CN112160794B - Positioning assembly, turbine disc or compressor disc of positioning assembly and aircraft engine - Google Patents
Positioning assembly, turbine disc or compressor disc of positioning assembly and aircraft engine Download PDFInfo
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- CN112160794B CN112160794B CN202010988356.6A CN202010988356A CN112160794B CN 112160794 B CN112160794 B CN 112160794B CN 202010988356 A CN202010988356 A CN 202010988356A CN 112160794 B CN112160794 B CN 112160794B
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- Prior art keywords
- disc
- positioning assembly
- baffle
- balance
- weight
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/027—Arrangements for balancing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/662—Balancing of rotors
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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 positioning assembly, belongs to the technical field of balance block fixing structures, and solves the technical problem that stress concentration is generated on a disc due to products in the prior art. The positioning assembly is balanced by the weight of the disc, the disc (3) comprising an outer circular portion and an inner circular portion, comprising a baffle (2) and a balancing mass (1), wherein: one end of the baffle (2) is connected with the outer circle part of the disc (3) in a buckling way, and the other end of the baffle is connected with one end of the balance block (1) in a buckling way; the other end of the balance weight (1) is in contact connection with the inner circle part of the disc (3) and is connected with a turbine disc or a compressor disc and an aircraft engine. The invention is used for perfecting the fixing function of the balance block and meeting the requirements of people on the fixing of the balance block and the service life of the balance block improving disc.
Description
Technical Field
The invention belongs to the technical field of balance block fixing structures on turbine disks, and particularly relates to a positioning assembly, a turbine disk or a compressor disk of the positioning assembly, and an aero-engine of the positioning assembly.
Background
When the turbine rotor is combined and dynamically balanced, the main method for adjusting the unbalance amount is to use a disc, wherein the disc can be a turbine disc or a compressor disc, and a balancing weight block is added on the turbine disc. The prior art method is shown in fig. 1, a balancing weight block structure commonly used on a disc is shown in fig. 1, a circumferential pin hole is formed in an installation edge of a disc a, a balancing block b is fixed on the installation edge of the disc through an installation pin c, the pin is punched by using a punching point method, and if d is axial 4 points, the pin is prevented from falling off in work.
The inventors have found that the prior art has at least the following drawbacks:
1. overhead holes in the disc destroy the integrity of the disc. The temperature is very high during operation of the disc, and during operation, the disc is subjected to very large thermal stress and centrifugal force, stress concentration can be generated due to discontinuity of materials around the pin hole, the fatigue life of the disc can be reduced due to the open hole, and fatigue cracks are easily generated around the pin hole.
2. Disassembly is inconvenient and the counterweight and/or baffle are reused. In the engine development stage, the turbine rotor needs often to be dismantled and the repacking, and the repacking at every turn all needs to be balanced again, and consequently the frequency of balancing piece dismantlement is very high, because this structural installation back is died around the pinhole, consequently need destroy the method and dismantle, destroys the dismantlement and causes the damage to the turbine dish easily, causes the unable used repeatedly of balancing piece simultaneously.
In view of the above, the present invention is particularly proposed.
Disclosure of Invention
The invention aims to provide a positioning assembly, which solves the technical problem of stress concentration of a disc caused by a product in the prior art. The technical scheme of the scheme has a plurality of technical beneficial effects, which are described as follows:
in one aspect the present disclosure provides a positioning assembly for weight balancing of a disc, the disc including an outer circular portion and an inner circular portion, including a baffle and a counterweight, wherein:
one end of the baffle is connected with the outer circle part of the disc in a buckling manner, and the other end of the baffle is connected with one end of the balance block in a buckling manner;
the other end of the balance weight is in contact connection with the inner circle part of the disc.
The structure of present case avoids spending the hole on the dish to avoided appearing because of the condition that the pinhole causes stress concentration, improved the life of dish. Compared with the method in the prior art, the balance position is increased by about 1 time in the circumferential direction, and the balance position can be adjusted more finely during balance. Through the mode of joint, its structural installation is dismantled conveniently, does not have connection structure such as threaded connection, riveting, pin connection, need not trompil, groove structure on the turbine dish, has guaranteed the integrality of dish structure to need not carry out destructive dismantlement to the balancing piece, guaranteed balancing piece reuse, increase the reliability and the life of dish, practice thrift economic cost. And the baffle and balancing piece joint on the dish can limit the six ascending degrees of freedom of balancing piece on the dish with the firm joint of balancing piece. When needing to point out, the technical scheme of present case effectively utilizes centrifugal force to increase buckle structure's fastness and steadiness, and when needing to be changed spare part, the dish stall, centrifugal force is zero, convenient dismantlement.
In a preferred or alternative embodiment, one end of the baffle penetrates through one end of the balance weight and is provided with a protruding section, and the protruding section can be folded to buckle the balance weight.
In a preferred or alternative embodiment, the inner circular portion of the disc is provided with spaced first grooves, the balance weight being adapted to the first groove arrangement by passing through the arrangement of the first groove sections.
In a preferred or alternative embodiment, a second groove is provided at an edge of one end of the weight, and a lug for blocking the baffle from moving out is provided at the edge of the second groove.
In a preferred or alternative embodiment, one end of the baffle is arranged in an arc-shaped configuration with the snap-fit section of the outer cylindrical portion of the disc.
In a preferred or alternative embodiment, one end of the baffle is snap-fit to one side of the outer circumference of the disc and the other end is snap-fit to one end of the weight on the other side of the disc and adjacent to the inner circumference of the disc.
In a preferred or alternative embodiment, the baffle is provided with a protrusion extending outwardly along one side edge.
In a preferred or alternative embodiment, the shape of the weight is rectangular or L-shaped or square or arc-shaped.
Another aspect provides a turbine or compressor disk mounted, e.g., with a positioning assembly as above, in part or in whole.
Another aspect provides an aircraft engine fitted with a turbine disk or a compressor disk as part or all of the above.
Compared with the prior art, the technical scheme provided by the invention has the following beneficial effects:
according to the technical scheme, the positioning assembly is arranged, so that the upper overhead hole of the disc is avoided, the situation of stress concentration caused by pin hole opening is avoided, and the service life of the disc is prolonged. Compared with the method in the prior art, the balance position is increased by about 1 time in the circumferential direction, and the balance position can be adjusted more finely during balance. Through the mode of joint, its structural installation is dismantled conveniently, does not have connection structure such as threaded connection, riveting, pin connection, need not trompil, groove structure on the turbine dish, has guaranteed the integrality of dish structure to need not carry out destructive dismantlement to the balancing piece, guaranteed balancing piece reuse.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the prior art descriptions will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic view of a prior art structure for forming pin holes in a disk;
FIG. 2 is a top view of the positioning assembly of the present invention mounted on a disk;
FIG. 3 isbase:Sub>A cut-away view looking toward A-A of the positioning assembly of the present invention;
FIG. 4 is a perspective view of a weight in the positioning assembly of the present invention;
FIG. 5 is a perspective view of a baffle plate in the positioning assembly of the present invention;
wherein:
1. a counterbalance; 2. a baffle plate; 3. a disc; 11. a lug; 12. a second groove; 21. a protruding section; 31. a first groove.
Detailed Description
The embodiments of the present invention are described below with reference to specific embodiments, and other advantages and effects of the present invention will be easily understood by those skilled in the art from the disclosure of the present specification. It should be apparent that the described embodiments are only some embodiments of the present invention, and not all embodiments. The invention is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the disclosure, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should be further noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present invention, and the drawings only show the components related to the present invention rather than being drawn according to the number, shape and size of the components in actual implementation, and the type, quantity and proportion of each component in actual implementation can be changed freely, and the layout of the components can be more complicated.
In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that aspects may be practiced without these specific details. In order that those skilled in the art will better understand the disclosure, the invention will be described in further detail with reference to the accompanying drawings and specific embodiments. The terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
Referring to fig. 1, a positioning assembly for balancing the weight of a disc 3, the disc 3 being a turbine disc 3 or a gas compressor disc 3, the disc 3 being circular, the disc 3 including an outer circular portion and an inner circular portion, including a baffle 2 and a balance mass 1, wherein:
one end of the baffle 2 is connected with the excircle part of the disc 3 in a buckling way, for example, one end of the baffle 2 is arranged in an arc structure and is mutually matched with the excircle shape of the disc 3, generally, the arc turning angle is slightly smaller than the radian conversion angle of the excircle of the disc 3, the arc turning is clamped on the excircle of the disc 3 by using a tool, and the other end of the baffle is connected with one end of the balance block 1 in a buckling way;
the other end of the balance weight 1 is in contact connection with the inner circle part of the disc 3, and can be in natural contact or arc clamping connection.
The structure of present case avoids opening the pinhole on dish 3 to avoided appearing because of the condition that the pinhole causes stress concentration, improved dish 3's life. Compared with the method in the prior art, the balance position is increased by about 1 time in the circumferential direction, and the balance position can be adjusted more finely during balance. Through the mode of joint, its structural mounting dismantles the convenience, does not have connection structure such as threaded connection, riveting, pin connection, need not trompil, groove structure on turbine disc 3, has guaranteed the integrality of disc 3 structure to need not carry out destructive dismantlement to balancing piece 1, guaranteed 1 reuse of balancing piece, increase disc 3's reliability and life, practice thrift economic cost. And baffle 2 and balancing piece 1 joint on dish 3, can limit the ascending degree of freedom in six directions of balancing piece 1 with the firm joint of balancing piece 1 on dish 3.
When needing to point out, the technical scheme of present case effectively utilizes centrifugal force to increase buckle structure's fastness and steadiness, and when needing to be changed spare part, 3 stall on the dish, centrifugal force is zero, convenient dismantlement.
As a technical solution provided by the present disclosure, as shown in fig. 3, 4 and 5, one end of the baffle 2 passes through one end of the balance weight 1 and is provided with an extending section 21, and the extending section 21 can be folded to buckle the balance weight 1. The protruding section 21 can increase the contact area between the baffle 2 and the balance block 1, increase the stability of the balance block 1, and enable the static friction force to be in a buckling mode when the disc 3 rotates.
As the technical scheme that the present case provided, the interior circular portion interval of dish 3 sets up first recess 31, generally, the interior circular portion of aeroengine's turbine dish 3 sets up first recess 31, and the technical scheme of present case can effectively utilize the structure of turbine dish 3 to fix balancing piece 1, and the structure that balancing piece 1 passed first recess 31 section is with first recess 31 structural adaptation.
The structural design of the existing middle disc 3 is reasonably applied, the stability of the balance block 1 in the radial direction and the circumferential direction is improved, and the circumferential limiting effect can be achieved.
As the technical scheme that the present case provided, be equipped with second recess 12 on 1 one end border position department of balancing piece, and second recess 12 border position sets up the lug 11 that blocks baffle 2 and shift out, can carry out axial spacing to balancing piece 1 and baffle 2.
As the technical scheme provided by the scheme, one end of the baffle 2 and the buckling section of the outer circle part of the disc 3 are arranged in an arc-shaped structure.
Workpiece manufacturing process is simple, and the joint relation can be spacing in 6 directions, and secondly, the arc structure setting can the mutual adaptation with the excircle structure of dish 3, increase area of contact, and the steadiness promotes.
As the technical scheme that the present case provided, the one end of baffle 2 and dish 3 one side buckle connection of excircle portion, the other end and the one end of balancing piece 1 are at the opposite side of dish 3 and be close to dish 3 interior circular portion buckle connection.
As the technical solution provided by the present application, the baffle 2 is provided with a protrusion extending outwards along one side, and the structure of the baffle is the same as that of the protruding section 21, and the baffle can be made of high temperature resistant and high toughness alloy material, for example, GH3536 material, which axially limits the movement of the balance weight 1.
As the technical scheme provided by the scheme, the shape of the balance weight 1 is rectangular, L-shaped, square, arc or step shape, so that the actual installation is more convenient.
Another aspect is to provide a turbine disk or a compressor disk, which is equipped with a positioning assembly as described above, wherein the turbine disk 3 can be effectively balanced without forming pin holes in the disk 3. The unbalance amount of the disc 3 is eliminated, the installation is convenient, the condition that the disc 3 has stress concentration is avoided, and the reliability and the service life of the disc 3 are improved.
Another aspect provides an aircraft engine fitted with a turbine or compressor disk as described above.
The aero-engine adopting the disc can prolong the service life of the aero-engine, and promote the development and further exploration and research of the aviation field in China.
The invention provides a square positioning component and an aero-engine thereof, which are described in detail above. The principles and embodiments of the present invention are explained herein using specific examples, which are presented only to assist in understanding the core concepts of the present invention. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the invention without departing from the inventive concept, and those improvements and modifications also fall within the scope of the claims of the invention.
Claims (10)
1. A positioning assembly for the weight balance of a disc (3), said disc (3) comprising an outer circular portion and an inner circular portion, characterized by a baffle (2) and a weight (1), wherein:
one end of the baffle (2) is connected with the outer circle part of the disc (3) in a buckling manner, and the other end of the baffle is connected with one end of the balance block (1) in a buckling manner;
the other end of the balance weight (1) is in contact connection with the inner circle part of the disc (3).
2. The positioning assembly according to claim 1, wherein one end of the baffle (2) penetrates through one end of the balance weight (1) and is provided with a protruding section (21), and the protruding section (21) can be folded to be buckled with the balance weight (1).
3. The positioning assembly according to claim 1 or 2, characterized in that the inner circle of the disc (3) is provided with first grooves (31) at intervals, and the structure of the counterweight (1) passing through the first groove (31) section is matched with the structure of the first groove (31).
4. The positioning assembly of claim 3,
and a second groove (12) is arranged at the edge of one end of the balance block (1), and a lug (11) for blocking the baffle (2) from moving out is arranged at the edge of the second groove (12).
5. The positioning assembly according to claim 1, characterized in that one end of the baffle (2) is arranged in an arc-shaped configuration with a snap-in section of the outer circular portion of the disc (3).
6. A positioning assembly according to claim 3, characterized in that said baffle (2) has one end snap-fitted to one side of the outer circle of said disc (3) and the other end snap-fitted to one end of said weight (1) on the other side of said disc (3) and adjacent to the inner circle of said disc (3).
7. The positioning assembly according to claim 1, characterized in that the baffle (2) is provided with a protrusion extending outwards along one side.
8. The positioning assembly according to claim 1, characterized in that the shape of the counterweight (1) is rectangular or L-shaped or square or arc-shaped.
9. A turbine or compressor disk, wherein the positioning assembly of any one of claims 1 to 8 is mounted.
10. An aircraft engine, characterized in that a turbine or compressor disk according to claim 9 is installed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010988356.6A CN112160794B (en) | 2020-09-18 | 2020-09-18 | Positioning assembly, turbine disc or compressor disc of positioning assembly and aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010988356.6A CN112160794B (en) | 2020-09-18 | 2020-09-18 | Positioning assembly, turbine disc or compressor disc of positioning assembly and aircraft engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112160794A CN112160794A (en) | 2021-01-01 |
| CN112160794B true CN112160794B (en) | 2023-02-17 |
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| CN202010988356.6A Active CN112160794B (en) | 2020-09-18 | 2020-09-18 | Positioning assembly, turbine disc or compressor disc of positioning assembly and aircraft engine |
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