Gas turbine and turbine and blade locking structure thereof

Abstract

The invention discloses a gas turbine and a turbine and blade locking structure thereof, and relates to the technical field of gas turbines. The blade locking structure comprises a limiting ring; the limiting ring is elastic, and a first notch is formed in the limiting ring; the L-shaped clamping blocks are in one-to-one correspondence with the turbine blades; each L-shaped clamping block is arranged on the corresponding turbine blade; each L-shaped clamping block is provided with a limiting hole; the plurality of limiting pins are in one-to-one correspondence with the L-shaped clamping blocks; the limiting pin is matched with the limiting hole; a plurality of C-shaped clamping blocks; the C-shaped clamping blocks are arranged on the limiting ring in the circumferential direction of the limiting ring. And each C-shaped clamping block is elastic. Through collaborative design of the limiting rings, the L-shaped clamping blocks, the limiting pins and the C-shaped clamping blocks, bolt mounting holes do not need to be formed in the turbine disc, the problem of stress concentration caused by hole forming is fundamentally avoided, and the service life of the turbine disc is effectively prolonged.

Description

Technical Field

[0001] This application relates to the field of gas turbine technology, specifically a gas turbine and its turbine and blade locking structure. Background Technology

[0002] like Figure 1 As shown, in the turbine of a gas turbine, the turbine disk and turbine blades are connected by a tenon and mortise structure. Since the turbine blades are a crucial component of the gas turbine, the reliability of their installation and locking is directly related to the operational stability of the gas turbine. To prevent axial relative displacement between the turbine disk and turbine blades during long-term use, a common method is as follows: Figure 2 As shown, a first baffle and a second baffle are used at the front and rear ends of the turbine disk to prevent the turbine blades from moving axially. Both the first and second baffles are bolted to the turbine disk. If the baffle (i.e., the first baffle or the second baffle) is bolted to the turbine disk, holes need to be drilled at the corresponding positions on the turbine disk, which will cause stress concentration and affect the life of the turbine disk. Summary of the Invention

[0003] The purpose of this application is to provide a gas turbine and its turbine and blade locking structure to solve the technical problem that the existing blade locking structure requires bolt mounting holes on the turbine disk, which leads to stress concentration on the turbine disk and thus shortens the service life of the turbine disk.

[0004] To achieve the above objectives, this application provides the following technical solution:

[0005] Firstly, this application proposes a technical solution for a blade locking structure. This blade locking structure is applied to a turbine, which includes a turbine disk and multiple turbine blades; the blade locking structure includes:

[0006] A limiting ring; the limiting ring is elastic and has a first notch;

[0007] Multiple L-shaped locking blocks corresponding to each turbine blade; each L-shaped locking block is set on the corresponding turbine blade; each L-shaped locking block is provided with a limiting hole, the axis of which is parallel to the turbine axis; the turbine axis is the axis of the turbine disk.

[0008] Multiple limiting pins corresponding one-to-one with each L-shaped card block; the limiting pins are adapted to the limiting holes;

[0009] Multiple C-shaped locking blocks; each C-shaped locking block is disposed circumferentially on the limiting ring; and each C-shaped locking block is elastic;

[0010] The outer circumferential surface of the turbine disk is provided with limiting grooves that correspond one-to-one with each C-shaped locking block.

[0011] In one specific embodiment of the technical solution of this application, the cross-section of the limiting ring is square or circular; the difference between the outer diameter of the limiting pin and the inner diameter of the limiting hole is greater than or equal to 0.01 mm and less than or equal to 0.20 mm.

[0012] In one specific embodiment of the technical solution of this application, the ratio of the first distance to the second distance is greater than or equal to 1 / 3 and less than or equal to 1 / 2; the first distance is the distance between the upper end of the turbine blade tenon in the axial projection of the turbine along the radial direction of the turbine and the center line of the limiting ring; the second distance is the distance between the lower end of the turbine blade tenon in the axial projection of the turbine along the radial direction of the turbine and the center line of the limiting ring.

[0013] In one specific embodiment of the technical solution of this application, the number of each C-type card block is equal to the number of each turbine blade, and the C-type card blocks are distributed in a linear array around the axis of the turbine disk.

[0014] In one specific embodiment of the technical solution of this application, the limiting pin is cylindrical and its hardness is less than that of the turbine disk; or, the limiting pin is a rivet or an expansion bolt.

[0015] In one specific embodiment of the technical solution of this application, the blade locking structure further includes:

[0016] First baffle and second baffle;

[0017] Two sets of first snap-fit ​​components; one set of first snap-fit ​​components is disposed on the first baffle, and the other set of first snap-fit ​​components is disposed on the second baffle;

[0018] Two sets of second snap-fit ​​components; one set of second snap-fit ​​components is disposed at the front end of the turbine disk, and the other set of second snap-fit ​​components is disposed at the rear end of the turbine disk; the first baffle and the second baffle can be snapped with the front end and the rear end of the turbine disk respectively through the corresponding first snap-fit ​​components and second snap-fit ​​components; after the first baffle and the second baffle are snapped with the turbine disk, they are used to limit the relative displacement of each turbine blade with the turbine disk along the turbine axis.

[0019] In one specific embodiment of the technical solution of this application, the first snap-fit ​​component includes a first hook ring; the second snap-fit ​​component includes a second hook ring; the first hook ring has a second notch and is elastic; the first hook ring and the second hook ring can form a snap-fit ​​connection.

[0020] In one specific embodiment of the technical solution of this application, the first card-connecting component includes:

[0021] The first retaining ring; the first retaining ring is elastic and has a third notch; the outer side wall of the first retaining ring has a locking groove;

[0022] A second retaining ring is disposed on the first baffle; the second retaining ring is elastic and has a fourth notch; in use, the second retaining ring is used to engage with the retaining groove;

[0023] The second snap-fit ​​assembly includes an annular stop; the annular stop is used to limit the relative displacement between the first snap ring and the turbine disk along the turbine axis of the turbine disk.

[0024] Secondly, this application proposes a technical solution for a turbine. The turbine includes a blade locking structure as described in any one of the first aspects.

[0025] Thirdly, this application proposes a technical solution for a gas turbine. The gas turbine includes a blade locking structure as described in any one of the first aspects; or, it includes a turbine as described in the second aspect.

[0026] Compared with the prior art, the beneficial effects of this application are:

[0027] This application utilizes a collaborative design of a limiting ring, an L-shaped locking block, a limiting pin, and a C-shaped locking block to eliminate the need for bolt mounting holes on the turbine disk, thus fundamentally avoiding stress concentration problems caused by such holes and effectively extending the service life of the turbine disk. The limiting ring, with its first notch, can elastically contract for assembly. After resetting, it engages with the L-shaped locking blocks on each turbine blade. Combined with the limiting pins that mate with the limiting holes, this reliably restricts the axial and radial relative displacement between the limiting ring and the turbine blades. Furthermore, the C-shaped locking block engages with the turbine disk's limiting groove, further fixing the circumferential, radial, and axial positions of the limiting ring and the turbine disk. Ultimately, this achieves a comprehensive and secure locking of the turbine blades and turbine disk, adapting to the extreme operating conditions of high-speed gas turbine operation, ensuring locking reliability and gas turbine operational stability. Moreover, the overall structure relies on the elasticity of the components (i.e., the limiting ring and the C-shaped locking block) for assembly, making operation convenient and efficient. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of a connection between a turbine disk and turbine blades in the prior art;

[0029] Figure 2 This is a schematic diagram of a blade locking structure in the prior art;

[0030] Figure 3 This is a schematic diagram of a blade locking structure proposed in an embodiment of this application;

[0031] Figure 4 This is a partial schematic diagram of a blade locking structure proposed in an embodiment of this application;

[0032] Figure 5 This is a partial schematic diagram of another blade locking structure proposed in the embodiments of this application (the first retaining ring and the second retaining ring are separated);

[0033] Figure 6 This is a partial schematic diagram of another blade locking structure proposed in the embodiments of this application (the first retaining ring and the second retaining ring are engaged);

[0034] Figure 7 This is a partial schematic diagram of another blade locking structure proposed in the embodiments of this application;

[0035] Figure 8 for Figure 7 Enlarged view of section A;

[0036] Figure 9 This is a schematic diagram of a connection between a turbine disk and turbine blades as proposed in an embodiment of this application;

[0037] Figure 10 This is a schematic diagram of the structure of a limiting ring proposed in an embodiment of this application;

[0038] Figure 11 for Figure 9 A partial schematic diagram showing the connection between the turbine disk and the turbine blades;

[0039] Figure 12 for Figure 11 Cross-sectional view of the turbine disk and the limiting ring along the BB line;

[0040] Figure 13 for Figure 11 A cross-sectional view of the turbine blades and limiting ring along the CC line;

[0041] Figure 14 This is a schematic diagram of another connection structure between a turbine disk and turbine blades proposed in the embodiments of this application;

[0042] Figure 15 This is a schematic diagram showing the relative positions of a limiting ring and a turbine blade as proposed in an embodiment of this application.

[0043] In the diagram: 1. Turbine disk; 2. Turbine blade; 3. First baffle; 4. Second baffle; 5. Turbine shaft centerline; 6. Bolt; 7. Second snap-fit ​​assembly; 8. First snap-fit ​​assembly; 81. First snap ring; 811. First annular contact surface; 82. Second snap ring; 821. Second annular contact surface; 83. Snap-fit ​​groove; 84. Separation groove; 9. Elastic ring; 10. Limiting ring; 11. C-shaped locking block; 12. L-shaped locking block; 13. Limiting pin; 14. First notch; 15. Limiting groove. Detailed Implementation

[0044] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0045] It should be noted that in the description of this application, the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0046] Furthermore, it should be understood that, for ease of description, the dimensions of the various components shown in the accompanying drawings are not drawn to actual scale; for example, the thickness or width of some layers may be exaggerated relative to other layers.

[0047] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined or described in one figure, it will not need to be discussed or described in detail in the description of the subsequent figures.

[0048] It's important to understand that creating holes in the turbine disk (with the hole's centerline parallel to the turbine disk's centerline) disrupts the continuity of force transmission during operation, leading to stress concentration. The turbine disk rotates at high speed, generating significant stress. When this stress (force flow) encounters a hole, it cannot pass directly through the hole area and must instead circulate around the hole's edge. This circumventing stress line becomes highly concentrated near the hole's edge, and the smaller the hole and the sharper the edge, the higher the stress line density. In other words, because the effective load-bearing cross-section of the turbine disk decreases after creating the hole, under the same load (the turbine disk's load is positively correlated with its rotational speed), the force per unit area around the hole's edge significantly increases, resulting in stress concentration.

[0049] To address the technical problem that existing blade locking structures require bolt mounting holes in the turbine disk, leading to stress concentration and shortening the turbine disk's service life, this application proposes an embodiment of a blade locking structure. This blade locking structure is applied to a turbine, which includes a turbine disk 1 and multiple turbine blades 2.

[0050] In this embodiment, the blade locking structure includes a limiting ring 10, multiple L-shaped locking blocks 12 corresponding to each turbine blade 2, multiple limiting pins 13 corresponding to each L-shaped locking block 12, and multiple C-shaped locking blocks 11. Wherein, as... Figure 10 As shown, the limiting ring 10 has a first notch 14, and the limiting ring 10 is elastic. Figure 11 and Figure 13 As shown, each L-shaped locking block 12 is positioned on a corresponding turbine blade 2. Each L-shaped locking block 12 has a limiting hole, the centerline of which is parallel to the turbine shaft centerline 5, and the limiting pin 13 is adapted to the limiting hole. The adaptation of the limiting pin 13 to the limiting hole means that the limiting pin 13 can be inserted into the limiting hole without any radial wobble. For example, the difference between the outer diameter of the limiting pin 13 and the inner diameter of the limiting hole can be 0.01 mm or 0.05 mm, etc. Figure 11 As shown, each C-shaped locking block 11 is disposed circumferentially on the limiting ring 10, and each C-shaped locking block 11 is elastic. Figure 12 As shown, the outer circumferential surface of the turbine disk 1 is provided with limiting grooves 15 that correspond one-to-one with each of the C-shaped locking blocks 11.

[0051] In this embodiment, the relative position between the limiting ring 10 and the turbine blade 2 is not restricted, as long as the limiting ring 10 can limit the turbine blade 2 along the axial direction of the turbine disk 1 after installation. For example, it can be as follows: Figure 11 The limiting ring 10 shown is located near the upper end of the tenon in the turbine blade 2, and can also be used as follows: Figure 15 The limiting ring 10 is located near the middle of the tenon of the turbine blade 2. It should be noted that the upper end of the tenon of the turbine blade 2 is larger than the lower end. To ensure stable positioning of the turbine blade 2 by the limiting ring 10, in one embodiment of this application, the ratio of the first distance to the second distance is greater than or equal to 1 / 3 and less than or equal to 1 / 2. The first distance is the distance from the upper end of the tenon of the turbine blade 2 along the radial direction of the turbine to the center line of the limiting ring 10 in the axial projection of the turbine (i.e., as shown). Figure 15 The distance between the light-colored dashed lines shown (i.e., as shown) Figure 15 The distance S1 is shown; the second distance is the distance from the lower end of the turbine blade 2 tenon along the radial direction of the turbine to the center line of the limiting ring 10 in the axial projection of the turbine (i.e., as shown). Figure 15 (See distance S2). If the ratio of the first distance to the second distance is greater than or equal to 1 / 3 and less than or equal to 1 / 2, it indicates that the installation position of the limiting ring 10 should correspond to the upper end area of ​​the tenon of the turbine blade 2. This installation position can make full use of the larger structural size at the upper end of the tenon to provide reliable limiting support, and can also avoid the problem of weakened limiting effect caused by the positional offset of the limiting ring 10 through a reasonable radial distance ratio.

[0052] When using it, firstly as follows Figure 1 As shown, each turbine blade 2 ( Figure 1 The turbine blade 2 (not shown, L-shaped locking block 12) forms a tenon joint with the turbine disk 1; further, a contraction force is applied to the limiting ring 10 by tightening the first notch 14 provided on the limiting ring 10, causing the diameter of the limiting ring 10 to decrease; further, the limiting ring 10 with its reduced diameter is aligned with the L-shaped locking block 12 on each turbine blade 2, and then the contraction force applied to the limiting ring 10 is released; further, as Figure 9 As shown, the limiting ring 10, under its own elastic force, can be engaged into the grooves formed by each L-shaped locking block 12 and the corresponding turbine blade 2; further, each limiting pin 13 is driven into the corresponding limiting hole; further, as... Figure 12 As shown, the C-shaped locking block 11 on the limiting ring 10 is inserted into the corresponding limiting groove 15 in the turbine disk 1.

[0053] In this embodiment, if the limiting pin 13 is driven into the corresponding limiting hole, then as follows: Figure 13 As shown, under the constraint of the L-shaped locking block 12 and the limiting pin 13, the limiting ring 10 and the turbine blade 2 cannot produce relative displacement along their own axial direction and along their own radial direction; if the C-shaped locking block 11 is inserted into the corresponding limiting groove 15 in the turbine disk 1, then as Figure 12 As shown, the limiting ring 10 cannot generate relative displacement with respect to the turbine disk 1 in the circumferential, radial, and axial directions. That is, in this embodiment, through the cooperation of the limiting ring 10, the L-shaped locking block 12, the limiting pin 13, and the C-shaped locking block 11, the relative displacement between the turbine blade 2 and the turbine disk 1 along the turbine axis 5 can be reliably limited, achieving a stable lock between the two. Furthermore, there is no need to drill bolt mounting holes on the turbine disk 1 throughout the process, thus avoiding stress concentration problems at the source and effectively extending the service life of the turbine disk 1.

[0054] In this embodiment, the number of C-type locking blocks 11 is not limited. For example, there can be 10 or 20 C-type locking blocks 11. In order for the limiting ring 10 and the turbine disk 1 to form a stable limiting through each C-type locking block 11, in one embodiment of this application, the number of each C-type locking block 11 is equal to the number of each turbine blade 2, and the C-type locking blocks 11 are distributed in an array around the axis of the turbine disk 1.

[0055] In the embodiments of this application, the shape and structure of the limiting ring 10 are not limited, as long as the limiting ring 10 can cooperate with the L-shaped locking block 12, the limiting pin 13, and the C-shaped locking block 11 to lock the turbine blade 2 to the turbine disk 1. For example, the cross-section of the limiting ring 10 can be square; or, as... Figure 12 and Figure 13 As shown, the cross-section of the limiting ring 10 can also be circular.

[0056] In the embodiments of this application, the matching of the limiting pin 13 with the limiting hole means that the limiting pin 13 can be inserted into the limiting hole, and the limiting pin 13 will not wobble radially after being inserted into the limiting hole. That is to say, in this embodiment, it is necessary to ensure that the limiting pin 13 can be easily and smoothly inserted into the limiting hole, and also to ensure that the limiting pin 13 will not wobble after being inserted into the limiting hole. Based on this, after multiple studies, the inventors found that controlling the difference between the outer diameter of the limiting pin 13 and the inner diameter of the limiting hole within the range of greater than or equal to 0.01 mm and less than or equal to 0.20 mm can ensure that the limiting pin 13 can be smoothly inserted into the limiting hole, and also ensure that the limiting pin 13 will not wobble after being inserted into the limiting hole.

[0057] In this embodiment, to prevent the limiting pin 13 from disengaging after being inserted into the limiting hole, a hammer or other tool can be used to strike the limiting pin 13 along its axial direction to deform both ends of the limiting pin 13, thereby making the diameter of both ends of the limiting pin 13 larger than the inner diameter of the limiting hole. If the diameter of both ends of the limiting pin 13 is larger than the inner diameter of the limiting hole, the limiting pin 13 cannot disengage from the limiting hole along its own axial direction, thus achieving reliable fixation between the limiting pin 13 and the L-shaped locking block 12, further ensuring the connection stability between the turbine blade 2 and the limiting ring 10, and ensuring that the entire blade locking structure can maintain a stable locked state under the high-speed operation of the gas turbine.

[0058] In order to prevent the limiting pin 13 from damaging the turbine disk 1 when it is struck, in the embodiments of this application, the hardness of the limiting pin 13 can be lower than the hardness of the turbine disk 1.

[0059] Of course, in other embodiments of this application, the limiting pin 13 can also be similar to a rivet or an expansion screw, etc. After it is inserted into the limiting hole, the outer diameter of its two ends can be changed with the help of a tool, so that the limiting pin 13 cannot be dislodged from the limiting hole along its own axis.

[0060] It should be noted that during gas turbine operation, the turbine blades 2 are subjected to enormous centrifugal force from high-speed rotation and the continuous impact force of high-temperature airflow. Relying solely on the cooperation of the limiting ring 10, L-shaped locking block 12, limiting pin 13, and C-shaped locking block 11 for basic locking may still pose a risk of slight axial displacement between the turbine blades 2 and the turbine disk 1 under long-term extreme operating conditions. To further improve the reliability of the blade locking structure, achieve dual stable limiting of the turbine blades 2 and turbine disk 1, and avoid potential safety hazards to gas turbine operation due to the failure of a single locking structure, in one embodiment of this application, the blade locking structure may further include a first baffle 3 and a second baffle 4, two sets of first locking components 8, and two sets of second locking components 7. Figure 3As shown, one set of the two sets of first engaging components 8 is disposed on the first baffle 3, and the other set of first engaging components 8 is disposed on the second baffle 4. One set of the two sets of second engaging components 7 is disposed on the front end of the turbine disk 1, and the other set of second engaging components 7 is disposed on the rear end of the turbine disk 1. In this embodiment, the first baffle 3 and the second baffle 4 can be engaged with the front end and the rear end of the turbine disk 1 respectively through the corresponding first engaging components 8 and second engaging components 7. After the first baffle 3 and the second baffle 4 are engaged with the turbine disk 1, they are used to limit the relative displacement between each turbine blade 2 and the turbine disk 1 along the turbine axis 5. The turbine axis 5 is the axis of the turbine disk 1.

[0061] In the embodiments of this application, there are no restrictions on the connection method between the second snap-fit ​​component 7 and the turbine disk 1. For example, the second snap-fit ​​component 7 can be welded and fixed to the turbine disk 1, or it can be an integral structure with the turbine disk 1.

[0062] It needs to be clear that existing technologies, such as Figure 2 As shown, the connection between the first baffle 3 and the second baffle 4 and the turbine disk 1 via bolts 6 requires drilling holes in the turbine disk 1, which causes stress concentration and reduces its service life. Furthermore, the protruding bolt heads disturb the surrounding airflow during turbine rotation, leading to temperature rise in the turbine disk 1 and reducing turbine efficiency. This embodiment addresses this by using two sets of first snap-fit ​​components 8 and two sets of second snap-fit ​​components 7 to reliably snap the first baffle 3 and the second baffle 4 to the front and rear ends of the turbine disk 1, respectively, replacing the traditional bolt connection method and solving the technical drawbacks of bolt connections at the source. This structure eliminates the need for drilling holes at corresponding positions on the turbine disk 1, effectively avoiding stress concentration and extending the service life of the turbine disk 1. Simultaneously, the elimination of protruding bolt heads prevents disturbance of the surrounding airflow during turbine rotation, reducing temperature rise in the turbine disk 1 caused by airflow disturbance and thus maintaining turbine efficiency. In addition, after the first baffle 3 and the second baffle 4 are engaged with the turbine disk 1, they can stably limit the slight relative displacement between each turbine blade 2 and the turbine disk 1 along the turbine axis 5, ensuring the reliability of the turbine blade 2 installation and locking, and thus ensuring the stability of the gas turbine operation. This not only takes into account the firmness of the connection between the turbine blade 2 and the turbine disk 1, but also optimizes the aerodynamic performance and structural safety of the turbine.

[0063] It is important to understand that since the first snap-fit ​​assembly 8 and the second snap-fit ​​assembly 7, which form a snap-fit ​​connection between the first baffle 3 and the turbine disk 1, are completely identical in structural design, connection principle, and assembly logic to the first snap-fit ​​assembly 8 and the second snap-fit ​​assembly 7, which form a snap-fit ​​connection between the second baffle 4 and the turbine disk 1, will be used as an example in subsequent embodiments to describe in detail the specific structure, assembly steps, and working principle of the first snap-fit ​​assembly 8 and the second snap-fit ​​assembly 7, in order to avoid redundancy, the following embodiments will only use the snap-fit ​​relationship between the first baffle 3 and the turbine disk 1 as an example to describe the specific structure, assembly steps, and working principle of the first snap-fit ​​assembly 8 and the second snap-fit ​​assembly 7. The details of how the second baffle 4 and the turbine disk 1 are snap-fitted through the first snap-fit ​​assembly 8 and the second snap-fit ​​assembly 7 will not be repeated. The structural configuration and assembly method in actual application can be directly referred to the snap-fit ​​structure corresponding to the first baffle 3.

[0064] In this embodiment, the structure of the first snap-fit ​​component 8 and the second snap-fit ​​component 7 is not limited, as long as the first snap-fit ​​component 8 and the second snap-fit ​​component 7 can reliably snap the first baffle 3 and the turbine disk 1 together. For example, the first snap-fit ​​component 8 and the second snap-fit ​​component 7 can be at least as shown in Embodiment 1 and Embodiment 2 below.

[0065] Embodiment 1 of the first and second snap-fit ​​components

[0066] In this embodiment, as Figure 4 As shown, the first snap-fit ​​assembly 8 may include a first hook ring. The second snap-fit ​​assembly 7 may include a second hook ring. In this embodiment, the hook ring (i.e., the first hook ring or the second hook ring) refers to a ring-shaped hook with a C-shaped cross-section. The first hook ring has a second notch (not shown in the figure) and is elastic. In this embodiment, the second notch of the first hook ring is as described above... Figure 10 The first notch 14 on the limiting ring 10 shown, as well as the third and fourth notches mentioned below, are similar and will not be described further. The diameter of the first hook ring can be adjusted by external force using the second notch on the first hook ring. Furthermore, as... Figure 4 As shown, this allows the first hook ring and the second hook ring to engage.

[0067] In use, if it is necessary to reliably engage the first baffle 3 with the turbine disk 1 using the first and second hook rings, firstly, radial tension is applied to the first hook ring using the second notch on it, utilizing the elastic properties of the first hook ring to increase its diameter; then, the enlarged first hook ring (i.e., Figure 4 The first snap-fit ​​component 8) is fitted onto the second hook ring (i.e. Figure 4 The second snap-fit ​​assembly 7) is located outside the first hook ring; further, a contraction force is applied to the first hook ring to cause it to contract, the direction of the contraction force being parallel to the radial direction of the turbine disk 1 and pointing from the outer side of the turbine disk 1 to the inner side (i.e., as shown in the image). Figure 4 As shown in direction E); further, since both the first and second hook rings are elastic, under the action of contraction force, the first hook ring can form a shape with the second hook ring as shown in the figure. Figure 4 The circumferential snap-fit ​​connection shown in the figure has an interlocking and limiting structure between the two after snapping, which can effectively prevent the first baffle 3 and the turbine disk 1 from relative displacement along the turbine axis 5, thereby achieving reliable fixation of the first baffle 3 and the turbine disk 1 and providing stable support for limiting the axial displacement of the turbine blade 2.

[0068] It should be noted that in this embodiment, the cooperation of the first hook ring and the second hook ring enables a reliable snap-fit ​​connection between the first baffle 3 and the turbine disk 1, replacing the traditional bolt connection to avoid stress concentration and airflow disturbance problems. However, if maintenance or replacement of the first baffle 3, turbine disk 1, or other components is required after installation, the snap-fit ​​can only be released by breaking the elastic first hook ring or the second hook ring with external force. This makes it impossible to completely disassemble and reuse the components, increasing the cost of component replacement and extending maintenance time. To solve this problem and meet the dual requirements of reliable fixing and convenient reuse of the snap-fit ​​structure in practical applications, and to avoid resource waste caused by destructive disassembly, this application further provides a second embodiment of the first snap-fit ​​assembly and the second snap-fit ​​assembly. Through a special structural design, it ensures the stability of the snap-fit ​​connection between the first baffle 3 and the turbine disk 1 while achieving non-destructive disassembly and reuse of the components.

[0069] Embodiment 2 of the first and second snap-fit ​​components

[0070] In this embodiment, the first snap-fit ​​assembly 8 includes a first snap ring 81 and a second snap ring 82. Wherein, as... Figure 5 As shown, the first retaining ring 81 has a third notch (not shown in the figure) and is elastic; the outer wall of the first retaining ring 81 has a locking groove 83. The second retaining ring 82 is disposed on the first baffle 3, the second retaining ring 82 is elastic, and the second retaining ring 82 has a fourth notch. In use, the second retaining ring 82 is used to engage with the locking groove 83. The second locking assembly 7 includes an annular stop. Figure 5 As shown, the annular stop is used to limit the relative displacement between the first retaining ring 81 and the turbine disk 1 along the turbine axis 5.

[0071] In the embodiments of this application, the snap-fit ​​groove 83 formed on the outer wall of the first snap ring 81 is not limited. For example, the snap-fit ​​groove 83 can be a U-shaped groove in the shape of an annulus (not shown in the figure; U-shaped grooves are common grooves and will not be shown or described in detail here); or, as Figure 7As shown, the first retaining ring 81 includes an inner ring and an outer ring with different outer diameters; the inner ring and the outer ring are staggered along the axial direction of the turbine disk 1 to form the first retaining ring 81, and a retaining groove 83 is formed between the inner ring and the outer ring.

[0072] It should be noted that in the embodiments of this application, if the first baffle 3 and the second baffle 4 are in a ring shape connected end to end, then corresponding notches need to be provided in the first baffle 3 and the second baffle 4. If the first baffle 3 and the second baffle 4 are in a ring shape formed by splicing multiple arc segments, then no notches need to be provided.

[0073] In use, if a reliable engagement is required between the first baffle 3 and the turbine disk 1 via the first engaging assembly 8 and the second engaging assembly 7, radial tension is first applied to the first retaining ring 81 using the third notch on the first retaining ring 81, utilizing the elastic properties of the first retaining ring 81 to increase its diameter; then the enlarged first retaining ring 81 is fitted onto the turbine disk 1 and the annular stop (i.e., as shown in the image). Figure 5 The second snap-fit ​​assembly 7 shown is between; further, a contraction force is applied to the first snap ring 81 (i.e., as shown). Figure 5 The force F1 shown is used to retract the first retaining ring 81 into the groove formed by the turbine disk 1 and the second retaining assembly 7; further, radial tension is applied to the second retaining ring 82 by means of the fourth notch on the second retaining ring 82, and the elasticity of the second retaining ring 82 is used to increase its diameter; then the enlarged second retaining ring 82 is fitted between the turbine disk 1 and the first retaining ring 81, and a thrust is applied to the second retaining ring 82 (i.e., as shown). Figure 5 The force F2 shown is used to align the second retaining ring 82 with the engaging groove 83 in the first retaining ring 81; further, the contraction force applied to the first retaining ring 81 is released, and the first retaining ring 81 is reset so that it can engage with the second retaining ring 82 through the engaging groove 83. The state after the first retaining ring 81 and the second retaining ring 82 are engaged is as follows: Figure 6 As shown.

[0074] In this embodiment, the first retaining ring 81, with its own elasticity and adjustable diameter due to the third notch, is fitted between the turbine disk 1 and the annular stop (i.e., the second snap-fit ​​assembly 7), and its axial displacement along the turbine axis 5 is restricted by the annular stop. The second retaining ring 82 on the first baffle 3, with its own elasticity and expanded due to the fourth notch, can be fitted between the first retaining ring 81 and the turbine disk 1. Further, when the first retaining ring 81 is aligned with the snap-fit ​​groove 83 of the first retaining ring 81, if the first retaining ring 81 is released, the elastic tension of the first retaining ring 81 causes the snap-fit ​​groove 83 to fit tightly with the second retaining ring 82. The annular stop and the snap-fit ​​structure (i.e., the first retaining ring 81 and the second retaining ring 82) work together to restrict the axial movement of the first retaining ring 81 and the second retaining ring 82, and also prevent the first retaining ring 81 and the second retaining ring 82 from loosening radially through their interlocking fixation, ultimately achieving a reliable snap-fit ​​between the first baffle 3 and the turbine disk 1 (i.e., as shown in the image). Figure 6 (The snap-in state is shown).

[0075] In use, if it is necessary to remove the first retaining ring 81 and the second retaining ring 82 without damage, first apply a radially inward contraction force (with) to the first retaining ring 81. Figure 5 The force F1 in the middle is in the same direction, and this force will compress the first retaining ring 81. If the first retaining ring 81 is compressed, the retaining groove 83 and the second retaining ring 82 will disengage from circumferential engagement (as shown in the image). Figure 5 (As shown). Then, radial tension is applied to the second retaining ring 82 using the fourth notch, and its elastic properties are used to increase its diameter, allowing it to be easily removed from the outside of the first retaining ring 81. Finally, the contraction force applied to the first retaining ring 81 is removed, and tension is applied to the first retaining ring 81 to increase its diameter. Then, the first retaining ring 81 is directly removed from between the turbine disk 1 and the annular stop (second retaining assembly 7). The entire process does not require damage to any parts, achieving non-destructive removal of the first retaining ring 81 and the second retaining ring 82, ensuring that the parts can be reused.

[0076] In this embodiment, only after the contraction force applied to the first retaining ring 81 is removed can the first retaining ring 81 automatically spring back (i.e., the first retaining ring 81 always maintains an outward expansion trend). Only then can the first retaining ring 81 and the second retaining ring 82 form a tight circumferential engagement through the engaging groove 83 of the first retaining ring 81, thereby achieving the engaging and limiting of the first baffle 3 and the turbine disk 1. To ensure that the first retaining ring 81 always maintains an outward expansion trend, in one embodiment of this application, the blade locking structure may further include an elastic ring 9, such as... Figure 7 As shown, the elastic ring 9 is used to apply an elastic force to the first retaining ring 81, which causes the first retaining ring 81 to expand.

[0077] In this embodiment, the location of the elastic ring 9 is not limited, as long as the elastic ring 9 can apply an elastic force to the first retaining ring 81, and this elastic force can drive the first retaining ring 81 to expand. For example, the elastic ring 9 can be located between the first retaining ring 81 and the second retaining ring 82; or it can be located as follows: Figure 7 As shown, it is positioned between the turbine disk 1 and the first retaining ring 81.

[0078] In this embodiment, the elastic ring 9 continuously applies an elastic force to the first retaining ring 81, ensuring that the first retaining ring 81 always maintains an outward expansion trend. This allows the retaining groove 83 of the first retaining ring 81 to form a tight and stable circumferential engagement with the second retaining ring 82. Ultimately, this achieves a long-term reliable engagement between the first baffle 3 and the turbine disk 1, stably limiting the relative displacement of the turbine blade 2 and the turbine disk 1 along the turbine axis 5. In other words, the elastic ring 9 not only avoids the risk of loosening of the engagement between the first retaining ring 81 and the second retaining ring 82 due to vibrations generated during long-term high-speed turbine operation, but also eliminates the problem of axial displacement of the turbine blade 2 caused by engagement failure of the first retaining ring 81 and the second retaining ring 82, further ensuring the stability of the gas turbine operation.

[0079] In this embodiment, the shape and structure of the elastic ring 9 are not limited, as long as the elastic ring 9 can apply an elastic force to the first retaining ring 81, and the elastic force can drive the first retaining ring 81 to expand. For example, the elastic ring 9 can have at least two forms: one is an elastic ring 9 formed by multiple springs arranged in a ring, with the elastic deformation direction of each spring matching the radial direction of the ring, and a stable elastic force is continuously provided through the coordinated deformation of multiple springs; the other is as follows... Figure 7 As shown, the elastic ring 9 is a ring formed by a V-shaped cross section. It utilizes the elastic properties of the V-shaped structure itself to generate a continuous opening force. Both structures can provide a lasting opening driving force for the first retaining ring 81, ensuring the long-term stability of the engagement between the first retaining ring 81 and the second retaining ring 82.

[0080] It should be noted that the more components the first retaining assembly 8 has, the higher the risk of overall damage due to prolonged exposure to the vibration environment of the turbine's high-speed operation. While the elastic ring 9 ensures the expansion trend of the first retaining ring 81, it also increases structural complexity and potential failure points. To ensure that the first retaining ring 81 remains in an expanded state even without the elastic ring 9, thereby forming a tight and stable circumferential engagement with the second retaining ring 82, in one embodiment of this application, as shown... Figure 8 As shown, the first retaining ring 81 includes a first annular contact surface 811, and the second retaining ring 82 includes a second annular contact surface 821. The radial direction of the turbine disk 1 is perpendicular to the first annular contact surface 811 and the second annular contact surface 821. When the first retaining ring 81 and the second retaining ring 82 are not subjected to any external force, the diameter of the first annular contact surface 811 is larger than the diameter of the second annular contact surface 821.

[0081] In this embodiment, by coordinating the diameters of the first annular contact surface 811 and the second annular contact surface 821 (the diameter of the first annular contact surface 811 is larger than the diameter of the second annular contact surface 821 when there is no external force), and by setting both the first annular contact surface 811 and the second annular contact surface 821 to be radially perpendicular to the turbine disk 1, the dependence on an additional elastic ring 9 is eliminated from the source. A tight engagement between the first retaining ring 81 and the second retaining ring 82 can be achieved without the need for an external elastic component (i.e., the elastic ring 9). When the second retaining ring 82 is inserted into the retaining groove 83 of the first retaining ring 81, due to the natural diameter advantage of the first annular contact surface 811, an outward expansion tension is automatically generated radially along the turbine disk 1. This tension direction is perfectly matched to the radial direction of the turbine disk 1, driving the retaining groove 83 and the contact surface of the second retaining ring 82 to form a tight fit, avoiding gaps. In other words, this design eliminates the need for additional components such as the elastic ring 9, simplifying the overall complexity of the blade locking structure and reducing potential failure points when multiple components work together. It also utilizes the natural tension brought about by the diameter difference to resist the vibration and impact generated during the high-speed operation of the turbine, effectively avoiding the risk of the first retaining ring 81 and the second retaining ring 82 becoming loose due to vibration. At the same time, it prevents the first baffle 3 and the turbine disk 1 from being relatively displaced along the turbine axis 5 due to the gap in the retaining mechanism, which could lead to the axial movement of the turbine blade 2. Ultimately, it ensures the long-term reliable limiting effect of the blade locking structure and provides structural support for the stable operation of the gas turbine.

[0082] It is important to understand that during the long-term operation and maintenance of the gas turbine turbine, the blade locking structure not only needs to achieve stable fixation of the first baffle 3 and the turbine disk 1 to limit the axial displacement of the turbine blade 2 through the snap-fit ​​engagement of the first retaining ring 81 and the second retaining ring 82, but also needs to meet the requirements for non-destructive disassembly and reuse of the first retaining ring 81 and the second retaining ring 82 during subsequent shutdown maintenance. If the second retaining ring 82 and the snap-fit ​​groove 83 in the first retaining ring 81 form a snap-fit, and the contact surface of the two is only fixed by biting without any special structural design, there will be a difficulty in applying separation force by inserting tools into the snap-fit ​​gap during disassembly. Forcibly prying may damage the first retaining ring 81, the second retaining ring 82, or the annular stop. In order to facilitate the application of separation force to the second retaining ring 82 during disassembly (i.e., as... Figure 5 The force F1 shown, in one embodiment of this application, is as follows: Figure 6 As shown, after the second retaining ring 82 and the retaining groove 83 in the first retaining ring 81 are engaged, a separation groove 84 is also formed between the first retaining ring 81 and the second retaining ring 82.

[0083] This embodiment, through the design of the separation groove 84, eliminates the problem from the outset that tools (e.g., pry bars or levers) are difficult to insert into the locking gap during disassembly, and that forced prying can easily damage components. Ultimately, when the first retaining ring 81 and the second retaining ring 82 are separated, tools can easily be inserted into the separation groove 84 to apply precise separation force, completing the non-destructive disassembly of the first retaining ring 81 and the second retaining ring 82. In other words, the design of the separation groove 84 not only avoids the risk of damage to the first retaining ring 81, the second retaining ring 82, or the annular stop block due to improper force during disassembly, but also avoids the problems of excessively long maintenance time and low component reuse rate caused by the difficulty in disassembling the locking structure, ensuring the ease of maintenance and component economy of the blade locking structure during long-term use.

[0084] This concludes the description of Embodiment 2 of the first and second snap-fit ​​components.

[0085] It is important to understand that the coordinated arrangement of two sets of first and two sets of second snap-fit ​​components allows the first and second baffles to reliably engage with the front and rear ends of the turbine disk, respectively, replacing traditional bolt connections and fundamentally solving the technical drawbacks of bolted connections. This structure eliminates the need for drilling holes at relative positions on the turbine disk, effectively avoiding stress concentration and extending the service life of the turbine disk.

[0086] In the embodiments of this application, a blade locking structure centered on the limiting ring 10 (hereinafter referred to as the first locking structure) and a blade locking structure centered on the first snap-fit ​​component 8 and the second snap-fit ​​component 7 (hereinafter referred to as the second locking structure) can be used simultaneously, as long as the first locking structure and the second locking structure do not interfere with each other during installation through reasonable design. For example, it can be as follows: Figure 14 As shown, the upper end of the tenon of the turbine blade 2 is axially limited by the first locking structure; the lower end of the tenon of the turbine blade 2 is axially limited by the second locking structure.

[0087] The blade locking structure embodiment proposed in this application, through the coordinated design of the limiting ring, L-shaped locking block, limiting pin, and C-shaped locking block, eliminates the need for bolt mounting holes on the turbine disk, fundamentally avoiding stress concentration problems caused by opening holes and effectively extending the service life of the turbine disk. The limiting ring can elastically contract for assembly via the first notch, and after resetting, it engages with the L-shaped locking blocks of each turbine blade. In conjunction with the limiting pins that match the limiting holes, it can reliably limit the axial and radial relative displacement between the limiting ring and the turbine blade. Furthermore, the engagement of the C-shaped locking block with the turbine disk limiting groove further fixes the circumferential, radial, and axial positions of the limiting ring and the turbine disk, ultimately achieving a comprehensive and stable locking of the turbine blade and the turbine disk. This is suitable for the extreme operating conditions of high-speed gas turbine operation, ensuring locking reliability and gas turbine operating stability. Moreover, the overall structure relies on the elasticity of the components (i.e., the limiting ring and C-shaped locking block) for assembly, making operation convenient and efficient.

[0088] Having described the blade locking structure proposed in the embodiments of this application, the following describes an embodiment of a turbine proposed in this application, which includes the blade locking structure as described in any of the embodiments above.

[0089] The turbine embodiment proposed in this application, through the collaborative design of a limiting ring, an L-shaped locking block, a limiting pin, and a C-shaped locking block, eliminates the need for bolt mounting holes on the turbine disk, fundamentally avoiding stress concentration problems caused by opening holes and effectively extending the service life of the turbine disk. The limiting ring can elastically contract via a first notch for assembly. After resetting, it engages with the L-shaped locking blocks of each turbine blade. In conjunction with the limiting pins that match the limiting holes, it reliably limits the axial and radial relative displacement between the limiting ring and the turbine blades. Furthermore, the engagement of the C-shaped locking block with the turbine disk's limiting groove further fixes the circumferential, radial, and axial positions of the limiting ring and the turbine disk, ultimately achieving a comprehensive and secure locking of the turbine blades and the turbine disk. This adapts to the extreme operating conditions of high-speed gas turbine operation, ensuring locking reliability and gas turbine operational stability. Moreover, the overall structure relies on the elasticity of the components (i.e., the limiting ring and the C-shaped locking block) for assembly, making operation convenient and efficient.

[0090] Having described the turbine proposed in the embodiments of this application, we now describe a gas turbine proposed in this application. This gas turbine includes a blade locking structure as described in any of the above embodiments; or, it includes a turbine as described in any of the above embodiments.

[0091] The gas turbine embodiment proposed in this application, through the coordinated design of a limiting ring, an L-shaped locking block, a limiting pin, and a C-shaped locking block, eliminates the need for bolt mounting holes on the turbine disk, fundamentally avoiding stress concentration problems caused by opening holes and effectively extending the service life of the turbine disk. The limiting ring can elastically contract via a first notch for assembly. After resetting, it engages with the L-shaped locking blocks of each turbine blade. In conjunction with the limiting pins that match the limiting holes, it reliably limits the axial and radial relative displacement between the limiting ring and the turbine blades. Furthermore, the engagement of the C-shaped locking block with the turbine disk's limiting groove further fixes the circumferential, radial, and axial positions of the limiting ring and the turbine disk, ultimately achieving a comprehensive and secure locking of the turbine blades and the turbine disk. This adapts to the extreme operating conditions of high-speed gas turbine operation, ensuring locking reliability and gas turbine operational stability. Moreover, the overall structure relies on the elasticity of the components (i.e., the limiting ring and the C-shaped locking block) for assembly, making operation convenient and efficient.

[0092] Although embodiments of this application have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of this application, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A blade locking structure applied to a turbine, the turbine comprising a turbine disk (1) and a plurality of turbine blades (2); characterized in that, The blade locking structure includes: A limiting ring (10); the limiting ring (10) is elastic, and the limiting ring (10) is provided with a first notch (14); Multiple L-shaped locking blocks (12) corresponding one-to-one with each turbine blade (2); each L-shaped locking block (12) is set on the corresponding turbine blade (2); each L-shaped locking block (12) is provided with a limiting hole, the axis of the limiting hole is parallel to the turbine axis (5); the turbine axis (5) is the axis of the turbine disk (1); Multiple limiting pins (13) corresponding one-to-one with each L-shaped card block (12); the limiting pins (13) are adapted to the limiting holes; Multiple C-shaped locking blocks (11); each C-shaped locking block (11) is disposed on the limiting ring (10) circumferentially; and each C-shaped locking block (11) is elastic; The outer circumferential surface of the turbine disk (1) is provided with limiting grooves (15) that correspond one-to-one with each C-type card block (11).

2. The blade locking structure according to claim 1, characterized in that, The cross-section of the limiting ring (10) is square or circular; the difference between the outer diameter of the limiting pin (13) and the inner diameter of the limiting hole is greater than or equal to 0.01 mm and less than or equal to 0.20 mm.

3. The blade locking structure according to claim 1, characterized in that, The ratio of the first distance to the second distance is greater than or equal to 1 / 3 and less than or equal to 1 / 2; the first distance is the distance between the upper end of the tenon of the turbine blade (2) along the radial direction of the turbine and the center line of the limiting ring (10) in the axial projection of the turbine; the second distance is the distance between the lower end of the tenon of the turbine blade (2) along the radial direction of the turbine and the center line of the limiting ring (10) in the axial projection of the turbine.

4. The blade locking structure according to claim 1, characterized in that, The number of each C-type card block (11) is equal to the number of each turbine blade (2), and the C-type card blocks (11) are distributed in a linear array around the axis of the turbine disk (1).

5. The blade locking structure according to claim 1, characterized in that, The limiting pin (13) is cylindrical, and the hardness of the limiting pin (13) is less than that of the turbine disk (1); or, the limiting pin (13) is a rivet or an expansion screw.

6. The blade locking structure according to any one of claims 1 to 5, characterized in that, The blade locking structure also includes: First baffle (3) and second baffle (4); Two sets of first snap-fit ​​components (8); one set of first snap-fit ​​components (8) is disposed on the first baffle (3), and the other set of first snap-fit ​​components (8) is disposed on the second baffle (4); Two sets of second snap-fit ​​components (7); one set of second snap-fit ​​components (7) is disposed at the front end of the turbine disk (1), and the other set of second snap-fit ​​components (7) is disposed at the rear end of the turbine disk (1); the first baffle (3) and the second baffle (4) can be snapped with the front end and the rear end of the turbine disk (1) respectively through the corresponding first snap-fit ​​components (8) and the second snap-fit ​​components (7); after the first baffle (3) and the second baffle (4) are snapped with the turbine disk (1), they are used to limit the relative displacement of each turbine blade (2) and the turbine disk (1) along the turbine axis (5).

7. The blade locking structure according to claim 6, characterized in that, The first snap-fit ​​assembly (8) includes a first hook ring; the second snap-fit ​​assembly (7) includes a second hook ring; the first hook ring has a second notch and is elastic; the first hook ring and the second hook ring are capable of snapping together.

8. The blade locking structure according to claim 6, characterized in that, The first card-connecting component (8) includes: First retaining ring (81); the first retaining ring (81) is elastic, and the first retaining ring (81) is provided with a third notch; the outer side wall of the first retaining ring (81) is provided with a retaining groove (83); A second retaining ring (82) is disposed on the first baffle (3); the second retaining ring (82) is elastic and is provided with a fourth notch; in use, the second retaining ring (82) is used to engage with the retaining groove (83); The second snap-fit ​​assembly (7) includes an annular stop; the annular stop is used to limit the relative displacement between the first snap ring (81) and the turbine disk (1) along the turbine axis (5) of the turbine disk (1).

9. A turbine, characterized in that, Includes the blade locking structure as described in any one of claims 1 to 8.

10. A gas turbine, characterized in that, It includes the blade locking structure as described in any one of claims 1 to 8; or, it includes the turbine as described in claim 9.

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