Device and method for simulating abnormal vibration of disc-drum rotor system of aircraft engine

Abstract

A vibration abnormality simulation test device and method for a disc-drum rotor system of an aircraft engine belongs to the technical field of vibration simulation test for aircraft engines. The front support assembly, high-pressure compressor disc assembly, disc-drum combined structure and rear support assembly of the device are arranged on the high-pressure turbine shaft in sequence, the front support assembly is placed on the front bracket assembly, and the rear support assembly is placed on the rear bracket assembly. The method is: connect the high-pressure turbine shaft to the drive motor through an elastic coupling; arrange a sensor for measuring the vibration abnormality of the rotor system; start the drive motor after adjusting the device to a preset abnormal state, and aggregate the data collected by the sensor to a computer for analysis. The present invention has a high structural similarity and dynamic similarity with a real aircraft engine disc-drum rotor system, the structural design is more concise and reasonable, and the vibration transmission is good, and it can more realistically simulate the working state and abnormal vibration characteristics of the connection interface of the elastic support structure and the disc-drum combined structure.

Description

Technical Field

[0001] The invention belongs to the technical field of aviation engine vibration simulation test, and in particular relates to an aviation engine disc-drum rotor system vibration abnormality simulation test device and method. Background Art

[0002] As the core component of modern aviation equipment, the reliability and stability of aircraft engines are directly related to the performance and service safety of the whole machine. As the core component of aircraft engines, the disc-drum rotor system is easily affected by complex assembly factors such as bolt connections and is prone to abnormal vibration under the action of high-speed rotation and complex loads. With the continuous improvement of performance requirements and operational reliability of modern aircraft engines, the vibration characteristics of the disc-drum rotor system and the ability of elastic supports to suppress vibration have become key factors in aircraft engine design and ensuring its service safety.

[0003] The vibration anomalies of the disc-drum rotor system of an aircraft engine mainly include vibration amplitude that is too large exceeding the allowable value, vibration effective value fluctuation that exceeds the tolerance value, and sudden increase or decrease in vibration. If these vibration anomalies occur during the test run and service of the aircraft engine, they will seriously affect the overall safety of the aircraft engine.

[0004] There are many factors that lead to abnormal vibration of the disc-drum rotor system of aircraft engines, including residual preload unevenness of bolted connections, nonlinearity of elastic supports, rolling bearing damage, etc. The existence of any single factor or the coupling of multiple factors will cause complex vibration problems in the disc-drum rotor system.

[0005] Therefore, in order to understand the dynamic characteristics of the disc-drum rotor system of an aircraft engine, it is necessary to clarify the generation mechanism of abnormal vibration, key sensitive factors and vibration evolution laws, and it is necessary to carry out relevant experimental research.

[0006] However, considering the test cost and time period, there are great limitations in conducting experimental research on vibration abnormality sensitive factors on real aircraft engines. In addition, due to the structural complexity of aircraft engines, existing technical means have not been able to achieve direct acquisition of rotor system vibration data. Since there are constraints on the direct acquisition of test data, the test data obtained under the existing technical means cannot truly reflect the abnormal vibration characteristics of the disc-drum rotor system.

[0007] In addition, although numerical simulation technology, as one of the existing technical means, can restore the disc-drum rotor system of an aircraft engine more realistically in structure, it cannot accurately simulate the working state of the rotor system, and it is even more difficult to accurately analyze the complex nonlinear behavior caused by the coupled vibration of bolted connections and elastic supports.

[0008] At present, most of the existing related test devices adopt a disc-shaft rigid support structure, without considering the state of the elastic support structure and the state of the connection interface of the disc-drum combined structure. There is a big difference in structure from the actual aircraft engine disc-drum rotor system, and it cannot truly simulate the abnormal vibration characteristics of the disc-drum rotor system. Summary of the invention

[0009] In view of the problems existing in the prior art, the present invention provides a vibration abnormality simulation test device and method for an aircraft engine disk-drum rotor system. Compared with a real aircraft engine disk-drum rotor system, the device and method have higher structural similarity and dynamic similarity, a simpler and more reasonable structural design and good vibration transmission performance, and can more realistically simulate the working state of the connection interface between the elastic support structure and the disk-drum combination structure, and thus more realistically simulate the working state of the disk-drum rotor system, as well as more realistically simulate the abnormal vibration characteristics of the disk-drum rotor system, so that the analysis of the complex nonlinear behavior caused by the coupled vibration of the bolt connection and the elastic support is more accurate.

[0010] In order to achieve the above-mentioned purpose, the present invention adopts the following technical scheme: an abnormal vibration simulation test device for a disc-drum rotor system of an aircraft engine, comprising a front bracket assembly, a front support assembly, a high-pressure compressor disc assembly, a disc-drum combination structure, a rear support assembly, a rear bracket assembly and a high-pressure turbine shaft; the high-pressure turbine shaft is arranged horizontally; the front support assembly, the high-pressure compressor disc assembly, the disc-drum combination structure and the rear support assembly are arranged sequentially on the high-pressure turbine shaft; the front support assembly is arranged on the front bracket assembly; the rear support assembly is arranged on the rear bracket assembly.

[0011] There are two front bracket assemblies, which are symmetrically distributed on both sides of the front support assembly; the front bracket assembly includes a front bracket base plate, a front bracket column, a front bracket hanging point fastening bolt and a reinforcing rib plate; the front bracket column is vertically fixed above the front bracket base plate; the front bracket hanging point fastening bolt is vertically installed on the top of the front bracket column; the reinforcing rib plate is fixed between the front bracket column and the front bracket base plate, and the reinforcing rib plates are evenly distributed along the circumferential direction of the front bracket column.

[0012] The front support assembly includes a front support web, a front support bearing cone shell, a front support auxiliary plate, a front support hanging point transfer protrusion, a front support squirrel cage, a threaded positioning pin, a front support bearing seat, a front support bearing seat cover and a front support bearing, a first transfer fastening bolt, a second transfer fastening bolt, a third transfer fastening bolt and a fourth transfer fastening bolt, an oil inlet and an oil outlet; the front support bearing is coaxially sleeved on the high-pressure turbine shaft; the front support bearing seat is coaxially fixedly sleeved on the outer ring of the front support bearing; the oil inlet The front support bearing seat is provided with a transparent cover, and the front support bearing seat is coaxially arranged with the front support bearing seat. The front support bearing is located between the transparent cover and the front support bearing seat. The front support cage is fixedly connected to the front support bearing seat by a second transition fastening bolt, and the front support cage is coaxially arranged with the front support bearing seat. The front support bearing, the transparent cover and the front support bearing seat are located between the transparent cover and the front support bearing seat. On the inner side of the front support cage; the front support bearing cone shell is fixedly connected to the front support cage by a third transition fastening bolt, the front support bearing cone shell is coaxially distributed with the front support cage, and the front support cage is located on the inner side of the front support bearing cone shell; the front support auxiliary plate is also fixedly connected to the front support cage and the front support bearing cone shell by a third transition fastening bolt, and the front support auxiliary plate is also circumferentially positioned with the front support bearing cone shell by a threaded locating pin, the front support auxiliary plate is coaxially distributed with the front support bearing cone shell, and the front support auxiliary plate is transparent to the front support bearing seat The cover is distributed on the same side; the front support web is fixedly connected to the front support load-bearing cone shell by a fourth transfer fastening bolt, the front support web and the front support load-bearing cone shell are coaxially distributed, and the front support load-bearing cone shell is located on the inner side of the front support web; the front support hanging point transfer protrusion is fixedly arranged on the edge of the front support web, and the number of the front support hanging point transfer protrusions is two, and the two front support hanging point transfer protrusions are mirror-symmetrically distributed on the left and right sides of the front support web, and the front support hanging point transfer protrusion is fixedly connected to the front support column by the front support hanging point fastening bolt.

[0013] The high-pressure compressor disc assembly includes a concentrated mass disc, a high-pressure compressor disc expansion sleeve and a high-pressure compressor disc expansion tension bolt; the high-pressure compressor disc expansion sleeve is coaxially sleeved on the high-pressure turbine shaft; the concentrated mass disc is coaxially sleeved on the high-pressure compressor disc expansion sleeve; the high-pressure compressor disc expansion tension bolts are evenly distributed on the high-pressure compressor disc expansion sleeve along the circumferential direction.

[0014] The disc-drum assembly structural component comprises a primary sealing disc, a primary sealing disc expansion sleeve, a primary sealing disc expansion tension bolt, a high-pressure turbine front drum, a sealing grate disc, a high-pressure turbine disc, a high-pressure turbine disc expansion sleeve, a high-pressure turbine disc expansion tension bolt, a fifth transition fastening bolt and a sixth transition fastening bolt; the primary sealing disc expansion sleeve is coaxially sleeved on the high-pressure turbine shaft; the primary sealing disc is coaxially sleeved on the primary sealing disc expansion sleeve; the primary sealing disc expansion tension bolts are evenly distributed on the primary sealing disc expansion sleeve along the circumferential direction; the high-pressure turbine disc expansion sleeve is coaxially sleeved on On the high-pressure turbine shaft; the high-pressure turbine disc is coaxially sleeved on the high-pressure turbine disc expansion sleeve; the high-pressure turbine disc expansion tension bolts are evenly distributed on the high-pressure turbine disc expansion sleeve along the circumferential direction; the sealing grate disc is fixedly connected to the high-pressure turbine disc by the fifth transition fastening bolt, and the sealing grate disc and the high-pressure turbine disc are coaxially distributed; one end of the high-pressure turbine front drum is also fixedly connected to the sealing grate disc by the fifth transition fastening bolt, and the other end of the high-pressure turbine front drum is fixedly connected to the first-level sealing disc by the sixth transition fastening bolt, and the high-pressure turbine front drum is coaxially distributed with the high-pressure turbine shaft.

[0015] The rear support assembly comprises a rear support bearing seat, a rear support auxiliary plate, a front sealing ring, a rear support bearing, an oil supply port, a front positioning sleeve, a locking retaining ring, a rear sealing ring, a rear positioning sleeve, an oil drain port and a seventh transition fastening bolt; the rear support bearing is coaxially sleeved on the high-pressure turbine shaft; the rear support bearing seat is coaxially fixedly sleeved on the outer ring of the rear support bearing; the oil supply port and the oil drain port are both arranged on the rear support bearing seat; the front positioning sleeve and the rear positioning sleeve are respectively located on both sides of the rear support bearing, and the front positioning sleeve and the rear positioning sleeve are coaxially distributed with the rear support bearing; the rear support auxiliary plate is fixedly connected to the rear support bearing seat by the seventh transition fastening bolt, and the rear support auxiliary plate is coaxially distributed with the rear support bearing seat; the front sealing ring is arranged between the rear support auxiliary plate and the front positioning sleeve; the rear sealing ring is arranged between the rear support bearing seat and the rear positioning sleeve; the locking retaining ring is coaxially fixedly sleeved on the high-pressure turbine shaft, and the locking retaining ring is close to the rear positioning sleeve.

[0016] The rear bracket assembly includes a rear bracket base plate, a rear bracket column, a rear bracket pressure cover and a rear bracket clamping bolt; the rear bracket column is vertically fixed above the rear bracket base plate, and a lower clamping semicircular groove is arranged on the top of the rear bracket column; the rear bracket pressure cover is located directly above the rear bracket column, and an upper clamping semicircular groove is arranged at the lower part of the rear bracket pressure cover; lower clamping transition protrusions are fixed on the rear bracket columns on both sides of the lower clamping semicircular groove; upper clamping transition protrusions are fixed on the rear bracket pressure cover on both sides of the upper clamping semicircular groove, and the upper clamping transition protrusion and the lower clamping transition protrusion are fixedly connected by the rear bracket clamping bolt; the rear support bearing seat is clamped and fixed between the lower clamping semicircular groove and the upper clamping semicircular groove.

[0017] A vibration abnormality simulation test method for a disk-drum rotor system of an aircraft engine is provided, which adopts the vibration abnormality simulation test device for a disk-drum rotor system of an aircraft engine, and comprises the following steps:

[0018] Step 1: Connect the high-pressure turbine shaft to the drive motor through an elastic coupling;

[0019] Step 2: Arrange sensors for measuring abnormal vibration of the rotor system;

[0020] ①, a first eddy current displacement sensor and a second eddy current displacement sensor are arranged in the circumferential direction of the high-pressure turbine shaft in front of the front support assembly, respectively. The first eddy current displacement sensor is arranged vertically and used to measure the vibration displacement signal of the high-pressure turbine shaft in the vertical direction, and the second eddy current displacement sensor is arranged horizontally and used to measure the vibration displacement signal of the high-pressure turbine shaft in the horizontal direction;

[0021] ②, arrange the first acceleration sensor and the second acceleration sensor in the circumferential direction of the front support bearing cone shell of the front support assembly respectively, the first acceleration sensor is arranged vertically and used to measure the vibration acceleration response signal of the elastic support part of the front support assembly in the vertical direction, and the second acceleration sensor is arranged horizontally and used to measure the vibration acceleration response signal of the elastic support part of the front support assembly in the horizontal direction;

[0022] ③. A third eddy current displacement sensor is arranged axially on the edge of the high-pressure turbine disk of the disk-drum combination structural component, and a fourth eddy current displacement sensor is arranged axially on the edge of the sealing grate disk of the disk-drum combination structural component. The third eddy current displacement sensor and the fourth eddy current displacement sensor are distributed on the same side. The third eddy current displacement sensor is used to measure the vibration displacement signal of the high-pressure turbine disk in the axial direction, and the fourth eddy current displacement sensor is used to measure the vibration displacement signal of the sealing grate disk in the axial direction.

[0023] ④. Arrange a third acceleration sensor on the top of the rear bracket gland of the rear bracket assembly, and arrange a fourth acceleration sensor on the side of the rear bracket gland of the rear bracket assembly. The third acceleration sensor is arranged vertically and used to measure the vibration acceleration response signal of the bearing support part of the rear bracket assembly in the vertical direction. The fourth acceleration sensor is arranged horizontally and used to measure the vibration acceleration response signal of the bearing support part of the rear bracket assembly in the horizontal direction.

[0024] Step three: first adjust the aircraft engine disc-drum rotor system vibration abnormality simulation test device to a preset abnormal state, then start the drive motor to drive the high-pressure turbine shaft, the high-pressure compressor disc assembly and the disc-drum combination structure to rotate synchronously, and the first eddy current displacement sensor, the second eddy current displacement sensor, the first acceleration sensor, the second acceleration sensor, the third eddy current displacement sensor, the fourth eddy current displacement sensor, the third acceleration sensor and the fourth acceleration sensor transmit the collected data to the computer, and the collected data is analyzed by the computer.

[0025] Beneficial effects of the present invention:

[0026] The concentrated mass disk of the present invention performs corresponding equivalent treatment with respect to the high-pressure compressor structure and dynamic characteristics of a real aircraft engine, and can more specifically highlight the coupling relationship between the high-pressure turbine disk assembly and the entire rotor system and the influence of the state of the bolt connection interface.

[0027] The high-pressure turbine front drum of the present invention adopts an internal flange connection form between the sealing comb plate and the high-pressure turbine plate, and an external flange connection form is adopted between the first-stage sealing plate and the high-pressure turbine front drum, so that it is consistent with the disk-drum rotor structure of a real aircraft engine, can more realistically reflect the bolt connection boundary conditions of the disk-drum rotor, and is also easy to disassemble; the components of the main part of the disk-drum combination structure of the device are simulated test pieces obtained after the detailed structure is deleted and simplified, which can more realistically reflect the vibration characteristics of the thin-walled cylindrical high-pressure turbine front drum in the rotating state.

[0028] The disc-drum assembly structural component of the present invention is installed on a through-shaft high-pressure turbine shaft, which not only retains the non-coordinated deformation of the connection interface of the disc-drum assembly structural component caused by uneven residual preload, but also ensures that the connection interface of the drum assembly structure will not be completely opened or closed after the bolts are loosened, thereby avoiding safety accidents and ensuring the safety of the test.

[0029] The present invention can simulate abnormal states of the rotor system such as nonlinearity of the connection interface caused by uneven residual pre-tightening of bolts of the disc-drum combined structural parts, nonlinearity of the bolt connection interface of the elastic supporting member of the front support assembly, and nonlinearity caused by bearing deflection or damage, and these abnormal states can exist alone or simultaneously, thereby realizing a true simulation of the vibration abnormality of the disc-drum rotor system, and further simulating the influence of rotor imbalance and misalignment on the dynamic characteristics of the disc-drum rotor system of an aircraft engine and abnormal vibration, and can realize the research on the vibration characteristics and sensitive factors of vibration abnormality of the disc-drum rotor system of an aircraft engine, making up for the lack of current related research, and can also carry out relevant experimental research on the influence of the bolt connection interface state, bearing pitting / peeling and other damage states and other complex assembly and use conditions on the vibration characteristics of the aircraft engine rotor system, and the influence of squirrel cage spring support stiffness on vibration transmission characteristics and vibration abnormality suppression ability. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a structural schematic diagram of the abnormal vibration simulation test device (whole) of the aircraft engine disc-drum rotor system of the present invention;

[0031] Figure 2 It is a structural schematic diagram of the abnormal vibration simulation test device (cross-section view) of the aircraft engine disc-drum rotor system of the present invention;

[0032] Figure 3 It is a schematic structural diagram of the front bracket assembly (whole) of the present invention;

[0033] Figure 4 is a schematic structural diagram of a front support assembly (cross-section view) of the present invention;

[0034] Figure 5 is a schematic structural diagram of a high-pressure compressor disc assembly (cross-section view) of the present invention;

[0035] Figure 6 It is a structural schematic diagram of the disc-drum combined structural member (cross-section view) of the present invention;

[0036] Figure 7 is a schematic structural diagram of a rear support assembly (cross-section view) of the present invention;

[0037] Figure 8 It is a schematic structural diagram of the rear support assembly (whole) of the present invention;

[0038] In the figure, I—front bracket assembly, II—front support assembly, III—high-pressure compressor disc assembly, IV—disc-drum assembly, V—rear support assembly, VI—rear bracket assembly, VII—high-pressure turbine shaft, 1—front bracket bottom plate, 2—front bracket column, 3—front bracket hanging point fastening bolt, 4—strengthening rib plate, 5—front support web plate, 6—front support bearing cone shell, 7—front support auxiliary plate, 8—front support hanging point transfer convex block, 9—front support squirrel cage, 10—threaded positioning pin, 11—front support Support bearing seat, 12-front support bearing seat cover, 13-front support bearing, 14-first transfer fastening bolt, 15-second transfer fastening bolt, 16-third transfer fastening bolt, 17-fourth transfer fastening bolt, 18-lubricating oil inlet, 19-lubricating oil outlet, 20-centralized mass disk, 21-high-pressure compressor disk expansion sleeve, 22-high-pressure compressor disk expansion tension bolt, 23-first-level sealing disk, 24-first-level sealing disk expansion sleeve, 25-first-level sealing disk expansion tension bolt, 2 6—high-pressure turbine front drum, 27—sealing grate disc, 28—high-pressure turbine disc, 29—high-pressure turbine disc expansion sleeve, 30—high-pressure turbine disc expansion tension bolt, 31—fifth transition fastening bolt, 32—rear support bearing seat, 33—rear support auxiliary plate, 34—front sealing ring, 35—rear support bearing, 36—lubricating oil supply port, 37—front positioning sleeve, 38—locking retaining ring, 39—rear sealing ring, 40—rear positioning sleeve, 41—lubricating oil drain port, 42—seventh transition fastening bolt, 43—rear bracket base plate, 44—rear bracket column, 45—rear bracket pressure cover, 46—lower pressing semicircular groove, 47—upper pressing semicircular groove, 48—lower pressing adapter protrusion, 49—upper pressing adapter protrusion, A—first eddy current displacement sensor, B—second eddy current displacement sensor, C—first acceleration sensor, D—second acceleration sensor, E—third eddy current displacement sensor, F—fourth eddy current displacement sensor, G—third acceleration sensor, H—fourth acceleration sensor. DETAILED DESCRIPTION

[0039] The present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0040] like Figures 1 to 8 As shown, a vibration abnormality simulation test device for a disk-drum rotor system of an aircraft engine comprises a front support assembly I, a front support assembly II, a high-pressure compressor disk assembly III, a disk-drum combined structural member IV, a rear support assembly V, a rear support assembly VI and a high-pressure turbine shaft VII; the high-pressure turbine shaft VII is arranged horizontally; the front support assembly II, the high-pressure compressor disk assembly III, the disk-drum combined structural member IV and the rear support assembly V are sequentially arranged on the high-pressure turbine shaft VII; the front support assembly II is arranged on the front support assembly I; the rear support assembly V is arranged on the rear support assembly VI.

[0041] Specifically, the high-pressure turbine shaft VII is a through shaft that runs through the rotor system, which can retain the nonlinear state of the disk-drum connection interface caused by the uneven residual pre-tightening of the bolts, and can also use the through-shaft feature to make the high-pressure turbine shaft VII a safety shaft, thereby ensuring that the drum component of the disk-drum combination structure IV will not be completely opened or broken after the bolts are loosened, thereby improving safety; the front bracket assembly I and the front support assembly II cooperate to form the front fulcrum of the rotor system, and the rear support assembly V and the rear bracket assembly VI cooperate to form the rear fulcrum of the rotor system.

[0042] There are two front bracket components I, and the two front bracket components I are symmetrically distributed on both sides of the front support component II; the front bracket component I includes a front bracket base plate 1, a front bracket column 2, a front bracket hanging point fastening bolt 3 and a reinforcing rib plate 4; the front bracket column 2 is vertically fixed above the front bracket base plate 1; the front bracket hanging point fastening bolt 3 is vertically installed on the top of the front bracket column 2; the reinforcing rib plate 4 is fixed between the front bracket column 2 and the front bracket base plate 1, and the reinforcing rib plates 4 are evenly distributed along the circumferential direction of the front bracket column 2.

[0043] Specifically, the cross-sectional shape of the front bracket column 2 is square, and the front bracket column 2, the front bracket base plate 1 and the reinforcing rib plate 4 are an integrally welded component, which can ensure that the front bracket assembly I has good load-bearing capacity and structural stability. A vertical threaded hole for connecting the front bracket hanging point fastening bolt 3 is processed on the top of the front bracket column 2, and the front bracket hanging point fastening bolt 3 is used to fix the front bracket assembly I and the front support assembly II together.

[0044] The front support assembly II includes a front support web 5, a front support bearing cone shell 6, a front support auxiliary plate 7, a front support hanging point transfer protrusion 8, a front support squirrel cage 9, a threaded positioning pin 10, a front support bearing seat 11, a front support bearing seat cover 12 and a front support bearing 13, a first transfer fastening bolt 14, a second transfer fastening bolt 15, a third transfer fastening bolt 16 and a fourth transfer fastening bolt 17, an oil inlet 18 and an oil outlet 19; the front support bearing 13 is coaxially sleeved on the high-pressure turbine shaft VII; the front support bearing seat 11 is coaxially fixedly sleeved on the outer side of the front support bearing 13 The lubricating oil inlet 18 and the lubricating oil outlet 19 are both arranged on the front support bearing seat 11; the front support bearing seat transparent cover 12 is fixedly connected to the front support bearing seat 11 by a first transition fastening bolt 14, the front support bearing seat transparent cover 12 and the front support bearing seat 11 are coaxially distributed, and the front support bearing 13 is located between the front support bearing seat transparent cover 12 and the front support bearing seat 11; the front support cage 9 is fixedly connected to the front support bearing seat 11 by a second transition fastening bolt 15, the front support cage 9 and the front support bearing seat 11 are coaxially distributed, the front support bearing 13, the front support shaft The bearing seat cover 12 and the front support bearing seat 11 are both located on the inner side of the front support cage 9; the front support bearing cone shell 6 is fixedly connected to the front support cage 9 by a third transition fastening bolt 16, the front support bearing cone shell 6 is coaxially distributed with the front support cage 9, and the front support cage 9 is located on the inner side of the front support bearing cone shell 6; the front support auxiliary plate 7 is also fixedly connected to the front support cage 9 and the front support bearing cone shell 6 by a third transition fastening bolt 16, and the front support auxiliary plate 7 is also circumferentially positioned with the front support bearing cone shell 6 by a threaded locating pin 10, the front support auxiliary plate 7 is coaxially distributed with the front support bearing cone shell 6, and the front support auxiliary plate 7 is coaxially distributed with the front support bearing cone shell 6. Plate 7 is distributed on the same side as the front support bearing seat cover 12; the front support web 5 is fixedly connected to the front support load-bearing cone shell 6 by the fourth adapter fastening bolt 17, the front support web 5 and the front support load-bearing cone shell 6 are coaxially distributed, and the front support load-bearing cone shell 6 is located on the inner side of the front support web 5; the front support hanging point adapter protrusion 8 is fixedly arranged on the edge of the front support web 5, and the number of the front support hanging point adapter protrusions 8 is two, and the two front support hanging point adapter protrusions 8 are mirror-symmetrically distributed on the left and right sides of the front support web 5, and the front support hanging point adapter protrusion 8 is fixedly connected to the front support column 2 by the front support hanging point fastening bolt 3.

[0045] Specifically, the front support bearing 13 adopts a three-point angular contact ball bearing, and the outer ring of the front support bearing 13 is interference-connected with the front support bearing seat 11. The position of the front support bearing 13 is the front fulcrum of the rotor system. The front support bearing 13 is provided with lubricating oil through the lubricating oil inlet 18 and the lubricating oil is discharged through the lubricating oil outlet 19; the front support bearing 13 is axially positioned and fixed by the front support bearing seat cover 12; the front support web 5 adopts a hollow disc structure in the middle, which has the characteristics of high rigidity and not easy to deform, and is more consistent with the real aircraft engine load-bearing casing structure; the front support bearing seat cover 12 and the front support bearing seat 11 are fixedly connected by 12 first transition fastening bolts 14 evenly distributed in the circumferential direction; the front support bearing seat 11 and the front support cage 9 are fixedly connected by 12 second transition fastening bolts 15 evenly distributed in the circumferential direction; the front support cage 9, the front support load-bearing cone shell 6 and the front support auxiliary plate 7 are connected by circumferential direction The front support cage 9 is a hollow cylindrical structure, which is formed by hollowing out a rib-like structure, so that the front support cage 9 has a lower stiffness and better elasticity as a whole, and can play a better vibration reduction role for the vibration from the front support bearing 13; the front support assembly II is similar to the elastic support structure of a real aircraft engine, which not only includes the front support cage 9 with a vibration reduction effect, but also simplifies the cone shell and the web structure in the real aircraft engine, that is, it retains the necessary dynamic characteristics, and realizes the requirement of being consistent with the vibration transmission path of the rotor system of the real aircraft engine, so that the simulation of the vibration characteristics is more realistic.

[0046] The high-pressure compressor disc assembly III includes a concentrated mass disc 20, a high-pressure compressor disc expansion sleeve 21 and a high-pressure compressor disc expansion tension bolt 22; the high-pressure compressor disc expansion sleeve 21 is coaxially sleeved on the high-pressure turbine shaft VII; the concentrated mass disc 20 is coaxially sleeved on the high-pressure compressor disc expansion sleeve 21; the high-pressure compressor disc expansion tension bolt 22 is evenly distributed on the high-pressure compressor disc expansion sleeve 21 along the circumferential direction.

[0047] Specifically, the high-pressure compressor disc expansion sleeve 21 cooperates with 14 high-pressure compressor disc expansion tension bolts 22 evenly distributed in the circumferential direction to realize the keyless connection between the concentrated mass disc 20 and the high-pressure turbine shaft VII. By tightening the high-pressure compressor disc expansion tension bolts 22, a radial expansion force will be generated on the high-pressure compressor disc expansion sleeve 21, thereby generating a huge clamping force between the high-pressure compressor disc expansion sleeve 21 and the concentrated mass disc 20 and the high-pressure turbine shaft VII. At the same time, it has the advantages of high centering accuracy, convenient installation / adjustment / disassembly, high strength, stable and reliable connection, etc. The concentrated mass disc 20 utilizes the equivalent treatment of the concentrated mass method relative to the structure and dynamic characteristics of the high-pressure compressor disc of a real aircraft engine, so that the coupling relationship between the high-pressure turbine disc assembly of the aircraft engine and the entire rotor system and the influence of the state of the bolt connection interface can be highlighted.

[0048] The disc-drum assembly structural member IV comprises a primary sealing disc 23, a primary sealing disc expansion sleeve 24, a primary sealing disc expansion tension bolt 25, a high-pressure turbine front drum 26, a sealing grate disc 27, a high-pressure turbine disc 28, a high-pressure turbine disc expansion sleeve 29, a high-pressure turbine disc expansion tension bolt 30, a fifth transition fastening bolt 31 and a sixth transition fastening bolt; the primary sealing disc expansion sleeve 24 is coaxially sleeved on the high-pressure turbine shaft VII; the primary sealing disc 23 is coaxially sleeved on the primary sealing disc expansion sleeve 24; the primary sealing disc expansion tension bolt 25 is evenly distributed on the primary sealing disc expansion sleeve 24 along the circumferential direction; the high-pressure turbine disc expansion sleeve 29 is coaxially sleeved on On the high-pressure turbine shaft VII; the high-pressure turbine disc 28 is coaxially sleeved on the high-pressure turbine disc expansion sleeve 29; the high-pressure turbine disc expansion tension bolts 30 are evenly distributed on the high-pressure turbine disc expansion sleeve 29 along the circumferential direction; the sealing grate disc 27 is fixedly connected to the high-pressure turbine disc 28 by the fifth transition fastening bolts 31, and the sealing grate disc 27 and the high-pressure turbine disc 28 are coaxially distributed; one end of the high-pressure turbine front drum 26 is also fixedly connected to the sealing grate disc 27 by the fifth transition fastening bolts 31, and the other end of the high-pressure turbine front drum 26 is fixedly connected to the first-level sealing disc 23 by the sixth transition fastening bolts, and the high-pressure turbine front drum 26 is coaxially distributed with the high-pressure turbine shaft VII.

[0049] Specifically, the first-level sealing disk expansion sleeve 24 cooperates with 14 first-level sealing disk expansion tension bolts 25 evenly distributed in the circumferential direction to realize the keyless connection between the first-level sealing disk 23 and the high-pressure turbine shaft VII. By tightening the first-level sealing disk expansion tension bolts 25, a radial expansion force will be generated on the first-level sealing disk expansion sleeve 24, thereby generating a huge clamping force between the first-level sealing disk expansion sleeve 24, the first-level sealing disk 23 and the high-pressure turbine shaft VII. At the same time, it has the advantages of high centering accuracy, easy installation / adjustment / disassembly, high strength, stable and reliable connection, etc. The high-pressure turbine disc expansion sleeve 29 cooperates with 14 high-pressure turbine disc expansion tension bolts 30 evenly distributed in the circumferential direction to realize the keyless connection between the high-pressure turbine disc 28 and the high-pressure turbine shaft VII. By tightening the high-pressure turbine disc expansion tension bolts 30, a radial expansion force will be generated on the high-pressure turbine disc expansion sleeve 29, thereby generating a huge clamping force between the high-pressure turbine disc expansion sleeve 29, the high-pressure turbine disc 28 and the high-pressure turbine shaft VII. At the same time, it has the advantages of high centering accuracy, convenient installation / adjustment / disassembly, high strength, stable and reliable connection, etc. The first-level sealing disc 23 and the high-pressure turbine front drum 26 are connected in the form of an external flange, with circumferential and axial stop positioning, which is easy to disassemble and consistent with the disc-drum combination structure of a real aircraft engine. The geometric structure and size of the first-stage sealing disc 23, the high-pressure turbine front drum 26, the sealing grate disc 27 and the high-pressure turbine disc 28 are obtained by scaling down the disc-drum assembly of the real aircraft engine and are appropriately simplified, retaining the necessary structural features and connection features as well as the circular structural size parameters, etc., which can truly reflect the vibration characteristics of the thin-walled drum assembly in the rotating state. The high-pressure turbine front drum 26 and the sealing grate disc 27 and the high-pressure turbine disc 28 are connected in the form of internal flanges, with circumferential and axial stopper positioning, and are connected and fixed by 24 fifth transfer fastening bolts 31 evenly distributed in the circumferential direction, which is consistent with the structure of the disc-drum rotor of the real aircraft engine. By adjusting the installation sequence, preload size and preload distribution of the 24 fifth transfer fastening bolts 31, the abnormal vibration of the rotor system caused by the change of the bolt connection state of the disc-drum assembly can be effectively simulated. At the same time, the influence of the disc-drum assembly structure IV on the dynamic characteristics and vibration abnormality of the rotor system with the change of the assembly deflection angle can be further simulated, so that the simulation of the vibration characteristics is more realistic.

[0050] The rear support assembly V comprises a rear support bearing seat 32, a rear support auxiliary plate 33, a front sealing ring 34, a rear support bearing 35, an oil supply port 36, a front positioning sleeve 37, a locking retaining ring 38, a rear sealing ring 39, a rear positioning sleeve 40, an oil drain port 41 and a seventh adapter fastening bolt 42; the rear support bearing 35 is coaxially sleeved on the high-pressure turbine shaft VII; the rear support bearing seat 32 is coaxially fixedly sleeved on the outer ring of the rear support bearing 35; the oil supply port 36 and the oil drain port 41 are both arranged on the rear support bearing seat 32; the front positioning sleeve 37 and the rear positioning sleeve 40 are respectively sleeved on the outer ring of the rear support bearing 35; the oil supply port 36 and the oil drain port 41 are arranged on the rear support bearing seat 32; the front positioning sleeve 37 and the rear positioning sleeve 40 are respectively sleeved on the outer ring of the rear support bearing 35; the oil supply port 36 and the oil drain port 41 are respectively sleeved ... They are respectively located on both sides of the rear support bearing 35, and the front locating sleeve 37 and the rear locating sleeve 40 are coaxially distributed with the rear support bearing 35; the rear support auxiliary plate 33 is fixedly connected to the rear support bearing seat 32 by the seventh adapter fastening bolt 42, and the rear support auxiliary plate 33 and the rear support bearing seat 32 are coaxially distributed; the front sealing ring 34 is arranged between the rear support auxiliary plate 33 and the front locating sleeve 37; the rear sealing ring 39 is arranged between the rear support bearing seat 32 and the rear locating sleeve 40; the locking retaining ring 38 is coaxially fixedly sleeved on the high-pressure turbine shaft VII, and the locking retaining ring 38 and the rear locating sleeve 40 are in contact with each other.

[0051] Specifically, the rear support bearing 35 adopts a three-point angular contact ball bearing, the outer ring of the rear support bearing 35 is interference connected with the rear support bearing seat 32, the outer ring of the rear support bearing 35 is positioned, installed and fixed by circumferential and axial stoppers, the position of the rear support bearing 35 is the rear fulcrum of the rotor system, the rear support bearing 35 is provided with lubricating oil through the lubricating oil supply port 36, and the lubricating oil is discharged through the lubricating oil drain port 41; the rear support bearing 35 is axially positioned and fixed by the front positioning sleeve 37 and the rear positioning sleeve 40; the rear support auxiliary plate 33 and the rear support bearing seat 32 are fixedly connected by 8 seventh transition fastening bolts 42 evenly distributed in the circumferential direction.

[0052] The rear support assembly VI includes a rear support base plate 43, a rear support column 44, a rear support pressure cover 45 and a rear support clamping bolt; the rear support column 44 is vertically fixed above the rear support base plate 43, and a lower clamping semicircular groove 46 is provided on the top of the rear support column 44; the rear support pressure cover 45 is located directly above the rear support column 44, and an upper clamping semicircular groove 47 is provided at the lower part of the rear support pressure cover 45; lower clamping transition protrusions 48 are fixed on the rear support column 44 on both sides of the lower clamping semicircular groove 46; upper clamping transition protrusions 49 are fixed on the rear support pressure cover 45 on both sides of the upper clamping semicircular groove 47, and the upper clamping transition protrusions 49 and the lower clamping transition protrusions 48 are fixedly connected by the rear support clamping bolts; the rear support bearing seat 32 is clamped and fixed between the lower clamping semicircular groove 46 and the upper clamping semicircular groove 47.

[0053] Specifically, the cross-sectional shape of the rear support column 44 is a rectangle, and the rear support column 44 and the rear support base plate 43 are an integrally welded component, which can ensure that the component has good load-bearing capacity and structural stability; vertical circular holes for installing the rear support clamping bolts are processed on the lower clamping adapter protrusion 48 and the upper clamping adapter protrusion 49, and the rear support clamping bolts are used to fasten the lower clamping adapter protrusion 48 and the upper clamping adapter protrusion 49 together, and then clamp and fix the rear support component V between the lower clamping semicircular groove 46 and the upper clamping semicircular groove 47 through the rear support bearing seat 32, and the rear support bearing seat 32 is positioned, installed and fixed with the rear support component VI through the circumferential stop.

[0054] A vibration abnormality simulation test method for a disk-drum rotor system of an aircraft engine is provided, which adopts the vibration abnormality simulation test device for a disk-drum rotor system of an aircraft engine, and comprises the following steps:

[0055] Step 1: Connect the high-pressure turbine shaft VII to the drive motor through an elastic coupling;

[0056] Step 2: Arrange sensors for measuring abnormal vibration of the rotor system;

[0057] ①, a first eddy current displacement sensor A and a second eddy current displacement sensor B are respectively arranged in the circumferential direction of the high-pressure turbine shaft VII in front of the front support assembly II, the first eddy current displacement sensor A is arranged vertically and used to measure the vibration displacement signal of the high-pressure turbine shaft VII in the vertical direction, and the second eddy current displacement sensor B is arranged horizontally and used to measure the vibration displacement signal of the high-pressure turbine shaft VII in the horizontal direction;

[0058] ②, the first acceleration sensor C and the second acceleration sensor D are arranged in the circumferential direction of the front support bearing cone shell 6 of the front support assembly II, the first acceleration sensor C is arranged vertically and used to measure the vibration acceleration response signal of the elastic support part of the front support assembly II in the vertical direction, and the second acceleration sensor D is arranged horizontally and used to measure the vibration acceleration response signal of the elastic support part of the front support assembly II in the horizontal direction;

[0059] ③. A third eddy current displacement sensor E is arranged axially on the edge of the high-pressure turbine disk 28 of the disk-drum combination structural component IV, and a fourth eddy current displacement sensor F is arranged axially on the edge of the sealing grate disk 27 of the disk-drum combination structural component IV. The third eddy current displacement sensor E and the fourth eddy current displacement sensor F are distributed on the same side. The third eddy current displacement sensor E is used to measure the vibration displacement signal of the high-pressure turbine disk 28 in the axial direction, and the fourth eddy current displacement sensor F is used to measure the vibration displacement signal of the sealing grate disk 27 in the axial direction.

[0060] ④. A third acceleration sensor G is arranged on the top of the rear support cover 45 of the rear support assembly VI, and a fourth acceleration sensor H is arranged on the side of the rear support cover 45 of the rear support assembly VI. The third acceleration sensor G is arranged vertically and used to measure the vibration acceleration response signal of the bearing support part of the rear support assembly VI in the vertical direction, and the fourth acceleration sensor H is arranged horizontally and used to measure the vibration acceleration response signal of the bearing support part of the rear support assembly VI in the horizontal direction;

[0061] Step three: first adjust the aircraft engine disc-drum rotor system vibration abnormality simulation test device to a preset abnormal state, then start the drive motor to drive the high-pressure turbine shaft VII, the high-pressure compressor disc assembly III and the disc-drum combination structure IV to rotate synchronously, and the first eddy current displacement sensor A, the second eddy current displacement sensor B, the first acceleration sensor C, the second acceleration sensor D, the third eddy current displacement sensor E, the fourth eddy current displacement sensor F, the third acceleration sensor G and the fourth acceleration sensor H transmit the collected data to the computer, and analyze the collected data through the computer.

[0062] In this embodiment, the preset abnormal state of the aircraft engine disc-drum rotor system vibration abnormality simulation test device is uneven residual pre-tightening of the bolts. Through this preset abnormal state, it is used to test the opening and closing of the connection interface IV of the disc-drum combination structural component.

[0063] Specifically, the pre-tightening force of the 24 fifth transfer fastening bolts 31 is first adjusted to the same by a fixed torque wrench, and the 24 fifth transfer fastening bolts 31 are tightened one by one in a diagonal tightening manner to ensure that the disc-drum combination structural member IV has a suitable coaxiality in the initial state. Subsequently, 8 consecutive adjacent fifth transfer fastening bolts 31 are loosened to simulate the opening and closing state of the sealing comb tooth disk 27 and the high-pressure turbine disk 28. First, the speed of the drive motor is set, and then the drive motor is started at the set speed, and then the disc-drum combination structural member IV is driven to rotate synchronously through the high-pressure turbine shaft VII. At the same time, the third acceleration sensor G and the fourth acceleration sensor H will transmit the real-time measured vibration acceleration response signal to the computer, and then the computer will analyze the collected vibration acceleration response signal. By comparing the characteristics of the opening and closing angles of the sealing comb tooth disk 27 and the high-pressure turbine disk 28 before and after opening and closing with time, it can be used to determine the connection interface state. At the same time, the first eddy current displacement sensor A and the second eddy current displacement sensor B will transmit the real-time measured vibration displacement signal to the computer, and then the computer will analyze the collected vibration displacement signal, and by comparing the vibration displacement signal in the vertical and horizontal directions of the high-pressure turbine shaft VII, the axis trajectory and time-frequency characteristics of the high-pressure turbine shaft VII can be analyzed, and the rotor vibration characteristics caused by the opening and closing of the connection interface of the disc-drum combination structural member IV can be further determined. In addition, the first acceleration sensor C and the second acceleration sensor D will transmit the real-time measured vibration acceleration response signal to the computer, and then the computer will analyze the collected vibration acceleration response signal, and by comparing the vibration acceleration response signal in the vertical and horizontal directions of the front support bearing cone shell 6, it can be used to determine the influence of the front support cage 9 as an elastic support on the vibration transfer characteristics of the rotor.

[0064] In addition, the analysis methods include relative displacement analysis, short-time Fourier transform analysis and axis trajectory analysis. When the relative displacement analysis method is used, the relative vibration displacement of the sealing grate disc 27 and the high-pressure turbine disc 28 in the axial direction is obtained, and then combined with the radius of the sealing grate disc 27 and the high-pressure turbine disc 28, the change characteristics of the opening and closing angles of the sealing grate disc 27 and the high-pressure turbine disc 28 at the measurement point over time can be further obtained. When the short-time Fourier transform analysis method is used, it can be used to obtain the time-frequency characteristics of the vibration displacement signal and the vibration acceleration signal, and the time-frequency characteristics include vibration frequency and vibration amplitude. When the axis trajectory analysis method is used, it can be used to obtain the change characteristics of the axis trajectory of the high-pressure turbine shaft VII over time, and further combined with time domain synchronous averaging and Poincare reconstruction, nonlinear vibration characteristics can be further obtained. In the actual vibration signal testing and processing process, according to different vibration fault types, one or several analysis methods can be selected to process and analyze the vibration signal.

[0065] The solutions in the embodiments are not intended to limit the protection scope of the present invention. All equivalent implementations or changes that do not deviate from the present invention are included in the protection scope of the present invention.

Claims

1. An abnormal vibration simulation test device for a disc-drum rotor system of an aircraft engine, characterized in that: It includes a front bracket assembly, a front support assembly, a high-pressure compressor disc assembly, a disc-drum assembly structure, a rear support assembly, a rear bracket assembly and a high-pressure turbine shaft; the high-pressure turbine shaft is arranged horizontally; the front support assembly, the high-pressure compressor disc assembly, the disc-drum assembly structure and the rear support assembly are arranged on the high-pressure turbine shaft in sequence; the front support assembly is arranged on the front bracket assembly; the rear support assembly is arranged on the rear bracket assembly; the high-pressure compressor disc assembly includes a concentrated mass disc, a high-pressure compressor disc expansion sleeve and a high-pressure compressor disc expansion tension bolt; the high-pressure compressor disc expansion sleeve The sleeve is coaxially sleeved on the high-pressure turbine shaft; the concentrated mass disk is coaxially sleeved on the high-pressure compressor disk expansion sleeve; the high-pressure compressor disk expansion tension bolts are evenly distributed on the high-pressure compressor disk expansion sleeve along the circumferential direction; the disk-drum assembly structural component includes a primary sealing disk, a primary sealing disk expansion sleeve, a primary sealing disk expansion tension bolt, a high-pressure turbine front drum, a sealing grate disk, a high-pressure turbine disk, a high-pressure turbine disk expansion sleeve, a high-pressure turbine disk expansion tension bolt, a fifth transition fastening bolt and a sixth transition fastening bolt; the primary sealing disk expansion sleeve is coaxially sleeved on the high-pressure turbine shaft ; The first-level sealing disc is coaxially sleeved on the first-level sealing disc expansion sleeve; the first-level sealing disc expansion tension bolts are evenly distributed on the first-level sealing disc expansion sleeve along the circumferential direction; the high-pressure turbine disc expansion sleeve is coaxially sleeved on the high-pressure turbine shaft; the high-pressure turbine disc is coaxially sleeved on the high-pressure turbine disc expansion sleeve; the high-pressure turbine disc expansion tension bolts are evenly distributed on the high-pressure turbine disc expansion sleeve along the circumferential direction; the sealing grate disc is fixedly connected to the high-pressure turbine disc by the fifth transfer fastening bolt, and the sealing grate disc is coaxially distributed with the high-pressure turbine disc; the high-pressure turbine front drum is The first end is also fixedly connected to the sealing comb plate by the fifth transition fastening bolt, the other end of the high-pressure turbine front drum is fixedly connected to the first-stage sealing plate by the sixth transition fastening bolt, and the high-pressure turbine front drum is coaxially distributed with the high-pressure turbine shaft; by adjusting the installation sequence, preload force and preload force distribution of the fifth transition fastening bolt, the abnormal vibration of the rotor system caused by the change of the bolt connection state of the disk-drum assembly is simulated, and at the same time, the influence of the disk-drum combined structural parts on the dynamic characteristics and abnormal vibration of the rotor system with the change of the assembly deflection angle is further simulated, so that the simulation of the vibration characteristics is more realistic.

2. The aero-engine disc-drum rotor system vibration abnormality simulation test device according to claim 1, characterized in that: There are two front bracket assemblies, which are symmetrically distributed on both sides of the front support assembly; the front bracket assembly includes a front bracket base plate, a front bracket column, a front bracket hanging point fastening bolt and a reinforcing rib plate; the front bracket column is vertically fixed above the front bracket base plate; the front bracket hanging point fastening bolt is vertically installed on the top of the front bracket column; the reinforcing rib plate is fixed between the front bracket column and the front bracket base plate, and the reinforcing rib plates are evenly distributed along the circumferential direction of the front bracket column.

3. The aero-engine disc-drum rotor system vibration abnormality simulation test device according to claim 2, characterized in that: The front support assembly includes a front support web, a front support bearing cone shell, a front support auxiliary plate, a front support hanging point transfer protrusion, a front support squirrel cage, a threaded positioning pin, a front support bearing seat, a front support bearing seat cover and a front support bearing, a first transfer fastening bolt, a second transfer fastening bolt, a third transfer fastening bolt and a fourth transfer fastening bolt, an oil inlet and an oil outlet; the front support bearing is coaxially sleeved on the high-pressure turbine shaft; the front support bearing seat is coaxially fixedly sleeved on the outer ring of the front support bearing; the oil inlet The front support bearing seat is provided with a transparent cover, and the front support bearing seat is coaxially arranged with the front support bearing seat. The front support bearing is located between the transparent cover and the front support bearing seat. The front support cage is fixedly connected to the front support bearing seat by a second transition fastening bolt, and the front support cage is coaxially arranged with the front support bearing seat. The front support bearing, the transparent cover and the front support bearing seat are located between the transparent cover and the front support bearing seat. On the inner side of the front support cage; the front support bearing cone shell is fixedly connected to the front support cage by a third transition fastening bolt, the front support bearing cone shell is coaxially distributed with the front support cage, and the front support cage is located on the inner side of the front support bearing cone shell; the front support auxiliary plate is also fixedly connected to the front support cage and the front support bearing cone shell by a third transition fastening bolt, and the front support auxiliary plate is also circumferentially positioned with the front support bearing cone shell by a threaded locating pin, the front support auxiliary plate is coaxially distributed with the front support bearing cone shell, and the front support auxiliary plate is transparent to the front support bearing seat The cover is distributed on the same side; the front support web is fixedly connected to the front support load-bearing cone shell by a fourth transfer fastening bolt, the front support web and the front support load-bearing cone shell are coaxially distributed, and the front support load-bearing cone shell is located on the inner side of the front support web; the front support hanging point transfer protrusion is fixedly arranged on the edge of the front support web, and the number of the front support hanging point transfer protrusions is two, and the two front support hanging point transfer protrusions are mirror-symmetrically distributed on the left and right sides of the front support web, and the front support hanging point transfer protrusion is fixedly connected to the front support column by the front support hanging point fastening bolt.

4. The abnormal vibration simulation test device for the disc-drum rotor system of an aircraft engine according to claim 3, characterized in that: The rear support assembly comprises a rear support bearing seat, a rear support auxiliary plate, a front sealing ring, a rear support bearing, an oil supply port, a front positioning sleeve, a locking retaining ring, a rear sealing ring, a rear positioning sleeve, an oil drain port and a seventh transition fastening bolt; the rear support bearing is coaxially sleeved on the high-pressure turbine shaft; the rear support bearing seat is coaxially fixedly sleeved on the outer ring of the rear support bearing; the oil supply port and the oil drain port are both arranged on the rear support bearing seat; the front positioning sleeve and the rear positioning sleeve are respectively located on both sides of the rear support bearing, and the front positioning sleeve and the rear positioning sleeve are coaxially distributed with the rear support bearing; the rear support auxiliary plate is fixedly connected to the rear support bearing seat by the seventh transition fastening bolt, and the rear support auxiliary plate is coaxially distributed with the rear support bearing seat; the front sealing ring is arranged between the rear support auxiliary plate and the front positioning sleeve; the rear sealing ring is arranged between the rear support bearing seat and the rear positioning sleeve; the locking retaining ring is coaxially fixedly sleeved on the high-pressure turbine shaft, and the locking retaining ring is close to the rear positioning sleeve.

5. The aero-engine disc-drum rotor system vibration abnormality simulation test device according to claim 4, characterized in that: The rear bracket assembly includes a rear bracket base plate, a rear bracket column, a rear bracket pressure cover and a rear bracket clamping bolt; the rear bracket column is vertically fixed above the rear bracket base plate, and a lower clamping semicircular groove is arranged on the top of the rear bracket column; the rear bracket pressure cover is located directly above the rear bracket column, and an upper clamping semicircular groove is arranged at the lower part of the rear bracket pressure cover; lower clamping transition protrusions are fixed on the rear bracket columns on both sides of the lower clamping semicircular groove; upper clamping transition protrusions are fixed on the rear bracket pressure cover on both sides of the upper clamping semicircular groove, and the upper clamping transition protrusion and the lower clamping transition protrusion are fixedly connected by the rear bracket clamping bolt; the rear support bearing seat is clamped and fixed between the lower clamping semicircular groove and the upper clamping semicircular groove.

6. A method for simulating abnormal vibration of a disk-drum rotor system of an aircraft engine, using the device for simulating abnormal vibration of a disk-drum rotor system of an aircraft engine as claimed in claim 5, characterized in that: The steps include: Step 1: Connect the high-pressure turbine shaft to the drive motor through an elastic coupling; Step 2: Arrange sensors for measuring abnormal vibration of the rotor system; ①, a first eddy current displacement sensor and a second eddy current displacement sensor are arranged in the circumferential direction of the high-pressure turbine shaft in front of the front support assembly, respectively. The first eddy current displacement sensor is arranged vertically and used to measure the vibration displacement signal of the high-pressure turbine shaft in the vertical direction, and the second eddy current displacement sensor is arranged horizontally and used to measure the vibration displacement signal of the high-pressure turbine shaft in the horizontal direction; ②, arrange the first acceleration sensor and the second acceleration sensor in the circumferential direction of the front support bearing cone shell of the front support assembly respectively, the first acceleration sensor is arranged vertically and used to measure the vibration acceleration response signal of the elastic support part of the front support assembly in the vertical direction, and the second acceleration sensor is arranged horizontally and used to measure the vibration acceleration response signal of the elastic support part of the front support assembly in the horizontal direction; ③. A third eddy current displacement sensor is arranged axially on the edge of the high-pressure turbine disk of the disk-drum combination structural component, and a fourth eddy current displacement sensor is arranged axially on the edge of the sealing grate disk of the disk-drum combination structural component. The third eddy current displacement sensor and the fourth eddy current displacement sensor are distributed on the same side. The third eddy current displacement sensor is used to measure the vibration displacement signal of the high-pressure turbine disk in the axial direction, and the fourth eddy current displacement sensor is used to measure the vibration displacement signal of the sealing grate disk in the axial direction. ④. Arrange a third acceleration sensor on the top of the rear bracket gland of the rear bracket assembly, and arrange a fourth acceleration sensor on the side of the rear bracket gland of the rear bracket assembly. The third acceleration sensor is arranged vertically and used to measure the vibration acceleration response signal of the bearing support part of the rear bracket assembly in the vertical direction. The fourth acceleration sensor is arranged horizontally and used to measure the vibration acceleration response signal of the bearing support part of the rear bracket assembly in the horizontal direction. Step three: first adjust the aircraft engine disc-drum rotor system vibration abnormality simulation test device to a preset abnormal state, then start the drive motor to drive the high-pressure turbine shaft, the high-pressure compressor disc assembly and the disc-drum combination structure to rotate synchronously, and the first eddy current displacement sensor, the second eddy current displacement sensor, the first acceleration sensor, the second acceleration sensor, the third eddy current displacement sensor, the fourth eddy current displacement sensor, the third acceleration sensor and the fourth acceleration sensor transmit the collected data to the computer, and the collected data is analyzed by the computer.

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