the first and second movable blades;
a seal assembly as claimed in any one of claims 1 to 9, the seal ring being disposed coaxially with the turbine disk and the turbine vanes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811628421.3A CN111379628A (en) | 2018-12-28 | 2018-12-28 | Sealing assembly for gas turbine and gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811628421.3A CN111379628A (en) | 2018-12-28 | 2018-12-28 | Sealing assembly for gas turbine and gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111379628A true CN111379628A (en) | 2020-07-07 |
Family
ID=71216429
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811628421.3A Pending CN111379628A (en) | 2018-12-28 | 2018-12-28 | Sealing assembly for gas turbine and gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111379628A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112012833A (en) * | 2020-09-10 | 2020-12-01 | 上海和兰透平动力技术有限公司 | Interstage sealing structure of radial-flow gas turbine and simulation design method thereof |
-
2018
- 2018-12-28 CN CN201811628421.3A patent/CN111379628A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112012833A (en) * | 2020-09-10 | 2020-12-01 | 上海和兰透平动力技术有限公司 | Interstage sealing structure of radial-flow gas turbine and simulation design method thereof |
| CN112012833B (en) * | 2020-09-10 | 2023-06-06 | 上海和兰透平动力技术有限公司 | Radial-flow gas turbine interstage sealing structure and simulation design method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102865108B (en) | Labyrinth | |
| US8066475B2 (en) | Labyrinth compression seal and turbine incorporating the same | |
| US9103223B2 (en) | Shaft sealing device and rotating machine comprising same | |
| US20140234076A1 (en) | Outer rim seal assembly in a turbine engine | |
| US10281046B2 (en) | Fluid machine having a labyrinth seal | |
| US8784045B2 (en) | Seal assembly | |
| US7059821B2 (en) | Method and apparatus to facilitate sealing within turbines | |
| EP2960558B1 (en) | Shaft seal device and rotary machine | |
| JP2012072736A (en) | Shaft seal device of rotary machine | |
| JP2015511677A (en) | Labyrinth seal for turbine | |
| CN102392692A (en) | Apparatus and system for sealing a turbine rotor | |
| US9677410B2 (en) | Shaft sealing device, and rotary machine equipped therewith | |
| CN111379628A (en) | Sealing assembly for gas turbine and gas turbine | |
| CN103670529B (en) | For cooling method and the cooling system of the blade of at least one blade row | |
| CN111878449A (en) | Centrifugal compressor sealing device, centrifugal compressor and gas turbine | |
| EP2305957B1 (en) | Improved staggered seal assembly | |
| US8132815B1 (en) | Card seal for a turbine | |
| CN209483486U (en) | Seal assembly and gas turbine for gas turbines | |
| US20160376900A1 (en) | Stator device for a continuous-flow machine with a housing appliance and multiple guide vanes | |
| KR20220140001A (en) | Improved turbine and blades for protection of routes from flow path hot gases | |
| EP3438512B1 (en) | Seal segment and rotary machine | |
| CN210397223U (en) | Rotary machine | |
| CN111379861A (en) | Floating seal device for rotary machine and rotary machine | |
| US20100322799A1 (en) | Turbomolecular pump | |
| CN111120011A (en) | Stationary blade ring |
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 |