Indirect measurement method for dynamic balance of turbine rotor assembly

Abstract

The present invention discloses an indirect measurement method for the dynamic balance of a turbine rotor during final assembly, comprising the following steps: setting the weight difference between the left and right blades of any group of rotor blades, and the weight difference between two groups of rotor blades at any diameter; ensuring that the dynamic unbalance, radial runout, and end runout of the turbine main shaft, turbine rotor portion, and turbine rotor respectively meet requirements, and marking the number of the rotor blade corresponding to the maximum radial runout of the turbine rotor portion and the position of the maximum end runout; ensuring that the radial runout, end runout, rotor blade corresponding to the maximum radial runout, and the maximum end runout during final assembly of the turbine rotor respectively meet requirements with the radial runout and end runout during dynamic balancing, the rotor blade position difference corresponding to the maximum radial runout, and the position difference of the maximum end runout. The indirect measurement method of the present invention can indirectly ensure that the dynamic balance of the turbine rotor during final assembly meets requirements, thereby reducing workload, reducing labor intensity for workers, and increasing work efficiency.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, and in particular to an indirect measurement method for dynamic balance of a turbine rotor assembly. Background Art

[0002] The turbine rotor of a certain type of engine is as follows Figure 1 As shown, it is mainly composed of turbine working blades 1, turbine discs 2, tension bolts 3, turbine shafts 4 and bearings 5. The engine uses the turbine rotor to do work and drive the compressor and propeller.

[0003] During assembly, turbine rotors undergo static and dynamic balancing tests to ensure that their dynamic imbalance is less than 10g·cm. Due to assembly requirements, the turbine rotor must be disassembled after dynamic balancing testing and then reassembled in stages for overall assembly. Verification of the dynamic balance after assembly is then conducted to ensure that it meets the required balance requirements.

[0004] In the prior art, after the turbine rotor is dynamically balanced, it is directly assembled and tested. During the test, if the engine vibration does not meet the requirements, it is disassembled again and corrected, and then dynamically balanced again after correction. This process is repeated, which is labor-intensive, labor-intensive, and inefficient. It is also difficult to meet the vibration requirements of the engine. Summary of the Invention

[0005] The present invention provides an indirect measurement method for the dynamic balance of a turbine rotor assembly, which solves the technical problems of the existing method, such as heavy workload, high labor intensity for workers, low work efficiency, and difficulty in meeting engine vibration requirements.

[0006] The technical solution adopted in the present invention is as follows:

[0007] A method for indirectly measuring the dynamic balance of a turbine rotor assembly, wherein the turbine rotor includes a turbine main shaft, and a first-stage rotor, a second-stage rotor, and a third-stage rotor mounted on the turbine main shaft, and the first-stage rotor, the second-stage rotor, and the third-stage rotor each include a turbine disk mounted on the turbine main shaft, and a plurality of groups of rotor blades sequentially mounted on the outer circle of the turbine disk, and each group of rotor blades includes a left blade and a right blade that are arranged in a coordinated manner. The indirect measurement method includes the following steps: S10: setting the weight difference between the left blade and the right blade of any group of rotor blades in the first-stage rotor, the second-stage rotor, and the third-stage rotor, and the weight difference between the two groups of rotor blades on any diameter to ensure the static balance of the turbine rotor; S20: ensuring the dynamic unbalance of the turbine main shaft, the turbine rotor portion consisting of the turbine main shaft, the first-stage rotor, and the second-stage rotor, the turbine rotor, the radial runout of the center hole, and the end runout of the turbine disk end face. The quantities meet the requirements respectively, and the number of the rotor blade corresponding to the maximum radial runout of the turbine rotor part, the position of the maximum end runout, and the number of the rotor blade corresponding to the maximum radial runout of the turbine rotor are marked; S30: Ensure that the radial runout, end runout, rotor blades corresponding to the maximum radial runout, and the maximum end runout of the turbine rotor part during final assembly of the turbine rotor, respectively meet the requirements with the difference between the radial runout and the end runout of the turbine rotor part during dynamic balancing, the position difference of the rotor blades corresponding to the maximum radial runout, and the position difference of the maximum end runout, and ensure that the radial runout, end runout, rotor blades corresponding to the maximum radial runout, and the maximum end runout of the turbine rotor during final assembly of the turbine rotor, respectively meet the requirements with the difference between the radial runout and the end runout of the turbine rotor during dynamic balancing, the position difference of the rotor blades corresponding to the maximum radial runout, and the position difference of the maximum end runout.

[0008] Furthermore, in step S10, the weight difference between the left blades and the right blades of any group of rotor blades in the first-stage rotor is set to be no more than 2g, and the weight difference between the two groups of rotor blades on any diameter is set to be no more than 1g; the weight difference between the left blades and the right blades of any group of rotor blades in the second-stage rotor is set to be no more than 3.5g, and the weight difference between the two groups of rotor blades on any diameter is set to be no more than 2g; the weight difference between the left blades and the right blades of any group of rotor blades in the third-stage rotor is set to be no more than 4g, and the weight difference between the two groups of rotor blades on any diameter is set to be no more than 2g.

[0009] Furthermore, in step S10, it is also set that the weight difference between any two groups of rotor blades in the first-stage rotor is no more than 2g.

[0010] Furthermore, in step S10, when the weight difference between any two groups of rotor blades in the first-stage rotor, the weight difference between the left blades and the right blades of any group of rotor blades, and the weight difference between two groups of rotor blades on any diameter do not meet the requirements, they can be processed by replacing the paired left blades and right blades, adding balancing blocks to the rotor blades, or removing material from the rotor blades.

[0011] Furthermore, step S20 specifically includes the following steps: S21: performing the first dynamic balancing on the turbine main shaft to ensure the dynamic unbalance; S22: performing the second dynamic balancing on the turbine rotor part to ensure its dynamic unbalance, radial runout and end runout, and marking the number of the rotor blade corresponding to the maximum radial runout and the position of the maximum end runout; S23: performing the third dynamic balancing on the turbine rotor to ensure its dynamic unbalance, radial runout and end runout, and marking the number of the rotor blade corresponding to the maximum radial runout and the position of the maximum end runout.

[0012] Furthermore, in step S21 , the dynamic unbalance is ensured to be less than 5 g·cm, and when the dynamic unbalance does not meet the requirement, both ends of the turbine main shaft are subjected to material removal.

[0013] Furthermore, in step S22, the dynamic unbalance is ensured to be less than 5g·cm; the radial runout of the second-stage rotor is ensured to be no greater than 0.06 and the end runout is ensured to be no greater than 0.1, and the number of the rotor blade corresponding to the maximum radial runout of the second-stage rotor and the position of the maximum end runout are identified.

[0014] Furthermore, in step S23, the dynamic unbalance is ensured to be less than 10 g·cm; the radial runout of the third-stage rotor is ensured to be no greater than 0.06 and the end runout is ensured to be no greater than 0.1, and the number of the rotor blade corresponding to the maximum radial runout of the third-stage rotor and the position of the maximum end runout are identified.

[0015] Furthermore, step S30 specifically includes the following steps: S31: measuring the radial runout and end runout of the turbine rotor part to ensure that the difference between its radial runout and end runout and the corresponding radial runout and end runout in the second dynamic balancing, and also ensuring that the position difference between the blade corresponding to the maximum radial runout and the rotor blade corresponding to the maximum radial runout in the second dynamic balancing, and the position difference between the position of the maximum end runout and the position of the maximum end runout in the second dynamic balancing meet the requirements; S32: measuring the radial runout and end runout of the turbine rotor to ensure that the difference between its radial runout and end runout and the corresponding radial runout and end runout in the third dynamic balancing, and also ensuring that the position difference between the rotor blade corresponding to the maximum radial runout and the rotor blade corresponding to the maximum radial runout in the third dynamic balancing, and the position difference between the position of the maximum end runout and the position of the maximum end runout in the third dynamic balancing meet the requirements.

[0016] Further, in step S31, it is ensured that the difference between its radial runout and the corresponding radial runout in the second dynamic balancing is not greater than 0.03, the difference between its end runout and the corresponding end runout in the second dynamic balancing is not greater than 0.03, the number of rotor blades corresponding to the rotor blade corresponding to the maximum radial runout in the second dynamic balancing is not more than four groups of rotor blades, and the number of rotor blades between the position of the maximum end runout and the position of the maximum end runout in the second dynamic balancing is not more than four groups; in step S32, it is ensured that the difference between its radial runout and the corresponding radial runout in the third dynamic balancing is not greater than 0.03, the difference between its end runout and the corresponding end runout in the third dynamic balancing is not greater than 0.03, the number of rotor blades corresponding to the rotor blade corresponding to the maximum radial runout in the third dynamic balancing is not more than four groups, and the number of rotor blades between the position of the maximum end runout and the position of the maximum end runout in the third dynamic balancing is not more than four groups.

[0017] The present invention has the following beneficial effects:

[0018] In the indirect measurement method of the present invention, first, the rotor blades are grouped by weight through step S10 to meet the static balance requirement of the turbine rotor; then the turbine rotor is dynamically balanced, that is, the dynamic balance of the turbine main shaft, the dynamic balance of the turbine rotor part composed of the turbine main shaft, the first-stage rotor and the second-stage rotor, and the dynamic balance of the turbine rotor as a whole, to ensure that the final unbalance amount is not greater than 10g·cm. Under the premise of meeting the dynamic balance, the number of the rotor blade corresponding to the maximum radial runout of the turbine rotor and the position of the maximum end runout are recorded and marked; then, the turbine rotor is disassembled after dynamic balancing and then assembled during final assembly. During the assembly, the radial runout and end runout are measured again, and the difference between the radial runout and end runout and the radial runout and end runout during dynamic balancing, as well as the position corresponding to the maximum radial runout, are ensured. The position difference of the rotor blades and the position difference of the maximum end runout respectively meet the requirements, thereby indirectly ensuring that the dynamic balance of the turbine rotor meets the requirements during final assembly. Since there is no need to repeatedly disassemble, correct and reassemble, the workload is small, the labor intensity of the workers is low, and the work efficiency is high, and it well meets the vibration requirements of the engine; the present invention determines the dynamic balance requirements of the turbine rotor through multiple dynamic balancing, and utilizes the process of combination-decomposition-reassembly of the turbine rotor to select the maximum value of the indirect measurement of the diameter runout and the end runout, gives the runout position range, and determines the position of the maximum runout value, thereby determining that the dynamic balance meets the requirements during final assembly, and using the position difference to determine the runout range is more direct and specific, without the need for tooling to measure again, and after calculation and verification, the present invention meets the engine requirements and can well reflect the effect of dynamic balancing.

[0019] In addition to the above-described objects, features and advantages, the present invention has other objects, features and advantages. The present invention will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The accompanying drawings, which constitute part of this application, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0021] Figure 1 is a schematic diagram of a turbine rotor in the prior art;

[0022] Figure 2 is a two-dimensional schematic diagram of a turbine rotor blade according to the present invention;

[0023] Figure 3 This is a schematic diagram of the dynamic balance of the turbine rotor part of the present invention

[0024] Figure 4 It is a schematic diagram of the turbine rotor assembly measurement of the present invention.

[0025] Legend

[0026] 10. Turbine main shaft; 20. First-stage rotor; 30. Second-stage rotor; 40. Third-stage rotor; 50. Turbine disk; 501. Small hole; 502. Center hole; 503. End face; 60. Rotor blade; 61. Left blade; 62. Right blade. DETAILED DESCRIPTION

[0027] 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.

[0028] Reference Figure 2-Figure 4 A preferred embodiment of the present invention provides an indirect measurement method for the dynamic balance of a turbine rotor assembly. The turbine rotor includes a turbine main shaft 10, and a first-stage rotor 20, a second-stage rotor 30, and a third-stage rotor 40 mounted on the turbine main shaft 10. The first-stage rotor 20, the second-stage rotor 30, and the third-stage rotor 40 each include a turbine disk 50 mounted on the turbine main shaft 10, and multiple groups of rotor blades 60 sequentially mounted on the outer circumference of the turbine disk 50. Each group of rotor blades 60 includes a left blade 61 and a right blade 62 arranged in a coordinated manner. The indirect measurement method includes the following steps:

[0029] S10: Setting the weight difference between the left blade 61 and the right blade 62 of any group of rotor blades 60 in the first-stage rotor 20, the second-stage rotor 30, and the third-stage rotor 40, and the weight difference between two groups of rotor blades 60 on any diameter, to ensure the static balance of the turbine rotor;

[0030] S20: Ensure that the turbine main shaft 10, the turbine rotor portion consisting of the turbine main shaft 10, the first-stage rotor 20, and the second-stage rotor 30, the dynamic unbalance of the turbine rotor, the radial runout of the center hole 502, and the end runout of the end surface 503 of the turbine disk 50 meet the requirements, and mark the number and position of the rotor blade 60 corresponding to the maximum radial runout of the turbine rotor portion, and the number and position of the rotor blade 60 corresponding to the maximum radial runout of the turbine rotor;

[0031] S30: Ensure that the radial runout, end runout, rotor blade 60 corresponding to the maximum radial runout, and the maximum end runout of the turbine rotor part during final assembly meet the requirements respectively with the difference between the radial runout and the end runout during dynamic balancing of the turbine rotor part, the position difference of the rotor blade 60 corresponding to the maximum radial runout, and the position difference at the maximum end runout, and ensure that the radial runout, end runout, rotor blade 60 corresponding to the maximum radial runout, and the maximum end runout of the turbine rotor part during final assembly meet the requirements respectively with the difference between the radial runout and the end runout during dynamic balancing of the turbine rotor part, the position difference of the rotor blade 60 corresponding to the maximum radial runout, and the position difference at the maximum end runout.

[0032] In the indirect measurement method of the present invention, first, the rotor blades are grouped by weight through step S10 to meet the static balance requirement of the turbine rotor; then the turbine rotor is dynamically balanced, that is: the dynamic balance of the turbine main shaft 10, the dynamic balance of the turbine rotor part composed of the turbine main shaft 10, the first-stage rotor 20 and the second-stage rotor 30, and the dynamic balance of the turbine rotor as a whole, to ensure that the final unbalance amount is not greater than 10g·cm. Under the premise of meeting the dynamic balance, the number of the rotor blade 60 corresponding to the maximum radial runout of the turbine rotor and the position of the maximum end runout are recorded and marked; then, the turbine rotor is disassembled after dynamic balancing, and then assembled during final assembly. During assembly, the radial runout and end runout are measured again, and it is ensured that the difference between the radial runout and end runout and the radial runout and end runout during dynamic balancing, as well as the maximum radial runout, are The position difference of the corresponding rotor blades 60 and the position difference of the maximum end runout respectively meet the requirements, thereby indirectly ensuring that the dynamic balance of the turbine rotor meets the requirements during final assembly. Since there is no need to repeatedly disassemble, correct and recombine, the workload is small, the labor intensity of the workers is low, and the work efficiency is high, and it well meets the vibration requirements of the engine; the present invention determines the dynamic balance requirements of the turbine rotor through multiple dynamic balancing, and utilizes the process of combination-decomposition-recombination of the turbine rotor to select the maximum value of the indirect measurement of the diameter runout and the end runout, gives the runout position range, and determines the position of the maximum runout value, thereby determining that the dynamic balance meets the requirements during final assembly, and using the position difference to determine the runout range is more direct and specific, without the need for tooling to measure again, and after calculation and verification, the present invention meets the engine requirements and can well reflect the effect of dynamic balancing.

[0033] Alternatively, as Figure 1 As shown, in step S10, in order to ensure the static balance of the rotor blades, the left blades 61 and the right blades 62 processed in each stage of the rotor are grouped by weight. The grouping method is as follows:

[0034] The weight difference between the left blade 61 and the right blade 62 of any group of rotor blades 60 in the first-stage rotor 20 is set to be no greater than 2g, and the weight difference between the two groups of rotor blades 60 on any diameter is set to be no greater than 1g;

[0035] The weight difference between the left blade 61 and the right blade 62 of any group of rotor blades 60 in the second-stage rotor 30 is set to be no more than 3.5g, and the weight difference between the two groups of rotor blades 60 on any diameter is no more than 2g;

[0036] The weight difference between the left blade 61 and the right blade 62 of any group of rotor blades 60 in the third-stage rotor 40 is not greater than 4 g, and the weight difference between the two groups of rotor blades 60 on any diameter is not greater than 2 g.

[0037] Specifically, through the above grouping method of the first-stage rotor 20, the second-stage rotor 30 and the third-stage rotor 40, the static balance requirement of the turbine rotor can be well met.

[0038] Preferably, in step S10, the weight difference between any two groups of rotor blades 60 in the first-stage rotor 20 is set to be no more than 2g; since the first-stage rotor 20 is the benchmark of the turbine rotor, this grouping setting of the first-stage rotor 20 is added to further meet the static balance requirements of the turbine rotor.

[0039] Optionally, in step S10, when the weight difference between any two groups of rotor blades 60 in the first-stage rotor 20, the weight difference between the left blade 61 and the right blade 62 of any group of rotor blades 60, or the weight difference between two groups of rotor blades 60 on any diameter does not meet the requirements, the rotor blades 60 may be processed by replacing the paired left blades 61 and right blades 62, adding balancing blocks to the rotor blades 60, or removing material from the rotor blades 60 to ensure the static balance requirements of the turbine rotor. In this optional solution, if Figure 2 As shown, by adding a balancing block in the small hole 501 of the turbine disk 50, the weight difference can be made to meet the requirements; or, in order to ensure the blade processing rate and cost rate, the blade crown or grate of the rotor blade 60 can also be removed to meet the weight difference requirements.

[0040] Optionally, after ensuring the weight requirement of the turbine blades, the rotor blades 60 that meet the requirements are assembled into the grooves of the turbine disk 50, and then the turbine rotor is dynamically balanced, such as Figure 3 As shown, step S20 specifically includes the following steps:

[0041] S21: Perform the first dynamic balancing on the turbine main shaft 10 to ensure the dynamic unbalance amount;

[0042] S22: Performing a second dynamic balancing on the turbine rotor to ensure the dynamic unbalance, radial runout, and end runout, and marking the number of the rotor blade 60 corresponding to the maximum radial runout and the position of the maximum end runout;

[0043] S23: Perform a third dynamic balancing on the turbine rotor to ensure its dynamic unbalance, radial runout and end runout, and mark the number of the rotor blade 60 corresponding to the maximum radial runout and the position of the maximum end runout.

[0044] In this optional solution, in step S21 , the dynamic unbalance is ensured to be less than 5 g·cm, and when the dynamic unbalance does not meet the requirement, both ends of the turbine main shaft 10 are subjected to material removal processing.

[0045] In this optional solution, in step S22:

[0046] Ensure that the dynamic unbalance is less than 5g·cm. In actual operation, if the dynamic unbalance does not meet the requirements, the left blade 61 and the right blade 62 are replaced, or a balancing weight is added to the small hole 501 of the turbine disk 50, or material is removed from the rotor blade 60.

[0047] Ensure that the radial runout of the second-stage rotor 30 is no greater than 0.06 and the end runout is no greater than 0.1. The number of the rotor blade 60 corresponding to the point of maximum radial runout of the second-stage rotor 30 and the position of the point of maximum end runout are marked. If the radial runout of the second-stage rotor 30 does not meet the requirements, the center hole of the second-stage rotor 30 can be corrected. If the end runout of the second-stage rotor 30 does not meet the requirements, the end surface of the turbine disk of the second-stage rotor 30 can be corrected.

[0048] In this optional solution, in step S23:

[0049] Ensure that the dynamic unbalance is less than 10g·cm. In actual operation, if the dynamic unbalance does not meet the requirements, the left blade 61 and the right blade 62 are replaced, or a balancing weight is added to the small hole 501 of the turbine disk 50, or material is removed from the rotor blade 60.

[0050] Ensure that the radial runout of the third-stage rotor 40 is no greater than 0.06 and the end runout is no greater than 0.1. The number of the rotor blade 60 corresponding to the point of maximum radial runout and the position of the point of maximum end runout are marked. If the radial runout of the third-stage rotor 40 does not meet the requirements, the center hole of the third-stage rotor 40 can be corrected. If the end runout of the third-stage rotor 40 does not meet the requirements, the end surface of the turbine disk of the third-stage rotor 40 can be corrected.

[0051] Alternatively, as Figure 4 As shown, after the entire turbine rotor is dynamically balanced, it needs to be disassembled and then assembled in stages during final assembly. During final assembly, step S30 specifically includes the following steps:

[0052] S31: Measure the radial runout and end runout of the turbine rotor to ensure that the differences between the radial runout and end runout and the corresponding radial runout and end runout in the second dynamic balancing are met, and also ensure that the position difference between the blade corresponding to the maximum radial runout point and the rotor blade 60 corresponding to the maximum radial runout point in the second dynamic balancing, and the position difference between the position of the maximum end runout point and the position of the maximum end runout point in the second dynamic balancing meet the requirements;

[0053] S32: Measure the radial runout and end runout of the turbine rotor to ensure that the difference between its radial runout and end runout and the corresponding radial runout and end runout in the third dynamic balancing, and also ensure that the position difference between the rotor blade 60 corresponding to the maximum radial runout and the rotor blade 60 corresponding to the maximum radial runout in the third dynamic balancing, and the position difference between the position of the maximum end runout and the position of the maximum end runout in the third dynamic balancing meet the requirements.

[0054] In this optional solution, in step S31, it is ensured that the difference between its radial runout and the corresponding radial runout in the second dynamic balancing is not greater than 0.03, the difference between its end runout and the corresponding end runout in the second dynamic balancing is not greater than 0.03, the number of rotor blades 60 corresponding to the maximum radial runout and the rotor blade 60 corresponding to the maximum radial runout in the second dynamic balancing is not more than four groups of rotor blades 60, and the number of rotor blades 60 between the position of the maximum end runout and the position of the maximum end runout in the second dynamic balancing is not more than four groups of rotor blades 60;

[0055] In step S32, it is ensured that the difference between its radial runout and the corresponding radial runout in the third dynamic balancing is not greater than 0.03, the difference between its end runout and the corresponding end runout in the third dynamic balancing is not greater than 0.03, the number of rotor blades 60 corresponding to the maximum radial runout and the rotor blades 60 corresponding to the maximum radial runout in the third dynamic balancing is no more than four groups of rotor blades 60, and the number of rotor blades 60 between the position of the maximum end runout and the position of the maximum end runout in the third dynamic balancing is no more than four groups of rotor blades 60.

[0056] In this optional solution, it is more direct and specific to determine the runout range value by using the actual quantity (i.e., the rotor blades 60 corresponding to the maximum radial runout during assembly and the rotor blades 60 corresponding to the maximum radial runout during dynamic balancing are no more than four groups of rotor blades 60, and the position of the maximum end runout during assembly and the position of the maximum end runout during dynamic balancing) without the need for tooling to measure again, thereby greatly reducing the labor intensity of workers and improving measurement efficiency. Calculations and verification have shown that the present invention meets engine requirements and can well reflect the effect of dynamic balancing.

[0057] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A method for indirectly measuring the dynamic balance of a turbine rotor assembly, wherein the turbine rotor comprises a turbine main shaft (10), and a first-stage rotor (20), a second-stage rotor (30), and a third-stage rotor (40) mounted on the turbine main shaft (10), and the first-stage rotor (20), the second-stage rotor (30), and the third-stage rotor (40) each comprise a turbine disk (50) mounted on the turbine main shaft (10), and a plurality of groups of rotor blades (60) sequentially mounted on the outer circumference of the turbine disk (50), and each group of the rotor blades (60) comprises a left blade (61) and a right blade (62) arranged in a coordinated manner, characterized in that: The indirect measurement method includes the following steps: S10: setting a weight difference between the left blade (61) and the right blade (62) of any group of rotor blades (60) in the first-stage rotor (20), and a weight difference between the two groups of rotor blades (60) on any diameter, setting a weight difference between the left blade (61) and the right blade (62) of any group of rotor blades (60) in the second-stage rotor (30), and a weight difference between the two groups of rotor blades (60) on any diameter, and setting a weight difference between the left blade (61) and the right blade (62) of any group of rotor blades (60) in the third-stage rotor (40), and a weight difference between the two groups of rotor blades (60) on any diameter, to ensure the static balance of the turbine rotor; S20: Ensure that the turbine main shaft (10), the turbine rotor portion composed of the turbine main shaft (10) plus the first-stage rotor (20) plus the second-stage rotor (30), the dynamic unbalance of the turbine rotor, the radial runout of the center hole (502), and the end runout of the turbine disk (50) end surface (503) meet the requirements, and mark the number of the rotor blade (60) corresponding to the maximum radial runout of the turbine rotor portion and the position of the maximum end runout, and the number of the rotor blade (60) corresponding to the maximum radial runout of the turbine rotor and the position of the maximum end runout; S30: Ensure that the radial runout, end runout, rotor blade (60) corresponding to the maximum radial runout, and the maximum end runout of the turbine rotor portion during final assembly of the turbine rotor meet the requirements respectively, and ensure that the radial runout, end runout, rotor blade (60) corresponding to the maximum radial runout, and the maximum end runout of the turbine rotor portion during final assembly of the turbine rotor meet the requirements respectively, and ensure that the radial runout, end runout, rotor blade (60) corresponding to the maximum radial runout, and the maximum end runout of the turbine rotor portion during final assembly of the turbine rotor meet the requirements respectively, and the radial runout and end runout of the turbine rotor portion during final assembly of the turbine rotor meet the requirements respectively, and the radial runout and end runout of the turbine rotor portion during final assembly of the turbine rotor meet the requirements respectively, and the radial runout and end runout of the turbine rotor portion during final assembly of the turbine rotor meet the requirements respectively.

2. The indirect measurement method for dynamic balance of turbine rotor assembly according to claim 1, characterized in that: In step S10, The weight difference between the left blade (61) and the right blade (62) of any group of rotor blades (60) in the first-stage rotor (20) is set to be no greater than 2g, and the weight difference between the two groups of rotor blades (60) on any diameter is set to be no greater than 1g; The weight difference between the left blade (61) and the right blade (62) of any group of rotor blades (60) in the second-stage rotor (30) is set to be no greater than 3.5 g, and the weight difference between the two groups of rotor blades (60) on any diameter is set to be no greater than 2 g; The weight difference between the left blade (61) and the right blade (62) of any group of rotor blades (60) in the third-stage rotor (40) is set to be no greater than 4g, and the weight difference between the two groups of rotor blades (60) on any diameter is set to be no greater than 2g.

3. The indirect measurement method for dynamic balance of turbine rotor assembly according to claim 2, characterized in that: In step S10, it is further set that the weight difference between any two groups of rotor blades (60) in the first-stage rotor (20) is no more than 2g.

4. The indirect measurement method for dynamic balance of turbine rotor assembly according to claim 3, characterized in that: In step S10, when the weight difference between any two groups of rotor blades (60) in the first-stage rotor (20), the weight difference between the left blade (61) and the right blade (62) of any group of rotor blades (60), or the weight difference between two groups of rotor blades (60) on any diameter do not meet the requirements, the problems can be treated by replacing the paired left blades (61) and right blades (62), adding balancing blocks to the rotor blades (60), or removing material from the rotor blades (60).

5. The indirect measurement method for dynamic balance of turbine rotor assembly according to claim 1, characterized in that: Step S20 specifically includes the following steps: S21: Perform the first dynamic balancing on the turbine main shaft (10) to ensure the dynamic unbalance amount; S22: performing a second dynamic balancing on the turbine rotor portion to ensure its dynamic unbalance, radial runout, and end runout, and marking the number of the rotor blade (60) corresponding to the maximum radial runout and the position of the maximum end runout; S23: Performing a third dynamic balancing on the turbine rotor to ensure its dynamic unbalance, radial runout, and end runout, and marking the number of the rotor blade (60) corresponding to the maximum radial runout and the position of the maximum end runout.

6. The indirect measurement method for dynamic balance of turbine rotor assembly according to claim 5, characterized in that: In step S21, the dynamic unbalance is ensured to be less than 5 g·cm, and when the dynamic unbalance does not meet the requirement, both ends of the turbine main shaft (10) are subjected to material removal processing.

7. The indirect measurement method for dynamic balance of turbine rotor assembly according to claim 5, characterized in that: In step S22, Ensure that the dynamic unbalance is less than 5g·cm; Ensure that the radial runout of the second-stage rotor (30) is no greater than 0.06 and the end runout is no greater than 0.1, and mark the number of the rotor blade (60) corresponding to the maximum radial runout of the second-stage rotor (30) and the position of the maximum end runout.

8. The indirect measurement method for dynamic balance of turbine rotor assembly according to claim 7, characterized in that: In step S23, Ensure that the dynamic unbalance is less than 10g·cm; Ensure that the radial runout of the third-stage rotor (40) is no greater than 0.06 and the end runout is no greater than 0.1, and mark the number of the rotor blade (60) corresponding to the maximum radial runout of the third-stage rotor (40) and the position of the maximum end runout.

9. The indirect measurement method for dynamic balance of turbine rotor assembly according to claim 5, characterized in that: Step S30 specifically includes the following steps: S31: measuring the radial runout and end runout of the turbine rotor portion to ensure that the difference between the radial runout and end runout and the radial runout and end runout corresponding to the second dynamic balancing, and also ensuring that the position difference between the blade corresponding to the maximum radial runout and the rotor blade (60) corresponding to the maximum radial runout in the second dynamic balancing, and the position difference between the position of the maximum end runout and the position of the maximum end runout in the second dynamic balancing meet the requirements; S32: The radial runout and end runout of the turbine rotor are measured to ensure that the difference between the radial runout and end runout and the corresponding radial runout and end runout in the third dynamic balancing is met, and also ensure that the position difference between the rotor blade (60) corresponding to the maximum radial runout point and the rotor blade (60) corresponding to the maximum radial runout point in the third dynamic balancing, and the position difference between the position of the maximum end runout point and the position of the maximum end runout point in the third dynamic balancing meet the requirements.

10. The indirect measurement method for dynamic balance of turbine rotor assembly according to claim 9, characterized in that: In step S31, it is ensured that the difference between its radial runout and the corresponding radial runout in the second dynamic balancing is not greater than 0.03, the difference between its end runout and the corresponding end runout in the second dynamic balancing is not greater than 0.03, the number of rotor blades (60) corresponding to the maximum radial runout and the rotor blades (60) corresponding to the maximum radial runout in the second dynamic balancing is not more than four groups of rotor blades (60), and the number of rotor blades (60) between the position of the maximum end runout and the position of the maximum end runout in the second dynamic balancing is not more than four groups of rotor blades (60); In step S32, it is ensured that the difference between its radial runout and the corresponding radial runout in the third dynamic balancing is not greater than 0.03, the difference between its end runout and the corresponding end runout in the third dynamic balancing is not greater than 0.03, the number of rotor blades (60) corresponding to the maximum radial runout and the rotor blade (60) corresponding to the maximum radial runout in the third dynamic balancing is not more than four groups of rotor blades (60), and the number of rotor blades (60) between the position of the maximum end runout and the position of the maximum end runout in the third dynamic balancing is not more than four groups of rotor blades (60).

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