Three-section type assembly method of gas compressor rotor and gas compressor rotor

Abstract

The invention provides a three-section type assembly method for a gas compressor rotor and the gas compressor rotor, and the method comprises the steps: measuring the eccentricity and self unbalance of each stage of disc and journal of a multi-stage rotor in the gas compressor rotor, and obtaining basic data; calculating unbalance data caused by eccentricity of each stage of disc and shaft neck of a multi-stage rotor in the compressor rotor; the caused unbalance amount is compared with self unbalance amount data, and each disc and journal of a multi-stage rotor in the compressor rotor are assembled in a centroid stacking and / or centroid stacking mode according to comparison result data; a to-be-assembled part in the gas compressor rotor is divided into three sections; and corresponding assembly modes are selected based on the comparison result, and the first section, the second section and the third section are sequentially assembled. Through three-section type assembly, errors in the assembly process are reduced, the overall assembly precision of the gas compressor rotor is improved, the balance performance of the gas compressor rotor is optimized, and the stability of the gas compressor rotor is improved.

Description

Technical Field

[0001] The invention belongs to the technical field of compressor rotor assembly and control, and in particular relates to a three-stage assembly method of a compressor rotor and a compressor rotor. Background Art

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

[0003] For the assembly of multi-stage compressor disks and journals, the traditional assembly method adopts the method of staggering the light and heavy points of adjacent blades. Common assembly methods include staggering the light and heavy points of adjacent disks and journals by 180°, 120°, or the light and heavy points of each level of disks and journals in a "M" shape. In recent years, with the improvement of the processing level of disks and journals, the residual unbalance of each level of disks and journals has been continuously reduced. Compared with the influence of the unbalance of each level of disks and journals on the performance of compressor rotor components, the accumulation of the shape and position tolerances of the stoppers of each level of disks and journals has a greater influence on the performance of compressor rotor components. Therefore, the superposition projection method is used for assembly to control the coaxiality of the compressor rotor components. However, whether the assembly is staggered or the superposition projection phase assembly is used, the initial unbalance of the component cannot be controlled to the minimum. The influence of the residual unbalance of the disk and journal and the centroid offset on the unbalance of the component can be comprehensively considered to optimize the unbalance of the component. In summary, in the current assembly of compressor rotors, the initial unbalance of the compressor rotor assembly is not controlled to be small enough, resulting in the stability of the compressor rotor after assembly to be further improved and optimized. Summary of the invention

[0004] The present invention provides a three-stage assembly method for a compressor rotor and a compressor rotor, aiming to solve the problem that, during the current assembly of the compressor rotor, the initial unbalance amount of the compressor rotor assembly is not controlled to be small enough, resulting in the stability of the compressor rotor after assembly needing to be further improved and optimized.

[0005] In order to achieve the above object, the present invention adopts the following technical scheme: The present invention provides a three-stage assembly method for a compressor rotor, comprising the following steps: S1. Measure the eccentricity of each stage of the disk and the journal and the self-imbalance of the multi-stage rotor in the compressor rotor, obtain the data of the eccentricity of each stage of the disk and the journal and the self-imbalance, and form basic data; S2. Calculate the unbalance data caused by the eccentricity of each disc and journal of the multi-stage rotor in the compressor rotor; S3. Compare the imbalance caused by the compressor rotor with the imbalance itself, 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 according to the comparison result data; S4, dividing the components to be assembled in the compressor rotor into three sections; selecting corresponding assembly methods based on the comparison results of S3, and assembling the first section, the second section and the third section in sequence to complete the assembly of the compressor rotor.

[0006] In some embodiments, in S1, a vertical balancing machine and a horizontal balancing machine are used to measure the eccentricity of each stage of the disk and the journal and the self-imbalance of the multi-stage rotor in the compressor rotor.

[0007] In some embodiments, in S2, the unbalance data caused by the eccentricity of each stage disk and journal 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 disk and journal, is the weighting factor, For the quality of parts, is the eccentricity.

[0008] In some embodiments, in S3, the rule for selecting the centroid stacking and / or centroid stacking assembly mode is as follows: like , then centroid stacking is adopted; like , then centroid stacking is used; like or , then the centroid and centroid fusion stacking is adopted; in, is the unbalance caused by the eccentricity of the disk and journal, is the coefficient, is the self-imbalance amount.

[0009] In some embodiments, in S4, dividing the components to be assembled in the compressor rotor into three sections specifically includes: The third-stage disk, the fourth-stage disk and the fifth-stage disk in the compressor rotor are set as the first section, the front journal, the first-stage disk and the second-stage disk in the compressor rotor are set as the second section, and the comb disk and the rear journal in the compressor rotor are set as the third section.

[0010] In some embodiments, in S4, before each stage of assembly, the components to be assembled are also cleaned and pre-treated.

[0011] In some embodiments, in S4, during the assembly, it also includes performing a dynamic balancing test on the compressor rotor as a whole to adjust the balance state of the compressor rotor.

[0012] In some embodiments, S4 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 shaft in combination with the status of the components to be assembled.

[0013] Furthermore, in S4, during the assembly, the parameters of the compressor rotor assembly process are recorded and saved as historical data.

[0014] A compressor rotor is assembled by the three-stage assembly method of the above-mentioned compressor rotor. The compressor rotor includes a primary disk, a secondary disk, a tertiary disk, a fourth disk, a fifth disk and a comb disk arranged from bottom to top. The comb disk is provided with a rear journal at one end away from the fifth disk, and a front journal is provided at one end of the primary disk away from the second disk.

[0015] Compared with the prior art, the three-stage assembly method of a compressor rotor and the compressor rotor of the present invention have the following beneficial effects: The present invention provides a three-stage assembly method for a compressor rotor, comprising the following steps: S1, measuring the eccentricity and self-imbalance of each stage of the disk and the journal of a multi-stage rotor in the compressor rotor, obtaining the eccentricity and self-imbalance data of each stage of the disk and the journal of the multi-stage rotor in the compressor rotor, and forming basic data; S2, calculating the imbalance data caused by the eccentricity of each stage of the disk and the journal of the multi-stage rotor in the compressor rotor; S3, comparing the size of the imbalance caused with the self-imbalance data, and selecting the centroid stacking and / or centroid stacking assembly method for each disk and journal of the multi-stage rotor in the compressor rotor according to the comparison result data; S4, dividing the components to be assembled in the compressor rotor into three sections; selecting the corresponding assembly method based on the comparison results, assembling the first section, the second section and the third section in turn, and completing the assembly of the compressor rotor. Based on the above, the present invention accurately measures the eccentricity of each stage of the multi-stage rotor, the journal and the self-unbalance of the compressor rotor, and forms basic data, which provides a basis for subsequent calculation and assembly, helps to reduce errors in the assembly process, and improves the overall assembly accuracy of the rotor. The present invention compares the imbalance data caused and the self-unbalance data, so that the centroid stacking and / or centroid stacking assembly method can be selected in a targeted manner, optimizes the balance performance of the rotor, reduces vibration and noise during operation, and improves the stability and reliability of the rotor. In addition, the present invention divides the components to be assembled in the compressor rotor into three sections, and selects the corresponding assembly method based on the previous comparison results. This segmented assembly method not only simplifies the assembly process, but also makes the assembly work orderly and efficient. At the same time, the segmented assembly also helps to find and solve problems in time during the assembly process, avoids the complexity and uncertainty that may occur during the overall assembly, and improves the overall stability of the compressor rotor.

[0016] The present invention is not only applicable to compressor rotors, but can also be flexibly adjusted according to the characteristics and requirements of different types of rotors. For example, according to the actual measured data and comparison results, the centroid stacking, the center of mass stacking or the fusion stacking of the two can be flexibly selected to meet the assembly requirements of different rotors. The present invention helps to reduce the wear and failure of the rotor during operation through precise measurement and calculation, as well as optimized assembly methods, thereby extending the service life of the compressor rotor. The maintenance cost is reduced and the overall stability of the compressor rotor is improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The drawings in the specification are used to provide further understanding of the present invention and constitute a part of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute improper limitations on the present invention.

[0018] Figure 1 It is a three-stage assembly method of a compressor rotor and a schematic structural diagram of a compressor rotor in a compressor rotor of the present invention; Figure 2 It is a schematic diagram of a three-stage assembly method of a compressor rotor and the principle of eccentricity of parts in a compressor rotor according to the present invention; Figure 3 It is a structural schematic diagram of a three-section assembly method of a compressor rotor and a first section of a compressor rotor in a compressor rotor of the present invention; Figure 4 It is a structural schematic diagram of a three-stage assembly method of a compressor rotor and a second stage of a compressor rotor in a compressor rotor of the present invention; Figure 5 The present invention provides a three-section assembly method for a compressor rotor and a schematic structural diagram of a third section of a compressor rotor in the compressor rotor.

[0019] In the figure, 1, first-level disc, 2, second-level disc, 3, third-level disc, 4, fourth-level disc, 5, fifth-level disc, 6, comb-toothed disc, 7, rear axle journal, 8, front axle journal. DETAILED DESCRIPTION

[0020] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0021] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0022] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0023] In the description of the embodiments of the present invention, it should be noted that if the terms "upper", "lower", "horizontal", "inner", etc. indicate an orientation or positional relationship based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of the invention is usually placed when in use, it is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply 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 a limitation on the present invention. In addition, the terms "first", "second", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0024] In addition, if the term "horizontal" appears, it does not mean that the component must be absolutely horizontal, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", which does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0025] In the description of the embodiments of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal connection of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0026] How to comprehensively consider the influence of the residual unbalance of the compressor rotor disk and journal and the centroid offset on the component unbalance, so as to optimize the unbalance of the compressor rotor component, thereby obtaining good vibration performance of the entire aircraft engine and improving the stability of the engine as a whole.

[0027] like Figure 1 As shown, a three-stage assembly method of a compressor rotor of the present invention comprises the following steps: S1. Measure the eccentricity of each stage of the disk and the journal and the self-imbalance of the multi-stage rotor in the compressor rotor, obtain the data of the eccentricity of each stage of the disk and the journal and the self-imbalance, and form basic data; S2. Calculate the unbalance data caused by the eccentricity of each disc and journal of the multi-stage rotor in the compressor rotor; S3. Compare the imbalance caused by the compressor rotor with the imbalance itself, 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 according to the comparison result data; S4, dividing the components to be assembled in the compressor rotor into three sections; selecting corresponding assembly methods based on the comparison results of S3, and assembling the first section, the second section and the third section in sequence to complete the assembly of the compressor rotor.

[0028] For high-precision and high-speed modern aircraft engine compressor rotors, the initial imbalance of the high-pressure compressor rotor plays a decisive role in the vibration performance of the whole machine. Based on this, the present invention proposes the above-mentioned three-stage assembly method of the compressor rotor. First, the eccentricity of each stage of the multi-stage rotor in the compressor rotor, the journal eccentricity and the self-imbalance are measured. Then, the imbalance data caused by these eccentricities are calculated. Then, according to the results of comparing the imbalance and the self-imbalance data, the centroid stacking and / or centroid stacking assembly method is selected. Finally, the parts 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 invention improves the assembly accuracy and balancing performance of the compressor rotor, simplifies the assembly process through segmented assembly, improves the assembly efficiency, and thus enhances the stability and reliability of the rotor, and reduces the vibration and noise during operation. When assembling a multi-stage rotor, the present invention combines the structural characteristics of the components, comprehensively considers the influence of the centroid offset of the components and the residual imbalance on the imbalance of the rotor assembly to guide the assembly, and at the same time corrects and adjusts according to the status of the components during the assembly process. It can effectively reduce the initial imbalance of the compressor rotor assembly, thereby improving the working performance of the compressor rotor, and has certain applicability.

[0029] In some embodiments, a three-stage assembly method of a compressor rotor of the present invention uses a vertical balancing machine and a horizontal balancing machine to measure the eccentricity of each stage of the multi-stage rotor in the compressor rotor, the journal, and the self-imbalance, to form accurate basic data, providing relatively reliable data support for subsequent calculations and assembly.

[0030] Furthermore, the present invention provides a three-stage assembly method for a compressor rotor, and proposes a formula (1) for calculating the unbalance data caused by the eccentricity of each stage of the multi-stage rotor and the journal: (1); in, is the unbalance caused by the eccentricity of the disk and journal, is the weighting factor, For the quality of parts, is the eccentricity.

[0031] The present invention takes into account factors such as weighting factors, part mass and eccentricity, and provides an operational formula for calculating the unbalance amount, which helps to accurately evaluate the influence of the eccentricity on the rotor balance and provides technical support.

[0032] In actual working conditions, the three-stage assembly method of the compressor rotor of the present invention selects the rules of centroid stacking and / or centroid stacking assembly methods, which are based on the comparison results of the unbalance amount and the self-unbalance amount, and a coefficient n, which is obtained through experiments. At present, there is no industry standard for the coefficient n, and it can be selected in combination with the characteristics of the compressor rotor parts. Based on this, a clear guide is provided for the selection of the assembly method of the present invention, which is helpful to optimize the balance performance of the rotor.

[0033] like Figure 2-Figure 5 As shown, in some embodiments, the present invention provides a three-stage assembly method for a compressor rotor, and the components to be assembled in the compressor rotor are divided into three sections, specifically including: setting the third-stage disc 3, the fourth-stage disc 4, and the fifth-stage disc 5 in the compressor rotor as the first section, setting the front journal 8, the first-stage disc 1, and the second-stage disc 2 in the compressor rotor as the second section, and setting the comb disc 6 and the rear journal 7 in the compressor rotor as the third section. The present invention adopts this segmentation method through experiments and parameter measurement and setting, taking into account the structural and functional requirements of the rotor, which can make the assembly process more orderly and efficient. The segmented assembly helps to timely discover and solve problems during the assembly process, and is convenient for maintenance.

[0034] In addition, it is further preferred that the present invention cleans and pre-treats the components to be assembled before each assembly, which helps to remove dirt and impurities on the surface of the components, improves the assembly quality, improves the cleanliness and assembly quality of the assembled components, and helps to extend the service life of the rotor.

[0035] In addition, the present invention performs a dynamic balance test on the compressor rotor as a whole during the assembly process, which helps to adjust the balance state of the rotor, ensure that it meets the operating requirements, improve the balance performance of the rotor, and reduce vibration and noise during operation.

[0036] In a specific embodiment, the present invention measures the eccentricity data of the components to be assembled in each section after each section of assembly is completed during the assembly process, and provides data input for the next section of assembly. This facilitates timely adjustment and optimization of the assembly method during the assembly process, improves the flexibility and adaptability of the assembly process, and helps ensure that the rotor finally assembled has good balance performance. At the same time, the parameters of the compressor rotor assembly process are recorded and saved during the assembly process as historical data, providing experience and data support for subsequent assembly, which is expected to improve assembly quality and efficiency.

[0037] like Figure 1As shown, the present invention further provides a compressor rotor, which is assembled by the three-stage assembly method of the compressor rotor of the present invention, and the compressor rotor includes a primary disk 1, a secondary disk 2, a tertiary disk 3, a quaternary disk 4, a fifth disk 5 and a comb disk 6 arranged from bottom to top, and the comb disk 6 is provided with a rear journal 7 at one end away from the fifth disk 5, and a front journal 8 is provided at one 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 has good balance performance and stability, and can meet the requirements of a high-performance compressor rotor.

[0038] 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.

[0039] Data measurement: Measure the eccentricity and unbalance data of each stage of the multi-stage rotor disk and journal to obtain the eccentricity and unbalance data of each stage of the disk and journal; Calculate the effect of eccentricity on unbalance: unbalance caused by eccentricity of the disc and journal; (1); in, is the unbalance caused by the eccentricity of the disk and journal, is the weighting factor, For the quality of parts, is the eccentricity; Analyze the impact weight: Compare the imbalance caused by the eccentricity of the disc and journal at each level Residual imbalance with itself Size, if , using centroid stacking; if , using centroid stacking; if or , using centroid and centroid fusion stacking; Three-stage assembly: The first stage is centroid and center-of-mass fusion stacking assembly. The residual unbalance of the three-stage disc, the four-stage disc and the five-stage disc is about 80g·mm, and the eccentricity affects the unbalance by about 100g·mm. The centroid and center-of-mass stacking optimization assembly scheme is adopted for assembly; the second stage adopts centroid and center-of-mass fusion stacking. The residual unbalance of the front journal is about 400g·mm, and the residual unbalance of the single disc of the first-stage disc 1 and the second-stage disc 2 is about 80g·mm. The eccentricity affects the unbalance by about 100g·mm. The centroid and center-of-mass fusion stacking is adopted; 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 center-of-mass stacking is adopted; Assembly process control: During the assembly process, after each section of assembly is completed, the eccentricity data of the component in that section is measured to verify the current assembly status and provide data input for the next section of assembly. The disk and shaft assembly are adjusted in combination with the component status.

[0040] The three-stage assembly method of the compressor rotor was used to assemble a compressor rotor of a certain type of aircraft engine. The initial imbalance of the compressor rotor of the engine was reduced from 1723g·mm to 1236g·mm, and the initial imbalance was reduced by about 28%. Therefore, the assembly accuracy of the engine compressor rotor was improved, which is expected to improve the overall quality and stability of the aircraft engine.

[0041] Finally, it should be noted that the above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any ordinary technician in the industry can smoothly implement the present invention as shown in the specification and described above. However, any equivalent changes, modifications and evolutions made by technicians familiar with the profession without departing from the scope of the technical solution of the present invention using the technical content disclosed above are all equivalent embodiments of the present invention. At the same time, any equivalent changes, modifications and evolutions made to the above embodiments based on the essential technology of the present invention are still within the protection scope of the technical solution of the present invention.

Claims

1. A three-stage assembly method for a compressor rotor, characterized in that: The steps include: S1. Measure the eccentricity of each stage of the disk and the journal and the self-imbalance of the multi-stage rotor in the compressor rotor, obtain the data of the eccentricity of each stage of the disk and the journal and the self-imbalance, and form basic data; S2. Calculate the unbalance data caused by the eccentricity of each disc and journal of the multi-stage rotor in the compressor rotor; S3. Compare the imbalance caused by the compressor rotor with the imbalance itself, 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 according to the comparison result data; S4, dividing the components to be assembled in the compressor rotor into three sections; selecting corresponding assembly methods based on the comparison results of S3, and assembling 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 of the disk and the journal and the self-imbalance 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 S2, the unbalance data caused by the eccentricity of each stage disk and journal 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 disk and journal, is the weighting factor, For the quality of parts, is the eccentricity.

4. The three-stage assembly method of a compressor rotor according to claim 1, characterized in that: In S3, the rules for selecting the centroid stacking and / or centroid stacking assembly method are as follows: like , then centroid stacking is adopted; like , then centroid stacking is used; like or , then the centroid and centroid fusion stacking is adopted; in, is the unbalance caused by the eccentricity of the disk and journal, is the coefficient, is the self-imbalance amount.

5. 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.

6. 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 parts to be assembled are cleaned and pre-treated.

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

8. 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.

9. The three-stage assembly method of a compressor rotor according to claim 8, characterized in that: In the step S4, during the assembly, the parameters of the compressor rotor assembly process are recorded and saved as historical data.

10. 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 9, and the compressor rotor comprises a primary disk (1), a secondary disk (2), a tertiary disk (3), a quaternary disk (4), a fifth disk (5) and a comb-toothed disk (6) arranged from bottom to top, and the comb-toothed disk (6) is provided with a rear journal (7) at one end away from the fifth disk (5), and a front journal (8) is provided at one end of the primary disk (1) away from the secondary disk (2).

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