Method and system for selecting a gas turbine rotor balance weight

Abstract

The application discloses a kind of gas turbine rotor balancing weight matching method and system, it first establishes rotor simplified model, then constructs the balancing weight group distribution map of honeycomb uniform distribution based on rotor simplified model, when matching, only need to obtain the actual initial unbalance of rotor and the included angle between actual initial unbalance and the nearest matching point, then the corresponding honeycomb area can be found from balancing weight group distribution map based on actual initial unbalance and included angle, and each honeycomb area is characterized as a group of balancing weight group combination unbalance meets the coverage area of unbalance requirement, to obtain target balancing weight group, directly using target balancing weight group for assembly can meet the unbalance requirement, can realize the automatic matching of gas turbine rotor balancing weight, compared with the existing multi-iteration matching mode, greatly shorten the matching time, simplify the matching process, and improve the accuracy and reliability of matching.

Description

Technical Field

[0001] This invention relates to the field of aero-engine assembly technology, and in particular, to a method and system for selecting and matching counterweights for a gas turbine rotor. Background Technology

[0002] Before being assembled into the engine, the gas turbine rotor assembly (rotor with blades) of the aero-engine needs to undergo a static balance test. The static imbalance of the rotor is ensured to be less than 5 g·mm by assembling a balancing weight. The initial imbalance of the rotor is about 50 g·mm, and the balancing radius of the balancing weight is 59 mm. Table 1 shows the changes in rotor imbalance caused by different balancing weights, after assembly, and 5° deviation in assembly position.

[0003] Table 1. Balance Weights for First and Second Stage Gas Turbines

[0004]

[0005] As can be seen from Table 1, the rotor structure and the weight of the counterweight present the following problems with the balance requirements:

[0006] 1) The imbalance caused by installing the counterweight (minimum 51.15 mm) and the imbalance caused by replacing the counterweight (the difference between adjacent groups is 15 g.mm and 21 g.mm respectively) are too large relative to the imbalance requirement (5 g.mm);

[0007] 2) The first and second stage turbine rotors of the gas turbine have five evenly distributed balancing weights, spaced 72° apart. The balancing radius of the balancing weights is 59mm. When the balancing weights deviate by 5° from the balancing radius, the minimum unbalance change is 4.8g·mm. The 5° deviation from the 72° spacing of the balancing weights is too large. The deviation in the balancing weight assembly position is illustrated in the diagram below. Figure 1 As shown.

[0008] The two problems mentioned above mean that the initial imbalance of the rotor cannot be balanced in most cases by assembling one or two counterweights. The existing method of selecting counterweights is to install the counterweight closest to the initial imbalance at the counterweight point close to the light point (opposite to the initial imbalance). After multiple iterations, the imbalance is kept up until the requirements are met. However, due to the large weight of the counterweights, the group difference, and the large angle between the assembly points, the balancing process is time-consuming, cumbersome, and sometimes even fails to achieve the required balance. The balancing process often relies on luck to achieve the required balance. Summary of the Invention

[0009] This invention provides a method and system for selecting and matching counterweights for gas turbine rotors, in order to solve the technical problems of long balancing time and complicated process in existing counterweight selection and matching methods.

[0010] According to one aspect of the present invention, a method for selecting and matching counterweights for a gas turbine rotor is provided, comprising the following:

[0011] A simplified rotor model is established based on the rotor's symmetrical structure and the range of its initial unbalance.

[0012] Based on the simplified rotor model, a balanced weight distribution map with a honeycomb-like uniform distribution was constructed.

[0013] Obtain the actual initial imbalance of the rotor and the angle between the actual initial imbalance and the nearest balance point. Based on the actual initial imbalance and the angle, find the target balance assembly from the balance assembly distribution map and assemble it.

[0014] Furthermore, the simplified rotor model is a sector-shaped region with a radius of 100 g.mm and an angle of 36°.

[0015] Furthermore, the process of constructing a honeycomb-shaped uniform distribution map of the equilibrium weight distribution based on the simplified rotor model specifically involves:

[0016] Calculate the initial rotor imbalance when the imbalance of each balanced configuration is 0, and obtain a point distribution diagram of the initial rotor imbalance.

[0017] The simplified rotor model is divided into a honeycomb-shaped, uniformly distributed grid, with the center of each honeycomb cell corresponding to an initial rotor imbalance.

[0018] For the initial unbalance of the rotor corresponding to each cell in the mesh diagram, the combined unbalance under each type of balanced assembly is obtained through iterative calculation. Multiple balanced assembly sets that meet the unbalance requirements are obtained, and the balanced assembly set with the smallest combined unbalance is selected.

[0019] Based on the dot distribution map, and combined with several balanced combination groups with the smallest unbalanced amount selected, a honeycomb-shaped distribution sketch of balanced combination groups is generated.

[0020] The equilibrium compound distribution sketch is homogenized to obtain an equilibrium compound distribution map with a honeycomb-like uniform distribution.

[0021] Furthermore, the process of calculating the initial rotor imbalance corresponding to the combination imbalance being 0 under each balanced configuration is specifically as follows:

[0022] Calculate the unbalance amount for each balanced configuration, and the unbalance amount for any balanced configuration has one and only one initial rotor unbalance amount that cancels each other out, thus obtaining the initial rotor unbalance amount corresponding to the combination unbalance amount being 0 under each balanced configuration.

[0023] Furthermore, the imbalance of each balanced combination is calculated based on the following formula:

[0024] Mx=M1×cos(0°)+M2×cos(-72°)+M3×cos(-144°)+M4×cos(144°)+M5×cos(72°) My=M1×sin(0°)+M2×sin(-72°)+M3×sin(-144°)+M4×sin(144°)+M5×sin(72°)

[0025] Where Mx represents the unbalanced component of the balanced compound in the x-direction, My represents the unbalanced component of the balanced compound in the y-direction, and M1, M2, M3, M4, and M5 represent the magnitude of the unbalanced amount of the first to fifth weight points, respectively.

[0026] Furthermore, the center of each cell in the grid diagram represents the initial imbalance of the rotor, and the radius of the cell represents the required imbalance.

[0027] Furthermore, the process of homogenizing the balanced distribution sketch includes the following:

[0028] Remove the balanced distribution groups that extend beyond the simplified rotor model area in the balanced distribution group sketch. For the blank and uneven areas between adjacent cells, find the corresponding coordinate points in the point distribution map, and use the balanced distribution groups corresponding to the coordinate points to generate new cells for filling or replacement, resulting in a balanced distribution group distribution map that is uniformly distributed in a honeycomb pattern.

[0029] In addition, the present invention also provides a system for selecting and matching counterweights for a gas turbine rotor, employing the selection and matching method described above, including:

[0030] The rotor simplified model building module is used to build a simplified rotor model based on the rotor's symmetrical structure and the range of the rotor's initial unbalance.

[0031] The balance weight diagram construction module is used to construct a honeycomb-shaped, uniformly distributed balance weight distribution diagram based on the simplified rotor model.

[0032] The balancing assembly selection module is used to obtain the actual initial imbalance of the rotor and the angle between the actual initial imbalance and the nearest balancing point. Based on the actual initial imbalance and the angle, the target balancing assembly is found from the balancing assembly distribution map and assembled.

[0033] In addition, the present invention also provides an electronic device, including a processor and a memory, wherein the memory stores a computer program, and the processor executes the steps of the method described above by calling the computer program stored in the memory.

[0034] In addition, the present invention provides a computer-readable storage medium for storing a computer program for selecting and matching balancing weights for a gas turbine rotor, wherein the computer program executes the steps of the method described above when run on a computer.

[0035] The present invention has the following effects:

[0036] The method for selecting and matching counterweights for gas turbine rotors in this invention first establishes a simplified rotor model based on the rotor's symmetrical structure and the range of its initial imbalance. The simplified model's area occupies only one-tenth of the rotor model, significantly reducing subsequent computational load. Then, based on the simplified rotor model, a honeycomb-shaped, uniformly distributed counterweight distribution map is constructed. During selection, only the actual initial imbalance of the rotor and the angle between the actual initial imbalance and the nearest counterweight point need to be obtained. The corresponding honeycomb region can then be found from the counterweight distribution map based on the actual initial imbalance and the angle. Each honeycomb region represents the coverage area where the combined imbalance of a set of counterweights meets the imbalance requirements, thus obtaining the target counterweight set. Directly using the target counterweight set for assembly satisfies the imbalance requirements, enabling automated selection and matching of gas turbine rotor counterweights. Compared to existing multi-round iterative selection methods, this significantly shortens the balancing time, simplifies the balancing process, and improves the accuracy and reliability of balancing.

[0037] In addition, the gas turbine rotor balancing counterweight selection system of the present invention also has the above-mentioned advantages.

[0038] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0039] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0040] Figure 1 This is a schematic diagram showing the deviation of the balancing counterweight assembly position in this invention.

[0041] Figure 2 This is a flowchart illustrating the method for selecting and matching the counterweights of a gas turbine rotor according to a preferred embodiment of the present invention.

[0042] Figure 3 This is a schematic diagram of the first and second stage rotors of the gas turbine in this invention.

[0043] Figure 4This is a schematic diagram of a simplified rotor model according to a preferred embodiment of the present invention.

[0044] Figure 5 This is a schematic diagram of the rotor weight points in a preferred embodiment of the present invention, numbered sequentially in the forward direction.

[0045] Figure 6 This is a schematic diagram of the rotor weight points in a preferred embodiment of the present invention, numbered sequentially in a counterclockwise direction.

[0046] Figure 7 yes Figure 2 A schematic diagram of the sub-process of step S2.

[0047] Figure 8 This is a schematic diagram illustrating the principle of calculating the unbalance amount of each balanced combination in a preferred embodiment of the present invention.

[0048] Figure 9 This is a schematic diagram illustrating the principle of using a balancing and matching unit to balance the initial imbalance of the rotor in a preferred embodiment of the present invention.

[0049] Figure 10 This is a schematic diagram illustrating the principle of a honeycomb-shaped uniform distribution of the balanced compound in a preferred embodiment of the present invention.

[0050] Figure 11 This is a schematic diagram of the point distribution of the initial rotor imbalance in a preferred embodiment of the present invention.

[0051] Figure 12 This is a schematic diagram of dividing the region of the simplified rotor model into a honeycomb-shaped uniformly distributed grid in a preferred embodiment of the present invention.

[0052] Figure 13 This is a schematic diagram of the balanced compound distribution sketch of a preferred embodiment of the present invention.

[0053] Figure 14 This is a schematic diagram of the balance weight diagram of the first stage rotor of the gas turbine according to a preferred embodiment of the present invention.

[0054] Figure 15 This is a schematic diagram of the balance weight diagram of the second stage rotor of the gas turbine according to a preferred embodiment of the present invention.

[0055] Figure 16 This is a schematic diagram of finding the corresponding target weight from the balance weight diagram based on the initial unbalance of the first stage rotor of the gas turbine (94, 6°) in a preferred embodiment of the present invention.

[0056] Figure 17 This is the preferred embodiment of the present invention. Figure 16 A schematic diagram of the unbalance of the selected recombinant mix after balancing.

[0057] Figure 18This is a schematic diagram of the module structure of the optional system for the counterweight of the gas turbine rotor according to another embodiment of the present invention. Detailed Implementation

[0058] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0059] Understandable, such as Figure 2 As shown, a preferred embodiment of the present invention provides a method for selecting a counterweight for a gas turbine rotor, comprising the following:

[0060] Step S1: Establish a simplified rotor model based on the rotor's symmetrical structure and the range of its initial unbalance.

[0061] Step S2: Construct a balanced weight distribution map with a honeycomb-like uniform distribution based on the simplified rotor model;

[0062] Step S3: Obtain the actual initial imbalance of the rotor and the angle between the actual initial imbalance and the nearest balance point. Based on the actual initial imbalance and the angle, find the target balance assembly from the balance assembly distribution map and assemble it.

[0063] It is understood that the method for selecting and matching the balancing weights of the gas turbine rotor in this embodiment first establishes a simplified rotor model based on the rotor's symmetrical structure and the range of its initial imbalance. The simplified rotor model occupies only one-tenth of the rotor model, greatly reducing the subsequent computational load. Then, based on the simplified rotor model, a honeycomb-shaped uniform distribution map of the balancing weights is constructed. During the selection and matching process, it is only necessary to obtain the actual initial imbalance of the rotor and the angle between the actual initial imbalance and the nearest balancing point. Based on the actual initial imbalance and the angle, the corresponding honeycomb region can be found from the distribution map of the balancing weights. Each honeycomb region represents the coverage area where the combined imbalance of a set of balancing weights meets the imbalance requirements, thus obtaining the target balancing weight set. The target balancing weight set can be directly used for assembly to meet the imbalance requirements, realizing automated selection and matching of the balancing weights of the gas turbine rotor. Compared with the existing multi-round iterative selection and matching method, this greatly shortens the balancing time, simplifies the balancing process, and improves the accuracy and reliability of balancing.

[0064] It is understood that in step S1, as Figure 3 As shown, the first and second stage rotors of the gas turbine have five circumferentially distributed balancing points. The fan-shaped regions between adjacent balancing points are cyclically symmetrical, and each fan-shaped region is also an axisymmetric image, for example... Figure 3Regions A and B in the model are axially symmetrical. Therefore, one-tenth of the rotor model's circumference is extracted as the simplified rotor model, for example, region B. Furthermore, considering that the initial rotor imbalance is typically 50 g·mm, this invention sets the initial rotor imbalance range to 0–100 g·mm. Of course, in other embodiments of this invention, the initial rotor imbalance range can also be set to 0–110 g·mm, 0–120 g·mm, etc. Therefore, the simplified rotor model is a fan-shaped region with a radius of 100 g·mm and an angle of 36°, as shown in the schematic diagram below. Figure 4 As shown. Optionally, since subsequent calculations are needed to ensure that all balancing units that can achieve acceptable initial imbalance within the entire sector area are properly balanced, a rectangular area can be formed by expanding outwards from the sector area based on the required imbalance value (5 g·mm) as the subsequent calculation range. The rectangular area has a value range of (-5, 105) g·mm in the x-direction and (-5, 65) g·mm in the y-direction. The upper limit of 65 in the y-direction is determined by the following formula: 100 × sin36° + 5 = 63.8 ≈ 65. Furthermore, to distinguish the five balancing points, the direction of the rotor's initial imbalance is designated as position 0, and the balancing point closest to position 0 is designated as position 1. Positions 2, 3, 4, and 5 are sequentially ordered according to this rotation direction. Position 1 is set to 0°, position 2 to -72°, position 3 to -144°, position 4 to 144°, and position 5 to 72°, as detailed below. Figure 5 and Figure 6 As shown. Therefore, the horizontal coordinate of the sector region of the simplified rotor model represents the initial rotor imbalance, and the angle represents the angle α between the initial rotor imbalance and position 1. Each initial rotor imbalance can be represented by (g, α) in the sector region, where g represents the value of the initial rotor imbalance.

[0065] Understandable, such as Figure 7 As shown in step S2, the process of constructing a honeycomb-shaped uniform distribution map of the equilibrium weight distribution based on the simplified rotor model specifically involves:

[0066] Step S21: Calculate the initial rotor imbalance when the unbalance of each balanced combination is 0, and obtain the point distribution diagram of the initial rotor imbalance.

[0067] Step S22: Divide the region of the simplified rotor model into a uniformly distributed honeycomb grid, with the center of each honeycomb cell corresponding to an initial rotor imbalance.

[0068] Step S23: For the initial unbalance of the rotor corresponding to each cell in the grid diagram, the combined unbalance under each type of balanced assembly is obtained by iterative calculation, and multiple balanced assembly sets that meet the unbalance requirements are obtained. The balanced assembly set with the smallest combined unbalance is then selected.

[0069] Step S24: Based on the dot distribution map, combine the selected balanced combination with the smallest imbalance amount to generate a honeycomb-shaped balanced combination distribution sketch.

[0070] Step S25: Homogenize the equilibrium compound distribution sketch to obtain a uniformly distributed equilibrium compound distribution map with a honeycomb pattern.

[0071] It can be understood that the principle of static balancing of a gas turbine rotor is to perform correction balancing on a correction plane of the rotor, ensuring that the combined unbalance after balancing is within the required unbalance range (i.e., 0-5 g·mm). In practice, this means using the unbalance M of the balancing assembly to offset the initial unbalance G of the rotor. For example... Figure 8 As shown, the unbalance M(x, y) for each balanced combination can be calculated based on the following formula:

[0072] Mx=M1×cos(0°)+M2×cos(-72°)+M3×cos(-144°)+M4×cos(144°)+M5×cos(72°)My=M1×sin(0°)+M2×sin(-72°)+M3×sin(-144°)+M4×sin(144°)+M5×sin(72°) Formula (1)

[0073] Where Mx represents the unbalance component of the balancing unit in the x-direction, My represents the unbalance component of the balancing unit in the y-direction, and M1, M2, M3, M4, and M5 represent the magnitudes of the unbalance at balance points one through five, respectively. The x-direction refers to the direction of position 1, while the y-direction is perpendicular to the x-direction and points upwards. Furthermore, the unbalance M of any balancing unit is mutually canceled by one and only one initial rotor unbalance G, i.e., the combined unbalance L = M + G = 0. According to... Figure 9 It can be seen that when the initial unbalance of the rotor is G+R (R must be less than 5 g·mm), the combined unbalance of the rotor is L = G+M+R. Since G+M = 0, L = R, meaning the combined unbalance of the rotor is less than 5 g·mm, satisfying the unbalance requirement. Therefore, each balancing combination can ensure that the initial unbalance in a region is properly balanced. Figure 9 The balancing region in the diagram. Therefore, theoretically, a portion of the balanced balancing groups M1, M2, M3, ..., Mn, which are uniformly distributed in a honeycomb pattern, can be selected, such as... Figure 10As shown, (-M1+R), (-M2+R), (-M3+R), ..., (-Mn+R) can cover the region where the initial imbalance G is located, so that any initial imbalance can be balanced by one of the balancing combinations M1, M2, M3, ..., Mn. However, in practice, it is not possible to directly find M1, M2, M3, ..., Mn that are uniformly distributed in a honeycomb pattern. Therefore, this invention first finds a distribution map of the rotor's initial imbalance that is uniformly distributed in a honeycomb pattern, then calculates the balancing combination that minimizes the combined imbalance after combining with each initial imbalance, thus obtaining a roughly uniformly distributed balancing combination distribution sketch. The balancing combination distribution sketch is then homogenized to improve uniformity, resulting in a uniformly distributed balancing combination distribution map in a honeycomb pattern.

[0074] Specifically, in step S21, the unbalance amount M of each balanced combination is first calculated based on formula (1). The unbalance amount M of any balanced combination has one and only one unique initial rotor unbalance amount G that cancels each other out, thus obtaining the initial rotor unbalance amount G = -M when the combined unbalance amount under each balanced combination is 0. This yields several initial rotor unbalance amounts. Then, based on the magnitude g of each initial rotor unbalance amount and the angle α between it and position 1, it is added to the area of ​​the simplified rotor model to form a point distribution map of the initial rotor unbalance amount. The specific calculation process can be automatically executed by an Excel VBA program. For example, by creating a new Excel file and naming two tables [Data Input Area 1] and [CAD Coordinate Area], the data of each counterweight is entered in table [Data Input Area 1] using the counterweight CAD coordinate program of Excel VBA. After automatic calculation, the program will output the initial unbalance amount data corresponding to each balanced combination in table [CAD Coordinate Area], as shown in Table 2. Then, the CAD system will automatically draw a diagram based on the initial imbalance data in the [CAD coordinate area] table, converting the coordinates of the initial imbalance data into a dotted circle with a radius of 0.1, thus forming a dotted distribution diagram of the rotor's initial imbalance, as shown below. Figure 11 As shown. Furthermore, Excel VBA is existing mature commercial software, and the specific working principles of its various programs are existing technologies, which will not be elaborated upon in this invention.

[0075] Table 2. Initial Imbalance Quantity for Each Balanced Combination Recombination

[0076]

[0077] In step S22, the present invention divides the region of the simplified rotor model into a uniformly distributed honeycomb grid. The center point of each honeycomb cell corresponds to an initial imbalance, and the radius of the honeycomb cell is the required imbalance value (generally 5 g·mm). The honeycomb distribution pattern is adopted because the honeycomb structure has high utilization and can minimize the number of selected balancing units, thus reducing the amount of calculation. Optionally, the radius of the honeycomb cell can also be set to 4 g·mm, leaving a 1 g·mm margin. This is to account for the difficulty in obtaining a perfectly uniformly distributed honeycomb structure and to account for other errors in practical applications. Furthermore, the process of dividing the region of the simplified rotor model into a uniformly distributed honeycomb grid is specifically implemented using an Excel VBA mesh generation program. For example, the mesh generation program obtains Table 3 by using methods such as single / double column division, symmetry, and datum transformation. Then, circles are drawn with each data point in Table 3 as the center and a radius of 4 g·mm to obtain a uniformly distributed honeycomb grid. Figure 12 As shown. In addition, the initial imbalance corresponding to the center point of each cell may not be the same as the initial imbalance calculated in step S21, that is, the data points in Table 3 do not come from Table 2.

[0078] Table 3. Initial Imbalance Table for Uniform Distribution

[0079]

[0080] In step S23, for Figure 12 The initial rotor imbalance G corresponding to each cell cell is calculated using an Excel VBA program through a loop to obtain the combined imbalance L under each balanced arrangement, where L = G + M. Multiple balanced arrangements with a combined imbalance L less than 5 g·mm are obtained. The balanced arrangement with the smallest combined imbalance L is then selected using an Excel VBA data filtering program and the data is stored in the [data output area].

[0081] In step S24, based on the point distribution map obtained in step S21, the corresponding target point is found according to the selected balanced combination with the smallest unbalance amount. A circle is drawn with the target point as the center and a radius of 4 g·mm, thereby generating a honeycomb-shaped balanced combination distribution sketch, as shown below. Figure 13 As shown in Table 4, the specific drawing process is implemented using the Excel VBA program for calculating CAD coordinates. This program can automatically process data coordinates in batches and convert them into code for drawing a circle with a radius of 4, as shown in Table 4. Then, based on the converted circle drawing code, a honeycomb-shaped balanced distribution sketch is generated on the point distribution map obtained in step S21.

[0082] Table 4. Initial imbalance and circle drawing code for the balanced combination with the minimum combined imbalance.

[0083]

[0084]

[0085] It is understandable that, for the initial imbalance amount corresponding to each cell in step S22, there may not actually be a balanced weight combination that makes the combined imbalance amount L exactly 0. Therefore, the screening mechanism in step S23 is to select the balanced weight combination closest to the initial imbalance amount G. Thus, the resulting balanced weight distribution sketch is not uniformly distributed, and there may be blank areas and uneven areas between adjacent cell regions. Therefore, it is necessary to homogenize the balanced weight distribution sketch to improve its uniformity. Specifically, in step S25, balanced weight combinations that exceed the simplified rotor model area in the balanced weight distribution sketch are removed. For blank areas and uneven areas between adjacent cells, the coordinate points corresponding to the blank areas and uneven areas are found in the point distribution map, and new cell regions are generated using the balanced weight combinations corresponding to the coordinate points to fill or replace them, resulting in a balanced weight distribution map with a uniform honeycomb distribution. Then, information such as the weight number, weight type, and weight numbering rules corresponding to each balanced weight combination are added to the balanced weight distribution map to obtain a balanced weight map. The balanced weight maps for the first and second stage rotors of the gas turbine are as follows: Figure 14 and Figure 15 As shown.

[0086] It can be understood that in step S3, the initial imbalance g of the rotor and the angle α (α < 36°) between the initial imbalance and the nearest counterweight are obtained from the balancing machine. Then, based on (g, α), the corresponding target balancing weight is found in the balancing weight diagram. Then, assembly is performed according to the numbering rules of the counterweights and the target balancing weight, i.e., the balancing is qualified. For example, taking the initial imbalance (94, 6°) of the first-stage rotor of the gas turbine as an example, the corresponding counterweight is found to be 72523 in the balancing weight diagram. Figure 16 As shown, position 1 is unloaded, position 2 is loaded with the second set of counterweights, position 3 is loaded with the fifth set of counterweights, position 4 is loaded with the second set of counterweights, and position 5 is loaded with the third set of counterweights. The unbalance of the balanced assembly is 0.5911 g·mm. Figure 17 As stated above.

[0087] It is understandable that when searching for a balanced distribution group based on the actual initial imbalance, a single initial imbalance may be contained within multiple cell regions. Theoretically, selecting any one of these cell regions and its corresponding balanced distribution group will result in a satisfactory balance. Optionally, this invention selects the cell region whose center is closest to the point where the actual initial imbalance is located. The combined imbalance after balancing based on the distribution group corresponding to this cell region is minimized.

[0088] In addition, such as Figure 18 As shown, another embodiment of the invention also provides a system for selecting the counterweight of a gas turbine rotor, preferably employing the selection method described above, including:

[0089] The rotor simplified model building module is used to build a simplified rotor model based on the rotor's symmetrical structure and the range of the rotor's initial unbalance.

[0090] The balance weight diagram construction module is used to construct a honeycomb-shaped, uniformly distributed balance weight distribution diagram based on the simplified rotor model.

[0091] The balancing assembly selection module is used to obtain the actual initial imbalance of the rotor and the angle between the actual initial imbalance and the nearest balancing point. Based on the actual initial imbalance and the angle, the target balancing assembly is found from the balancing assembly distribution map and assembled.

[0092] It is understood that the gas turbine rotor balancing counterweight selection system of this embodiment first establishes a simplified rotor model based on the rotor's symmetrical structure and the range of its initial imbalance. The simplified rotor model's area occupies only one-tenth of the rotor model, greatly reducing the subsequent computational load. Then, based on the simplified rotor model, a honeycomb-shaped uniform distribution map of balancing counterweights is constructed. During selection, it is only necessary to obtain the rotor's actual initial imbalance and the angle between the actual initial imbalance and the nearest counterweight point. Based on the actual initial imbalance and the angle, the corresponding honeycomb region can be found from the balancing counterweight distribution map. Each honeycomb region represents the coverage area where the combined imbalance under a set of balancing counterweights meets the imbalance requirements, thus obtaining the target balancing counterweight. Directly using the target balancing counterweight for assembly can meet the imbalance requirements, realizing automated selection of gas turbine rotor balancing counterweights. Compared with the existing multi-round iterative selection method, this greatly shortens the balancing time, simplifies the balancing process, and improves the accuracy and reliability of balancing.

[0093] In addition, another embodiment of the present invention provides an electronic device including a processor and a memory, wherein the memory stores a computer program, and the processor executes the steps of the method described above by calling the computer program stored in the memory.

[0094] In addition, another embodiment of the present invention provides a computer-readable storage medium for storing a computer program for selecting and matching balancing weights for a gas turbine rotor, wherein the computer program executes the steps of the method described above when run on a computer.

[0095] Common computer-readable storage media include: floppy disks, flexible disks, hard disks, magnetic tapes, any other magnetic media, CD-ROMs, any other optical media, punch cards, paper tape, any other physical media with perforated patterns, random access memory (RAM), programmable read-only memory (PROM), erasable programmable read-only memory (EPROM), flash erasable programmable read-only memory (FLASH-EPROM), any other memory chips or cartridges, or any other media readable by a computer. Instructions may further be transmitted or received by a transmission medium. The term transmission medium can include any tangible or intangible medium used to store, encode, or carry instructions for machine execution, and includes digital or analog communication signals or intangible media that facilitate communication of such instructions. Transmission media include coaxial cables, copper wires, and optical fibers, which contain conductors for transmitting a bus of computer data signals.

[0096] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

[0097] Those skilled in the art will understand that embodiments of this application can be provided as methods, systems, or computer program products. Therefore, this application can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this application can take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code. The solutions in the embodiments of this application can be implemented in various computer languages, such as the object-oriented programming language Java and the interpreted scripting language JavaScript.

[0098] This application is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of this application. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart... Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0099] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0100] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0101] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application.

[0102] Obviously, those skilled in the art can make various modifications and variations to this application without departing from the spirit and scope of this application. Therefore, if such modifications and variations fall within the scope of the claims of this application and their equivalents, this application also intends to include such modifications and variations.

Claims

1. A method of selecting a balance weight for a gas turbine rotor, characterized by, Includes the following: A simplified rotor model is established based on the rotor's symmetrical structure and the range of its initial unbalance. Based on the simplified rotor model, a balanced weight distribution map with a honeycomb-like uniform distribution was constructed. Obtain the actual initial imbalance of the rotor and the angle between the actual initial imbalance and the nearest balance point. Based on the actual initial imbalance and the angle, find the target balance assembly from the balance assembly distribution map and assemble it. The process of constructing a honeycomb-shaped uniform distribution map of the equilibrium weight distribution based on the simplified rotor model is as follows: Calculate the initial rotor imbalance when the imbalance of each balanced configuration is 0, and obtain a point distribution diagram of the initial rotor imbalance. The simplified rotor model is divided into a honeycomb-shaped, uniformly distributed grid, with the center of each honeycomb cell corresponding to an initial rotor imbalance. For the initial unbalance of the rotor corresponding to each cell in the mesh diagram, the combined unbalance under each type of balanced assembly is obtained through iterative calculation. Multiple balanced assembly sets that meet the unbalance requirements are obtained, and the balanced assembly set with the smallest combined unbalance is selected. Based on the dot distribution map, and combined with several balanced combination groups with the smallest unbalanced amount selected, a honeycomb-shaped distribution sketch of balanced combination groups is generated. The equilibrium compound distribution sketch is homogenized to obtain an equilibrium compound distribution map with a honeycomb-like uniform distribution.

2. The method of matching a gas turbine rotor balance weight of claim 1, wherein, The simplified rotor model is a sector-shaped region with a radius of 100 g.mm and an angle of 36°.

3. The method for selecting and matching the counterweights for a gas turbine rotor as described in claim 1, characterized in that, The process of calculating the initial rotor imbalance when the imbalance of each balanced configuration is 0 is as follows: Calculate the unbalance amount for each balanced configuration, and the unbalance amount for any balanced configuration has one and only one initial rotor unbalance amount that cancels each other out, thus obtaining the initial rotor unbalance amount corresponding to the combination unbalance amount being 0 under each balanced configuration.

4. The method for selecting and matching the counterweights for a gas turbine rotor as described in claim 3, characterized in that, The imbalance amount of each balanced combination is calculated based on the following formula: ； Where Mx represents the unbalanced component of the balanced compound in the x-direction, My represents the unbalanced component of the balanced compound in the y-direction, and M1, M2, M3, M4, and M5 represent the magnitude of the unbalanced amount of the first to fifth weight points, respectively.

5. The method for selecting and matching the counterweights for a gas turbine rotor as described in claim 1, characterized in that, The center of each cell in the grid diagram represents the initial imbalance of the rotor, and the radius of the cell represents the required imbalance.

6. The method for selecting and matching the counterweights for a gas turbine rotor as described in claim 1, characterized in that, The process of homogenizing the balanced weight distribution sketch includes the following: Remove the balanced distribution groups that extend beyond the simplified rotor model area in the balanced distribution group sketch. For the blank and uneven areas between adjacent cells, find the corresponding coordinate points in the point distribution map, and use the balanced distribution groups corresponding to the coordinate points to generate new cells for filling or replacement, resulting in a balanced distribution group distribution map that is uniformly distributed in a honeycomb pattern.

7. A system for selecting and matching counterweights for a gas turbine rotor, employing the selection and matching method as described in any one of claims 1 to 6, characterized in that, include: The rotor simplified model building module is used to build a simplified rotor model based on the rotor's symmetrical structure and the range of the rotor's initial unbalance. The balance weight diagram construction module is used to construct a honeycomb-shaped, uniformly distributed balance weight distribution diagram based on the simplified rotor model. The balancing assembly selection module is used to obtain the actual initial imbalance of the rotor and the angle between the actual initial imbalance and the nearest balancing point. Based on the actual initial imbalance and the angle, the target balancing assembly is found from the balancing assembly distribution map and assembled.

8. An electronic device, characterized in that, The method includes a processor and a memory, wherein the memory stores a computer program, and the processor executes the steps of the method as described in any one of claims 1 to 6 by calling the computer program stored in the memory.

9. A computer-readable storage medium for storing a computer program for selecting and matching balancing weights for a gas turbine rotor, characterized in that, The computer program, when run on a computer, performs the steps of the method as described in any one of claims 1 to 6.

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