CN114151143A - Gas turbine and seal assembly therefor - Google Patents
Gas turbine and seal assembly therefor Download PDFInfo
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- CN114151143A CN114151143A CN202111333881.5A CN202111333881A CN114151143A CN 114151143 A CN114151143 A CN 114151143A CN 202111333881 A CN202111333881 A CN 202111333881A CN 114151143 A CN114151143 A CN 114151143A
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- honeycomb core
- seal
- partition plate
- seal assembly
- grid
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- 238000005192 partition Methods 0.000 claims abstract description 83
- 238000007789 sealing Methods 0.000 claims abstract description 76
- 230000002093 peripheral effect Effects 0.000 claims abstract description 18
- 125000006850 spacer group Chemical group 0.000 claims description 16
- 208000002925 dental caries Diseases 0.000 claims description 8
- 239000012530 fluid Substances 0.000 claims description 6
- 244000126211 Hericium coralloides Species 0.000 abstract description 4
- 241000264877 Hippospongia communis Species 0.000 description 137
- 230000001965 increasing effect Effects 0.000 description 9
- 238000011144 upstream manufacturing Methods 0.000 description 7
- 238000013461 design Methods 0.000 description 4
- 238000004891 communication Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000000638 solvent extraction Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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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
- F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
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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)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a gas turbine and a sealing assembly thereof, wherein the sealing assembly of the embodiment of the invention comprises a sealing ring and a comb tooth, the sealing ring is arranged on a blade root of a stationary blade of the gas turbine, the sealing ring comprises a sealing section, the inner circumferential surface of the sealing section is provided with a plurality of honeycomb core grids, at least one of the honeycomb core grids is a partition plate honeycomb core grid, a partition plate is arranged in the partition plate honeycomb core grid, and the partition plate extends along the radial direction of the sealing ring so as to divide the partition plate honeycomb core grid into a plurality of cavity units; the grate is arranged on the outer edge of a turbine wheel disc of the gas turbine, and the outer peripheral surface of the grate is matched with the inner peripheral surface of the sealing section. The sealing assembly provided by the embodiment of the invention has the advantages of small leakage amount and the like.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a gas turbine and a sealing assembly thereof.
Background
The honeycomb labyrinth seal is a high-performance seal structure, is widely applied to the rim seal of a hot end part of a gas turbine, and can play a role in reducing leakage, improving the dynamic characteristic of a rotor, reducing friction damage between rotating and static surfaces and the like.
In order to reduce leakage flow, researchers at home and abroad develop a modified design for sealing the honeycomb labyrinth. At present, the leakage flow of the honeycomb labyrinth seal is remarkably reduced, and how to further reduce the leakage amount through the structural design is always the leading edge and the hot point of research.
Disclosure of Invention
The present invention is based on the discovery and recognition by the inventors of the following facts and problems:
the straight-through honeycomb comb tooth seal is widely applied to sealing the blade root of the turbine stationary blade of the gas turbine, and the jet flow between the teeth enters the honeycomb core grids to generate vortex, so that a good blocking effect is generated on the leakage airflow. The minimum flow area influences the sealing leakage amount of the honeycomb labyrinth. For honeycombs at other positions in the tooth chamber, the inlet air quantity should be increased as much as possible to sufficiently dissipate the kinetic energy of the leakage flow. How to design the design of the honeycomb core grids according to the flowing characteristics of different positions, and simultaneously meeting the requirements of different positions of the tooth tops and the tooth cavities of the grid teeth on reducing the leakage amount, increasing the air input of the core grids and enhancing the dissipation of kinetic energy, is a difficult problem to be solved urgently.
The present invention is directed to solving, at least to some extent, one of the technical problems in the related art.
To this end, embodiments of the present invention provide a seal assembly with a reduced amount of leakage.
Embodiments of the present invention also provide a gas turbine with high thermal efficiency.
The seal assembly of an embodiment of the present invention includes:
the sealing ring is used for being arranged on a stator blade root of a gas turbine and comprises a sealing section, the inner circumferential surface of the sealing section is provided with a plurality of honeycomb core grids, at least one of the honeycomb core grids is a partition plate honeycomb core grid, a partition plate is arranged in the partition plate honeycomb core grid, and the partition plate extends along the radial direction of the sealing ring so as to divide the partition plate honeycomb core grid into a plurality of cavity units;
the grate is arranged on the outer edge of a turbine wheel disc of the gas turbine, and the outer peripheral surface of the grate is matched with the inner peripheral surface of the sealing section.
The sealing assembly provided by the embodiment of the invention has the advantages of small leakage amount and the like.
In some embodiments, the grid teeth are arranged corresponding to the honeycomb core grids with the partition plates in the radial direction of the sealing ring.
In some embodiments, the partition plate is disposed in a radial direction of the seal ring so as to be spaced apart from the bottom wall of the compartmented honeycomb core cell so as to communicate with outer ends of a plurality of the cavity units, at least two of the cavity units being arranged in an axial direction of the seal ring.
In some embodiments, the ratio of the dimension of the divider plate in the radial direction of the seal ring to the dimension of the compartmented honeycomb core cell in the radial direction of the seal ring is from 0.7 to 0.9.
In some embodiments, a portion of the plurality of honeycomb core cells is the baffled honeycomb core cell and another portion of the plurality of honeycomb core cells is a non-baffled honeycomb core cell.
In some embodiments, each of the spacer-containing honeycomb core cells and the non-spacer honeycomb core cells is provided with a plurality of groups, the plurality of groups of spacer-containing honeycomb core cells and the plurality of groups of non-spacer honeycomb core cells being alternately arranged in the axial direction of the seal ring;
the plurality of the grid teeth are arranged at intervals along the axial direction of the sealing ring, a tooth cavity is defined between every two adjacent grid teeth, each grid tooth in the plurality of the grid teeth is arranged in a one-to-one correspondence mode with the plurality of groups of partition plate honeycomb core grids in the radial direction of the sealing ring, and each tooth cavity in the plurality of the grid teeth is arranged in a one-to-one correspondence mode with the plurality of groups of partition plate-free honeycomb core grids in the radial direction of the sealing ring.
In some embodiments, each group of the honeycomb core grids with the partition plates is provided with a plurality of rows, the plurality of rows of the honeycomb core grids with the partition plates are arranged along the axial direction of the sealing ring, and at least one part of the grid teeth is positioned between two adjacent rows of the honeycomb core grids with the partition plates in the axial direction of the sealing ring.
In some embodiments, the seal ring has axially opposed inlet and outlet ends, the inlet end for fluid to enter the seal assembly and the outlet end for fluid to exit the seal assembly, the baffled honeycomb core cells being disposed axially of the seal ring relative to the baffle-free honeycomb core cells and closer to the inlet end.
In some embodiments, the partition-plate honeycomb core cells are arranged in a plurality of rows, the plurality of rows are arranged along the axial direction of the sealing ring, and at least a part of the comb teeth is positioned between two adjacent rows of the partition-plate honeycomb core cells in the axial direction of the sealing ring.
In some embodiments, each of the plurality of honeycomb core cells is a baffled honeycomb core cell.
In some embodiments, the separator plate has a cross-shaped or T-shaped cross-section.
In some embodiments, the sealing section comprises a first sealing section and a second sealing section, the first sealing section and the second sealing section are arranged at intervals along the axial direction of the sealing ring, the labyrinth comprises a first labyrinth and a second labyrinth, the outer peripheral surface of the first labyrinth is matched with the inner peripheral surface of the first sealing section, and the outer peripheral surface of the second labyrinth is matched with the inner peripheral surface of the second sealing section.
The gas turbine of the present invention includes:
a cylinder;
a turbine wheel disc;
a first movable blade and a second movable blade, each of the first movable blade and the second movable blade being provided at an outer edge of the turbine disk;
the fixed blade of the cylinder surrounds the turbine wheel disc and is positioned between the first movable blade and the second movable blade; and
a seal assembly according to any preceding embodiment.
The gas turbine provided by the embodiment of the invention has the advantages of high thermal efficiency and the like.
Drawings
FIG. 1 is a schematic illustration of a partial structure of a gas turbine according to an embodiment of the present invention.
FIG. 2 is a partial schematic structural view of a seal assembly according to one embodiment of the present invention.
Fig. 3 is a partial schematic view of the first segment of fig. 2.
Fig. 4 is a partial structural view of the sealing ring of fig. 2.
Fig. 5 is a partial schematic view of a seal assembly according to another embodiment of the present invention.
Fig. 6 is a partial schematic structural view of a seal assembly according to yet another embodiment of the present invention.
Reference numerals:
a turbine disk 10;
a first bucket 20;
a second bucket 30;
a stationary blade 40; a first gas channel 401; a blade root 402;
a cylinder 50;
a seal assembly 100;
a seal ring 1; a first seal segment 101; a second seal segment 102; a sealing section 103; a spacer honeycomb core cell 104; a bottom wall 1041; a side wall 1042; a partition plate 1043; a cavity unit 1044; a communicating chamber 1045; a partition-free honeycomb core cell 105; an inlet end 106; an outlet end 107; a second gas passage 108;
the comb teeth 2; a first comb tooth 201; a second grate 202; a tooth chamber 203;
an inlet grate 60.
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.
As shown in fig. 1, a gas turbine according to an embodiment of the present invention includes a cylinder 50, a turbine disk 10, a first movable blade 20, a second movable blade 30, a stationary blade 40, and a seal assembly 100, and each of the first movable blade 20 and the second movable blade 30 is provided at an outer edge of the turbine disk 10. The stationary blade 40 is provided on the inner circumferential surface of the cylinder 50, and the stationary blade 40 surrounds the turbine disk 10 and is located between the first movable blade 20 and the second movable blade 30.
The blade root 402 of the vane 40 has a seal gap with the turbine disk 10 in which the seal assembly 100 is disposed.
A seal assembly 100 according to an embodiment of the present invention will now be described with reference to fig. 1 to 6.
The sealing assembly 100 of the embodiment of the invention comprises a sealing ring 1 and a comb tooth 2, wherein the sealing ring 1 is arranged on a blade root 402 of a stator blade 40 of a gas turbine, the sealing ring 1 comprises a sealing section 103, and the inner circumferential surface of the sealing section 103 is provided with a plurality of honeycomb core grids. At least one of the honeycomb core grids is the partition plate honeycomb core grid 104, a partition plate 1043 is arranged in the partition plate honeycomb core grid 104, and the partition plate 1043 extends along the radial direction of the sealing ring 1 so as to divide the partition plate honeycomb core grid 104 into a plurality of cavity units 1044.
The grate 2 is arranged on the outer edge of a turbine disk 10 of the gas turbine, and the outer circumferential surface of the grate 2 is matched with the inner circumferential surface of the sealing section 103. For example, the outer peripheral surface of the labyrinth 2 is in clearance fit with the inner peripheral surface of the seal segment 103.
In order to make the technical solution of the present application easier to understand, the technical solution of the present application is further described below by taking as an example that the radial direction of the seal ring 1 coincides with the inside-outside direction, and the axial direction of the seal ring 1 coincides with the left-right direction, where the inside-outside direction and the left-right direction are as shown in fig. 1.
For example, as shown in FIG. 1, the seal ring 1 is annular and connected to the blade root 402 of the vane 40, and the seal ring 1 includes a seal segment 103 extending in the left-right direction. At least one of the plurality of honeycomb core cells is a spacer honeycomb core cell 104, in other words, the number of spacer honeycomb core cells 104 is 1, or the number of spacer honeycomb core cells 104 is one third or one half of the number of all honeycomb core cells, or all honeycomb core cells are spacer honeycomb core cells 104.
Each honeycomb core cell has a bottom wall 1041 and a side wall 1042 connected to the bottom wall 1041, the honeycomb core cell extending in the inward-outward direction with an opening of the honeycomb core cell facing inward and opposite to the outer edge of the turbine disk 10. Partition plates 1043 are provided in the partition-plate honeycomb core cells 104, the partition plates 1043 extend in the inside-outside direction and are connected to the side walls 1042 of the partition-plate honeycomb core cells 104, thereby partitioning each partition-plate honeycomb core cell 104 into a plurality of cavity units 1044. The labyrinth 2 is arranged on the outer edge of the turbine disk 10, the sealing section 103 and the labyrinth 2 are arranged oppositely in the inner and outer directions, and a gap is formed between the outer peripheral surface of the labyrinth 2 and the inner peripheral surface of the sealing section 103 to form a flow passage.
In the seal assembly 100 according to the embodiment of the present invention, the stationary blade 40 is provided with the first gas channel 401, the seal ring 1 is provided with the second gas channel 108, the first gas channel 401 is communicated with the second gas channel 108 to form a fluid channel, and the gas flow outside the cylinder 50 sequentially passes through the first gas channel 401 and the second gas channel 108 to enter the fluid channel, and then flows along the left-right direction.
According to the sealing assembly 100 provided by the embodiment of the invention, the partition plate 1043 is arranged in the partition plate honeycomb core grid 104, so that the effective flow area between the grid tooth 2 and the honeycomb core grid can be effectively reduced, the leakage rate at the position of the sealing assembly 100 can be reduced, the gas loss of a gas turbine can be further reduced, and the heat efficiency of the gas turbine can be improved.
Thus, the seal assembly 100 of the embodiment of the present invention can significantly reduce the amount of gas leakage compared to the related art.
Therefore, the sealing assembly 100 of the embodiment of the invention has the advantages of less leakage and the like.
The gas turbine provided by the embodiment of the invention has the advantages of high thermal efficiency and the like.
In addition, the overall structural strength of the honeycomb core cell can be increased by providing the partition plates 1043 within the partition plate honeycomb core cell 104.
In some embodiments, the grate 2 is arranged corresponding to the honeycomb core cells 104 with the partition plates in the radial direction of the sealing ring 1.
For example, as shown in fig. 1 to 2, the comb 2 is disposed to face the partition-provided honeycomb core cell 104 in the inward and outward direction. Therefore, by arranging the partition plate 1043 in the partition plate honeycomb core grid 104, the effective flow area between the grid teeth 2 and the honeycomb core grid can be more effectively reduced, thereby further reducing the gas loss of the gas turbine and improving the heat efficiency of the gas turbine.
In some embodiments, the partition plate 1043 is disposed spaced apart from the bottom wall 1041 of the compartmented honeycomb core cell 104 in the radial direction of the seal ring 1 so that the outer ends of the plurality of cavity units 1044 communicate, at least two cavity units 1044 being arranged in the axial direction of the seal ring 1.
For example, as shown in fig. 2 and 3, the partition plate 1043 includes a first partition plate portion extending in the left-right direction and a second partition plate portion extending in the inward-outward direction, cavity units 1044 are defined between the first partition plate portion, the second partition plate portion, and the side wall 1042, communication cavities 1045 are defined between the bottom wall 1041, the side wall 1042, and the partition plate 1043 of the honeycomb core cell, and the cavity units 1044 of each partitioned honeycomb core cell 104 are communicated with each other through the communication cavities 1045.
The at least two cavity units 1044 are arranged in the left-right direction means that the number of the cavity units 1044 arranged in the left-right direction among the plurality of cavity units 1044 is 2, 3, or the like. In other words, at least one chamber unit 1044 is located upstream and at least one chamber unit 1044 is located downstream in the airflow direction.
Therefore, as shown in fig. 3, the airflow entering from the upstream cavity unit 1044 enters the communicating cavity 1045 and flows out through the downstream cavity unit 1044, that is, the airflow entering into the honeycomb core cell 104 with the partition plates can form a backflow between two adjacent cavity units 1044 arranged in the axial direction of the seal ring 1, so that the number and size of the vortices between the labyrinth 2 and the honeycomb core cell are increased, a part of flow channels between a part of the labyrinth 2 and the honeycomb core cell are blocked, the leakage flow resistance is increased, the airflow leakage amount at the position of the seal assembly 100 is further reduced, and the thermal efficiency of the gas turbine is improved.
Optionally, the partition plate 1043 has a cross-shaped or T-shaped cross-section. When the cross section of the partition plate 1043 is cross-shaped, the partition plate 1043 is used to partition the partition plate honeycomb core lattice 104 into four cavity units 1044. When the cross section of the partition plate 1043 is T-shaped, the partition plate 1043 is used to partition the partition plate honeycomb core lattice 104 into three cavity units 1044.
In some embodiments, the ratio of the dimension of the divider plate 1043 in the radial direction of the seal ring 1 to the dimension of the compartmented honeycomb core cell 104 in the radial direction of the seal ring 1 is 0.7 to 0.9.
For example, as shown in fig. 3, the dimension of the cavity partition side plate is L, the dimension of the side plate of the honeycomb core cell is H, and L is 0.7 to 0.9 times H in the inward and outward direction. For example, L is 0.7 times, 0.8 times, 0.9 times, etc. of H.
Therefore, the airflow entering the partition plate honeycomb core grids 104 is favorable for forming backflow in the partition plate honeycomb core grids 104, the swirl number and the swirl size between the grid 2 and the honeycomb core grids are further increased, the airflow leakage rate at the sealing assembly 100 is further reduced, and the heat efficiency of the gas turbine is improved. .
In some embodiments, a portion of the plurality of honeycomb core cells are spacer honeycomb core cells 104 and another portion of the plurality of honeycomb core cells are non-spacer honeycomb core cells 105.
The partition-free honeycomb core cell 105 means that no partition plate is provided in the honeycomb core cell.
Therefore, the effective flow area between the grid 2 and the honeycomb core grids can be effectively reduced by utilizing the honeycomb core grids 104 with the partition plates, so that the leakage quantity at the position of the sealing assembly 100 can be reduced; the utilization of the partition-free honeycomb core cells 105 facilitates more airflow entering the partition-free honeycomb core cells 105 to dissipate kinetic energy of the airflow, which is beneficial to further improving the thermal efficiency of the gas turbine.
In some embodiments, each of the partition-plate honeycomb core cells 104 and the partition-free honeycomb core cells 105 is provided with a plurality of sets of partition-plate honeycomb core cells 104 and partition-free honeycomb core cells 105 alternately arranged in the axial direction of the seal ring 1. The plurality of grid teeth 2 are arranged along the axial direction of the sealing ring 1 at intervals, a tooth cavity 203 is defined between every two adjacent grid teeth 2, each grid tooth 2 is arranged in a one-to-one correspondence manner with the plurality of groups of partition plate honeycomb core grids 104 in the radial direction of the sealing ring 1, and each grid tooth 203 is arranged in a one-to-one correspondence manner with the plurality of groups of partition plate-free honeycomb core grids 105 in the radial direction of the sealing ring 1.
For example, as shown in fig. 2 to 4, in the left-right direction, a plurality of sets of partition-plate-provided honeycomb core cells 104 and a plurality of sets of partition-plate-free honeycomb core cells 105 are alternately arranged. And a plurality of grid teeth 2 are arranged at intervals along the left-right direction, a tooth cavity 203 is formed between two adjacent grid teeth 2, in the inner and outer directions, each grid tooth 2 is arranged opposite to the honeycomb core lattice 104 with the partition plate, and each tooth cavity 203 is arranged opposite to the honeycomb core lattice 105 without the partition plate.
Therefore, the effective flow area between the grid 2 and the honeycomb core grids can be more effectively reduced by utilizing the honeycomb core grids 104 with the partition plates, so that the leakage quantity at the position of the sealing assembly 100 can be better reduced; the utilization of the bulkhead-free honeycomb core cells 105 facilitates more airflow into the bulkhead-free honeycomb core cells 105 to dissipate kinetic energy of the airflow and further increase the thermal efficiency of the gas turbine.
In some embodiments, each group of the plurality of rows of the plurality of the rows of the plurality of the spacer honeycomb core cells 104 along the axial direction of the sealing ring 1.
For example, as shown in fig. 2 and 3, each group of the partition plate honeycomb core cells 104 includes 2 rows of the partition plate honeycomb core cells 104 arranged in the left-right direction, and the tooth tips of the comb teeth 2 are provided at positions between the two rows of the partition plate honeycomb core cells 104.
Therefore, the jet flow of the tooth tops of the cutting grid 2 is cut by utilizing the partition between the two rows of partition plate honeycomb core grids 104, so that the jet flow at the tooth tops mainly forms two branches, and the two branches respectively enter the two rows of partition plate honeycomb core grids 104, so that backflow is respectively formed at the upstream and the downstream of the tooth tops of the grid 2, the vortex number and the vortex size between the grid 2 and the honeycomb core grids are increased, the airflow leakage amount at the position of the sealing assembly 100 is further reduced, and the heat efficiency of the gas turbine is improved.
Alternatively, the crest of the grate 2 is positioned at the middle of the two rows of baffle cells 104.
Alternatively, each group of spacer honeycomb core cells 104 may include 3, 4, or 5 rows of spacer honeycomb core cells 104.
In some embodiments, the seal segment 103 has axially opposite inlet and outlet ends 106, 107 thereof, with the spacer honeycomb core cells 104 disposed axially of the seal ring 1, relatively spacer-free honeycomb core cells 105, closer to the inlet end 106.
For example, as shown in fig. 6, the packing ring segment 103 has an inlet end 106 and an outlet end 107 opposite in the left-right direction, the inlet end 106 being disposed upstream of the flow passage, and the outlet end 107 being disposed downstream of the flow passage. A baffle honeycomb cell 104 is disposed adjacent the inlet end 106 and a baffle-free honeycomb cell 105 is disposed adjacent the outlet end 107.
Therefore, at the upstream of the grate 2 and the sealing section 103, the partition plates 1043 are arranged in the partition plate honeycomb core grids 104 at the upstream, so that the effective flow area between the grate 2 and the honeycomb core grids can be effectively reduced, the leakage amount at the position of the sealing assembly 100 can be reduced, more airflow can conveniently enter the partition plate-free honeycomb core grids 105 by utilizing the partition plate-free honeycomb core grids 105 at the downstream, the kinetic energy of the airflow is dissipated, and the thermal efficiency of the gas turbine is further improved.
Optionally, the grate 2 comprises an inlet grate 60, the inlet grate 60 being arranged closer to the inlet end 106 than the remaining grates in the axial direction of the seal ring 1, the baffle-free honeycomb core cells 104 corresponding to the inlet grate 60 in the radial direction of the seal ring 1, the baffle-free honeycomb core cells 105 being arranged downstream of the inlet grate 60.
Therefore, the number of the partition plate honeycomb core grids 104 is small, and the effective flow area between the inlet grid 60 and the partition plate honeycomb core grids 104 is reduced by utilizing the partition plate honeycomb core grids 104, so that the sealing section 103 is simple in integral structure and convenient to process.
In some embodiments, the partition-plate honeycomb core cells 104 are provided in a plurality of rows, the plurality of rows of the partition-plate honeycomb core cells 104 are arranged in the axial direction of the seal ring 1, and at least a part of the comb teeth 2 is located between two adjacent rows of the partition-plate honeycomb core cells 104 in the axial direction of the seal ring 1.
For example, as shown in fig. 2 and 3, each group of the partition-plate honeycomb core cells 104 includes a plurality of rows of the partition-plate honeycomb core cells 104 arranged in the left-right direction, and the tooth tops of the comb teeth 2 are provided at positions between the two rows of the partition-plate honeycomb core cells 104.
Therefore, the jet flow at the tooth tops of the grid 2 is cut by utilizing the partitions between the two rows of partition plate honeycomb core grids 104, so that the jet flow at the tooth tops mainly forms two branches, the two branches respectively enter the two rows of partition plate honeycomb core grids 104, backflow is respectively formed at the upstream and the downstream of the tooth tops of the grid 2, the vortex number between the grid 2 and the honeycomb core grids is increased, the dissipation of kinetic energy of leaked airflow is increased, the airflow leakage amount at the sealing assembly 100 is further reduced, and the thermal efficiency of the gas turbine is improved.
In some embodiments, as shown in fig. 5, each of the plurality of honeycomb core cells is a baffled honeycomb core cell 104. Therefore, by arranging the partition plate 1043 in each honeycomb core grid, the effective flow area between the grid tooth 2 and the honeycomb core grid can be more effectively reduced, so that the gas loss of the gas turbine is further reduced, and the heat efficiency of the gas turbine is improved.
In some embodiments, seal segment 103 includes a first seal segment 101 and a second seal segment 102, with first seal segment 101 and second seal segment 102 being spaced apart along an axial direction of the seal ring. The grate 2 comprises a first grate 201 and a second grate 202, wherein the outer peripheral surface of the first grate 201 is matched with the inner peripheral surface of the first sealing section 101, and the outer peripheral surface of the second grate 202 is matched with the inner peripheral surface of the second sealing section 102.
As shown in fig. 1, the seal ring 1 includes a first seal segment 101 and a second seal segment 102 arranged in the left-right direction, an outer circumferential surface of the first labyrinth 201 is clearance-fitted with an inner circumferential surface of the first seal segment 101, and an outer circumferential surface of the second labyrinth 202 is clearance-fitted with an inner circumferential surface of the second seal segment 102.
Optionally, the second gas channel 108 is located between the first seal segment 101 and the second seal segment 102 in the axial direction of the seal ring 1.
In some embodiments, the honeycomb core cells are hexagonal in cross-section.
Of course, in other embodiments, the cross-section of the honeycomb core cells may be rectangular, triangular, or diamond-shaped.
In some embodiments, the longitudinal section of the labyrinth comprises a rectangular portion and a trapezoidal portion connected in series, the rectangular portion being disposed closer to the sealing ring 1 than the trapezoidal portion in the axial direction of the sealing ring 1.
In other embodiments, the longitudinal section of the grate may be triangular.
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 devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
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 connected internally or in any other suitable relationship, unless expressly stated 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.
In the present disclosure, the terms "one embodiment," "some embodiments," "an example," "a specific example," or "some examples" and the like mean that a specific feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. 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.
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 (13)
1. A seal assembly, comprising:
the sealing ring is used for being arranged on a stator blade root of a gas turbine and comprises a sealing section, the inner circumferential surface of the sealing section is provided with a plurality of honeycomb core grids, at least one of the honeycomb core grids is a partition plate honeycomb core grid, a partition plate is arranged in the partition plate honeycomb core grid, and the partition plate extends along the radial direction of the sealing ring so as to divide the partition plate honeycomb core grid into a plurality of cavity units;
the grate is arranged on the outer edge of a turbine wheel disc of the gas turbine, and the outer peripheral surface of the grate is matched with the inner peripheral surface of the sealing section.
2. The seal assembly of claim 1, wherein the labyrinth is disposed radially of the seal ring in correspondence with the baffled honeycomb core cells.
3. The seal assembly of claim 2, wherein the divider plate is disposed radially of the seal ring in spaced relation to the bottom wall of the compartmented honeycomb core cell so that outer ends of a plurality of the cavity units communicate, at least two of the cavity units being disposed axially of the seal ring.
4. The seal assembly of claim 3, wherein the ratio of the dimension of the divider plate in the radial direction of the seal ring to the dimension of the compartmented honeycomb core cell in the radial direction of the seal ring is from 0.7 to 0.9.
5. The seal assembly of claim 3, wherein a portion of the plurality of honeycomb core cells are the baffled honeycomb core cells and another portion of the plurality of honeycomb core cells are non-baffled honeycomb core cells.
6. The seal assembly of claim 5, wherein each of the baffled and non-baffled honeycomb core cells is provided in a plurality of sets, the plurality of sets of baffled and non-baffled honeycomb core cells being alternately arranged in an axial direction of the seal ring;
the plurality of the grid teeth are arranged at intervals along the axial direction of the sealing ring, a tooth cavity is defined between every two adjacent grid teeth, each grid tooth in the plurality of the grid teeth is arranged in a one-to-one correspondence mode with the plurality of groups of partition plate honeycomb core grids in the radial direction of the sealing ring, and each tooth cavity in the plurality of the grid teeth is arranged in a one-to-one correspondence mode with the plurality of groups of partition plate-free honeycomb core grids in the radial direction of the sealing ring.
7. The seal assembly of claim 6, wherein each group of the plurality of rows of the plurality of the spacer honeycomb core cells.
8. The seal assembly of claim 5, wherein the seal ring has axially opposed inlet and outlet ends, the inlet end for fluid to enter the seal assembly and the outlet end for fluid to exit the seal assembly, the baffled honeycomb core cell being disposed axially of the seal ring closer to the inlet end than the baffle-free honeycomb core cell.
9. The seal assembly of claim 8, wherein the plurality of rows of the baffle core cells are arranged in an axial direction of the seal ring, and at least a portion of the labyrinth is located between two adjacent rows of the baffle core cells in the axial direction of the seal ring.
10. The seal assembly of any of claims 1-4, wherein each of the plurality of honeycomb core cells is a baffled honeycomb core cell.
11. The seal assembly of any one of claims 1-9, wherein the separator plate has a cross-shaped or T-shaped cross-section.
12. The seal assembly according to any one of claims 1 to 9, wherein the seal section comprises a first seal section and a second seal section, the first seal section and the second seal section are arranged at intervals along the axial direction of the seal ring, the labyrinth comprises a first labyrinth tooth and a second labyrinth tooth, the outer circumferential surface of the first labyrinth tooth is matched with the inner circumferential surface of the first seal section, and the outer circumferential surface of the second labyrinth tooth is matched with the inner circumferential surface of the second seal section.
13. A gas turbine engine, comprising:
a turbine wheel disc;
a first movable blade and a second movable blade, each of the first movable blade and the second movable blade being provided at an outer edge of the turbine disk;
the fixed blade of the cylinder surrounds the turbine wheel disc and is positioned between the first movable blade and the second movable blade; and
a seal assembly according to any one of claims 1 to 12.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111333881.5A CN114151143B (en) | 2021-11-11 | 2021-11-11 | Gas turbine and seal assembly thereof |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111333881.5A CN114151143B (en) | 2021-11-11 | 2021-11-11 | Gas turbine and seal assembly thereof |
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| CN114151143A true CN114151143A (en) | 2022-03-08 |
| CN114151143B CN114151143B (en) | 2023-11-10 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020108360A1 (en) * | 2001-02-09 | 2002-08-15 | Mikio Ishihara | Honeycomb structure constituted by main and sub honeycomb structures |
| JP2011226559A (en) * | 2010-04-20 | 2011-11-10 | Mitsubishi Heavy Ind Ltd | Machinable honeycomb sealant material and gas turbine |
| US20180045054A1 (en) * | 2016-08-15 | 2018-02-15 | Rolls-Royce Plc | Inter-stage cooling for a turbomachine |
| CN107939455A (en) * | 2017-11-10 | 2018-04-20 | 中国联合重型燃气轮机技术有限公司 | Gas turbine and its seal assembly |
| US20190010819A1 (en) * | 2017-07-07 | 2019-01-10 | MTU Aero Engines AG | Turbomachine sealing element |
| CN110017180A (en) * | 2017-12-13 | 2019-07-16 | 劳斯莱斯有限公司 | Improved sealing element |
-
2021
- 2021-11-11 CN CN202111333881.5A patent/CN114151143B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020108360A1 (en) * | 2001-02-09 | 2002-08-15 | Mikio Ishihara | Honeycomb structure constituted by main and sub honeycomb structures |
| JP2011226559A (en) * | 2010-04-20 | 2011-11-10 | Mitsubishi Heavy Ind Ltd | Machinable honeycomb sealant material and gas turbine |
| US20180045054A1 (en) * | 2016-08-15 | 2018-02-15 | Rolls-Royce Plc | Inter-stage cooling for a turbomachine |
| US20190010819A1 (en) * | 2017-07-07 | 2019-01-10 | MTU Aero Engines AG | Turbomachine sealing element |
| CN107939455A (en) * | 2017-11-10 | 2018-04-20 | 中国联合重型燃气轮机技术有限公司 | Gas turbine and its seal assembly |
| CN110017180A (en) * | 2017-12-13 | 2019-07-16 | 劳斯莱斯有限公司 | Improved sealing element |
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| Publication number | Publication date |
|---|---|
| CN114151143B (en) | 2023-11-10 |
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