CN110206646A - A kind of Aero-engine Bearing bearing assembly and aero-engine - Google Patents
A kind of Aero-engine Bearing bearing assembly and aero-engine Download PDFInfo
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- CN110206646A CN110206646A CN201810166235.6A CN201810166235A CN110206646A CN 110206646 A CN110206646 A CN 110206646A CN 201810166235 A CN201810166235 A CN 201810166235A CN 110206646 A CN110206646 A CN 110206646A
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- bearing
- spacing collar
- aero
- engine
- mounting surface
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Support Of The Bearing (AREA)
- Shafts, Cranks, Connecting Bars, And Related Bearings (AREA)
Abstract
The object of the present invention is to provide a kind of Aero-engine Bearing bearing assembly and aero-engines.Aero-engine Bearing bearing assembly provided by the invention, including mounting base, mounting base have mounting surface, and mounting surface is a part of spherical surface；Aero-engine Bearing bearing assembly further includes positioning ring, connector, the first spacing collar and the second spacing collar；First spacing collar and the second spacing collar respectively with the mounting surface sphere-contact, for supporting the bearing respectively；Positioning ring is fixed on mounting surface；Connector is for the first spacing collar, the second spacing collar to be fixedly connected integrally with positioning ring.Positioning ring is detached from for bearing overload power with mounting surface.Since positioning ring is clamped, will not fly off, therefore safety with higher.Aero-engine provided by the invention includes above-mentioned Aero-engine Bearing bearing assembly, therefore safety with higher.
Description
Technical field
The present invention relates to a kind of Aero-engine Bearing bearing assembly and aero-engines.
Background technique
According to the requirement of air worthiness regulation (FAR33.74, FAR33.94), commercial aviation engine must assure that FBO event
The generation of (fan blade flies out) will not lead to disastrous consequence.To guarantee safety of the aero-engine after the generation of FBO event,
Traditional method is to increase the structural strength of each component in engine Path of Force Transfer, such as rotor support structure, support case, installation
System etc. increases its stress Margin, to guarantee that critical component will not destroy under FBO load.Start however, this will lead to
Machine weight increases, and is unfavorable for loss of weight design.
In recent years, with the promotion of motor power, fan blade diameter is increasing, imbalance caused by FBO event
Load is also increasing.After in the case where not significantly increasing engine weight, guaranteeing that FBO event does not cause calamity
Fruit, the concept for the design that fuses are applied in engine design.Common fusing design scheme is in No. 1 apart from fan recently
Primary fusing part, the usually structure of mechanical performance weakness, such as thinning section, constriction bolt, Neng Gou is nearby arranged in bearing
The lower failure of predetermined load (fusing threshold value) effect.After FBO event occurs, No. 1 bearing primary fusing part failure nearby, by fan
The decoupling of the stators supporting structure such as rotor and Middle casing, reduces the imbalance that Middle casing is transmitted to by bearing and its support etc.
Load avoids the other critical components of engine from being destroyed.
However, constraint of the fan shaft at No. 1 bearing is released after primary fusing part failure, the only quilt at No. 2 bearings
Constraint, pendulum radius are bigger than before the failure of primary fusing part.This will lead to fan shaft and is produced at No. 2 bearings due to restrained
The bending deformation of raw part and stress are concentrated, in some instances it may even be possible to lead to fan axle fracture, fan propeller is flown off, and jeopardizes the peace of aircraft
Entirely.Therefore, it is necessary to carry out secondary fusing design near No. 2 bearings, excessive stress is generated to avoid fan shaft and is concentrated, is protected
Demonstrate,prove the safety of engine.
As shown in figure 5, United States Patent (USP) US6491497B1 discloses a kind of component for the supporting rotor in imbalance,
Wherein there is outrigger shaft, from the installation seat ring 350 of outrigger shaft top protrusion, cooperates with the concave surface 364 of inner bearing ring,
Under normal operating conditions, the retainer 354,355 positioned at installation 350 two sides of seat ring makes the concave surface 364 and peace of inner bearing ring
Dress seat ring 350 keeps opposing stationary.When rotor c.g. offset occurring being more than the limit of setting, in retainer 354,355 one
It is a to be broken, so that opposite slide can occur between the spherical surface and concave surface 364 of installation seat ring 350.Although keeping
Frame 354,355 can play the role of fusing by fracture, but still can fly from the part that retainer 354,355 is broken
It is de-, to cause secondary damage to engine.
Summary of the invention
The purpose of the present invention is to provide a kind of Aero-engine Bearing bearing assemblies, will not be to engine when fusing
Cause secondary damage.
The object of the invention is also to provide a kind of aero-engine, including above-mentioned Aero-engine Bearing bearing assembly,
Therefore safety with higher.
For the Aero-engine Bearing bearing assembly for realizing the purpose, for being supported to bearing, including mounting base,
The mounting base has mounting surface；The mounting surface is a part of spherical surface；
The Aero-engine Bearing bearing assembly further includes positioning ring, connector, the first spacing collar and the second spacing collar；
First spacing collar and second spacing collar respectively with mounting surface sphere-contact each other, and for point
The inner ring of the bearing is not supported；The positioning ring is connect with the mounting surface, and is located at first spacing collar and described
Between second spacing collar；First spacing collar, second spacing collar are fixedly connected by the connector with the positioning ring
Integrally；
The positioning ring is arranged to be detached from the case where bearing overload power with the mounting surface, and allows by the connection
Part is fixedly connected with integral first spacing collar, second spacing collar and the positioning ring can be on the mounting surface
Sliding.
The Aero-engine Bearing bearing assembly, further feature are that the connector is stay bolt, described
One end of stay bolt is then passed through described after being provided in one in first spacing collar and second spacing collar
Positioning ring is connect, thus by described first again later with another in first spacing collar and second spacing collar
Spacing collar, second spacing collar are fixedly connected integrally with the positioning ring.
The Aero-engine Bearing bearing assembly, further feature are that first spacing collar is radially
Inside there is the first contact surface, the inside radially of second spacing collar has the second contact surface, first contact
Face and second contact surface are used to distinguish sphere-contact each other with the mounting surface；
The outside radially of first spacing collar and the outside radially of second spacing collar are provided in
Two end faces of the inner ring of the bearing in the axial direction are supported in axial direction respectively, to carry out axial limiting to the bearing, and
Two convex shoulders of the inner ring of the bearing are supported, respectively radially to carry out radial limit to the bearing.
The Aero-engine Bearing bearing assembly, further feature are that first spacing collar is radially
Outside there is first annular face and first annular flange, the first annular flange is radially raised in first ring
Shape face；The outside of second spacing collar has the second annular surface and the second annular flange, and second annular flange is radially
Outwardly convex is in second annular surface；
The first annular flange and second annular flange are spaced setting in the axial direction, and are configured in the axial direction
Support two end faces of the inner ring of the bearing in the axial direction respectively, and support respectively radially two of the bearing it is convex
Shoulder to support the inner ring of the bearing, and makes the inner ring, the first annular flange, second annular flange, described
First annular face, second annular surface limit jointly and form closed annular housing.
The Aero-engine Bearing bearing assembly, further feature are the Aero-engine Bearing bearings
Component further includes the damping energy-absorbing body being made of damping energy-absorbing material；The damping energy-absorbing material is full of the annular housing, with
The damping energy-absorbing body is formed in the annular housing.
The Aero-engine Bearing bearing assembly, further feature are that the damping energy-absorbing material is metal
Rubber or foamed aluminium.
For the aero-engine for realizing the purpose, including bearing, the bearing includes inner ring, roller and outer ring, described
Aero-engine further includes Aero-engine Bearing bearing assembly as described above, the Aero-engine Bearing bearing assembly packet
Mounting base is included, the mounting base has mounting surface；The mounting surface is a part of spherical surface；
The Aero-engine Bearing bearing assembly further includes positioning ring, connector, the first spacing collar and the second spacing collar；
First spacing collar and second spacing collar respectively with mounting surface sphere-contact each other, and for point
The inner ring of the bearing is not supported；The positioning ring is connect with the mounting surface, and is located at first spacing collar and described
Between second spacing collar；The connector is for fixing first spacing collar, second spacing collar and the positioning ring
It links into an integrated entity；
The positioning ring is arranged to be detached from the case where bearing overload power with the mounting surface, so that by the connector
Being fixedly connected with integral first spacing collar, second spacing collar and the positioning ring can slide on the mounting surface
It is dynamic.
The aero-engine, further feature are that the aero-engine further includes Middle casing and fan
Axis；
The outer ring is fixedly mounted on the Middle casing；The mounting base is fixedly mounted on the fan shaft, and
Positioned at the inside of the inner ring.
The aero-engine, further feature are that the bearing is the fan of the aero-engine
The rear support bearing of axis.
The aero-engine, further feature are that there are two convex shoulders along axial tool for the inner ring, described in two
Protrusion is set to two end faces of the inner ring in the axial direction to convex shoulder respectively.
The positive effect of the present invention is that: Aero-engine Bearing bearing assembly provided by the invention, for axis
It holds and is supported, including mounting base, mounting base has mounting surface；Mounting surface is a part of spherical surface；Aero-engine Bearing branch
Bearing assembly further includes positioning ring, connector, the first spacing collar and the second spacing collar；First spacing collar and the second spacing collar respectively with
Mounting surface sphere-contact each other, and for distinguishing bearing support；Positioning ring is fixed on mounting surface, and is located at first
Between spacing collar and the second spacing collar；Connector is used to the first spacing collar, the second spacing collar and positioning ring being fixedly connected into one
Body.Positioning ring is for bearing overload power and being detached from mounting surface, so that connected piece is fixedly connected with the first integral limit
Position circle, the second spacing collar and positioning ring can slide on mounting surface.
It is still clamped by the first spacing collar and the second spacing collar after being disconnected due to positioning ring and mounting surface, it is fixed
Position ring will not be flown off, and also would not cause secondary damage to engine.Aero-engine provided by the invention includes above-mentioned aviation
Engine bearing bearing assembly, therefore safety with higher.
Detailed description of the invention
The above and other features of the present invention, property and advantage will pass through retouching with reference to the accompanying drawings and examples
It states and becomes readily apparent from, in which:
Fig. 1 is the cross-sectional view of aero-engine in the present invention；
Fig. 2 is the enlarged drawing in Fig. 1 at B, it is shown that bearing and Aero-engine Bearing bearing assembly；
Fig. 3 is the enlarged drawing in Fig. 2 at C；
The schematic diagram that Fig. 4 is the first spacing collar, the second spacing collar and positioning ring slide on mounting surface；
Fig. 5 is the schematic diagram of the component of supporting rotor in imbalance in the prior art.
Specific embodiment
The invention will be further described with attached drawing combined with specific embodiments below, elaborates in the following description more
Details to facilitate a thorough understanding of the present invention, still the present invention obviously can be come with a variety of other ways different from this description it is real
It applies, those skilled in the art can make similar popularization according to practical situations without violating the connotation of the present invention, drill
It unravels silk, therefore should not be limited the scope of the invention with the content of this specific embodiment.
In the description of the present invention, it is to be understood that, term " length ", " width ", "upper", "lower", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner" and "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of description of the present invention and simplification of the description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as to limit of the invention
System.
In addition, term " first ", " second " are used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance
Or implicitly indicate the quantity of indicated technical characteristic.Define " first " as a result, the feature of " second " can be expressed or
Implicitly include one or more of the features.In the description of the present invention, the meaning of " plurality " is two or more,
Unless otherwise specifically defined.
In the present invention unless specifically defined or limited otherwise, term " installation ", " connected ", " connection ", " fixation " etc.
Term shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or integral；It can be mechanical connect
It connects, is also possible to be electrically connected；It can be directly connected, can also can be in two elements indirectly connected through an intermediary
The interaction relationship of the connection in portion or two elements.It for the ordinary skill in the art, can be according to specific feelings
Condition understands the concrete meaning of above-mentioned term in the present invention.
It should be noted that Fig. 1 to Fig. 5 only as an example, its not be according to equal proportion condition draw, and
It should not be construed as limiting in this, as the protection scope to actual requirement of the present invention." axial direction ", " radial direction " and circumferential direction in the present invention
With with the orientation of aero-engine 100 be reference.
Fig. 1 shows one embodiment of aero-engine 100 in the present invention, and aero-engine 100 has central axis
A-A, drawing illustrate only the half of the cross-sectional view of aero-engine 100, do not show completely part and the part shown
It is symmetrical about central axis A-A." annular " in the present invention circular axis is center axis A-A.
It continues to refer to figure 1, aero-engine 100 includes fan propeller 3, Middle casing 4, bearing 1 and aviation engine shaft
Hold bearing assembly 2, fan shaft 5 and outrigger shaft 6.Bearing 1 is No. 2 axis of aero-engine 100 in the embodiment shown in fig. 1
It holds.In a further embodiment, Aero-engine Bearing bearing assembly 2 can also be used to the other positions of bearing aero-engine
Bearing, such as No. 1 bearing 7.
It is of the invention to be discussed in detail below for the application by Aero-engine Bearing bearing assembly 2 on No. 2 bearings
Embodiment.
In this embodiment, bearing 1, that is, No. 2 bearings, including inner ring 10, roller 11 and outer ring 12, outer ring 12 with
Middle casing 4 connects, and inner ring 10 with 6 fusible of outrigger shaft of fan shaft 5 is connected by Aero-engine Bearing bearing assembly 2
It connects, i.e., inner ring 10 is supported by Aero-engine Bearing bearing assembly 2.The front end of fan shaft 5 is supported by No. 1 bearing 7, support cone wall
8 are connected to No. 1 bearing 7 on Middle casing 4, and support cone wall 8 is the important path that fan propeller load is transmitted to Middle casing.
In other embodiments, Aero-engine Bearing bearing assembly 2 can not also support inner ring 10, and other portions of bearing support 1
Point, such as supporting outer ring 12.
In the embodiment shown in fig. 1, fan shaft 5 is supported jointly by No. 1 bearing 7 and No. 2 bearing, wherein No. 1 bearing 7 is
Stick roller bearing provides radial constraint to fan shaft 5；No. 2 bearings are ball bearing, provide axis simultaneously to the outrigger shaft 6 of fan shaft 5
To and radial constraint.
To reduce the load for being transmitted to Middle casing 4 after FBO event occurs from fan propeller 3, in the bearing of No. 1 bearing 7
It bores wall 8 and is equipped with primary fusing part 9, specific structure can be thinning section.The outrigger shaft 6 of fan shaft 5 passes through aero-engine
Bearing bearing assembly 2 and No. 2 bearing is connect, and is connected further on Middle casing 4.Fusing design at No. 1 bearing 7 is known as
Primary fusing design is also required to fuse at No. 2 bearings to set to further decrease the stress of fan shaft and improving safety
It counts, the fusing design at No. 2 bearings is known as secondary fusing design.
Fusing design at No. 2 bearings can be realized by the specific structure of Aero-engine Bearing bearing assembly 2.
In conjunction with Fig. 1,2,3, Aero-engine Bearing bearing assembly 2 includes mounting base 20, and mounting base 20 has mounting surface
20a.In order to which the inner ring 10 to bearing 1 supports, mounting surface 20a is located at the inside of the inner ring 10 of bearing 1.Mounting surface 20a with
Concentrically line designs the inner ring 10 of bearing 1, and is oppositely arranged with the inner surface of inner ring 10 radially.Mounting surface 20a is spherical surface
A part, can be convex spherical either concave spherical surface.Mounting base 20 is annular, and correspondingly mounting surface 20a is also annular.Installation
Seat 20 and the concentrically axis A-A of bearing 1.
To realize bearing to inner ring 10, Aero-engine Bearing bearing assembly 2 further include positioning ring 21, connector 22,
First spacing collar 23 and the second spacing collar 24；First spacing collar 23 and the second spacing collar 24 are respectively sleeved on mounting surface 20a simultaneously
With mounting surface 20a sphere-contact, and the inner ring 10 of bearing support 1 respectively each other；In addition, the first spacing collar 23 and the second limit
Circle 24 can be respectively formed flexural pivot between mounting surface 20a and connect.Positioning ring 21, the first spacing collar 23 and the second spacing collar 24 are
It is to surround central axis A-A and be arranged.
Positioning ring 21 is connect with mounting surface 20a, and between the first spacing collar 23 and the second spacing collar 24；Connector
22 for the first spacing collar 23, the second spacing collar 24 to be fixedly connected integrally with positioning ring 21, and make 23 He of the first spacing collar
Second spacing collar 24 clamps positioning ring 21.There are many forms of connector 22, will discuss later.
The junction of positioning ring 21 and mounting surface 20a are using fusing design, such as can be attached using thinning section, with
Guarantee that positioning ring 21 is detached from the case where bearing overload power with mounting surface 20a, and allows connected piece 22 is fixed to connect
Being connected into the first integrated spacing collar 23, the second spacing collar 24 and positioning ring 21 can slide on mounting surface 20a, reach fusing and set
The purpose of meter.
In a more specific embodiment, positioning ring 21 has that (fusing connection can be with mounting surface 20a fusing connection
Be using bonding agent connect) joint face, the joint face be spherical surface a part.Connect when the joint face and mounting surface 20a are disconnected
After connecing (i.e. bonding agent failure), which can slide on mounting surface 20a.
In another embodiment, positioning ring 21 can be integrally manufactured with mounting base 20, so that positioning ring 21 is radially
It outwardly protrudes in the mounting surface 20a, it in this embodiment, can be along the radian of mounting surface 20a in positioning ring 21 and mounting surface
Crackle or groove of the junction setting of 20a for fusing, in this way after positioning ring 21 and mounting surface 20a are disconnected, positioning ring
21 form the section of arc, and the section can also slide on mounting surface 20a.
As shown in figure 4, positioning ring 21 and mounting surface 20a are disconnected later still by the first limit due to the presence of connector 22
Position circle 23 and the second spacing collar 24 clamp, therefore positioning ring 21 will not be flown off, and also would not cause secondary damage to engine.
In one embodiment, connector 22 can be stay bolt, and one end of connector 22 is provided in across first
It is then passed through positioning ring 21 after one in spacing collar 23 and the second spacing collar 24, is limited again with the first spacing collar 23 and second later
Another connection in circle 24, so that the first spacing collar 23, the second spacing collar 24 are fixedly connected integrally with positioning ring 21.
Correspondingly, one in the first spacing collar 23 and the second spacing collar 24 is provided with through-hole, is provided with connecting hole on another；Positioning
Through-hole is offered on ring 21, connector 22 runs through through-hole, it ensure that positioning ring 21 is set in always on connector 22, into one
Step is flown off after preventing positioning ring 21 to be broken.
The specific structure of the first spacing collar 23 and the second spacing collar 24 is discussed below.
With continued reference to Fig. 3 and Fig. 4, the inside radially of the first spacing collar 23 has the first contact surface 23a, the second limit
The inside radially of circle 24 has the second contact surface 24a, the first contact surface 23a and the second contact surface 24a is used for and mounting surface
20a distinguishes sphere-contact each other；The outside radially of first spacing collar 23 and the outside quilt radially of the second spacing collar 24
It is arranged to support two end faces of the inner ring 10 of bearing 1 in the axial direction respectively in the axial direction, to carry out axial limiting to bearing 1,
And support two convex shoulder 10a of the inner ring 10 of bearing 1 respectively radially, to carry out radial limit to bearing 1.First contact
Face 23a and the second contact surface 24a is a part of spherical surface respectively, can be concave spherical surface, is also possible to convex spherical.
The outside radially of first spacing collar 23 has first annular face 23b and first annular flange 23c, first annular
Flange 23c is radially raised in first annular face 23b；The outside of second spacing collar 24 has the second annular surface 24b and the
Second ring flange 24c, the second annular flange 24c are radially raised in the second annular surface 24b；
First annular flange 23c and the second annular flange 24c are spaced setting in the axial direction, and are configured to divide in the axial direction
Two end faces of the inner ring 10 of bearing 1 in the axial direction are not supported, and support two convex shoulder 10a of bearing 1 respectively radially,
To the inner ring 10 of bearing support 1, and make inner ring 10, first annular flange 23c, the second annular flange 24c, first annular face
23b, the second annular surface 24b are limited jointly forms closed annular housing 2a.
Further to alleviate the radial load under non-equilibrium state, Aero-engine Bearing bearing assembly 2 further includes by hindering
The damping energy-absorbing body 25 that Buddhist nun's energy-absorbing material is constituted；It damps energy-absorbing material and is full of annular housing 2a, to be formed in annular housing 2a
Damp energy-absorbing body 25.Damping energy-absorbing material can be metal-rubber or foamed aluminium.
As shown in figure 4, fan propeller 3 generates huge unbalanced load, and positioning ring 21 is being installed after FBO event occurs
It fails at the 20a of face by predetermined manner, makes to form flexural pivot connection between the first spacing collar 23 and the second spacing collar 24 and mounting surface 20a,
Pitch stiffness of the fan shaft at No. 2 bearings is discharged, after avoiding the primary fusing part at No. 1 bearing from failing, fan propeller 3 is put
Dynamic radius increases, and fan shaft 5 generates the case where excessive stress is concentrated at No. 2 bearings.Meanwhile the convex shoulder 10a on inner ring 10
Fracture makes that radially the opposite position of generation in range can be being limited between inner ring 10 and the first spacing collar 23 and the second spacing collar 24
It moves, squeezed air-damping energy-absorbing body 25, to further consume the energy of FBO, reduces the load for being transmitted to the critical components such as Middle casing 4
Lotus.
Although the present invention is disclosed as above with preferred embodiment, it is not for limiting the present invention, any this field skill
Art personnel without departing from the spirit and scope of the present invention, can make possible variation and modification, all without departing from this hair
The content of bright technical solution, according to the technical essence of the invention any modification to the above embodiments, equivalent variations and repair
Decorations, each fall within the protection scope that the claims in the present invention are defined.
Claims (10)
1. a kind of Aero-engine Bearing bearing assembly is used to support bearing (1), including mounting base (20), the peace
Filling seat (20) has mounting surface (20a)；The mounting surface (20a) is a part of spherical surface；
It is characterized in that, the Aero-engine Bearing bearing assembly (2) further includes positioning ring (21), connector (22), first
Spacing collar (23) and the second spacing collar (24)；
First spacing collar (23) and second spacing collar (24) respectively with the mounting surface (20a) sphere-contact each other,
And the inner ring (10) for supporting the bearing (1) respectively；The positioning ring (21) connect with the mounting surface (20a), and
And between first spacing collar (23) and second spacing collar (24)；The connector (22) limits described first
Circle (23), second spacing collar (24) are fixedly connected integrally with the positioning ring (21)；
The positioning ring (21) is arranged to be detached from the case where bearing overload power with the mounting surface (20a), and allows by institute
It states connector (22) and is fixedly connected with integral first spacing collar (23), second spacing collar (24) and the positioning ring
(21) it can be slided on the mounting surface (20a).
2. Aero-engine Bearing bearing assembly as described in claim 1, which is characterized in that the connector (22) is long spiral shell
Bolt, one end of the stay bolt are provided in one in first spacing collar (23) and second spacing collar (24)
The positioning ring (21) are then passed through after a, later again with it is another in first spacing collar (23) and second spacing collar (24)
An outer connection, thus by the fixed company of first spacing collar (23), second spacing collar (24) and the positioning ring (21)
It is connected into one.
3. Aero-engine Bearing bearing assembly as described in claim 1, which is characterized in that first spacing collar (23)
Inside radially has the first contact surface (23a), and the inside radially of second spacing collar (24) has the second contact
Face (24a), first contact surface (23a) and second contact surface (24a) are used for the mounting surface (20a) difference each other
Sphere-contact；
The outside radially of first spacing collar (23) and the outside radially of second spacing collar (24) are set
At two end faces of the inner ring (10) of the bearing (1) in the axial direction are supported respectively in the axial direction, to be carried out to the bearing (1)
Axial limiting, and support two convex shoulders (10a) of the inner ring (10) of the bearing (1) respectively radially, to the axis
It holds (1) and carries out radial limit.
4. Aero-engine Bearing bearing assembly as claimed in claim 3, which is characterized in that first spacing collar (23)
Outside radially has first annular face (23b) and first annular flange (23c), and the first annular flange (23c) is along diameter
To outwardly convex in the first annular face (23b)；The outside of second spacing collar (24) have the second annular surface (24b) and
Second annular flange (24c), second annular flange (24c) are radially raised in second annular surface (24b)；
The first annular flange (23c) and second annular flange (24c) are spaced setting in the axial direction, and are provided in
Two end faces of the inner ring (10) of the bearing (1) in the axial direction are supported in axial direction respectively, and support institute respectively radially
Two convex shoulders (10a) of bearing (1) are stated, to support the inner ring (10) of the bearing (1), and make the inner ring (10), described
First annular flange (23c), second annular flange (24c), the first annular face (23b), second annular surface
(24b) is limited jointly and is formed closed annular housing (2a).
5. Aero-engine Bearing bearing assembly as claimed in claim 4, which is characterized in that the Aero-engine Bearing branch
Bearing assembly (2) further includes the damping energy-absorbing body (25) being made of damping energy-absorbing material；The damping energy-absorbing material is full of the ring
Shape cavity (2a), to form the damping energy-absorbing body (25) in the annular housing (2a).
6. Aero-engine Bearing bearing assembly as claimed in claim 5, which is characterized in that the damping energy-absorbing material is gold
Belong to rubber or foamed aluminium.
7. a kind of aero-engine, including bearing (1), the bearing (1) includes inner ring (10), roller (11) and outer ring (12),
It is characterized in that, the aero-engine (100) further includes the boat as described in any one of claim 1 to 6 claim
Empty engine bearing bearing assembly (2), the Aero-engine Bearing bearing assembly (2) include mounting base (20), the installation
Seat (20) has mounting surface (20a)；The mounting surface (20a) is a part of spherical surface；
The Aero-engine Bearing bearing assembly (2) further include positioning ring (21), connector (22), the first spacing collar (23) and
Second spacing collar (24)；
First spacing collar (23) and second spacing collar (24) respectively with the mounting surface (20a) sphere-contact each other,
And the inner ring (10) for supporting the bearing (1) respectively；The positioning ring (21) connect with the mounting surface (20a), and
And between first spacing collar (23) and second spacing collar (24)；The connector (22) is used for described first
Spacing collar (23), second spacing collar (24) are fixedly connected integrally with the positioning ring (21)；
The positioning ring (21) is arranged to be detached from the case where bearing overload power with the mounting surface (20a), so that described
Connector (22) is fixedly connected with integral first spacing collar (23), second spacing collar (24) and the positioning ring
(21) it can be slided on the mounting surface (20a).
8. aero-engine as claimed in claim 7, which is characterized in that the aero-engine (100) further includes intermediary machine
Casket (4) and fan shaft (5)；
The outer ring (12) is fixedly mounted on the Middle casing (4)；The mounting base (20) is fixedly mounted on the fan
On axis (5), and it is located at the inside of the inner ring (10).
9. aero-engine as claimed in claim 8, which is characterized in that the bearing (1) for the aero-engine institute
State the rear support bearing of fan shaft (5).
10. aero-engine as claimed in claim 7, which is characterized in that there are two convex shoulders along axial tool for the inner ring (10)
(10a), protrusion is set to two end faces of the inner ring (10) in the axial direction to two convex shoulders (10a) respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810166235.6A CN110206646B (en) | 2018-02-28 | 2018-02-28 | Aeroengine bearing support subassembly and aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810166235.6A CN110206646B (en) | 2018-02-28 | 2018-02-28 | Aeroengine bearing support subassembly and aeroengine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110206646A true CN110206646A (en) | 2019-09-06 |
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| CN112498708A (en) * | 2020-06-01 | 2021-03-16 | 重庆宗申航空发动机制造有限公司 | Aviation unmanned aerial vehicle and aeroengine installing support |
| CN112983651A (en) * | 2021-04-26 | 2021-06-18 | 黄锴 | Small-size aviation birotor unmanned aerial vehicle engine |
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| CN110206646B (en) | 2020-08-11 |
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