Integrated Lock Piece, Turbine Rotor and Their Assembly Method

Abstract

The present invention discloses an integrated locking piece, a turbine rotor and an assembly method thereof. After assembling the blade and the turbine disk by using the integrated locking piece, the axial positions of the blades are locked from both sides by two axial edge portions, which also play a role in controlling the air flow rate. The radial edge portion abuts against the disk edge of the turbine disk, and there is a gap between the damping portion and the inner side surface of the blade flange. So that the damping portion can be attached to the inner side surface of the blade flange under the action of centrifugal force during the working state, achieving the effect of friction damping. It integrates the functions of the existing locking piece, damper and sealing piece, realizes the functions of three parts with one part, greatly reduces the number of parts and the total weight on the turbine rotor, greatly simplifies the assembly process of the turbine rotor, avoids the problem of reduced engine reliability caused by improper assembly of parts, and greatly reduces the number of replacement parts that must be replaced when disassembling and reassembling the turbine rotor during engine maintenance, saving the replacement cost.

Description

Technical Field

[0001] The present invention relates to the technical field of turbine rotor assembly, and in particular, to an integrated locking piece. In addition, the present invention particularly relates to a turbine rotor using the above integrated locking piece, and also relates to an assembly method of the above turbine rotor. Background Art

[0002] The structural design of a turbine rotor needs to consider various requirements. When designing a turbine rotor without a guide disk and non-integral bladed disk, it is usually necessary to design a locking piece in the rotor to axially position the blades. When the excitation amplitude value of the blades at the resonance frequency is large, it is necessary to design a damper between the blades and the turbine disk to dissipate the energy of blade excitation through the friction between the damper and the blades. When the gap between the blades and the turbine disk is large, if the air system needs to control this gap, it is also necessary to design a sealing piece or similar parts to control the air flow rate. The current design structure of the turbine rotor usually designs and assembles parts such as locking pieces, vibration damping devices, and sealing pieces separately and then assembles them into the turbine rotor respectively. In order to reduce the weight of the turbine rotor, such parts are generally designed as small, thin, and light sheet metal parts, and there are a large number of them. The assembly process is cumbersome, and it is very easy to reduce the reliability of the engine due to improper assembly. Moreover, such parts are very easy to be damaged and are all classified as parts that must be replaced in the engine. During the engine overhaul, if it is necessary to check the condition of each blade of the turbine rotor, the turbine rotor needs to be disassembled, and the locking pieces, dampers, and sealing pieces must be replaced with new parts each time, resulting in a large economic cost for part replacement. Summary of the Invention

[0003] The present invention provides an integrated locking piece, a turbine rotor and its assembly method to solve the technical problems of cumbersome assembly process and high part replacement cost existing in the existing turbine rotor structure that designs and assembles locking pieces, vibration damping devices and sealing pieces separately.

[0004] According to one aspect of the present invention, an integrated locking piece is provided, which includes a first axial stop portion, a transition portion, a damping portion, a radial stop portion, and a second axial stop portion that are arranged in sequence and have an integral structure. When assembling the blade and the turbine disk, first, the first axial stop portions of multiple integrated locking pieces are correspondingly attached to the tenon end faces of the blades evenly distributed in a circle. At the same time, the transition portion, the damping portion, the radial stop portion, and the second axial stop portion pass through between the blade roots and under the blade rims, and position the integrated locking pieces and the blades in a circle. Then, the tenons of the blades in a circle are pushed into the tenon grooves of the turbine disk along the engine axis. Then, the second axial stop portion is bent and snapped into the locking piece groove of the turbine disk. At this time, the axial positions of the blades are locked from both sides by the first axial stop portion and the second axial stop portion, and the air flow rate between the blades and the turbine disk is controlled. The radial stop portion abuts against the rim of the turbine disk, and there is a gap between the damping portion and the inner side surface of the blade rim, so that the damping portion fits against the inner side surface of the blade rim due to centrifugal force in the working state, so as to play a role in friction damping.

[0005] Further, the length L of the damping portion along the engine axis 0 and the length L of the blade rim along the engine axis need to satisfy the following conditions: -0.05 mm ≤ L 0 -L ≤ 0 mm, and the height difference h along the engine radius between the upper surface of the transition portion and the lower surface of the radial stop portion 0 and the radial clearance h between the inner reinforcing rib of the blade rim and the turbine disk need to satisfy the following conditions: -0.05 mm ≤ h 0 -h ≤ 0 mm, and the width A of the first axial stop portion and the second axial stop portion 0 and the distance A between the adjacent tenon groove edges of the turbine disk need to satisfy the following conditions: -0.05 mm ≤ A 0 -A ≤ 0 mm.

[0006] Further, the included angle α between the damping portion and the radial stop portion 0 and the included angle α between the blade rim and the edge contour of the turbine disk need to satisfy the following conditions: α 0 = α.

[0007] Further, when optimizing the design of the quality of the integrated locking piece, by simplifying the blade-locking piece damping model into a single-degree-of-freedom model and constructing the dynamic equation of the single-degree-of-freedom macroscopic sliding system, the optimal design quality of the integrated locking piece is obtained after solving the dynamic equation to obtain the best damping effect.

[0008] Further, the expression of the dynamic equation is:

[0009]

[0010] Wherein, m represents the blade modal mass, and x represents the blade amplitude. and respectively represent the second derivative and the first derivative of the blade amplitude, c represents the blade damping coefficient, and c eq represents the equivalent damping coefficient of the damper, k represents the blade stiffness, and k eq represents the equivalent stiffness of the damper, f 0 represents the exciting load, ω represents the angular velocity of the exciting load, t represents the loading time of the exciting load, and f represents the frictional force of the damper. By solving the dynamic equation, the relationship curve between the blade amplitude x of the contact surface and the frictional force f of the damper is obtained, and then the relationship curve between the blade amplitude x of the contact surface and the locking piece mass is converted. The locking piece mass corresponding to the minimum point of the blade amplitude x is selected from the relationship curve as the optimal design mass of the integrated locking piece.

[0011] Furthermore, the first axial edge portions of several integrated locking pieces evenly distributed in a full circle are connected to each other to form an annular edge, so that several integrated locking pieces form an integral annular locking piece. When assembling the blade and the turbine disk, the annular edge is closely attached to the end face of the blade tenon evenly distributed in a full circle.

[0012] Furthermore, after the assembly of the blade and the turbine disk is completed, each vibration damping portion of the annular locking piece is attached to the inner side surface of the blade flange.

[0013] Furthermore, after the assembly of the blade and the turbine disk is completed, the axial clearance between the blade tenon and the integrated locking piece is 0 mm to 0.15 mm.

[0014] In addition, the present invention also provides a turbine rotor, and the integrated locking piece as described above is used for assembling the blade and the turbine disk.

[0015] In addition, the present invention also provides an assembly method for a turbine rotor, which is used for assembling the turbine rotor as described above, and includes the following contents:

[0016] Correspondingly attach the first axial edge portions of multiple integrated locking pieces to the end faces of the tenons of the blades evenly distributed in a full circle, and at the same time pass the transition portion, the vibration damping portion, the radial edge portion and the second axial edge portion through between the blade roots and under the flanges, and position the integrated locking pieces and the blades in a full circle;

[0017] Push the tenons of the blades in a full circle into the tenon grooves of the turbine disk along the axial direction of the engine;

[0018] Bend the second axial stop portion of each integrated locking piece and snap it into the locking piece groove of the turbine disk. At this time, the axial position of the blade is locked from both sides by the first axial stop portion and the second axial stop portion, and the air flow rate between the blade and the turbine disk is controlled. The radial stop portion abuts against the edge of the turbine disk, and there is a gap between the damping portion and the inner side surface of the blade flange, so that the damping portion fits against the inner side surface of the blade flange under the action of centrifugal force during the working state, so as to play a role in friction damping.

[0019] The present invention has the following effects:

[0020] For the integrated locking piece of the present invention, after the blade and the turbine disk are assembled, the axial position of the blade is locked from both sides by the first axial stop portion and the second axial stop portion, and the wide stop portions on both sides can also seal the gas, playing a role in controlling the air flow rate between the blade and the turbine disk, and at the same time acting as a locking piece and a sealing piece. The radial stop portion abuts against the edge of the turbine disk, and there is a gap between the damping portion and the inner side surface of the blade flange, so that the damping portion can fit against the inner side surface of the blade flange under the action of centrifugal force during the working state, thereby forming a friction damping between the inner side surface of the blade flange and the turbine disk. The vibration excitation energy of the blade is dissipated through the friction between the damping portion and the inner side surface of the blade flange, and thus the effect of friction damping is achieved. The integrated locking piece integrates the functions of the existing locking piece, damper and sealing piece, realizes the functions of three parts with one part, greatly reduces the number of parts and the total weight on the turbine rotor, greatly simplifies the assembly process of the turbine rotor, avoids the problem of reducing the reliability of the engine caused by improper assembly of parts, and during the disassembly and reassembly of the turbine rotor during the engine overhaul, the number of parts to be replaced is greatly reduced, saving the replacement cost.

[0021] In addition to the purposes, features and advantages described above, the present invention has other purposes, features and advantages. The present invention will be further described in detail below with reference to the drawings. Description of the Drawings

[0022] The drawings forming a part of this application are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0023] Figure 1 is a schematic structural diagram of the integrated locking piece of the preferred embodiment of the present invention.

[0024] Figure 2 is a schematic structural diagram of the assembly of the blade and the turbine disk using the integrated locking piece in the preferred embodiment of the present invention.

[0025] Figure 3It is a partial structural schematic diagram of bending the second axial edge part and clamping it into the locking piece groove of the turbine disk when assembling the blade and the turbine disk by using the integrated locking piece in the preferred embodiment of the present invention.

[0026] Figure 4 It is a schematic diagram of the meridian section of the turbine rotor after assembly in the preferred embodiment of the present invention.

[0027] Figure 5 It is a schematic diagram of some structural parameters of the turbine rotor.

[0028] Figure 6 It is a schematic diagram of some other structural parameters of the turbine rotor.

[0029] Figure 7 It is a schematic diagram of some structural parameters of the integrated locking piece in the preferred embodiment of the present invention.

[0030] Figure 8 It is a schematic diagram of some other structural parameters of the integrated locking piece in the preferred embodiment of the present invention.

[0031] Figure 9 It is a system schematic diagram of the single-degree-of-freedom model in the preferred embodiment of the present invention.

[0032] Figure 10 It is a structural schematic diagram of the annular locking piece in another embodiment of the present invention.

[0033] Figure 11 It is a structural schematic diagram of assembling the blade and the turbine disk by using the annular locking piece in another embodiment of the present invention. Detailed implementation manners

[0034] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways defined and covered by the following.

[0035] It can be understood that, as Figure 1As shown in the figure, a preferred embodiment of the present invention provides an integrated locking piece, which includes a first axial edge portion, a transition portion, a damping portion, a radial edge portion, and a second axial edge portion that are arranged in sequence and are of an integral structure. Specifically, the first axial edge portion is connected to the damping portion through the transition portion, the damping portion is connected to the second axial edge portion through the radial edge portion, the first axial edge portion and the second axial edge portion are used to lock the axial position of the blade and play a role in sealing and blocking air, while the damping portion is used to fit against the inner side surface of the blade flange in the working state to achieve a friction damping effect. Among them, the integrated locking piece can be made by one-piece molding or can be welded into a whole after being separately molded. In order to ensure the structural strength of the locking piece, the one-piece molding method is preferably used. In addition, in the initial state, the overall shape of the integrated locking piece is in the shape of a "7", that is, the transition portion, the damping portion, the radial edge portion, and the second axial edge portion are in a parallel state as a whole, while the first axial edge portion is in a vertical state for easy assembly. It can be understood that as Figure 2 shown, when assembling the blade and the turbine disk, first make the first axial edge portions of a plurality of integrated locking pieces correspond to and fit against the tenon end faces of the blades evenly distributed in a circle, that is, each integrated locking piece corresponds to and fits against one blade tenon end face. At the same time, pass the transition portion, the damping portion, the radial edge portion, and the second axial edge portion through between the blade roots and under the blade flanges, and use a tooling to position the integrated locking pieces and the blades in a circle, and then push the tenons of the blades in a circle into the tenon grooves of the turbine disk along the axial direction of the engine. Then, bend the second axial edge portion and snap it into the locking piece groove of the turbine disk, specifically as Figure 3 shown. At this time, the axial positions of the blades are locked from both sides by the first axial edge portion and the second axial edge portion and play a role in controlling the air flow rate between the blades and the turbine disk. The radial edge portion abuts against the disk edge of the turbine disk, and there is a gap between the damping portion and the inner side surface of the blade flange, so that the damping portion fits against the inner side surface of the blade flange due to centrifugal force in the working state to achieve a friction damping effect, specifically as Figure 4 shown.

[0036] It can be understood that for the integrated locking piece of this embodiment, after assembling the blade and the turbine disk, the axial position of the blade is locked from both sides by the first axial edge portion and the second axial edge portion. Moreover, the wide edge portions on both sides can also seal the gas, playing a role in controlling the air flow rate between the blade and the turbine disk. At the same time, it serves as both a locking piece and a sealing piece, and makes the radial edge portion abut against the edge of the turbine disk, leaving a gap between the damping portion and the inner side surface of the blade flange. So that the damping portion can be attached to the inner side surface of the blade flange under the action of centrifugal force in the working state, thereby forming a friction damping between the inner side surface of the blade flange and the turbine disk, dissipating the blade excitation energy through the friction between the damping portion and the inner side surface of the blade flange, and further achieving the effect of friction damping and vibration reduction. The integrated locking piece of the present invention integrates the functions of the existing locking piece, damper and sealing piece, realizes the functions of three parts with one part, greatly reduces the number of parts and the total weight on the turbine rotor, greatly simplifies the assembly process of the turbine rotor, avoids the problem of reduced engine reliability caused by improper part assembly, and during the disassembly and reassembly of the turbine rotor during engine maintenance, greatly reduces the number of replaceable parts to be replaced, saving the replacement cost.

[0037] It can be understood that after completing the assembly of the blade and the turbine disk, in order to ensure that the turbine blade has a certain amount of movement, the axial clearance between the blade tenon and the integrated locking piece is 0 mm to 0.15 mm.

[0038] It can be understood that in order to ensure the sealing effect and vibration damping effect of the integrated locking piece, it is necessary to optimize the design of some structural parameters of the integrated locking piece. Specifically, as Figures 5 to 8 shown, the length L of the damping portion along the axial direction of the engine 0 and the length L of the blade flange along the axial direction of the engine need to meet the following conditions: -0.05 mm ≤ L 0 -L ≤ 0 mm, the height difference h along the radial direction of the engine between the upper surface of the transition portion and the lower surface of the radial edge portion 0 and the radial clearance h between the inner side reinforcing rib of the blade flange and the turbine disk need to meet the following conditions: -0.05 mm ≤ h 0 -h ≤ 0 mm, the width A of the first axial edge portion and the second axial edge portion 0 and the spacing A between the adjacent tenon groove edges of the turbine disk need to meet the following conditions: -0.05 mm ≤ A 0 -A ≤ 0 mm, to ensure the sealing effect of the integrated locking piece and at the same time ensure the assemblability. In addition, the included angle α between the damping portion and the radial edge portion 0 and the included angle α between the blade flange and the edge contour of the turbine disk need to meet the following conditions: α 0= α, that is, the vibration damping part is parallel to the inner side surface of the blade flange, so as to ensure that under the action of centrifugal force, the contact area between the vibration damping part and the blade flange is the largest, and the best friction vibration damping effect is obtained.

[0039] It can be understood that in the working state, the integrated locking piece will be pressed against the inner side surface of the blade flange through the vibration damping part under the action of centrifugal force, thereby generating frictional force to consume the excitation load of the blade under specific working conditions. The centrifugal force of the integrated locking piece has an optimal solution for the vibration damping effect of the blade under specific working conditions, and specifically can be obtained through modal calculation and analysis of the rotor. Therefore, the design quality of the integrated locking piece is a key design element related to the vibration damping effect. In the present invention, the working position of the locking piece damping is inside the blade flange, and its mass is much smaller than that of the blade, so the locking piece damping has almost no influence on the inherent vibration characteristics of the blade. Therefore, when optimizing the design of the mass of the integrated locking piece in the present invention, by simplifying the blade-locking piece damping model into a single-degree-of-freedom model, specifically as Figure 9 shown, and constructing the dynamic equation of the single-degree-of-freedom macroscopic sliding system, after solving the dynamic equation, the optimal design mass of the integrated locking piece can be obtained to obtain the best vibration damping effect. Among them, the expression of the dynamic equation is:

[0040]

[0041] Among them, m represents the modal mass of the blade, x represents the relative displacement of the contact surface, that is, the blade amplitude, and respectively represent the second derivative and the first derivative of the blade amplitude, c represents the blade damping coefficient. Generally speaking, the damping of a rigid structure is very small, so it can be approximated as 0, c eq represents the equivalent damping coefficient of the damper, k represents the blade stiffness, k eq represents the equivalent stiffness of the damper, f 0 represents the excitation load, ω represents the angular velocity of the excitation load, that is, the product of the excitation frequency and 2π, t represents the loading time of the excitation load, and f represents the frictional force of the damper. By using Ansys simulation software to solve the above dynamic equation, the relationship curve between the blade amplitude x of the contact surface and the frictional force f of the damper is obtained, and then the relationship curve between the blade amplitude x of the contact surface and the mass of the locking piece is converted. The mass of the locking piece corresponding to the point with the smallest blade amplitude x in the relationship curve is selected as the optimal design mass of the integrated locking piece, so as to obtain the best friction vibration damping effect.

[0042] Optionally, as Figure 10As shown, in another embodiment of the present invention, in order to further simplify the assembly process, the first axial edge portions of several integrally distributed integrated locking pieces are connected to form an annular edge, so that several integrated locking pieces form an integral annular locking piece. Compared with the original design where multiple integrated locking pieces are assembled corresponding to multiple tenon grooves, several integrated locking pieces are simplified into a single annular locking piece, further greatly simplifying the assembly process, and the annular edge can further improve the sealing and air-blocking effect. When assembling the blade and the turbine disk, the annular edge is closely attached to the end face of the blade tenons evenly distributed in a circle, and the other side of the annular locking piece (i.e., the transition portion, damping portion, radial edge portion, and second axial edge portion) is placed between the root extensions of the turbine blades and under the flange, and after positioning with a tooling, the tenons of the turbine blades are pushed flat into the tenon grooves of the turbine disk. The rotor assembly state at this time is as Figure 11 shown. Finally, each second axial edge portion of the annular locking piece is bent and snapped into the locking piece groove on the side of the turbine disk.

[0043] In addition, after completing the assembly of the blade and the turbine disk, each damping portion of the annular locking piece needs to be in contact with the inner side surface of the blade flange.

[0044] It can be understood that since the annular locking piece is an integral structure, during assembly, due to assembly errors, the gaps between multiple damping portions and the inner side surface of the blade flange may be uneven after assembly, resulting in some damping portions not being in close contact with the inner side surface of the blade flange in the working state, and the damping effect at some positions is not good. Therefore, in order to ensure the damping and vibration reduction effect of the annular locking piece, after assembly, each damping portion of the annular locking piece must be in contact with the inner side surface of the blade flange in the non-working state. When in the working state, the centrifugal force causes the annular locking piece to press against the inner side surface of the blade flange, ensuring a good friction damping effect. In addition, at this time, the normal pressure of the annular locking piece pressing against the blade flange is composed of the centrifugal force of the annular locking piece and the elastic force generated by bending. When designing the mass of the annular locking piece based on the above process, the elastic force generated by bending needs to be taken into account.

[0045] In addition, another embodiment of the present invention also provides a turbine rotor, preferably using the above-mentioned integrated locking piece for assembling the blade and the turbine disk.

[0046] In addition, another embodiment of the present invention also provides an assembly method for a turbine rotor, which is used to assemble the above-mentioned turbine rotor, including the following content:

[0047] Step S1: The first axial edge portions of multiple integrated locking pieces are correspondingly attached to the end faces of the tenons of the blades evenly distributed in a circle. At the same time, the transition portion, damping portion, radial edge portion, and second axial edge portion are passed through between the root extensions of the blades and under the flange, and the integrated locking pieces and blades in a circle are positioned;

[0048] Step S2: Push the tenons of the whole ring of blades into the tenon grooves of the turbine disk along the axial direction of the engine;

[0049] Step S3: Bend the second axial edge portion of each integrated locking piece and snap it into the locking piece groove of the turbine disk. At this time, the axial positions of the blades are locked from both sides by the first axial edge portion and the second axial edge portion, and the air flow rate between the blades and the turbine disk is controlled. The radial edge portion abuts against the edge of the turbine disk, and there is a gap between the damping portion and the inner side surface of the blade flange, so that the damping portion fits against the inner side surface of the blade flange due to centrifugal force during the working state, so as to play a role in friction damping.

[0050] It can be understood that when an integral annular locking piece is used for assembly, only the annular edge of the annular locking piece needs to be fitted to the end face of the tenons of the whole ring of evenly distributed blades, without fitting each individual locking piece to each tenon, which greatly simplifies the assembly process. The remaining steps are the same as those of the individual locking piece assembly process.

[0051] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. An integrated locking piece, characterized in that, it includes a first axial stop portion, a transition portion, a damping portion, a radial stop portion, and a second axial stop portion that are integrally formed and arranged in sequence. When assembling the blade and the turbine disk, first, the first axial stop portions of multiple integrated locking pieces are correspondingly fitted to the tenon end faces of the blades evenly distributed in a circle. At the same time, the transition portion, the damping portion, the radial stop portion, and the second axial stop portion pass through between the blade roots and under the blade rims, and position the integrated locking pieces and the blades in a circle. Then, push the tenons of the blades in a circle into the tenon grooves of the turbine disk along the engine axis. Then, bend the second axial stop portion and snap it into the locking piece groove of the turbine disk. At this time, the first axial stop portion and the second axial stop portion lock the axial position of the blade from both sides and control the air flow rate between the blade and the turbine disk. The radial stop portion abuts against the turbine disk rim, and there is a gap between the damping portion and the inner side of the blade rim, so that the damping portion fits against the inner side of the blade rim under the action of centrifugal force in the working state to play a role in friction damping; When optimizing the quality design of the integrated locking piece, by simplifying the blade-locking piece damping model into a single-degree-of-freedom model and constructing the dynamic equation of the single-degree-of-freedom macroscopic sliding system, the optimal design quality of the integrated locking piece is obtained after solving the dynamic equation to obtain the best damping effect; The expression of the dynamic equation is: where m represents the blade modal mass, and x represents the blade amplitude. and respectively represent the second derivative and the first derivative of the blade amplitude, c represents the blade damping coefficient, and c eq represents the equivalent damping coefficient of the damper, k represents the blade stiffness, and k eq represents the equivalent stiffness of the damper, f 0 represents the exciting load, ω represents the angular velocity of the exciting load, t represents the loading time of the exciting load, f represents the friction force of the damper. By solving the dynamic equation, the relationship curve between the blade amplitude x of the contact surface and the friction force f of the damper is obtained, and then the relationship curve between the blade amplitude x of the contact surface and the locking piece mass is converted. The locking piece mass corresponding to the minimum point of the blade amplitude x is selected from the relationship curve as the optimal design mass of the integrated locking piece.

2. The integrated locking piece according to claim 1, characterized in that, The length L of the damping part along the axial direction of the engine 0 and the length L of the blade shroud along the axial direction of the engine shall satisfy the following condition: -0.05 mm ≤ L 0 -L ≤ 0 mm, and the height difference h along the radial direction of the engine between the upper surface of the transition part and the lower surface of the radial edge part 0 and the radial clearance h between the inner rib of the blade shroud and the turbine disk shall satisfy the following condition: -0.05 mm ≤ h 0 -h ≤ 0 mm, and the width A of the first axial edge part and the second axial edge part 0 and the distance A between the adjacent tenon groove edges of the turbine disk shall satisfy the following condition: -0.05 mm ≤ A 0 -A ≤ 0 mm.

3. The integrated locking piece according to claim 1, characterized in that, The included angle α between the vibration damping part and the radial rib 0 The included angle α between the blade flange and the edge contour of the turbine disk needs to satisfy the following condition: α 0 = α.

4. The integrated locking piece according to claim 1, characterized in that, The first axial stop portions of several integrated locking pieces evenly distributed in a circle are connected to form an annular stop, so that several integrated locking pieces form an integral annular locking piece. When assembling the blade and the turbine disk, press the annular stop against the tenon end faces of the blades evenly distributed in a circle.

5. The integrated locking piece according to claim 4, characterized in that, After completing the assembly of the blade and the turbine disk, each damping portion of the annular locking piece fits against the inner side of the blade rim.

6. The integrated locking piece according to claim 1, characterized in that, After completing the assembly of the blade and the turbine disk, the axial gap between the blade tenon and the integrated locking piece is 0 mm to 0.15 mm.

7. A turbine rotor, characterized in that, the integrated locking piece according to any one of claims 1 to 6 is used for assembling the blade and the turbine disk.

8. An assembly method of a turbine rotor for assembling the turbine rotor according to claim 7, characterized in that, it includes the following contents: Correspondingly fit the first axial stop portions of multiple integrated locking pieces to the tenon end faces of the blades evenly distributed in a circle. At the same time, pass the transition portion, the damping portion, the radial stop portion, and the second axial stop portion through between the blade roots and under the blade rims, and position the integrated locking pieces and the blades in a circle; Push the tenons of the blades in a circle into the tenon grooves of the turbine disk along the engine axis; Bend the second axial retaining edge part of each integrated locking piece and snap it into the locking piece groove of the turbine disk. At this time, the axial positions of the blades are locked from both sides by the first axial retaining edge part and the second axial retaining edge part, and the air flow rate between the blades and the turbine disk is controlled. The radial retaining edge part abuts against the edge of the turbine disk, and there is a gap between the damping part and the inner side surface of the blade flange, so that the damping part fits against the inner side surface of the blade flange due to centrifugal force in the working state to play a role in friction damping.

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