CN112648295B

CN112648295B - Bearing assembly of aircraft engine and aircraft engine

Info

Publication number: CN112648295B
Application number: CN201910951695.4A
Authority: CN
Inventors: 沈洁阳; 李佳琪; 占锐; 李铠月; 王军
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2019-10-09
Filing date: 2019-10-09
Publication date: 2022-07-08
Anticipated expiration: 2039-10-09
Also published as: CN112648295A

Abstract

The present disclosure relates to a bearing assembly for an aircraft engine supported between a main shaft and a bearing housing, comprising: the bearing is provided with a split type bearing inner ring; the oil collecting ring is attached to one side of the bearing along the axial direction; the spraying direction of the nozzle is opposite to the oil collecting ring and is used for spraying lubricating oil for lubricating the bearing; the main shaft is provided with a groove body, the groove body is located in a sleeving area of the main shaft and the oil collecting ring, the groove body and the oil collecting ring form a lubricating oil channel together, and the lubricating oil channel can receive lubricating oil sprayed by the nozzle and conduct the lubricating oil to the split type bearing inner ring. The embodiment of the disclosure can realize high-efficiency radial oil collection and under-ring oil supply of the bearing of the aeroengine, and ensure that the bearing oil supply device has stable and high-efficiency performance at each state point of the engine, especially a large state point with severe conditions, the bearing is well lubricated and cooled, and the weight of the oil supply device is favorably reduced to a certain extent.

Description

Bearing assembly of aircraft engine and aircraft engine

Technical Field

The disclosure relates to the field of gas turbines, in particular to a bearing assembly of an aircraft engine and the aircraft engine.

Background

The bearing of the advanced aeroengine has high rotating speed, large load and compact installation space, so that the lubricating and cooling design of the advanced aeroengine faces the dilemma different from the common bearing. Firstly, when the DN (speed factor) value of the bearing exceeds a certain range, the common spray lubrication mode can not meet the requirements of the bearing on the aspects of lubrication cooling effect, lubricating oil cleanliness, vibration and the like, and needs to be replaced by an under-ring oil supply mode; secondly, due to the considerations of engine performance, weight reduction and the like, the installation space of the bearing is continuously compressed, so that the traditional under-ring oil supply design with the axial oil collecting device is difficult to implement.

In order to solve the above problems, one of the solutions commonly used in the industry at present is to use an impeller type oil collecting ring (hereinafter referred to as an oil collecting ring) capable of achieving a radial oil collecting function to collect the lubricating oil injected from the nozzle, and further supply the lubricating oil to the bearing through a ring oil passage.

As shown in fig. 1, in general, a bearing oil supply system includes an oil collecting ring 2 mounted on a main shaft 1, a bearing 3, and a nozzle 7, wherein

inner rings

31, 32 of the bearing may be in a split form. At this time, as indicated by an arrow a in fig. 1, the lubricating oil is discharged from the nozzle 7, collected and transferred by the oil collecting ring, discharged from between the split bearing

inner rings

31 and 32 through the lubricating oil flow passage, and introduced into the space where the rolling elements 33 are present, thereby providing a lubricating effect.

As shown in FIGS. 2 to 3, a schematic cross-sectional view (A-A) of a main shaft 1 and a oil-collecting ring 2 in the prior art is shown. The oil collecting ring 2 comprises 4 blades 21 with specific shapes, the inner surfaces of the blades 21 are provided with a sharp point 22, a small channel is formed between the sharp point 22 and the main shaft 1 to form a throttling opening 24, a large channel is formed between two adjacent blades 21 and the main shaft 1 to form an oil collecting area 23, and a channel is formed between the inner surfaces of the blades 21 and the main shaft 1 to form an oil storing area 25.

When the lubricating oil collecting device works, the main shaft 1 drives the oil collecting ring 2 to rotate together, lubricating oil is sprayed out from the nozzle 7, enters the oil collecting area 23 along a route indicated by an arrow, passes through the throttling port 24 and then enters the oil storage area 25. Finally, the oil collected in the oil reservoir 25 enters the bearing through the oil gallery under centrifugal force. The existing scheme is limited by mutual design interference caused by structural association of the oil receiving area 23, the throttling port 24 and the oil storage area 25, so that the design scheme adopted in compromise often has the problems of obvious throttling and serious insufficient oil delivery capacity at the same time, and particularly when an engine enters a large state, the oil receiving rate of an oil supply system is easily reduced, so that the amount of lubricating oil entering the bearing 3 is insufficient, and the safety of the bearing is seriously influenced.

Disclosure of Invention

In view of this, the embodiments of the present disclosure provide a bearing assembly for an aircraft engine, and provide a feasible alternative to the design defects existing in the prior art, so as to solve the problem of low efficiency of an oil supply device, and ensure that at each state point of the engine, especially at a large state point with high rotation speed, large load and large flow rate, the performance of the bearing oil supply device is stable and efficient, and the bearing obtains good lubrication and cooling.

In one aspect of the present disclosure, there is provided a bearing assembly for an aircraft engine, supported between a main shaft and a bearing housing, comprising:

the bearing is sleeved on the main shaft and is provided with a split type bearing inner ring;

the oil collecting ring is sleeved on the main shaft and is attached to one side of the bearing along the axial direction; and

the nozzle is positioned on the outer side of the oil collecting ring along the radial direction, and the spraying direction of the nozzle is opposite to the oil collecting ring and is used for spraying lubricating oil for lubricating the bearing;

the main shaft is provided with a groove body, the groove body is located in a sleeving area of the main shaft and the oil collecting ring, the groove body and the oil collecting ring form a lubricating oil channel together, and the lubricating oil channel can receive lubricating oil sprayed by the nozzle and conduct the lubricating oil to the split type bearing inner ring.

In some embodiments, the bottom surface of the groove body is a plane, and the bottom surface of the groove body is parallel to the tangential direction of the main shaft.

In some embodiments, the axial width of the groove body ranges from 4 mm to 20mm, and the radial depth of the groove body ranges from 0.4 mm to 5 mm.

In some embodiments, the oil trap ring comprises:

the first side wall is positioned on one side of the oil collecting ring close to the bearing;

the second side wall is positioned on one side of the oil collecting ring away from the bearing; and

a plurality of vanes disposed between the first sidewall and the second sidewall, the plurality of vanes being evenly distributed along a circumferential direction, and each of the vanes extending spirally outward from an inner diameter of the oil gathering ring to an outer diameter of the oil gathering ring;

wherein, the outer end of each blade is partially overlapped with the inner end of the adjacent blade in the circumferential angle range, thereby forming a receiving opening of the lubricating oil channel.

In some embodiments, in the direction of rotation of the main shaft, the blades comprise a windward side and a leeward side;

the projection of the leeward surface on a surface perpendicular to the axial direction is a smooth first spiral line, and the inner end and the outer end of the first spiral line are respectively positioned on the inner diameter and the outer diameter of the oil collecting ring;

the projection of the windward side on the surface perpendicular to the axial direction comprises a smooth second spiral line intersected at a sharp point and a smooth concave curve which is concave outwards along the radial direction, the inner end and the outer end of the second spiral line are respectively positioned on the inner diameter and the outer diameter of the oil collecting ring, and the two ends of the smooth concave curve are both positioned on the inner diameter of the oil collecting ring.

In some embodiments, a line passing through the point and the rotational center of the spindle passes through the slot.

In some embodiments, the sharp point is directly opposite to the maximum groove depth point of the bottom surface of the groove body, and the curvature between the second spiral line and the smooth curve on both sides of the sharp point is discontinuous.

In some embodiments, the distance between the sharp point and the bottom surface of the groove body is 0.4-5 mm. In some embodiments, the inner end of the first spiral line intersects with a contour line of the main shaft on which the groove body is located at a connection point, and the curvatures of the first spiral line and the contour line on both sides of the connection point are continuous.

In some embodiments, the oil passage comprises:

the oil collecting area is enclosed by the first side wall, the second side wall, the part of the windward side corresponding to the second spiral line, the leeward side and part of the bottom surface of the tank body; and

the oil storage area is defined by the first side wall, the second side wall, the part of the windward side corresponding to the smooth concave curve, part of the bottom surface of the groove body and part of the outer peripheral surface of the main shaft;

the oil receiving area and the oil storage area are divided by taking the sharp point as a boundary, and a throttling opening is formed between the sharp point and the bottom surface of the groove body.

In some embodiments, the inner ends of the blades cooperate with the outer circumferential surface of the main shaft such that the oil reservoir is circumferentially closed on a side adjacent to the inner ends of the blades.

In some embodiments, the oil receiving area is a smooth flow passage with a reduced passage area from outside to inside.

In some embodiments, the oil gathering ring further comprises:

the mounting edge is vertically arranged on the first side wall and is close to the adjacent inner ring of the bearing; and

the outflow port is formed in the first side wall and communicated with the oil storage area;

wherein the oil passage further includes:

and the annular flow path is surrounded by the mounting edge and the outer peripheral surface of the corresponding main shaft and is used for conducting the lubricating oil in the oil storage area to the split type bearing inner ring from the outflow port.

In some embodiments, the split bearing inner race comprises:

the first inner ring split body is positioned on one side close to the oil collecting ring along the axial direction;

the second inner ring split body is axially positioned on one side far away from the oil collecting ring, and a radial oil hole is formed between the second inner ring split body and the first inner ring split body;

and an axial oil groove is formed in the inner circumferential surface of the first inner ring split body and used for conducting lubricating oil in the oil storage area to the radial oil hole.

In some embodiments, a cross-sectional shape of the axial oil groove is a circular arc shape, a U shape, or a V shape, a cross-sectional shape of the radial oil hole is a rectangular shape, a triangular shape, a circular arc shape, or a circular shape, and the axial oil groove corresponds to a position of the radial oil hole in a circumferential direction.

In some embodiments, each of the oil storage areas is communicated with at least two axial oil grooves arranged along the circumferential direction.

In some embodiments, a first step structure is provided on the main shaft, a second step structure is provided on the bearing seat, and the bearing assembly further includes:

the pressing piece can be sleeved on the main shaft, is positioned on one side of the split type bearing inner ring, which is far away from the oil collecting ring, and is used for forming mounting limit for the oil collecting ring and the split type bearing inner ring together with the first step; and

and the nut can be arranged on the bearing seat and used for forming an installation limit for a bearing outer ring of the bearing by combining with the second step.

In one aspect of the present disclosure, there is provided an aircraft engine comprising a bearing assembly as described in any of the previous embodiments.

Therefore, according to the embodiment of the disclosure, aiming at the design defects existing in the prior art, a feasible alternative scheme can be provided, the problem of low efficiency of the oil supply device is solved, high-efficiency radial oil collection and under-ring oil supply of an aircraft engine bearing are realized, and the oil supply device for the bearing can ensure stable and high-efficiency performance at each state point of the engine, especially at a large state point with high rotating speed, large load and large flow, is favorable for lubricating and cooling the bearing, and is favorable for lightening the oil supply device to a certain extent.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the disclosure and together with the description, serve to explain the principles of the disclosure.

The present disclosure may be more clearly understood from the following detailed description, taken with reference to the accompanying drawings, in which:

FIG. 1 is a schematic structural view of an aircraft engine bearing assembly according to some embodiments of the present disclosure;

FIG. 2 is a schematic diagram of a structure of an oil gathering ring and a main shaft according to the prior art;

FIG. 3 is a partially enlarged structural view of an oil gathering ring and spindle arrangement according to the prior art;

FIG. 4 is a schematic structural view of a spindle and bearing assembly according to some embodiments of the present disclosure;

FIG. 5 is a schematic structural view of a bearing assembly according to some embodiments of the present disclosure;

FIG. 6 is a structural schematic view of a principal viewing angle of a principal axis according to some embodiments of the present disclosure;

FIG. 7 is a cross-sectional angled structural schematic of a spindle according to some embodiments of the present disclosure;

FIG. 8 is a perspective view of an oil gathering ring according to some embodiments of the present disclosure;

FIG. 9 is a cross-sectional structural schematic of a gathering ring according to some embodiments of the present disclosure;

FIG. 10 is a schematic structural view of a gathering ring and a main shaft according to some embodiments of the present disclosure;

in the figure: 1-main shaft (prior art);

2-oil collecting ring (prior art), 21-blade, 22-sharp point, 23-oil collecting area, 24-throttling orifice, 25-oil storing area, 26-matching surface;

3-bearing, 31-first inner ring split body, 311-axial oil groove, 312-radial oil hole, 32-second inner ring split body, 33-rolling body, 34-retainer and 35-bearing outer ring;

4-bearing seats; 5-a nut; 6, pressing pieces; 7-a nozzle;

8-oil collecting ring (the application), 81-blade, 811-leeward side, 811 a-first spiral line, 812-windward side, 812 a-second spiral line, 812 b-smooth concave curve, 82-sharp point, 83-oil collecting area, 84-throttling port, 85-oil storage area, 86-matching surface, 87-connecting point, 88-second side wall, 89-first side wall, 891-mounting edge, 892-outflow port and 893-annular flow path;

9-main shaft (application), 91-tank, 911-tank bottom;

r₁spindle peripheral surface radius, r₂Equivalent radius of cusp, r₃Bottom diameter of reservoir, d₁Choke gap (prior art), d₂Reservoir depth, d₃Choke gap (application), d₄Groove depth, d₅-slot width or blade width;

a-flow, w-direction of rotation.

It should be understood that the dimensions of the various parts shown in the figures are not drawn to scale. Further, the same or similar reference numerals denote the same or similar components.

Detailed Description

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 is in no way intended to limit the disclosure, its application, or uses. The present disclosure may be embodied in many different forms and is not limited to the embodiments described herein. These embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that: the relative arrangement of parts and steps, the composition of materials, numerical expressions and numerical values set forth in these embodiments are to be construed as merely illustrative, and not as limitative, unless specifically stated otherwise.

The use of "first," "second," and similar terms in this disclosure is not intended to indicate any order, quantity, or importance, but rather are used to distinguish one element from another. The word "comprising" or "comprises", and the like, means that the element preceding the word covers the element listed after the word, and does not exclude the possibility that other elements are also covered. "upper", "lower", "left", "right", and the like are used merely to indicate relative positional relationships, and when the absolute position of the object being described is changed, the relative positional relationships may also be changed accordingly.

In the present disclosure, when a specific device is described as being located between a first device and a second device, there may or may not be intervening devices between the specific device and the first device or the second device. When a particular device is described as being coupled to other devices, that particular device may be directly coupled to the other devices without intervening devices or may be directly coupled to the other devices with intervening devices.

All terms (including technical or scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this disclosure belongs unless specifically defined otherwise. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the relevant art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.

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.

It should be noted that the discussion of the dimensional structure of the bearing assembly in the present specification is mainly based on the structural schematic diagram of the sectional angle in the drawings of the specification, and at this time, the points and lines in the sectional view should correspond to the lines and the faces respectively in the actual three-dimensional structure, taking the sharp point as an example, the sharp point should be a sharp line in the actual structure, and the chokes formed by the sharp point should also have the concept of width. For convenience of description, and to be more readily apparent as the description proceeds, the present application describes the structure of the bearing assembly in cross-section without departing from the understanding of those skilled in the art.

As shown in fig. 1, 4 to 10, in one aspect of the present disclosure, there is provided a bearing 3 assembly for an aircraft engine, supported between a main shaft 9 and a bearing housing 4, comprising:

the bearing 3 is sleeved on the main shaft 9 and is provided with a split type bearing inner ring 31;

the oil collecting ring 8 is sleeved on the main shaft 9 and is attached to one side of the bearing 3 along the axial direction; and

the nozzle 7 is positioned on the outer side of the oil collecting ring 8 along the radial direction, and the spraying direction of the nozzle is opposite to the oil collecting ring 8 and is used for spraying lubricating oil for lubricating the bearing 3;

a groove 91 is formed in the main shaft 9, the groove 91 is located in a sleeving area between the main shaft 9 and the oil collecting ring 8, the groove 91 and the oil collecting ring 8 jointly form a lubricating oil channel, and the lubricating oil channel can receive lubricating oil sprayed by the nozzle 7 and conduct the lubricating oil to the split type bearing inner ring 31.

The main shaft 9 is grooved, and the groove body 91 and the oil collecting ring 8 jointly form a lubricating oil channel, so that the existing thought mainly based on the single piece design of the oil collecting ring 8 can be changed into the combined design thought of the oil collecting ring 8 and the main shaft 9, and the specific technical scheme is that the orifice 84 is changed from the geometric characteristic mainly based on the oil collecting ring 8 into the geometric characteristic mainly based on the main shaft 9, so that the relatively independent design of the orifice 84 and the oil storage area 85 is realized, and the difficulty that the design orientation of the gap of the orifice 84 and the design orientation of the depth of the oil storage area 85 cannot be met simultaneously is overcome.

As shown in fig. 2 and 3, first, the key structural parameters affecting the oil collecting capacity of the oil collecting ring 2 are described by the structure of the oil collecting ring 2 in the prior art:

first, the radial dimension of the throttle zone 24, i.e., the equivalent radius r of the cusp 22₂With the outer radius r of the main shaft 1₁A difference of (d) is called a throttle zone gap d₁Throttle zone gap d₁Is directly related to the critical dimension of the oil entering the reservoir 25 from the oil recovery zone 23, it is often desirable to design a larger value to minimize the throttling effect of the oil in the throttling zone 24 so that as much oil as possible enters the reservoir 25.

Second, the effective depth of the reservoir 25, i.e. the equivalent radius r of the cusp 22₂And the bottom diameter r of the oil storage area₃Is called the reservoir depth d₂Depth d of reservoir₂Is a critical dimension that directly affects the short term storage capacity of the oil storage area 25 and establishes the centrifugal pressure of the lubricant, and it is often desirable to obtain a large value during design to achieve two objectives: increasing the short term capacity of the oil reservoir 25 prevents oil that has entered the oil reservoir 25 from flowing back out of the oil collection annulus from the restriction 24, causing loss of oil; the maximum radial level of the oil in the oil reservoir is increased to ensure that sufficient centrifugal pressure of the oil is built up in the oil reservoir 25 to increase oil delivery capacity.

Secondly, the defects of the prior scheme are introduced:

the throttle zone 24 and the oil reservoir zone 25 are geometrical features of the oil collecting ring 2 only, and the outer radius r of the main shaft is designed in the prior art₁The bottom diameter r of the oil storage area can not be reduced under the restriction of other conditions in the engine₃Cannot be increased under the oil path depth constraint of the bearing inner ring 31 and the strength constraint of the blades 21, and only the equivalent radius r of the cusp 22₂Adjustable, and the cusps, whether adjusted radially inward or outward, do not simultaneously increase the choke zone gap d₁And the depth d of the oil reservoir₂Resulting in a choke zone gap d₁Design orientation and reservoir depth d₂The design orientations of (a) and (b) are not satisfied simultaneously and contradictory to each other.

The oil collecting capacity can not reach a better level due to the design of compromise parameters, the oil collecting ring 2 has the problems of obvious throttling and serious insufficient oil conveying capacity when facing larger nozzle oil supply, the oil receiving rate of an oil supply system is rapidly reduced, the lubricating oil entering the bearing 3 is insufficient when the engine is in a large state, and the safety of the bearing is seriously influenced.

As shown in fig. 4 to 5, in the present application, the groove 91 is formed in the main shaft 9, the oil collecting ring 8 does not independently affect the structure of the lubricating oil channel, and at this time, the main shaft 9 acts on the structure of the lubricating oil channel through the groove 91, so as to provide a larger dimensional tolerance for the design of the lubricating oil channel. That is, on the basis that the main shaft 9 is provided with the groove body 91, the position adjustment range of the sharp point 82 is greatly improved relative to the prior art, so that even if the sharp point 82 is adjusted inwards along the radial direction, the depth d of the oil storage area 85 can be ensured₂The gap d of the throttling port 84 is ensured while the requirement is met₃The size requirement of the oil cylinder, thereby realizing the high-efficiency radial oil collection and the annular oil supply of the main bearing of the aircraft engine at the same time.

It is conceivable that the groove 91 may have different depths, widths and shapes depending on the oil collecting and supplying needs of the bearing 3 assembly, and the balance and satisfaction of the oil collecting function and the oil supplying function of the bearing 3 assembly can be more sufficient.

However, since the main shaft 9 of the aircraft engine is a core component for transmitting power in the core engine, the structural design thereof needs to strictly meet the design requirements of strength, rigidity and the like. And the strength of the spindle 9 is affected to some extent by the grooving of the spindle 9.

Therefore, in some embodiments, it is necessary to limit the shape of the groove 91, that is, to limit the bottom surface of the groove 91 to be a plane, and the bottom surface of the groove 91 is parallel to the tangential direction of the spindle 9, so as to reduce the influence of the groove 91 on the structural strength of the spindle 9 and to reduce the processing difficulty to some extent.

Correspondingly, as shown in fig. 6 to 7, in some embodiments, it is necessary to limit the size of the groove body 91, especially the width and the depth of the groove body 91, that is, the axial width of the groove body 91 is limited to be 4 to 20mm, and the radial depth of the groove body 91 is limited to be 0.4 to 5mm, so as to ensure that when the groove body 91 is matched with the oil supply system of the bearing 3 to work and different shapes are selected, the operation of the main shaft 9 is not adversely affected.

Further, as shown in fig. 8-9, in some embodiments, the oil collecting ring 8 includes:

a first side wall 89 located on a side of the oil collecting ring 8 adjacent to the bearing 3;

a second side wall 88 located on a side of the oil gathering ring 8 remote from the bearing 3; and

a plurality of vanes 81 disposed between the first side wall 89 and the second side wall 88, the plurality of vanes 81 being evenly distributed along the circumferential direction, and each of the vanes 81 spirally extending outward from the inner diameter of the oil collecting ring 8 to the outer diameter of the oil collecting ring 8;

wherein, the outer end of each vane 81 is partially overlapped with the inner end of the adjacent vane 81 in the circumferential angle range, thereby forming a receiving opening of the oil passage.

The oil collecting ring 8 may include 4 or other number of blades 81 with specific shapes, and the profile shape of the blades 81 may be an arc shape or a straight shape as shown in the figure. However, for better oil collection and supply, the number of the vanes 81 included in the oil collecting ring 8 is preferably 4, and the shape and contour thereof preferably have an arc shape of the configuration of the vanes 81, so as to reduce the possibility of the lubricant escaping from the oil collecting ring 8 and to make the flow of the lubricant inside the oil collecting ring 8 smoother.

Further, as shown in fig. 10, in order to provide a specific oil collecting and supplying functional partition inside the oil collecting ring 8 by the shape profile of the blade 81, in some embodiments, the blade 81 includes a windward side 812 and a leeward side 811 along the rotation direction of the main shaft 9;

the projection of the leeward surface 811 on the surface perpendicular to the axial direction is a smooth first spiral line 811a, and the inner end and the outer end of the first spiral line 811a are respectively located on the inner diameter and the outer diameter of the oil collecting ring 8;

the projection of the windward side 812 on the plane perpendicular to the axial direction includes a smooth second spiral line 812a intersecting at the sharp point 82 and a smooth concave curve 812b concave outward in the radial direction, the inner end and the outer end of the second spiral line 812a are respectively located on the inner diameter and the outer diameter of the oil collecting ring 8, and both ends of the smooth concave curve 812b are located on the inner diameter of the oil collecting ring 8.

Thus, in some embodiments, the different functional zones within the oil passage are constituted by the shape profile of the vanes 81:

the oil collecting area 83 is enclosed by the first side wall, the second side wall, the part of the windward side 811 corresponding to the second spiral line 812a, the leeward side 812 and the bottom surface of the groove body 91; and

the oil storage area 85 is formed by the first side wall, the second side wall, the part of the windward side 811 corresponding to the smooth concave curve, part of the bottom surface of the groove body 91 and part of the outer peripheral surface of the main shaft 9 in a surrounding manner;

the oil receiving area 83 and the oil storage area 85 are divided by the sharp point 82, and a throttle 84 is formed between the sharp point 82 and the bottom surface of the groove body 91.

Offer on the main shaft 9 of this application on the basis of cell body 91, the cusp 82 can be closer to the rotation center of main shaft 9 also makes the inner of second helix 812a with the both ends homoenergetic of smooth indent curve 812b are located on the external diameter of main shaft 9. So that no matter the gap d of the throttle orifice 84₃Or the reservoir 85 depth d₂The shape profiles of the second spiral line 812a and the smooth concave curve 812b have better radian, and are more suitable for collecting and transferring lubricating oil in the process of high-speed rotation.

Further, in order to make the choke 84 have a clearance d₃And the depth d of the oil reservoir 85₂Can make full use of the slot 91, in some embodiments, viaThe line passing through the sharp point 82 and the rotation center of the spindle 9 passes through the groove 91.

Specifically, in some embodiments, the sharp point 82 is opposite to the maximum groove depth point of the bottom surface of the groove body 91, and the curvature of the second spiral line 812a on both sides of the sharp point 82 is discontinuous from the smooth curve. In some embodiments, the distance from the point 82 to the bottom surface of the groove 91 can be taken to be the groove depth d₄Thereby ensuring the gap d of the throttle orifice 84₃And (4) maximization.

Further, in some embodiments, the inner end of the first spiral line 811a intersects with the contour line of the groove 91 on the spindle 9 at a connection point 87, and the curvature between the first spiral line 811a and the contour line on both sides of the connection point 87 is continuous. The curvature between the first spiral line 811a passing through the connection point 87 and the contour line is continuous, so that the blade 81 and the groove are smoothly transited at the connection point 87, and further the channel of the oil collecting area 83 is smooth.

Further, in some embodiments, the inner end of the vane 81 is engaged with the outer peripheral surface of the main shaft 9, so that the oil storage region 85 is closed at a side close to the inner end of the vane 81 in the circumferential direction.

Thus, based on the continuous curvature between the first spiral line 811a and the contour line on both sides of the connection point 87 and the shape and contour of the first spiral line 811a and the second spiral line 812a, in some embodiments, the oil collecting area 83 is a smooth flow passage with a reduced passage area from outside to inside, thereby enhancing the oil collecting ability of the oil collecting area 83.

Further, in order to conduct the lubricant in the oil collecting ring 8 to the inner ring of the bearing 3, in some embodiments, the oil collecting ring 8 further includes:

a mounting edge vertically arranged on the first side wall 89 and abutted against the adjacent inner ring of the bearing 3; and

an outlet port which is opened in the first side wall 89 and communicates with the oil reservoir 85;

wherein the oil passage further includes:

and an annular flow path 893, which is surrounded by the mounting edge and the outer peripheral surface of the main shaft 9, and is used for guiding the lubricating oil in the oil storage area 85 from the outlet to the split bearing inner ring 31.

Further, in order to achieve good lubrication of the rolling elements 33 in the bearing 3 by the lubricant outside the inner ring of the bearing 3, in some embodiments, the split bearing inner ring 31 includes:

the first inner ring split body 31 is positioned on one side close to the oil collecting ring 8 along the axial direction;

a second inner ring split body 32 located on a side away from the oil collecting ring 8 in the axial direction, and forming a radial oil hole 312 with the first inner ring split body 31;

an axial oil groove 311 is formed in an inner circumferential surface of the first inner ring split body 31, and is used for guiding lubricating oil in the oil storage area 85 to the radial oil hole 312.

Further, in order to adapt the through-flow shapes of the axial oil groove 311 and the radial oil hole 312 to the structures of the oil collecting ring 8 and the bearing 3, in some embodiments, the cross-sectional shape of the axial oil groove 311 is circular arc, U-shaped or V-shaped, the cross-sectional shape of the radial oil hole 312 is rectangular, triangular, circular arc or circular, and the positions of the axial oil groove 311 and the radial oil hole 312 correspond in the circumferential direction.

And in order to ensure that the lubricating oil in the oil storage area 85 can enter the bearing 3 more smoothly, in some embodiments, each of the oil storage areas 85 is communicated with at least two axial oil grooves arranged along the circumferential direction.

Further, in order to fix the bearing 3, in some embodiments, a first step structure is provided on the main shaft 9, a second step structure is provided on the bearing seat 4, and the bearing 3 assembly further includes:

the pressing piece 6 can be sleeved on the main shaft 9, is positioned on one side of the split type bearing inner ring 31 far away from the oil collecting ring 8, and is used for forming mounting limit for the oil collecting ring 8 and the split type bearing inner ring 31 together with the first step structure; and

and the nut 5 can be arranged on the bearing seat 4 and is used for forming an installation limit for a bearing outer ring 32 of the bearing 3 together with the second step structure.

In order to define the relative position of the rolling elements 33 in the bearing 3, the rolling elements 33 are embedded in a cage 34.

In one aspect of the present disclosure there is provided an aircraft engine comprising a bearing 3 assembly as described in any of the previous embodiments.

Therefore, according to the embodiment of the disclosure, aiming at the design defects existing in the prior art, a feasible alternative scheme can be provided, the problem of low efficiency of the oil supply device is solved, high-efficiency radial oil collection and under-ring oil supply of an aircraft engine bearing are realized, and the oil supply device for the bearing can ensure stable and high-efficiency performance at each state point of the engine, especially at the large state point with high rotating speed, large load and large flow, is favorable for lubricating and cooling the bearing, and is favorable for lightening the oil supply device to a certain extent.

Specifically, compared with the prior art, the throttling area clearance has relatively large value freedom degree, the maximum value of the depth of the oil storage area can be the difference between the bottom diameter of the oil storage area and the outer radius of the main shaft, the throttling effect of the lubricating oil in the throttling area can be effectively reduced, the short-time capacity and the oil conveying capacity of the oil storage area can be increased to the maximum extent, particularly, the accommodation degree of the oil supply device for large flow can be improved, and the stable and efficient oil receiving rate of each state can be ensured.

In addition to the above main effects, this solution can also reach the following additional benefits:

1. because of the inner contraction of the outer surface of the main shaft, the original oil collecting area is correspondingly increased, and meanwhile, the contraction-shaped channel of the oil collecting area can be made to be more streamline, so that the resistance of the part to lubricating oil can be further reduced, and the oil collection is facilitated;

2. because the throttling area is eliminated from the oil collecting ring, the design range of the depth of the oil storage area of the oil collecting ring is enlarged, designers can adjust the parameters according to requirements, even reduce the bottom diameter of the oil storage area, so that the outer diameter of the whole oil collecting ring can be correspondingly reduced, and the effects of saving space and reducing weight are achieved.

In conclusion, the invention has the final effects of realizing high-efficiency radial oil collection and under-ring oil supply of the main bearing of the aircraft engine and being beneficial to the light-weight design of the oil supply device to a certain extent.

Thus, various embodiments of the present disclosure have been described in detail. Some details that are well known in the art have not been described in order to avoid obscuring the concepts of the present disclosure. It will be fully apparent to those skilled in the art from the foregoing description how to practice the presently disclosed embodiments.

Although some specific embodiments of the present disclosure have been described in detail by way of example, it should be understood by those skilled in the art that the foregoing examples are for purposes of illustration only and are not intended to limit the scope of the present disclosure. It will be understood by those skilled in the art that various changes may be made in the above embodiments or equivalents may be substituted for elements thereof 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. An aircraft engine, comprising: a spindle and a bearing assembly supported between the spindle and the bearing housing, comprising:

2. The aircraft engine of claim 1, wherein the bottom surface of the slot body is a plane and is parallel to the tangential direction of the main shaft.

3. The aircraft engine of claim 1, wherein the axial width of the slot body ranges from 4 mm to 20mm, and the radial depth of the slot body ranges from 0.4 mm to 5 mm.

4. The aircraft engine of claim 1, wherein said oil gathering ring comprises:

5. The aircraft engine of claim 4, wherein in the direction of rotation of said main shaft, said blades comprise a windward side and a leeward side;

6. An aircraft engine according to claim 5, wherein a line passing through the point and the centre of rotation of the main shaft passes through the slot.

7. An aircraft engine according to claim 6, wherein the point is directly opposite the point of greatest groove depth of the bottom surface of the slot, the curvature of the second helix on either side of the point being discontinuous with the smooth concave curve.

8. The aircraft engine of claim 7, wherein the distance from the sharp point to the bottom surface of the slot body is 0.4-5 mm.

9. An aircraft engine according to claim 5, wherein the inner end of the first helix intersects with the contour line of the slot body on the main shaft at a connection point, and the curvatures of the first helix and the contour line on both sides of the connection point are continuous.

10. The aircraft engine of claim 5, wherein said oil gallery comprises:

11. The aircraft engine of claim 10, wherein the inner ends of said blades are engaged with the outer peripheral surface of said main shaft, so that said oil reservoir is circumferentially closed at the engagement surface.

12. The aircraft engine of claim 10, wherein said oil recovery zone presents a smooth flow path of decreasing passage area from outside to inside.

13. The aircraft engine of claim 10, wherein said oil catcher ring further comprises:

the outflow port is arranged on the first side wall and communicated with the oil storage area;

wherein the oil passage further includes:

14. The aircraft engine of claim 10 wherein said split bearing inner race comprises:

the first inner ring split body is positioned on one side close to the oil collecting ring along the axial direction, and an axial oil groove is formed in the inner circumferential surface;

wherein, the axial oil groove is used for leading lubricating oil in the oil storage area to the radial oil hole.

15. The aircraft engine according to claim 14, wherein the axial oil groove has a circular arc-shaped, U-shaped, or V-shaped cross-sectional shape, the radial oil hole has a rectangular, triangular, circular arc-shaped, or circular cross-sectional shape, and the axial oil groove corresponds to the position of the radial oil hole in the circumferential direction.

16. The aircraft engine of claim 14, wherein each of said oil storage regions communicates with at least two of said axial oil sumps arranged in a circumferential direction.

17. The aircraft engine of claim 1, wherein said main shaft is provided with a first step structure, said bearing housing is provided with a second step structure, said bearing assembly further comprising: