A turbine hollow blade modeling method and system based on multi-blade surveying data

Abstract

The application discloses a kind of based on multi-blade surveying data's turbine hollow blade modeling method and system, method includes: in same type gas turbine turbine, select same row multiple blades;Performance parameter measurement is carried out to selected same row multiple blades, select the blade of key parameter in performance parameter as standard blade;Same row multiple blades are scanned and surveyed, obtain the surveying data of multiple blades, and based on the surveying data of standard blade, establish the geometric model of standard blade;The surveying data of same row multiple blades after alignment processing is compared and analyzed with the geometric model of standard blade, and the geometric model of standard blade is necessary by comparison and analysis result Structure fine tuning.It is moderate that the performance parameter of standard blade geometric model established by the method disclosed by the application, can same row multiple blades processing tolerance range, provide data support for turbine hollow blade structure size tolerance evaluation, obtain higher precision turbine hollow blade structure.

Description

Technical Field

[0001] This invention relates to the field of model design technology, specifically to a method and system for modeling hollow turbine blades based on multi-blade mapping data. Background Technology

[0002] Turbine blades are one of the key core components of gas turbines. They are precision cast from high-temperature alloys and have extremely complex internal cooling channels and surface film cooling holes. The blade surface is coated. Their design and manufacturing are quite difficult. They are the most prominent component in the long-term service and maintenance of heavy-duty gas turbines in China. Achieving the localization of turbine blades has huge economic and social benefits.

[0003] Due to unavoidable errors in the blade manufacturing process, the structural dimensions of blades exhibit a degree of randomness. The blade geometric model generated from the mapping data of a single blade will deviate from the theoretical blade profile. With the accumulation of manufacturing errors, there is a risk of critical structural dimensions of the blade exceeding tolerances, affecting the safe and reliable operation of the blade.

[0004] Currently, the multi-blade profile mean processing method is used for reverse modeling. That is, a unified blade measurement coordinate system is established through the outer tenon teeth, multiple (2 to 5) blades in the same row are scanned and mapped, all the original data of the same section of all blades are averaged to obtain a mean profile, and a three-dimensional solid model of the average blade profile is realized using three-dimensional modeling software.

[0005] Turbine cooling blades are made using investment casting, and their internal hollow channels are formed using ceramic cores. During the blade casting process, the positioning and deformation of the ceramic core directly affect the dimensions of the internal cooling structure of the blade. This results in differences in the offset and deformation of the internal cooling structure relative to the blade's outer tenon teeth among blades produced by different manufacturers or different batches of blades from the same manufacturer. In such cases, the reverse modeling method using the multi-blade profile averaging method does not consider the relative displacement between the internal cooling structure and the blade's outer tenon teeth. The averaging of the mapping data of the internal cooling structure at different relative displacement positions results in low accuracy of the average profile. Summary of the Invention

[0006] Therefore, in order to solve the unreasonable problems existing in the modeling of hollow turbine blades, this invention provides a method and system for modeling hollow turbine blades based on multi-blade mapping data, which provides data support for the evaluation of the structural dimensional tolerances of hollow turbine blades, thereby obtaining a high-precision hollow turbine blade structure.

[0007] To achieve the above objectives, the present invention provides the following technical solution:

[0008] In a first aspect, embodiments of the present invention provide a method for modeling hollow turbine blades based on multi-blade mapping data, comprising: selecting multiple blades in the same row on a gas turbine of the same type;

[0009] The performance parameters of multiple blades in the same row were measured, and the blade with moderate key performance parameters was selected as the standard blade.

[0010] Multiple blades in the same row are scanned and mapped to obtain mapping data of multiple blades, and a geometric model of the standard blade is established based on the mapping data of the standard blade.

[0011] The geometric model of the standard blade is compared and analyzed with the mapping data of multiple blades in the same row after alignment. Based on the comparison and analysis results, the geometric model of the standard blade is finely adjusted as necessary.

[0012] Furthermore, the sources of the selected multiple blades in the same row include at least one of the following: blades from the same batch from the same blade manufacturer, blades from different batches from the same blade manufacturer, and blades produced by different blade manufacturers.

[0013] Furthermore, performance parameters of the selected multiple blades in the same row were measured, including: weight measurement, weight moment measurement, flow rate test, vibration characteristic measurement, and key structural dimension measurement.

[0014] Furthermore, select blades with appropriate key performance parameters, including at least one of the following: blades with appropriate weight among multiple blades in the same row, or blades with appropriate weight moment, or blades with appropriate blade cooling airflow characteristics, or blades with appropriate vibration characteristics, or blades with appropriate structural dimensions of key parts.

[0015] Furthermore, the process of establishing a standard blade geometric model includes:

[0016] For single-source mapping data, a geometric model of the standard blade is established based on the single-source mapping data of the standard blade.

[0017] For multi-source mapping data, select the mapping data with the largest or most complete blade structure information from the multi-source mapping data of the standard blade to establish the initial geometric model of the standard blade; refine the initial geometric model of the standard blade based on the mapping data of other sources of the standard blade to establish the geometric model of the standard blade.

[0018] Furthermore, the hollow turbine blade includes: an external profile and an internal cooling structure. The process of comparing and analyzing the geometric model of the standard blade with the mapping data of multiple blades in the same row after alignment to determine whether the geometric model of the standard blade needs structural fine-tuning includes:

[0019] Align the source mapping data of the blade's external profile or internal cooling structure, and extract the characteristic parameters of the external profile or internal cooling structure of multiple blades in the same row. If the characteristic parameters of the standard blade's external profile or internal cooling structure are close to the average value of the characteristic parameters of multiple blades in the same row, the geometric model of the blade's external profile or internal cooling structure does not need to be structurally adjusted. If the characteristic parameters of the standard blade's external profile or internal cooling structure are close to the extreme values ​​of the characteristic parameters of multiple blades in the same row, the geometric model of the blade's external profile or internal cooling structure is finely adjusted.

[0020] Furthermore, different standard blades are selected according to different parts of the blade, and geometric models of different parts of multiple standard blades are established and assembled to form a complete geometric model of a standard blade.

[0021] Secondly, embodiments of the present invention provide a turbine hollow blade modeling system based on multi-blade mapping data, comprising:

[0022] The blade selection module is used to select multiple blades in the same row from gas turbines of the same model.

[0023] The standard blade selection module is used to measure the performance parameters of multiple selected blades in the same row and select the blade with appropriate key performance parameters as the standard blade.

[0024] The standard blade geometric model establishment module is used to scan and map multiple blades in the same row, obtain the mapping data of multiple blades, and establish the geometric model of the standard blade based on the mapping data of the standard blade.

[0025] The machining tolerance range acquisition module is used to compare and analyze the geometric model of the standard blade and the mapping data of multiple blades in the same row after alignment. Based on the comparison and analysis results, the geometric model of the standard blade is finely adjusted as necessary.

[0026] Thirdly, embodiments of the present invention provide a computer device, including: at least one processor, and a memory communicatively connected to the at least one processor, wherein the memory stores instructions executable by the at least one processor, the instructions being executed by the at least one processor to cause the at least one processor to execute the turbine hollow blade modeling method based on multi-blade mapping data according to the first aspect of the present invention.

[0027] Fourthly, embodiments of the present invention provide a computer-readable storage medium storing computer instructions for causing a computer to execute the turbine hollow blade modeling method based on multi-blade mapping data according to the first aspect of the present invention.

[0028] The technical solution of this invention has the following advantages:

[0029] This invention provides a method and system for modeling hollow turbine blades based on multi-blade mapping data. The method involves selecting multiple blades in the same row from a gas turbine of the same type; measuring the performance parameters of the selected blades; choosing a blade with suitable key performance parameters as a standard blade; scanning and mapping the blades to obtain their mapping data; and establishing a geometric model of the standard blade based on the standard blade's mapping data. The geometric model of the standard blade is then compared and analyzed with the aligned mapping data of the multiple blades in the same row. Based on the comparison and analysis results, necessary structural fine-tuning is performed on the geometric model of the standard blade. The standard blade geometric model established by the method proposed in this invention has suitable performance parameters, allowing for the determination of the machining tolerance range of the multiple blades in the same row, thus providing data support for the evaluation of dimensional tolerances in the hollow turbine blade structure. Attached Figure Description

[0030] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0031] Figure 1 A flowchart illustrating a specific example of a turbine hollow blade modeling method based on multi-blade mapping data provided in an embodiment of the present invention;

[0032] Figure 2 This is a module composition diagram of an example of a turbine hollow blade modeling system based on multi-blade mapping data provided in an embodiment of the present invention;

[0033] Figure 3 This is a composition diagram of a specific example of a computer device provided in an embodiment of the present invention. Detailed Implementation

[0034] The technical solution of the present invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0035] Furthermore, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0036] Example 1

[0037] This invention provides a method for modeling hollow turbine blades based on multi-blade mapping data, such as... Figure 1 As shown, the method includes the following steps:

[0038] Step S1: Select multiple blades in the same row from the same type of gas turbine.

[0039] The sources of the multiple blades selected in the same row in this embodiment of the invention include at least one of the following: blades from the same batch from the same blade manufacturer, blades from different batches from the same blade manufacturer, and blades from different blade manufacturers. Because blades from the same batch from the same blade manufacturer have narrow manufacturing tolerances, while blades from different manufacturers or different batches have wider manufacturing tolerances, blades from different manufacturers or different batches are prioritized when selecting blades to comprehensively understand their manufacturing tolerance range. The more blades of the same type there are, the more accurate and reliable the geometric model constructed using the method provided by this invention will be.

[0040] Step S2: Measure the performance parameters of the selected multiple blades in the same row, and select the blade with appropriate key performance parameters as the standard blade.

[0041] In this embodiment of the invention, blade performance parameters are measured for multiple blades in the same row, including blade weight measurement, moment of mass measurement, flow rate test, vibration characteristic measurement, and key structural dimension measurement. This yields the weight, moment of mass, cooling air flow characteristics, vibration characteristics, and structural dimensions of key components of the multiple blades in the same row. Key parameters are selected from the measured performance parameters based on blade design experience and usage requirements, focusing on parameters that significantly influence blade performance.

[0042] The number of key parameters can be one or more. A standard blade is a blade with suitable key parameters selected from multiple blades in the same row. These include blades with suitable weight, blades with suitable moment of weight, blades with suitable airflow characteristics for cooling, blades with suitable vibration characteristics, blades with suitable structural dimensions for key parts, or blades with suitable performance parameters of some of the aforementioned factors.

[0043] Step S3: Scan and map multiple blades in the same row to obtain the mapping data of multiple blades, and establish the geometric model of the standard blade based on the mapping data of the standard blade.

[0044] In practical applications, based on the structural characteristics and design requirements of hollow turbine blades, appropriate scanning schemes are used to map the internal and external structures of the blades. These schemes include coordinate measuring machine (CMM) scanning, laser scanning, industrial CT scanning, or combinations of these methods, to obtain mapping data for multiple blades in the same row. After analyzing and processing the mapping data of multiple blades in the same row, more effective data is obtained. Common analysis and processing methods include: outlier removal, point cloud data noise reduction, and data sampling, with appropriate processing based on the actual mapping data conditions.

[0045] For single-source mapping data, a geometric model of the standard blade is established based on the single-source mapping data of the standard blade. For multi-source mapping data, the mapping data with the largest or most complete blade structure information is selected from the multi-source mapping data of the standard blade to establish an initial geometric model of the standard blade; the initial geometric model of the standard blade is then refined based on the mapping data of other sources of the standard blade to establish a new geometric model of the standard blade.

[0046] In practical applications, different standard blades can be selected according to different parts of the blade to establish geometric models of different parts of multiple standard blades, and then assembled to form a complete geometric model of the blade.

[0047] Step S4: Compare and analyze the geometric model of the standard blade and the measurement data of the multiple blades in the same row after alignment to determine whether the geometric model of the standard blade needs structural fine-tuning, and obtain the machining tolerance range of the structural dimensions of the multiple blades in the same row through the confirmed geometric model of the standard blade.

[0048] Specifically, based on the structural characteristics of hollow turbine blades, the blades are divided into external profiles and internal cooling structures. The source mapping data of the blade's external profile or internal cooling structure are aligned, and characteristic parameters of the external profiles or internal cooling structures of multiple blades in the same row are extracted. When the characteristic parameters of the standard blade's external profile or internal cooling structure are close to the average value of the characteristic parameters of multiple blades in the same row, the geometric model of the blade's external profile or internal cooling structure does not require structural adjustment. When the characteristic parameters of the standard blade's external profile or internal cooling structure are close to the extreme values ​​of the characteristic parameters of multiple blades in the same row, the geometric model of the blade's external profile or internal cooling structure is fine-tuned.

[0049] Common alignment methods include blade coordinate system-based alignment, feature section-based alignment, and optimal alignment. Different mapping data alignment methods can be selected according to different areas of the blade.

[0050] The turbine hollow blade modeling method provided by this invention, based on multi-blade mapping data, selects a standard blade from multiple blades in the same row of turbines for geometric modeling. Structural fine-tuning is then performed based on the comparative analysis results of source mapping data from different parts of the multiple blades in the same row and the geometric model of the standard blade. The blade geometric model established by the method proposed in this invention has appropriate performance parameters such as weight, moment of mass, cooling airflow characteristics, and vibration characteristics, and obtains the processing tolerance range of the multiple blades in the same row, providing data support for the evaluation of structural dimensional tolerances of turbine hollow blades.

[0051] Example 2

[0052] This invention provides a turbine hollow blade modeling system based on multi-blade mapping data, such as... Figure 2 As shown, it includes:

[0053] The blade selection module 1 is used to select multiple blades in the same row from the same type of gas turbine. This module performs the method described in step S1 of embodiment 1, which will not be repeated here.

[0054] The standard blade selection module 2 is used to measure the performance parameters of multiple selected blades in the same row, and select the blade with appropriate key performance parameters as the standard blade; the module executes the method described in step S2 of embodiment 1, which will not be repeated here.

[0055] The standard blade geometric model establishment module 3 is used to scan and map multiple blades in the same row to obtain the mapping data of multiple blades, and establish the geometric model of the standard blade based on the mapping data of the standard blade. This module executes the method described in step S3 of embodiment 1, which will not be repeated here.

[0056] The machining tolerance range acquisition module 4 is used to compare and analyze the geometric model of the standard blade and the mapping data of multiple blades in the same row after alignment. Based on the comparison and analysis results, necessary structural fine-tuning is performed on the geometric model of the standard blade. This module performs the method described in step S4 of Example 1, which will not be repeated here.

[0057] Example 3

[0058] This invention provides a computer device, such as... Figure 3As shown, the system includes: at least one processor 401, such as a CPU (Central Processing Unit), at least one communication interface 403, a memory 404, and at least one communication bus 402. The communication bus 402 is used to establish communication between these components. The communication interface 403 may include a display screen or a keyboard; optionally, the communication interface 403 may also include a standard wired interface or a wireless interface. The memory 404 may be a high-speed RAM (Random Access Memory) or a non-volatile memory, such as at least one disk storage device. Optionally, the memory 404 may also be at least one storage device located remotely from the processor 401. The processor 401 can execute the turbine hollow blade modeling method based on multi-blade mapping data of Embodiment 1. The memory 404 stores a set of program code, and the processor 401 calls the program code stored in the memory 404 to execute the turbine hollow blade modeling method based on multi-blade mapping data of Embodiment 1.

[0059] The communication bus 402 can be a peripheral component interconnect (PCI) bus or an extended industry standard architecture (EISA) bus, etc. The communication bus 402 can be divided into an address bus, a data bus, and a control bus, etc. For ease of representation, Figure 3 The symbol is represented by a single line, but this does not mean that there is only one bus or one type of bus.

[0060] The memory 404 may include volatile memory, such as random-access memory (RAM); the memory may also include non-volatile memory, such as flash memory, hard disk drive (HDD) or solid-state drive (SSD); the memory 404 may also include a combination of the above types of memory.

[0061] The processor 401 can be a central processing unit (CPU), a network processor (NP), or a combination of CPU and NP.

[0062] The processor 401 may further include a hardware chip. This hardware chip may be an application-specific integrated circuit (ASIC), a programmable logic device (PLD), or a combination thereof. The PLD may be a complex programmable logic device (CPLD), a field-programmable gate array (FPGA), a generic array logic (GAL), or any combination thereof.

[0063] Optionally, the memory 404 is also used to store program instructions. The processor 401 can call the program instructions to implement the turbine hollow blade modeling method based on multi-blade mapping data as described in Embodiment 1 of this application.

[0064] This invention also provides a computer-readable storage medium storing computer-executable instructions that can execute the turbine hollow blade modeling method based on multi-blade mapping data of Embodiment 1. The storage medium can be a magnetic disk, optical disk, read-only memory (ROM), random access memory (RAM), flash memory, hard disk drive (HDD), or solid-state drive (SSD), etc.; the storage medium may also include combinations of the above types of memory.

[0065] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. A method for modeling hollow turbine blades based on multi-blade mapping data, characterized in that, include: Select multiple blades in the same row from the same type of gas turbine; The performance parameters of multiple blades in the same row were measured, and the blade with moderate key performance parameters was selected as the standard blade. Multiple blades in the same row are scanned and mapped to obtain mapping data of multiple blades, and a geometric model of the standard blade is established based on the mapping data of the standard blade. The geometric model of the standard blade and the mapping data of the aligned multiple blades in the same row are compared and analyzed. The geometric model of the standard blade is finely adjusted based on the comparison and analysis results. The machining tolerance range of the structural dimensions of the multiple blades in the same row is obtained through the confirmed geometric model of the standard blade. The sources of the selected multiple blades in the same row include at least one of the following: blades from the same batch from the same blade manufacturer, blades from different batches from the same blade manufacturer, and blades produced by different blade manufacturers. The performance parameters of the selected multiple blades in the same row were measured, including: weight measurement, weight moment measurement, flow test and vibration characteristic measurement; Select blades with appropriate key performance parameters, including at least one of the following: blades with appropriate weight, appropriate moment of weight, appropriate blade cooling airflow characteristics, or appropriate vibration characteristics among multiple blades in the same row. The process of establishing a standard blade geometry model includes: For single-source mapping data, a geometric model of the standard blade is established based on the single-source mapping data of the standard blade. For multi-source mapping data, select the mapping data with the largest or most complete blade structure information from the multi-source mapping data of the standard blade to establish the initial geometric model of the standard blade; refine the initial geometric model based on the mapping data of other sources of the standard blade to establish the geometric model of the standard blade. The hollow turbine blade includes an external profile and an internal cooling structure. The process of comparing and analyzing the geometric model of the standard blade with the measurement data of multiple blades in the same row after alignment to determine whether the geometric model of the standard blade requires structural fine-tuning includes: Align the source mapping data of the blade's external profile or internal cooling structure, and extract the characteristic parameters of the external profile or internal cooling structure of multiple blades in the same row. If the characteristic parameters of the standard blade's external profile or internal cooling structure are close to the average value of the characteristic parameters of multiple blades in the same row, the geometric model of the blade's external profile or internal cooling structure does not need to be structurally adjusted. If the characteristic parameters of the standard blade's external profile or internal cooling structure are close to the extreme values ​​of the characteristic parameters of multiple blades in the same row, the geometric model of the blade's external profile or internal cooling structure is finely adjusted.

2. The method for modeling hollow turbine blades based on multi-blade mapping data according to claim 1, characterized in that, Different standard blades are selected based on different parts of the blade, and geometric models of different parts of multiple standard blades are established and assembled to form a complete geometric model of a standard blade.

3. A turbine hollow blade modeling system based on multi-blade mapping data, characterized in that, The turbine hollow blade modeling method based on multi-blade mapping data, applied to any one of claims 1 and 2, wherein the system comprises: The blade selection module is used to select multiple blades in the same row from gas turbines of the same model. The standard blade selection module is used to measure the performance parameters of multiple selected blades in the same row and select the blade with appropriate key performance parameters as the standard blade. The standard blade geometric model establishment module is used to scan and map multiple blades in the same row, obtain the mapping data of multiple blades, and establish the geometric model of the standard blade based on the mapping data of the standard blade. The machining tolerance range acquisition module is used to compare and analyze the geometric model of the standard blade and the mapping data of multiple blades in the same row after alignment. Based on the comparison and analysis results, the geometric model of the standard blade is finely adjusted.

4. A computer device, characterized in that, include: At least one processor, and a memory communicatively connected to the at least one processor, wherein the memory stores instructions executable by the at least one processor, the instructions being executed by the at least one processor to cause the at least one processor to perform the turbine hollow blade modeling method based on multi-blade mapping data as described in any one of claims 1 and 2.

5. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer instructions for causing the computer to execute the turbine hollow blade modeling method based on multi-blade mapping data as described in any one of claims 1 and 2.

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