Bearing assembly with elastic support and aeroengine

Abstract

The present disclosure relates to a bearing assembly with elastic support and an aero-engine. The bearing assembly includes: a ball bearing (20) configured to be sleeved on a rotor (10); a roller bearing (50) coaxially arranged with the ball bearing (20) and configured to be sleeved on the rotor (10); a ball bearing elastic support (30) sleeved on an outer ring (21) of the ball bearing (20) and configured to be connected to a rigid support; a roller bearing elastic support (40) connected to or integrally formed with an outer ring (51) of the roller bearing (50) and configured to be connected to the rigid support, wherein an axial engagement structure is formed between the outer ring (21) of the ball bearing (20) and the roller bearing elastic support (40). The embodiments of the present disclosure can reduce the risk of elastic support failure to improve structural reliability.

Description

Technical Field

[0001] The present disclosure relates to the technical field of bearings, and particularly to a bearing assembly with elastic support and an aeroengine. Background Art

[0002] A turbofan aeroengine generally includes components such as a fan, a compressor, a combustion chamber, and a turbine. The core part of a gas turbine engine is located downstream of the fan, and generally includes a compressor, a combustion chamber, a turbine, and an exhaust section, and is located within a rotating casing. For a twin-spool aeroengine, its compressor part includes a fan booster stage and a high-pressure compressor, and its turbine part includes a high-pressure turbine coaxial with the high-pressure compressor and a low-pressure turbine coaxial with the fan. Generally, the shaft connecting the high-pressure compressor and the high-pressure turbine is called the high-pressure shaft, and the shaft connecting the fan and the low-pressure turbine is called the low-pressure shaft.

[0003] A part of the air reaching the fan enters the core duct. This part of the air is compressed step by step through the fan booster stage and the high-pressure compressor, and the compressed air reaches the combustion chamber. Fuel is mixed and burned with the compressed air in the combustion chamber, and the high-temperature combustion gas enters the high-pressure turbine from the combustion chamber and passes through the low-pressure turbine, and drives the high-pressure turbine and the low-pressure turbine to rotate. The high-pressure turbine and the low-pressure turbine respectively drive the high-pressure compressor and the fan through the high-pressure shaft and the low-pressure shaft. Finally, the burned gas is discharged through the tail nozzle.

[0004] During the normal operation of an aeroengine, both the high-pressure rotor and the low-pressure rotor are supported by rolling bearings. In order to adjust the rotor critical speed to avoid the resonance region and reduce the amplitude, in the related art, the bearing outer ring is often connected to an elastic support with a lower stiffness and used in combination with a squeeze film damper.

[0005] With the continuous increase in engine thrust requirements and higher speeds, four-point angular contact ceramic ball bearings are more commonly used. In order to adapt to high-speed performance, a number of oil drain holes are generally provided on the bearing outer ring; in order to ensure the alignment of the oil drain holes on the bearing outer ring and the elastic support, a circumferential positioning structure needs to be designed for the ball bearing outer ring and the ball bearing elastic support. The related art generally uses pins or baffles to prevent torsion or provide positioning for the bearing outer ring. Summary of the Invention

[0006] It has been found through research that the elastic support for the thrust bearing supporting the high-pressure rotor needs to bear an axial force of several tons or even more than ten tons. At the same time, in order to reduce the radial load of the ball bearing, the elastic support at the thrust bearing is often required to have a smaller support stiffness. However, under the condition of limited space, the length of the squirrel cage bars of the elastic support is limited. In order to achieve a lower stiffness, a smaller cross-section of the cage bars is designed to meet the requirement of a smaller radial stiffness. Under the condition of a higher axial force, the stress of this elastic support approaches or even exceeds the limit of the infinite fatigue life of the material, and it has a lower anti-torsion ability.

[0007] In addition, when a compressor or turbine blade shedding failure occurs in the engine, a large unbalanced force is transmitted to the elastic support through the bearing, causing the clearance of the squeeze film damper to approach zero, and the elastic support and the bearing thus whirl with a large amplitude. This large-amplitude whirling will cause the cage bars of the thrust bearing elastic support to undergo large torsion and bending. Torsion is more likely to cause the cage bars of the elastic support to break, causing the high-pressure rotor to lose its limiting function, resulting in the inability of the aero-engine rotor to rotate continuously and the aircraft being unable to return safely.

[0008] The inventors also found that the related art's method of using pins or baffles to prevent torsion or provide positioning for the outer ring of the bearing will result in an increase in the number of components, complex installation, and low reliability.

[0009] In view of this, the embodiments of the present disclosure provide a bearing assembly with an elastic support and an aero-engine, which can reduce the risk of elastic support failure and improve the structural reliability.

[0010] In one aspect of the present disclosure, a bearing assembly with an elastic support is provided, including:

[0011] A ball bearing configured to be sleeved on a rotor;

[0012] A roller bearing coaxially arranged with the ball bearing and configured to be sleeved on the rotor;

[0013] A ball bearing elastic support sleeved on the outer ring of the ball bearing and configured to be connected to a rigid support member;

[0014] A roller bearing elastic support connected to or integrally formed with the outer ring of the roller bearing and configured to be connected to the rigid support member,

[0015] wherein an axial fitting structure is formed between the outer ring of the ball bearing and the roller bearing elastic support.

[0016] In some embodiments, a radial fitting structure with a transition fit or an interference fit is formed between the outer ring of the ball bearing and the ball bearing elastic support.

[0017] In some embodiments, the axial fitting structure includes:

[0018] A first groove located in the roller bearing elastic support;

[0019] A first boss located on the outer ring of the ball bearing, extending axially towards the roller bearing and axially inserted into the first groove,

[0020] wherein there are clearances between the first boss and the first groove both circumferentially and axially.

[0021] In some embodiments, a radial engagement structure is formed between the outer ring of the ball bearing and the ball bearing spring support. The radial engagement structure includes:

[0022] A second groove, located in the ball bearing spring support;

[0023] A second boss, located on the outer ring of the ball bearing and radially embedded in the second groove,

[0024] wherein, the second boss and the second groove are in transitional fit or interference fit in the circumferential direction and / or the axial direction.

[0025] In some embodiments, the axial engagement structure includes a plurality of first bosses located on the outer ring of the ball bearing, and the radial engagement structure includes a plurality of second bosses located on the outer ring of the ball bearing. The plurality of second bosses all extend axially towards the roller bearing.

[0026] In some embodiments, the plurality of first bosses and the plurality of second bosses are alternately arranged on the outer ring of the ball bearing in the circumferential direction.

[0027] In some embodiments, the plurality of first bosses and the plurality of second bosses are equiangularly spaced in the circumferential direction.

[0028] In some embodiments, the outer ring of the ball bearing has a plurality of first oil drain holes arranged at intervals in the circumferential direction, and the ball bearing spring support has a plurality of second oil drain holes arranged at intervals in the circumferential direction. At least part of the plurality of first oil drain holes is radially aligned with at least part of the plurality of second oil drain holes. There is a fixed angular relationship between the plurality of first oil drain holes and the first bosses, and there is a fixed angular relationship between the plurality of second oil drain holes and the second grooves.

[0029] In some embodiments, the bottom of the inner raceway of the outer ring of the ball bearing has an annular oil drain groove, and the plurality of first oil drain holes are all located at the bottom of the annular oil drain groove.

[0030] In some embodiments, the rolling elements of the ball bearing include silicon nitride ceramic rolling elements.

[0031] In some embodiments, the ball bearing spring support includes: a first mounting section, a first cage section, and a first support section. The first cage section is bent relative to the first mounting section, and the first support section is bent relative to the first cage section. The first mounting section is configured to be connected to the rigid support. The first cage section includes a plurality of elastic ribs that are circumferentially spaced apart and axially extend. The first support section is sleeved on the outer ring of the ball bearing.

[0032] In some embodiments, the roller bearing elastic support includes: a second mounting section, a second squirrel cage section, and a second support section. The second squirrel cage section is bent relative to the second mounting section. The second support section axially extends on a side of the second squirrel cage section away from the ball bearing. The second mounting section is configured to be connected to the rigid support member and is connected between the first mounting section and the rigid support member. The second squirrel cage section includes a plurality of elastic ribs that are circumferentially spaced apart and axially extend. The second support section is sleeved on the outer ring of the roller bearing or is integrally formed with the outer ring of the roller bearing.

[0033] In some embodiments, the bearing assembly further includes:

[0034] An oil film squeeze damper, sleeved on the roller bearing elastic support and configured to form an oil film squeeze gap of 0.1 - 0.3 mm;

[0035] A sealing ring, located in a sealing groove on the roller bearing elastic support.

[0036] In one aspect of the present disclosure, there is provided an aeroengine including the aforementioned bearing assembly.

[0037] In some embodiments, the aeroengine further includes:

[0038] A front compressor shaft, fixedly connected to the inner ring of the ball bearing and the inner ring of the roller bearing as the rotor;

[0039] An intermediate inner casing, having an intermediate inner casing mounting edge that extends inward and serves as the rigid support member.

[0040] Therefore, according to the embodiments of the present disclosure, the ball bearing and the roller bearing are coaxially arranged on the rotating shaft, and the elastic supports between the rigid support member and the ball bearing and the roller bearing are respectively realized through the ball bearing elastic support and the roller bearing elastic support. The anti-twist of the roller bearing elastic support with a higher stiffness to the ball bearing elastic support with a lower stiffness is realized by using the axial engagement structure formed between the outer ring of the ball bearing and the roller bearing elastic support, thereby reducing the risk of failure of the ball bearing elastic support and improving the reliability of the structure of the bearing assembly. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] The drawings forming a part of the specification depict embodiments of the present disclosure and, together with the description, are used to explain the principles of the present disclosure.

[0042] Referring to the drawings, the present disclosure can be more clearly understood from the following detailed description, where:

[0043] Figure 1 is a schematic installation structure diagram of some embodiments of the bearing assembly with elastic support according to the present disclosure;

[0044] Figure 2 is a schematic structural view of some embodiments of a bearing assembly with elastic support according to the present disclosure;

[0045] Figure 3 is a schematic structural view of the ball bearing elastic support in some embodiments of a bearing assembly with elastic support according to the present disclosure;

[0046] Figure 4 is a three-dimensional structural view of the outer ring of a ball bearing in some embodiments of a bearing assembly with elastic support according to the present disclosure;

[0047] Figure 5 is an internal structural view of the outer ring of a ball bearing in some embodiments of a bearing assembly with elastic support according to the present disclosure;

[0048] Figure 6 is a three-dimensional structural view of the roller bearing elastic support in some embodiments of a bearing assembly with elastic support according to the present disclosure;

[0049] Figure 7 is an internal structural view of the roller bearing elastic support in some embodiments of a bearing assembly with elastic support according to the present disclosure;

[0050] Figure 8 is Figure 2 an enlarged view of the position corresponding to circle A in

[0051] Figure 9 is Figure 2 an enlarged view of the position corresponding to circle B from another angle in

[0052] Figure 10 is Figure 2 an enlarged view of the position corresponding to circle C in

[0053] Figure 11 is Figure 10 a partial enlarged view from the D perspective in

[0054] Figure 12 is a schematic structural view of some embodiments of an aeroengine according to the present disclosure.

[0055] It should be understood that the dimensions of the various parts shown in the drawings are not drawn according to actual proportional relationships. In addition, the same or similar reference numerals represent the same or similar components. Detailed implementation manners

[0056] Various exemplary embodiments of the present disclosure will now be described in detail with reference to the accompanying drawings. The description of the exemplary embodiments is merely illustrative and in no way limits the present disclosure or its application or use. The present disclosure may be implemented in many different forms and is not limited to the embodiments described herein. These embodiments are provided to make the present disclosure thorough and complete, and to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that: unless otherwise specifically stated, the relative arrangements of components and steps, the compositions of materials, numerical expressions, and numerical values set forth in these embodiments should be construed as merely exemplary and not as limitations.

[0057] The terms "first", "second", and similar terms used in the present disclosure do not denote any order, quantity, or importance, but are merely used to distinguish different parts. Words such as "including" or "comprising" mean that the elements before the word cover the elements listed after the word, and do not exclude the possibility of also covering other elements. Terms such as "upper", "lower", "left", "right", etc. are only used to indicate relative positional relationships, and when the absolute position of the object being described changes, the relative positional relationship may also change accordingly.

[0058] In the present disclosure, when it is described that a specific device is located between a first device and a second device, there may or may not be an intermediate device between the specific device and the first device or the second device. When it is described that a specific device is connected to other devices, the specific device may be directly connected to the other devices without an intermediate device, or may not be directly connected to the other devices and have an intermediate device.

[0059] All terms used in the present disclosure (including technical terms or scientific terms) have the same meaning as understood by those of ordinary skill in the art to which the present disclosure pertains, unless otherwise specifically defined. It should also be understood that terms defined in a general dictionary, such as those, should be construed as having a meaning consistent with their meaning in the context of the relevant art, and should not be interpreted in an idealized or overly formal sense, unless specifically defined as such herein.

[0060] Technologies, methods, and devices known to those of ordinary skill in the relevant art may not be discussed in detail, but where appropriate, the technologies, methods, and devices should be regarded as part of the specification.

[0061] Combined Figures 1-12 As shown, the embodiments of the present disclosure provide a bearing assembly with an elastic support and an aeroengine, which can reduce the risk of elastic support failure and improve structural reliability.

[0062] Reference Figure 1, in some embodiments, a bearing assembly with elastic supports includes: a ball bearing 20, a roller bearing 50, a ball bearing elastic support 30, and a roller bearing elastic support 40. The ball bearing 20 can be sleeved on the rotor 10. The roller bearing 50 is coaxially arranged with the ball bearing 20 and can be sleeved on the rotor 10. The ball bearing elastic support 30 is sleeved on the outer ring 21 of the ball bearing 20 and is configured to be connected to a rigid support.

[0063] The roller bearing elastic support 40 is connected to or integrally formed with the outer ring 51 of the roller bearing 50 and is configured to be connected to the rigid support. The roller bearing elastic support 40 can be configured to provide centering for the roller bearing 50 and bear the load when the structure of the bearing assembly is in a high-load condition or a fault condition. For example, when installed in an intermediate casing, when one or more of the fan blades, compressor blades, or turbine blades are partially or completely damaged, it bears the load caused by the failure of any such blades. An axial fitting structure is formed between the outer ring 21 of the ball bearing 20 and the roller bearing elastic support 40. The stiffness of the roller bearing elastic support 40 is greater than that of the ball bearing elastic support.

[0064] In this embodiment, the ball bearing and the roller bearing are coaxially arranged on the rotating shaft, and the elastic supports between the rigid support and the ball bearing and the roller bearing are respectively realized through the ball bearing elastic support and the roller bearing elastic support. The axial fitting structure formed between the outer ring of the ball bearing and the roller bearing elastic support enables the roller bearing elastic support with higher stiffness to prevent torsion of the ball bearing elastic support with lower stiffness, thereby reducing the risk of failure of the ball bearing elastic support and improving the reliability of the bearing assembly structure.

[0065] Compared with the pin anti-torsion structure adopted by the ball bearing elastic support in the related art, the anti-torsion of the axial fitting structure can achieve different force transmission paths. When the structure where the bearing assembly is installed is in a high-load condition or a fault condition, the rotor is subjected to a large unbalanced force and generates large-amplitude whirling. The torque brought by the rotor to the outer ring of the ball bearing can be directly transmitted to the roller bearing elastic support through the axial fitting structure, thereby reducing the torque transmitted to the ball bearing elastic support, and effectively preventing the ball bearing elastic support from being damaged under a large torque. Compared with directly stopping on the ball bearing elastic support, the torque transmitted to the ball bearing elastic support will be effectively reduced, for example, reduced by 50%.

[0066] In addition, this axial fitting structure can also achieve the locking torque stop of the ball bearing elastic support or the roller bearing elastic support during the installation process of the bearing assembly. Overall, it can effectively improve the fulcrum strength of this bearing assembly structure. When applied to an aeroengine, it can work normally under the conditions of engine blade flying off and unconventional working conditions, has high reliability, and is convenient for installation.

[0067] In this embodiment, the rigid support member can be any structural member that can achieve rigid support, such as the intermediate inner casing mounting edge 81 of the intermediate inner casing 82 in an aeroengine. The rotor can be any object that rotates around an axis, such as the front shaft of a compressor in an aeroengine. The axial, circumferential, and radial directions mentioned hereinafter are all relative to the axis of the rotor.

[0068] Refer to Figures 2-5 , in some embodiments, the axial fitting structure includes: a first groove 411 and a first boss 213. The first groove 411 is located on the roller bearing elastic support 40. The first boss 213 is located on the outer ring 21 of the ball bearing 20, extends axially towards the roller bearing 50, and is axially embedded in the first groove 411. There are gaps between the first boss 213 and the first groove 411 both circumferentially and axially. In Figures 6-8 , the first groove 411 can be formed by two protrusions 4111 and 4112 extending axially on the roller bearing elastic support 40.

[0069] For an aeroengine, during its normal operation, the ball bearing supports the front shaft of the high-pressure compressor and bears the axial force and part of the radial force generated by the high-pressure rotor. The outer ring of the roller bearing can be connected to an squeeze film damper. The squeeze film structure provides radial damping for the rotor system and bears most of the radial force. During a failure mode caused by the flying off of a fan blade or a compressor or turbine blade, the rotor will generate a very high unbalanced load, which will cause the above-mentioned squeeze film gap to close, and due to the large whirling, a harmonic driving effect will be generated. At this time, a large torque will be generated on the elastic support. During this period, the roller bearing elastic support will bear large radial and axial loads, and due to its low stiffness and non-torsion-resistant characteristics, if a large circumferential torsion occurs, it is easy to be damaged. However, in fact, the circumferential torsion will be limited by the cooperation between the first boss and the first groove, thus preventing the roller bearing elastic support from being twisted off.

[0070] A circumferential gap i1 and an axial gap i2 can be formed between the first boss and the first groove. These two gaps can avoid abnormal wear between the outer ring of the ball bearing and the roller bearing elastic support during the normal operation of the bearing assembly, and prevent the support stiffness of the roller bearing elastic support from changing. These gaps can be eliminated when the outer ring of the ball bearing undergoes circumferential torsion, so as to transmit the torsion moment to the roller bearing elastic support. In addition, during the installation of the outer ring of the ball bearing on the roller bearing elastic support, when tightening the compression nut, a tightening torque is applied on the outer ring of the ball bearing, and the first boss on the outer ring of the ball bearing can play a stop role, which is convenient for installation.

[0071] Refer to Figures 2-3 and Figure 9, in some embodiments, a radial fitting structure with a transition fit or interference fit is formed between the outer ring 21 of the ball bearing 20 and the ball bearing elastic support 30. This radial fitting structure can be used to position the outer ring 21 of the ball bearing 20 and the ball bearing elastic support 30, and achieve stopping and anti-twisting between the two. For related technologies that do not prevent twisting of the two, during continuous operation of the rotor, once relative rotation occurs between the outer ring of the ball bearing and the ball bearing elastic support, additional heat will be generated, and this heat cannot be taken away by the lubricating oil in time. Eventually, the temperatures of the ball bearing and the ball bearing elastic support will be too high and failure will occur. The stopping function achieved by the radial fitting structure of this embodiment will prevent relative movement between the outer ring of the ball bearing and the ball bearing elastic support, so that no additional heat is generated. This is more beneficial for ensuring continuous rotation of the bearing under special working conditions.

[0072] In Figure 2 , Figure 3 and Figure 9 , the radial fitting structure includes: a second groove 331 and a second boss 211. The second groove 331 is located on the ball bearing elastic support 30. The second boss 211 is located on the outer ring 21 of the ball bearing 20 and is radially embedded in the second groove 331. The second boss 211 and the second groove 331 are in a transition fit or interference fit in the circumferential direction and / or the axial direction. Compared with the gap between the first boss and the first groove in the circumferential or axial direction, the gap between the second boss and the second groove in the circumferential or axial direction is smaller. The second groove 331 can be formed by two protrusions 3311 and 3312 extending radially inward on the ball bearing elastic support 30.

[0073] Referring to Figure 3 , Figure 4 and Figure 6 , in some embodiments, the axial fitting structure includes a plurality of first bosses 213 located on the outer ring 21 of the ball bearing 20, and the radial fitting structure includes a plurality of second bosses 211 located on the outer ring 21 of the ball bearing 20. The plurality of second bosses 211 all extend axially towards the roller bearing 50. By arranging a plurality of bosses on the outer ring 21, functions such as effective positioning of the elastic support, anti-twisting, and installation stopping can be achieved. Compared with the pin positioning method in related technologies, the number of parts is reduced, the structure of the bearing assembly is simplified, the weight is reduced, and there is a higher-precision anti-twisting gap control effect, which is more beneficial for controlling the torsional deformation of the ball bearing elastic support. In addition, this also makes the installation operation more convenient and has higher reliability.

[0074] In Figure 4Among them, the multiple first bosses 213 and the multiple second bosses 211 are alternately arranged circumferentially on the outer ring 21 of the ball bearing 20. This is beneficial to making the force on the outer ring 21 more balanced. In some embodiments, the multiple first bosses 213 and the multiple second bosses 211 can be arranged at equal angular intervals circumferentially. This is also beneficial to making the force on the outer ring 21 more balanced.

[0075] Reference Figures 2-5 and Figures 10-11 , in some embodiments, the outer ring 21 of the ball bearing 20 has a plurality of first oil drain holes 212 arranged at circumferential intervals, and the ball bearing elastic support 30 has a plurality of second oil drain holes 332 arranged at circumferential intervals. At least part of the plurality of first oil drain holes 212 is radially aligned with at least part of the plurality of second oil drain holes 332. For example, the number of the plurality of first oil drain holes 212 is equal to the number of the plurality of second oil drain holes 332, and they are in one-to-one correspondence. There is a fixed angular relationship between the plurality of first oil drain holes 212 and the first bosses 213, and there is a fixed angular relationship between the plurality of second oil drain holes 332 and the second grooves 331. The angular relationship here refers to the positional relationship in the angular direction relative to the rotor axis.

[0076] The first oil drain holes 212 and the second oil drain holes 332 can be used to realize the timely discharge of the lubricating oil on the outer ring 21 to improve the cooling and lubrication effect of the ball bearing. In order to enable the first oil drain holes 212 to be accurately aligned with the second oil drain holes 332 (see Figure 10 and Figure 11 ), the cooperation between the second bosses 211 on the outer ring 21 and the second grooves 331 on the ball bearing elastic support 30 effectively provides circumferential positioning for the first oil drain holes 212 on the outer ring 21.

[0077] In Figure 4 , Figure 5 , Figure 10 and Figure 11 , the bottom of the inner raceway on the inner side of the outer ring 21 of the ball bearing 20 has an annular oil drain groove 214, and the plurality of first oil drain holes 212 are all located at the bottom of the annular oil drain groove 214. The annular oil drain groove 214 can be used to guide the lubricating oil, and the shape of the first oil drain holes 212 can be set to be strip-shaped, and the edges do not extend beyond the annular oil drain groove 214 so as to match the annular oil drain groove 214.

[0078] Reference Figure 1 , in some embodiments, in addition to the outer ring 21, the ball bearing 20 further includes rolling elements 22, a rolling element cage 27 and an inner ring. The inner ring can be integral or split, for example Figure 1The split inner rings 23 and 24 therein. The rolling elements 22 include silicon nitride ceramic rolling elements. Rolling elements of this material can significantly reduce the heat generated by the bearing and improve the high-speed performance of the bearing.

[0079] In Figure 1 , the roller bearing 50 includes an inner ring 54, rolling elements 53, a rolling element cage 52, and an outer ring 51. The outer ring 51 can be connected to or integrally formed with the roller bearing elastic support 40. To achieve axial positioning of the ball bearing and the roller bearing, a plurality of stoppers can be provided in the bearing assembly. For example, a plurality of mounting holes 333 can be provided on the ball bearing elastic support 30, and a plurality of stoppers 61 can be respectively fixed to the outer ring of the ball bearing 20 on the side away from the roller bearing 50 through a plurality of bolts 12. Another example is to provide a stopper 62 between the inner ring of the ball bearing and the inner ring of the roller bearing, and a stopper 63 on the side of the inner ring 54 of the roller bearing away from the ball bearing 20, etc.

[0080] Referring to Figure 2 and Figure 3 , in some embodiments, the ball bearing elastic support 30 includes: a first mounting section 31, a first cage section 32, and a first support section 33. The first cage section 32 is bent relative to the first mounting section 31, and the first support section 33 is bent relative to the first cage section 32. The first mounting section 31, the first cage section 32, and the first support section 33 can jointly form a folded-back structure. The first mounting section 31 can be formed as a flange structure extending radially outward, and a plurality of bolt holes and pin holes can be provided on this flange structure to limit its axial and circumferential movement. The first mounting section 31 can be connected to the rigid support.

[0081] The first cage section 32 includes a plurality of elastic ribs spaced circumferentially and extending axially. The first support section 33 is sleeved on the outer ring 21 of the ball bearing 20. A plurality of mounting holes 333 and second oil drain holes 332 can be provided on the first support section 33. A second groove 331 can also be provided on the first support section 33.

[0082] Referring to Figure 2 , Figures 6-7 , in some embodiments, the roller bearing elastic support 40 includes: a second mounting section 41, a second cage section 42, and a second support section 43. The second cage section 42 is bent relative to the second mounting section 41, and the second support section 43 axially extends on the side of the second cage section 42 away from the ball bearing 20. The second mounting section 41 is configured to be connected to the rigid support and is connected between the first mounting section 31 and the rigid support. This is equivalent to setting the mounting points of both the roller bearing elastic support and the ball bearing elastic support on the same side of the rigid support, which is beneficial for a more compact space layout.

[0083] The second mounting section 41 can also be formed as a radially extending flange structure, on which a plurality of bolt holes and pin holes can be provided to restrict its movement in the axial and circumferential directions. A positioning pin 412 can be provided on the second mounting section 41 to accurately position it with the first mounting section 31 during installation. In addition to using bolts or pins to connect the first mounting section or the second mounting section to the rigid support, other connection methods can also be used, such as welding, riveting, etc.

[0084] The second squirrel-cage section 42 includes a plurality of elastic ribs that are circumferentially spaced apart and axially extended. The second support section 43 is sleeved on the outer ring 51 of the roller bearing 50 or integrally formed with the outer ring 51 of the roller bearing 50. The first groove 411 can be provided on the second mounting section 41 or at a position on the second squirrel-cage section 42 close to the second mounting section 41.

[0085] Reference Figure 1 , in some embodiments, the bearing assembly further includes: an squeeze-film damper 70 and a seal ring. The squeeze-film damper 70 is sleeved on the roller bearing elastic support 40 and is configured to form an squeeze-film gap 701 of 0.1~0.3 mm. The seal ring is located in the seal groove 431 on the roller bearing elastic support 40. Specifically, the squeeze-film damper 70 can be provided on the radial outer side of the outer ring of the roller bearing integrated with the roller bearing elastic support 40 to form a circumferentially continuous squeeze film. The vibration reduction of the rotor can be achieved through the squeeze film. The squeeze-film damper 70 includes a housing, one end of the housing is also fixed on the rigid support, and the gap between the other end and the outer ring of the roller bearing is filled with lubricating oil to form an squeeze film, and the sealing of the oil film is also achieved through the seal ring embedded in the seal groove 431. The size of the squeeze-film gap determines the damping characteristics of the damper, and usually this gap is between 0.1 mm and 0.3 mm.

[0086] Each of the above embodiments of the bearing assembly can be used in various scenarios that require supporting a rotor, such as being applied to an aeroengine with higher requirements for rotor stability and environmental complexity. Correspondingly, the present disclosure also provides an aeroengine including any one of the above embodiments of the bearing assembly.

[0087] Reference Figure 12 At the position corresponding to the circle E in

[0088] Reference Figure 12, the aeroengine may be a gas turbine engine (or a turbofan engine), the main thrust of which comes from the fan 91, and generally includes an intermediate casing 94, a fan booster stage 92, and a high-pressure compressor 93 downstream thereof. The outlet of the high-pressure compressor 93 is a combustion chamber, and downstream of the combustion chamber is a high-pressure turbine 97, and a low-pressure turbine 98 is connected behind the high-pressure turbine 97. The shaft connecting the high-pressure compressor 93 and the high-pressure turbine 97 is a high-pressure shaft 95, and the shaft connecting the low-pressure compressor and the low-pressure turbine 98 is a low-pressure shaft 96. It should be recognized that Figure 1 The exemplary turbofan engine shown in is only for illustration, and in other exemplary embodiments, the aeroengine may have any other suitable configuration. For example, in other exemplary embodiments, the fan may be configured in any other suitable manner (e.g., as a fixed-pitch fan), and any other suitable fan frame configuration may also be used for support. In addition, it should also be recognized that in other exemplary embodiments, any other suitable configurations of the high-pressure compressor and the high-pressure turbine may be used. In other exemplary embodiments, aspects of the present disclosure may be incorporated into any other suitable gas turbine engine. For example, in other exemplary embodiments, aspects of the present disclosure may be incorporated into, for example, a turboshaft engine, a turboprop engine, a turbocore engine, a turbojet engine, etc., and applied to turbine engines in other fields.

[0089] So far, the embodiments of the present disclosure have been described in detail. To avoid obscuring the concept of the present disclosure, some details well known in the art have not been described. Those skilled in the art can fully understand how to implement the technical solutions disclosed herein based on the above description.

[0090] Although some specific embodiments of the present disclosure have been described in detail by way of examples, those skilled in the art should understand that the above examples are only for illustration and not for limiting the scope of the present disclosure. Those skilled in the art should understand that the above embodiments can be modified or some technical features can be equivalently replaced without departing from the scope and spirit of the present disclosure. The scope of the present disclosure is defined by the appended claims.

Claims

1. A bearing assembly with elastic support, characterized in that, Comprising: A ball bearing (20), configured to be sleeved on a rotor (10); A roller bearing (50), coaxially arranged with the ball bearing (20) and configured to be sleeved on the rotor (10); A ball bearing elastic support (30), sleeved on an outer ring (21) of the ball bearing (20) and configured to be connected to a rigid support; A roller bearing elastic support (40), connected to or integrally formed with an outer ring (51) of the roller bearing (50) and configured to be connected to the rigid support, wherein, an axial engagement structure is formed between the outer ring (21) of the ball bearing (20) and the roller bearing elastic support (40).

2. The bearing assembly according to claim 1, characterized in that, A radial engagement structure with a transitional fit or an interference fit is formed between the outer ring (21) of the ball bearing (20) and the ball bearing elastic support (30).

3. The bearing assembly according to claim 1, wherein, The axial engagement structure includes: A first groove (411), located on the roller bearing elastic support (40); A first boss (213), located on the outer ring (21) of the ball bearing (20), extending axially towards the roller bearing (50) and axially embedded in the first groove (411), wherein, there are gaps between the first boss (213) and the first groove (411) both circumferentially and axially.

4. The bearing assembly according to claim 3, wherein, A radial engagement structure is formed between the outer ring (21) of the ball bearing (20) and the ball bearing elastic support (30), and the radial engagement structure includes: A second groove (331), located on the ball bearing elastic support (30); A second boss (211), located on the outer ring (21) of the ball bearing (20) and radially embedded in the second groove (331), wherein, the second boss (211) and the second groove (331) are in a transitional fit or an interference fit both circumferentially and / or axially.

5. The bearing assembly according to claim 4, wherein, The axial engagement structure includes a plurality of first bosses (213) located on the outer ring (21) of the ball bearing (20), and the radial engagement structure includes a plurality of second bosses (211) located on the outer ring (21) of the ball bearing (20), and the plurality of second bosses (211) all extend axially towards the roller bearing (50).

6. The bearing assembly according to claim 5, characterized in that, The plurality of first bosses (213) and the plurality of second bosses (211) are alternately arranged circumferentially on the outer ring (21) of the ball bearing (20).

7. The bearing assembly according to claim 5, characterized in that, The plurality of first bosses (213) and the plurality of second bosses (211) are equally angularly spaced circumferentially.

8. The bearing assembly according to claim 4, characterized in that, The outer ring (21) of the ball bearing (20) has a plurality of first oil drain holes (212) arranged at intervals circumferentially, the ball bearing elastic support (30) has a plurality of second oil drain holes (332) arranged at intervals circumferentially, at least part of the plurality of first oil drain holes (212) is radially aligned with at least part of the plurality of second oil drain holes (332), there is a fixed angular relationship between the plurality of first oil drain holes (212) and the first boss (213), and there is a fixed angular relationship between the plurality of second oil drain holes (332) and the second groove (331).

9. The bearing assembly according to claim 8, wherein, The bottom of the inner raceway of the outer ring (21) of the ball bearing (20) has an annular oil drain groove (214), and the plurality of first oil drain holes (212) are all located at the bottom of the annular oil drain groove (214).

10. The bearing assembly according to claim 1, characterized in that, The rolling elements (22) of the ball bearing (20) include silicon nitride ceramic rolling elements.

11. The bearing assembly according to claim 1, wherein, The ball bearing elastic support (30) includes: a first mounting section (31), a first squirrel cage section (32), and a first support section (33). The first squirrel cage section (32) is bent relative to the first mounting section (31), and the first support section (33) is bent relative to the first squirrel cage section (32). The first mounting section (31) is configured to be connected to the rigid support. The first squirrel cage section (32) includes a plurality of elastic ribs that are circumferentially spaced apart and axially extend. The first support section (33) is sleeved on the outer ring (21) of the ball bearing (20).

12. The bearing assembly according to claim 11, wherein, The roller bearing elastic support (40) includes: a second mounting section (41), a second squirrel cage section (42), and a second support section (43). The second squirrel cage section (42) is bent relative to the second mounting section (41), and the second support section (43) axially extends on the side of the second squirrel cage section (42) away from the ball bearing (20). The second mounting section (41) is configured to be connected to the rigid support and is connected between the first mounting section (31) and the rigid support. The second squirrel cage section (42) includes a plurality of elastic ribs that are circumferentially spaced apart and axially extend. The second support section (43) is sleeved on the outer ring (51) of the roller bearing (50) or is integrally formed with the outer ring (51) of the roller bearing (50).

13. The bearing assembly according to claim 1, characterized in that It further includes: An squeeze film damper (70), sleeved on the roller bearing elastic support (40), and configured to form an squeeze film gap (701) of 0.1 - 0.3 mm; A sealing ring, located in a sealing groove (431) on the roller bearing elastic support (40).

14. An aeroengine, characterized in that, It includes: The bearing assembly according to any one of claims 1 to 13.

15. The aeroengine according to claim 14, wherein It further includes: The front compressor shaft is fixedly connected to the inner rings (23, 24) of the ball bearing (20) and the inner ring (54) of the roller bearing (50) as the rotor (10). The intermediate inner casing (82) has an intermediate inner casing mounting edge (81) that extends inward and serves as the rigid support.

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