CN116857288A - Bearing seat cooling structure of main bearing of aero-engine - Google Patents
Bearing seat cooling structure of main bearing of aero-engine Download PDFInfo
- Publication number
- CN116857288A CN116857288A CN202310888635.9A CN202310888635A CN116857288A CN 116857288 A CN116857288 A CN 116857288A CN 202310888635 A CN202310888635 A CN 202310888635A CN 116857288 A CN116857288 A CN 116857288A
- Authority
- CN
- China
- Prior art keywords
- bearing
- oil
- wall
- oil return
- channel
- 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.)
- Granted
Links
- 238000001816 cooling Methods 0.000 title claims abstract description 29
- 239000003921 oil Substances 0.000 claims abstract description 76
- 239000010687 lubricating oil Substances 0.000 claims abstract description 13
- 239000000463 material Substances 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 abstract description 3
- 238000005461 lubrication Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000020169 heat generation Effects 0.000 description 1
- JEIPFZHSYJVQDO-UHFFFAOYSA-N iron(III) oxide Inorganic materials O=[Fe]O[Fe]=O JEIPFZHSYJVQDO-UHFFFAOYSA-N 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 239000000314 lubricant Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000003756 stirring Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C37/00—Cooling of bearings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
- F16C33/02—Parts of sliding-contact bearings
- F16C33/04—Brasses; Bushes; Linings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C35/00—Rigid support of bearing units; Housings, e.g. caps, covers
- F16C35/02—Rigid support of bearing units; Housings, e.g. caps, covers in the case of sliding-contact bearings
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Mounting Of Bearings Or Others (AREA)
Abstract
The application belongs to the technical field of engine assembly, and particularly relates to a bearing seat cooling structure of an aeroengine main bearing. A spiral groove (4) is formed in the inner wall of a bearing seat (1) of an aeroengine main bearing, the spiral groove (4) extends along the circumferential direction and the axial direction of the bearing seat (1) in a spiral mode, meanwhile, an oil inlet channel and an oil return channel which penetrate through the inner wall and the outer wall of the bearing seat are formed in the bearing seat (1), one end of the oil inlet channel is connected with an oil inlet pipe (2), the other end of the oil inlet channel is connected with the starting end of the spiral groove (4), one end of the oil return channel is connected with an oil return pipe (3), the other end of the oil return channel is connected with the tail end of the spiral groove (4), and the inner wall of the bearing seat (1) is in interference fit with the outer wall of a bearing outer ring (6) of a bearing (5) so that the spiral groove (4) forms an lubricating oil cooling channel. The application reduces the flow of lubricating oil entering the bearing, reduces the self-heating of the bearing and effectively controls the temperature of the bearing.
Description
Technical Field
The application belongs to the technical field of engine assembly, and particularly relates to a bearing seat cooling structure of an aeroengine main bearing.
Background
As an important part of an aeroengine, the main bearing plays a vital role in the running process of the engine, and needs to stably and reliably work for a long time under complex working conditions such as high speed, high temperature, load and the like. Lubrication and cooling are necessary conditions for ensuring stable operation of the bearing, and the lubricant in the bearing can not only avoid abnormal abrasion of the working surface, but also play roles in maintaining normal working temperature of the bearing, reducing contact stress, absorbing vibration, preventing rust and the like. To ensure efficient and reliable operation of the bearing, the bearing must be adequately lubricated.
The traditional bearing mainly adopts ring lubrication, oil spraying lubrication, oil bath lubrication, splash lubrication and the like, and the lubricating oil enters the bearing to cool the running parts. However, for the bearing with higher rotating speed in the engine, the lubricating oil enters the bearing to generate intense stirring along with the running of the bearing, but the heat generation quantity of the bearing is increased, the temperature of the bearing is increased, the cooling effect is weakened, and the long-time reliable running of the bearing is not facilitated.
Disclosure of Invention
In order to solve the problems, the application provides a bearing seat cooling structure of an aeroengine main bearing, which achieves the aim of cooling the bearing under the condition that lubricating oil does not enter the bearing.
According to the bearing seat cooling structure of the aeroengine main bearing, the spiral groove is formed in the inner wall of the bearing seat of the aeroengine main bearing, the spiral groove extends along the circumferential direction and the axial direction of the bearing seat in a spiral mode, meanwhile, the oil inlet channel and the oil return channel which penetrate through the inner wall and the outer wall of the bearing seat are formed in the bearing seat, one end of the oil inlet channel is connected with the oil inlet pipe, the other end of the oil inlet channel is connected with the starting end of the spiral groove, one end of the oil return channel is connected with the oil return pipe, the other end of the oil return channel is connected with the tail end of the spiral groove, and the inner wall of the bearing seat is in interference fit with the outer wall of the bearing outer ring of the bearing, so that the spiral groove forms an lubricating oil cooling channel.
Preferably, the radius R of the spiral groove is not more than L/15, and the screw pitch B is not less than L/5, wherein L refers to the effective assembly surface length of the bearing seat and the bearing outer ring.
Preferably, the interference u between the inner wall of the bearing seat and the outer wall of the bearing outer ring satisfies:
u≥α 1 ·D·T 1 -α 2 ·D·T 2 ；
wherein alpha is 1 And alpha 2 The linear expansion coefficients of the materials of the bearing seat and the bearing outer ring are respectively T 1 And T 2 The working temperatures of the bearing seat and the bearing outer ring are respectively shown, and D is the diameter of the bearing outer ring.
Preferably, the oil supply cooling flow rate Q of the spiral groove is configured to:
preferably, the oil inlet channel is connected with the oil inlet pipe through threads, and the oil return channel is connected with the oil return pipe through threads.
Preferably, the end head of the oil inlet pipe is pressed into the oil inlet channel through interference fit, and the end head of the oil return pipe is pressed into the oil return channel through interference fit.
The application reduces the flow of lubricating oil entering the bearing, reduces the self-heating of the bearing and effectively controls the temperature of the bearing.
Drawings
Fig. 1 is a schematic overall structure of a preferred embodiment of a bearing housing cooling structure for an aero-engine main bearing according to the present application.
Fig. 2 is an enlarged schematic view of the structure at I of the embodiment shown in fig. 1.
Wherein, 1-bearing frame, 2-oil inlet pipe, 3-oil return pipe, 4-spiral groove, 5-bearing, 6-bearing outer lane.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the drawings are exemplary and intended to illustrate the present application and should not be construed as limiting the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the present application without making any inventive effort, are intended to fall within the scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The application provides a bearing seat cooling structure of an aeroengine main bearing, as shown in fig. 1-2, a spiral groove 4 is formed in the inner wall of a bearing seat 1 of the aeroengine main bearing, the spiral groove 4 extends spirally along the circumferential direction and the axial direction of the bearing seat 1, meanwhile, an oil inlet channel and an oil return channel which penetrate through the inner wall and the outer wall of the bearing seat are formed in the bearing seat 1, one end of the oil inlet channel is connected with an oil inlet pipe 2, the other end of the oil inlet channel is connected with the starting end of the spiral groove 4, one end of the oil return channel is connected with an oil return pipe 3, the other end of the oil return channel is connected with the tail end of the spiral groove 4, and the inner wall of the bearing seat 1 is in interference fit with the outer wall of a bearing outer ring 6 of a bearing 5 so that the spiral groove 4 forms an oil cooling channel.
After the bearing 5 is arranged on the bearing seat 1, a closed oil path is formed by the bearing outer ring 6 and the spiral groove 4 on the bearing seat 1, cooling lubricating oil enters the spiral groove 4 through the oil inlet pipe 2 and returns to the lubricating oil system through the oil return pipe 3, so that cooling circulation is formed, heat of the bearing outer ring is taken away, and the purpose of cooling is achieved. The application provides a bearing outer ring mounting seat with a spiral oil groove structure, and lubricating oil cools a bearing through the oil groove, so that the purpose of cooling the bearing under the condition that the lubricating oil does not enter the bearing is achieved. By adopting the structure and matching with the conventional cooling mode, the flow of lubricating oil entering the bearing can be reduced, the self-heating of the bearing is reduced, and the temperature of the bearing is effectively controlled.
In order to ensure sufficient bearing rigidity of the bearing outer race 6 and the bearing housing 2, the radius R and the pitch B of the helical groove 4 need to be limited. For example, in some alternative embodiments, the radius R of the spiral groove 4 is not greater than L/15, and the pitch B is not less than L/5, where L refers to the effective assembly surface length of the bearing housing 2 and the bearing outer race 6.
In order to prevent oil leakage from between the bearing seat 2 and the bearing outer ring 6, the bearing seat 2 and the bearing outer ring 6 are ensured to be in interference fit in the working process. For example, in some alternative embodiments, the interference u between the inner wall of the bearing housing 1 and the outer wall of the bearing outer ring 6 satisfies:
u≥α 1 ·D·T 1 -α 2 ·D·T 2 ；
wherein alpha is 1 And alpha 2 The linear expansion coefficients of the materials of the bearing seat 2 and the bearing outer ring 6 are respectively T 1 And T 2 The working temperatures of the bearing seat 2 and the bearing outer ring 6 are respectively shown, and D is the diameter of the bearing outer ring 6.
In some alternative embodiments, the oil supply cooling flow Q of the spiral groove 4 is configured to:
in some alternative embodiments, the oil inlet passage is screwed with the oil inlet pipe 2, and the oil return passage is screwed with the oil return pipe 3. In this embodiment, for example, internal threads are formed in the oil inlet passage and the oil return passage, and the oil inlet pipe 2 and the oil return pipe 3 are adapted to be externally threaded. In an alternative embodiment, a flange plate can be further processed at the outlets of the oil inlet channel and the oil return channel, and the oil inlet pipe 2 and the oil return pipe 3 are in butt joint through the flange plate.
In some alternative embodiments, the end of the oil inlet pipe 2 is pressed into the oil inlet channel through interference fit, and the end of the oil return pipe 3 is pressed into the oil return channel through interference fit.
While the application has been described in detail in the foregoing general description and with reference to specific embodiments thereof, it will be apparent to one skilled in the art that modifications and improvements can be made thereto. Accordingly, such modifications or improvements may be made without departing from the spirit of the application and are intended to be within the scope of the application as claimed.
Claims (6)
1. The utility model provides a bearing frame cooling structure of aeroengine main bearing, its characterized in that has seted up helicla flute (4) on the bearing frame (1) inner wall of aeroengine main bearing, helicla flute (4) are along the circumference and the axial spiral extension of bearing frame (1), are simultaneously seted up on bearing frame (1) and are run through the oil feed passageway and the oil return passageway of bearing frame inner and outer wall, and oil feed pipe (2) are connected to oil feed passageway one end, and the other end is connected at the starting end of helicla flute (4), and oil return pipe (3) are connected to oil return passageway one end, and the other end is connected at the end of helicla flute (4), the outer wall interference fit of bearing frame (1) inner wall and bearing outer lane (6) of bearing (5), so that helicla flute (4) form lubricating oil cooling channel.
2. Bearing block cooling structure of an aeroengine main bearing according to claim 1, wherein the radius R of the spiral groove (4) is not more than L/15 and the pitch B is not less than L/5, wherein L refers to the effective assembly surface length of the bearing block (2) and the bearing outer ring (6).
3. Bearing housing cooling structure of an aeroengine main bearing according to claim 2, wherein the interference u of the inner wall of the bearing housing (1) with the outer wall of the bearing outer ring (6) is such that:
u≥α 1 ·D·T 1 -α 2 ·D·T 2 ；
wherein alpha is 1 And alpha 2 The linear expansion coefficients of the materials of the bearing seat (2) and the bearing outer ring (6), T 1 And T 2 The working temperatures of the bearing seat (2) and the bearing outer ring (6) are respectively shown, and D is the diameter of the bearing outer ring (6).
4. A bearing housing cooling arrangement for an aircraft engine main bearing according to claim 3, characterized in that the oil supply cooling flow Q of the spiral groove (4) is configured to:
5. bearing housing cooling structure for an aeroengine main bearing according to claim 1, wherein the oil inlet channel is screwed with the oil inlet tube (2) and the oil return channel is screwed with the oil return tube (3).
6. Bearing housing cooling structure for an aeroengine main bearing according to claim 1, wherein the end of the oil inlet pipe (2) is pressed into the oil inlet channel by an interference fit, and the end of the oil return pipe (3) is pressed into the oil return channel by an interference fit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310888635.9A CN116857288B (en) | 2023-07-19 | 2023-07-19 | Bearing seat cooling structure of main bearing of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310888635.9A CN116857288B (en) | 2023-07-19 | 2023-07-19 | Bearing seat cooling structure of main bearing of aero-engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116857288A true CN116857288A (en) | 2023-10-10 |
| CN116857288B CN116857288B (en) | 2024-07-05 |
Family
ID=88235751
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310888635.9A Active CN116857288B (en) | 2023-07-19 | 2023-07-19 | Bearing seat cooling structure of main bearing of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116857288B (en) |
Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2004104434A1 (en) * | 2003-05-20 | 2004-12-02 | Mtu Aero Engines Gmbh | Roller bearing for lubricated and cooled continuous operation at high speed |
| JP2008163983A (en) * | 2006-12-27 | 2008-07-17 | Ntn Corp | Bearing device |
| CN102678767A (en) * | 2011-12-24 | 2012-09-19 | 河南科技大学 | Radiating method for rolling bearing |
| US20120328226A1 (en) * | 2009-12-02 | 2012-12-27 | Schaeffler Technologies AG & Co. KG | Rolling bearing arrangement |
| CN106062394A (en) * | 2014-02-28 | 2016-10-26 | 日本精工株式会社 | Main shaft device |
| CN205806234U (en) * | 2016-06-21 | 2016-12-14 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of engine bearing lubricating and cooling |
| CN106438725A (en) * | 2016-08-31 | 2017-02-22 | 合肥华升泵阀股份有限公司 | Self-sucking type bearing lubricating device |
| CN106838010A (en) * | 2017-02-08 | 2017-06-13 | 中国航发沈阳发动机研究所 | The base bearing holding meanss component and aero-engine of a kind of aero-engine |
| DE102016223805A1 (en) * | 2016-11-30 | 2018-05-30 | Schaeffler Technologies AG & Co. KG | Use of the wheel bearing waste heat for the interior heating |
| CN210565832U (en) * | 2019-06-18 | 2020-05-19 | 河南澈蓝环保技术有限公司 | Cooling device for main bearing of machine tool |
| 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 |
| CN218760915U (en) * | 2022-11-14 | 2023-03-28 | 新昌县凯伦达轴承有限公司 | Flange type ball screw precision combined supporting bearing |
-
2023
- 2023-07-19 CN CN202310888635.9A patent/CN116857288B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2004104434A1 (en) * | 2003-05-20 | 2004-12-02 | Mtu Aero Engines Gmbh | Roller bearing for lubricated and cooled continuous operation at high speed |
| JP2008163983A (en) * | 2006-12-27 | 2008-07-17 | Ntn Corp | Bearing device |
| US20120328226A1 (en) * | 2009-12-02 | 2012-12-27 | Schaeffler Technologies AG & Co. KG | Rolling bearing arrangement |
| CN102678767A (en) * | 2011-12-24 | 2012-09-19 | 河南科技大学 | Radiating method for rolling bearing |
| CN106062394A (en) * | 2014-02-28 | 2016-10-26 | 日本精工株式会社 | Main shaft device |
| CN205806234U (en) * | 2016-06-21 | 2016-12-14 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of engine bearing lubricating and cooling |
| CN106438725A (en) * | 2016-08-31 | 2017-02-22 | 合肥华升泵阀股份有限公司 | Self-sucking type bearing lubricating device |
| DE102016223805A1 (en) * | 2016-11-30 | 2018-05-30 | Schaeffler Technologies AG & Co. KG | Use of the wheel bearing waste heat for the interior heating |
| CN106838010A (en) * | 2017-02-08 | 2017-06-13 | 中国航发沈阳发动机研究所 | The base bearing holding meanss component and aero-engine of a kind of aero-engine |
| CN210565832U (en) * | 2019-06-18 | 2020-05-19 | 河南澈蓝环保技术有限公司 | Cooling device for main bearing of machine tool |
| 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 |
| CN218760915U (en) * | 2022-11-14 | 2023-03-28 | 新昌县凯伦达轴承有限公司 | Flange type ball screw precision combined supporting bearing |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116857288B (en) | 2024-07-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106838010B (en) | A kind of the base bearing holding meanss component and aero-engine of aero-engine | |
| US10329952B2 (en) | Bearing assembly, in particular for a turbomachine, and turbomachine having such a bearing assembly | |
| US6884022B2 (en) | Diesel engine water pump with improved water seal | |
| US8210316B2 (en) | Oil scavenge system for a gas turbine engine | |
| CN109648372B (en) | Knife handle suitable for ultra-low temperature medium cooling and lubricating | |
| US6918746B2 (en) | Diesel engine water pump with thrust bearing preload | |
| CN116857288B (en) | Bearing seat cooling structure of main bearing of aero-engine | |
| US6929449B2 (en) | Diesel engine water pump with improved oil control | |
| CN108561435A (en) | A kind of combination split bearing of supporting rod rotor | |
| JP5983147B2 (en) | Turbocharger | |
| CN107524480B (en) | Turbocharger bearing body structure with integral ball bearing | |
| CN103939472A (en) | Sliding bearing of double-screw compressor | |
| CN113236425A (en) | Sealing structure of bearing cavity of aero-engine | |
| CN114508570A (en) | Lubricated and cooled ball screw device and working method | |
| US2744796A (en) | Fluid-cooled bearing | |
| CN207830412U (en) | Multi-plate wet clutch | |
| CN209800048U (en) | Lubricating oil way device | |
| CN220770109U (en) | Gear box lubricating oil connector | |
| CN207981886U (en) | A kind of plunger type coiling machine hot rolling reel of high coil amount | |
| CN114109606B (en) | Stepped oil thrower with curved surface at high-speed shaft end | |
| CN216278632U (en) | Water bearing applied to water pump | |
| CN109128303A (en) | A kind of ring-like mist of oil injection drill bushing of flow-changing low-temperature | |
| CN210660646U (en) | Semi-closed centrifugal compressor | |
| CN220732512U (en) | Bearing lubricating structure of oil-cooled motor | |
| CN215215686U (en) | Lubricating and oiling device for axial flow fan |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |