Broadband vibration absorber and multi-fulcrum shared bearing structure

Abstract

The invention belongs to the technical field of aero-engine complete machine vibration control, and particularly relates to a broadband vibration absorber and a multi-fulcrum shared bearing structure, and the broadband vibration absorber comprises a shell, a baffle and a lamination group; the shell is detachably connected with the lamination group, and an annular cavity is formed inside; the lamination group is mounted in the annular cavity in the radial direction of the annular cavity, and comprises bolts, and a metal rubber ring I, an arc-shaped metal lamination I, a metal rubber ring II, an arc-shaped metal lamination II, a metal rubber ring III, an arc-shaped metal lamination III, a metal rubber ring IV, an arc-shaped metal lamination IV and a metal rubber ring V which are stacked and penetrated by the bolts. Under the condition that the radial rigidity of the main force bearing structure is guaranteed, high-frequency mechanical vibration which is uploaded to the outer casing from the two rotors along the force transmission route is absorbed through the metal lamination and metal rubber sheet combined structure which are arranged on the main force transmission route and have different sizes, and the whole machine vibration response level reflected in the outer casing can be remarkably reduced.

Description

Technical Field This invention belongs to the field of vibration control technology for aero-engines, specifically relating to a wideband vibration absorber and a multi-support shared load-bearing structure. Background Technology

[0001] With the development of modern helicopters, high power-to-weight ratio turboshaft engines require a more compact structural layout and higher reliability design to meet modern development needs. In structural design, a shared load-bearing structure between turbine stages is often used to achieve the design requirements of lightweight, compactness, and high reliability. In a dual-rotor turboshaft engine, the shared load-bearing frame between turbine stages supports both the gas generator rotor and the power turbine rotor. Damage to the engine rotor system, such as rotor imbalance caused by foreign object impacts, misalignment due to maneuvering flight, and exceeding critical speeds, can lead to significant vibration response in the entire engine, affecting its reliability and safety during operation.

[0002] To reduce overall engine vibration, a common method is to employ vibration isolation and damping structural designs. For example, patent CN116733551A, "Multi-Support Shared Load-Bearing Structure Between Turbine Stages with High Vibration Isolation," proposes a "herringbone" vibration isolation structure to separate vibration coupling between the two rotors and reduce the load-bearing structure's sensitivity to rotor excitation frequency changes. However, high power-to-weight ratio engines are often constrained by the layout of the air and lubrication systems, making it difficult to design such a "herringbone" bifurcated structure. Yet, a shared load-bearing frame is needed to support both rotors simultaneously to reduce overall engine weight. Therefore, vibration-damping and energy-absorbing structural optimization designs are frequently employed in structural layout design to reduce overall engine vibration.

[0003] The inter-stage load-bearing frame supports both the gas turbine rotor and the power turbine rotor. The vibration frequency of its transmitted vibration load is a combination of the rotational speed frequencies of the two rotors (300~500Hz) and their higher harmonics (500~1500Hz), and it varies with the rotor speed, exhibiting significant broadband characteristics. Furthermore, the inter-stage load-bearing frame is located between the two turbines and experiences high temperature loads (200~800℃). Currently, no effective vibration damping or absorption structures for this type of broadband, high-temperature structure have been found in the literature and patents. Summary of the Invention

[0004] To solve the above-mentioned technical problems, this invention provides a metal-rubber composite laminate broadband vibration absorber for multi-support shared load-bearing structures. To achieve the above-mentioned objective, the technical solution adopted by this invention is as follows: This invention provides a wideband vibration absorber, which includes a housing, a baffle, and a stack of plates; The outer shell and the laminated assembly are detachably connected, forming an annular cavity inside; The stacked plate assembly is installed in the annular cavity and along the radial direction of the annular cavity. The stacked plate assembly includes a fastening bolt and stacked metal rubber ring 1, arc-shaped metal plate 1, metal rubber ring 2, arc-shaped metal plate 2, metal rubber ring 3, arc-shaped metal plate 3, metal rubber ring 4, arc-shaped metal plate 4, and metal rubber ring 5 through which the fastening bolt passes.

[0005] Furthermore, along the radial direction of the annular cavity, the stacked assembly includes a first stacked structure and a second stacked structure; Along the radial direction from the outside to the inside of the annular cavity, the first layered structure includes, in sequence, a metal rubber ring 1, an arc-shaped metal plate 1, a metal rubber ring 2, an arc-shaped metal plate 2, a metal rubber ring 3, an arc-shaped metal plate 3, a metal rubber ring 4, an arc-shaped metal plate 4, and a metal rubber ring 5. Along the radial direction from the outside to the inside of the annular cavity, the second layered structure includes, in sequence, a metal rubber ring 1, an arc-shaped metal plate 4, a metal rubber ring 2, an arc-shaped metal plate 3, a metal rubber ring 3, an arc-shaped metal plate 2, a metal rubber ring 4, an arc-shaped metal plate 1, and a metal rubber ring 5. The first and second stacked structures share metal rubber rings 1, 2, 3, 4, and 5.

[0006] Furthermore, the arc lengths of the arc-shaped metal laminates one, two, three, and four increase sequentially.

[0007] Furthermore, along the circumference of the annular cavity, the first and second stacked structures are alternately arranged.

[0008] Furthermore, both the first and second stacked structures are provided with four sets.

[0009] Furthermore, the materials used in Metal Rubber Ring 1, Metal Rubber Ring 2, Metal Rubber Ring 3, Metal Rubber Ring 4, and Metal Rubber Ring 5 are all metal rubber materials. The metal rubber material is made by winding metal wire into a spiral coil, and then undergoing stretching, weaving, molding, and post-processing.

[0010] The present invention also provides a multi-support shared load-bearing structure, including a gas generator rotor, a load-bearing frame, a turbine rotor, a front bearing, a middle bearing, and a rear bearing; Along the axial direction of the gas generator rotor, the gas generator rotor and the turbine rotor are arranged in sequence, and the front bearing, the middle bearing and the rear bearing are arranged in sequence. The front bearing is mounted on the surface of the gas generator rotor, while the middle and rear bearings are both mounted on the surface of the turbine rotor. The outer rings of the front bearing, middle bearing, and rear bearing are all connected to the load-bearing frame, which integrates the aforementioned wideband vibration absorber.

[0011] Furthermore, the load-bearing frame is connected in sequence along the radial direction of the gas generator rotor to the load-bearing outer casing, the turbine stage casing, the wide-frequency vibration absorber, and the common bearing housing.

[0012] Furthermore, the common bearing housing includes the bearing housing body, the front support spring, and the rear support spring; One end of the front support spring is connected to the bearing housing body, and the inner ring of the other end is connected to the outer ring of the front bearing to bear the load of the gas generator rotor. One end of the rear support spring is connected to the bearing housing body on its outer surface, and the lower surface is connected to the outer ring of the middle bearing. The other end of the rear support spring is connected to the outer ring of the rear bearing.

[0013] Furthermore, an aircraft engine is also installed at the end of the gas generator rotor that is away from the load-bearing frame.

[0014] Compared with the prior art, the present invention has the following beneficial effects: This invention achieves vibration reduction and energy absorption design for the load-bearing structure between turbine stages of an aero-engine by employing a metal-rubber composite laminated broadband vibration absorber. During the operation of an aero-engine, the engine rotor system vibrates when damaged by foreign objects, during maneuvering flight, or when exceeding critical speeds. When the vibration energy is transmitted outward along the force transmission path through the vibration absorber, depending on the excitation frequency, the arc-shaped metal sheets of corresponding sizes in the laminated assembly are excited to resonate, compressing the internal metal wires of adjacent metal-rubber damping rings to generate friction and absorb energy, thereby reducing the energy and intensity of the vibration. This reduces the vibration energy transmitted to the outer casing of the aero-engine, achieving control of the overall vibration level.

[0015] The metal-rubber composite laminate broadband vibration absorber used in this invention can achieve wide-frequency vibration absorption, which is achieved through the design of arc-shaped metal laminates of different sizes. By designing the cantilever length, thickness, and width of the arc-shaped metal laminates, selecting the metal material, and considering the elastic modulus and energy dissipation factor of the metal-rubber ring, the resonant frequencies of the first bend, first torsion, and second bend of the metal laminates in the vibration absorber laminate assembly cover a frequency range of 300~1500Hz.

[0016] The metal-rubber composite laminate broadband vibration absorber used in this invention can achieve vibration control of high-temperature structures because both the metal rubber and the metal laminate can be made of high-temperature alloys, making it suitable for vibration absorption design in high-temperature environments. Attached Figure Description

[0017] Figure 1 A simplified structural diagram of the dual-rotor turboshaft engine provided by the present invention; Figure 2 A simplified diagram of a multi-support shared load-bearing structure provided by the present invention; Figure 3 for Figure 2 Cross-sectional view of a broadband vibration absorber with medium-sized metal-rubber composite laminate; Figure 4 for Figure 2 A three-dimensional cross-sectional view of a broadband vibration absorber with a medium-metal rubber-composite laminate; Figure 5 for Figure 2 Three-dimensional appearance of a broadband vibration absorber with medium-metal rubber-composite laminate; Figure 6 for Figure 4 Composition and distribution structure diagram of medium metal-rubber composite laminate.

[0018] Figure label: 1. Gas generator rotor; 2. Load-bearing frame; 21. Outer casing; 22. Turbine stage casing; 23. Wideband vibration absorber; 231. Outer casing; 232. Baffle; 233. Laminate assembly; 2330. Fastening bolts; 2331. Metal rubber ring one; 2332. Arc-shaped metal lamination one; 2333. Metal rubber ring two; 2334. Arc-shaped metal lamination two; 2335. Metal rubber ring three; 2336. Arc-shaped metal lamination three; 2337. Metal rubber ring four; 2338. Arc-shaped metal lamination four; 2339. Metal rubber ring five; 24. Common bearing housing; 241. Bearing housing body; 242. Front support spring support; 243. Rear support spring support; 3. Turbine rotor; 4. Front bearing; 5. Intermediate bearing; 6. Rear bearing; 7. Aero engine. Detailed Implementation

[0019] The following will be based on embodiments of the present invention. Figures 1-6 The technical solutions in the embodiments of the present invention will be clearly and completely described. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Unless otherwise specified, the technical means used in the embodiments are conventional means well known to those skilled in the art.

[0020] like Figure 1 The diagram shown is a simplified structural diagram of a dual-rotor turboshaft engine, which includes a multi-support shared load-bearing structure as described in this embodiment. It mainly comprises a gas generator rotor 1, a load-bearing frame 2, a turbine rotor 3, a front bearing 4, a middle bearing 5, and a rear bearing 6. It should be noted that... Figure 1-3 The diagram shows a cross-sectional view. In this embodiment, the aircraft engine 7 refers to a turboshaft engine. Both the gas generator rotor 1 and the turbine rotor 3 are coaxial rotating structures, referred to as rotor structures. The shared load-bearing frame 2 is a coaxial non-rotating structure, referred to as a stator structure. Furthermore, in this embodiment, "radial" refers to the direction pointing up and down from the central axis in the attached diagram; "radial outer" refers to the direction in which the structure deviates from the central axis; "radial inner" refers to the direction in which the structure tends towards the central axis. In this embodiment, "circumferential" refers to the circumferential direction around the central axis in the attached diagram.

[0021] Along the axial direction of the gas generator rotor 1, the gas generator rotor 1 and the turbine rotor 3 are arranged sequentially; simultaneously, the front bearing 4, the middle bearing 5, and the rear bearing 6 are also arranged sequentially along this axial direction. The front bearing 4 is mounted on the outer surface of the gas generator rotor 1, while the middle bearing 5 and the rear bearing 6 are both mounted on the outer surface of the turbine rotor 3. The outer rings of the front bearing 4, the middle bearing 5, and the rear bearing 6 are all connected to the load-bearing frame 2, and the load-bearing frame 2 integrates the following wide-frequency vibration absorber 23.

[0022] like Figure 2 As shown, the load-bearing frame 2, along the radial direction of the gas generator rotor 1, is sequentially connected to the load-bearing outer casing 21, the turbine interstage casing 22, the wideband vibration absorber 23, and the common bearing housing 24. It is mainly used to absorb and reduce the vibration load transmitted from the aero-engine 7 rotor to the turbine interstage casing 22 through the common bearing housing 24. The gas generator rotor 1, the common load-bearing frame 2, and the power turbine rotor 3 are all rotor-stator structures.

[0023] The shared bearing housing 24 is a three-point bearing housing, comprising a bearing housing body 241, a front support spring 243, and a rear support spring 242. One end (left end) of the front support spring 243 is connected to the bearing housing body 241 by bolts or other structures, and the inner ring of the other end is connected to the outer ring of the front bearing 4. This front support spring 243 is used to bear the load generated by the gas generator rotor 1. The outer surface of one end (left end) of the rear support spring 242 is connected to the bearing housing body 241, and the lower surface (inner surface) is connected to the outer ring of the intermediate bearing 5. The other end of the rear support spring 242 is connected to the outer ring of the rear bearing 6, so that the intermediate bearing 5 and the rear bearing 6 are connected together to the turbine rotor 3 and bear the load of the turbine rotor 3. In addition, an aircraft engine 7 is installed at the end of the gas generator rotor 1 away from the load-bearing frame 2.

[0024] It should be noted that in the multi-support shared load-bearing structure, the gas generator rotor 1 and turbine rotor 3 are arranged sequentially along the axial direction, and are radially positioned and supported by the front bearing 4, the middle bearing 5, and the rear bearing 6. The front bearing 4 supports the gas generator rotor 1, and the middle bearing 5 and the rear bearing 6 support the turbine rotor 3. The outer rings of the three bearings are all connected to the load-bearing frame 2, so that the radial load generated by the rotor can be transmitted to the load-bearing frame 2.

[0025] It should be further explained that the load-bearing frame 2 forms a complete load transfer path through the radially connected load-bearing outer casing 21, turbine stage casing 22, wide-frequency vibration absorber 23, and common bearing housing 24. Specifically, the front support spring 243 of the common bearing housing 24 directly bears the load of the gas generator rotor 1 and transfers the load to the bearing housing body 241; the rear support spring 242 simultaneously connects the outer rings of the intermediate bearing 5 and the rear bearing 6, concentrating the load generated by the turbine rotor 3 to the bearing housing body 241. Finally, all loads are distributed and transferred to the external structure through the load-bearing frame 2, achieving shared load-bearing across multiple support points. Furthermore, the wide-frequency vibration absorber 23 integrated on the load-bearing frame 2 can simultaneously absorb rotor vibration, reducing the impact of vibration loads on the load-bearing structure.

[0026] like Figure 3 As shown, the broadband vibration absorber 23 in this embodiment can absorb and reduce the transmission of vibration loads from the rotor of the aero-engine 7. It mainly includes a housing 231, a baffle 232, and a lamination assembly 233. The housing 231 and the lamination assembly 233 are detachably connected, preferably by bolts. The housing 231 and the baffle 232 form a closed structure, with an annular cavity inside. Furthermore, the lower end (inner surface) of the broadband vibration absorber 23 is connected to a common bearing housing 24, and the upper end (outer surface) is connected to the turbine stage casing 22, transferring the load of the common bearing housing 24 to the turbine stage casing 22 and then outward to the load-bearing outer casing 21.

[0027] like Figure 4 As shown, both the outer shell 231 and the baffle 232 adopt an annular rotating body structure. The outer shell 231 has an annular recess on its surface facing the baffle 232, and the baffle 232 closes the annular recess with bolts to form an inner cavity structure. The stacked plate assembly 233 is installed in the inner cavity structure, ultimately forming a structure as shown. Figure 5 The common bearing housing 24 is shown.

[0028] Combination Figure 6 It is known that the laminate assembly 233 is installed in the annular cavity. Along the radial direction of the annular cavity, the laminate assembly 233 includes fastening bolts 2330 and laminated components that are sequentially passed through by the fastening bolts 2330: metal rubber ring one 2331, arc-shaped metal laminate one 2332, metal rubber ring two 2333, arc-shaped metal laminate two 2334, metal rubber ring three 2335, arc-shaped metal laminate three 2336, metal rubber ring four 2337, arc-shaped metal laminate four 2338, and metal rubber ring five 2339.

[0029] In addition, through Figure 6It can be seen that, along the radial direction of the annular cavity, the stacked plate group 233 is specifically divided into a first stacked structure and a second stacked structure. Among them, along the radial direction from the outside to the inside of the annular cavity, the first stacked structure includes the following sequentially stacked metal rubber ring 2331, arc-shaped metal plate 2332, metal rubber ring 2333, arc-shaped metal plate 2334, metal rubber ring 3 2335, arc-shaped metal plate 3 2336, metal rubber ring 4 2337, arc-shaped metal plate 4 2338, and metal rubber ring 5 2339.

[0030] Along the radial direction from the outside to the inside of the annular cavity, the second stacked structure includes, in sequence, a metal rubber ring 1 (2331), an arc-shaped metal plate 4 (2338), a metal rubber ring 2 (2333), an arc-shaped metal plate 3 (2336), a metal rubber ring 3 (2335), an arc-shaped metal plate 2 (2334), a metal rubber ring 4 (2337), an arc-shaped metal plate 1 (2332), and a metal rubber ring 5 (2339). The first and second stacked structures share metal rubber rings 1 (2331), 2 (2333), 3 (2335), 4 (2337), and 5 (2339). Furthermore, the arc lengths of the arc-shaped metal plates 1 (2332), 2 (2334), 3 (2336), and 4 (2338) exhibit distinct differences, increasing sequentially.

[0031] In addition, Figure 6 Along the circumferential direction of the annular cavity, the first and second stacked structures are alternately arranged, and each of the first and second stacked structures has four groups. Specifically, there are eight groups of stacked plates 233. These eight groups of arc-shaped metal stacked plates are evenly distributed circumferentially. In four groups, the shorter plates are on the outer diameter and the longer plates are on the inner diameter; in the other four groups, the longer plates are on the outer diameter and the shorter plates are on the inner diameter. Each group of stacked plates is bolted to the outer shell, and the dimensions of adjacent circumferentially adjacent stacked plate groups are complementary. Therefore… Figure 6 The middle absorber plate assembly consists of five metal rubber rings of different diameters and eight groups of a total of 32 arc-shaped metal plates.

[0032] In addition, the materials used for metal rubber ring 1 (2331), metal rubber ring 2 (2333), metal rubber ring 3 (2335), metal rubber ring 4 (2337), and metal rubber ring 5 (2339) are all metal rubber materials. These metal rubber materials are made by winding metal wires into a spiral coil and then stretching, weaving, molding, and post-processing.

[0033] It should be noted that when the wideband vibration absorber 23 is working, the annular cavity inside the housing 231 provides installation space for the lamination assembly 233, and the baffle 232 acts as an axial limiter for the lamination assembly 233 to prevent the lamination assembly 233 from moving axially during vibration. When the rotor of the aero-engine 7 generates a vibration load, the vibration load is transmitted to the lamination assembly 233 through the housing 231.

[0034] The metal rubber rings 2331 to 2339 in the laminate assembly 233 are made of metal rubber material. When subjected to vibration loads, the spirally wound metal wires inside this material undergo relative sliding and deformation. Through friction between the wires and the elastic deformation of the material itself, vibration energy is converted into heat energy and dissipated, achieving initial absorption of vibration. Simultaneously, the arc-shaped metal laminates 2332 to 2338, with their successively increasing arc lengths, exhibit differences in stiffness and natural frequency, enabling them to respond to vibration loads in different frequency ranges and further absorb vibration energy through their bending deformation.

[0035] Furthermore, because the first and second stacked structures are alternately arranged along the circumference of the annular cavity, with four groups of each, and the arrangement order of the arc-shaped metal laminations in the two stacked structures is different, the absorption capacity of the lamination group 233 for vibration is more uniform at different positions in the circumference, and it can cover a wider frequency range. In addition, the first and second stacked structures share a metal rubber ring, which reduces the amount of material used and simplifies the structure while ensuring the vibration absorption effect, ultimately achieving broadband absorption and reduction of vibration load on the rotor of the aero-engine 7.

[0036] It should be noted that during the operation of the aero-engine 7, the gas generator rotor 1 and the power turbine rotor 3 vibrate due to rotor imbalance, rotor misalignment, or exceeding the critical speed. The vibration load is transmitted to the outside through the bearings. After passing through the wide-frequency vibration absorber 23, it is absorbed by the metal-rubber composite laminate with wide frequency range and high damping characteristics. The vibration intensity and vibration energy will be reduced, and the vibration response transmitted to the turbine interstage casing 22 and the load-bearing outer casing 21 will be greatly reduced, thereby reducing the overall vibration of the aero-engine 7.

[0037] It should be further clarified that the materials used in Metal Rubber Ring 1 (2331), Metal Rubber Ring 2 (2333), Metal Rubber Ring 3 (2335), Metal Rubber Ring 4 (2337), and Metal Rubber Ring 5 (2339) are all metal rubber materials. These are microstructured functional metal materials made by winding metal wires into spiral coils, followed by stretching, weaving, molding, and post-processing. Metal rubber is a special material woven from metal wires, combining the advantages of metal and rubber, and possessing unique properties. Its internal structure, woven from metal wires, effectively absorbs and disperses vibration energy, thereby reducing the impact of vibration on the overall structural system of the aero-engine. Metal rubber has high heat resistance, maintaining its performance in high-temperature environments, and can be directly used in the load-bearing frame 2 between turbine stages to withstand high temperatures.

[0038] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Any modifications, alterations, alterations, or substitutions made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. A broadband vibration absorber, characterized in that, The broadband vibration absorber (23) includes a housing (231), a baffle (232), and a stack of plates (233); The outer shell (231) is detachably connected to the stacked plate group (233), and the interior forms an annular cavity; The stacked plate assembly (233) is installed in the annular cavity and along the radial direction of the annular cavity. The stacked plate assembly (233) includes a fastening bolt (2330) and a stacked metal rubber ring one (2331), an arc-shaped metal plate one (2332), a metal rubber ring two (2333), an arc-shaped metal plate two (2334), a metal rubber ring three (2335), an arc-shaped metal plate three (2336), a metal rubber ring four (2337), an arc-shaped metal plate four (2338), and a metal rubber ring five (2339) through which the fastening bolt (2230) passes.

2. The broadband vibration absorber according to claim 1, characterized in that, Along the radial direction of the annular cavity, the stacked assembly (233) includes a first stacked structure and a second stacked structure; Along the radial direction from the outside to the inside of the annular cavity, the first stacked structure includes, in sequence, a metal rubber ring one (2331), an arc-shaped metal plate one (2332), a metal rubber ring two (2333), an arc-shaped metal plate two (2334), a metal rubber ring three (2335), an arc-shaped metal plate three (2336), a metal rubber ring four (2337), an arc-shaped metal plate four (2338), and a metal rubber ring five (2339); Along the radial direction from the outside to the inside of the annular cavity, the second stacked structure includes, in sequence, a metal rubber ring one (2331), an arc-shaped metal plate four (2338), a metal rubber ring two (2333), an arc-shaped metal plate three (2336), a metal rubber ring three (2335), an arc-shaped metal plate two (2334), a metal rubber ring four (2337), an arc-shaped metal plate one (2332), and a metal rubber ring five (2339); The first and second stacked structures share the metal rubber ring one (2331), metal rubber ring two (2333), metal rubber ring three (2335), metal rubber ring four (2337), and metal rubber ring five (2339).

3. A broadband vibration absorber according to claim 2, characterized in that, The arc lengths of the arc-shaped metal stack 1 (2332), arc-shaped metal stack 2 (2334), arc-shaped metal stack 3 (2336) and arc-shaped metal stack 4 (2338) increase sequentially.

4. A broadband vibration absorber according to claim 2, characterized in that, Along the circumference of the annular cavity, the first stacked structure and the second stacked structure are alternately arranged.

5. A broadband vibration absorber according to claim 4, characterized in that, The first and second stacked structures are each provided with four sets.

6. A broadband vibration absorber according to claim 4, characterized in that, The materials used in the metal rubber ring one (2331), metal rubber ring two (2333), metal rubber ring three (2335), metal rubber ring four (2337), and metal rubber ring five (2339) are all metal rubber materials. The metal rubber materials are made by winding metal wires into a spiral coil and then stretching, weaving, molding, and post-processing.

7. A multi-support shared load-bearing structure, characterized in that, It includes a gas generator rotor (1), a load-bearing frame (2), a turbine rotor (3), a front bearing (4), a middle bearing (5), and a rear bearing (6). Along the axial direction of the gas generator rotor (1), the gas generator rotor (1) and the turbine rotor (3) are arranged in sequence, and the front bearing (4), the middle bearing (5) and the rear bearing (6) are arranged in sequence; The front bearing (4) is mounted on the surface of the gas generator rotor (1), and the middle bearing (5) and the rear bearing (6) are both mounted on the surface of the turbine rotor (3). The outer rings of the front bearing (4), the middle bearing (5) and the rear bearing (6) are all connected to the load-bearing frame (2), and the load-bearing frame (2) integrates a broadband vibration absorber as described in any one of claims 1-6.

8. A multi-support shared load-bearing structure according to claim 7, characterized in that, The load-bearing frame (2) is connected in the radial direction of the gas generator rotor (1) to the load-bearing outer casing (21), the turbine stage casing (22), the wideband vibration absorber (23), and the common bearing seat (24).

9. A multi-support shared load-bearing structure according to claim 7, characterized in that, The common bearing housing (24) includes a bearing housing body (241), a front support spring (243), and a rear support spring (242); One end of the front support spring (243) is connected to the bearing housing body (241), and the inner ring of the other end is connected to the outer ring of the front bearing (4) to bear the load of the gas generator rotor (1). One end of the rear support spring (242) is connected to the bearing housing body (241) on its outer surface, and the lower surface is connected to the outer ring of the middle bearing (5). The other end of the rear support spring (242) is connected to the outer ring of the rear bearing (6).

10. A multi-support shared load-bearing structure according to claim 7, characterized in that, An aircraft engine (7) is also installed at the end of the gas generator rotor (1) away from the load-bearing frame (2).

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