Aero-engine high-pressure compressor assembly platform and method

Abstract

The application discloses an aero-engine high-pressure compressor assembling platform and method, and the assembling platform comprises a stator mounting seat for assembling a stator casing, the stator casing is provided with a stop opening, and the stator mounting seat comprises an upper mounting plate, the upper end surface of the upper mounting plate is sequentially provided with a supporting surface and a sliding surface from inside to outside, the sliding surface is used for supporting the stop opening of the stator casing to slide in the assembling process, the supporting surface is used for supporting the stator casing to maintain a stationary state, the height of the sliding surface is H1, the height of the supporting surface is H2, the height of the stop opening of the stator casing is h, the gap between the blade of the adjacent rotor and the adjacent stator blade is d, and H2-H1-h<d. By controlling H2-H1-h to be less than the gap d between the blade of the adjacent rotor and the adjacent stator blade, the stator blade will not collide with the rotor blade when the displacement of the up-and-down shaking of the stator casing occurs in the assembling process.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine assembly and measurement technology, and particularly relates to an aero-engine high-pressure compressor assembly platform and method. Background Technology

[0002] The high-pressure compressor of an aero-engine consists of a compressor rotor, a front stator split casing, and a rear stator split casing. During the assembly process, the compressor rotor blades and the stator blades of the split casing have relatively small clearances. Especially when the compressor rotor rotates, the compressor rotor blades and the stator blades of the split casing are prone to collision, which can damage the product. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to overcome the defect in the prior art that the rotor blades and stator blades are prone to collision when the rotor rotates during the compressor assembly process, and to provide an assembly platform and method for a high-pressure compressor of an aero-engine.

[0004] The present invention solves the above-mentioned technical problems through the following technical solution:

[0005] An assembly platform for a high-pressure compressor of an aero-engine includes a stator mounting base for assembling a stator casing. The stator casing has a stop. The stator mounting base includes an upper mounting plate. The upper end surface of the upper mounting plate has a support surface and a sliding surface from the inside out. The sliding surface supports the stop of the stator casing to slide during assembly. The support surface supports the stator casing to maintain a stationary state. The height of the sliding surface is H1, the height of the support surface is H2, the height of the stop of the stator casing is h, the clearance between adjacent rotor blades and adjacent stator blades is d, H2 is greater than H1, and H2-H1-h. <d。

[0006] In this design, the upper mounting plate of the stator mounting base serves to support the stator casing during compressor assembly. From the inside out, the upper mounting plate consists of a support surface and a sliding surface, with the support surface slightly higher than the sliding surface. From the initial installation stage to the final assembly position, the stator casing slowly slides from the sliding surface to the support surface. During this sliding phase, the stator casing primarily relies on the stop portion for support. Because the stop portion of the stator casing is slightly higher than the main body of the stator casing, the main body of the stator casing is suspended on the sliding surface. As it slowly slides to the support surface, the main body of the stator casing gradually abuts against the support surface. Due to the height difference between the support surface and the sliding surface being greater than the height of the stop portion, the stator casing experiences a slight increase in height (H2-H1-h) from the initial installation stage to the final assembly position. By controlling H2-H1-h to be less than the gap d between adjacent rotor blades and adjacent stator blades, the stator blades will not collide with the rotor blades during the vertical displacement caused by the stator casing's vertical movement during assembly.

[0007] Preferably, the aero-engine high-pressure compressor assembly platform further includes a rotor mounting base. The stator mounting base includes a lower mounting plate and a connecting plate. The upper mounting plate and the lower mounting plate are connected by the connecting plate. The rotor mounting base includes a rotor base, which is disposed on the lower mounting plate and located between the upper mounting plate and the lower mounting plate. The rotor base has a through hole and a receiving cavity. The receiving cavity is used to receive the front journal of the rotor. The through hole communicates with the receiving cavity. The aero-engine high-pressure compressor assembly platform also includes a measuring device. The measuring device is used to measure the runout of the front journal of the rotor through the through hole toward the receiving cavity.

[0008] In this design, the rotor mounting base is fixed between the upper and lower mounting plates via a rotor base. The rotor base has a receiving cavity to accommodate the front journal of the rotor, and the rotor base also has a through hole that communicates with the receiving cavity. The detection device can directly monitor the runout of the front journal of the compressor rotor during compressor assembly through the through hole. By correcting the runout measurement value, the impact of rotational error during rotor assembly can be reduced.

[0009] Preferably, there are multiple connecting plates, at least one of which is eccentrically arranged relative to the rotor shaft center, and the measuring device is arranged on the eccentrically arranged connecting plate so as to face the rotor shaft center.

[0010] In this design, the measuring device is mounted on the connecting plate, which serves both as a connection between the upper and lower mounting plates and as a base for the measuring device. This eliminates the need for a separate measuring base, resulting in a more compact compressor assembly platform and lower production costs. Considering the distance between the measuring part of the measuring device and its mounting surface, the connecting plate, acting as the mounting base, is eccentrically positioned relative to the rotor shaft. This ensures that the measuring part of the measuring device is directly aligned with the center of the rotor's front journal, guaranteeing the accuracy of the measurement data.

[0011] Preferably, the rotor base is provided with a first convex stop, and the lower mounting plate is provided with a first concave stop, the first convex stop and the first concave stop cooperating.

[0012] In this design, a first convex stop and a first concave stop are respectively provided on the rotor base and the lower mounting plate to ensure that the rotor and the stator are arranged coaxially.

[0013] Preferably, the rotor mounting base includes a bearing assembly and a bushing, the bushing being used to house the front journal of the rotor, the bearing assembly being disposed on the rotor base, and the bushing being rotatably disposed on the bearing assembly.

[0014] In this solution, the above-mentioned structure is adopted. The bushing is rotatably mounted on the bearing device of the rotor mounting base. The front journal of the rotor can rotate freely relative to the rotor base through the bushing. This avoids direct contact between the front journal of the rotor and the bearing device, and prevents the front journal of the rotor from wearing during rotation, thus reducing the accuracy of the compressor.

[0015] Preferably, the bearing assembly includes a tapered roller bearing, and the bushing is rotatably mounted on the tapered roller bearing.

[0016] In this design, the tapered roller bearing is fitted outside the bushing and located between the rotor base and the bushing. The tapered roller bearing can withstand radial and axial combined loads, which are mainly radial, allowing the assembly platform to support a large rotor and ensuring the rotor's rotational accuracy.

[0017] Preferably, the bearing assembly includes a bearing housing and an adjusting shim, the tapered roller bearing is disposed on the bearing housing, and the bearing housing is disposed on the rotor base via the adjusting shim.

[0018] In this design, the tapered roller bearing is mounted on a bearing housing, which in turn is mounted on the rotor base via adjusting shims. During assembly, workers can adjust the adjusting shims to control the height difference between the rotor blades and the stator blades. This adjustment method is relatively easy and cost-effective to manufacture and maintain, and it also prevents the rotor blades from colliding with the stator blades.

[0019] Preferably, the bearing assembly includes a sliding bearing disposed on the rotor base, the upper part of the bushing is rotatably disposed on the tapered roller bearing, and the lower part of the bushing is clearance-fitted with the sliding bearing.

[0020] In this design, a tapered roller bearing is rotatably mounted on the upper part of the bushing, and a sliding bearing is mounted on the lower part of the bushing. When the bushing rotates relative to the tapered roller bearing, the lower part of the bushing rotates synchronously within the sliding bearing. At the same time, due to the clearance fit between the lower part of the bushing and the sliding bearing, the radial displacement of the bushing is small, which can further improve the accuracy of the rotor rotation and prevent the rotor blades from colliding with the stator blades.

[0021] Preferably, the rotor mounting base includes a support plate and a pin. The support plate is fixedly disposed at the end of the bushing. The support plate is provided with a stop groove. The upper mounting plate is provided with a stop hole. The pin can be inserted into the stop groove and the stop hole.

[0022] In this solution, with the above-described structure, after the rotor has rotated to a suitable angle, the plate can be prevented from rotating relative to the upper mounting plate by inserting a pin into the stop groove and stop hole. That is, the rotor is kept stationary by inserting the pin.

[0023] Preferably, the measuring device includes a measuring base, a measuring part, a locking element, and a fine-tuning device. The measuring base is fixedly mounted on the stator mounting base, the measuring part is movably mounted on the measuring base, the fine-tuning device is used to adjust the position of the measuring part relative to the rotor shaft center, and the locking element is used to lock the measuring part.

[0024] In this design, the fine-tuning device, through the aforementioned structural form, can adjust the radial distance of the measuring section relative to the rotor shaft center, ensuring that the measuring section contacts the outer surface of the rotor's front journal and maintains a certain amount of pressure. After finding the appropriate distance, the measuring section is locked in place by a locking component to maintain it in the ideal position.

[0025] Preferably, the aero-engine high-pressure compressor assembly platform includes a movable base, and the stator mounting base is disposed on the movable base.

[0026] In this design, the high-pressure compressor assembly platform for aero-engines can be moved to a suitable position as needed via a movable base.

[0027] A method for assembling a high-pressure compressor for an aero-engine, using the aforementioned high-pressure compressor assembly platform for an aero-engine, includes the following steps:

[0028] S1. Place the front journal of the rotor into the bushing;

[0029] S2. Rotate the rotor and after the rotor blades are installed, insert the pin into the stop groove and the stop hole;

[0030] S3. Use the measuring device to measure and correct the runout value of the rotor rotation;

[0031] S4. Place the stator housing on the sliding surface and push the stator housing to slide onto the support surface to complete the installation.

[0032] Using this assembly method, the rotor blades and stator blades will not collide during the compressor assembly process, ensuring the product quality of the compressor.

[0033] The positive and progressive effects of this invention are as follows: the upper mounting plate consists of a support surface and a sliding surface from the inside out, with the support surface slightly higher than the sliding surface. From the pre-installation stage to the final assembly stage, the stator casing slowly slides from the sliding surface to the support surface. During this sliding phase, the stator casing primarily relies on the stop portion to support its own weight. Because the stop portion of the stator casing is slightly higher than the main body of the stator casing, the main body of the stator casing is suspended in the air when on the sliding surface. As it slowly slides to the support surface, the main body of the stator casing gradually abuts against the support surface. Since the height difference between the support surface and the sliding surface is greater than the height of the stop portion, the stator casing will slightly increase in height (H2-H1-h) from the installation stage to the final assembly stage. By controlling H2-H1-h to be less than the gap d between adjacent rotor blades and adjacent stator blades, the stator blades will not collide with the rotor blades during the displacement caused by the up-and-down shaking of the stator casing during assembly. Attached Figure Description

[0034] Figure 1 This is a schematic diagram of the assembly platform according to an embodiment of the present invention.

[0035] Figure 2 This is a schematic diagram of the upper mounting plate according to an embodiment of the present invention.

[0036] Figure 3 This is another structural schematic diagram of the upper mounting plate according to an embodiment of the present invention.

[0037] Figure 4 This is a schematic diagram of the structure of the lower mounting plate and connecting plate according to an embodiment of the present invention.

[0038] Figure 5 This is a schematic diagram of the rotor mounting base according to an embodiment of the present invention.

[0039] Figure 6 This is a schematic diagram of the structure of a measuring device according to an embodiment of the present invention.

[0040] Figure 7 This is a flowchart of an assembly method according to an embodiment of the present invention.

[0041] Explanation of reference numerals in the attached figures

[0042] Stator Mounting Base 1

[0043] Upper mounting plate 11

[0044] Support surface 111

[0045] Sliding surface 112

[0046] Lower mounting plate 12

[0047] First concave stop 121

[0048] Connecting plate 13

[0049] Rotor mounting base 2

[0050] Rotor base 21

[0051] Through hole 211

[0052] Reception cavity 212

[0053] First protrusion 213

[0054] Bearing assembly 22

[0055] Tapered roller bearing 221

[0056] Bearing housing 222

[0057] Adjustment pad 223

[0058] 224 sliding bearing

[0059] Bushing 23

[0060] pallet 24

[0061] Stop groove 241

[0062] Pin 25

[0063] Stator Casing 3

[0064] Stop 31

[0065] Rotor 4

[0066] Measuring device 5

[0067] Measuring base 51

[0068] Measurement Department 52

[0069] Locking part 53

[0070] Fine-tuning device 54

[0071] Slide 55

[0072] Mobile base 6

[0073] Main body 61

[0074] Casters 62

[0075] Foot support 63

[0076] Support leg 64

[0077] Handrail 65 Detailed Implementation

[0078] The present invention will be further illustrated by way of embodiments below, but the present invention is not limited to the scope of the embodiments.

[0079] like Figure 1 , Figure 2 , Figure 3 As shown, this embodiment provides an assembly platform for a high-pressure compressor of an aero-engine, including a stator mounting base 1 for assembling a stator casing 3. The stator casing 3 is provided with a stop 31. The stator mounting base 1 includes an upper mounting plate 11. The upper end surface of the upper mounting plate 11 consists of a support surface 111 and a sliding surface 112 from the inside out. The sliding surface 112 is used to support the stop 31 of the stator casing 3 to slide during the assembly process. The support surface 111 is used to support the stator casing 3 to maintain a stationary state. The height of the sliding surface 112 is H1, the height of the support surface 111 is H2, the height of the stop 31 of the stator casing 3 is h, the gap between the blades of adjacent rotors 4 and adjacent stator blades is d, H2 is greater than H1, and H2-H1-h. <d。

[0080] In this embodiment, the upper mounting plate 11 of the stator mounting base 1 serves to support the stator casing 3 during compressor assembly. The upper mounting plate 11 consists of a support surface 111 and a sliding surface 112, arranged from the inside out, with the support surface 111 slightly higher than the sliding surface 112. From the pre-installation stage to the final assembly stage, the stator casing 3 slowly slides from the sliding surface 112 to the support surface 111. While sliding on the sliding surface 112, the stator casing 3 primarily relies on the stop 31 to support its own weight. Since the stop 31 of the stator casing 3 is slightly higher than the main body of the stator casing 3, the main body of the stator casing 3 is suspended on the sliding surface 112. As it slowly slides to the support surface 111, the main body of the stator casing 3 gradually comes into contact with the support surface 111. Because the height difference between the support surface 111 and the sliding surface 112 is greater than the height of the stop 31, the stator casing 3 will slightly increase in height from the installation stage to the final assembly stage, i.e., H2-H1-h. By controlling H2-H1-h to be less than the gap d between the blades of the adjacent rotor 4 and the adjacent stator blades, the stator blades will not collide with the blades of the rotor 4 when the stator casing 3 is displaced by vertical shaking during assembly.

[0081] like Figure 1 and Figure 5 As shown, in a preferred embodiment, the high-pressure compressor assembly platform for aero-engines also includes a rotor mounting base 2. The stator mounting base 1 includes a lower mounting plate 12 and a connecting plate 13. The upper mounting plate 11 and the lower mounting plate 12 are connected by the connecting plate 13. The rotor mounting base 2 includes a rotor base 21, which is disposed on the lower mounting plate 12 and located between the upper mounting plate 11 and the lower mounting plate 12. The rotor base 21 is provided with a through hole 211 and a receiving cavity 212. The receiving cavity 212 is used to receive the front journal of the rotor 4. The through hole 211 communicates with the receiving cavity 212. The high-pressure compressor assembly platform for aero-engines also includes a measuring device 5, which is directed through the through hole 211 toward the receiving cavity 212 to measure the runout of the front journal of the rotor 4.

[0082] The rotor mounting base 2 is fixedly mounted between the upper mounting plate 11 and the lower mounting plate 12 via the rotor base 21. The rotor base 21 is provided with a receiving cavity 212 for accommodating the front journal of the rotor 4. The rotor base 21 is also provided with a through hole 211 that communicates with the receiving cavity 212. The detection device can directly monitor the runout of the front journal of the compressor rotor 4 during compressor assembly through the through hole 211. By correcting the runout measurement value, the influence of rotation error during rotor 4 assembly is reduced.

[0083] like Figure 4 As shown, in a preferred embodiment, there are 10 connecting plates 13, two of which are eccentrically arranged relative to the rotor 4 shaft center. The measuring device 5 is mounted on one of these two connecting plates 13 and faces the rotor 4 shaft center. The remaining eight connecting plates 13 are facing the rotor 4 shaft center and are arranged axially symmetrically.

[0084] The measuring device 5 is mounted on the connecting plate 13, which serves both to connect the upper mounting plate 11 and the lower mounting plate 12 and as a base for the measuring device 5. This eliminates the need for a separate measuring base 51, resulting in a more compact compressor assembly platform structure and lower production costs. Considering the distance between the measuring part of the measuring device 5 and its mounting surface, the connecting plate 13, acting as a mounting base, is eccentrically positioned relative to the rotor 4's shaft center. This ensures that the measuring part of the measuring device 5 is directly aligned with the shaft center of the front journal of the rotor 4, thereby guaranteeing the accuracy of the measurement data.

[0085] In an alternative embodiment, the measuring device may not be mounted on the connecting plate 13. Instead, a separate mounting plate may be provided to support and mount the measuring device, as long as the measuring part of the measuring device is aligned with the center of the front journal of the rotor 4.

[0086] like Figure 5 As shown, in a preferred embodiment, the rotor base 21 is provided with a first convex stop 213, and the lower mounting plate 12 is provided with a first concave stop 121, the first convex stop 213 and the first concave stop 121 cooperating.

[0087] In this embodiment, a first convex stop 213 and a first concave stop 121 that cooperate with each other are respectively provided on the rotor base 21 and the lower mounting plate 12, which can ensure that the rotor 4 and the stator are arranged coaxially.

[0088] like Figure 5 As shown, in a preferred embodiment, the rotor mounting base 2 includes a bearing device 22 and a bushing 23. The bushing 23 is used to place the front journal of the rotor 4. The bearing device 22 is disposed on the rotor base 21, and the bushing 23 is rotatably disposed on the bearing device 22.

[0089] With the above-mentioned structure, the bushing 23 is rotatably mounted on the bearing device 22 of the rotor mounting base 2. The front journal of the rotor 4 can rotate freely relative to the rotor base 21 through the bushing 23, which can avoid direct contact between the front journal of the rotor 4 and the bearing device 22, and prevent the front journal of the rotor 4 from wearing during rotation, thus reducing the accuracy of the compressor.

[0090] In a preferred embodiment, the bearing assembly 22 includes a tapered roller bearing 221, and a bushing 23 is rotatably mounted on the tapered roller bearing 221.

[0091] The tapered roller bearing 221 is sleeved on the outside of the bushing 23 and located between the rotor base 21 and the bushing 23. The tapered roller bearing 221 can withstand radial and axial combined loads, with radial load being the main component. The rotor 4 is placed on the tapered roller bearing 221 through the bushing 23, so that the assembly platform can support the large rotor 4 and ensure the rotational accuracy of the rotor 4.

[0092] In a preferred embodiment, the bearing assembly 22 includes a bearing housing 222 and an adjusting shim 223. A tapered roller bearing 221 is disposed on the bearing housing 222, and the bearing housing 222 is disposed on the rotor base 21 via the adjusting shim 223.

[0093] The tapered roller bearing 221 is mounted on the bearing housing 222, which in turn is mounted on the rotor base 21 via an adjusting shim 223. During assembly, workers can adjust the adjusting shim 223 to control the height difference between the rotor blades 4 and the stator blades. This adjustment method is relatively easy to manufacture and maintain, and also prevents the rotor blades 4 from colliding with the stator blades.

[0094] In a preferred embodiment, the bearing device 22 includes a sliding bearing 224, which is disposed on the rotor base 21. The upper part of the bushing 23 is rotatably disposed on the tapered roller bearing 221, and the lower part of the bushing 23 is clearance-fitted with the sliding bearing 224.

[0095] In this embodiment, a tapered roller bearing 221 is rotatably provided on the upper part of the bushing 23, and a sliding bearing 224 is provided on the lower part of the bushing 23. When the bushing 23 rotates relative to the tapered roller bearing 221, the lower part of the bushing 23 rotates synchronously within the sliding bearing 224. At the same time, due to the clearance fit between the lower part of the bushing 23 and the sliding bearing 224, the radial displacement of the bushing 23 is small, which can further improve the accuracy of the rotor 4 during rotation and prevent the rotor 4 blades from colliding with the stator blades.

[0096] In a preferred embodiment, the rotor mounting base 2 includes a support plate 24 and a pin 25. The support plate 24 is fixedly disposed at the end of the bushing 23. The support plate 24 is evenly provided with a plurality of stop grooves 241 along the circumference. The upper mounting plate 11 is provided with a stop hole. The pin 25 can be inserted into the stop grooves 241 and the stop hole.

[0097] With the above structure, after the rotor 4 has rotated to a suitable angle, the pin 25 can be inserted into the stop groove 241 and the stop hole to prevent the support plate 24 from rotating relative to the upper mounting plate 11. That is, the rotor 4 is kept fixed by inserting the pin 25.

[0098] like Figure 6 As shown, in a preferred embodiment, the measuring device 5 includes a measuring base 51, a measuring part 52, a locking member 53, and a fine-tuning device 54. The measuring base 51 is fixedly mounted on the connecting plate 13. The measuring part 52 is a circular runout measuring instrument and is movably mounted on the measuring base 51. The fine-tuning device 54 is used to adjust the position of the measuring part 52 relative to the axis of the rotor 4. The locking member 53 is used to lock the measuring part 52.

[0099] The measuring base 51 is provided with a slide groove 55, within which the measuring part 52 can move. Through this structure, the fine-tuning device 54 can adjust the movement of the measuring part 52 within the slide groove 55 to change its radial distance relative to the axis of the rotor 4, ensuring that the measuring part 52 contacts the outer surface of the front journal of the rotor 4 and maintains a certain amount of pressure. After finding a suitable distance, the locking member 53 locks the measuring part 52 to maintain it in that ideal position.

[0100] In a preferred embodiment, the aero-engine high-pressure compressor assembly platform includes a movable base 6, on which a stator mounting base 1 is mounted. The movable base 6 comprises a base body 61, casters 62, supports 63, outriggers 64, and handrails 65. The casters 62 are connected to the base body 61, enabling the movable base 6 to be moved within the factory; the supports 63 prevent movement during temporary parking; when compressor assembly is required, the outriggers 64 provide support to ensure the platform's stability; the handrails 65 are located on both sides of the base body, facilitating the platform's movement and repositioning by workers. The aero-engine high-pressure compressor assembly platform can be moved to a suitable position as needed via the movable base 6.

[0101] like Figure 7 As shown, this embodiment also provides a method for assembling a high-pressure compressor for an aero-engine, using the aforementioned aero-engine high-pressure compressor assembly platform. The assembly method includes the following steps:

[0102] S1. Place the front journal of rotor 4 into bushing 23;

[0103] S2. Rotate rotor 4. After completing the installation of rotor 4 blades, insert pin 25 into stop groove 241 and stop hole.

[0104] S3. Use measuring device 5 to measure and correct the runout value of rotor 4 during rotation;

[0105] S4. Place the stator housing 3 on the sliding surface 112 and push the stator housing 3 to slide it onto the support surface 111 to complete the installation.

[0106] Using this assembly method, the rotor blades and stator blades will not collide during the compressor assembly process, ensuring the product quality of the compressor.

[0107] While specific embodiments of the present invention have been described above, those skilled in the art should understand that these are merely illustrative examples, and the scope of protection of the present invention is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but all such changes and modifications fall within the scope of protection of the present invention.

Claims

1. An assembly platform for a high-pressure compressor of an aero-engine, comprising a stator mounting base for assembling a stator casing, wherein the stator casing is provided with a stop, characterized in that, The stator mounting base includes an upper mounting plate. The upper surface of the upper mounting plate, from the inside out, consists of a support surface and a sliding surface. The sliding surface supports the stator housing's stop during assembly, allowing it to slide. The support surface supports the stator housing to maintain a stationary state. The height of the sliding surface is H1, the height of the support surface is H2, the height of the stator housing's stop is h, the gap between adjacent rotor blades and adjacent stator blades is d, H2 is greater than H1, and H2 - H1 - h. <d; The aero-engine high-pressure compressor assembly platform also includes a rotor mounting base. The stator mounting base includes a lower mounting plate and a connecting plate. The upper mounting plate and the lower mounting plate are connected by the connecting plate. The rotor mounting base includes a rotor base. The rotor base is disposed on the lower mounting plate and located between the upper mounting plate and the lower mounting plate. The rotor base is provided with a through hole and a receiving cavity. The receiving cavity is used to accommodate the front journal of the rotor. The through hole communicates with the receiving cavity. The aero-engine high-pressure compressor assembly platform also includes a measuring device, which measures the runout of the rotor's front journal through the through hole toward the receiving cavity.

2. The aero-engine high-pressure compressor assembly platform as described in claim 1, characterized in that, The number of connecting plates is multiple, and at least one of the multiple connecting plates is eccentrically arranged relative to the rotor shaft center. The measuring device is arranged on the eccentrically arranged connecting plate so as to face the rotor shaft center.

3. The aero-engine high-pressure compressor assembly platform as described in claim 1, characterized in that, The rotor base is provided with a first convex stop, and the lower mounting plate is provided with a first concave stop, the first convex stop and the first concave stop cooperating.

4. The aero-engine high-pressure compressor assembly platform as described in claim 1, characterized in that, The rotor mounting base includes a bearing assembly and a bushing. The bushing is used to house the front journal of the rotor. The bearing assembly is disposed on the rotor base, and the bushing is rotatably disposed on the bearing assembly.

5. The aero-engine high-pressure compressor assembly platform as described in claim 4, characterized in that, The bearing assembly includes a tapered roller bearing, and the bushing is rotatably mounted on the tapered roller bearing.

6. The aero-engine high-pressure compressor assembly platform as described in claim 5, characterized in that, The bearing assembly includes a bearing housing and an adjusting shim. The tapered roller bearing is mounted on the bearing housing, and the bearing housing is mounted on the rotor base via the adjusting shim.

7. The aero-engine high-pressure compressor assembly platform as described in claim 5, characterized in that, The bearing assembly includes a sliding bearing mounted on the rotor base, the upper part of the bushing being rotatably mounted on the tapered roller bearing, and the lower part of the bushing being clearance-fitted with the sliding bearing.

8. The aero-engine high-pressure compressor assembly platform as described in claim 7, characterized in that, The rotor mounting base includes a support plate and a pin. The support plate is fixedly disposed at the end of the bushing. The support plate is provided with a stop groove. The upper mounting plate is provided with a stop hole. The pin can be inserted into the stop groove and the stop hole.

9. The aero-engine high-pressure compressor assembly platform as described in claim 1, characterized in that, The measuring device includes a measuring base, a measuring part, a locking element, and a fine-tuning device. The measuring base is fixedly mounted on the stator mounting base, and the measuring part is movably mounted on the measuring base. The fine-tuning device is used to adjust the position of the measuring part relative to the rotor shaft center, and the locking element is used to lock the measuring part.

10. The aero-engine high-pressure compressor assembly platform as described in claim 1, characterized in that, The aero-engine high-pressure compressor assembly platform includes a movable base, and the stator mounting base is disposed on the movable base.

11. A method for assembling a high-pressure compressor for an aero-engine, characterized in that, The aero-engine high-pressure compressor assembly method uses the aero-engine high-pressure compressor assembly platform as described in claim 8, and the assembly method includes the following steps: S1. Place the front journal of the rotor into the bushing; S2. Rotate the rotor and after the rotor blades are installed, insert the pin into the stop groove and the stop hole; S3. Use the measuring device to measure and correct the runout value of the rotor rotation; S4. Place the stator housing on the sliding surface and push the stator housing to slide onto the support surface to complete the installation.

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