CN215890216U

CN215890216U - Aircraft engine

Info

Publication number: CN215890216U
Application number: CN202120608103.1U
Authority: CN
Inventors: 梁霄; 徐和; 赵越超
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2021-03-25
Filing date: 2021-03-25
Publication date: 2022-02-22
Anticipated expiration: 2031-03-25

Abstract

The utility model discloses an aircraft engine. The aero-engine comprises a casing, a bearing, a low-pressure rotor and a high-pressure rotor, wherein the bearing comprises an inner ring, a middle ring, an outer ring and rolling bodies, the inner ring is connected with the low-pressure rotor, the middle ring is connected with the casing, the outer ring is connected with the high-pressure rotor, the outer ring, the middle ring and the inner ring are sequentially arranged from outside to inside in the radial direction, and the rolling bodies are arranged between the inner ring and the middle ring and between the outer ring and the middle ring. The two sides of the middle ring are provided with rolling bodies to support the inner ring and the outer ring at the same time, the inner ring is connected with the low-pressure rotor, and the outer ring is connected with the high-pressure rotor, so that the bearing can support the two rotors at the same time, and the coaxiality of the rotors is improved.

Description

Aircraft engine

Technical Field

The utility model relates to an aircraft engine.

Background

In general, as shown in fig. 1, a rolling bearing includes an inner ring 1a, an outer ring 3a, rolling elements 8a, and a cage 5 a. The supporting scheme of the aircraft engine generally involves five to eight fulcrums, namely five to eight sets of bearings, and the force bearing case generally needs three to four. The weight of the whole machine is high due to more parts, the thrust-weight ratio is further improved and is greatly limited, and meanwhile, the reliability of the whole machine is poor and the assembly difficulty is high due to more parts.

It is important to note here that the statements in this background section merely provide background information related to the present disclosure and may not necessarily constitute prior art.

SUMMERY OF THE UTILITY MODEL

The utility model provides an aircraft engine, which aims to improve the coaxiality of a rotor.

The utility model provides an aircraft engine, which comprises a casing, a bearing, a low-pressure rotor and a high-pressure rotor, wherein the bearing comprises

The inner ring is connected with the low-pressure rotor;

the middle ring is connected with the casing;

the outer ring is connected with the high-pressure rotor, and the outer ring, the middle ring and the inner ring are sequentially arranged from outside to inside in the radial direction; and

and rolling bodies are arranged between the inner ring and the middle ring and between the outer ring and the middle ring.

In some embodiments, both the inner and outer surfaces of the middle ring are provided with raceways for accommodating rolling elements.

In some embodiments, the rolling elements comprise balls, cylindrical rollers, tapered rollers, or spherical rollers.

In some embodiments, balls are arranged between the inner ring and the middle ring, and a cylindrical roller is arranged between the outer ring and the middle ring; or a cylindrical roller is arranged between the inner ring and the middle ring, and a ball is arranged between the outer ring and the middle ring.

In some embodiments, the middle ring includes an adapter shaft extending axially outward for connection with the case.

In some embodiments, the coupling shaft is a stepped shaft and includes a first shaft section and a second shaft section, an outer surface of the first shaft section forming a locating surface, the second shaft section having threads disposed thereon.

In some embodiments, the middle ring is provided with an oil groove, and the oil groove is used for conveying lubricating oil.

In some embodiments, the middle ring is further provided with at least two lubricating oil passages communicated with the oil groove, and the at least two lubricating oil passages are used for conveying lubricating oil to the inner surface of the middle ring.

In some embodiments, the bearing further comprises a cage for mounting the rolling bodies.

In some embodiments, the outer ring comprises a first outer half ring and a second outer half ring axially interconnected; and/or the inner ring comprises a first inner half ring and a second inner half ring which are mutually connected in the axial direction.

The aero-engine provided by the utility model comprises a casing, a bearing, a low-pressure rotor and a high-pressure rotor, wherein the bearing comprises an inner ring, a middle ring, an outer ring and rolling bodies, the inner ring is connected with the low-pressure rotor, the middle ring is connected with the casing, the outer ring is connected with the high-pressure rotor, the outer ring, the middle ring and the inner ring are sequentially arranged from outside to inside in the radial direction, and the rolling bodies are arranged between the inner ring and the middle ring and between the outer ring and the middle ring. The two sides of the middle ring are provided with rolling bodies to support the inner ring and the outer ring at the same time, the inner ring is connected with the low-pressure rotor, and the outer ring is connected with the high-pressure rotor, so that the bearing can support the two rotors at the same time, and the coaxiality of the rotors is improved.

Other features of the present invention and advantages thereof will become apparent from the following detailed description of exemplary embodiments thereof, which proceeds with reference to the accompanying drawings.

Drawings

The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the utility model and together with the description serve to explain the utility model without limiting the utility model. In the drawings:

fig. 1 is a schematic structural view of a rolling bearing of the prior art.

Fig. 2 is a schematic cross-sectional structure of a bearing according to some embodiments of the present invention.

Fig. 3 is a schematic cross-sectional structure view of the middle ring of the bearing shown in fig. 2.

Fig. 4 is a side view of the bearing shown in fig. 2.

Fig. 5 is an assembly structure view of another embodiment of the middle ring shown in fig. 3.

FIG. 6 is a schematic cross-sectional view of a bearing according to further embodiments of the present invention.

Fig. 7 is a sectional structure view of the middle ring of the bearing shown in fig. 6.

Fig. 8 is an assembly structure view of the middle ring shown in fig. 7.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the utility model, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail, but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.

Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously positioned and the spatially relative descriptors used herein interpreted accordingly.

The aircraft engine comprises a casing, a bearing, a low-pressure rotor and a high-pressure rotor. Wherein the bearings are used to support the low pressure rotor and the high pressure rotor. Referring to fig. 2, in some embodiments, the bearing includes an inner ring 1, a middle ring 2, an outer ring 3, and rolling elements, the inner ring 1 is connected to the low pressure rotor, the middle ring 2 is connected to the casing, the outer ring 3 is connected to the high pressure rotor, and the outer ring 3, the middle ring 2, and the inner ring 1 are sequentially arranged from outside to inside in a radial direction. Rolling bodies are arranged between the inner ring 1 and the middle ring 2 and between the outer ring 3 and the middle ring 2.

The two sides of the middle ring 2 are provided with rolling bodies to support the inner ring 1 and the outer ring 3 at the same time, the inner ring 1 is connected with the low-pressure rotor, and the outer ring 3 is connected with the high-pressure rotor, so that the bearing can support the two rotors at the same time, and the coaxiality of the rotors is improved. The improvement of the coaxiality of the high-pressure rotor and the low-pressure rotor is beneficial to preventing the collision and friction between the high-pressure rotor and the low-pressure rotor and is also beneficial to reducing the fuel consumption rate.

Referring to fig. 3, in some embodiments, both the inner and outer surfaces of the middle ring 2 are provided with raceways for accommodating rolling bodies. In the embodiment shown in particular in fig. 3, the inner surface of the middle ring 2 is provided with an inner raceway 23 and the outer surface is provided with an outer raceway 24. The inner raceway 23 is intended to receive the cylindrical rollers 6 and the outer raceway 24 is intended to receive the balls 7.

Referring to fig. 6, in other embodiments, both the inner and outer surfaces of the middle ring 2 are provided with raceways. The inner raceway 23 of the intermediate ring 2 is intended to receive the balls 7 and the outer raceway 24 is intended to receive the cylindrical rollers 6.

In other exemplary embodiments, which are not shown in the figures, the rolling elements can also be tapered rollers or spherical rollers. Also the inner and outer races of the middle ring can be used to accommodate the same type of rolling elements, e.g. the middle ring is provided with balls on both sides or cylindrical rollers. The inner and outer races of the middle ring can also be used to accommodate different types of rolling elements.

Referring to fig. 2, in some embodiments, the bearing further comprises a cage 5. The cage 5 is used for mounting rolling elements. For ease of installation, with reference to fig. 5, the cage 5, the rolling elements and the middle ring 2 may be assembled as a whole. The cage 5 is then provided with locking points for the purpose of retaining the rolling bodies within the raceways.

In some embodiments, referring to fig. 2, the middle ring 2 includes an adapter shaft 22 extending axially outward. The transfer shaft 22 is used to connect with the casing. The middle ring of this embodiment adopts the design of integrating, all sets up the raceway at inner surface and surface, and sets up the switching axle simultaneously to reduce part quantity, reduce the assembly degree of difficulty.

Referring to fig. 4, in some embodiments, the adapter shaft 22 is a stepped shaft and includes a first shaft section 221 and a second shaft section 222, an outer surface of the first shaft section 221 forms a locating surface, and the second shaft section 222 is provided with threads thereon. The outer surface of the first shaft section 221 is used for mounting and positioning with the support seat, the thread arranged on the second shaft section 222 is used for mounting a nut, and the nut is used for fixing the axial position of the bearing.

The support stiffness of the adapter shaft 22 of some embodiments is adjustably set to facilitate controlling engine vibration.

In some embodiments, referring to fig. 2, an oil groove 21 is provided on the middle ring 2, and the oil groove 21 is used for conveying lubricating oil. The bearings are provided with oil grooves 21, so that the lubricating system of the engine can be simplified.

In some embodiments, referring to fig. 2 and 3, the middle ring 2 is further provided with at least two lubrication oil passages 25 communicating with the oil groove 21, and the at least two lubrication oil passages 25 are used for conveying the lubricating oil to the inner surface of the middle ring 2. The lubrication oil path 25 is used for lubrication of the bearing working surface, and includes lubrication between the rolling elements and the raceway, between the cage 5 and the guide surface, and between the cage 5 and the rolling elements.

Specifically, some of the at least two lubrication oil passages 25 communicate with the raceway.

In some embodiments, with reference to fig. 2, the outer ring 3 comprises a first outer half ring 31 and a second outer half ring 32 axially connected to each other. Referring to fig. 6, the inner ring 1 includes a first inner half ring 11 and a second inner half ring 12 that are connected to each other in the axial direction.

The structure of the bearing according to the embodiment of the present invention will be described in detail with reference to fig. 2 to 8.

Fig. 2 to 5 show a bearing of an embodiment. As shown in fig. 2, the bearing of this embodiment includes an inner ring 1, an intermediate ring 2, an outer ring 3, a cage 5, cylindrical rollers 6, and balls 7.

As shown in fig. 3, the middle ring 2 includes an oil groove 21, an adapter shaft 22, an inner race 23, an outer race 24, and a lubrication oil passage 25. The inner raceway 23 is rectangular in cross section and the outer raceway 24 is semicircular in cross section, as shown in fig. 2, the inner raceway 23 being for accommodating the cylindrical rollers 6 and the outer raceway 24 being for accommodating the balls 7. The inner surface of the outer ring 3 is also provided with a raceway, and the outer surface of the inner ring 1 is also provided with a raceway. The cage 5 is used for mounting rolling elements. The outer ring 3 includes a first outer half ring 31 and a second outer half ring 32.

The middle ring 2 of the bearing of the embodiment adopts integrated design and manufacturing technology, the inner surface and the outer surface of the middle ring 2 are both provided with a roller path, and the middle ring 2 is simultaneously provided with a transfer shaft 22. The adapter shaft of integrating the design reduces part quantity, reduces the assembly degree of difficulty. The adapter shaft 22 is used for installing and positioning with the supporting seat, and is provided with threads for installing a nut which is used for fixing the axial position of the bearing. The support stiffness of the transfer shaft 22 is adjustable, which is helpful for controlling engine vibration.

As shown in fig. 2 and 3, the oil groove 21 communicates with three lubrication oil passages 25, and the lubrication oil enters from the oil groove 21 and flows to different positions of the middle ring 2 through the three lubrication oil passages 25 to lubricate parts at different positions. Specifically, as shown in fig. 3, the lubricating oil passage located in the middle of the three lubricating oil passages 25 flows toward the inner raceway 23. The other two lubrication oil paths flow to positions on both sides of the raceway 23 on the inner surface of the middle ring 2, respectively. The bearing of the embodiment is provided with a lubricating oil path to simplify an engine lubricating system.

As shown in fig. 4, in this embodiment in particular, three oil grooves 21 are provided at different positions in the circumferential direction of the middle ring 2 to lubricate parts of the bearing at the different positions.

As shown in fig. 5, for the convenience of installation, normally the cage 5, the rolling elements and the middle ring 2 are assembled as a whole.

Fig. 6 to 8 show a bearing of another embodiment. Unlike the bearing of the embodiment shown in fig. 2, the bearing of the present embodiment has balls 7 disposed between the inner ring 1 and the middle ring 2, and cylindrical rollers 6 disposed between the middle ring 2 and the outer ring 3. In addition, the inner ring 1 of the present embodiment includes the first inner half ring 11 and the second inner half ring 12, which is provided to facilitate assembly.

Other structures and effects that are not described can be obtained by referring to the description of the embodiment shown in fig. 2, and are not described again here.

Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention and not to limit it; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art will understand that: modifications to the specific embodiments of the utility model or equivalent substitutions for parts of the technical features may be made; without departing from the spirit of the present invention, it is intended to cover all aspects of the utility model as defined by the appended claims.

Claims

1. The aircraft engine is characterized by comprising a casing, a bearing, a low-pressure rotor and a high-pressure rotor, wherein the bearing comprises

An inner ring (1) connected to the low-pressure rotor;

the middle ring (2) is connected with the casing;

the outer ring (3) is connected with the high-pressure rotor, and the outer ring (3), the middle ring (2) and the inner ring (1) are sequentially arranged from outside to inside in the radial direction; and

the rolling bodies are arranged between the inner ring (1) and the middle ring (2) and between the outer ring (3) and the middle ring (2).

2. An aircraft engine according to claim 1, characterised in that both the inner and the outer surface of the intermediate ring (2) are provided with raceways for accommodating the rolling bodies.

3. The aircraft engine of claim 2 wherein said rolling elements comprise balls, cylindrical rollers, tapered rollers or spherical rollers.

4. An aircraft engine according to claim 3, characterised in that balls are arranged between the inner ring (1) and the middle ring (2), and cylindrical rollers are arranged between the outer ring (3) and the middle ring (2); or a cylindrical roller is arranged between the inner ring (1) and the middle ring (2), and a ball is arranged between the outer ring (3) and the middle ring (2).

5. An aircraft engine according to claim 1, characterised in that the middle ring (2) comprises a swivel shaft (22) extending axially outwards, the swivel shaft (22) being intended to be connected with the casing.

6. An aircraft engine according to claim 5, characterised in that the transfer shaft (22) is a stepped shaft and comprises a first shaft section (221) and a second shaft section (222), the outer surface of the first shaft section (221) forming a locating surface and the second shaft section (222) being provided with a thread.

7. An aircraft engine according to claim 1, characterised in that an oil sump (21) is provided in the intermediate ring (2), said oil sump (21) being used for conveying lubricating oil.

8. An aircraft engine according to claim 7, characterized in that the middle ring (2) is further provided with at least two lubricating oil passages (25) communicating with the oil groove (21), the at least two lubricating oil passages (25) being used for conveying the lubricating oil to the inner surface of the middle ring (2).

9. An aircraft engine according to claim 1, characterised in that the bearing further comprises a cage (5), the cage (5) being used for mounting rolling bodies.

10. An aircraft engine according to claim 1, characterised in that the outer ring (3) comprises a first outer half ring (31) and a second outer half ring (32) connected to each other in the axial direction; and/or the inner ring (1) comprises a first inner half ring (11) and a second inner half ring (12) which are connected with each other in the axial direction.