CN217080906U - Gas turbine compressor stator blade mounting structure - Google Patents
Gas turbine compressor stator blade mounting structure Download PDFInfo
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- CN217080906U CN217080906U CN202221582287.XU CN202221582287U CN217080906U CN 217080906 U CN217080906 U CN 217080906U CN 202221582287 U CN202221582287 U CN 202221582287U CN 217080906 U CN217080906 U CN 217080906U
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- stator blade
- mounting ring
- tenon
- rectangular
- dovetail
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Abstract
A stator blade mounting structure of a gas turbine compressor comprises stator blades, an outer mounting ring and an inner mounting ring; the outer end part of the stator blade is provided with a dovetail tenon, and the inner end part of the stator blade is provided with a rectangular tenon; the inner side surface of the outer mounting ring is provided with a dovetail-shaped mortise, and a dovetail-shaped tenon of the stator blade is in inserting fit with the dovetail-shaped mortise; the outer side surface of the inner mounting ring is provided with a rectangular mortise, and a rectangular tenon of the stator blade is in inserted fit with the rectangular mortise; the outer mounting ring is provided with a threaded hole, a positioning screw is arranged in the threaded hole, and the outer mounting ring and the air cylinder are fixed through the positioning screw; the inner mounting ring and the rectangular tenon are coaxially provided with positioning pin holes, positioning pins are arranged in the positioning pin holes, and the stator blade and the inner mounting ring are fixed through the positioning pins; and the inner side surface of the inner mounting ring is provided with a ring groove for mounting the honeycomb component. The utility model discloses can further simplify the cylinder structure, make the cylinder rigidity obtain the reinforcing, the stator blade forms two fulcrum structures, and every stator blade all can independently be changed.
Description
Technical Field
The utility model belongs to the technical field of gas turbine, especially, relate to a gas turbine compressor stator blade mounting structure.
Background
At present, the stator blade of the gas turbine adopts two mounting structures, wherein the first mounting structure is a direct fixed mounting structure, and the second mounting structure is an indirect fixed mounting structure. For the stator blade of the gas turbine adopting the direct fixed mounting structure, the stator blade is directly fixed in a special-shaped annular groove on the inner wall of a cylinder through tenons in different forms. For a gas turbine stator vane with an indirect fixed mounting structure, the stator vane is mounted in a full ring or a half ring of a feature and forms an assembly, and a honeycomb is welded inside the assembly and finally fixed in a cylinder.
However, when the stator blade of the gas turbine adopts a direct fixed mounting structure, the problems of complex cylinder processing and high precision requirement exist, and the grooves and holes at the connecting part weaken the rigidity of the cylinder. When the stator blade of the gas turbine adopts an indirect fixed mounting structure, although the cylinder structure is simplified, the stator blade cannot be independently replaced, residual stress is easily generated at a welding position, and fatigue fracture is easily generated after long-time operation. In addition, two kinds of current gas turbine stator blade mounting structure, its stator blade all belong to single pivot structure, consequently can't solve because the blade that airflow pulsation leads to produces the vibration crackle and then takes place the problem of destruction.
SUMMERY OF THE UTILITY MODEL
Aiming at the problems in the prior art, the utility model provides a stator blade mounting structure of a gas turbine compressor, which is characterized in that an inner mounting ring and an outer mounting ring are configured for a stator blade, so that the structure of a cylinder can be further simplified, the rigidity of the cylinder is enhanced, and the cylinder is not easy to deform; through the configuration of the inner mounting ring and the outer mounting ring, the stator blade forms a double-pivot structure, the stress condition of the stator blade can be obviously improved, and the service life of the stator blade is prolonged; all stator blades and the inner mounting ring and the outer mounting ring are connected in an inserting mode, so that any one stator blade can have the capability of independent replacement and maintenance.
In order to achieve the above purpose, the utility model adopts the following technical scheme: a stator blade mounting structure of a gas turbine compressor comprises stator blades, an outer mounting ring and an inner mounting ring; the outer end part of the stator blade is provided with a dovetail tenon, and the inner end part of the stator blade is provided with a rectangular tenon; the inner side surface of the outer mounting ring is provided with a dovetail mortise, and a dovetail tenon at the outer end part of the stator blade is in inserted fit with the dovetail mortise; the outer side surface of the inner mounting ring is provided with a rectangular mortise, and a rectangular tenon at the inner end part of the stator blade is in inserting fit with the rectangular mortise.
And a threaded hole is formed in the outer mounting ring, a positioning screw is arranged in the threaded hole, and the outer mounting ring and the air cylinder are fixed through the positioning screw.
And positioning pin holes are coaxially formed in the inner mounting ring and the rectangular tenon, positioning pins are arranged in the positioning pin holes, and the stator blade and the inner mounting ring are fixed through the positioning pins.
And the inner side surface of the inner mounting ring is provided with a ring groove for mounting the honeycomb component.
The utility model has the advantages that:
the stator blade mounting structure of the gas turbine compressor of the utility model is provided with the inner mounting ring and the outer mounting ring for the stator blade, so that the structure of the cylinder can be further simplified, the rigidity of the cylinder is enhanced and the cylinder is not easy to deform; through the configuration of the inner mounting ring and the outer mounting ring, the stator blade forms a double-pivot structure, the stress condition of the stator blade can be obviously improved, and the service life of the stator blade is prolonged; all stator blades and the inner mounting ring and the outer mounting ring are connected in an inserting mode, so that any one stator blade can have the capability of independent replacement and maintenance.
Drawings
Fig. 1 is a schematic structural diagram of a mounting structure of a stator blade of a gas turbine compressor of the present invention;
FIG. 2 is a schematic structural view of a stator blade according to the present invention;
fig. 3 is a schematic structural view of the outer mounting ring of the present invention;
fig. 4 is a schematic structural view of the inner mounting ring of the present invention;
in the figure, 1-stator blade, 2-outer mounting ring, 3-inner mounting ring, 4-dovetail tenon, 5-rectangular tenon, 6-dovetail mortise, 7-rectangular mortise, 8-threaded hole, 9-positioning pin hole and 10-annular groove.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
As shown in fig. 1 to 4, a gas turbine compressor stator blade mounting structure comprises a stator blade 1, an outer mounting ring 2 and an inner mounting ring 3; a dovetail tenon 4 is arranged at the outer end part of the stator blade 1, and a rectangular tenon 5 is arranged at the inner end part of the stator blade 1; the inner side surface of the outer mounting ring 2 is provided with a dovetail type mortise 6, and a dovetail type tenon 4 at the outer end part of the stator blade 1 is in inserted fit with the dovetail type mortise 6; the outer side surface of the inner mounting ring 3 is provided with a rectangular mortise 7, and the rectangular tenon 5 at the inner end part of the stator blade 1 is in inserted fit with the rectangular mortise 7.
The outer mounting ring 2 is provided with a threaded hole 8, a positioning screw is arranged in the threaded hole 8, and the outer mounting ring 2 and the air cylinder are fixed through the positioning screw.
The inner mounting ring 3 and the rectangular tenon 5 are coaxially provided with positioning pin holes 9, positioning pins are arranged in the positioning pin holes 9, and the stator blade 1 and the inner mounting ring 3 are fixed through the positioning pins.
On the inner side surface of the inner mounting ring 3 is provided a ring groove 10 for mounting the honeycomb assembly.
Firstly, an outer mounting ring 2 and an inner mounting ring 3 are mounted in place in a cylinder, then, a part of stator blades 1 are uniformly and uniformly mounted in place in the circumferential direction, the dovetail-shaped tenon 4 and the rectangular tenon 5 of each stator blade 1 are guaranteed to be accurately inserted into the corresponding dovetail-shaped mortise 6 and the corresponding rectangular mortise 7, then, the rest stator blades 1 are all mounted in place, then, stator blades 1 with the total number of 1/10 are selected from the stator blades 1 which are mounted in place, positioning pin holes 9 are combined and machined on the corresponding inner mounting ring 3 and the corresponding rectangular tenon 5, positioning pins are mounted in the machined positioning pin holes 9, then, honeycomb components are mounted in the ring grooves 10, and finally, positioning screws are mounted in the threaded holes 8.
Through the inserting and matching of the dovetail tenon 4 at the outer end part of the stator blade 1 and the dovetail mortise 6, the space size of the stator blade 1 is ensured, and the stress distribution at the matching position is improved. Through the inserting and matching of the rectangular tenon 5 and the rectangular mortise 7 at the inner end part of the stator blade 1, on the basis, the installation of the positioning pin is completed between a few stator blades 1 and the inner mounting ring 3 through the positioning pin holes 9, so that the free thermal expansion of the assembly is ensured, the thermal stress is reduced, the reliable centering of the inner mounting ring 3 is also ensured, and the separation is not easy. By installing the honeycomb component in the ring groove 10 of the inner installation ring 3, interstage loss can be effectively reduced, and the efficiency of the compressor is improved.
The embodiments are not intended to limit the scope of the present invention, and all equivalent implementations or modifications that do not depart from the scope of the present invention are intended to be included within the scope of the present invention.
Claims (4)
1. The utility model provides a gas turbine compressor stator blade mounting structure which characterized in that: comprises a stator blade, an outer mounting ring and an inner mounting ring; the outer end part of the stator blade is provided with a dovetail tenon, and the inner end part of the stator blade is provided with a rectangular tenon; the inner side surface of the outer mounting ring is provided with a dovetail mortise, and a dovetail tenon at the outer end part of the stator blade is in inserted fit with the dovetail mortise; the outer side surface of the inner mounting ring is provided with a rectangular mortise, and a rectangular tenon at the inner end part of the stator blade is in inserting fit with the rectangular mortise.
2. The gas turbine compressor stator blade mounting structure of claim 1, wherein: and a threaded hole is formed in the outer mounting ring, a positioning screw is mounted in the threaded hole, and the outer mounting ring is fixed with the cylinder through the positioning screw.
3. The gas turbine compressor stator blade mounting structure of claim 1, wherein: and the inner mounting ring and the rectangular tenon are coaxially provided with positioning pin holes, positioning pins are arranged in the positioning pin holes, and the stator blade is fixed with the inner mounting ring through the positioning pins.
4. The gas turbine compressor stator blade mounting structure of claim 1, wherein: and the inner side surface of the inner mounting ring is provided with a ring groove, and a honeycomb component is mounted in the ring groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221582287.XU CN217080906U (en) | 2022-06-23 | 2022-06-23 | Gas turbine compressor stator blade mounting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221582287.XU CN217080906U (en) | 2022-06-23 | 2022-06-23 | Gas turbine compressor stator blade mounting structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217080906U true CN217080906U (en) | 2022-07-29 |
Family
ID=82503311
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221582287.XU Active CN217080906U (en) | 2022-06-23 | 2022-06-23 | Gas turbine compressor stator blade mounting structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217080906U (en) |
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2022
- 2022-06-23 CN CN202221582287.XU patent/CN217080906U/en active Active
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