Turbine blade balancing device, balancing method and assembly method

Abstract

The present invention discloses a turbine blade balancing device, a balancing method and an assembly method, wherein the turbine blade balancing device comprises a base, a cover plate and a clamping assembly, wherein the base and the cover plate are arranged at intervals and parallel to each other, and the base and the cover plate are both set in a disc shape, and the edge of the base facing the cover plate is provided with a first limiting groove for clamping the blade along the radial direction of the base, and the edge of the cover plate facing the base is provided with a second limiting groove for clamping the blade along the axial direction of the cover plate, and the clamping assembly is used to clamp and fix the cover plate on the base along the axial direction of the cover plate, and the second limiting groove and the first limiting groove clamp and fix the blade. The turbine blade balancing device provided by the present invention is convenient for disassembling and assembling each blade separately, and is convenient for adjusting the positions of different blades, reducing the difficulty of balancing and debugging the entire disk of blades, and improving the efficiency of balancing and debugging.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine assembly and debugging, and in particular to a turbine blade balancing device, a turbine blade balancing method, and a turbine blade assembly method. Background Art

[0002] In the assembly of turbine blades and turbine disks of aircraft engines, the balancing and correction process is usually: turbine disk assembly - turbine disk balancing - turbine blade assembly - turbine blade balancing, and before assembly, the unbalance of different parts on the turbine disk must be measured first, and then the weights and weights must be staggered based on experience. For example, before assembling the blades, the weight moment must be measured first, and then multiple blades must be cross-arranged in four quadrants according to the weight moment to make the weight distance as uniform as possible. However, directly staggering the weights and weights of the blades and cross-arranging them in four quadrants based on experience cannot make the assembled rotor directly meet the balancing requirements. Generally, it is still necessary to use a balancing machine to test and gradually adjust the relative positions of the turbine disk and blades.

[0003] like Figure 1 As shown in the figure, since the blade crown of a certain type of aircraft engine rotor blade is a folded structure, the axial limit between two adjacent blades is achieved by the folded structure. This structure will cause interference between the blades, and they cannot be disassembled and assembled separately along the axial direction of the turbine disk. During assembly, all blades can only be installed into a whole disk of blades and then the whole disk of blades can be installed into the wheel disk with a special disassembly tool. When adjusting the position of the blades, the whole disk of blades must be disassembled together with the disassembly tool to adjust the position of the blades. Due to the complex structure and difficulty of using the disassembly tool of the whole disk of blades, the disassembly time of the whole disk of blades is more than three times that of the conventional assembly method. In addition, due to the large mass of the rotor of a large aircraft engine, it needs to be hoisted with the help of a hoist and transferred between the assembly rack and the balancing machine. The hoisting and handling process will also be time-consuming. Secondly, since the actual adjustment of the blade position during rotor balancing requires at least two times, the rotor is hoisted at least five times between the assembly rack and the balancing machine, which wastes manpower and material resources, and the assembly and debugging costs are high and the efficiency is low. Summary of the invention

[0004] The present invention primarily provides a turbine blade balancing device to solve the technical problem of difficult and low efficiency blade balancing adjustment.

[0005] The present invention also provides a turbine blade balancing method, which adopts the turbine blade balancing device.

[0006] The present invention also provides a turbine blade assembly method, which adopts the turbine blade balancing method.

[0007] According to a first aspect of the present invention, a turbine blade balancing device is provided, which is used to install a whole disk of blades and test the balance of the whole disk of blades on a balancing machine, wherein the whole disk of blades includes a plurality of blades spliced ​​in sequence along a circumferential direction, and the turbine blade balancing device includes a base, a cover plate and a clamping assembly, wherein the base and the cover plate are arranged at intervals and parallel to each other, and the clamping assembly is arranged between the base and the cover plate, and the base and the cover plate are both arranged in a disc shape, and an edge of the base facing the cover plate is provided with a first limiting groove for clamping the blade along the radial direction of the base, and an edge of the cover plate facing the base is provided with a second limiting groove for clamping the blade along the axial direction of the cover plate, and the clamping assembly is used to clamp and fix the cover plate to the base along the axial direction of the cover plate, and enable the second limiting groove and the first limiting groove to clamp and fix the blade.

[0008] Furthermore, the first limiting groove includes a first groove wall, which is used to abut against a side of the blade crown facing the center of the base radially outward along the base, and the first limiting groove extends in a direction away from the center of the base to form an escape space for the blade crown to move radially along the base.

[0009] Furthermore, a first support portion and a second support portion are provided on a side of the base facing the cover plate, and the first support portion and the second support portion are arranged on both sides of the first limiting groove along the radial direction of the base, the first support portion is used to support the tenon of the blade, and the second support portion is used to support the root of the blade.

[0010] Furthermore, the second limiting groove comprises a second groove wall, and the second groove wall is used to abut against a side of the blade crown of the blade away from the center of the base inwardly along the radial direction of the base.

[0011] Preferably, the first limiting groove extends in a circular ring shape along the circumferential direction of the base, and the second limiting groove extends in a circular ring shape along the circumferential direction of the cover plate.

[0012] Preferably, the clamping assembly includes a positioning shaft and a clamping nut, the cover plate is provided with a positioning hole along its axis, the first end of the positioning shaft is installed on the base, the second end of the positioning shaft passes through the side of the cover plate away from the base along the positioning hole and is provided with an external thread, and the clamping nut is threadedly connected to the second end of the positioning shaft and abuts against the side of the cover plate away from the base.

[0013] More preferably, the clamping assembly further comprises a limiting nut, which is threadedly connected to the second end of the positioning shaft and abuts against a side of the cover plate facing the base.

[0014] According to a second aspect of the present invention, a turbine blade balancing method is further provided, using the above-mentioned turbine blade balancing device, the turbine blade balancing method comprising the following steps:

[0015] S10: installing the base of the turbine blade balancing device on a balancing machine;

[0016] S20: installing a plurality of blades on the first limiting groove along the circumferential direction of the base and assembling them into a whole set of blades, and then pressing and fixing the cover plate on the base by a pressing assembly, and making the second limiting groove and the first limiting groove clamp and fix the whole set of blades;

[0017] S30: Start the balancing machine to test the unbalance of the entire blade disc to determine whether the unbalance of the entire blade disc meets the requirements;

[0018] S40: When the unbalanced amount of the entire disk of blades meets the requirements, the entire disk of blades is taken out and enters the next assembly process; when the unbalanced amount of the entire disk of blades does not meet the requirements, the cover plate is removed, the blades in the unbalanced position are moved out radially along the base, the arrangement order of the blades is readjusted, and then steps S20 to S30 are repeated.

[0019] According to a third aspect of the present invention, there is also provided a turbine blade assembly method, comprising the following steps:

[0020] S100: using the turbine blade balancing method to match a whole blade disk whose unbalance amount meets the requirements, and using a balancing machine to test the unbalance amount of the turbine disk;

[0021] S200: Assemble the whole blade disk onto the turbine disk, and arrange the weighted position of the whole blade disk and the weighted position of the turbine disk symmetrically along the axis of the turbine disk.

[0022] Preferably, step S100 specifically includes: using the turbine blade balancing method as described in claim 8 to match multiple sets of whole-disc blades whose imbalance amounts meet the requirements, and using a balancing machine to test the imbalance amounts of multiple turbine disks; step S200 specifically includes: sorting the multiple sets of whole-disc blades according to the size of the imbalance amounts, and sorting the multiple turbine disks according to the size of the imbalance amounts, pairing the multiple sets of whole-disc blades and the multiple turbine disks one by one in sequence, and then assembling the whole-disc blades on the turbine disk, and making the offset position of the whole-disc blades and the offset position of the turbine disk symmetrically arranged along the axis of the turbine disk.

[0023] The present invention has the following beneficial effects:

[0024] The turbine blade balancing device provided by the present invention realizes the pre-fixation of the blades through the first limiting groove on the base, so that a plurality of blades can be spliced ​​together on the base to form a whole disk of blades, and then the whole disk of blades is clamped and fixed by the second limiting groove and the first limiting groove on the cover plate, so as to limit the blades axially and radially, and stably fix the whole disk of blades, so that the whole disk of blades can be directly installed on the balancing machine for balancing test through the turbine blade balancing device, and the balancing test method is convenient and fast, and the accuracy of the test results can be ensured. Moreover, since the base and the cover plate are both set to be disc-shaped, the weight at any position along the circumferential direction is the same, which is convenient for balancing and debugging, and will not limit the installation angle of the whole disk of blades, so that the installation position of the blade can be flexibly adjusted. More importantly, the limit on the blade in multiple directions can be released at the same time by removing the cover plate, so that the blade can be taken out along the radial direction of the base without being interfered by the folding structure on the blade crown, which is convenient for disassembling and assembling each blade separately, and then it is convenient to adjust the position of different blades, so that the whole disk of blades can be more conveniently and quickly adjusted to a balanced state that meets the requirements, reducing the difficulty of balancing and debugging the whole disk of blades, and improving the efficiency of balancing and debugging.

[0025] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The exemplary 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:

[0027] Figure 1 It is a structural diagram of the splicing of two adjacent existing leaves at one end of the leaf crown;

[0028] Figure 2 A cross-sectional view of a turbine blade balancing device provided by an embodiment of the present invention;

[0029] Figure 3 for Figure 2 A partial enlarged view of area A in the turbine blade balancing device shown;

[0030] Figure 4 for Figure 2 A top view of a base in a turbine blade balancing device is shown;

[0031] Figure 5 for Figure 2 A bottom view of a cover plate in a turbine blade balancing device is shown;

[0032] Figure 6 For application Figure 2 A three-dimensional view of a whole disk blade of a turbine blade balancing device is shown;

[0033] Figure 7 A step diagram of a turbine blade balancing method provided by an embodiment of the present invention;

[0034] Figure 8 A step diagram of a turbine blade assembly method provided in an embodiment of the present invention.

[0035] Legend:

[0036] 1. Turbine blade balancing device; 11. Base; 111. First limiting groove; 1111. First groove wall; 112. First support portion; 113. Second support portion; 114. First weight-reducing hole; 12. Cover plate; 121. Second limiting groove; 1211. Second groove wall; 122. Positioning hole; 123. Second weight-reducing hole; 13. Clamping assembly; 131. Positioning shaft; 132. Clamping nut; 2. Blade; 21. Blade root; 22. Blade body; 23. Blade crown; 24. Tenon. DETAILED DESCRIPTION

[0037] The embodiments of the present invention are described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0038] Please combine Figure 2 and Figure 3 An embodiment of the present invention provides a turbine blade balancing device 1, which is used to install a whole disk of blades and test the balance of the whole disk of blades on a balancing machine. The whole disk of blades includes a plurality of blades 2 spliced ​​in sequence along a circumferential direction. The blade 2 includes a blade root 21, a blade body 22 and a blade crown 23 arranged in sequence along a length direction. The blade crown 23 is provided with a tenon 24 for snap-fitting with an assembly groove on a turbine disk.

[0039] The turbine blade balancing device 1 includes a base 11, a cover plate 12 and a clamping assembly 13. The base 11 and the cover plate 12 are arranged at intervals and parallel to each other. The base 11 and the cover plate 12 are both disc-shaped. The edge of the base 11 facing the cover plate 12 is provided with a first limiting groove 111 for clamping the blade 2 along the radial direction of the base 11, and the edge of the cover plate 12 facing the base 11 is provided with a second limiting groove 121 for clamping the blade 2 along the axial direction of the cover plate 12. The clamping assembly 13 is arranged between the base 11 and the cover plate 12. The clamping assembly 13 is used to clamp and fix the cover plate 12 on the base 11 along the axial direction of the cover plate 12, and make the second limiting groove 121 and the first limiting groove 111 clamp and fix the blade 2 to each other.

[0040] Please combine Figure 6The turbine blade balancing device 1 pre-fixes the blade 2 through the first limiting groove 111 on the base 11, so that multiple blades 2 can be spliced ​​together on the base 11 to form a whole blade disk, and then the whole blade disk is clamped and fixed to each other through the second limiting groove 121 on the cover plate 12 and the first limiting groove 111, so as to axially limit and radially limit the blade 2, and stably fix the whole blade disk, so that the whole blade disk can be directly installed on the balancing machine for balancing test through the turbine blade balancing device 1, and the balancing test method is convenient and fast, and the accuracy of the test results can be ensured. In addition, since the base 11 and the cover plate 12 are both set to be disc-shaped, The weight of the turbine blade balancing device 1 at any position along the circumferential direction is the same, which is convenient for balancing and debugging, and will not limit the installation angle of the entire disk of blades, so that the installation position of the blades can be flexibly adjusted. More importantly, it is only necessary to remove the cover plate 12 to simultaneously release the limitations on the blades 2 in multiple directions, so that the blades 2 can be taken out along the radial direction of the base 11 without being interfered by the folding structure on the blade crown 23, so that each blade 2 can be disassembled and assembled separately, and then it is easy to adjust the position of different blades 2, so that the entire disk of blades can be more conveniently and quickly adjusted to a balanced state that meets the requirements, thereby reducing the difficulty of balancing and debugging the entire disk of blades and improving the efficiency of balancing and debugging.

[0041] like Figure 3 As shown, the first limiting groove 111 includes a first groove wall 1111, and the first groove wall 1111 is used to abut against a side of the crown 23 of the blade 2 toward the center of the base 11 radially outwardly of the base 11, and the first limiting groove 111 extends in a direction away from the center of the base 11 to form an escape space for the crown 23 to move radially along the base 11.

[0042] The first limiting groove 111 radially limits the blade 2 through the first groove wall 1111, and an avoidance space adapted to the blade crown 23 is set in the first limiting groove 111, so that the blade crown 23 of the blade 2 can slide in the first limiting groove 111 along the radial direction of the base 11 to realize the disassembly and assembly of a single blade 2, and when the blade 2 slides to a preset installation position, the first groove wall 1111 abuts against the blade crown 23, which facilitates confirmation of the installation position of the blade 2 and ensures that it is installed in place.

[0043] Furthermore, a first supporting portion 112 and a second supporting portion 113 are provided on a side of the base 11 facing the cover plate 12. The first supporting portion 112 and the second supporting portion 113 are arranged on both sides of the first limiting groove 111 along the radial direction of the base 11. The first supporting portion 112 is used to support the tenon 24 of the blade 2, and the second supporting portion 113 is used to support the blade root 21 of the blade 2. The blade 2 is supported in a horizontal state by the first supporting portion 112 and the second supporting portion 113, thereby ensuring the assembly accuracy and stability of the blade 2.

[0044] Preferably, the second limiting groove 121 includes a second groove wall 1211, and the second groove wall 1211 is used to abut against a side of the crown 23 of the blade 2 away from the center of the base 11 along the radial inward direction of the base, thereby limiting the blade 2 from moving in a direction away from the center of the base 11 through the second groove wall 1211.

[0045] The turbine blade balancing device 1 can clamp and fix the blade 2 in the thickness direction of the blade 2 through the cooperation of the cover plate 12 and the base 11, and can also clamp and fix the blade 2 in the length direction of the blade 2 through the cooperation of the first groove wall 1111 and the second groove wall 1211, and simultaneously realize the axial and radial limitation of the blade 2, effectively ensuring the stability of the blade 2. Secondly, the minimum inner diameter of the whole blade is limited by the first groove wall 1111, and the maximum outer diameter of the whole blade is limited by the second groove wall 1211, which effectively improves the assembly accuracy of the whole blade, and makes the whole blade coaxial and concentric relative to the base 11, which is convenient for balancing test.

[0046] Furthermore, the lower surface of the cover plate 12 facing the base 11 is used to abut against the tenon 24 , so as to press and fix the tenon 24 on the first supporting portion 112 of the base 11 .

[0047] like Figure 4 and Figure 5 As shown, the first limiting groove 111 extends into a circular ring shape along the circumferential direction of the base 11, and the second limiting groove 121 extends into a circular ring shape along the circumferential direction of the cover plate 12, so that the blade 2 can be adjusted and installed to any position of the turbine blade balancing device 1 along the circumferential direction, the installation position is more flexible and changeable, and there is no blocking structure between two adjacent blades 2, which will not interfere with the disassembly and assembly of the blade 2, and it is convenient to perform balance adjustment of multiple blades 2.

[0048] Furthermore, the base 11 is provided with a plurality of first weight-reducing holes 114, which are axially symmetrically arranged along the axis of the base 11; the cover plate 12 is provided with a plurality of second weight-reducing holes 123, which are axially symmetrically arranged along the axis of the cover plate 12; the first weight-reducing holes 114 and the second weight-reducing holes 123 are used to reduce the weight of the turbine blade balancing device 1, thereby reducing the influence of the turbine blade balancing device 1 on the balance test structure.

[0049] Preferably, the first weight-reducing holes 114 and the second weight-reducing holes 123 are arranged in one-to-one correspondence to make the weight distribution between the base 11 and the cover plate 12 more balanced, and the press-fitting position of the cover plate 12 can be judged by the alignment state of the first weight-reducing holes 114 and the second weight-reducing holes 123, so as to rotate and adjust the installation direction of the cover plate 12, thereby facilitating the symmetrical arrangement of the weighted position of the cover plate 12 and the weighted position of the base 11 along the positioning axis 131, and adjusting the turbine blade balancing device 1 to the optimal balance state before assembling the blade 2.

[0050] exist Figure 2 As shown in the figure, the clamping assembly 13 includes a positioning shaft 131 and a clamping nut 132, the cover plate 12 is provided with a positioning hole 122 along its axis, the first end of the positioning shaft 131 is installed on the base 11 and is coaxially arranged relative to the base 11, the second end of the positioning shaft 131 passes through the side of the cover plate 12 away from the base 11 along the positioning hole 122 and is provided with an external thread, the clamping nut 132 is threadedly connected to the second end of the positioning shaft 131 and abuts against the side of the cover plate 12 away from the base 11, so that the cover plate 12 is clamped along the positioning shaft 131 by the clamping nut 132, the clamping structure is simple and efficient, and it is convenient to disassemble and assemble, and the positioning shaft 131 can also play a role in axial positioning, to ensure that the cover plate 12 and the base 11 are coaxial and concentric, to avoid the cover plate 12 from tilting relative to the base 11 and affecting the balance.

[0051] Optionally, the clamping assembly 13 also includes a limiting nut (not shown, the same below), which is threadedly connected to the second end of the positioning shaft 131 and abuts against the side of the cover plate 12 facing the base 11. The limiting nut limits the extreme position of the movement of the cover plate 12 toward the base 11 to avoid the cover plate 12 being pressed down too much and causing damage to the blade 2, and the limiting nut can be rotatably adjusted relative to the positioning shaft 131 to facilitate adaptation to different limiting requirements.

[0052] In other embodiments, a limiting step may be directly provided on the outer periphery of the positioning shaft 131 , and the limiting step abuts against a side of the cover plate 12 facing the base 11 , thereby providing higher support strength and better stability.

[0053] like Figure 7 As shown, as a second aspect, an embodiment of the present invention further provides a turbine blade balancing method, using the turbine blade balancing device 1, the turbine blade balancing method comprises the following steps:

[0054] Step S10: installing the base 11 of the turbine blade balancing device 1 on a balancing machine.

[0055] After the base 11 is installed on the balancing machine, it is necessary to check whether the runout of the base 11 meets the requirements, and start the balancing machine to test the unbalance of the base 11. When the unbalance of the base 11 does not meet the requirements, it is necessary to adjust the weight of the base 11, or grind the unbalanced position of the base 11, or directly replace another base 11 until the base 11 on the balancing machine meets the test requirements.

[0056] Step S20: install multiple blades 2 on the first limiting groove 111 along the circumferential direction of the base 11 and assemble them into a whole plate of blades, then press and fix the cover plate 12 on the base 11 through the clamping assembly 13, and make the second limiting groove 121 and the first limiting groove 111 clamp and fix the whole plate of blades.

[0057] Before installing the blades 2, the weights of the blades 2 are measured and sorted respectively, and then a plurality of blades 2 are cross-arranged on the surface of the base 1 in order of weight, and the light and heavy blades are staggered to make the weight distance as uniform as possible.

[0058] When installing the blade 2, the crown 23 of the blade 2 is abutted against the first groove wall 1111, and the tenon 24 of the blade 2 is supported on the first support portion 112, and the root 21 of the blade 2 is supported on the second support portion 113. The blade 2 is supported and fixed by the first limiting groove 111, the first support portion 112 and the second support portion 113, so that the blade 2 is in a horizontal state.

[0059] After all the blades 21 are assembled in place to form the entire blade plate, an elastic rope such as a cotton rope or a rubber rope is sleeved on the outer circumference of the entire blade plate, and all the blades 21 are gathered inward and pressed against the first groove wall 1111 by the elastic rope, so that the entire blade plate is tightened in place to prevent the blades 2 from loosening.

[0060] Finally, the cover plate 12 is pressed and fixed on the base 11 by the pressing assembly 13, and the entire blade plate is clamped and fixed by the second limiting groove 121 and the first limiting groove 111. After the entire blade plate is installed in place, the elastic rope is removed.

[0061] S30: Start the balancing machine to test the unbalance amount of the entire blade disc to determine whether the unbalance amount of the entire blade disc meets the requirements.

[0062] The turbine blade balancing device 1 is used to directly install the entire blade disk on a balancing machine for testing. Before the balancing test, there is no need to install the entire blade disk as a whole on the turbine disk. The testing method is more convenient and quick, and can ensure the accuracy of the test results, and avoid other structures on the turbine disk fan affecting the balance of the entire blade disk.

[0063] S40: When the unbalanced amount of the entire disk of blades meets the requirements, the entire disk of blades is taken out and enters the next assembly process; when the unbalanced amount of the entire disk of blades does not meet the requirements, the cover plate 12 is removed, the blades 2 in the unbalanced position are moved out radially along the base 11, the arrangement order of the blades 2 is readjusted, and then steps S20 to S30 are repeated.

[0064] When the imbalance of the entire disc of blades does not meet the requirements, it is only necessary to remove the cover plate 12 to simultaneously release the limitations on the blades 2 in multiple directions, so that the blades 2 can be directly pulled out along the radial direction of the base 11. The disassembly and assembly process is not interfered by the folding structure on the blade crown 23, which facilitates the individual disassembly and assembly of each blade 2, and further facilitates the adjustment of the assembly position of each blade 2.

[0065] Regarding the position adjustment method of the blade 2, specifically, at least one blade 2 in a heavy position and at least one blade 2 in a light position in the entire disk of blades can be replaced. The actual number of blades 2 to be replaced is selected according to the size of the weight difference between the two positions. When the weight difference is small, only one blade 2 needs to be replaced. When the weight difference is large, at least two blades 2 should be replaced to adjust the entire disk of blades to a balanced state that meets the requirements.

[0066] After the arrangement sequence of the blades 2 is readjusted, steps S20 to S30 are repeated until the unbalanced amount of the entire set of blades meets the requirements, and then the entire set of blades can be taken out and enter the next assembly process.

[0067] In summary, the turbine blade balancing method uses the turbine blade balancing device 1 for balancing and debugging, and the balancing test method is convenient and fast, and can ensure the accuracy of the test results. More importantly, each blade 2 can be individually disassembled and assembled along the radial direction of the base 11, which is convenient for adjusting the positions of different blades 2, so that the entire disk of blades can be more conveniently and quickly adjusted to a balanced state that meets the requirements, reducing the difficulty of balancing and debugging the entire disk of blades. Secondly, since the entire disk of blades does not need to be assembled on the turbine disk during the balancing and debugging operation, the overall weight is greatly reduced, and there is no need to use large-scale lifting equipment for lifting and transportation during the balancing and debugging process, which reduces the waste of manpower and material resources, reduces costs, and effectively improves the efficiency of balancing and debugging.

[0068] like Figure 8 As shown, as a third aspect, an embodiment of the present invention further provides a turbine blade assembly method, comprising:

[0069] Step S100: using the turbine blade balancing method provided in an embodiment of the present invention to match a whole blade disk whose unbalance amount meets the requirements, and using a balancing machine to test the unbalance amount of the turbine disk.

[0070] The turbine blade balancing device 1 can be used to independently complete the balancing and debugging of the entire disk of blades, so that the balancing and debugging operations of the entire disk of blades and the turbine disk can be carried out simultaneously on different equipment, thereby improving the debugging efficiency and conveniently marking the parameters such as the weight position and weight value of the entire disk of blades, so that the entire disk of blades can better match the turbine disk.

[0071] Furthermore, when there are multiple sets of whole disk blades to be assembled, the turbine blade balancing method is used to match multiple sets of whole disk blades whose unbalance amounts meet the requirements, and a balancing machine is used to test the unbalance amounts of multiple turbine disks.

[0072] Since the turbine blade balancing device 1 can flexibly disassemble and assemble each blade 2, when the number of blades 2 is greater, more blades 2 can be replaced, thereby being able to accurately match and replace blades 2 of more different weights, and better match multiple sets of whole disc blades with unbalance amounts that meet the requirements, so that the unbalance amount of each set of whole disc blades is better.

[0073] Step S200: Assemble the whole blade disk onto the turbine disk, and make the weighted position of the whole blade disk and the weighted position of the turbine disk symmetrically arranged along the axis of the turbine disk.

[0074] By adopting the turbine blade balancing method, the entire blade disk can be treated as an integral structure for a balance test, and the actual imbalance of the entire blade disk can be accurately measured, so that the weighted position of the entire blade disk and the weighted position of the turbine disk can be symmetrically arranged along the axis of the turbine disk, so that the imbalance positions of the entire blade disk and the turbine disk are staggered, the mass difference is balanced, and the static imbalance is reduced.

[0075] Furthermore, when there are multiple sets of whole disc blades that need to be assembled, the turbine blade balancing method provided in the embodiment of the present invention is used to match the whole disc blades whose imbalance amounts meet the requirements, and a balancing machine is used to test the imbalance amount of the turbine disk. Then, the multiple sets of whole disc blades are sorted according to the size of the imbalance amount, and the multiple turbine disks are sorted according to the size of the imbalance amount. The multiple sets of whole disc blades and the multiple turbine disks are paired one by one in sequence, and then the whole disc blades are assembled on the turbine disk, and the unbalanced position of the whole disc blades and the unbalanced position of the turbine disk are symmetrically arranged along the axis of the turbine disk.

[0076] Compared with traditional assembly methods, matching between multiple sets of complete blades and multiple turbine disks can improve the balancing effect, simplify the blade position adjustment cycle, and significantly shorten the assembly cycle.

[0077] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A turbine blade balancing device, used for installing a whole blade disk and testing the balance of the whole blade disk on a balancing machine, wherein the whole blade disk comprises a plurality of blades (2) spliced ​​in sequence along a circumferential direction, characterized in that: The turbine blade balancing device comprises a base (11), a cover plate (12) and a clamping assembly (13); the base (11) and the cover plate (12) are arranged at intervals and parallel to each other; the clamping assembly (13) is arranged between the base (11) and the cover plate (12); the base (11) and the cover plate (12) are both disc-shaped; an edge of the base (11) facing the cover plate (12) is provided with a clamping member for clamping the blade along the radial direction of the base (11) The cover plate (12) is provided with a first limiting groove (111) on the side facing the base (11), a second limiting groove (121) for clamping the blade (2) along the axial direction of the cover plate (12), and the clamping assembly (13) is used to clamp and fix the cover plate (12) on the base (11) along the axial direction of the cover plate (12), and the second limiting groove (121) and the first limiting groove (111) clamp and fix the blade (2); The first limiting groove (111) comprises a first groove wall (1111), the first groove wall (1111) being used to abut against a side of a blade crown (23) of the blade (2) facing the center of the base (11) in a radially outward direction of the base (11), and the first limiting groove (111) extending in a direction away from the center of the base (11) to form an escape space for the blade crown (23) to move radially along the base (11).

2. The turbine blade balancing device according to claim 1, characterized in that: A first supporting portion (112) and a second supporting portion (113) are provided on a side of the base (11) facing the cover plate (12); the first supporting portion (112) and the second supporting portion (113) are arranged on both sides of the first limiting groove (111) along the radial direction of the base (11); the first supporting portion (112) is used to support the tenon (24) of the blade (2), and the second supporting portion (113) is used to support the blade root (21) of the blade (2).

3. The turbine blade balancing device according to claim 1, characterized in that: The second limiting groove (121) comprises a second groove wall (1211), and the second groove wall (1211) is used to abut against a side of the blade crown (23) of the blade (2) away from the center of the base (11) inwardly along the radial direction of the base (11).

4. The turbine blade balancing device according to claim 1, characterized in that: The first limiting groove (111) extends in a circular ring shape along the circumferential direction of the base (11), and the second limiting groove (121) extends in a circular ring shape along the circumferential direction of the cover plate (12).

5. The turbine blade balancing device according to claim 1, characterized in that: The clamping assembly (13) comprises a positioning shaft (131) and a clamping nut (132); the cover plate (12) is provided with a positioning hole (122) along its axis; the first end of the positioning shaft (131) is mounted on the base (11); the second end of the positioning shaft (131) passes through a side of the cover plate (12) away from the base (11) along the positioning hole (122) and is provided with an external thread; the clamping nut (132) is threadedly connected to the second end of the positioning shaft (131) and abuts against a side of the cover plate (12) away from the base (11).

6. The turbine blade balancing device according to claim 5, characterized in that: The clamping assembly (13) further comprises a limiting nut, which is threadedly connected to the second end of the positioning shaft (131) and abuts against a side of the cover plate (12) facing the base (11).

7. A turbine blade balancing method, characterized in that: Using the turbine blade balancing device according to any one of claims 1 to 6, the turbine blade balancing method comprises the following steps: S10: installing a base (11) of the turbine blade balancing device onto a balancing machine; S20: installing a plurality of blades (2) on the first limiting groove (111) along the circumferential direction of the base (11) and assembling them into a whole set of blades, and then pressing and fixing the cover plate (12) on the base (11) by means of a pressing assembly (13), and making the second limiting groove (121) and the first limiting groove (111) mutually clamp and fix the whole set of blades; S30: Start the balancing machine to test the unbalance of the entire blade disc to determine whether the unbalance of the entire blade disc meets the requirements; S40: When the unbalanced amount of the entire disk of blades meets the requirements, the entire disk of blades is taken out and enters the next assembly process; when the unbalanced amount of the entire disk of blades does not meet the requirements, the cover plate (12) is removed, the blades (2) at the unbalanced position are moved out radially along the base (11), the arrangement order of the blades (2) is readjusted, and then steps S20 to S30 are repeated.

8. A method for assembling a turbine blade, characterized in that: The following steps are involved: S100: using the turbine blade balancing method as claimed in claim 7 to match a whole blade disk whose unbalance amount meets the requirements, and using a balancing machine to test the unbalance amount of the turbine disk; S200: Assemble the whole blade disk onto the turbine disk, and arrange the weighted position of the whole blade disk and the weighted position of the turbine disk symmetrically along the axis of the turbine disk.

9. The turbine blade assembly method according to claim 8, characterized in that: Step S100 specifically includes: using the turbine blade balancing method as claimed in claim 7 to match multiple sets of whole-disk blades whose unbalance amounts meet the requirements, and using a balancing machine to test the unbalance amounts of multiple turbine disks; Step S200 specifically includes: sorting multiple sets of whole-disk blades according to the size of the imbalance, and sorting multiple turbine disks according to the size of the imbalance, pairing the multiple sets of whole-disk blades and the multiple turbine disks one by one in sequence, and then assembling the whole-disk blades on the turbine disk, and making the unbalanced position of the whole-disk blades and the unbalanced position of the turbine disk symmetrically arranged along the axis of the turbine disk.

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