CN114215610B - Axial positioning structure of turbine movable blade of gas turbine and mounting and dismounting method - Google Patents
Axial positioning structure of turbine movable blade of gas turbine and mounting and dismounting method Download PDFInfo
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- CN114215610B CN114215610B CN202111454956.5A CN202111454956A CN114215610B CN 114215610 B CN114215610 B CN 114215610B CN 202111454956 A CN202111454956 A CN 202111454956A CN 114215610 B CN114215610 B CN 114215610B
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
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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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- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses an axial positioning structure of a turbine movable blade of a gas turbine, which comprises a movable blade, wherein the movable blade comprises a blade profile, a blade root platform and a blade root, the blade root platform is arranged on the radial inner side of the blade profile, and the blade root is arranged on the radial inner side of the blade root platform; the wheel disc is provided with a blade root groove and a stud hole, and the blade root groove is matched and clamped with the blade root; the tooth-shaped air seal is concentric with the wheel disc and is arranged on the air inlet side of the movable blade; the tooth-shaped air seal is provided with a waist-shaped groove facing the wheel disc and provided with an arc, and a first through hole which is opposite to the stud Kong Pi is arranged in the waist-shaped groove; the outer end part of the tooth-shaped air seal is provided with peripheral teeth; the compression air seal is concentric with the wheel disc and is arranged on the air outlet side of the movable blade; the pressing gas seal is provided with a second through hole which is paired with the stud Kong Pi; the outer end part of the compression air seal extends to the blade root groove; the wheel disc, the tooth-shaped air seal and the compression air seal are fixed through stud nuts. By adopting the axial positioning structure and the mounting and dismounting method for the turbine movable blade of the gas turbine, the manufacturing and maintenance cost can be reduced, and the mounting and dismounting workload of the movable blade can be reduced.
Description
Technical Field
The invention relates to an axial positioning structure of a turbine movable blade of a gas turbine and an installation and disassembly method, and belongs to the technical field of gas turbines.
Background
The turbine movable blade is axially arranged in a blade root groove of the wheel disc through the blade root, the blade root forms of the turbine movable blade comprise T-shaped, fir-tree-shaped and dovetail-shaped, the blade root groove in the wheel disc is axially communicated, and a corresponding turbine movable blade axial positioning structure is needed for preventing the turbine movable blade from sliding in the blade root groove.
Chinese patent application 201680052860.7 discloses a gas turbine device which axially secures a bucket to one side relative to a disk by means of a locking plate, while the device further axially secures a bucket to the other side relative to the disk by means of another locking plate.
At present, the axial positioning of the turbine movable blade in the prior art adopts the limit of the sealing plate, the sealing plate is large in radial extending size, and the centrifugal force of the sealing plate is large in the rotating process, so that the turbine movable blade limit groove is subjected to large centrifugal load in the operating process, and the service life of the turbine movable blade is further shortened.
In the prior art, the dynamic and static air seals are arranged on the air inlet and outlet sides of the wheel disc, so that the wheel disc is large in axial dimension, and the manufacturing cost and the processing difficulty of the wheel disc are increased. Meanwhile, the axial positioning structure is formed by installing a plurality of parts in sequence in the circumferential direction, so that the disassembly and installation workload is large, and the manufacturing and maintenance cost is high. Therefore, in view of the above shortcomings, it is desirable to provide a turbine bucket axial positioning structure that saves manufacturing costs, facilitates service and maintenance, and extends turbine bucket life.
Disclosure of Invention
The invention aims at: in order to solve the problems, the invention provides an axial positioning structure of a turbine blade of a gas turbine, which can reduce the number of parts of the axial positioning structure on the air inlet side of the blade, reduce the manufacturing and maintenance costs and reduce the workload of installing and dismantling the blade.
The technical scheme adopted by the invention is as follows:
the utility model provides a gas turbine movable vane axial positioning structure, includes the movable vane, and it includes blade type, blade root platform and blade root, the blade root platform sets up in the radial inboard of blade type, and the blade root sets up in the radial inboard of blade root platform;
the wheel disc is provided with a blade root groove and a stud hole, and the blade root groove is matched and clamped with the blade root;
the tooth-shaped air seal is concentric with the wheel disc and is arranged on the air inlet side of the movable blade; the tooth-shaped air seal is provided with a waist-shaped groove facing the wheel disc and provided with an arc, and a first through hole which is opposite to the stud Kong Pi is arranged in the waist-shaped groove; the outer end part of the tooth-shaped air seal is provided with peripheral teeth matched with the blade root grooves, and the peripheral teeth are opposite to the blade root grooves in the working state so as to limit the moving blades to move along the axial air inlet side;
the compression air seal is concentric with the wheel disc and is arranged on the air outlet side of the movable blade; the pressing gas seal is provided with a second through hole which is paired with the stud Kong Pi; the outer end part of the compression air seal extends to the blade root groove so as to limit the movable blade to move along the axial air outlet side;
the stud penetrates through the first through hole, the stud hole and the second through hole, and the wheel disc, the tooth-shaped air seal and the compression air seal are fixed through the nut.
In the invention, the movable blade is embedded and clamped into the blade root groove through the blade root in the axial direction, the compressing air seal arranged on the air outlet side limits the movable blade to move along the axial air outlet side, and the tooth-shaped air seal arranged on the air inlet side limits the movable blade to move along the axial air inlet side. The tooth-shaped air seal can be rotated when the movable blade is required to be disassembled or installed, so that the peripheral teeth of the tooth-shaped air seal are opposite to the blade root groove or are circumferentially staggered, the axial limiting state of the movable blade is changed by the tooth-shaped air seal, and the movable blade is convenient to disassemble and install. When the tooth-shaped air seal is required to be rotated, the screw bolt is moved out of the first through hole to the waist-shaped groove along the air outlet side only by removing the nut at the air inlet side, and then the tooth-shaped air seal can be rotated to enable the peripheral teeth of the tooth-shaped air seal to be staggered with the blade root groove in the circumferential direction.
According to the scheme provided by the invention, the number of parts of the axial positioning structure on the air inlet side of the movable blade can be reduced, the manufacturing and maintenance cost is reduced, and the workload of installing and dismantling the movable blade is reduced.
Preferably, the peripheral teeth are uniformly distributed along the outer end part of the tooth-shaped air seal, and the number of the peripheral teeth is the same as that of the movable blades.
In the above scheme, the peripheral teeth can limit the axial movement of each movable blade, and the size of the peripheral teeth is smaller than the size between two adjacent blade root grooves, and the peripheral teeth are positioned between two adjacent blade root grooves after rotation and staggered with each movable blade.
Preferably, the peripheral teeth have a trapezoidal shape.
In the scheme, the trapezoid structure is stable, the blade root of the movable blade is conveniently moved out of the blade root groove in the axial direction, and the shielding of the blade root is avoided.
Preferably, the outer end parts of the tooth-shaped air seals and the compression air seals are respectively attached to the end surfaces of the wheel discs.
Preferably, the tooth-shaped gas seal is provided with a dynamic and static gas seal extending along the axial air inlet side, and the dynamic and static gas seal and the tooth-shaped gas seal are integrally arranged.
Preferably, the compression gas seal is provided with a dynamic and static gas seal extending along the axial air outlet side, and the dynamic and static gas seal and the compression gas seal are integrally arranged.
In the scheme, the dynamic and static air seals, the tooth-shaped air seals and the compression air seals are integrally designed, so that the axial size of the wheel disc can be reduced, and the manufacturing cost is reduced.
Preferably, the dynamic and static air seals are labyrinth air seals, honeycomb air seals or brush air seals, and are used for controlling the cooling air flow rate of the wheel disc chamber at the air inlet side of the movable blade.
Preferably, the waist-shaped grooves are uniformly distributed along the circumferential direction and symmetrically distributed relative to the rotation center of the wheel disc.
Preferably, the first through hole is located at the midpoint of the waist-shaped groove, and the diameter of the first through hole is the same as the width of the waist-shaped groove.
Preferably, the radian of the waist-shaped groove is 360 degrees/Z, and Z is the number of the movable blades.
In the scheme, the radian of the waist-shaped groove and the position of the first through hole are set, when the tooth-shaped air seal is rotated, the outermost edge of the waist-shaped groove is staggered with the blade root groove when contacting with the stud, and the positioning is completed by rotation.
Preferably, the wheel disc is provided with a first protruding part facing the tooth-shaped air seal, and the first protruding part is attached to the tooth-shaped air seal on the radial inner side of the first protruding part so as to limit the radial movement of the tooth-shaped air seal; the wheel disc is provided with a second protruding part facing the compression gas seal, and the second protruding part is attached to the compression gas seal on the radial inner side of the second protruding part so as to limit the radial movement of the compression gas seal.
In the scheme, the first protruding part not only can limit radial movement of the tooth-shaped gas seal, but also can be radially attached to the tooth-shaped gas seal, so that the tooth-shaped gas seal can be installed and positioned, and meanwhile, the tooth-shaped gas seal can be rotated conveniently.
Preferably, gaskets are arranged between the nut and the tooth-shaped air seal and between the nut and the compression air seal, and the gaskets are stop gaskets or anti-loose gaskets.
In the scheme, the gasket ensures that the axial positioning structure of the turbine movable blade is firm and difficult to loosen in the running process of the combustion engine, and can inhibit the tooth-shaped gas seal limiting state switching in non-overhauling time.
The method for mounting and dismounting the turbine movable blade of the gas turbine adopts the axial positioning structure of the turbine movable blade of the gas turbine, and changes the switching of the axial limiting state of the movable blade by the tooth-shaped gas seal through rotating the tooth-shaped gas seal, thereby facilitating the dismounting and mounting of the movable blade.
Specifically, the turbine blade mounting process of the gas turbine is as follows: firstly, rotating a tooth-shaped air seal to enable peripheral teeth to be staggered with a blade root groove; then pushing blade roots of the movable blades into the blade root grooves from the axial air inlet side to be clamped until the blade roots are bonded with the compressed air seal; then, the tooth-shaped air seal is rotated along the circumferential direction until the first through hole is communicated with the stud hole, and the peripheral teeth are opposite to the blade root; and moving the stud, and installing the nut and the gasket to complete the installation of the turbine movable blade.
Specifically, the disassembly process of the turbine blade of the gas turbine is as follows: firstly, removing the nuts and the gaskets, and moving the studs out to the air outlet side to the bottom surface of the waist-shaped groove; then, the tooth-shaped air seal is rotated along the circumferential direction, so that the peripheral teeth and the blade root are dislocated along the circumferential direction; and then the movable blade is moved out of the blade root groove along the axial air inlet side, and the disassembly of the turbine movable blade is completed.
In summary, due to the adoption of the technical scheme, the beneficial effects of the invention are as follows:
1. the number of parts of the axial positioning structure on the air inlet side of the movable blade is reduced, the manufacturing and maintenance cost is reduced, and the workload of installing and dismantling the movable blade is reduced;
2. the dynamic and static air seals and the tooth-shaped air seals are integrally arranged, and the dynamic and static air seals and the compression air seals are integrally arranged, so that the cooling air flow of the movable vane in and out of the air side wheel disc cavity can be effectively controlled, the axial width of the wheel disc is reduced, and the manufacturing cost of the wheel disc is reduced;
3. the first protruding part can limit radial movement of the tooth-shaped gas seal, plays a role in installing and positioning the tooth-shaped gas seal, and facilitates rotation of the tooth-shaped gas seal.
Drawings
The invention will now be described by way of example and with reference to the accompanying drawings in which:
FIG. 1 is a schematic view of an axial positioning structure of an inlet and outlet side of a first stage turbine bucket;
FIG. 2 is a schematic view of a turbine bucket axial positioning structure;
FIG. 3 is a schematic view of a turbine bucket construction;
FIG. 4 is a schematic view of a turbine disk root slot configuration;
FIG. 5 is a schematic view of a tooth-shaped air seal air outlet side structure;
FIG. 6 is an enlarged partial view of the vicinity of the waist-shaped groove of the toothed gas seal;
FIG. 7 is a C-C cross-sectional view of FIG. 6;
FIG. 8 is a schematic diagram of a compression gas seal;
FIGS. 9-13 are schematic views of the turbine bucket assembly process.
The marks in the figure: 1-movable blade, 2-wheel disc, 3-tooth-shaped air seal, 4-compression air seal, 5-stud, 6-dynamic and static air seal, 11-blade profile, 12-blade root platform, 13-blade root, 21-blade root groove, 22-stud hole, 23-first protruding part, 24-second protruding part, 31-peripheral tooth, 32-waist-shaped groove, 33-first through hole, 34-radial positioning surface, 41-second through hole, 51-nut, 52-gasket, 71-stationary blade and 72-air seal ring.
Detailed Description
All of the features disclosed in this specification, or all of the steps in a method or process disclosed, may be combined in any combination, except for mutually exclusive features and/or steps.
Any feature disclosed in this specification may be replaced by alternative features serving the same or equivalent purpose, unless expressly stated otherwise. That is, each feature is one example only of a generic series of equivalent or similar features, unless expressly stated otherwise.
As shown in FIG. 2, the axial positioning structure of the turbine blade of the gas turbine comprises a blade, a wheel disc, a tooth-shaped gas seal and a compression gas seal;
as shown in fig. 3, the movable blade includes a blade profile, a blade root platform disposed radially inward of the blade profile, and a blade root disposed radially inward of the blade root platform; as shown in fig. 4, a plurality of blade root grooves are uniformly formed in the outer end of the wheel disc, through stud holes are formed in the wheel disc, a plurality of moving blades are clamped in the blade root grooves through blade roots, and the blade root grooves and the blade roots are of the existing design and are not described again;
the tooth-shaped air seals concentric with the wheel disc are arranged on the air inlet side of the movable vane, the outer end parts of the tooth-shaped air seals are respectively attached to the end surfaces of the wheel disc, as shown in fig. 5, the tooth-shaped air seals are provided with waist-shaped grooves facing the wheel disc and having radians, first through holes which are opposite to the studs Kong Pi are arranged in the waist-shaped grooves, the waist-shaped grooves are uniformly distributed along the circumferential direction and symmetrically distributed relative to the rotation center of the wheel disc, the first through holes are positioned at the middle points of the waist-shaped grooves, the diameter of the first through holes is the same as the width of the waist-shaped grooves, the radian theta of the waist-shaped grooves is 360 DEG/Z as shown in fig. 6, and Z is the number of the movable vanes; the outer end part of the tooth-shaped air seal is provided with a trapezoid peripheral tooth matched with the blade root groove, and the peripheral tooth is opposite to the blade root groove in a working state to limit the movable blade to move along the axial air inlet side; the peripheral teeth are uniformly distributed along the outer end part of the tooth-shaped air seal, and the number of the peripheral teeth is the same as that of the movable blades;
a pressing air seal concentric with the wheel disc is arranged on the air outlet side of the movable blade, and as shown in fig. 8, a second through hole which is opposite to the stud Kong Pi is arranged on the pressing air seal; the outer end part of the compression air seal extends to the blade root groove to be attached to the blade root groove so as to limit the movable blade to move along the axial air outlet side;
the wheel disc is provided with a first protruding part facing the tooth-shaped air seal, the first protruding part is attached to the radial positioning surface of the tooth-shaped air seal on the radial inner side of the first protruding part so as to limit the radial movement of the tooth-shaped air seal, the tooth-shaped air seal is installed and positioned, and the tooth-shaped air seal is convenient to rotate; the wheel disc is provided with a second protruding part facing the compression gas seal, and the second protruding part is attached to the compression gas seal on the radial inner side of the second protruding part so as to limit the radial movement of the compression gas seal;
as shown in fig. 7, the tooth-shaped air seal is provided with a dynamic and static air seal extending along the axial air inlet side, and the dynamic and static air seal and the tooth-shaped air seal are integrally arranged; the compression gas seal is provided with a dynamic and static gas seal extending along the axial gas outlet side, and the dynamic and static gas seal and the compression gas seal are integrally arranged; through the integrated design of dynamic and static air seal and tooth-shaped air seal and compression air seal, the axial size of the wheel disc can be reduced, and therefore the manufacturing cost is reduced. The dynamic and static air seals can be selected from labyrinth air seals, honeycomb air seals or brush air seals and are used for controlling the cooling air flow of the wheel disc chamber at the air inlet side of the movable blade;
the stud penetrates through the first through hole, the stud hole and the second through hole, and the wheel disc, the tooth-shaped air seal and the compression air seal are fixed through the nuts and the gaskets.
Of course, as shown in FIG. 1, the axial positioning structure of the first-stage turbine movable blade further comprises stationary blades arranged on two sides of the movable blade and a gas seal ring fixed on the radial inner side of the stationary blades.
According to the method for mounting and dismounting the turbine movable blade of the gas turbine, the axial positioning structure of the turbine movable blade of the gas turbine is adopted, and the change of the axial limiting state of the movable blade by the tooth-shaped gas seal is changed by rotating the tooth-shaped gas seal, so that the dismounting and mounting of the movable blade are facilitated.
Specifically, the turbine blade mounting process of the gas turbine is as follows:
firstly, as shown in fig. 9, the tooth-shaped air seal is rotated along the circumferential direction to enable the peripheral teeth to be staggered with the blade root grooves, so that the peripheral teeth do not limit the moving blades to move along the axial air inlet side;
then, as shown in fig. 10, the blade root of the movable blade is pushed into the blade root groove from the axial air inlet side in the h1 direction to be engaged, so that the movement of the movable blade in the radial direction and the circumferential direction is limited; as shown in fig. 11, continuously pushing the blade root of the movable blade into the blade root groove from the axial air inlet side in the h2 direction until the blade root is attached to the compressed air seal;
then, as shown in fig. 12, the tooth-shaped air seal is rotated in the u1 direction along the circumferential direction until the first through hole is communicated with the stud hole, and at the moment, the peripheral teeth are opposite to the blade root, so that the peripheral teeth limit the movable blade to move along the axial air inlet side;
finally, as shown in FIG. 13, the bolts are moved in the direction of h3 and nuts and shims are installed to complete the installation of the turbine bucket.
The disassembly and the installation of the turbine movable blade of the gas turbine are opposite, and specifically, the disassembly process of the turbine movable blade of the gas turbine is as follows:
firstly, removing the nut and the gasket, and moving the stud out to the air outlet side to the bottom surface of the waist-shaped groove, so that the stud does not limit the tooth-shaped air seal to rotate;
then, the tooth-shaped air seal is rotated along the circumferential direction, so that the peripheral teeth and the blade root are dislocated along the circumferential direction, and the peripheral teeth do not limit the moving blade to move along the axial air inlet side;
and then, moving the movable blade out of the blade root groove along the axial air inlet side, and completing the disassembly of the turbine movable blade.
The invention is not limited to the specific embodiments described above. The invention extends to any novel one, or any novel combination, of the features disclosed in this specification, as well as to any novel one, or any novel combination, of the steps of the method or process disclosed.
Claims (10)
1. A gas turbine movable vane axial positioning structure which is characterized in that: the blade root platform is arranged on the radial inner side of the blade profile, and the blade root is arranged on the radial inner side of the blade root platform;
the wheel disc is provided with a blade root groove and a stud hole, and the blade root groove is matched and clamped with the blade root;
the tooth-shaped air seal is concentric with the wheel disc and is arranged on the air inlet side of the movable blade; the tooth-shaped air seal is provided with a waist-shaped groove facing the wheel disc and provided with an arc, and a first through hole which is opposite to the stud Kong Pi is arranged in the waist-shaped groove; the outer end part of the tooth-shaped air seal is provided with peripheral teeth matched with the blade root grooves, and the peripheral teeth are opposite to the blade root grooves in the working state so as to limit the moving blades to move along the axial air inlet side;
the compression air seal is concentric with the wheel disc and is arranged on the air outlet side of the movable blade; the pressing gas seal is provided with a second through hole which is paired with the stud Kong Pi; the outer end part of the compression air seal extends to the blade root groove so as to limit the movable blade to move along the axial air outlet side;
the stud penetrates through the first through hole, the stud hole and the second through hole, and the wheel disc, the tooth-shaped air seal and the compression air seal are fixed through the nut.
2. The gas turbine rotor blade axial positioning structure as recited in claim 1, wherein: the peripheral teeth are uniformly distributed along the outer end part of the tooth-shaped air seal, and the number of the peripheral teeth is the same as that of the movable blades.
3. The gas turbine rotor blade axial positioning structure as recited in claim 1, wherein: the outer end parts of the tooth-shaped air seals and the compression air seals are respectively attached to the end surfaces of the wheel discs.
4. The gas turbine rotor blade axial positioning structure as recited in claim 1, wherein: the tooth-shaped air seal is provided with a dynamic and static air seal extending along the axial air inlet side, the dynamic and static air seal and the tooth-shaped air seal are integrally arranged, and the dynamic and static air seal is a labyrinth air seal, a honeycomb air seal or a brush air seal.
5. The gas turbine rotor blade axial positioning structure as recited in claim 1, wherein: the waist-shaped grooves are uniformly distributed along the circumferential direction and symmetrically distributed relative to the rotation center of the wheel disc.
6. The gas turbine rotor blade axial positioning structure as recited in claim 1, wherein: the first through hole is positioned at the middle point of the waist-shaped groove, and the diameter of the first through hole is the same as the width of the waist-shaped groove.
7. The gas turbine rotor blade axial positioning structure as recited in claim 1, wherein: the radian of the waist-shaped groove is 360 degrees/Z, and Z is the number of the movable vanes.
8. The gas turbine rotor blade axial positioning structure as recited in claim 1, wherein: the wheel disc is provided with a first protruding part facing the tooth-shaped air seal, and the first protruding part is attached to the tooth-shaped air seal on the radial inner side of the first protruding part.
9. The gas turbine rotor blade axial positioning structure as recited in claim 1, wherein: gaskets are arranged between the nut and the tooth-shaped air seal and between the nut and the compression air seal, and the gaskets are stop gaskets or anti-loose gaskets.
10. A method for assembling and disassembling a turbine blade of a gas turbine, adopting the axial positioning structure of the turbine blade of the gas turbine according to any one of claims 1 to 9, characterized in that: the tooth-shaped gas seal is rotated to change the axial limiting state of the movable blade, so that the movable blade is convenient to disassemble and install.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111454956.5A CN114215610B (en) | 2021-12-01 | 2021-12-01 | Axial positioning structure of turbine movable blade of gas turbine and mounting and dismounting method |
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| CN202111454956.5A CN114215610B (en) | 2021-12-01 | 2021-12-01 | Axial positioning structure of turbine movable blade of gas turbine and mounting and dismounting method |
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| 某燃机用接触式气封设计;王刚德;陈尧;陈晓平;罗跃飞;唐玉莲;;东方电气评论(第04期);全文 * |
| 燃气轮机汽封圈制造技术研究;谢敏;***;孟秋建;;东方电气评论(第04期);全文 * |
| 齿形叶根动叶片工艺分析与改进;刘蓉;;机械工程师(第05期);全文 * |
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