CN221547052U - Turbine housing for gas turbine and gas turbine with turbine housing - Google Patents
Turbine housing for gas turbine and gas turbine with turbine housing Download PDFInfo
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- CN221547052U CN221547052U CN202323291601.6U CN202323291601U CN221547052U CN 221547052 U CN221547052 U CN 221547052U CN 202323291601 U CN202323291601 U CN 202323291601U CN 221547052 U CN221547052 U CN 221547052U
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- extending wall
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- 238000007789 sealing Methods 0.000 claims abstract description 149
- 238000005192 partition Methods 0.000 claims abstract description 34
- 238000001816 cooling Methods 0.000 claims abstract description 14
- 238000000576 coating method Methods 0.000 claims description 25
- 239000011248 coating agent Substances 0.000 claims description 23
- 238000005299 abrasion Methods 0.000 claims description 19
- 238000000034 method Methods 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 10
- 238000009434 installation Methods 0.000 abstract description 5
- 230000002035 prolonged effect Effects 0.000 description 4
- 238000002485 combustion reaction Methods 0.000 description 3
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 125000006850 spacer group Chemical group 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 239000011247 coating layer Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present disclosure provides a turbine housing for a gas turbine and a gas turbine having the same. A turbine housing for a gas turbine, comprising: a turbine outer casing (1); a turbine inner case (6) that is provided inside the turbine outer case (1) coaxially with the turbine outer case (1); one or more diaphragms (4) arranged between the outer turbine casing (1) and the inner turbine casing (6) to isolate adjacent cooling chambers (7); and outer sealing strip (2) and interior sealing strip (5), its characterized in that: the outer sealing strip (2) and the inner sealing strip (5) are L-shaped sealing strips with L-shaped cross sections, and comprise a radial extending wall (L1) and a circumferential extending wall (L2); the outer sealing strip (2) and the inner sealing strip (5) are arranged such that their radially extending walls (L1) are located on the low pressure side of the sealing strip mounting groove. The present disclosure improves convenience of partition installation while ensuring a partition sealing effect.
Description
Technical Field
The disclosure belongs to the technical field of gas turbines, and particularly relates to a turbine shell for a gas turbine and the gas turbine with the turbine shell.
Background
The gas turbine mainly comprises three parts, namely a gas compressor, a combustion chamber and a turbine. The air enters the compressor and is compressed into high-temperature high-pressure air, the air is supplied to the combustion chamber for fuel combustion, and the generated high-temperature high-pressure gas expands in the turbine to do work. The improvement of the temperature before the turbine is a main technical measure for improving the output and the thermal efficiency of the gas turbine, the temperature before the turbine reaches 1600 ℃ to date, which is far higher than the metal melting temperature, and in order to achieve the index, the high-temperature part of the gas turbine must be cooled, so that the structural strength and the service life of the high-temperature part of the gas turbine are ensured. The high temperature components of the turbine are typically cooled or sealed from the compressor bleed air using external bleed air lines or internal runner structures, which are designed to form a secondary air cooling system for the gas turbine. Thus, secondary air cooling systems become one of the key issues in gas turbine design.
At present, a gas turbine generally adopts a multi-stage turbine design, the working temperature and the pressure are reduced step by step, and the secondary air cooling system correspondingly adopts a multi-stage bleed air design in consideration of the performance of the whole machine, namely, the front stage of the turbine introduces compressed air of a relatively high compressor stage, and the rear stage of the turbine introduces compressed air of a relatively low compressor stage. The multistage bleed air design ensures that each stage of the turbine works stably and reliably under a reasonable working temperature environment, and can reduce work loss caused by bleed air to the maximum extent so as to improve the output and efficiency of the unit.
Chinese patent publication No. CN110761904a discloses a cooling system, a cold air chamber sealing structure and a sealing partition plate of a gas turbine. When the sealing partition plate of the cold air chamber of the gas turbine is utilized to separate the sealing chamber of the gas turbine, the annular sealing partition plate formed by splicing the two semi-annular partition plates is arranged between the spliced end parts of the two semi-annular partition plates, so that the butt joint gap of the two semi-annular partition plates is sealed, the two first U-shaped sealing strips at the outer edges of the two semi-annular partition plates are spliced into an outer sealing ring, the two second U-shaped sealing strips at the inner edges of the two semi-annular partition plates are spliced into an inner sealing ring, the side surface of the inner sealing ring is in compression sealing fit with the side surface of the annular sealing groove on the cylindrical shell of the rotor of the gas turbine under the action of air pressure difference at the two sides of the sealing partition plates, and the side surface of the outer sealing ring is in compression sealing fit with the side surface of the annular sealing groove on the sealing cylinder body of the secondary air cooling system.
The U-shaped sealing strip has good cooling sealing effect, but the two side walls of the U-shaped sealing strip are respectively tightly matched with the annular sealing groove and the semi-annular partition plate on the cylindrical shell in a pressing state, so that the resistance in the installation process is large, and the installation is inconvenient.
Moreover, in the working process of the gas turbine, the U-shaped sealing strip is easy to fail due to abrasion, and the service life is lower. While wear always occurs between the diaphragm and the housing recess. This problem needs to be solved.
Disclosure of utility model
One technical problem to be solved by the present disclosure is to provide a turbine housing for a gas turbine and a gas turbine having the same, so that installation of a partition plate and a sealing strip is more convenient.
Another technical problem to be solved by the present disclosure is to provide a turbine housing for a gas turbine and a gas turbine having the same, so that wear of a sealing strip can be reduced and a service life thereof can be prolonged.
To solve at least one of the above technical problems, according to one aspect of the present disclosure, there is provided a turbine housing for a gas turbine, comprising: a turbine outer housing having a turbine center axis; a turbine inner casing coaxially disposed inside the turbine outer casing with a plurality of annular cooling chambers arranged in an air flow direction formed therebetween; one or more diaphragms disposed between the turbine outer casing and the turbine inner casing, isolating adjacent ones of the cooling cavities; and the outer sealing strip and the inner sealing strip, the outer sealing strip sets up in the sealing strip mounting groove of turbine shell body, and be located the baffle with between the turbine shell body, the inner sealing strip sets up in the sealing strip mounting groove of turbine inner shell body, and be located the baffle with between the turbine inner shell body, its characterized in that: the outer sealing strip and the inner sealing strip are L-shaped sealing strips with L-shaped cross sections and comprise a radial extending wall and a circumferential extending wall; the outer seal strip is configured such that the radially extending wall of the outer seal strip is located on a low pressure side of a seal strip mounting groove of the turbine outer casing with respect to an outer edge of a diaphragm, and the circumferentially extending wall of the outer seal strip is located radially outward of the outer edge of the diaphragm; the inner seal strip is configured such that the radially extending wall thereof is located on a low pressure side of a seal strip mounting groove of the turbine outer casing with respect to an inner edge of a diaphragm, and the circumferentially extending wall of the inner seal strip is located radially inward of the inner edge of the diaphragm.
Preferably, wherein the diaphragm is arranged in a plane perpendicular to the turbine central axis.
In the present disclosure, since the outer sealing strip and the inner sealing strip are both L-shaped sealing strips, and the radially extending wall of the L-shaped sealing strip is located on the low pressure side of the turbine outer casing/turbine inner casing, so that when the diaphragm is in contact with the sealing strip mounting grooves on the turbine outer casing and the turbine inner casing, only the low pressure side of the outer edge/inner edge of the diaphragm is in contact with the L-shaped sealing strip, while the other side is in contact with the high pressure side of the rigid sealing strip mounting groove, the diaphragm can be conveniently mounted into the sealing strip mounting groove along the high pressure side of the rigid sealing strip mounting groove. Meanwhile, the hot air flow from the high pressure side can press the outer edge and the inner edge of the partition plate against the radial extension wall of the L-shaped sealing strip positioned on the low pressure side in the working state, so that the sealing effect can be ensured.
Further, the L-shaped sealing strip is provided with an abrasion-resistant coating.
In the present disclosure, since the L-shaped sealing strip has the abrasion-resistant coating, the service life of the sealing strip is improved, and the time and economic cost required for replacing the abrasion parts are reduced.
Further, the wear-resistant coating of the L-shaped sealing strip is located at least on the high pressure side and/or the low pressure side of the radially extending wall.
In the present disclosure: the two sides of the radial extending wall are main wearing parts, and the circumferential extending wall is less worn, so that the wear-resistant coating is mainly arranged on the high-pressure side and/or the low-pressure side of the radial extending wall, the wear-resistant coating is not required to be arranged on the circumferential extending wall, the good wear-resistant effect can be achieved, and the service life of the sealing strip is prolonged.
Further, the low pressure side walls of the sealing strip mounting grooves of the turbine outer shell and the turbine inner shell are provided with wear-resistant coatings.
In the present disclosure, by providing the abrasion-resistant coating on the low pressure side wall of the seal strip mounting groove, the abrasion resistance of the seal strip mounting groove of the turbine outer casing and the turbine inner casing is improved, thereby improving the service lives of the turbine outer casing and the turbine inner casing.
Further, the high pressure side walls of the sealing strip mounting grooves of the turbine outer shell and the turbine inner shell are provided with wear-resistant coatings.
In the present disclosure, by providing the wear-resistant coating on the high pressure side sidewall of the seal strip mounting groove, the wear caused by the inner edge/outer edge of the separator to the high pressure side sidewall of the seal strip mounting groove is reduced, and the wear resistance of the seal strip mounting grooves of the turbine outer casing and the turbine inner casing is further improved, thereby further improving the service lives of the turbine outer casing and the turbine inner casing.
Further, the circumferentially extending wall of the outer seal strip is mounted to the bottom of the seal strip mounting groove of the turbine outer casing, and a radial gap is formed between the outer edge of the partition plate and the circumferentially extending wall of the outer seal strip; and/or the circumferentially extending wall of the inner sealing strip is mounted to the groove bottom of the sealing strip mounting groove of the turbine inner shell, and a radial gap is formed between the inner edge of the partition plate and the circumferentially extending wall of the inner sealing strip.
In the present disclosure, by providing a gap between the outer edge and/or the inner edge of the separator and the circumferentially extending wall of the corresponding L-shaped sealing strip, the separator is easier to install while the sealing effect of the L-shaped sealing strip is not affected.
Further, positioning pins on the low pressure side of the respective seal strip mounting grooves are also provided on the turbine outer casing and the turbine inner casing, the positioning pins passing at least partially through the radially extending walls of the respective L-shaped seal strips to secure the respective L-shaped seal strips.
In the present disclosure, the L-shaped sealing strip is fixed by using the positioning pin, so that the use safety is ensured.
Further, the number of the outer sealing strips and the number of the inner sealing strips are multiple; the plurality of outer sealing strips jointly form an outer sealing ring; the plurality of inner sealing strips jointly form an inner sealing ring.
In the turbine shell, the outer sealing ring and the inner sealing ring are formed by a plurality of outer sealing strips and inner sealing strips, so that the turbine shell is more convenient to assemble and replace worn parts.
Further, the number of the partition plates is two, each partition plate forms a semi-annular shape, and the two partition plates jointly form an integral partition plate ring.
In the present disclosure, by making the diaphragm annular split structure, assembly of the turbine housing and replacement of the wear components is facilitated.
According to another aspect of the present disclosure, there is also provided a gas turbine, characterized by comprising a turbine housing as claimed in any one of the preceding claims.
In the present disclosure, the gas turbine not only facilitates the installation of the partition plate and the sealing strip, but also reduces the abrasion of the sealing strip and improves the service life thereof.
Drawings
The accompanying drawings, which are included to provide a further understanding of the disclosure, illustrate and explain the present disclosure, and together with the description serve to explain the present disclosure. In the drawings:
FIG. 1 is a schematic structural view of a turbine housing of the present disclosure.
Reference numerals illustrate:
| 1. A turbine outer housing; | 2. An outer sealing strip; | 21. an inner protrusion; |
| 3. a positioning pin; | 4. A partition plate; | 5. an inner sealing strip; |
| 6. A turbine inner housing; | 61. an outer protrusion; | 7. a cooling chamber; |
| L1, a radially extending wall; | L2, a circumferentially extending wall; | g. radial clearance. |
Detailed Description
The following description of the technical solutions in the embodiments of the present disclosure will be made clearly and completely with reference to the accompanying drawings in the embodiments of the present disclosure, and it is apparent that the described embodiments are only some embodiments of the present disclosure, not all embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the disclosure, its application, or uses. All other embodiments, which can be made by one of ordinary skill in the art without inventive effort, based on the embodiments in this disclosure are intended to be within the scope of this disclosure.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments in accordance with the present disclosure. As used herein, the singular is intended to include the plural unless the context clearly indicates otherwise.
FIG. 1 is a schematic structural view of a turbine housing of the present disclosure.
Referring to FIG. 1, the present disclosure provides a turbine housing for a gas turbine, comprising: a turbine outer case 1 having a turbine center axis; a turbine inner casing 6 coaxially provided inside the turbine outer casing 1 with the turbine outer casing 1, a plurality of annular cooling chambers 7 arranged in the air flow direction being formed between the turbine outer casing 1 and the turbine inner casing 6; one or more diaphragms 4 provided between the turbine outer casing 1 and the turbine inner casing 6, isolating adjacent cooling cavities 7; and the outer sealing strip 2 and the inner sealing strip 5, wherein the outer sealing strip 2 is arranged in a sealing strip mounting groove of the turbine outer shell 1 and is positioned between the partition plate 4 and the turbine outer shell 1, and the inner sealing strip 5 is arranged in a sealing strip mounting groove of the turbine inner shell 6 and is positioned between the partition plate 4 and the turbine inner shell 6.
It can also be seen from fig. 1 that the outer sealing strip 2 and the inner sealing strip 5 are each L-shaped sealing strips having an L-shaped cross section, comprising one radially extending wall L1 and one circumferentially extending wall L2.
The outer seal strip 2 is configured such that the radially extending wall L1 of the outer seal strip 2 is located on the low pressure side of the seal strip mounting groove of the turbine outer casing 1 with respect to the outer edge of the diaphragm 4. Also, the circumferentially extending wall L2 of the outer seal strip 2 is located radially outside the outer edge of the separator 4. Also, the inner seal 5 is configured such that its radially extending wall L1 is located on the low pressure side of the seal mounting groove of the turbine outer casing 1 with respect to the inner edge of the bulkhead 4, and the circumferentially extending wall L2 of the inner seal 5 is located radially inward of the inner edge of the bulkhead 4.
It can also be seen from fig. 1 that the partition 4 is arranged in a plane perpendicular to the centre axis of the turbine.
Since the outer seal strip 2 and the inner seal strip 5 are both L-shaped seal strips, and the radially extending wall of the L-shaped seal strips is located on the low pressure side of the turbine outer casing 1/turbine inner casing 6, so that the diaphragm 4, when fitted with the seal strip mounting grooves on the turbine outer casing 1 and the turbine inner casing 6, only the low pressure side of the outer rim/inner rim of the diaphragm 4 is in contact fit with the L-shaped seal strips, while the other side is in fit with the high pressure side of the rigid seal strip mounting groove, the diaphragm 4 can be conveniently fitted into the seal strip mounting groove along the high pressure side of the rigid seal strip mounting groove. At the same time, the hot air flow from the high pressure side can press the outer edge and the inner edge of the partition board against the radial extension wall L1 of the L-shaped sealing strip positioned at the low pressure side in the working state, so that the sealing effect can be ensured.
In the present embodiment shown in fig. 1, the L-shaped sealing strip has an abrasion-resistant coating. Because the L-shaped sealing strip is provided with the wear-resistant coating, the service life of the sealing strip is prolonged, and the time and the economic cost for replacing the wear part are reduced.
As an alternative embodiment, the wear-resistant coating of the L-shaped sealing strip is located at least on the high pressure side or the low pressure side of the radially extending wall L1. More specifically, in another embodiment not shown,
The two sides of the radial extending wall L2 are main wearing parts, and the circumferential extending wall L2 is less worn, so that the wear-resistant coating is mainly arranged on the high-pressure side and/or the low-pressure side of the radial extending wall L1, and the wear-resistant coating is not required to be arranged on the circumferential extending wall L2, so that the good wear-resistant effect can be achieved, and the service life of the sealing strip is prolonged.
In a not shown embodiment, the low pressure side walls of the seal mounting grooves of the turbine outer casing 1 and the turbine inner casing 6 are provided with an abrasion resistant coating.
By providing the abrasion-resistant coating on the low-pressure side wall of the seal strip mounting groove, the abrasion resistance of the seal strip mounting groove of the turbine outer casing 1 and the turbine inner casing 6 is improved, thereby improving the service lives of the turbine outer casing 1 and the turbine inner casing 6.
In an embodiment not shown, the high pressure side wall of the seal strip mounting groove of the turbine outer casing 1 and the turbine inner casing 6 is provided with the wear-resistant coating, or the high pressure side wall and the low pressure side wall of the seal strip mounting groove may be provided with the wear-resistant coating.
By providing the wear-resistant coating on the high pressure side wall of the seal strip mounting groove, the wear caused by the inner edge/outer edge of the partition plate 4 to the high pressure side wall of the seal strip mounting groove is reduced, and the wear resistance of the seal strip mounting grooves of the turbine outer casing 1 and the turbine inner casing 6 is further improved, thereby further improving the service lives of the turbine outer casing 1 and the turbine inner casing 6.
It can also be seen from fig. 1 that the circumferentially extending wall L2 of the outer seal strip 2 is mounted to the groove bottom of the seal strip mounting groove of the turbine outer casing 1 with a radial gap g between the outer edge of the bulkhead 4 and the circumferentially extending wall L2 of the outer seal strip 2, and that the circumferentially extending wall L2 of the inner seal strip 5 is mounted to the groove bottom of the seal strip mounting groove of the turbine inner casing 6 with a radial gap g between the inner edge of the bulkhead 4 and the circumferentially extending wall L2 of the inner seal strip 5. In alternative embodiments, it is also possible to have a gap g only between the outer edge of the separator 4 and the circumferentially extending wall L2 of the outer seal strip 2, or to have a gap g only between the inner edge of the separator 4 and the circumferentially extending wall L2 of the inner seal strip 5.
By providing a gap between the outer and/or inner edge of the spacer 4 and the circumferentially extending wall L2 of the respective L-shaped sealing strip, the spacer 4 is made easier to install without affecting the sealing effect of the L-shaped sealing strip.
It can also be seen from fig. 1 that the turbine outer casing 1 and the turbine inner casing 6 are further provided with a positioning pin 3 at the low pressure side of the respective sealing strip mounting groove, the positioning pin 3 at least partially penetrating the radially extending wall L1 of the respective L-shaped sealing strip to fix the respective L-shaped sealing strip.
The L-shaped sealing strip is fixed by using the locating pin 3, so that the use safety is ensured.
In a not shown embodiment, the outer sealing strip 2 and the inner sealing strip 5 are each plural; the plurality of outer sealing strips 2 together form an outer sealing ring; the plurality of inner sealing strips 5 together form an inner sealing ring.
The outer sealing ring and the inner sealing ring are formed by a plurality of outer sealing strips and inner sealing strips, so that the turbine shell is more convenient to assemble and replace abrasion parts.
In an embodiment not shown, the number of baffles 4 is two, each baffle 4 forming a semi-ring shape, the two baffles 4 together forming an integral baffle ring. By making the diaphragm annular into a split configuration, assembly of the turbine housing and replacement of wear parts is facilitated.
According to another aspect of the present disclosure, there is also provided a gas turbine comprising a turbine housing of any one of the preceding claims. The gas turbine not only facilitates the installation of the partition plate and the sealing strip, but also reduces the abrasion of the sealing strip and prolongs the service life of the sealing strip.
The present disclosure has the following technical effects, particularly technical effects brought about by the improvement points.
The wear-resistant coating between the diaphragm ring formed by the diaphragm and the turbine housing (either the inner or outer turbine housing) enables easy replacement of potential wear parts without the need to replace turbine housing parts.
One or more L-shaped sealing strips (outer sealing strip 2 and inner sealing strip 5) having an abrasion-resistant coating layer form a sealing ring of L-shaped cross section, are mounted on the low pressure side walls of the sealing strip mounting grooves of the turbine outer casing 1 and the turbine inner casing 6, and are fixed by the positioning pins 3. The L-section seal ring may be split into two or more sections (i.e., a plurality of L-shaped seal strips) at a horizontal or other location along the turbine casing flange with a smaller gap between each L-shaped seal strip during assembly. Both surfaces of the L-shaped sealing strip and the separator are coated with an abrasion-resistant coating to prevent surface abrasion. There is also a gap between the separator and the L-shaped weather strip in the radial direction. If wear problems occur, the L-ring component can be replaced with a new component without the need to repair a large housing component.
The foregoing is merely a preferred embodiment of the present disclosure and it should be noted that modifications and adaptations to those skilled in the art may be made without departing from the principles of the present disclosure and are intended to be comprehended within the scope of the present disclosure.
Claims (10)
1. A turbine housing for a gas turbine, comprising:
A turbine outer case (1) having a turbine center axis;
A turbine inner casing (6) coaxially provided inside the turbine outer casing (1) with the turbine outer casing (1), and a plurality of annular cooling chambers (7) arranged in the air flow direction are formed between the turbine outer casing (1) and the turbine inner casing (6);
One or more diaphragms (4) arranged between the turbine outer casing (1) and the turbine inner casing (6) to isolate adjacent cooling chambers (7); and
The outer sealing strip (2) and the inner sealing strip (5), the outer sealing strip (2) is arranged in a sealing strip mounting groove of the turbine outer shell (1) and is positioned between the baffle plate (4) and the turbine outer shell (1), the inner sealing strip (5) is arranged in a sealing strip mounting groove of the turbine inner shell (6) and is positioned between the baffle plate (4) and the turbine inner shell (6),
The method is characterized in that:
The outer sealing strip (2) and the inner sealing strip (5) are L-shaped sealing strips with L-shaped cross sections, and each sealing strip comprises a radial extending wall (L1) and a circumferential extending wall (L2);
The outer seal strip (2) is configured such that the radially extending wall (L1) of the outer seal strip (2) is located on a low pressure side of a seal strip mounting groove of the turbine outer casing (1) with respect to an outer edge of a bulkhead (4), and the circumferentially extending wall (L2) of the outer seal strip (2) is located radially outside of the outer edge of the bulkhead (4);
The inner seal strip (5) is configured such that the radially extending wall (L1) thereof is located on a low pressure side of a seal strip mounting groove of the turbine outer casing (1) with respect to an inner edge of a bulkhead (4), and the circumferentially extending wall (L2) of the inner seal strip (5) is located radially inward of the inner edge of the bulkhead (4).
2. The turbine housing of claim 1, wherein the turbine housing is configured to receive the turbine housing,
The L-shaped sealing strip is provided with an abrasion-resistant coating.
3. The turbine housing of claim 2, wherein the turbine housing is configured to receive the turbine housing,
The wear-resistant coating of the L-shaped sealing strip is located at least on the high-pressure side and/or the low-pressure side of the radially extending wall (L1).
4. The turbine housing of claim 3,
The low-pressure side wall of the sealing strip mounting groove of the turbine outer shell (1) and the turbine inner shell (6) is provided with an abrasion-resistant coating.
5. The turbine housing of claim 4,
The high-pressure side wall of the sealing strip mounting groove of the turbine outer shell (1) and the turbine inner shell (6) is provided with an abrasion-resistant coating.
6. The turbine housing of claim 1, wherein the turbine housing is configured to receive the turbine housing,
The circumferentially extending wall (L2) of the outer sealing strip (2) is mounted to the bottom of a sealing strip mounting groove of the turbine outer shell (1), and a radial gap (g) is formed between the outer edge of the partition plate (4) and the circumferentially extending wall (L2) of the outer sealing strip (2); and/or
The circumferentially extending wall (L2) of the inner seal strip (5) is mounted to the groove bottom of a seal strip mounting groove of the turbine inner casing (6), and a radial gap (g) is formed between the inner edge of the partition plate (4) and the circumferentially extending wall (L2) of the inner seal strip (5).
7. The turbine housing of claim 1, wherein the turbine housing is configured to receive the turbine housing,
The turbine outer casing (1) and the turbine inner casing (6) are further provided with positioning pins (3) located on the low pressure side of the corresponding sealing strip mounting grooves, and the positioning pins (3) at least partially penetrate through the radially extending walls (L1) of the corresponding L-shaped sealing strips to fix the corresponding L-shaped sealing strips.
8. The turbine housing of claim 1, wherein the turbine housing is configured to receive the turbine housing,
The number of the outer sealing strips (2) and the number of the inner sealing strips (5) are multiple;
A plurality of outer sealing strips (2) jointly form an outer sealing ring; a plurality of inner sealing strips (5) jointly form an inner sealing ring.
9. The turbine housing of claim 1, wherein the turbine housing is configured to receive the turbine housing,
The number of the partition boards (4) is two, each partition board (4) forms a semi-annular shape, and the two partition boards (4) together form an integral partition board ring.
10. Gas turbine comprising a turbine housing according to any of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323291601.6U CN221547052U (en) | 2023-12-04 | 2023-12-04 | Turbine housing for gas turbine and gas turbine with turbine housing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202323291601.6U CN221547052U (en) | 2023-12-04 | 2023-12-04 | Turbine housing for gas turbine and gas turbine with turbine housing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221547052U true CN221547052U (en) | 2024-08-16 |
Family
ID=92252127
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202323291601.6U Active CN221547052U (en) | 2023-12-04 | 2023-12-04 | Turbine housing for gas turbine and gas turbine with turbine housing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN221547052U (en) |
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2023
- 2023-12-04 CN CN202323291601.6U patent/CN221547052U/en active Active
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