A locking device for a turbine blade
By designing positioning plates and bosses that fit together with grooves on the turbine blades to form a ring structure, the problem of axial positioning failure caused by the deformation of the locking plates is solved, thereby improving the stability and lifespan of the turbine blades.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- QINGHANG AEROSPACE (BEIJING) TECH CO LTD
- Filing Date
- 2023-11-14
- Publication Date
- 2026-07-24
AI Technical Summary
Under high temperature and high pressure conditions, existing turbine rotor blades suffer from axial positioning failure due to deformation of the locking plates, leading to blade vibration and wear, which affects the lifespan of the turbine rotor.
By using the positioning plate and the groove on the turbine disk to cooperate, and through the design of the boss and positioning groove, a positioning ring with a continuous ring structure is formed, which restricts the axial displacement of the positioning plate and the tenon, and realizes the axial positioning of the turbine blade.
It improves the axial positioning stability of turbine blades, reduces blade vibration and wear, and extends the service life of turbine rotors.
Smart Images
Figure CN117449917B_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of turbines, and more particularly to a locking device for turbine blades. Background Technology
[0002] The turbine rotor of an aero-engine is a critical structural component, and its lifespan determines the overall lifespan of the engine. The turbine rotor operates under high temperature, high pressure, and high speed conditions for extended periods, enduring corrosion from high-temperature, high-speed exhaust gases, and withstanding immense centrifugal force, aerodynamic forces, and thermal stress. Turbine rotor failure is fatal to the engine. A turbine rotor typically consists of a turbine disk and rotor blades. Each rotor blade includes a tenon, blade body, and blade crown. The outer edge of the turbine disk has a mortise and tenon structure. The turbine rotor blades are connected by inserting their lower tenons into the mortise and tenon of the turbine disk. However, axial positioning between the turbine disk and rotor blades requires other components. Current turbines use locking plates for positioning due to bending deformation, but under centrifugal force and thermal stress, the locking plates can deform, causing them to lose their axial positioning function. When the locking plates lose their axial positioning function, the rotor blades will move axially within the mortise and tenon. This movement causes significant damage to the turbine rotor, increasing blade vibration and causing friction between the blades and the casing, thus greatly reducing the lifespan of the blades and the entire turbine rotor. Summary of the Invention
[0003] In view of this, this application provides a locking device for turbine blades, which solves the problems in the prior art, improves the axial positioning of turbine blades, and facilitates the installation of the locking device.
[0004] The turbine blade locking device provided in this application adopts the following technical solution:
[0005] A locking device for a turbine blade, the turbine blade comprising a blade body and a tenon, the tenon being mounted on a turbine disk, the locking device comprising a plurality of positioning plates, the plurality of positioning plates being circumferentially distributed around the turbine axis to form a continuous annular positioning ring, the turbine disk having a groove for inserting one side of the inner ring of the positioning plate, the end face of the positioning ring facing the tenon having a boss, the end face of the tenon near the groove having a positioning groove for inserting the boss, the length of the positioning groove being greater than the length of the boss in the turbine radial direction, when the boss enters the positioning groove and the side of the boss away from the turbine axis contacts the side of the positioning groove away from the turbine axis, the positioning plate is located outside the groove and the positioning plate is aligned with the groove, when the boss is located on the side of the positioning groove near the turbine axis, the boss is locked with the positioning groove and one side of the inner ring of the positioning plate is inserted into the groove.
[0006] Optionally, the boss gradually increases in size from the inside to the outside of the turbine in the turbine radial direction, and the positioning groove gradually decreases in size from the outside to the inside of the turbine in the turbine radial direction. The large end of the boss is smaller than the large end of the positioning groove in the turbine radial direction. When the boss enters the positioning groove and the side of the boss away from the turbine shaft contacts the side of the positioning groove away from the turbine shaft, there is a gap between the small end of the boss and the positioning groove. When the small end of the boss and the small end of the positioning groove are engaged in the turbine radial direction, the boss and the positioning groove are interference fit.
[0007] Optionally, both ends of the positioning piece are provided with protrusions in the circumferential direction of the turbine. When two adjacent positioning pieces are mated, the two protrusions at the mating positions of the two positioning pieces combine to form a boss.
[0008] Optionally, the protrusion and the positioning piece are integrally formed.
[0009] Optionally, the turbine disk has a lug on its side facing the turbine intake or exhaust side, the opening of the lug facing away from the turbine shaft, and the gap between the lug and the turbine disk forms the groove.
[0010] Optionally, the boss gradually increases in size from the side closer to the positioning plate to the side farther away from the positioning plate in the turbine axial direction, and the positioning groove gradually increases in size from the groove opening to the groove bottom.
[0011] Optionally, the connection position between the boss and the positioning piece is provided with a rounded corner that is recessed inward towards the inside of the boss.
[0012] In summary, this application includes the following beneficial technical effects:
[0013] In this application, the engagement of the positioning plate and the groove on the turbine disk restricts the axial displacement of the positioning plate, and the clamping of the boss and the positioning groove restricts the displacement between the positioning plate and the tenon. The turbine disk restricts the axial displacement of the turbine blades by restricting the axial displacement of the positioning plate and the tenon.
[0014] The positioning piece of this application is easy to install: When installing the turbine blade, the tenon and mortise are engaged, and then the boss is inserted into the positioning groove. At this time, the boss is located on the side of the positioning groove away from the turbine shaft, and the boss and positioning groove are not locked. The positioning piece is located outside the groove and is aligned with the groove. The positioning piece is moved radially toward the turbine shaft until it is inserted into the groove 22 and the boss and positioning groove are locked. Multiple positioning pieces are installed sequentially to form a continuous, annular positioning ring. Attached Figure Description
[0015] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0016] Figure 1 This is a schematic diagram of the turbine blades mounted on the turbine disk in this application;
[0017] Figure 2 This is a schematic diagram of the structure of the boss and the positioning groove in this application.
[0018] Figure 3 This is a schematic diagram of the turbine blade structure of this application;
[0019] Figure 4 This is a schematic diagram of the turbine disk structure of this application;
[0020] Figure 5 This is a schematic diagram of the positioning ring structure of this application;
[0021] Figure 6 for Figure 5 A magnified structural diagram of part A in the middle;
[0022] Figure 7 This is a schematic diagram of the positioning plate in this application;
[0023] Figure 8 This is a schematic diagram of the structure of the boss in this application, which gradually increases in size from the side closer to the positioning surface to the side farther away from the positioning piece;
[0024] Figure 9 This is a schematic diagram of the positioning groove in this application, which gradually increases in size from the groove opening to the groove bottom.
[0025] Explanation of reference numerals in the attached drawings: 1. Turbine blade; 11. Blade body; 12. Tenon; 13. Positioning groove; 2. Turbine disk; 21. Lug; 22. Groove; 3. Positioning piece; 4. Positioning ring; 41. Boss; 42. Protrusion; 43. Rounded corner. Detailed Implementation
[0026] The embodiments of this application will now be described in detail with reference to the accompanying drawings.
[0027] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.
[0028] It should be noted that various aspects of embodiments within the scope of the appended claims are described below. It will be apparent that the aspects described herein can be embodied in a wide variety of forms, and any particular structure and / or function described herein is merely illustrative. Based on this application, those skilled in the art will understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects set forth herein can be used to implement the device and / or practice the method. Additionally, this device and / or method can be implemented using structures and / or functionalities other than one or more of the aspects set forth herein.
[0029] It should also be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of this application. The drawings only show the components related to this application and are not drawn according to the actual number, shape and size of the components in the actual implementation. In the actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.
[0030] Furthermore, specific details are provided in the following description to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.
[0031] This application provides a locking device for turbine blades.
[0032] like Figures 1-5As shown, a locking device for a turbine blade is provided. The turbine blade 1 includes a blade body 11, a blade crown, and a tenon 12. The tenon 12 is mounted on a turbine disk 2. The turbine disk 2 is provided with a mortise that mates with the tenon 12. The mating of the tenon 12 and the mortise enables the installation and connection of the turbine blade 1 and the turbine disk 2. The locking device includes several positioning pieces 3, which are arranged circumferentially around the turbine shaft to form a continuous annular positioning ring 4. The turbine disk 2 has a groove 22 for inserting one side of the inner ring of the positioning piece 3. The end face of the positioning ring 4 facing the tenon 12 has a boss 41. The end face of the tenon 12 near the groove 22 has a positioning groove 13 for inserting the boss 41. In the radial direction of the turbine, the length of the positioning groove 13 is greater than the length of the boss 41. When the boss 41 enters the positioning groove 13 and the side of the boss 41 away from the turbine shaft contacts the side of the positioning groove 13 away from the turbine shaft, the positioning piece 3 is located outside the groove 22 and aligned with the groove 22. The positioning piece 3 moves radially toward the turbine shaft. When the boss 41 is located on the side of the positioning groove 13 near the turbine shaft, the boss 41 is locked with the positioning groove 13 and the inner ring of the positioning piece 3 is inserted into the groove 22.
[0033] When installing turbine blade 1, the tenon 12 and mortise are engaged, and then the boss 41 is inserted into the positioning groove 13. At this time, the boss 41 is located on the side of the positioning groove 13 away from the turbine shaft, and the boss 41 and the positioning groove 13 are not locked. The positioning piece 3 is located outside the groove 22 and is aligned with the groove 22. The positioning piece 3 is moved radially toward the turbine shaft until the positioning piece 3 is inserted into the groove 22 and the boss 41 and the positioning groove 13 are locked. Multiple positioning pieces 3 are installed sequentially to form a continuous, annular positioning ring 4. The positioning piece 3 of this application is easy to install. In one embodiment, the positioning groove 13 includes a large space and a locking part. The large space is used for the boss 41 to enter the positioning groove 13. The large space is larger than the boss 41 as a whole, and the locking part and the boss 41 can form an interference fit.
[0034] In this application, the engagement between the positioning piece 3 and the groove 22 on the turbine disk 2 restricts the axial displacement of the positioning piece 3. The locking of the boss 41 and the positioning groove 13 restricts the displacement between the positioning piece 3 and the tenon 12. The turbine disk 2 restricts the axial displacement of the turbine blade 1 by limiting the axial displacement of the positioning piece 3 and the tenon 12. The positioning piece 3, which engages with the groove 22 on the turbine disk 2, abuts against one end face of the tenon 12, further restricting the displacement of the turbine blade 1 towards the positioning piece 3.
[0035] like Figure 2 , Figure 3 and Figure 6As shown, in the radial direction of the turbine, the boss 41 gradually increases in size from the inside to the outside of the turbine, and the positioning groove 13 gradually decreases in size from the outside to the inside of the turbine. In the radial direction of the turbine, the larger end of the boss 41 is smaller than the larger end of the positioning groove 13. When the boss 41 enters the positioning groove 13 and the side of the boss 41 away from the turbine axis contacts the side of the positioning groove 13 away from the turbine axis, there is a gap between the smaller end of the boss 41 and the positioning groove 13, and the boss 41 can move in the positioning groove 13. When the smaller end of the boss 41 and the smaller end of the positioning groove 13 are engaged in the radial direction of the turbine, the boss 41 and the positioning groove 13 are in an interference fit. This application reduces the length of the large space section, merges a portion of the large space section with a portion of the clamping section, reduces the size of the positioning groove 13, and minimizes the impact of the positioning groove 13 on the strength of the tenon 12 itself. When the boss 41 is located on the side of the positioning groove 13 away from the turbine shaft, the small end of the boss 41 is already inside the clamping section. The tapered design creates a gap between the small end of the boss 41 and the positioning groove 13 at this time. Only after the boss 41 moves axially does the gap between the boss 41 and the clamping section gradually decrease until an interference fit is formed. At the same time, this design allows for a larger boss 41 with the same size positioning groove 13, improving the connection strength between the boss 41 and the tenon 12, and enhancing the axial positioning effect of the turbine blade 1.
[0036] like Figure 7As shown, in one embodiment, both ends of the positioning piece 3 in the circumferential direction of the turbine are provided with protrusions 42. When two adjacent positioning pieces 3 are mated, the two protrusions 42 at the mating positions of the two positioning pieces 3 combine to form a boss 41. The two positioning pieces 3 are connected to the same tenon 12, and two adjacent tenons 12 also share a positioning piece 3. For example, three positioning pieces and four tenons are named sequentially along the circumferential direction: first positioning piece, second positioning piece, third positioning piece, first tenon, second tenon, third tenon, and fourth tenon. One protrusion 42 of the first positioning piece connects to the first tenon, and the other protrusion 42 connects to the second tenon. One protrusion 42 of the second positioning piece connects to the second tenon, and the other protrusion 42 connects to the third tenon. One protrusion 42 of the third positioning piece connects to the third tenon, and the other protrusion 42 connects to the fourth tenon. When the second positioning piece falls off, the second tenon remains connected to one protrusion 42 of the first positioning piece, and the third tenon remains connected to one protrusion 42 of the third positioning piece. At this time, the other protrusion 42 of the first positioning piece... The first positioning piece 3 and the third positioning piece 42 maintain a normal and stable fit with the first tenon, and the other protrusion 42 of the third positioning piece also maintains a normal and stable fit with the fourth tenon. That is, the first positioning piece 3 and the third positioning piece 42 will not fall off and can remain stable. The protrusion 42 of the first positioning piece 3 that fits with the second tenon can still apply force to the second tenon, providing a certain axial positioning function. Similarly, the protrusion 42 of the third positioning piece 3 that fits with the third tenon can still apply force to the third tenon, providing a certain axial positioning function. If the boss 41 is located in the middle of the positioning piece 3, with one positioning piece 3 corresponding to one tenon 12, when the positioning piece 3 falls off, the tenon 12 loses the axial positioning function originally provided by the positioning piece 3. This application improves the fault tolerance of the locking device by connecting the same tenon 12 with two positioning pieces 3 and allowing two adjacent tenons 12 to share one positioning piece 3. Even if individual positioning pieces 3 fall off, it still ensures a certain axial positioning function for the turbine blade 1.
[0037] The protrusion 42 and the positioning piece 3 are integrally formed.
[0038] like Figure 8 and Figure 9 As shown, in one embodiment, the boss 41 gradually increases in size from the side closest to the positioning surface to the side furthest from the positioning piece 3 in the turbine axial direction, and the positioning groove 13 gradually increases in size from the groove opening to the groove bottom. After the boss 41 and the positioning groove 13 engage, a clamping structure with a larger inner part and a smaller outer part is formed, which further improves the clamping strength of the boss 41 and the positioning groove 13, avoids failure due to overly rigid engagement, further prevents the boss 41 from falling out of the positioning groove 13, and improves the axial positioning effect of the turbine blade 1. It should be noted that the inclination of the boss 41 and the positioning groove 13 in the turbine axial direction should ensure that the boss 41 can smoothly enter the side of the positioning groove 13 furthest from the turbine axis.
[0039] The connection point between the boss 41 and the positioning piece 3 is provided with a rounded corner 43 that is recessed inward from the boss 41. The design of the rounded corner 43 avoids stress concentration at the connection point between the boss 41 and the positioning piece 3, improves the overall strength of the boss 41 and the positioning piece 3, and prevents the positioning piece 3 from losing its connection with the tenon 12 due to insufficient strength of the boss 41 and the positioning piece 3, thus preventing the turbine disk 2 from losing its restriction on the axial displacement of the turbine blade 1.
[0040] like Figure 4 As shown, the turbine disk 2 has a lug 21 on its side facing either the turbine intake or exhaust side. Whether the lug 21 is on the exhaust or intake side of the turbine disk 2 depends on the installation position of the locking device. The orientation of the lug 21 on the turbine disk 2 is consistent with the installation position of the locking device on the turbine disk 2. The opening of the lug 21 faces away from the turbine axis, and the gap between the lug 21 and the turbine disk 2 forms the groove 22. The lug 21 can be integrally formed with the turbine disk 2.
[0041] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.
Claims
1. A locking device for a turbine blade, the turbine blade (1) comprising a blade body (11) and a tenon (12), the tenon (12) being mounted on a turbine disk (2), characterized in that, The locking device includes several positioning plates (3), which are circumferentially distributed around the turbine axis to form a continuous annular positioning ring (4). The turbine disk (2) has a groove (22) for inserting one side of the inner ring of the positioning plate (3). The positioning ring (4) has a boss (41) on its end face facing the tenon (12). The end face of the tenon (12) near the groove (22) has a positioning groove (13) for inserting the boss (41). The length of the positioning groove (13) in the radial direction of the turbine is greater than that of the positioning plate (3). When the boss (41) is inserted into the positioning groove (13) and the side of the boss (41) away from the turbine shaft is in contact with the side of the positioning groove (13) away from the turbine shaft, the positioning piece (3) is located outside the groove (22) and the positioning piece (3) is aligned with the groove (22). When the boss (41) is located on the side of the positioning groove (13) close to the turbine shaft, the boss (41) is locked with the positioning groove (13) and the inner ring side of the positioning piece (3) is inserted into the groove (22).
2. The turbine blade locking device according to claim 1, characterized in that, In the radial direction of the turbine, the boss (41) gradually increases from the inside to the outside of the turbine, and the positioning groove (13) gradually decreases from the outside to the inside of the turbine. In the radial direction of the turbine, the large end of the boss (41) is smaller than the large end of the positioning groove (13). When the boss (41) enters the positioning groove (13) and the side of the boss (41) away from the turbine axis contacts the side of the positioning groove (13) away from the turbine axis, there is a gap between the small end of the boss (41) and the positioning groove (13). When the small end of the boss (41) and the small end of the positioning groove (13) are engaged in the radial direction of the turbine, the boss (41) and the positioning groove (13) are in an interference fit.
3. The turbine blade locking device according to claim 1, characterized in that, Both ends of the positioning piece (3) in the circumferential direction of the turbine are provided with protrusions (42). When two adjacent positioning pieces (3) are docked, the two protrusions (42) at the docking position of the two positioning pieces (3) combine to form a boss (41).
4. The turbine blade locking device according to claim 3, characterized in that, The protrusion (42) and the positioning piece (3) are integrally formed.
5. The turbine blade locking device according to claim 1, characterized in that, The turbine disk (2) has a lug (21) on its side facing the turbine intake or exhaust side. The opening of the lug (21) faces away from the turbine shaft. The gap between the lug (21) and the turbine disk (2) forms the groove (22).
6. The turbine blade locking device according to claim 1, characterized in that, In the turbine axial direction, the boss (41) gradually increases from the side closer to the positioning piece (3) to the side farther away from the positioning piece (3), and the positioning groove (13) gradually increases from the groove opening to the groove bottom.
7. The turbine blade locking device according to claim 1 or 6, characterized in that, The connection position between the boss (41) and the positioning piece (3) is provided with a rounded corner (43) that is recessed into the inside of the boss (41).