Device and method for press-fitting assembly of aero-engine core engine rotor

Abstract

The invention discloses an aero-engine core engine rotor press-fitting assembly device which comprises a supporting rod, a mounting base, a pull rod and an upper pressing plate which are sequentially arranged from top to bottom, a lower base is further arranged in the center of the top face of the mounting base, and connecting blocks are evenly arranged on the top face of the mounting base around the lower base. The bottom of the connecting block downwards penetrates through the mounting base and is connected with an actuating cylinder arranged at the bottom of the mounting base, the bottom of the pull rod is connected with the connecting block, a pull rod connecting clamping groove is formed in the position, right opposite to the pull rod, of the edge of the upper pressing plate, and a pressure sensor and an electronic display screen are further arranged on the top face of the lower base. The pressure sensor is located between the rotor and the lower base and is in electric signal connection with the electronic display screen. The problems that when a high-pressure compressor rotor and a high-pressure turbine rotor are assembled, due to interference of interference spigots and warping of installation edges, the rotors cannot be tightly attached, rotor assembly jumping is unqualified, and a main machine vibrates are solved.

Description

Technical Field

[0001] The invention relates to the field of aeroengine core rotor assembly, in particular to a device and method for press-assembling aeroengine core rotor. Background Art

[0002] After testing a certain type of aircraft engine disc components (thin-walled discs, such as three-stage disc shafts, comb discs, and front sealing discs), it was found that nearly 83% of them had "saddle-shaped" features on the end faces (double high points, narrow high point areas, symmetrical phases, consistent trends on the upper and lower end faces, and the magnitude ranged from 0.005mm to 0.03mm); testing of drum components found that 100% of their flange mounting surfaces had "crater" features (there was a height difference on the end faces along the radial direction, and the magnitude ranged from 0.005mm to 0.05mm). The reason for this phenomenon is the warping deformation of the disc drum parts under the engine working conditions after the alternating tug-of-war force. This type of connection method of two "point" or "circular line" contact instead of "surface" contact greatly affects the fit of the product assembly connection surface, resulting in rework due to the out-of-tolerance runout caused by the rotor not being properly installed. The rework rate of parts reached 48% and the rework rate of components reached 41.7%. At the same time, the above-mentioned warping deformation will greatly and randomly weaken the effective preload force of the bolts converted from the tightening torque. The measured dispersion of the bolt elongation is as high as 0.031. Such assembly connection characteristics greatly affect the overall rigidity of the rotor and are the main cause of the main engine vibration failure.

[0003] In addition, the traditional aircraft engine rotor assembly process can no longer meet the high-precision and high-repeatability assembly requirements. Combined with the on-site physical inspection of the rotor connection surface of the engine core with vibration failure, it was found that the connection surface had cavity color change, and the connecting bolts had bright marks caused by micro-wear, further confirming that the rotor end face fit is closely related to the core engine connection quality. Therefore, in order to ensure the one-time qualified rate of rotor disk assembly and the connection stability, a device was designed. The device can assist the rotor to fall into place by applying external force during the assembly process, eliminate the virtual connection caused by the warping of the flange mounting surface, realize the smooth conversion of tightening torque to bolt preload, optimize the connection surface fit and the discreteness of the bolt preload, and study the method of using it for assembly. Summary of the invention

[0004] The purpose of the present invention is to provide a device and method for press-fitting the rotor of an aircraft engine core machine, so as to solve the problem that when assembling the high-pressure compressor rotor and the high-pressure turbine rotor, the rotor cannot fit tightly due to interference from the interference stop and warping of the installation edge, thereby causing rotor assembly failure and main engine vibration failure.

[0005] In order to solve the above technical problems, the present invention adopts the following technical solutions: A device for press-fitting and assembling a rotor of an aircraft engine core, comprising a support rod, a mounting seat, a pull rod and an upper pressure plate arranged in sequence from top to bottom, a lower base is also arranged at the center of the top surface of the mounting seat, connecting blocks are evenly arranged on the top surface of the mounting seat around the lower base, the bottom of the connecting block passes downward through the mounting seat and is connected to an actuator cylinder arranged at the bottom of the mounting seat, the bottom of the pull rod is connected to the connecting block, a pull rod connecting groove is provided at the edge of the upper pressure plate facing the pull rod, a pressure sensor and an electronic display screen are also provided on the top surface of the lower base, the pressure sensor is located between the rotor and the lower base, and the pressure sensor is electrically connected to the electronic display screen.

[0006] There are three actuators, and the pressure generated by the three actuators comes from the same pressure pump. The connecting block is a splint-type rotating connecting block, which is specifically composed of a base and two splints. The bottom of the pull rod can be rotatably clamped between the two splints, and the pull rod is connected to the connecting block by connecting bolts.

[0007] As a further preferred embodiment of the present invention, a universal wheel is provided at the bottom of the support rod.

[0008] Easy to move.

[0009] As a further preferred embodiment of the present invention, the support rod is a lifting support rod.

[0010] This makes it easy to adjust the support height according to the operator's elevation.

[0011] As a further preferred embodiment of the present invention, the lower base has two types, one type of lower base is suitable for press-fitting assembly of high-pressure compressor rotors, and the other type of lower base is suitable for press-fitting assembly of high-pressure turbine rotors.

[0012] As a further preference of the present invention, there are three types of upper pressure plates, two types of which are suitable for press-fitting assembly of high-pressure turbine rotors, and another type of upper pressure plate is suitable for press-fitting assembly of high-pressure compressor rotors. The upper pressure plates suitable for press-fitting assembly of high-pressure turbine rotors include an upper pressure plate used when the drum shaft is located at the top of the component and an upper pressure plate used when the drum shaft is located on the top surface of the lower base.

[0013] The method for assembling a high-pressure compressor rotor using any of the above-mentioned devices comprises the following steps: placing a lower base suitable for press-fitting assembly of a high-pressure compressor rotor at the center of the top surface of a mounting seat, and installing a first-level to a second-level disk assembly on the lower base; heating a third-level disk shaft to a temperature of ≯177°C, and keeping the temperature for 20 to 30 minutes, and then installing the heated third-level disk shaft on the first-level to a second-level disk assembly, and then installing a fourth-level to a ninth-level disk assembly; after installing the fourth-level to a ninth-level disk assembly, installing an upper pressure plate on the rear end of the fourth-level to a ninth-level disk assembly, and then connecting a tie rod so that the bottom end of the tie rod is connected to a connecting block, and the upper end of the tie rod is clamped in a tie rod connection slot; shaking a pressure pump that provides pressure to an actuator so that the axial load reaches the assembly load of the press-fitting of the high-pressure compressor rotor; and waiting for the third-level disk to be assembled. After the shaft returns to room temperature, tighten the inner cavity nut and remove the upper pressure plate; then heat the grate disc, the temperature of the heated grate disc is ≯177℃, and keep it warm for 20~30min; then install the heated grate disc at the rear end of the fourth to ninth stage disc assembly, and install the upper pressure plate at the rear end of the grate disc, and connect the pull rod again; shake the pressure pump that provides pressure to the actuator cylinder so that the axial load reaches the assembly load of the high-pressure compressor rotor press again; after the grate disc returns to room temperature, tighten the clamping nut, remove the upper pressure plate and the high-pressure compressor rotor to complete the entire transfer; the upper pressure plate used in the assembly process is a model suitable for the press assembly of the high-pressure compressor rotor. During the press assembly process, in order to ensure the stability of the load application process of the press assembly device, a tension sensor is used to calibrate the cavity pressure and tension linearity of the actuator cylinder of the device.

[0014] As a further preference of the present invention, preparatory work is required before press assembly, and the preparatory work includes: conducting a core engine rotor strength simulation analysis in advance to clarify the maximum applied load; then, according to the core engine rotor strength simulation analysis, a customized press assembly pressure value is output, and a simulation analysis is carried out based on the product measurement deformation results; finally, the press assembly load of the high-pressure compressor rotor is determined based on the connection characteristics of the high-pressure compressor rotor, the shape and position status of the components under different load tests, and the allowable margin.

[0015] The purpose of carrying out core engine rotor strength simulation analysis in advance is to ensure that the axial load has no impact on the product structure.

[0016] The method for assembling a high-pressure turbine rotor using any of the above-mentioned devices comprises the following steps: placing a lower base suitable for press-fitting the high-pressure turbine rotor at the center of the top surface of the mounting seat, and installing the high scroll on the base; cooling the front stop of the high scroll and the rear stop of the drum shaft with liquid nitrogen; installing the front sealing plate on the high scroll, and then dropping the drum shaft; installing the upper pressure plate used when the drum shaft is located at the top of the component at the front end of the drum shaft, and connecting the pull rod; shaking the pressure pump that provides pressure for the actuator so that the measured axial load reaches the assembly load of the press-fitting of the high-pressure turbine rotor; tightening the front bolts of the plate after the front sealing plate and the drum shaft return to room temperature, and removing the upper pressure plate used when the drum shaft is located at the top of the component. The upper pressure plate when the drum shaft is on the top; after the rotor assembly is turned 180°, the drum shaft is installed on the lower base, and the rear stop of the high scroll is cooled by liquid nitrogen; the rear shaft is installed at the rear end of the high scroll, and the upper pressure plate used when the drum shaft is located on the top surface of the lower base is installed at the rear end of the rear shaft, and the pull rod is connected; the pressure pump that provides pressure to the actuator cylinder is shaken to make the measured axial load reach the assembly load of the high-pressure turbine rotor press-fit; after the rear shaft returns to room temperature, the bolts behind the disk are tightened, and the upper pressure plate and the high-pressure turbine rotor used when the drum shaft is located on the top surface of the lower base are removed. During the press-fitting process, in order to ensure the stability of the load application process of the press-fitting device, a tension sensor is used to calibrate the cavity pressure and tension linearity of the actuator cylinder of the device.

[0017] As a further preference of the present invention, preparatory work is required before press assembly, and the preparatory work includes: conducting a core engine rotor strength simulation analysis in advance to clarify the maximum applied load; then, according to the core engine rotor strength simulation analysis, a customized press assembly pressure value is output, and a simulation analysis is carried out according to the product measurement deformation results; finally, the high-pressure compressor rotor press assembly load is determined according to the connection characteristics of the high-pressure turbine rotor, the shape and position status of the components under different load tests, and the allowable margin.

[0018] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects: 1. The problem of rotor assembly failure and main engine vibration failure caused by interference from interference fit and warping of the installation edge during assembly of the high-pressure compressor rotor and the high-pressure turbine rotor has been solved.

[0019] 2. The use of the device and method to assemble high-pressure compressor rotors and high-pressure turbine rotors can ensure the safety of the product structure while ensuring that the rotor shape and position parameters meet the assembly technical requirements. The use of the device and method of the invention has increased the first-time qualified rate of core engine rotor parts from 52% to 94.2%, and the first-time qualified rate of core engine rotor assembly from 58.3% to 93.1%, and the single-unit assembly time has been shortened from more than 25 hours to 15 hours, which greatly shortens the assembly time, reduces production costs, and improves corporate benefits. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the structure of the present invention.

[0022] Figure 2 The present invention is a schematic diagram of the lower base structure suitable for press-fitting the high-pressure compressor rotor.

[0023] Figure 3 The present invention is a schematic diagram of the structure of an upper pressure plate used for press-fitting and assembling a high-pressure compressor rotor.

[0024] Figure 4 It is a schematic diagram of the structure of the lower base used for press-fitting of the high-pressure turbine rotor according to the present invention.

[0025] Figure 5 It is a schematic diagram of the structure of the upper pressure plate when the drum shaft is located at the uppermost part of the component during the press-fitting assembly process of the high-pressure turbine rotor used in the present invention.

[0026] Figure 6 It is a schematic diagram of the structure of the upper pressure plate when the drum shaft is located on the top surface of the lower base during the press-fitting assembly process of the high-pressure turbine rotor used in the present invention.

[0027] Figure 7 It is a simulation calculation diagram of the yield limit of each assembly process of the present invention.

[0028] Figure 8 This is a simulation calculation diagram of the 0.05mm warping deformation correction load of the present invention. DETAILED DESCRIPTION

[0029] 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.

[0030] 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.

[0031] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features of the embodiments may be combined with each other.

[0032] 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.

[0033] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, or the positions or positional relationships in which the product of the invention is usually placed when in use, or the positions or positional relationships commonly understood by those skilled in the art, which are only for the convenience of describing the present invention and simplifying the description, and do 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 limiting 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.

[0034] In the description 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 communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances. Specific embodiment 1: Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 , Figure 8 A device for press-fitting and assembling a rotor of an aircraft engine core is shown, comprising a support rod 1, a mounting seat 2, a pull rod 3 and an upper pressure plate 4 arranged in sequence from top to bottom, a lower base 5 is also arranged at the center of the top surface of the mounting seat 2, connecting blocks 6 are evenly arranged on the top surface of the mounting seat 2 around the lower base 5, the bottom of the connecting block 6 passes downward through the mounting seat 2 and is connected to an actuator 7 arranged at the bottom of the mounting seat 2, the bottom of the pull rod 3 is connected to the connecting block 6, a pull rod connecting groove 41 is provided at the edge of the upper pressure plate 4 facing the pull rod 3, a pressure sensor and an electronic display screen 8 are also provided on the top surface of the lower base 5, the pressure sensor is located between the rotor and the lower base 5, and the pressure sensor is electrically connected to the electronic display screen 8.

[0036] There are three actuators, and the pressure generated by the three actuators comes from the same pressure pump. The connecting block is a splint-type rotating connecting block, which is specifically composed of a base and two splints. The bottom of the pull rod can be rotatably clamped between the two splints, and the pull rod is connected to the connecting block by connecting bolts. Specific embodiment 2: This embodiment further illustrates the support rod on the basis of the specific embodiment 1. A universal wheel 11 is provided at the bottom of the support rod 1 .

[0038] Easy to move. Specific embodiment 3: This embodiment further illustrates the support rod on the basis of the specific embodiment 1, wherein the support rod 1 is a lifting support rod.

[0040] This makes it easy to adjust the support height according to the operator's elevation. Specific embodiment 4: This embodiment further illustrates the lower base on the basis of the specific embodiment 1. The lower base 5 has two types, one type of lower base is suitable for press-fitting assembly of high-pressure compressor rotors, and the other type of lower base is suitable for press-fitting assembly of high-pressure turbine rotors. Specific embodiment 5: This embodiment further explains the upper pressure plate on the basis of specific embodiment 1. The upper pressure plate 4 has three models, two of which are suitable for press-fitting of high-pressure turbine rotors, and the other type of upper pressure plate is suitable for press-fitting of high-pressure compressor rotors. The upper pressure plate suitable for press-fitting of high-pressure turbine rotors includes an upper pressure plate used when the drum shaft is located at the top of the component and an upper pressure plate used when the drum shaft is located on the top surface of the lower base. Specific embodiment 6: The method for assembling a high-pressure compressor rotor using any of the above-mentioned devices comprises the following steps: placing a lower base suitable for press-fitting assembly of a high-pressure compressor rotor at the center of the top surface of a mounting seat, and installing a first-level to a second-level disk assembly on the lower base; heating a third-level disk shaft to a temperature of ≯177°C, and keeping the temperature for 20 to 30 minutes, and then installing the heated third-level disk shaft on the first-level to a second-level disk assembly, and then installing a fourth-level to a ninth-level disk assembly; after installing the fourth-level to a ninth-level disk assembly, installing an upper pressure plate on the rear end of the fourth-level to a ninth-level disk assembly, and then connecting a tie rod so that the bottom end of the tie rod is connected to a connecting block, and the upper end of the tie rod is clamped in a tie rod connection slot; shaking a pressure pump that provides pressure to an actuator so that the axial load reaches the assembly load of the press-fitting of the high-pressure compressor rotor; and waiting for the third-level disk to be assembled. After the shaft returns to room temperature, tighten the inner cavity nut and remove the upper pressure plate; then heat the grate disc, the temperature of the heated grate disc is ≯177℃, and keep it warm for 20~30min; then install the heated grate disc at the rear end of the fourth to ninth stage disc assembly, and install the upper pressure plate at the rear end of the grate disc, and connect the pull rod again; shake the pressure pump that provides pressure to the actuator cylinder so that the axial load reaches the assembly load of the high-pressure compressor rotor press again; after the grate disc returns to room temperature, tighten the clamping nut, remove the upper pressure plate and the high-pressure compressor rotor to complete the entire transfer; the upper pressure plate used in the assembly process is a model suitable for the press assembly of the high-pressure compressor rotor. During the press assembly process, in order to ensure the stability of the load application process of the press assembly device, a tension sensor is used to calibrate the cavity pressure and tension linearity of the actuator cylinder of the device. Specific embodiment 7: This embodiment further explains the preparatory work before press assembly on the basis of specific embodiment 6. Preparatory work is required before press assembly, and the preparatory work includes: conducting core engine rotor strength simulation analysis in advance to clarify the maximum applied load; then, according to the core engine rotor strength simulation analysis, a customized press assembly pressure value is output, and a simulation analysis is carried out according to the product measurement deformation results; finally, the press assembly load of the high-pressure compressor rotor is determined according to the connection characteristics of the high-pressure compressor rotor, the shape and position status of the components under different load tests, and the allowable margin.

[0045] The purpose of carrying out core engine rotor strength simulation analysis in advance is to ensure that the axial load has no impact on the product structure. Specific embodiment 8: The method for assembling a high-pressure turbine rotor using any of the above-mentioned devices comprises the following steps: placing a lower base suitable for press-fitting the high-pressure turbine rotor at the center of the top surface of the mounting seat, and installing the high scroll on the base; cooling the front stop of the high scroll and the rear stop of the drum shaft with liquid nitrogen; installing the front sealing plate on the high scroll, and then dropping the drum shaft; installing the upper pressure plate used when the drum shaft is located at the top of the component at the front end of the drum shaft, and connecting the pull rod; shaking the pressure pump that provides pressure for the actuator so that the measured axial load reaches the assembly load of the press-fitting of the high-pressure turbine rotor; tightening the front bolts of the plate after the front sealing plate and the drum shaft return to room temperature, and removing the upper pressure plate used when the drum shaft is located at the top of the component. The upper pressure plate when the drum shaft is on the top; after the rotor assembly is turned 180°, the drum shaft is installed on the lower base, and the rear stop of the high scroll is cooled by liquid nitrogen; the rear shaft is installed at the rear end of the high scroll, and the upper pressure plate used when the drum shaft is located on the top surface of the lower base is installed at the rear end of the rear shaft, and the pull rod is connected; the pressure pump that provides pressure to the actuator cylinder is shaken to make the measured axial load reach the assembly load of the high-pressure turbine rotor press-fit; after the rear shaft returns to room temperature, the bolts behind the disk are tightened, and the upper pressure plate and the high-pressure turbine rotor used when the drum shaft is located on the top surface of the lower base are removed. During the press-fitting process, in order to ensure the stability of the load application process of the press-fitting device, a tension sensor is used to calibrate the cavity pressure and tension linearity of the actuator cylinder of the device. Specific embodiment 9: This embodiment further explains the preparatory work before press assembly on the basis of Specific Embodiment 8. Preparatory work is required before press assembly, and the preparatory work includes: conducting a core engine rotor strength simulation analysis in advance to clarify the maximum applied load; then, according to the core engine rotor strength simulation analysis, a customized press assembly pressure value is output, and a simulation analysis is carried out based on the product measurement deformation results; finally, the high-pressure compressor rotor press assembly load is determined based on the connection characteristics of the high-pressure turbine rotor, the shape and position status of the components under different load tests, and the allowable margin.

[0048] Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments, or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A device for press-fitting and assembling a rotor of an aircraft engine core, comprising a support rod (1), a mounting seat (2), a pull rod (3) and an upper pressure plate (4) arranged in sequence from top to bottom, a lower base (5) being also arranged at the center of the top surface of the mounting seat (2), connecting blocks (6) being evenly arranged on the top surface of the mounting seat (2) around the lower base (5), the bottom of the connecting block (6) passing downward through the mounting seat (2) and connected to an actuating cylinder (7) arranged at the bottom of the mounting seat (2), the bottom of the pull rod (3) being connected to the connecting block (6), a pull rod connecting slot (41) being provided at the edge of the upper pressure plate (4) facing the pull rod (3), a pressure sensor and an electronic display screen (8) being also provided on the top surface of the lower base (5), the pressure sensor being located between the rotor and the lower base (5), and the pressure sensor being connected to the electronic display screen (8) via an electrical signal.

2. The device for press-fitting and assembling the rotor of the core machine of an aircraft engine according to claim 1, characterized in that: A universal wheel (11) is provided at the bottom of the support rod (1).

3. The device for press-fitting and assembling the rotor of the core machine of an aircraft engine according to claim 1, characterized in that: The support rod (1) is a liftable support rod.

4. The device for press-fitting and assembling the rotor of the core machine of an aircraft engine according to claim 1, characterized in that: The lower base (5) has two models, one model of the lower base is suitable for press-fitting the high-pressure compressor rotor, and the other model of the lower base is suitable for press-fitting the high-pressure turbine rotor.

5. The device for press-fitting and assembling the rotor of the core machine of an aircraft engine according to claim 1, characterized in that: The upper pressure plate (4) has three models, two of which are suitable for press-fitting the high-pressure turbine rotor, and another type of upper pressure plate is suitable for press-fitting the high-pressure compressor rotor. The upper pressure plate suitable for press-fitting the high-pressure turbine rotor includes an upper pressure plate used when the drum shaft is located at the top of the component and an upper pressure plate used when the drum shaft is located on the top surface of the lower base.

6. A method for assembling a high pressure compressor rotor using the device according to any one of claims 1 to 5, characterized in that: The method comprises the following steps: placing a lower base suitable for press-fitting the high-pressure compressor rotor at the center of the top surface of the mounting seat, and installing the first and second disc assemblies on the lower base; heating the third disc shaft to a temperature of ≯177°C, and keeping the temperature for 20 to 30 minutes, and then installing the heated third disc shaft on the first and second disc assemblies, and then installing the fourth to ninth disc assemblies; after installing the fourth to ninth disc assemblies, installing the upper pressure plate on the rear end of the fourth to ninth disc assemblies, and then connecting the tie rod, so that the bottom end of the tie rod is connected to the connecting block, and the upper end of the tie rod is clamped in the tie rod connecting groove; shaking the pressure pump that provides pressure for the actuator so that the axial load reaches the assembly load of the high-pressure compressor rotor press-fitting; and tightening the inner cavity screw after the third disc shaft returns to room temperature. nut, remove the upper pressure plate; then heat the grate disc, the temperature of the heated grate disc is ≯177℃, and keep it warm for 20~30min; then install the heated grate disc at the rear end of the four-nine disc assembly, and install the upper pressure plate at the rear end of the grate disc, and connect the pull rod again; shake the pressure pump that provides pressure to the actuator cylinder so that the axial load reaches the assembly load of the high-pressure compressor rotor press again; after the grate disc returns to room temperature, tighten the clamping nut, remove the upper pressure plate and the high-pressure compressor rotor to complete the entire transfer; the upper pressure plate used in the assembly process is a model suitable for the press assembly of the high-pressure compressor rotor. During the press assembly process, in order to ensure the stability of the load application process of the press assembly device, a tension sensor is used to calibrate the cavity pressure and tension linearity of the actuator cylinder of the device.

7. The method for assembling a high-pressure compressor rotor according to claim 6, characterized in that: Preparatory work is required before press assembly, which includes: conducting core engine rotor strength simulation analysis in advance to clarify the maximum applied load; then, according to the core engine rotor strength simulation analysis, output a customized press assembly pressure value, and conduct simulation analysis based on the product measurement deformation results; finally, determine the high-pressure compressor rotor press assembly load based on the connection characteristics of the high-pressure compressor rotor, the shape and position status of the components under different load tests, and the allowable margin.

8. A method for assembling a high-pressure turbine rotor using a device according to any one of claims 1 to 5, characterized in that: The method comprises the following steps: placing a lower base suitable for press-fitting of a high-pressure turbine rotor at the center of the top surface of a mounting seat, and installing a high-volume disk on the base; cooling a front stop of the high-volume disk and a rear stop of a drum shaft with liquid nitrogen; installing a front sealing disk on the high-volume disk, and then dropping the drum shaft; installing an upper pressure plate used when the drum shaft is located at the top of a component at the front end of the drum shaft, and connecting a pull rod; shaking a pressure pump that provides pressure to an actuator so that the measured axial load reaches an assembly load for press-fitting of a high-pressure turbine rotor; tightening the front bolts of the disk after the front sealing disk and the drum shaft return to room temperature, and removing the upper pressure plate used when the drum shaft is located at the top of the component; and rotor assembly. After flipping 180°, install the drum shaft on the lower base, and cool the rear stop of the high scroll disk with liquid nitrogen; install the rear shaft on the rear end of the high scroll disk, and install the upper pressure plate used when the drum shaft is located on the top surface of the lower base on the rear end of the rear shaft, and connect the pull rod; shake the pressure pump that provides pressure to the actuator cylinder so that the measured axial load reaches the assembly load of the high-pressure turbine rotor press-fit; after the rear shaft returns to room temperature, tighten the bolts behind the disk, remove the upper pressure plate and the high-pressure turbine rotor used when the drum shaft is located on the top surface of the lower base, and during the press-fitting process, in order to ensure the stability of the load application process of the press-fitting device, a tension sensor is used to calibrate the cavity pressure and tension linearity of the actuator cylinder of the device.

9. The method for assembling a high-pressure turbine rotor according to claim 7, characterized in that: Preparatory work is required before press assembly, which includes: conducting core engine rotor strength simulation analysis in advance to clarify the maximum applied load; then, according to the core engine rotor strength simulation analysis, output a customized press assembly pressure value, and conduct simulation analysis based on the product measurement deformation results; finally, determine the high-pressure compressor rotor press assembly load based on the connection characteristics of the high-pressure turbine rotor, the shape and position status of the components under different load tests, and the allowable margin.

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