Rotary machinery blade disc area isolation assembly and balance orientation optimization method

Abstract

The invention discloses a rotary machine blade disc area isolation assembly and balance orientation optimization method, and belongs to the technical field of blade disc structure optimization. The method comprises the following steps: step 1, establishing a bladed disc structure dynamic model; 2, dividing a primary region and a secondary region based on the blade disc structure dynamic model; step 3, optimizing the inherent frequency distribution rule of the blade based on a wrong frequency anti-vibration principle to obtain a plurality of blade disc region isolation assembly preliminary schemes; fourthly, the unbalance amount and the circumferential installation angle of each blade are adjusted, so that the forced vibration response maximum amplitude of the blade disc is minimized, and a plurality of blade disc area isolation assembly schemes are obtained; and step 5, constructing a balance orientation optimization objective function, and solving to obtain a scheme of leaf disc region isolation assembly and balance orientation optimization. According to the method, after the blade disc area isolation assembly and balance orientation optimization scheme is obtained, the actual assembly work of the blade disc structure is carried out, the process is simple, the workload is small, the efficiency is high, and the vibration control effect is good.

Description

Technical Field

[0001] The invention relates to a method for isolating and assembling a rotary machine blade disc area and balancing and directional optimization, and belongs to the technical field of blade disc structure assembly and balancing optimization. Background Art

[0002] The blade disk structure of rotating machinery needs to properly deal with vibration-related problems such as blade detuning, blade flutter and imbalance.

[0003] Blade detuning: Due to the limiting factors such as material inhomogeneity and processing and assembly errors, the cyclic symmetry of the structure of the rotating machinery blade is destroyed, which is called blade detuning. Blade detuning is mainly manifested as localized vibration, that is, the vibration energy is concentrated on a few blades, making the response amplitude of these blades much higher than that of the rest of the blades, causing high-cycle fatigue failure of local blades, posing a serious threat to the normal operation of the entire structure.

[0004] Blade flutter: The flutter of rotating machinery blades is aeroelastic instability. When the energy absorbed by the blade movement from the airflow is greater than the mechanical damping work, the blade flutters and may cause catastrophic consequences.

[0005] Imbalance: The design, manufacturing, assembly, and operation processes may cause the centroid of the rotating machinery blade disc structure to not coincide with the axis of rotation, thus causing the blade disc structure to be unbalanced. Once the blade disc structure is unbalanced, it will become the main source of vibration for the rotating machinery.

[0006] To address the above issues, the current rotating machinery blade disc structure needs to be assembled first and then balanced. This process is cumbersome, labor-intensive, inefficient, and has poor vibration control effects.

[0007] A Chinese patent document with publication number CN115438437A discloses a topological optimization method for aeroelastic stability of a turbine blade cascade, including step one: given the blade installation angle θ, blade spacing s, and incoming flow velocity U∞ in the cascade; step two: calculating the blade unit blade mass m, the mass static moment Sα and the mass moment of inertia Iα about the elastic axis, and obtaining the mass matrix; step three: mapping the density field ρ of the two-dimensional cross-section of the blade to the model of the three-dimensional solid blade; step four: establishing a loop for the phase angle. For each loop: calculating the dimensionless aerodynamic coefficient force (CFq)η, (CFα)η and the moment coefficient (CMq)η, (CMα)η corresponding to the current phase angle by an iterative method, and obtaining the aerodynamic matrix and step five: solving the objective function and constraint function and their sensitivity; step six: obtaining the updated density field ρk.

[0008] However, this optimization method mainly achieves the purpose of maintaining the blade in an aeroelastic stable state by optimizing the material arrangement of the hollow area of ​​the bending-torsion coupled hollow blades in the impeller machinery blade cascade, and is not suitable for assembly and balance optimization of the blade disk structure of the rotating machinery. Summary of the invention

[0009] In order to solve the above technical problems, the present invention provides a method for isolating, assembling and balancing and directional optimization of a rotary machinery blade disk area.

[0010] The present invention is achieved through the following technical solutions:

[0011] A method for isolating and assembling a rotating mechanical blade disk and balancing and directional optimization, comprising the following steps:

[0012] Step 1: Use finite element or dynamics software to establish a blade disk structure dynamics model;

[0013] Step 2: Design the detuned mode of the blade disk based on the structural dynamics model, divide the area where the vibration energy is concentrated into the main area, and divide the area between the main areas into secondary areas;

[0014] Step 3: Optimize the natural frequency distribution of blades based on the principle of frequency error prevention, that is, by increasing the natural frequency difference between blades, weakening the aeroelastic coupling between blades, improving the aeroelastic stability of the blade vibration system, and suppressing the occurrence of blade flutter, a preliminary plan for the isolation assembly of multiple blade disk areas is obtained;

[0015] Step 4: During the blade arrangement process of the preliminary isolation assembly scheme of each blade disk area, the size of the unbalance amount and the circumferential installation angle of each blade are adjusted to minimize the maximum amplitude of the forced vibration response of the blade disk, and multiple isolation assembly schemes of the blade disk area are obtained;

[0016] Step 5: Construct the balanced directional optimization objective function and use the optimization algorithm to solve it to obtain the solution for the isolation assembly and balanced directional optimization of the blade disk area.

[0017] The method for optimizing the natural frequency distribution law of the blade based on the frequency error anti-vibration principle in step 3 comprises the following steps:

[0018] Step 1: Measure the mass m of the blade to be assembled i , centroid d i And the natural frequency f, and according to the natural frequency of the blades, the blades are divided into three groups: high frequency, medium frequency and low frequency, a blade database is established, and then the average value f of the natural frequency of the high frequency group blades is calculated h.av , the average value of the natural frequency of the blades in the medium frequency group f m.av and the average natural frequency of the low-frequency blade group f l.av ;

[0019] Step 2: Based on the principle of maximizing the difference in natural frequency between blades, the natural frequency of the blades in the high frequency group is subtracted from the natural frequency of the blades in the low frequency group to obtain the frequency difference. Then, the blades with a frequency difference not less than Δf1 are arranged in the order of low frequency-high frequency-low frequency and placed in the main area. The initial value of Δf1 is calculated according to the following formula:

[0020] Δf1=f h.av -f l.av (2);

[0021] Step 3: Based on the principle of maximizing the natural frequency difference between blades, the natural frequency of the blades in the medium frequency group is subtracted from the natural frequency of the blades in the low frequency group to obtain the frequency difference. Then, the blades with a frequency difference not less than Δf2 are arranged in the order of medium frequency-low frequency-medium frequency and placed in the secondary area. The initial value of Δf2 is calculated according to the following formula:

[0022] Δf2=f m.av -f l.av (3)

[0023] Among them, the blades located at the adjacent boundaries of the primary region and the secondary region also meet the requirement that the frequency difference is not less than Δf2;

[0024] Step 4: Repeat steps 2 and 3 to obtain a preliminary plan for isolating and assembling multiple leaf disk regions and construct an optimized initial population N. P .

[0025] The natural frequency of the blade to be assembled in step 1 conforms to the normal distribution law, and its probability density function is:

[0026]

[0027] In formula (1), μ and σ (σ>0) are constants. To meet the frequency requirements of blade frequency error protection, the blades with f>μ+σ are classified as the high-frequency group, the blades with μ≤f≤μ+σ are classified as the medium-frequency group, and the blades with f<μ are classified as the low-frequency group.

[0028] The fourth step is to revise the preliminary plan for isolating and assembling all blade disk areas, and the revision method includes the following steps:

[0029] Step (1), for the blade disk structure, its unbalance The amount of imbalance caused by each blade When the blade assembly plan is determined, the unbalance is

[0030]

[0031] in, Calculate as follows:

[0032]

[0033] In formula (5), θ i is the angle between the blade mass center and the disc geometric center in the assembled state, r i is the distance between the blade mass center and the disc geometric center in the assembled state, r i Calculate as follows:

[0034] r i =d+d i -x (6),

[0035] In formula (6), d is the radius of the wheel. i is the centroid of the blade, x is the overlap distance between the blade and the disk in the assembled state;

[0036] Step (2), establish the blade disk structure dynamic equation as follows:

[0037]

[0038] In formula (7), [M], [C], and [K] are the mass, damping, and stiffness matrices of the blade disk structure, respectively. [M], [c], and [K] are extracted through the blade disk structure dynamics model established in step 1. {R} is the generalized displacement of the blade disk structure, and {F} is the exciting force of the blade disk structure. When the blade disk structure is subjected to the unbalanced exciting force {F}, it will cause forced vibration. Let the exciting force be

[0039]

[0040] In formula (8), ω is the excitation frequency. Substituting formula (8) into formula (7), the vibration response of the blade under the detuned mode is calculated:

[0041] {R}={R1 R2 … R i … R n} T (9)

[0042] In formula (9), R i is the vibration response of the i-th blade, and the maximum value R of the blade vibration response is extracted i_max Constructing the optimization objective function

[0043] f obj_1 =min(R i_max ) (10);

[0044] Step (3), using the optimization algorithm to optimize and solve equation (10), according to the solution results, the blade arrangement scheme that minimizes the blade vibration response under the detuned mode of the blade disk structure is obtained, based on which the initial values ​​of Δf1 and Δf2 can be corrected. For the blade disk structure whose design state remains unchanged, the corrected Δf1_修 , Δf 2_修 is a constant;

[0045] Step (4), Δf 1_修 Replace Δf1 in step 2 and change Δf 2_修 Replace Δf2 in step 3;

[0046] Step (5), repeat step 2 and step 3 to obtain multiple blade disk area isolation assembly schemes, and construct the optimized correction population N P_修 .

[0047] The equilibrium directional optimization objective function constructed in step 5 is:

[0048]

[0049] In formula (11), a1 and a2 are the upper and lower limits of the unbalance directional optimization area angle, and x i is the weight of each blade set according to the detuned design of the blade disk.

[0050] After step five is completed, the vibration response of each blade under virtual assembly is solved by simulating the blade disk structure dynamics model.

[0051] The maximum value R of the vibration response of each blade in the virtual assembly state i_max To identify, if

[0052] R i_max <R d (12)

[0053] This means that the blade disk area isolation assembly and balance orientation optimization scheme meets the assembly requirements of the blade disk structure. The blade disk structure is assembled according to this scheme. In formula (12), R d is the threshold of blade vibration response.

[0054] The beneficial effects of the present invention are: establishing a blade disk structure dynamics model, and performing detuned modal dynamics analysis on the blade disk structure, dividing the blade disk structure into a main area and a secondary area through detuned design, measuring the mass, center of mass, and natural frequency of the blade to be assembled and establishing a blade database, combining the blade mismatch anti-vibration principle and unbalanced directional optimization technology to provide a blade disk area isolation assembly and balanced directional optimization scheme, and then using virtual assembly simulation technology to verify the vibration response of the scheme, thereby achieving effective control of the actual blade disk structure vibration. After obtaining the blade disk area isolation assembly and balanced directional optimization scheme, the actual assembly of the blade disk structure is carried out, and the process is simple, the workload is small, the efficiency is high, and the vibration control effect is good. DETAILED DESCRIPTION

[0055] The technical solution of the present invention is further described below, but the scope of protection claimed is not limited to the description.

[0056] Since the detuning of the actual blade disk structure of a rotating machinery is real and unavoidable, different blades of the detuned blade disk have different resonant frequencies. The frequency of the blade disk structure is detuned to convert the detuning of the blade disk into an effective measure to suppress blade flutter. To this end, the present invention provides a method for regional isolation assembly and balanced directional optimization of a rotating machinery blade disk based on detuning design, frequency error anti-flutter, unbalanced directional optimization and virtual assembly simulation technology, comprising the following steps:

[0057] S1: According to the nominal dimensions, material parameters and actual working conditions given in the design drawings of the rotating machinery blade disk structure, the blade disk structure dynamics model is established using finite element or dynamics software. Considering the influence of modeling errors and structural nonlinear factors, the blade disk structure characteristic parameters are combined with the model correction during the operation process, and finally a dynamic model that can accurately reflect the characteristics of the blade disk structure is obtained.

[0058] S2: Based on the dynamic model of the blade disk structure, the detuned mode is designed, and the area and number of the blade disk structure vibration energy concentration are set. The main area and the secondary area are divided according to the detuned mode design results. The location of the area is determined according to the detuned mode calculation results, and the area boundary can be determined according to the node connection line or node diameter of the vibration deformation. The main area is the vibration energy concentration area, and the secondary area is the area between the main areas.

[0059] S3: Based on the principle of frequency error prevention, the natural frequency distribution of blades is optimized, that is, by increasing the natural frequency difference between blades, weakening the aeroelastic coupling between blades, improving the aeroelastic stability of the blade vibration system, and suppressing the occurrence of blade flutter. Blades with a large natural frequency difference are installed in the main area to destroy the cyclic symmetry of the blade disk structure, which plays a role in isolating the blade frequency area.

[0060] S4: Measure the mass m of the blade to be assembled i , centroid d i and natural frequency f, and establish a blade database. The blade natural frequency is a random variable, which is divided into three groups: high frequency, medium frequency, and low frequency according to the frequency statistics (the natural frequencies of different blades obey different distribution functions and need to be grouped according to the actual situation). In most cases, the blade natural frequency conforms to the normal distribution law, and its probability density function is

[0061]

[0062] In formula (1), μ and σ (σ>0) are constants. To meet the frequency requirements of blade mismatch and anti-vibration, blades with f>μ+σ are classified as high-frequency groups, and the average natural frequency of the blades in the high-frequency group is calculated. h.av, classify the blades with μ≤f≤μ+σ into the intermediate frequency group, and calculate the average value of the natural frequency of the blades in the intermediate frequency group f m.av , classify the blades with f<μ into the low-frequency group, and calculate the average natural frequency f of the blades in the low-frequency group l.av .

[0063] S5: Based on the principle of maximizing the difference in natural frequency between blades, the natural frequency of the blades in the high frequency group is subtracted from the natural frequency of the blades in the low frequency group to obtain the frequency difference. Then, the blades with a frequency difference not less than Δf1 are arranged in the order of low frequency-high frequency-low frequency and placed in the main area. The initial value of Δf1 is calculated according to the following formula:

[0064] Δf1=f h.av -f l.av (2).

[0065] S6: Based on the principle of maximizing the difference in natural frequency between blades, the natural frequency of the blades in the medium frequency group is subtracted from the natural frequency of the blades in the low frequency group to obtain the frequency difference. Then, the blades with a frequency difference not less than Δf2 are arranged in the order of medium frequency-low frequency-medium frequency and placed in the secondary area. The initial value of Δf2 is calculated according to the following formula:

[0066] Δf2=f m.av -f l.av (3)

[0067] Among them, the blades located at the adjacent boundaries of the primary region and the secondary region also meet the requirement that the frequency difference is not less than Δf2.

[0068] S7: Repeat steps S5 and S6 to obtain a preliminary plan for isolating and assembling multiple leaf disk regions, and construct an optimized initial population N P .

[0069] S8: For the blade disk structure, its unbalance The amount of imbalance caused by each blade When the blade assembly plan is determined, the unbalance is

[0070]

[0071] in, Calculate as follows:

[0072]

[0073] In formula (5), θ i is the angle between the blade mass center and the disc geometric center in the assembled state, r i is the distance between the blade mass center and the disc geometric center in the assembled state, r i Calculate as follows:

[0074] r i =d+d i -x (6),

[0075] In formula (6), d is the radius of the wheel. i is the centroid of the blade, and x is the overlapping distance between the blade and the disk in the assembled state.

[0076] S9: The blade disk structure dynamic equation is established as follows:

[0077]

[0078] In formula (7), [M], [C], and [K] are the mass, damping, and stiffness matrices of the blade disk structure, respectively. [M], [C], and [K] are extracted through the blade disk structure dynamics model established in step 1. {R} is the generalized displacement of the blade disk structure. is the first-order derivative of {R}, is the second-order derivative of {R}, {F} is the exciting force of the blade disk structure. When the blade disk structure is subjected to the unbalanced exciting force {F}, it will cause forced vibration. Let the exciting force be

[0079]

[0080] In formula (8), ω is the excitation frequency. Substituting formula (8) into formula (7), the vibration response of the blade under the detuned mode is calculated:

[0081] {R}={R1 R2 … R i … R n} T (9)

[0082] In formula (9), R i is the vibration response of the i-th blade, and the maximum value R of the blade vibration response is extracted i_max Constructing the optimization objective function

[0083] f obj_1 =min(R i_max ) (10).

[0084] S10: The optimization algorithm is used to optimize and solve equation (10). According to the solution, the blade arrangement scheme that minimizes the blade vibration response under the detuned mode of the blade disk structure is obtained. Based on this scheme, the initial values ​​of Δf1 and Δf2 can be corrected. For the blade disk structure with unchanged design state, the corrected Δf 1_修 , Δf 2_修 is a constant.

[0085] S11: Δf 1_修 Replace Δf1 in step S5, and replace Δf 2_修Replace Δf2 in step S6. That is, based on the blade grouping in step S4, based on the principle of maximizing the natural frequency difference between blades, the natural frequency of the blades in the high frequency group is subtracted from the natural frequency of the blades in the low frequency group to obtain the frequency difference, and then the frequency difference is not less than Δf 1_修 The blades are arranged in the order of low frequency-high frequency-low frequency and placed in the main area; the natural frequency of the blades in the medium frequency group is subtracted from the natural frequency of the blades in the low frequency group to obtain the frequency difference, and then the frequency difference is not less than Δf 2_修 The blades are arranged in the order of medium frequency-low frequency-medium frequency and placed in the secondary area. The blades located at the adjacent boundaries of the main area and the secondary area also meet the frequency difference of not less than Δf 2_修 requirements.

[0086] S12: Repeat steps S5 and S6 to obtain multiple blade disk area isolation assembly schemes and construct an optimized modified population N P_修 That is, calculation and optimization are no longer performed according to formula (2) and formula (3).

[0087] S13: To avoid the aggravation of vibration stress in the main area (blade disk detuning position), the unbalanced amount of the assembly scheme cannot be in the main area. Therefore, the balance optimization goal of the blade disk structure is to adjust the size of the unbalanced amount and the circumferential installation angle of each blade during the blade arrangement process, so that the maximum amplitude of the forced vibration response of the blade disk is minimized, thereby achieving the goal of balanced directional optimization. The balanced directional optimization objective function is constructed as follows:

[0088]

[0089] In formula (11), a1 and a2 are the upper and lower limits of the unbalance directional optimization area angle, and x i is the weight of each blade set according to the detuned design of the blade disk.

[0090] S14: Using the optimization algorithm to solve equation (11) to obtain a solution for isolation assembly and balanced directional optimization of the blade disk area.

[0091] S15: The vibration response of each blade under virtual assembly is solved through the blade disk structural dynamics model simulation.

[0092] S16: Maximum value R of vibration response of each blade in virtual assembly state i_max To identify, if

[0093] R i_max <R d (12)

[0094] This means that the blade disk area isolation assembly and balance orientation optimization scheme meets the assembly requirements of the blade disk structure. The blade disk structure is assembled according to this scheme. In formula (12), R dis the threshold of blade vibration response. d Can be set according to test data.

Claims

1. A method for isolating, assembling and balancing orientation optimization of a rotating machinery blade disk, characterized in that: The following steps are involved: Step 1: Use finite element or dynamics software to establish a blade disk structure dynamics model; Step 2: Design the detuned mode of the blade disk based on the structural dynamics model, divide the area where the vibration energy is concentrated into the main area, and divide the area between the main areas into secondary areas; Step 3: Optimize the natural frequency distribution of blades based on the principle of frequency error prevention, that is, by increasing the natural frequency difference between blades, weakening the aeroelastic coupling between blades, improving the aeroelastic stability of the blade vibration system, and suppressing the occurrence of blade flutter, a preliminary plan for the isolation assembly of multiple blade disk areas is obtained; Step 4: During the blade arrangement process of the preliminary isolation assembly scheme of each blade disk area, the size of the unbalance amount and the circumferential installation angle of each blade are adjusted to minimize the maximum amplitude of the forced vibration response of the blade disk, and multiple isolation assembly schemes of the blade disk area are obtained; Step 5: Construct the balanced directional optimization objective function and use the optimization algorithm to solve it to obtain the solution for the isolation assembly and balanced directional optimization of the blade disk area.

2. The method for isolating, assembling and balancing orientation optimization of a rotary machine blade disk according to claim 1, characterized in that: The method for optimizing the natural frequency distribution law of the blade based on the frequency error anti-vibration principle in step 3 comprises the following steps: Step 1: Measure the mass m of the blade to be assembled i , centroid d i And the natural frequency f, and according to the natural frequency of the blades, the blades are divided into three groups: high frequency, medium frequency and low frequency, a blade database is established, and then the average value f of the natural frequency of the high frequency group blades is calculated h.av , the average value of the natural frequency of the blades in the medium frequency group f m.av and the average natural frequency of the low-frequency blade group f l.av ; Step 2: Based on the principle of maximizing the difference in natural frequency between blades, the natural frequency of the blades in the high frequency group is subtracted from the natural frequency of the blades in the low frequency group to obtain the frequency difference. Then, the blades with a frequency difference not less than Δf1 are arranged in the order of low frequency-high frequency-low frequency and placed in the main area. The initial value of Δf1 is calculated according to the following formula: Δf1=f h.av -f l.av (2); Step 3: Based on the principle of maximizing the natural frequency difference between blades, the natural frequency of the blades in the medium frequency group is subtracted from the natural frequency of the blades in the low frequency group to obtain the frequency difference. Then, the blades with a frequency difference not less than Δf2 are arranged in the order of medium frequency-low frequency-medium frequency and placed in the secondary area. The initial value of Δf2 is calculated according to the following formula: Δf2=f m.av -f l.av (3), Among them, the blades located at the adjacent boundaries of the primary region and the secondary region also meet the requirement that the frequency difference is not less than Δf2; Step 4: Repeat steps 2 and 3 to obtain a preliminary plan for isolating and assembling multiple leaf disk regions and construct an optimized initial population N. P .

3. The method for isolating, assembling and balancing orientation optimization of a rotary machine blade disk according to claim 2, characterized in that: The natural frequency of the blade to be assembled in step 1 conforms to the normal distribution law, and its probability density function is: In formula (1), μ and σ (σ>0) are constants. To meet the frequency requirements of blade frequency error protection, the blades with f>μ+σ are classified as the high-frequency group, the blades with μ≤f≤μ+σ are classified as the medium-frequency group, and the blades with f<μ are classified as the low-frequency group.

4. The method for isolating, assembling and balancing orientation optimization of a rotary machine blade disk according to claim 2, characterized in that: The fourth step is to revise the preliminary plan for isolating and assembling all blade disk areas, and the revision method includes the following steps: Step (1), for the blade disk structure, its unbalance The amount of imbalance caused by each blade When the blade assembly plan is determined, the unbalance is in, Calculate as follows: In formula (5), θ i is the angle between the blade mass center and the disc geometric center in the assembled state, r i is the distance between the blade mass center and the disc geometric center in the assembled state, r i Calculate as follows: r i =d+d i -x (6), In formula (6), d is the radius of the wheel. i is the centroid of the blade, x is the overlap distance between the blade and the disk in the assembled state; Step (2), establish the blade disk structure dynamic equation as follows: In formula (7), [M], [C], and [K] are the mass, damping, and stiffness matrices of the blade disk structure, respectively. [M], [C], and [K] are extracted through the blade disk structure dynamics model established in step 1. {R} is the generalized displacement of the blade disk structure, and {F} is the exciting force of the blade disk structure. When the blade disk structure is subjected to the unbalanced exciting force {F}, it will cause forced vibration. Let the exciting force be In formula (8), ω is the excitation frequency. Substituting formula (8) into formula (7), the vibration response of the blade under the detuned mode is calculated: {R}={R1 R2 … R i … R n } T (9), In formula (9), R i is the vibration response of the i-th blade, and the maximum value R of the blade vibration response is extracted i_max Constructing the optimization objective function f obj_1 =min(R i_max ) (10); Step (3), using the optimization algorithm to optimize and solve equation (10), according to the solution results, the blade arrangement scheme that minimizes the blade vibration response under the detuned mode of the blade disk structure is obtained, based on which the initial values ​​of Δf1 and Δf2 can be corrected. For the blade disk structure whose design state remains unchanged, the corrected Δf 1_修 , Δf 2_修 is a constant; Step (4), Δf 1_修 Replace Δf1 in step 2 and change Δf 2_修 Replace Δf2 in step 3; Step (5), repeat step 2 and step 3 to obtain multiple blade disk area isolation assembly schemes, and construct the optimized correction population N P_修 .

5. The method for isolating, assembling and balancing orientation optimization of a rotary machine blade disk according to claim 1, characterized in that: The equilibrium directional optimization objective function constructed in step 5 is: In formula (11), a1 and a2 are the upper and lower limits of the unbalance directional optimization area angle, and x i is the weight of each blade set according to the detuned design of the blade disk.

6. The method for isolating, assembling and balancing orientation optimization of a rotary machine blade disk according to claim 1, characterized in that: After step five is completed, the vibration response of each blade under virtual assembly is solved by simulating the blade disk structure dynamics model.

7. The method for isolating, assembling and balancing orientation optimization of a rotary machine blade disk according to claim 6, characterized in that: The maximum value R of the vibration response of each blade in the virtual assembly state i_max To identify, if R i_max <R d (12), This means that the blade disk area isolation assembly and balance orientation optimization scheme meets the assembly requirements of the blade disk structure. The blade disk structure is assembled according to this scheme. In formula (12), R d is the threshold of blade vibration response.

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