CN114458391A - Turbine blade locking assembly - Google Patents
Turbine blade locking assembly Download PDFInfo
- Publication number
- CN114458391A CN114458391A CN202210164793.5A CN202210164793A CN114458391A CN 114458391 A CN114458391 A CN 114458391A CN 202210164793 A CN202210164793 A CN 202210164793A CN 114458391 A CN114458391 A CN 114458391A
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- CN
- China
- Prior art keywords
- locking assembly
- locking
- turbine blade
- mounting
- sealing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000007789 sealing Methods 0.000 claims abstract description 45
- 238000006073 displacement reaction Methods 0.000 claims abstract description 9
- 238000009434 installation Methods 0.000 claims description 15
- 230000000694 effects Effects 0.000 claims description 6
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
Images
Classifications
-
- 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
- F01D5/32—Locking, e.g. by final locking blades or keys
- F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a turbine blade locking assembly of a gas turbine, wherein a turbine blade (1) is arranged on a wheel disc (3), at least one side of the wheel disc (3) is provided with a first mounting part (31), at least one side of the turbine blade is provided with a second mounting part (11), the locking assembly comprises a locking part (2), the first mounting part (31) and the second mounting part (11), the locking part (2) is matched with the first mounting part (31) and the second mounting part (11) to limit the axial displacement of the turbine blade (1), the locking part (2) comprises an elastic part (22) and a sealing part (21), the elastic part (22) is clamped into the first mounting part (31), and the sealing part (21) is clamped into the second mounting part (11) under the action of the elastic part (22) and the first mounting part (31); or the elastic part (22) is clamped into the second mounting part (11), and the sealing part (21) is clamped into the first mounting part (31) under the action of the elastic part (22) and the second mounting part (11).
Description
Technical Field
The invention relates to a heavy-duty gas turbine, in particular to a turbine blade locking assembly of the heavy-duty gas turbine.
Background
The turbine blade is an important component of an axial flow gas turbine, and the reliability of the connection and fixing form of the turbine blade and a turbine wheel disc is particularly important. At present, the most used turbine blade locking assemblies are mainly in the forms of baffle plates and locking pieces, wherein the baffle plates are common, and the configuration and the form of the baffle plates are variable. The baffle type is a locking mode of adding more locking structures on the baffle, and the structure and parts are relatively complex; the lock piece formula is the form of taking the locking plate on the baffle, through the fixed turbine blade of baffle, then locks the baffle with the locking plate, and its sealing portion 21 structure is comparatively complicated, and the while rim position of rim of the rim also needs to increase relevant cooperation structure, leads to the rim plate processing complicacy.
As in the prior art, such as EP1840338a1, a barrier-type locking device is proposed, the axial locking device of the turbine blade comprising a sealing unit arranged in a safety groove, the sealing unit being provided with a structure of an opening and a threaded blind hole aligned with the opening. Because the structure of the wheel disc is more, and the structure of the rim part of the wheel disc is relatively complex, the stress distribution of the rim part is negatively influenced, and the processing and mounting cost is higher.
The present invention has been made in view of the above problems.
Disclosure of Invention
The invention mainly aims to provide a turbine blade locking assembly to solve the problem that the structure of the turbine blade locking assembly in the prior art is complex.
In order to achieve the above object, according to one aspect of the present invention, there is provided a turbine blade locking assembly, a turbine blade is mounted on a wheel disc, at least one side of the wheel disc is provided with a first mounting portion, at least one side of the turbine blade is provided with a second mounting portion, the locking assembly includes a locking portion, the first mounting portion, and the second mounting portion, the locking portion is engaged with the first mounting portion and the second mounting portion to limit axial displacement of the turbine blade, the locking portion includes an elastic portion and a sealing portion, the elastic portion is clamped into the first mounting portion, and the sealing portion is clamped into the second mounting portion under the action of the elastic portion and the first mounting portion; or the elastic part is clamped into the second mounting part, and the sealing part is clamped into the first mounting part under the action of the elastic part and the second mounting part, so that the axial displacement of the turbine blade relative to the wheel disc is limited. And the locking assembly has a simple structure, simplifies the structural forms of related locking parts and the wheel disc, and reduces the processing difficulty, thereby reducing the cost. And the locking assembly does not contain a fastener, and can quickly realize the axial fixation of the turbine blade and the turbine wheel disc.
The following is a further optimization of the present invention to the above scheme:
further, the elastic part is provided with a fixed end and a deformation end.
Further, the fixed end is fixedly connected with the sealing part.
Further, the fixed end is welded to the sealing portion.
Further, the deformed end acts on the first mounting portion or the second mounting portion.
Further, the deformation end is designed with at least two deformation protrusions. The elastic force that the end produced warp can be weighed or measure according to the deflection, can design according to the weight of locking portion self, realizes locking Assembly's accurate design, has realized good locking effect, can realize turbine blade's axial fixity more accurately.
Further, the elastic part is an elastic element.
Further, the elastic element is a spring piece.
Further, the seal portion is provided in a plate shape.
Furthermore, the action ends of the sealing part and the first mounting part are provided with positioning blocks so as to limit the circumferential displacement of the locking part.
Further, the sealing portion is provided with a groove to facilitate disassembly.
Further, the first installation part or the second installation part is provided with a wedge-shaped groove. The wedge-shaped surface provides a mounting space for the locking part 2.
The locking component can simplify the structural forms of related locking parts and the wheel disc on the premise of ensuring the structural function, and reduces the processing difficulty, thereby reducing the cost; and the elastic force generated by the deformation end can be measured or measured according to the deformation amount, and can be designed according to the self weight of the locking part, so that the accurate design of the locking assembly is realized, the good locking effect is realized, and the axial fixation of the turbine blade can be realized accurately.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 illustrates an assembled front view of a turbine blade and locking assembly according to an embodiment of the present invention; and
FIG. 2 illustrates an assembled left side view of a turbine blade and locking assembly according to an embodiment of the present invention; and
FIG. 3 shows a schematic front view of a locking assembly according to an embodiment of the invention; and
FIG. 4 shows a left side view schematic of a locking assembly according to an embodiment of the invention; and
FIG. 5 illustrates a front view of a spring according to an embodiment of the present invention; and
FIG. 6 shows a schematic top view of the embodiment according to FIG. 5; and
FIG. 7 illustrates a schematic view of the elastic part and the sealing part being fixed according to an embodiment of the present invention; and
FIG. 8 shows a schematic view of a seal circumferential locating block according to an embodiment of the present invention; and
FIG. 9 illustrates a turbine blade positioning slot in accordance with an embodiment of the present invention.
Wherein the figures include the following reference numerals:
1. a turbine blade; 11. a second mounting portion;
2. a locking portion; 21. a sealing part; 211. positioning blocks; 212. a groove;
22. an elastic portion; 221. a fixed end; 222. a deformation end;
3. a wheel disc; 31. a first mounting portion; 4. and (6) positioning a groove.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
The present invention is described in further detail below with reference to specific examples, which are not to be construed as limiting the scope of the invention as claimed. The term "comprising" when used indicates the presence of a feature but does not preclude the presence or addition of one or more other features; the terms "lateral," "upper," "lower," "front," "rear," "left," "right," "top," "bottom," "inner," "outer," and the like are used in the orientation or positional relationship indicated in the drawings for ease of description only, and are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting; furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art. In addition, in the description of the present invention, "a plurality" means two or more unless otherwise specified.
The turbine blade 1 is an important part in an axial-flow gas turbine, the turbine blade 1 is installed into a mortise of the wheel disc 3 through a mortise and tenon structure of the turbine blade 1 so as to fix the turbine blade 1 in the circumferential direction and the radial direction of the turbine wheel disc 3, and in the axial direction, the turbine blade 1 still needs to be fixedly connected through a locking assembly so as to realize the axial fixation of the turbine blade 1 and the turbine wheel disc 3.
As shown in fig. 1 to 2, each turbine blade 1 is axially fixed to the turbine disk 3 in the axial direction of the turbine disk 3 by a locking assembly on both sides. The locking assembly comprises a locking part 2, a first mounting part 31 and a second mounting part 11. The first mounting portion 31 is provided on one side or both sides of the turbine disk 3. Likewise, the second mounting 11 is arranged on one or both sides of the turbine blade 1. The securing part 2 is mounted between the first mounting part 31 of the disk and the second mounting part 11 of the turbine blade 1 in order to achieve a limitation of the axial displacement of the turbine blade 1 relative to the disk. The locking part 2 includes an elastic part 22 and a sealing part 21. The sealing portion 21 is plate-shaped and is fitted into the second mounting portion 11. The elastic part 22 is connected with the sealing part 21 into a whole, the elastic part 22 is clamped into the first mounting part 31, an upward acting force is generated under the action of the elastic part 22 and the first mounting part 31, and the other end of the sealing part 21 is clamped into the second mounting part 11 under the upward acting force. In practical use, the elastic portion 22 may be engaged with the second mounting portion 11, and the other end of the sealing portion 21 may be engaged with the first mounting portion 31 by the elastic portion 22 and the second mounting portion 11. The locking assembly is simple in structure, does not contain a fastener, and can quickly realize axial fixation of the turbine blade 1 and the turbine wheel disc 3.
As shown in fig. 1-2, the first mounting portion 31 is disposed on at least one side of the wheel disc 3, the first mounting portion 31 is a wedge-shaped groove, the first mounting portion 31 may also be a circular groove structure having an inclined surface, such as a trapezoidal groove, and the circular groove design of the inclined surface of the first mounting portion 31 provides a space for mounting the sealing portion. The second mounting portion 11 is disposed on at least one side of the turbine blade 1 and is a narrow slot. Of course, the first mounting portion 31 may be a narrow slot, and the second mounting portion 11 may be a ring groove structure having an inclined surface, such as a wedge-shaped groove or a trapezoidal groove.
As shown in fig. 3-7, the elastic portion 22 is an elastic element, which may be a spring plate or other form of elastic element. The elastic member shown in fig. 5 is a spring plate provided with a fixed end 221 and a deformed end 222. The fixed end 221 is curved or otherwise shaped. Fig. 5 shows that the spring piece at the end of the fixed end 221 is bent in a small size to increase the strength of the spring piece at the end of the fixed end 221.
The fixing end 221 is fixedly connected to the sealing portion 21, and the fixing end 221 may be welded to the sealing portion 21 by spot welding, as shown in fig. 7, 3 positions of each fixing end 221 are selected, and in the 3 positions, the fixing end 221 is spot welded to the sealing portion 21. Spot welding ensures the strength of the connection and reduces the deformation of the seal as much as possible.
As shown in fig. 7, the deforming end 222 is designed with two deforming protrusions, and the deforming end 222 acts on the first mounting portion 31 or the second mounting portion 11 to generate an elastic force, wherein the deforming protrusions may be one or more, and the specific design is determined according to the actual application. The elastic force generated by the deformation end 222 can be measured according to the deformation amount, and can be designed according to the weight of the locking part, so that the accurate design of the locking assembly is realized, the good locking effect is realized, and the axial fixation of the turbine blade can be realized accurately.
As shown in fig. 3, the elastic portion 22 is spot-welded to the sealing portion 21, and then the integrated locking portion 2 is formed. When the elastic portion 22 is welded to the sealing portion 21, only the fixed end 221 is welded to the sealing portion 21, and the deformation end 222 is exposed so that the elastic portion 22 acts on the first mounting portion 31 to deform.
As shown in fig. 3 to 4, the sealing part 21 has a trapezoidal plate-like structure, the upper side of the plate has a longer length than the lower side, and the end of the sealing part 21 is provided with a positioning block 211 to limit the circumferential displacement of the locking part 2. Fig. 8 shows that the positioning block 211 is located at the top of the right side of the sealing portion 21, and the sealing portion 21 may be located at the top of the left side according to practical circumstances. Similarly, a positioning block 211 may be provided at the action ends of the seal portion 21 and the second mounting portion 11 to restrict circumferential displacement of the locking portion 2.
A groove 212 is further provided at a central position of the sealing part 21 to facilitate the removal of the sealing part 21. The groove 212 has a wedge-shaped surface and does not penetrate the seal portion 21 and does not affect the sealing of the seal portion 21.
The turbine blade 1 is further provided with a positioning groove 4, as shown in fig. 9, the positioning groove 4 being provided in a square shape for receiving a square-shaped positioning block 211 to restrict circumferential rotation of the sealing portion 21. Preferably, a small hole is further provided inside the positioning block 211, and such a small hole avoids position interference when the positioning block 211 is engaged with the positioning groove 4.
During the installation of locking portion 2, earlier install turbine blade 1 in the tongue-and-groove of rim plate 3, later with the certain angle of locking portion 2 slope, along the wedge face of first installation department 31 impress in the first installation department at 3 rims positions of rim plate, the wedge face is locking portion 2 provides installation space. Then, under the action of elastic force, the upper end of the locking part 2 is clamped into the clamping groove of the blade. At the same time, the circumferential positioning block 211 at the upper right corner of the sealing portion 21 is snapped into the corresponding positioning slot 4 on the blade. The locking component can simplify the structural forms of the related locking component and the wheel disc 3 on the premise of ensuring the structural function, and reduce the processing difficulty, thereby reducing the cost.
When the locking part 2 is removed, a tool is used to snap into the groove 212 reserved on the sealing part 21, and the locking part 2 can be removed after the elastic part 22 is compressed downwards.
From the above description, it can be seen that the above-described embodiments of the present invention achieve the following technical effects: the locking component can simplify the structural forms of related locking parts and the wheel disc 3 on the premise of ensuring the structural function, and reduces the processing difficulty, thereby reducing the cost; and the elastic force generated by the deformation end 222 can be measured or measured according to the deformation amount, and can be designed according to the self weight of the locking part, so that the accurate design of the locking assembly is realized, the good locking effect is realized, and the axial fixation of the turbine blade can be accurately realized.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (12)
1. The utility model provides a turbine blade locking Assembly, turbine blade (1) is installed on rim plate (3), rim plate (3) one side at least is provided with first installation department (31), turbine blade one side at least is provided with second installation department (11), locking Assembly includes locking portion (2), first installation department (31), second installation department (11), locking portion (2) with first installation department (31) with second installation department (11) cooperation, in order to restrict the axial displacement of turbine blade (1), its characterized in that:
the locking part (2) comprises an elastic part (22) and a sealing part (21), the elastic part (22) is clamped into the first mounting part (31), and the sealing part (21) is clamped into the second mounting part (11) under the action of the elastic part (22) and the first mounting part (31); or elastic part (22) is gone into second installation department (11) elastic part (22) with under the effect of second installation department (11), sealing part (21) is gone into first installation department (31).
2. Locking assembly according to claim 1, characterized in that the resilient part (22) is provided with a fixed end (221) and a deformable end (222).
3. Locking assembly according to claim 2, wherein the fixing end (221) is fixedly connected with the sealing portion (21).
4. Locking assembly according to claim 3, wherein the fixed end (221) is welded to the sealing portion (21).
5. Locking assembly according to claim 4, wherein the deformation end (222) acts on the first mounting portion (31) or the second mounting portion (11).
6. Locking assembly according to claim 5, wherein the deformation end (222) is designed with at least two deformation projections.
7. Locking assembly according to any of claims 1-6, wherein the resilient part (22) is a resilient element.
8. The locking assembly of claim 7 wherein the resilient member is a leaf spring.
9. Locking assembly according to claim 7, wherein the sealing portion (21) is provided in the form of a plate.
10. Locking assembly according to claim 7, wherein the active ends of the sealing portion (21) and the first mounting portion (31) are provided with a positioning block (211) to limit the circumferential displacement of the locking portion (2).
11. Locking assembly according to claim 7, characterized in that the sealing portion (21) is provided with a groove to facilitate disassembly.
12. Locking assembly according to any of claims 1-6, wherein the first mounting portion (31) or the second mounting portion (11) is provided as a wedge-shaped groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210164793.5A CN114458391A (en) | 2022-02-22 | 2022-02-22 | Turbine blade locking assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210164793.5A CN114458391A (en) | 2022-02-22 | 2022-02-22 | Turbine blade locking assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114458391A true CN114458391A (en) | 2022-05-10 |
Family
ID=81415096
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210164793.5A Pending CN114458391A (en) | 2022-02-22 | 2022-02-22 | Turbine blade locking assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114458391A (en) |
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| CN1656303A (en) * | 2002-05-24 | 2005-08-17 | Abb涡轮系统有限公司 | Axial securing means for impeller blades |
| US20050226729A1 (en) * | 2004-04-07 | 2005-10-13 | Joana Negulescu | Locking device for turbine blades |
| EP1643082A1 (en) * | 2004-09-30 | 2006-04-05 | Siemens Aktiengesellschaft | Turbine blade retention system |
| US20060088419A1 (en) * | 2004-10-21 | 2006-04-27 | Hermiston Brian G | Rotor assembly retaining apparatus |
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| US20140301854A1 (en) * | 2013-04-04 | 2014-10-09 | MTU Aero Engines AG | Securement system and method for securing an attachment portion of at least one rotor blade or rotor blade segment in a mounting site of a rotor base |
| US20180195399A1 (en) * | 2015-07-09 | 2018-07-12 | Siemens Aktiengesellschaft | Rotor blade arrangement having elastic support elements for a thermal turbomachine |
| CN113623270A (en) * | 2021-08-24 | 2021-11-09 | 中国联合重型燃气轮机技术有限公司 | Locking device and gas compressor and gas turbine comprising same |
-
2022
- 2022-02-22 CN CN202210164793.5A patent/CN114458391A/en active Pending
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| US20040065019A1 (en) * | 2002-10-02 | 2004-04-08 | Hawa Ag | Connecting device, cover device and dividing element |
| US20050226729A1 (en) * | 2004-04-07 | 2005-10-13 | Joana Negulescu | Locking device for turbine blades |
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