A compressor blade and disc damping and axial locking structure and its installation method

Abstract

The application discloses a compressor blade and wheel disc damping and axial locking structure and a mounting method thereof, and comprises a wheel disc and a rotor blade arranged on the wheel disc. The rotor blade comprises a blade root part. A circumferential through groove is arranged on the wheel disc. Non-through grooves are arranged on both sides of the blade root part. When the rotor blade is mounted on the wheel disc, the non-through grooves and the circumferential through groove are matched to form a locking groove. A damping type locking mechanism is arranged in the locking groove. On the basis of fully studying a damping structure of a compressor blade, a damping type locking mechanism is designed between a blade root extension and a rim. The damping structure formed by the damping type locking mechanism can effectively reduce blade vibration and improve blade vibration performance by establishing dry friction damping.

Description

Technical Field

[0001] This invention relates to the field of gas turbine technology, and in particular to a compressor blade and disc vibration damping and axial locking structure and its installation method. Background Technology

[0002] When the compressor blades of a gas turbine are operating, they are constantly subjected to the excitation force of the airflow, causing the blades to vibrate. In particular, the excitation force generated by the airflow deceleration during startup can easily cause blade resonance and even damage the blades. It is difficult to avoid all resonance points in blade design, and stall is even more difficult to predict. Therefore, considering vibration reduction measures in blade design can effectively reduce blade vibration and improve blade life.

[0003] Compressor blades are typically mounted axially into the grooves of the compressor disc. To prevent axial movement and rubbing against the stator structure during operation, the blades need to be locked in the grooves to prevent relative axial movement between the blades and the disc. Therefore, various locking structures have been designed. Common methods include riveting and locking plates. However, riveting damages the blade structure, and the removed blades cannot be reused. While locking plates do not damage the blade structure, they require specialized equipment to bend the plates, and these plates cannot be reused. Patents regarding compressor blade locking primarily focus on the locking function, neglecting vibration damping. Therefore, designing a structure that combines locking and vibration damping is crucial.

[0004] Patent CN204716615U discloses a compressor frequency modulation structure and a compressor locking structure using this structure. This patent modulates the mass and stiffness distribution of the blades through a frequency modulation hole located at the bottom of the compressor blade root, thereby reducing blade vibration. However, this method has a limited frequency modulation range and can only reduce blade vibration at specific speeds. As the operating environment changes, the blade frequency changes, making it difficult to achieve the desired vibration reduction effect. Furthermore, in this patent, the blade root and impeller are axially positioned by locking plates installed in the frequency modulation hole. Therefore, different types of locking plates need to be manufactured depending on the shape of the frequency modulation hole, and the removed locking plates cannot be reused. In addition, the compressor blade locking structures in the aforementioned prior art are generally complex in structure and assembly, resulting in high costs.

[0005] Patent CN210509729U discloses a blade locking structure with vibration reduction effect. This patent involves setting mounting holes between the blade root groove and the blade root, with a vibration damping rod inserted through the mounting holes. The two ends of the vibration damping rod are connected to the first and second locking blocks, respectively. When the blade is in operation, due to centrifugal force, the vibration damping rod will contact the blade root, and friction will occur between the root and the vibration damping rod under airflow excitation. Because the blade root is tightly fitted to the blade groove, the vibration stress on the blade root itself is very small; more vibration stress occurs at the blade root. Therefore, this method has limited vibration reduction effect and is unlikely to achieve the desired effect. Summary of the Invention

[0006] To address the problem mentioned in the background art that existing compressor blades cannot simultaneously achieve locking and vibration reduction during installation, this invention provides a compressor blade and impeller vibration reduction and axial locking structure and its installation method. Based on a thorough study of the compressor blade vibration reduction and damping structure, the vibration-damping locking mechanism at the blade-impeller connection effectively reduces blade vibration by establishing dry friction damping, while ensuring the blade is firmly installed and easy to install, significantly improving the working stability of the compressor blade.

[0007] Another objective of this invention is that, based on a thorough study of the vibration damping structure of compressor blades, a vibration-damping locking mechanism is designed between the blade root and the rim. The damping structure formed by the vibration-damping locking mechanism can effectively reduce blade vibration and improve blade vibration performance by establishing dry friction damping.

[0008] Another objective of this invention is that the vibration-damping locking mechanism has various variations, which can effectively reduce blade vibration. During the operation of the gas turbine unit, the vibration-damping locking mechanism contacts the blade root under the action of centrifugal force. When the blade is excited by airflow force, the vibration-damping locking mechanism and the blade root form dry friction damping, thereby achieving the purpose of vibration reduction.

[0009] To achieve the above objectives, the present invention adopts the following technical solution: A compressor blade and impeller vibration damping and axial locking structure includes an impeller and rotor blades mounted on the impeller. Each rotor blade has a root portion. The impeller has a circumferential through-slot, and both sides of the root portion have non-through-slots. When the rotor blade is mounted on the impeller, the non-through-slots and the circumferential through-slots cooperate to form a locking groove. A vibration damping locking mechanism is installed within the locking groove. The root portion of the rotor blade is assembled onto the impeller, and the non-through-slots are aligned with the circumferential through-slots on the impeller to form the locking groove for mounting the vibration damping locking mechanism. The vibration damping locking mechanism can provide axial vibration damping and fixation for the blade, allowing the blade to be stabilized under damping during impeller operation, effectively improving the blade stability during compressor operation.

[0010] Furthermore, the vibration-damping locking mechanism includes a damping rod and a spring. The spring is installed in a non-through groove, and the spring abuts against one end of the damping rod. The end of the damping rod away from the spring abuts against a circumferential through groove. The damping rod and the spring cooperate to form an energy-absorbing damping structure. During compressor operation, the blade root experiences concentrated force. Currently, most methods use hard locking to ensure stable blade installation, but this cannot prevent the blade from experiencing severe vibration and friction at the blade root due to airflow excitation force. Therefore, when the blade is subjected to airflow excitation force, the damping rod and spring cooperate in the locking groove to form dry friction damping, consuming vibration energy and buffering the hard friction between the blade root and the impeller, thereby ensuring that the blade is firmly installed on the impeller while effectively reducing vibration.

[0011] Preferably, the outer edge of the rotor disk is a groove, and the circumferential through groove is located at the top of the groove. The circumferential through groove is a straight groove with a "convex" shaped cross-section, including a side surface, an upper surface, and a bottom surface. The circumferential through groove also includes two opposing first contact surfaces. Any two adjacent surfaces of the circumferential through groove are perpendicular to each other, and the first contact surfaces are perpendicular to the axial direction of the disk. The rotor blades are mounted on the disk through the groove, and the circumferential through groove between adjacent grooves engages with the non-through grooves at both ends to mount damping rods and springs, thereby providing damping and buffering for the blades. The first contact surface of the circumferential through groove serves as the pressure surface of the damping rod when the rotor blades are axially displaced, preventing further axial movement of the damping rod and rotor blades, and forming a self-locking structure to ensure that the rotor blades remain locked.

[0012] Preferably, an extension root is provided at the upper end of the blade root of the rotor blade, and the non-through grooves on both sides of the extension root are of the same depth. The non-through grooves are provided on the extension root. The blade root is mainly used to tightly engage the wheel groove, while the extension root uses a vibration-damping locking mechanism provided in the non-through groove to dampen the vibration of the rotor blade. The non-through grooves on both sides of the extension root are symmetrically distributed, which can ensure that the damping force on both sides of the rotor blade due to vibration during operation is consistent.

[0013] Preferably, the non-through groove includes a second contact surface and a non-through groove side surface disposed opposite to each other, and a third contact surface disposed near the blade's central axis. The non-through groove also includes a top surface disposed on the side away from the blade root. The non-through groove is used to accommodate the end of the damping rod and the spring, and the top surface of the non-through groove is used to accommodate the protrusion of the damping rod, ensuring that the damping effect of the damping rod remains stable.

[0014] Preferably, the damping rod comprises a base block and a protrusion block arranged on the top of the base block, the top surface of the base block is a damping rod contact surface, both two side surfaces of the base block are damping rod end surfaces, and the bottom surface of the base block is a damping rod bottom surface; the front side of the base block is a damping rod side surface, a damping rod operation groove is further arranged in the middle of the protrusion block, and the top surface of the protrusion block is a damping rod convex surface; the damping rod operation groove is parallel to the damping rod end surfaces. The damping rod is composed of the base block and the protrusion block, the base block is arranged in the locking groove, the protrusion block is arranged on the top surface of the non-through groove, and the damping rod operation groove is further arranged in the middle of the damping rod, which facilitates technicians to install the damping rod in place.

[0015] Preferably, the compression length of the spring is a, the length of the damping rod is b, the machining depth of the non-through groove is c, wherein the length of the locking groove is equal to a+b; the height of the damping rod convex surface is g, the machining height of the top surface of the non-through groove is k, and g < k. It can be seen that the sum of the length of the spring in a natural uncompressed state and the length of the damping rod is greater than the length of the damping rod mounting groove, so that both ends of the damping rod are kept inside the non-through groove; that g is less than k can ensure that the damping rod convex surface does not contact the top surface of the non-through groove, avoiding the hidden danger of reduced service life caused by friction on the non-friction surface of the damping rod.

[0016] Preferably, the machining depth of the non-through groove is c, the machining depth of the top surface of the non-through groove is d, the length of the circumferential through groove is e, the length of the damping rod convex surface is f, wherein e+d < f < e+2d; the distance from the damping rod convex surface to the damping rod end surface is h, wherein d < f < e+2d, which ensures that the damping rod convex surface is always within the range of the machining depth of the top surfaces of the non-through grooves at both ends of the circumferential through groove; c-d < h, which ensures that the damping rod convex surface does not contact the machined surface of the top surface of the non-through groove.

[0017] The present application further discloses the above-mentioned compressor blade and wheel disc vibration damping and axial locking structure and the installation method thereof, comprising: S1: A first wheel groove and a second wheel groove are respectively provided at two ends of one circumferential through groove on the wheel disc, one rotor blade is selected as the first blade, the spring is installed in the non-through groove on the side of the blade root of the first blade close to the circumferential through groove, and then the blade root is inserted into the first wheel groove to complete the installation of the first blade; S2: One end of the damping rod is loaded into the locking groove, an operating tool is inserted into the damping rod operation groove, the damping rod is moved to compress the spring, until the damping rod end surface of the damping rod on the side away from the spring is retracted into the circumferential through groove; S3: Another rotor blade is taken as the second blade and loaded into the second wheel groove at the other end of the circumferential through groove according to the scheme of S1, and the damping rod end surface of the damping rod in S2 on the side away from the spring is loaded into the non-through groove of the second blade; S4: The operating tool is released, and the damping rod on the side away from the spring abuts against the third contact surface.

[0018] Using the operating tools, springs and damping bars can be quickly installed, ensuring that the locking groove, which consists of the circumferential through groove and the non-through grooves on both sides, is quickly filled. It is simple and convenient, and the vibration-damping locking mechanism can be disassembled and replaced at any time, which can ensure the assembly efficiency of the rotor blades on the entire wheel.

[0019] Preferably, the operating tool includes a handle and a rectangular plate disposed at the top of the handle, the length of which is equal to the machining depth of the circumferential through groove. The rectangular plate is used to insert and move the damping rod for installation.

[0020] Preferably, the top of the rectangular piece is wedge-shaped. The wedge-shaped tip of the rectangular piece can remain stably engaged after being inserted into the operating slot of the damping rod, and will not come out during lateral operation of the tool, thus affecting the operation result.

[0021] Preferably, both the surface of the damping rod and the surface of the non-through groove are provided with a wear-resistant coating. The wear-resistant coating can ensure that the friction between the rotor blades and the disk is reduced during the operation of the compressor, thereby improving the service life of the vibration-damping locking mechanism.

[0022] Therefore, the present invention has the following beneficial effects: (1) Based on a thorough study of the vibration damping structure of the compressor blade, the present invention designs a vibration damping locking mechanism between the blade root and the rim. The damping structure formed by the vibration damping locking mechanism can effectively reduce blade vibration and improve blade vibration performance by establishing dry friction damping. (2) The vibration-damping locking mechanism in this invention has various variations, which can effectively reduce blade vibration; when the gas turbine unit is running, the vibration-damping locking mechanism contacts the blade root under the action of centrifugal force. When the blade is excited by airflow force, the vibration-damping locking mechanism and the blade root form dry friction damping, thereby achieving the purpose of vibration reduction; (3) This invention simultaneously solves the functions of axial locking and vibration reduction of the blades, and achieves very convenient disassembly and assembly without damaging the blades and the impeller. Furthermore, the disassembled springs and damping rods can be reused. It has the advantage of simple structure. Attached Figure Description

[0023] Appendix Figure 1 This is an overall assembly effect diagram of the present invention.

[0024] Appendix Figure 2 This is a diagram of the wheel groove structure.

[0025] Appendix Figure 3 This is a diagram of the leaf root structure.

[0026] Appendix Figure 4 This is a structural diagram of a damping rod.

[0027] Appendix Figure 5 This is an assembly drawing of the damping rod.

[0028] Appendix Figure 6 This is a diagram showing the working state of the damping rod.

[0029] Appendix Figure 7 This is a schematic diagram for controlling the size distribution.

[0030] Appendix Figure 8 For the appendix Figure 6 Sectional view of section AA, i.e., the working effect of axial positioning of the damping rod. Figure 1 .

[0031] Appendix Figure 9 For the appendix Figure 6 The sectional view of section BB, which shows the working effect of the damping rod's axial positioning. Figure 2 .

[0032] Appendix Figure 10 This is the main view of the operation tool.

[0033] Appendix Figure 11 This is a side view of the operating tool.

[0034] Appendix Figure 12 A diagram showing the effect of a damping rod with planar contact surfaces (the first and second contact surfaces) mating with a non-through groove.

[0035] Appendix Figure 13 A diagram showing the effect of a damping rod with arc-shaped contact surfaces (both the contact surface and the second contact surface) mating with a non-through groove.

[0036] Appendix Figure 14 for Figure 1 A magnified view of a portion of point A in the middle.

[0037] Appendix Figure 15 for Figure 2 A magnified view of a section at point B in the middle.

[0038] 1-Disc, 2-Rotor blade, 3-Damping rod, 4-Operating tool, 5-Spring, 11-Wheel groove, 12-Circumferential through groove, 123-Side side, 124-Upper end face, 125-First contact surface, 126-Bottom surface, 21-Blade root, 22-Non-through groove, 221-Second contact surface, 222-Third contact surface, 223-Side side of non-through groove, 224-Top surface of non-through groove, 23-Root, 31-Damping rod contact surface, 32-Damping rod end face, 33-Bottom surface of damping rod, 34-Side side of damping rod, 35-Damping rod operating groove, 36-Convex surface of damping rod, 41-Handle, 42-Rectangular piece; a - Spring compression length, b - Damping rod length, c - Non-through groove machining depth, d - Non-through groove top surface machining depth, e - Circumferential through groove length, f - Damping rod convex surface length, h - Damping rod convex surface to damping rod end face distance, g - Damping rod convex surface height, k - Non-through groove top surface machining height. Detailed Implementation

[0039] The present invention will be further described below with reference to the accompanying drawings and specific embodiments. Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0040] Example 1 like Figure 1 As shown in Figure 14, this embodiment includes a wheel 1, rotor blades 2, damping rods 3, springs 5, and an operating tool 4 for assembly.

[0041] As attached Figure 2 , 15 As shown, the outer edge of the rotor disk is a groove 11, and a circumferential through groove 12 is machined on the top of the groove. The circumferential through groove 12 is a straight groove, and its specific structure is as follows: the cross-section is convex, including the side surface 123, the upper end surface 124, the first contact surface 125 and the bottom surface 126. All surfaces of the circumferential through groove 12 are planes, and two adjacent planes are perpendicular to each other.

[0042] As attached Figure 3 As shown, the bottom of the rotor blade consists of a blade root 21 and an extension root 23. Non-through grooves 22 are machined at equal radial positions on both sides of the extension root 23, and the two non-through grooves 22 on the same side of the extension root 23 have equal machining depths. The non-through groove 22 is a straight groove, which includes a second contact surface 221, a third contact surface 222, a non-through groove side surface 223, and a non-through groove top surface 224.

[0043] As attached Figure 4 As shown, the damping rod 3 is a metal rod with a uniform cross-sectional shape. The damping rod includes a contact surface 31, an end face 32, a bottom surface 33, a side surface 34, an operating groove 35, and a convex surface 36. The operating groove 35 is a narrow rectangular groove located in the middle of the convex surface 36. The operating groove 35 is parallel to the end face 32 and its depth is 1 / 5 of the height of the damping rod 3.

[0044] As attached Figure 5 With appendix Figure 6As shown, the spring 5 is installed in the non-through groove 22, which contacts one side 32 of the damping rod 3. The spring force presses the other side 32 of the damping rod 3 into another matching non-through groove 22, so that it contacts the third contact surface 222 of the non-through groove. Regardless of whether it is cold or hot, the above contact state remains unchanged, so that the spring 5 is always in a compressed state, maintaining the working conditions of the damping rod 3.

[0045] As attached Figure 5 With appendix Figure 6 As shown, the circumferential through groove 12 and the non-through groove 22 cooperate to form a damping rod mounting groove. Under working conditions, the damping rod 3 is thrown outward under the action of the rotor centrifugal force, and the damping rod contact surface 31 contacts the second contact surface 221 of the non-through groove. The damping rod 3 and the blade consume the vibration energy of the rotor blade 2 through dry friction damping.

[0046] As attached Figure 7 As shown, for ease of installation and operational stability, the dimensions of each component must meet the following relationships: The compression length a of spring 5 + the length b of damping rod 3 = the length of the damping rod mounting groove. That is, the sum of the length of spring 5 in its uncompressed state and the length of damping rod 3 is greater than the length of the damping rod mounting groove, ensuring that both ends of damping rod 3 are inside the non-through groove 22. The compression length a of spring 5 < the machining depth c of non-through groove 22 - the machining depth d of the top surface 224 of non-through groove, ensuring that the mounting depth of damping rod 3 is greater than the machining depth of the top surface 224 of non-through groove. The length e of the circumferential through groove 12 + the machining depth d of the top surface 224 of non-through groove < the length f of the convex surface 36 of damping rod < the length e + 2 * non-through groove 12. The machining depth d of the top surface 224 of the through groove ensures that the convex surface 36 of the damping rod is always within the machining depth range of the top surfaces 224 of the two adjacent non-through grooves; the distance h from the convex surface 36 of the damping rod to the end face 32 of the damping rod is greater than the machining depth c of the non-through groove 22 minus the machining depth d of the top surface 224 of the non-through groove, ensuring that the convex surface 36 of the damping rod does not contact the machining depth surface of the top surface 224 of the non-through groove; the height g of the convex surface 36 of the damping rod is less than the machining height k of the top surface 224 of the non-through groove, ensuring that the convex surface 36 of the damping rod does not contact the top surface 224 of the non-through groove; the outer diameter of the spring 5 is 1mm smaller than the inner circle diameter of the non-through groove 22.

[0047] As attached Figure 8 With appendix Figure 9As shown in the figure, the arrow indicates the axial displacement direction of rotor blade 2. When rotor blade 2 undergoes axial displacement, the non-through groove side 223 presses against the damping rod side 34, causing the damping rod 3 to also undergo axial displacement. When the other damping rod side 34 contacts the first contact surface 125 of the circumferential through groove, the first contact surface 125 prevents the damping rod 3 and rotor blade 2 from further axial displacement. At this time, rotor blade 2, damping rod 3, and wheel 1 form an interlocking structure to prevent rotor blade 2 from undergoing axial displacement. The surface of damping rod 3, the wall of non-through groove 22, and the first contact surface 125 of the circumferential through groove need to be coated with a wear-resistant layer to prevent wear on the contact surfaces during operation.

[0048] Example 2 As attached Figure 10 With appendix Figure 11 As shown, the operating tool 4 is used for the installation and removal of the damping rod 3. The damping rod 3 can be retracted and released using the tool 4. The operating tool 4 is a tool with a handle and a metal rectangular piece 42 at its top. The length of the metal rectangular piece 42 at the top of the operating tool 4 is equal to the machining depth of the circumferential through groove 12, and its width is 1mm smaller than the distance between the two sides 123 of the circumferential through groove. Simultaneously, the sides 123 of the circumferential through groove restrict the movement of the metal rectangular piece 42, preventing it from slipping out of the damping rod operating groove 35 and scratching the rotor blades. The thickness of the metal rectangular piece 42 is 0.1-0.2mm less than the thickness of the damping rod operating groove 35, and the top of the metal rectangular piece 42 is machined into a wedge shape to facilitate insertion of the top of the metal rectangular piece 42 into the damping rod operating groove 35. The handle 41 of the operating tool is covered with a rubber layer for easy gripping.

[0049] The installation method of the compressor blade and impeller vibration damping and axial locking structure and its installation method in this embodiment is as follows: First, assemble the spring 5 into the non-through groove 22 on one side of the blade root 21, and then insert the blade root 21 into the impeller groove 11 to complete the assembly of the rotor blade 2. Next, assemble one end of the damping rod 3 into the damping rod mounting groove, and then insert the operating tool 4 into the damping rod operating groove 35, move the damping rod 3 to compress the spring 5, until the other end face 32 of the damping rod 3 is completely retracted into the circumferential through groove 12. Subsequently, assemble another rotor blade 2 that mates with the circumferential through groove 12 into the impeller groove 11. Finally, release the operating tool 4, and the end face 32 of the damping rod presses against the third contact surface 222 to complete the assembly.

[0050] In this embodiment, as shown in the appendix Figure 12-13 As shown, the damping rod contact surface 31 can be machined into a flat surface or an arc surface. Correspondingly, the second contact surface 221 is machined into a flat surface or an arc surface. The same contact surface shape allows the damping rod 3 to fully contact the non-through groove 22.

[0051] In addition to the above embodiments, within the scope disclosed in the claims and specification of this invention, the technical features of this invention can be reselected and combined to form new embodiments. These can be achieved by those skilled in the art without creative effort. Therefore, these embodiments not described in detail in this invention should also be regarded as specific embodiments of this invention and within the protection scope of this invention.

Claims

1. A compressor blade and disc vibration damping and axial locking structure, characterized in that, The device includes a wheel and rotor blades mounted on the wheel. The rotor blades include a root portion, and the wheel has a circumferential through groove. An extension portion is provided at the upper end of the root portion of the rotor blade, and the non-through grooves on both sides of the extension portion have the same depth. When the rotor blades are mounted on the wheel, the non-through grooves and the circumferential through groove cooperate to form a locking groove. A vibration-damping locking mechanism is provided within the locking groove. The vibration-damping locking mechanism includes a damping rod. The damping rod includes a base block and a protrusion on the top of the base block. The top surface of the protrusion is the convex surface of the damping rod. The height of the convex surface of the damping rod is g, and the machining height of the top surface of the non-through groove is k, where g < k. The non-through groove includes a second contact surface and a non-through groove side surface arranged opposite each other, and a third contact surface located near the blade's central axis. The non-through groove also includes a top surface of the non-through groove located away from the blade root.

2. The compressor blade and disc vibration damping and axial locking structure according to claim 1, characterized in that, The vibration-damping locking mechanism also includes a spring, which is installed in a non-through groove. The spring abuts against one end of a damping rod, and the end of the damping rod away from the spring abuts against a circumferential through groove.

3. The compressor blade and disc vibration damping and axial locking structure according to claim 1, characterized in that, The outer edge of the wheel is a groove, and the circumferential through groove is provided at the top of the groove. The circumferential through groove is a straight groove with a "convex" shaped cross section. The circumferential through groove includes a side surface, an upper surface, and a bottom surface. The circumferential through groove also includes two opposing first contact surfaces. Any two adjacent surfaces of the circumferential through groove are perpendicular to each other, and the first contact surfaces are perpendicular to the axial direction of the wheel.

4. The compressor blade and disc vibration damping and axial locking structure according to claim 3, characterized in that, The non-through grooves on both sides of the root extension are symmetrically distributed.

5. The compressor blade and disc vibration damping and axial locking structure according to claim 1, characterized in that, The top surface of the base block is the contact surface of the damping rod, both sides of the base block are the end faces of the damping rod, and the bottom surface of the base block is the bottom surface of the damping rod; the front side of the base block is the side face of the damping rod, and a damping rod operating groove is also provided in the middle of the protrusion; the damping rod operating groove is parallel to the end face of the damping rod; the damping rod operating groove is a narrow rectangular groove, and the depth of the damping rod operating groove is one-fifth of the height of the damping rod.

6. The compressor blade and disc vibration damping and axial locking structure according to claim 2, characterized in that, The spring has a compression length of a, the damping rod has a length of b, and the locking groove has a length of a + b.

7. The compressor blade and disc vibration damping and axial locking structure according to claim 5, characterized in that, The machining depth of the non-through groove is c, the machining depth of the top surface of the non-through groove is d, the length of the circumferential through groove is e, and the length of the convex surface of the damping rod is f, where d < f < e + 2d; the distance from the convex surface of the damping rod to the end face of the damping rod is h, where c < h.

8. The installation method of the compressor blade and disc vibration damping and axial locking structure according to any one of claims 1-7, characterized in that, Includes the following steps: S1: There are first wheel grooves and second wheel grooves at both ends of a circumferential through groove on the wheel disk. Select a rotor blade as the first blade, install the spring in the non-through groove on the side of the blade root near the circumferential through groove of the first blade, and then insert the blade root into the first wheel groove to complete the installation of the first blade. S2: Insert one end of the damping rod into the locking groove, use the operating tool to insert into the damping rod operating groove, move the damping rod to compress the spring, until the damping rod end face away from the spring is drawn into the circumferential through groove. S3: Install another rotor blade as the second blade into the second wheel groove at the other end of the circumferential through groove according to the scheme of S1, and install the damping rod end face away from the spring in S2 into the non-through groove of the second blade. S4: Release the operating tool, and the damping rod on the side away from the spring abuts against the third contact surface.

9. The installation method of the compressor blade and disc vibration damping and axial locking structure according to claim 8, characterized in that, The operating tool includes a handle and a rectangular piece disposed at the top of the handle, the length of which is equal to the machining depth of the circumferential through groove.

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