CN105443587A - Integrated bearing supporting structure used for aviation engine - Google Patents
Integrated bearing supporting structure used for aviation engine Download PDFInfo
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- CN105443587A CN105443587A CN201410437393.2A CN201410437393A CN105443587A CN 105443587 A CN105443587 A CN 105443587A CN 201410437393 A CN201410437393 A CN 201410437393A CN 105443587 A CN105443587 A CN 105443587A
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- bearing
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- bearing supporting
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Abstract
The invention relates to an integrated bearing supporting structure for an aviation engine. The integrated bearing supporting structure comprises a mounting edge, a first bearing supporting spoke, a second bearing supporting spoke, a first bearing supporting seat and a second bearing supporting seat, one end of the first bearing supporting spoke is connected to the mounting edge, the other end of the first bearing supporting spoke is connected to the first bearing supporting seat, one end of the second bearing supporting spoke is connected to the mounting edge, the other end of the second bearing supporting spoke is connected to the second bearing supporting seat, the first bearing supporting seat is used for supporting a first bearing, the second bearing supporting seat is used for supporting a second bearing, and the quantity of the mounting edge is 1. The integrated bearing supporting structure for an aviation engine has the advantages of part quantity reduction, occupied space reduction, reduced weight, and convenience for dismounting and maintaining.
Description
Technical field
The present invention relates to the integrated form bearing support structure for aeroengine.
Background technique
In aeroengine, the scheme adopting two or more bearings to combine at same fulcrum can be improved bearing working environment, improve bearing life, the high pressure rotor front fulcrum of money type as several in GE company adopts the supporting structure scheme of duplex bearing, one of them bearing is allowed to bear more axial force, another bearing bears more radial force, and such technological scheme makes that bearing working environment significantly improves, the life-span improves greatly.But the structure that the problem that such technological scheme is brought is bearing pivot assembly becomes complicated, Assembly part quantity increases, and the weight of bearing support structure also increases.
Such as, as shown in Figure 1, in the typical duplex bearing supported scheme of one, the rotor axial power that ball bearing 4 and roller bearing 5 bear and radial force reasonable distribution, substantially improve bearing working environment, but can see that bearing support structure also becomes more complicated, need free-standing ball bearing supporting structure 11 and free-standing roller bearing structure 12, number of spare parts increases.
Therefore, wish there is a kind of bearing support structure for aeroengine, it can reduce number of spare parts, reduces to take up room, alleviates structure weight, is convenient to dismounting and safeguards.
Summary of the invention
Essential idea of the present invention is in common duplex bearing supported scheme, is combined with each other by the supporting structure of two bearings, to simplify fulcrum modular construction, to reduce number of spare parts, alleviates fulcrum lightweight packages simultaneously, also can reduce the complexity of assembling and maintenance.In addition, along with the progress of the technology such as 3D printing, powder metallurgy, in fulcrum assembly, supporting structure can realize diversified processing technology, and highly integrated structural type and technique also can manufacturing.
One object of the present invention is, for the above-mentioned defect for the bearing support structure of aeroengine in prior art, provides a kind of bearing support structure for aeroengine, it can reduce number of spare parts, reduction takes up room, and alleviates structure weight, is convenient to dismounting and safeguards.
Above object of the present invention is realized by a kind of integrated form bearing support structure for aeroengine, described integrated form bearing support structure comprises mounting edge, clutch shaft bearing supporting spoke, second bearing supporting spoke, clutch shaft bearing supporting base and the second bearing block, described clutch shaft bearing supporting spoke is connected to described mounting edge in its one end and is connected to described clutch shaft bearing supporting base at its other end, described second bearing supporting spoke is connected to described mounting edge in its one end and is connected to described second bearing block at its other end, described clutch shaft bearing supporting base is for supporting clutch shaft bearing, described second bearing block is for supporting the second bearing, the quantity of described mounting edge is one.
According to technique scheme, the integrated form bearing support structure for aeroengine of the present invention can play following Advantageous Effects: can reduce number of spare parts, reduce to take up room, alleviate structure weight, is convenient to dismounting and safeguards.
It is preferred that described clutch shaft bearing supporting spoke is many clutch shaft bearing supporting spokes, described second bearing supporting spoke is many second bearing supporting spokes; Described clutch shaft bearing supporting spoke and described second bearing supporting spoke are positioned at same planar annular in the radial direction at described integrated form bearing support structure, and at the circumferential direction alternate of described integrated form bearing support structure.
According to technique scheme, the integrated form bearing support structure for aeroengine of the present invention can play following Advantageous Effects: the uniform load of bearing can be made to be distributed in bearing supporting spoke; Save radial space, make overall structure compacter.
It is preferred that described clutch shaft bearing is ball bearing, described clutch shaft bearing supporting spoke is ball bearing supporting spoke, and described clutch shaft bearing supporting base is ball bearing supporting base; Described second bearing is roller bearing, and described second bearing supporting spoke is roller bearing spoke, and described second bearing block is roller bearing seat.
According to technique scheme, integrated form bearing support structure for aeroengine of the present invention can play following Advantageous Effects: for specific aeroengine structure, can reduce number of spare parts, reduce to take up room, alleviate structure weight, be convenient to dismounting and safeguard.
It is preferred that described clutch shaft bearing supporting base is nearer apart from described mounting edge than described second bearing block.
According to technique scheme, integrated form bearing support structure for aeroengine of the present invention can play following Advantageous Effects: can optimize the axial arranged of clutch shaft bearing supporting base and the second bearing block, thus save space further, make overall structure compacter.
It is preferred that described second bearing block is nearer apart from described mounting edge than described clutch shaft bearing supporting base.
According to technique scheme, integrated form bearing support structure for aeroengine of the present invention can play following Advantageous Effects: can optimize the axial arranged of clutch shaft bearing supporting base and the second bearing block, thus save space further, make overall structure compacter.
It is preferred that also comprise link, described link is used for the load-bearing frame described mounting edge being connected to aeroengine.
According to technique scheme, the integrated form bearing support structure for aeroengine of the present invention can play following Advantageous Effects: the load-bearing frame that integrated form bearing support structure can be connected to securely aeroengine.
It is preferred that the radial rigidity of described roller bearing spoke is larger than the radial rigidity of described ball bearing supporting spoke.
According to technique scheme, the integrated form bearing support structure for aeroengine of the present invention can play following Advantageous Effects: most of radial load can be transmitted by roller bearing.
Preferably, also comprise the 3rd bearing supporting spoke and the 3rd bearing block, described 3rd bearing supporting spoke is connected to described mounting edge in its one end and is connected to described 3rd bearing block at its other end, and described 3rd bearing block is for supporting the 3rd bearing.
According to technique scheme, integrated form bearing support structure for aeroengine of the present invention can play following Advantageous Effects: for specific three bearing aeroengine structures, can reduce number of spare parts, reduce to take up room, alleviate structure weight, be convenient to dismounting and safeguard.
Accompanying drawing explanation
Fig. 1 is the scheme of installation of the duplex bearing separate support structure for aeroengine of prior art.
Fig. 2 is the scheme of installation of the integrated form bearing support structure for aeroengine of the present invention.
Fig. 3 (a) is the sectional view of the integrated form bearing support structure for aeroengine of one embodiment of the invention.
Fig. 3 (b) is the stereogram of the integrated form bearing support structure for aeroengine of one embodiment of the invention.
Fig. 4 (a) is the sectional view of the integrated form bearing support structure for aeroengine of another embodiment of the present invention.
Fig. 4 (b) is the stereogram of the integrated form bearing support structure for aeroengine of another embodiment of the present invention.
Reference numerals list:
1, integrated form bearing support structure;
2, link;
3, attaching nut;
4, ball bearing;
5, roller bearing;
6, rotor;
7, load-bearing frame;
11, free-standing ball bearing supporting structure
12, free-standing roller bearing structure
101, mounting edge;
102, ball bearing supporting spoke;
103, ball bearing supporting base;
104, roller bearing spoke;
105, roller bearing seat.
Embodiment
Below in conjunction with specific embodiments and the drawings, the invention will be further described; set forth more details in the following description so that fully understand the present invention; but the present invention obviously can implement with multiple this alternate manner described that is different from; those skilled in the art when doing similar popularization, deduction without prejudice to when intension of the present invention according to practical situations, therefore should can not limit the scope of the invention with the content of this specific embodiment.
Fig. 2 is the scheme of installation of the integrated form bearing support structure for aeroengine of the present invention.Fig. 3 (a) is the sectional view of the integrated form bearing support structure for aeroengine of one embodiment of the invention.Fig. 3 (b) is the stereogram of the integrated form bearing support structure for aeroengine of one embodiment of the invention.Fig. 4 (a) is the sectional view of the integrated form bearing support structure for aeroengine of another embodiment of the present invention.Fig. 4 (b) is the stereogram of the integrated form bearing support structure for aeroengine of another embodiment of the present invention.
The rotor of aeroengine must rely on bearing to support and could operate, and the present invention devises a kind of integrated form bearing support structure for aeroengine, as shown in Figure 2.One end fulcrum of rotor 6 is adjacent arranges two bearings, ball bearing 4 and roller bearing (also claiming stick roller bearing) 5.Two bearings employ integrated form bearing support structure 1 and support it.
Integrated form bearing support structure 1 for aeroengine comprises mounting edge 101, ball bearing supporting spoke 102, roller bearing spoke 104, ball bearing supporting base 103 and roller bearing seat 105, ball bearing supporting spoke 102 is connected to mounting edge 101 in its one end and is connected to ball bearing supporting base 103 at its other end, roller bearing spoke 104 is connected to same mounting edge 101 in its one end and is connected to roller bearing seat 105 at its other end, ball bearing supporting base 103 is for rotating bearing ball bearing 4, roller bearing seat 105 is for supporting roller bearing 5, the quantity of mounting edge 101 is one.
Integrated form bearing support structure 1 is a holistic structure of list.
It is preferred that ball bearing 4 is fixed on ball bearing supporting base 103 by attaching nut 3.The thrust load of rotor 6 passes to integrated bearing support structure 1, and a small part radial load of rotor 6 also passes to integrated form bearing support structure 1 simultaneously.Roller bearing 5 contacts with roller bearing seat 105, mainly by the radial load transfer of rotor 6 to integrated form bearing support structure.
It is preferred that the mounting edge 101 of integrated form bearing support structure 1 and the load-bearing frame 7 of aeroengine link together by link 2, dynamic changes process ball bearing 4 and roller bearing 5 jointly transmitted is on load-bearing frame 7.
It is preferred that ball bearing supporting spoke 102 and roller bearing spoke 104 are positioned at same planar annular in the radial direction at integrated form bearing support structure 1.Part supporting spoke in planar annular constitutes ball bearing supporting spoke 102, and another part supporting spoke constitutes roller bearing spoke 104.
It is preferred that the spoke width of integrated form bearing support structure 1 and thickness equidimension can adjust as required, and then change the strength and stiffness of ball bearing supporting spoke 102 and roller bearing spoke 104.Ball bearing supporting spoke 102 and roller bearing spoke 104 can change its strength and stiffness as required, control magnitude of load that two bearing blocks transmit and direction respectively.
The radial rigidity of ball bearing supporting spoke 102 and roller bearing spoke 104 determines the radial load distribution of rotor 6 on ball bearing 4 and roller bearing 5.Generally, the radial rigidity of roller bearing spoke 104 is larger than the radial rigidity of ball bearing supporting spoke 102, and the radial load major part of rotor 6 is transmitted by roller bearing 5.
Ball bearing supporting spoke 102 and roller bearing spoke 104 are connected directly between on same mounting edge 101, do not use other linkage structures, decrease number of spare parts, alleviate structure weight to greatest extent, saved installing space simultaneously, overall bearing support structure makes detachable maintaining simpler, and assembling, maintenance get a promotion.
Specifically, beneficial effect of the present invention mainly contain following some:
(1) number of spare parts reduces, and reduces to an integrated form bearing support structure by original two free-standing bearing support structures;
(2) reduce taking up room of bearing support structure, make structural design compacter;
(3) alleviate structure weight, the structure division that can be shared by two bearing support structures merges, and alleviates structure weight;
(4) simpler during the dismounting of integrated form bearing support structure, maintenance cost is lower.
It is preferred that ball bearing supporting spoke 102 and roller bearing spoke 104 are positioned at same planar annular in the radial direction at integrated form bearing support structure 1, save radial space, make overall structure compacter.
In the embodiment shown in Fig. 3 (a) He Fig. 3 (b), ball bearing 4 is nearer apart from mounting edge 101, and roller bearing 5 is slightly far away apart from mounting edge 101.Therefore, ball bearing supporting base 103 is nearer apart from mounting edge 101, and roller bearing seat 105 is slightly far away apart from mounting edge 101.
In another embodiment shown in Fig. 4 (a) He Fig. 4 (b), roller bearing 5 is nearer apart from mounting edge 101, and ball bearing 4 is slightly far away apart from mounting edge 101.Therefore, roller bearing seat 105 is nearer apart from mounting edge 101, and ball bearing supporting base 103 is slightly far away apart from mounting edge 101.
It is preferred that as shown in Fig. 3 (b) He Fig. 4 (b), ball bearing supporting spoke 102 is many ball bearing supporting spokes, and roller bearing spoke 104 is many roller bearing spokes.
It is preferred that many ball bearing supporting spokes 102 and Duo Gen roller bearing spoke 104 separate one by one.Certainly, those skilled in the art are appreciated that on the basis of the disclosure of invention, many ball bearings supporting spokes 102 and Duo Gen roller bearing spoke 104 may not be and separate one by one, such as, there are two ball bearing supporting spokes 102 and a roller bearing spoke 104 in every three supporting spokes, or have a ball bearing supporting spoke 102 and two roller bearing spokes 104 in every three supporting spokes, etc.Above-mentioned modification falls within protection scope of the present invention equally.
The present invention is also not limited only to the combination of a ball bearing and a roller bearing, and for the situation that multiple bearing combines, all bearing support structures integrate, and (as previously mentioned, only having same mounting edge) is applicable to the present invention too.Such as, for the combination of two ball bearings, two ball bearing supporting structures can be integrated (only having same mounting edge); Or for the combination of two ball bearings and a roller bearing, two ball bearing supporting structures (can be only had same mounting edge) together with a roller bearing structure assembly; Or for the combination of a conical bearing and a roller bearing, a conical bearing supporting structure (can be only had same mounting edge) together with a roller bearing structure assembly; Etc..
That is, integrated form bearing support structure 1 such as also can comprise the 3rd bearing supporting spoke and the 3rd bearing block, 3rd bearing supporting spoke is connected to mounting edge 101 in its one end and is connected to the 3rd bearing block at its other end, and the 3rd bearing block is for supporting the 3rd bearing.
Above the specific embodiment of the present invention is described, but it will be understood to those of skill in the art that, above-mentioned embodiment is not construed as limiting the invention, and those skilled in the art can carry out multiple amendment on the basis of above disclosure, and do not exceed scope of the present invention.
Claims (8)
1. the integrated form bearing support structure for aeroengine, it is characterized in that, described integrated form bearing support structure comprises mounting edge, clutch shaft bearing supporting spoke, second bearing supporting spoke, clutch shaft bearing supporting base and the second bearing block, described clutch shaft bearing supporting spoke is connected to described mounting edge in its one end and is connected to described clutch shaft bearing supporting base at its other end, described second bearing supporting spoke is connected to described mounting edge in its one end and is connected to described second bearing block at its other end, described clutch shaft bearing supporting base is for supporting clutch shaft bearing, described second bearing block is for supporting the second bearing, the quantity of described mounting edge is one.
2. as claimed in claim 1 for the integrated form bearing support structure of aeroengine, it is characterized in that, described clutch shaft bearing supporting spoke is many clutch shaft bearing supporting spokes, and described second bearing supporting spoke is many second bearing supporting spokes; Described clutch shaft bearing supporting spoke and described second bearing supporting spoke are positioned at same planar annular in the radial direction at described integrated form bearing support structure, and at the circumferential direction alternate of described integrated form bearing support structure.
3. as claimed in claim 1 for the integrated form bearing support structure of aeroengine, it is characterized in that, described clutch shaft bearing is ball bearing, and described clutch shaft bearing supporting spoke is ball bearing supporting spoke, and described clutch shaft bearing supporting base is ball bearing supporting base; Described second bearing is roller bearing, and described second bearing supporting spoke is roller bearing spoke, and described second bearing block is roller bearing seat.
4. the integrated form bearing support structure for aeroengine as described in claim 1 or 3, is characterized in that, described clutch shaft bearing supporting base is nearer apart from described mounting edge than described second bearing block.
5. the integrated form bearing support structure for aeroengine as described in claim 1 or 3, is characterized in that, described second bearing block is nearer apart from described mounting edge than described clutch shaft bearing supporting base.
6. as claimed in claim 1 for the integrated form bearing support structure of aeroengine, it is characterized in that, also comprise link, described link is used for the load-bearing frame described mounting edge being connected to aeroengine.
7. as claimed in claim 3 for the integrated form bearing support structure of aeroengine, it is characterized in that, the radial rigidity of described roller bearing spoke is larger than the radial rigidity of described ball bearing supporting spoke.
8. as claimed in claim 1 for the integrated form bearing support structure of aeroengine, it is characterized in that, also comprise the 3rd bearing supporting spoke and the 3rd bearing block, described 3rd bearing supporting spoke is connected to described mounting edge in its one end and is connected to described 3rd bearing block at its other end, and described 3rd bearing block is for supporting the 3rd bearing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410437393.2A CN105443587A (en) | 2014-08-29 | 2014-08-29 | Integrated bearing supporting structure used for aviation engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410437393.2A CN105443587A (en) | 2014-08-29 | 2014-08-29 | Integrated bearing supporting structure used for aviation engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105443587A true CN105443587A (en) | 2016-03-30 |
Family
ID=55554117
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410437393.2A Pending CN105443587A (en) | 2014-08-29 | 2014-08-29 | Integrated bearing supporting structure used for aviation engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105443587A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112855776A (en) * | 2021-02-04 | 2021-05-28 | 中国航发沈阳发动机研究所 | Ball rolling rod duplex bearing structure |
| CN113790216A (en) * | 2021-09-22 | 2021-12-14 | 中国航发沈阳发动机研究所 | Rotating shaft double-bearing supporting structure |
| CN113803374A (en) * | 2021-09-22 | 2021-12-17 | 中国航发沈阳发动机研究所 | Rotating shaft supporting structure |
| CN115539146A (en) * | 2022-08-24 | 2022-12-30 | 中国航发湖南动力机械研究所 | Integrated squirrel cage elastic support and axial force measuring method |
| CN115789104A (en) * | 2022-12-26 | 2023-03-14 | 北京航空航天大学 | Squirrel cage-bearing integrated structure with adjustable rigidity |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080152483A1 (en) * | 2006-12-22 | 2008-06-26 | Rolls-Royce North American Technologies, Inc. | Bearing support |
| EP2149681A2 (en) * | 2008-07-31 | 2010-02-03 | General Electric Company | Nested bearing cages |
| CN102939437A (en) * | 2010-06-02 | 2013-02-20 | 斯奈克玛 | Antifriction bearing for an aircraft jet engine provided with a means for axially holding the outer ring thereof |
| US20130108202A1 (en) * | 2011-11-01 | 2013-05-02 | General Electric Company | Bearing support apparatus for a gas turbine engine |
| US20130280063A1 (en) * | 2012-04-23 | 2013-10-24 | General Electric Company | Dual spring bearing support housing |
-
2014
- 2014-08-29 CN CN201410437393.2A patent/CN105443587A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080152483A1 (en) * | 2006-12-22 | 2008-06-26 | Rolls-Royce North American Technologies, Inc. | Bearing support |
| EP2149681A2 (en) * | 2008-07-31 | 2010-02-03 | General Electric Company | Nested bearing cages |
| CN102939437A (en) * | 2010-06-02 | 2013-02-20 | 斯奈克玛 | Antifriction bearing for an aircraft jet engine provided with a means for axially holding the outer ring thereof |
| US20130108202A1 (en) * | 2011-11-01 | 2013-05-02 | General Electric Company | Bearing support apparatus for a gas turbine engine |
| US20130280063A1 (en) * | 2012-04-23 | 2013-10-24 | General Electric Company | Dual spring bearing support housing |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112855776A (en) * | 2021-02-04 | 2021-05-28 | 中国航发沈阳发动机研究所 | Ball rolling rod duplex bearing structure |
| CN113790216A (en) * | 2021-09-22 | 2021-12-14 | 中国航发沈阳发动机研究所 | Rotating shaft double-bearing supporting structure |
| CN113803374A (en) * | 2021-09-22 | 2021-12-17 | 中国航发沈阳发动机研究所 | Rotating shaft supporting structure |
| CN115539146A (en) * | 2022-08-24 | 2022-12-30 | 中国航发湖南动力机械研究所 | Integrated squirrel cage elastic support and axial force measuring method |
| CN115789104A (en) * | 2022-12-26 | 2023-03-14 | 北京航空航天大学 | Squirrel cage-bearing integrated structure with adjustable rigidity |
| CN115789104B (en) * | 2022-12-26 | 2023-06-02 | 北京航空航天大学 | Rigidity-adjustable squirrel cage-bearing integrated structure |
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| C06 | Publication | ||
| PB01 | Publication | ||
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| CB02 | Change of applicant information | ||
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Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Applicant after: China Hangfa commercial aviation engine limited liability company Address before: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Applicant before: AVIC Commercial Aircraft Engine Co.,Ltd. |
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| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160330 |