CN106762151A - A kind of aeroplane engine main bearing inner ring integral structure - Google Patents
A kind of aeroplane engine main bearing inner ring integral structure Download PDFInfo
- Publication number
- CN106762151A CN106762151A CN201611068975.3A CN201611068975A CN106762151A CN 106762151 A CN106762151 A CN 106762151A CN 201611068975 A CN201611068975 A CN 201611068975A CN 106762151 A CN106762151 A CN 106762151A
- Authority
- CN
- China
- Prior art keywords
- inner ring
- retainer
- bearing
- annular groove
- outer shroud
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- 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
-
- 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
- F02C7/12—Cooling of plants
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Rolling Contact Bearings (AREA)
Abstract
The present invention discloses a kind of aeroplane engine main bearing inner ring integral structure, mainly it is made up of outer shroud, retainer, inner ring, bearing, retainer is covered with inner ring, and radial hole and annular groove are formed between inner ring and retainer, outer shroud is covered with retainer top；Bearing is placed in the inner chamber that outer shroud, retainer, inner ring are formed；Through multiple nozzle openings are provided with inner ring, the nozzle opening is correspondingly arranged with retainer bottom, and is connected with radial hole；Lubricating oil is flowed up in radial hole by nozzle opening, then flows to bearing and annular groove, in a part of lubricating oil of annular groove memory storage, plays a part of continuous lubrication.The present invention solves the problems, such as lubrication effect on driving birds is not good, it is ensured that aero-engine is safe and reliable to be used.The present invention is conducive to simplifying design, reduces manufacturing cost, optimization lubrication structure, mitigates weight.Structure of the present invention can improve the functional reliability of bearing.
Description
Technical field
The invention belongs to aero-engine mechanical system design technical field, aeroplane engine main bearing is mainly used in,
Be conducive to simplifying design, reduce manufacturing cost, optimization lubrication system, and then improve the functional reliability of base bearing, specifically
A kind of aeroplane engine main bearing inner ring integral structure.
Background technology
Base bearing primarily served in aero-engine supporting be oriented to effect, and be determined for axial workpiece with
The relative motion position of other parts, the quality of its performance directly influences the performance of aero-engine transmission system.The axis of rolling
It is the important part of aero-engine machine driven system to hold, mainly by inner ring, outer shroud, rolling element and the part of retainer four
Composition.
By taking the existing five fulcrum rollers assembling of certain engine and lubrication system as an example, five fulcrum rollers belong to Internal and external cycle and revolve simultaneously
The intershaft bearing for turning, in the middle of high-pressure turbine and low-pressure turbine, inner ring is arranged on low-pressure turbine axle journal, is turned with low-pressure turbine
It is dynamic；Outer ring is arranged in high-pressure turbine journal hole, is rotated with high-pressure turbine, and retainer is fixed by outer ring guiding during work
The heart.Under current bearing and the design of left and right oil catcher, the lubrication of bearing working face is not enough, especially in inner ring.
According to current tangential velocity, the oily stream of lubricating oil injection is not up to the gap between inner ring and retainer, can be kept the side of frame
Face reflects and will not enter Bearing inner.
From fault data statistics, most main bearing of engine failure problems are all by bearing lubrication cooling effect
Caused by not good.Therefore, the receipts oil efficiency of base bearing, the major parameter as design bearing are improved.
The content of the invention
It is an object of the present invention to provide a kind of aeroplane engine main bearing inner ring integral structure, inner ring and left and right oil catcher
It is fused into one, redesigns the oil-hole location in inner ring, solves that aero-engine main bearing lubrication cooling effect is not good asks
Topic.
The scheme that uses to achieve the above object of the present invention is：
A kind of aeroplane engine main bearing inner ring integral structure, it is characterised in that：
Mainly it is made up of outer shroud, retainer, inner ring, bearing,
Retainer is covered with inner ring, and radial hole and annular groove are formed between inner ring and retainer, in retainer
Top is covered with outer shroud；
Bearing is placed in the inner chamber that outer shroud, retainer, inner ring are formed；
Through multiple nozzle openings are provided with inner ring, the nozzle opening is correspondingly arranged with retainer bottom, and is connected with radial hole；
Lubricating oil is flowed up in radial hole by nozzle opening, then flows to bearing and annular groove, in annular groove internal memory
A part of lubricating oil is stored up, plays a part of continuous lubrication.
Inner ring left side is additionally provided with installation groove, and inclined hole is provided with groove.
It is an advantage of the invention that：
The present invention solves the problems, such as lubrication effect on driving birds is not good, ensures that aero-engine is safe and reliable from design structure
Use.The present invention is conducive to simplifying design, reduces manufacturing cost, optimization lubrication structure, mitigates weight.Structure energy of the present invention
Improve the functional reliability of bearing.
Brief description of the drawings
Fig. 1 is schematic structural view of the invention.
Specific embodiment
As shown in figure 1, a kind of aeroplane engine main bearing inner ring integral structure, mainly by outer shroud 1, retainer 2, inner ring
3rd, bearing 4 is constituted,
Retainer 2 is covered with inner ring 3, and radial hole 6 and annular groove 7 are formed between inner ring 3 and retainer 2,
The top of retainer 2 is covered with outer shroud 1；
Bearing 4 is placed in the inner chamber that outer shroud 1, retainer 2, inner ring 3 are formed；
Through being provided with multiple nozzle openings 5 in inner ring 3, the nozzle opening 5 is correspondingly arranged with the bottom of retainer 2, and with radial hole 6
Connection；
Lubricating oil is flowed up in radial hole 6 by nozzle opening 5, bearing 4 and annular groove 7 is then flowed to, in annular groove 7
A part of lubricating oil of memory storage, plays a part of continuous lubrication.
The left side of inner ring 3 is additionally provided with installation groove, and inclined hole is provided with groove.
The upper left side of inner ring 3 is provided with 4 nozzle openings 5 of Φ 0.8, and right side is provided with 2 nozzle openings 5 of Φ 0.8.
As illustrated by the arrows in fig. 1, the oil-hole location in inner ring, can improve the lubrication effect of bearing.Lubricating oil passes through inner ring
On radial hole be directed to annular groove on bearing bore diameter, then directly by the radial hole under retainer spigot surface, the guiding
Contact surface on face and Internal and external cycle has also obtained preferable lubrication, not good to solve the problems, such as bearing lubrication cooling effect, meets
Engine health is reliably used.
Claims (3)
1. a kind of aeroplane engine main bearing inner ring integral structure, it is characterised in that：
Mainly it is made up of outer shroud, retainer, inner ring, bearing,
Retainer is covered with inner ring, and radial hole and annular groove are formed between inner ring and retainer, on retainer top
It is covered with outer shroud；
Bearing is placed in the inner chamber that outer shroud, retainer, inner ring are formed；
Through multiple nozzle openings are provided with inner ring, the nozzle opening is correspondingly arranged with retainer bottom, and is connected with radial hole；
Lubricating oil is flowed up in radial hole by nozzle opening, then flows to bearing and annular groove, in annular groove memory storage one
Parts of lubricating oil, plays a part of continuous lubrication.
2. a kind of aeroplane engine main bearing inner ring integral structure according to claim 1, it is characterised in that：
Inner ring left side is additionally provided with installation groove, and inclined hole is provided with groove.
3. a kind of aeroplane engine main bearing inner ring integral structure according to claim 1, it is characterised in that：
Inner ring upper left side is provided with 4 nozzle openings 5 of Φ 0.8, and right side is provided with 2 nozzle openings 5 of Φ 0.8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611068975.3A CN106762151A (en) | 2016-11-29 | 2016-11-29 | A kind of aeroplane engine main bearing inner ring integral structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611068975.3A CN106762151A (en) | 2016-11-29 | 2016-11-29 | A kind of aeroplane engine main bearing inner ring integral structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106762151A true CN106762151A (en) | 2017-05-31 |
Family
ID=58905106
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611068975.3A Pending CN106762151A (en) | 2016-11-29 | 2016-11-29 | A kind of aeroplane engine main bearing inner ring integral structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106762151A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107795381A (en) * | 2017-11-23 | 2018-03-13 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of lubricating oil collection structure of the bearing radial direction fuel feeding between rotor |
| CN108167336A (en) * | 2017-12-27 | 2018-06-15 | 中国航发哈尔滨轴承有限公司 | One kind is for Aero-engine Bearing and receives oil ring connection structure |
| CN108980202A (en) * | 2017-06-01 | 2018-12-11 | 中国航发湖南动力机械研究所 | A kind of roller bearing |
| CN111734673A (en) * | 2020-07-02 | 2020-10-02 | 中国航发常州兰翔机械有限责任公司 | Lubricating system for shaft of aircraft engine and using method of lubricating system |
| US10815830B2 (en) | 2017-12-21 | 2020-10-27 | Raytheon Technologies Corporation | Lightweight tierod |
| CN112648295A (en) * | 2019-10-09 | 2021-04-13 | 中国航发商用航空发动机有限责任公司 | Bearing assembly of aircraft engine and aircraft engine |
| CN114087289A (en) * | 2021-11-29 | 2022-02-25 | 中国航发哈尔滨轴承有限公司 | Aeroengine main shaft bearing assembly capable of improving lean oil resistance |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR635757A (en) * | 1926-06-19 | 1928-03-24 | Siemens Schuckertwerke Gmbh | Roller bearing for electrical machines and other machines |
| US3195965A (en) * | 1961-10-25 | 1965-07-20 | Fafnir Bearing Co | Lubricating means for an antifriction bearing |
| US4334720A (en) * | 1980-02-11 | 1982-06-15 | Industrial Tectonics, Inc. | Split-inner-ring ball bearing with lubrication structure |
| JP2008002659A (en) * | 2006-06-26 | 2008-01-10 | Ntn Corp | High-speed rotation single row cylindrical roller bearing |
| WO2012135254A1 (en) * | 2011-03-28 | 2012-10-04 | The Timken Company | Bearing lubrication passage |
| CN103946570A (en) * | 2011-10-10 | 2014-07-23 | 通用电气公司 | Dynamically-lubricated bearing and method of dynamically lubricating a bearing |
| CN204755603U (en) * | 2015-05-27 | 2015-11-11 | 邯郸鸿力轴承有限公司 | Antiwear high -speed floating bearing |
-
2016
- 2016-11-29 CN CN201611068975.3A patent/CN106762151A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR635757A (en) * | 1926-06-19 | 1928-03-24 | Siemens Schuckertwerke Gmbh | Roller bearing for electrical machines and other machines |
| US3195965A (en) * | 1961-10-25 | 1965-07-20 | Fafnir Bearing Co | Lubricating means for an antifriction bearing |
| US4334720A (en) * | 1980-02-11 | 1982-06-15 | Industrial Tectonics, Inc. | Split-inner-ring ball bearing with lubrication structure |
| JP2008002659A (en) * | 2006-06-26 | 2008-01-10 | Ntn Corp | High-speed rotation single row cylindrical roller bearing |
| WO2012135254A1 (en) * | 2011-03-28 | 2012-10-04 | The Timken Company | Bearing lubrication passage |
| CN103946570A (en) * | 2011-10-10 | 2014-07-23 | 通用电气公司 | Dynamically-lubricated bearing and method of dynamically lubricating a bearing |
| CN204755603U (en) * | 2015-05-27 | 2015-11-11 | 邯郸鸿力轴承有限公司 | Antiwear high -speed floating bearing |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108980202A (en) * | 2017-06-01 | 2018-12-11 | 中国航发湖南动力机械研究所 | A kind of roller bearing |
| CN107795381A (en) * | 2017-11-23 | 2018-03-13 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of lubricating oil collection structure of the bearing radial direction fuel feeding between rotor |
| US10815830B2 (en) | 2017-12-21 | 2020-10-27 | Raytheon Technologies Corporation | Lightweight tierod |
| CN108167336A (en) * | 2017-12-27 | 2018-06-15 | 中国航发哈尔滨轴承有限公司 | One kind is for Aero-engine Bearing and receives oil ring connection structure |
| CN112648295A (en) * | 2019-10-09 | 2021-04-13 | 中国航发商用航空发动机有限责任公司 | Bearing assembly of aircraft engine and aircraft engine |
| CN112648295B (en) * | 2019-10-09 | 2022-07-08 | 中国航发商用航空发动机有限责任公司 | Bearing assembly of aircraft engine and aircraft engine |
| CN111734673A (en) * | 2020-07-02 | 2020-10-02 | 中国航发常州兰翔机械有限责任公司 | Lubricating system for shaft of aircraft engine and using method of lubricating system |
| CN114087289A (en) * | 2021-11-29 | 2022-02-25 | 中国航发哈尔滨轴承有限公司 | Aeroengine main shaft bearing assembly capable of improving lean oil resistance |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170531 |