A three-stage assembly method for a compressor rotor, a compressor rotor

Abstract

The application provides a three-section assembly method of a compressor rotor and the compressor rotor, and the method comprises the following steps: measuring the eccentricity of the shaft neck and the self unbalance of each disc of the multi-stage rotor in the compressor rotor to obtain basic data; calculating the unbalance data caused by the eccentricity of the shaft neck of each disc of the multi-stage rotor in the compressor rotor; comparing the caused unbalance with the self unbalance data, and selecting the assembly mode of the centroid stacking and / or the barycenter stacking according to the comparison result data of each disc and the shaft neck of the multi-stage rotor in the compressor rotor; dividing the components to be assembled in the compressor rotor into three sections; and selecting the corresponding assembly mode based on the comparison result, and sequentially assembling the first section, the second section and the third section. Through the three-section assembly, the error in the assembly process is reduced, the overall assembly precision of the compressor rotor is improved, the balance performance of the compressor rotor is optimized, and the stability of the compressor rotor is improved.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of compressor rotor assembly and control, and particularly relates to a three-section assembly method of a compressor rotor and the compressor rotor. BACKGROUND

[0002] At present, for the modern aero-engine compressor rotor with high precision and high speed, the initial unbalance of the high-pressure compressor rotor plays a decisive role in the vibration performance of the whole machine, and reducing the initial unbalance of the compressor rotor is one of the important means to obtain good vibration performance of the whole aero-engine.

[0003] For the assembly of the multi-stage compressor disc and the journal, the traditional assembly method adopts the light and heavy point staggered mode of the adjacent disc, and the common assembly modes include the light and heavy point staggered by 180°, the light and heavy point staggered by 120° or the light and heavy point in the shape of "rice" of the discs and the journals of each stage. In recent years, with the improvement of the processing level of the disc and the journal, the residual unbalance of the discs and the journals of each stage is continuously reduced, and compared with the influence of the unbalance of the discs and the journals of each stage on the performance of the compressor rotor assembly, the influence of the accumulation of the shape and position tolerances of the stop of the discs and the journals of each stage on the performance of the compressor rotor assembly is greater, so the assembly is performed by using the superposition projection method to control the coaxiality of the compressor rotor assembly. However, no matter whether the light and heavy point staggered assembly or the superposition projection phase assembly is adopted, the initial unbalance of the assembly cannot be controlled to be the smallest. In combination with the influence of the residual unbalance of the disc and the journal and the centroid offset on the unbalance of the assembly, the unbalance of the assembly can be optimized. In summary, in the current assembly of the compressor rotor, the initial unbalance of the compressor rotor assembly is not small enough, which leads to the stability of the assembled compressor rotor to be further improved and optimized. SUMMARY

[0004] The present application provides a three-section assembly method of a compressor rotor and the compressor rotor, and aims to solve the problem that in the current assembly of the compressor rotor, the initial unbalance of the compressor rotor assembly is not small enough, which leads to the stability of the assembled compressor rotor to be further improved and optimized.

[0005] To achieve the above-mentioned purpose, the present application adopts the following technical solutions:

[0006] The present application provides a three-section assembly method of a compressor rotor, which comprises the following steps:

[0007] S1, measuring the eccentricity and the self-unbalance of the discs and the journals of each stage of the multi-stage rotor in the compressor rotor to obtain the eccentricity and the self-unbalance data of the discs and the journals of each stage and form the basic data;

[0008] S2, calculating the unbalance data caused by the eccentricity of the discs and the journals of each stage of the multi-stage rotor in the compressor rotor;

[0009] S3, comparing the imbalance caused by the imbalance of the part with the data size, and selecting the assembly mode of the centroid stacking and / or the center of mass stacking according to the comparison result data of each disc and journal of the multi-stage rotor in the compressor rotor;

[0010] S4, dividing the parts to be assembled in the compressor rotor into three sections; selecting the corresponding assembly mode based on the comparison result of S3, sequentially assembling the first section, the second section and the third section, and completing the assembly of the compressor rotor.

[0011] In some embodiments, in S1, the eccentricity and the self imbalance of each disc and journal of the multi-stage rotor in the compressor rotor are measured by using a vertical balancing machine and a horizontal balancing machine.

[0012] In some embodiments, in S2, the imbalance data caused by the eccentricity of each disc and journal of the multi-stage rotor in the compressor rotor is calculated by using the following formula (1):

[0013] (1);

[0014] Wherein, is the imbalance caused by the eccentricity of the disc and the journal, is the weighting factor, is the mass of the part, is the eccentricity.

[0015] In some embodiments, in S3, the rules for selecting the assembly mode of the centroid stacking and / or the center of mass stacking are as follows:

[0016] If , the centroid stacking is adopted;

[0017] If , the center of mass stacking is adopted;

[0018] If or , the fusion stacking of the centroid and the center of mass is adopted;

[0019] Wherein, is the imbalance caused by the eccentricity of the disc and the journal, is the coefficient, is the self imbalance.

[0020] In some embodiments, in S4, the parts to be assembled in the compressor rotor are divided into three sections, which specifically includes:

[0021] The three-stage disc, the four-stage disc and the five-stage disc in the compressor rotor are set as the first section, the front journal, the one-stage disc and the two-stage disc in the compressor rotor are set as the second section, and the screen disc and the rear journal in the compressor rotor are set as the third section.

[0022] In some embodiments, in S4, before assembling each section, the components to be assembled are cleaned and pretreated.

[0023] In some embodiments, in S4, when assembling, the entire compressor rotor is subjected to dynamic balance testing to adjust the balance state of the compressor rotor.

[0024] In some embodiments, in S4, the eccentricity data of the components to be assembled in each section of the assembly process is measured, and the data is provided as input for the next section of assembly to adjust the assembly of the disk and shaft of the components to be assembled.

[0025] Further, in S4, when assembling, the parameters in the compressor rotor assembly process are recorded and saved as historical data.

[0026] A compressor rotor assembled by the three-section assembly method of the compressor rotor, the compressor rotor comprising, from bottom to top, a first-stage disk, a second-stage disk, a third-stage disk, a fourth-stage disk, a fifth-stage disk, and a screen disk, the screen disk being provided with a rear journal at an end away from the fifth-stage disk, and the first-stage disk being provided with a front journal at an end away from the second-stage disk.

[0027] Compared with the prior art, the three-section assembly method of the compressor rotor and the compressor rotor have the following beneficial effects:

[0028] The three-section assembly method of the compressor rotor comprises the following steps: S1, measuring the eccentricity of the shaft neck and the self unbalance of each disc of the multi-stage rotor in the compressor rotor, obtaining the data of the eccentricity of the shaft neck and the self unbalance of each disc, and forming basic data; S2, calculating the unbalance data caused by the eccentricity of the shaft neck of each disc of the multi-stage rotor in the compressor rotor; S3, comparing the unbalance data caused by the eccentricity of the shaft neck with the self unbalance data, and selecting the assembly mode of the centroid stacking and / or the center of mass stacking according to the comparison result data of each disc and the shaft neck of the multi-stage rotor in the compressor rotor; S4, dividing the components to be assembled in the compressor rotor into three sections; selecting the corresponding assembly mode based on the comparison result, and sequentially assembling the first section, the second section and the third section to complete the assembly of the compressor rotor. Based on the above, the eccentricity of the shaft neck and the self unbalance of each disc of the multi-stage rotor in the compressor rotor are accurately measured, and the basic data is formed, which provides a basis for subsequent calculation and assembly, helps to reduce the error in the assembly process, and improves the overall assembly accuracy of the rotor. Through the comparison of the unbalance data caused by the eccentricity of the shaft neck and the self unbalance data, the assembly mode of the centroid stacking and / or the center of mass stacking can be selected accordingly, the balance performance of the rotor is optimized, the vibration and noise during operation are reduced, and the stability and reliability of the rotor are improved. Moreover, the components to be assembled in the compressor rotor are divided into three sections, and the corresponding assembly mode is selected based on the previous comparison result. This segmented assembly mode not only simplifies the assembly process, but also makes the assembly work orderly and efficient. At the same time, segmented assembly helps to discover and solve problems in the assembly process in time, avoids the complexity and uncertainty that may occur during overall assembly, and improves the overall stability of the compressor rotor.

[0029] The present application is not only suitable for compressor rotors, but also can be flexibly adjusted according to the characteristics and needs of different types of rotors. For example, the centroid stacking, the center of mass stacking or the fusion stacking mode of the two can be flexibly selected according to the actual measured data and the comparison result to adapt to the assembly needs of different rotors. The present application helps to reduce the wear and failure of the rotor during operation by accurate measurement and calculation, and the optimized assembly mode, thereby prolonging the service life of the compressor rotor. Reduces the maintenance cost and improves the overall stability of the compressor rotor. BRIEF DESCRIPTION OF DRAWINGS

[0030] The accompanying drawings are included to provide a further understanding of the present application, and constitute a part of the present application. The schematic embodiments of the present application and their descriptions are used to explain the present application, and do not constitute an improper limitation on the present application.

[0031] Figure 1 The three-section assembly method of the compressor rotor, and the structure diagram of the compressor rotor in the compressor rotor of the present application;

[0032] Figure 2 Figure 1 is a schematic diagram of the three-stage assembly method of a compressor rotor and the eccentricity principle of parts in the compressor rotor according to the present application;

[0033] Figure 3 Figure 2 is a schematic diagram of the structure of the first stage of the compressor rotor in the three-stage assembly method of a compressor rotor according to the present application;

[0034] Figure 4 Figure 3 is a schematic diagram of the structure of the second stage of the compressor rotor in the three-stage assembly method of a compressor rotor according to the present application;

[0035] Figure 5 Figure 4 is a schematic diagram of the structure of the third stage of the compressor rotor in the three-stage assembly method of a compressor rotor according to the present application.

[0036] In the figure, 1 is a first-stage disk, 2 is a second-stage disk, 3 is a third-stage disk, 4 is a fourth-stage disk, 5 is a fifth-stage disk, 6 is a sieve disk, and 7 is a rear journal, and 8 is a front journal. DETAILED DESCRIPTION

[0037] In order to make the objectives, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are some but not all of the embodiments of the present application. The components of the embodiments of the present application described and shown in the accompanying drawings herein can be arranged and designed in various different configurations.

[0038] Therefore, the following detailed description of the embodiments of the present application provided in the accompanying drawings is not intended to limit the scope of the claimed present application, but only represents selected embodiments of the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative work are within the scope of protection of the present application.

[0039] It should be noted that: similar reference numerals and letters represent similar items in the following drawings, and therefore, once an item is defined in one drawing, it does not need to be further defined and explained in subsequent drawings.

[0040] In the description of the embodiments of the present application, it should be noted that if the terms "upper", "lower", "horizontal", "inner" and the like indicating the orientation or position relationship are based on the orientation or position relationship shown in the drawings, or the orientation or position relationship when the product of the present application is usually placed, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second" and the like are only used for differentiation and cannot be understood as indicating or implying relative importance.

[0041] In addition, if the term "horizontal" appears, it does not mean that the component must be absolutely horizontal, but can be slightly inclined. For example, "horizontal" only means that its direction is relatively more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly inclined.

[0042] In the description of the embodiments of the present application, it should be noted that unless otherwise explicitly specified and limited, if the terms "arrangement", "installation", "connection", "connection" appear, they should be understood in a broad sense, for example, they can be fixedly connected, or can be detachably connected, or integrally connected; can be mechanically connected, or can be electrically connected; can be directly connected, or can be indirectly connected through an intermediate medium; can be the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0043] How to comprehensively consider the influence of the residual unbalance amount of the disc and the journal of the compressor rotor and the centroid offset on the unbalance amount of the assembly, so as to optimize the unbalance amount of the compressor rotor assembly, and then obtain good vibration performance of the whole aero-engine, and improve the stability of the engine as a whole.

[0044] As shown in Figure 1 A three-stage assembly method of a compressor rotor according to the present application comprises the following steps:

[0045] S1, measuring the eccentricity of each disc and journal of the multi-stage rotor in the compressor rotor and the self unbalance amount, obtaining the eccentricity data of each disc and journal and the self unbalance amount data, and forming the basic data;

[0046] S2, calculating the unbalance amount data caused by the eccentricity of each disc and journal of the multi-stage rotor in the compressor rotor;

[0047] S3, comparing the size of the caused unbalance amount and the self unbalance amount data, and selecting the assembly mode of centroid stacking and / or mass center stacking for each disc and journal of the multi-stage rotor in the compressor rotor according to the comparison result data;

[0048] S4, the components to be assembled in the compressor rotor are divided into three sections; the corresponding assembly method is selected based on the comparison results of S3, and the assembly of the first section, the second section and the third section is carried out in sequence, and the assembly of the compressor rotor is completed.

[0049] For modern aero-engine compressors with high precision and high speed, the initial unbalance of the high-pressure compressor rotor plays a decisive role in the vibration performance of the whole machine. Based on this, the three-section assembly method of the compressor rotor is proposed. First, the eccentricity of each stage disc and shaft neck and the self unbalance of the multi-stage rotor in the compressor rotor are measured. Then, the unbalance data caused by these eccentricities is calculated. Then, according to the comparison results of the unbalance and the self unbalance data, the assembly method of the centroid stacking and / or the centroid stacking is selected. Finally, the components to be assembled are divided into three sections, and the corresponding assembly method is selected based on the previous comparison results to complete the assembly. The present application improves the assembly precision and balancing performance of the compressor rotor. Through segmented assembly, the assembly process is simplified, the assembly efficiency is improved, and the stability and reliability of the rotor are enhanced, thereby reducing the vibration and noise during operation. When assembling the multi-stage rotor, the present application combines the structural characteristics of the components, comprehensively considers the influence of the centroid offset of the components and the residual unbalance on the unbalance of the rotor assembly to guide the assembly, and simultaneously adjusts and corrects the components according to the state during the assembly process, which can effectively reduce the initial unbalance of the compressor rotor assembly, thereby improving the working performance of the compressor rotor, and has certain applicability.

[0050] In some embodiments, the three-section assembly method of the compressor rotor of the present application uses a vertical balancing machine and a horizontal balancing machine to measure the eccentricity of each stage disc and shaft neck and the self unbalance of the multi-stage rotor in the compressor rotor, forming accurate basic data to provide relatively reliable data support for subsequent calculation and assembly.

[0051] Further, the three-section assembly method of the compressor rotor of the present application proposes a formula (1) for calculating the unbalance data caused by the eccentricity of each stage disc and shaft neck of the multi-stage rotor in the compressor rotor:

[0052] (1);

[0053] wherein, is the unbalance caused by the disc and shaft neck eccentricity, is a weighting factor, is the mass of the part, is the eccentricity.

[0054] The present application considers factors such as the weighting factor, the mass of the part and the eccentricity, providing an operable formula for calculating the unbalance, which helps to accurately evaluate the influence of the eccentricity on the balancing of the rotor and provides technical support.

[0055] In actual working conditions, the three-section assembly method of the compressor rotor of the application selects the rules of the centroid stacking and / or the center of mass stacking assembly mode, which are based on the comparison results of the unbalance and the self unbalance, and a coefficient n, which is obtained through experiments. At present, there is no industry standard for the coefficient n, which can be selected in combination with the characteristics of the parts of the compressor rotor. Based on this, the application provides clear guidance for the assembly mode selected by the application, which helps to optimize the balance performance of the rotor.

[0056] As shown in Figures 2-5 In some embodiments, the three-section assembly method of the compressor rotor of the application divides the parts to be assembled in the compressor rotor into three sections, which specifically includes: setting the third-stage disk 3, the fourth-stage disk 4 and the fifth-stage disk 5 in the compressor rotor as the first section, setting the front shaft neck 8, the first-stage disk 1 and the second-stage disk 2 in the compressor rotor as the second section, and setting the sieve disk 6 and the rear shaft neck 7 in the compressor rotor as the third section. Through experiments and parameter measurement and setting, the application considers the structural and functional requirements of the rotor by using this segmented assembly mode, which can make the assembly process more orderly and efficient. The segmented assembly helps to discover and solve problems in time during the assembly process, which is convenient for maintenance.

[0057] In addition, further preferably, the application cleans and pretreats the parts to be assembled before assembling each section. This helps to remove dirt and impurities on the surface of the parts, improves the assembly quality, improves the cleanliness and assembly quality of the assembled parts, and helps to prolong the service life of the rotor.

[0058] And the application performs dynamic balance test on the whole compressor rotor during the assembly process. This helps to adjust the balance state of the rotor, ensures that it meets the operation requirements, improves the balance performance of the rotor, and reduces the vibration and noise during operation.

[0059] In specific embodiments, the application measures the eccentricity data of the parts to be assembled in each section after completing the assembly of the section during the assembly process, and provides data input for the next section assembly. In this way, it is convenient to adjust and optimize the assembly mode in time during the assembly process, which improves the flexibility and adaptability of the assembly process, and helps to ensure that the finally assembled rotor has good balance performance. At the same time, the parameters in the assembly process of the compressor rotor are recorded and saved as historical data, which provides experience and data support for subsequent assembly, and is expected to improve the assembly quality and efficiency.

[0060] As shown in Figure 1As shown, the present invention further provides a compressor rotor, which is assembled using the three-stage assembly method of the compressor rotor of the present invention. The compressor rotor includes a primary disk 1, a secondary disk 2, a tertiary disk 3, a fourth disk 4, a fifth disk 5, and a grate disk 6 arranged from bottom to top. The grate disk 6 is provided with a rear journal 7 at the end away from the fifth disk 5, and a front journal 8 is provided at the end of the primary disk 1 away from the secondary disk 2. Based on the three-stage assembly method of the compressor rotor of the present invention, it is expected that the compressor rotor of the present invention will have good balance performance and stability, and can meet the requirements of a high-performance compressor rotor.

[0061] The three-stage assembly method of a compressor rotor and the compressor rotor of the present invention are further described in detail below through specific embodiments.

[0062] Data measurement: Measure the eccentricity and unbalance data of each stage of the multi-stage rotor disc and journal to obtain the eccentricity and unbalance data of each stage of the disc and journal;

[0063] Calculate the effect of eccentricity on unbalance: unbalance caused by disc and journal eccentricity;

[0064] (1);

[0065] in, is the unbalance caused by the eccentricity of the disc and journal, is the weighting factor, For the quality of parts, is the eccentricity;

[0066] Analyze the impact weight: Compare the imbalance caused by the eccentricity of the disc and journal at each level With its own residual imbalance Size, if , using centroid stacking; if , using centroid stacking; if or , using centroid and centroid fusion stacking;

[0067] Three-stage assembly: The first stage is assembled by fusion of centroid and center of mass. The residual unbalance of each of the third, fourth and fifth stage discs is about 80g·mm, and the eccentricity affects the unbalance by about 100g·mm. The assembly is performed by the optimized assembly scheme of centroid and center of mass stacking. The second stage adopts fusion of centroid and center of mass stacking. The residual unbalance of the front journal is about 400g·mm. The residual unbalance of each of the first and second stage discs is about 80g·mm, and the eccentricity affects the unbalance by about 100g·mm. The assembly is performed by fusion of centroid and center of mass. The third stage adopts center of mass stacking. The residual unbalance of the rear journal 7 is about 1200g·mm, and the eccentricity affects the unbalance by about 150g·mm. The assembly is performed by center of mass stacking.

[0068] Assembly process control: the eccentricity data of each completed assembly section is measured during the assembly process, which is used to check the current assembly state and provide data input for the next assembly section, combined with the assembly state adjustment disc and shaft assembly.

[0069] The three-section assembly method of the compressor rotor is used for assembling a compressor rotor of an aero-engine, and the initial unbalance of the compressor rotor of the aero-engine is reduced from 1723 g·mm to 1236 g·mm, which is reduced by about 28%, so that the assembly precision of the compressor rotor of the aero-engine is improved, and the overall quality and stability of the aero-engine are expected to be improved.

[0070] Finally, it should be noted that: the above is only the preferred embodiment of the present application, and does not limit the present application in any form; any person skilled in the art can easily implement the present application according to the description and the above; however, any equivalent changes, modifications and evolution made by those skilled in the art within the scope of the technical solutions of the present application, using the technical content disclosed above, are equivalent embodiments of the present application; at the same time, any equivalent changes, modifications and evolution of the above embodiments according to the essential technology of the present application are still within the protection scope of the technical solutions of the present application.

Claims

1. A three-stage assembly method for a compressor rotor, characterized in that: The steps include: S1. Measure the eccentricity and self-balance of the disks and journals of each stage of the multi-stage rotor in the compressor rotor to obtain data on the eccentricity and self-balance of the disks and journals of each stage to form basic data; S2. Calculate the unbalance data caused by the eccentricity of the discs and journals of each stage of the multi-stage rotor in the compressor rotor; The unbalance data caused by the eccentricity of the disks and journals of each stage of the multi-stage rotor in the compressor rotor is calculated using the following formula (1): （1）； in, is the unbalance caused by the eccentricity of the disc and journal, is the weighting factor, For the quality of parts, is the eccentricity; S3. Compare the induced imbalance amount with the inherent imbalance amount data, and select centroid stacking and / or centroid stacking as the assembly method for each disk and journal of the multi-stage rotor in the compressor rotor based on the comparison results; The rules for selecting centroid stacking and / or centroid stacking assembly methods are as follows: like , then centroid stacking is adopted; like , then centroid stacking is used; like or , the centroid and centroid fusion stacking is adopted; in, is the unbalance caused by the eccentricity of the disc and journal, is the coefficient, is the self-balance amount; S4. Divide the components to be assembled in the compressor rotor into three sections; select corresponding assembly methods based on the comparison results of S3, and assemble the first section, the second section, and the third section in sequence to complete the assembly of the compressor rotor.

2. The three-stage assembly method of a compressor rotor according to claim 1, characterized in that: In S1, a vertical balancing machine and a horizontal balancing machine are used to measure the eccentricity of each stage disk and journal and the self-unbalance of the multi-stage rotor in the compressor rotor.

3. The three-stage assembly method of a compressor rotor according to claim 1, characterized in that: In said S4, dividing the components to be assembled in the compressor rotor into three sections specifically includes: The third-stage disc (3), the fourth-stage disc (4) and the fifth-stage disc (5) in the compressor rotor are set as the first section, the front journal (8), the first-stage disc (1) and the second-stage disc (2) in the compressor rotor are set as the second section, and the grate disc (6) and the rear journal (7) in the compressor rotor are set as the third section.

4. The three-stage assembly method of a compressor rotor according to claim 1, characterized in that: In said S4, before each stage of assembly, the components to be assembled are cleaned and pre-treated.

5. The three-stage assembly method of a compressor rotor according to claim 1, characterized in that: In said S4, during the assembly, a dynamic balancing test is also performed on the entire compressor rotor to adjust the balance state of the compressor rotor.

6. The three-stage assembly method of a compressor rotor according to claim 1, characterized in that: In said S4, it also includes measuring the eccentricity data of the components to be assembled in each section after each section of assembly is completed during the assembly process, providing data input for the next section of assembly, and adjusting the assembly of the disk and the shaft in combination with the status of the components to be assembled.

7. The three-stage assembly method of a compressor rotor according to claim 6, characterized in that: In said S4, during the assembly, the parameters of the compressor rotor assembly process are recorded and saved as historical data.

8. A compressor rotor, characterized in that: The compressor rotor is assembled by the three-stage assembly method of the compressor rotor according to any one of claims 1 to 7, and the compressor rotor includes a first-stage disc (1), a second-stage disc (2), a third-stage disc (3), a fourth-stage disc (4), a fifth-stage disc (5) and a grate disc (6) arranged from bottom to top, and the grate disc (6) is provided with a rear journal (7) at the end away from the fifth-stage disc (5), and a front journal (8) is provided at the end of the first-stage disc (1) away from the second-stage disc (2).

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