CN113964999A - Oil cooling high-rotation-speed aviation motor bearing cooling structure - Google Patents
Oil cooling high-rotation-speed aviation motor bearing cooling structure Download PDFInfo
- Publication number
- CN113964999A CN113964999A CN202111284279.7A CN202111284279A CN113964999A CN 113964999 A CN113964999 A CN 113964999A CN 202111284279 A CN202111284279 A CN 202111284279A CN 113964999 A CN113964999 A CN 113964999A
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- China
- Prior art keywords
- oil
- bearing
- hollow shaft
- cooling
- shell
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- 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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- 238000001816 cooling Methods 0.000 title claims abstract description 43
- 239000003921 oil Substances 0.000 claims abstract description 136
- 239000007921 spray Substances 0.000 claims abstract description 16
- 239000010687 lubricating oil Substances 0.000 claims abstract description 9
- 230000017525 heat dissipation Effects 0.000 claims abstract description 4
- 238000004064 recycling Methods 0.000 claims abstract description 4
- 230000005540 biological transmission Effects 0.000 claims description 7
- 238000005507 spraying Methods 0.000 claims description 5
- 238000007789 sealing Methods 0.000 claims description 2
- 239000012809 cooling fluid Substances 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 5
- 238000002347 injection Methods 0.000 abstract description 3
- 239000007924 injection Substances 0.000 abstract description 3
- 238000009434 installation Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K5/00—Casings; Enclosures; Supports
- H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
- H02K5/16—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields
- H02K5/173—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields using bearings with rolling contact, e.g. ball bearings
- H02K5/1732—Means for supporting bearings, e.g. insulating supports or means for fitting bearings in the bearing-shields using bearings with rolling contact, e.g. ball bearings radially supporting the rotary shaft at both ends of the rotor
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K9/00—Arrangements for cooling or ventilating
- H02K9/19—Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
- H02K9/193—Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil with provision for replenishing the cooling medium; with means for preventing leakage of the cooling medium
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- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Mounting Of Bearings Or Others (AREA)
Abstract
The invention provides an oil-cooled high-rotation-speed aviation motor bearing cooling structure which comprises a shell, an end cover, a hollow shaft and an oil nozzle, wherein the shell is provided with a plurality of oil holes; the bearing is an angular contact ball bearing, an oil inlet groove and an oil inlet are formed in the inner ring of the bearing, and the oil injection hole in the hollow shaft is aligned with the oil inlet of the bearing. Cooling lubricating oil enters the end cover from the external oil way, then enters the hollow shaft through the oil nozzle, is sprayed out from the oil spray hole of the hollow shaft to carry out oil spray cooling on the ball of the bearing, the falling lubricating oil falls into the oil tank through the oil return hole, and oil in the oil tank is pumped out to the external heat dissipation oil way for recycling by the oil return pump arranged on the end cover. After adopting this bearing cooling structure, can need not to design special oil circuit in motor casing and cool off the bearing, simple structure and cooling effect are good.
Description
Technical Field
The invention belongs to the technical field of cooling of aviation motors, and particularly relates to an oil-cooled high-rotation-speed aviation motor bearing cooling structure.
Background
The bearing at the transmission end of the high-power aviation oil-cooled high-speed motor generates a great amount of heat and needs to be cooled, and the required cooling oil amount is large, so that the bearing of the high-power aviation oil-cooled high-speed motor is generally cooled by an oil inlet mode from the outer ring of the bearing, so that when a motor shell is designed, a special oil way needs to be arranged to guide lubricating oil for cooling the motor to the bearing, the thickness of the motor shell is large, and the structure weight is increased.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides an oil-cooled high-rotation-speed aviation motor bearing cooling structure, which can directly carry out oil injection cooling on an inner ring and balls of a motor bearing without arranging an oil circuit on a motor shell, meets the requirement of bearing cooling capacity through the design of the oil circuit, improves the cooling effect of the motor bearing and reduces the complexity of a motor shell.
The technical scheme of the invention is as follows:
the cooling structure of the oil-cooled high-rotation-speed aviation motor bearing comprises a shell, an end cover, a hollow shaft and an oil nozzle;
the shell and the end cover are axially, hermetically, fixedly and butted to form an aviation oil-cooled high-rotation-speed motor shell, and an oil supply oil way for cooling a motor bearing is not arranged on the shell;
the hollow shaft is arranged in the motor shell and is supported by a front group of bearings and a rear group of bearings; an oil tank is formed between the hollow shaft and the motor shell; oil return cavities are arranged between the front bearing mounting position and the shell, and between the rear bearing mounting position and the end cover;
the transmission end of the hollow shaft is matched with the outer end of the shell through a dynamic sealing component; the hollow structure in the hollow shaft is divided into two parts, one part is a mounting blind hole for connecting the transmission end with the external structure, the other part is an oil supply part, and the two parts are separated and are not communicated with each other;
the oil supply part is divided into an oil cavity and a mounting hole for mounting an oil nozzle, oil spray holes pointing to an oil inlet of the bearing inner ring are formed in the front end wall and the rear end wall of the oil cavity, and an oil return hole for communicating the oil return cavity with the oil tank is formed in the lower portion of the motor shell;
cooling lubricating oil enters the end cover from the external oil path, then enters an oil cavity of the hollow shaft through the oil nozzle, is sprayed out from an oil spraying hole of the hollow shaft to carry out oil spraying and cooling on balls of the bearing, the falling lubricating oil falls into an oil tank through an oil return hole, and oil in the oil tank is pumped out to the external heat dissipation oil path for recycling by an oil return pump arranged on the end cover.
Furthermore, the bearing is an angular contact ball bearing, the outer ring of the bearing is matched with the motor shell through a bearing bush, and the inner ring of the bearing is provided with an oil inlet groove and an oil inlet; the oil spray hole points to the oil inlet of the bearing inner ring.
Further, for meeting the requirement of bearing cooling capacity, the aperture of the oil spray hole, the included angle between the axis of the oil spray hole and the axis of the motor, the volume of an oil cavity in the hollow shaft and the pressure of oil inlet through the oil spray hole are subjected to matching calculation, so that the cooling oil flow sprayed out through the oil spray hole can meet the requirement of the bearing cooling capacity.
Advantageous effects
After the bearing cooling structure provided by the invention is adopted, a special oil way is not required to be designed in the motor shell to cool the bearing, the structure is simple, the weight and the design difficulty of the shell are reduced, and the cooling effect is good.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1: the invention has a structure schematic diagram.
The oil pump comprises a dynamic seal assembly 1, a bearing bush 2, a bearing 3, a hollow shaft 4, a shell 5, an end cover 6, an oil nozzle 7, an oil injection hole 8, an oil return hole 9 and an oil tank 10.
Detailed Description
The following detailed description of embodiments of the invention is intended to be illustrative, and not to be construed as limiting the invention.
As shown in fig. 1, the aviation oil-cooled high-speed motor bearing cooling structure proposed in this embodiment is composed of a housing 5, an end cover 6, a hollow shaft 4, and an oil nozzle 7.
The shell 5 and the end cover 6 are axially, hermetically, fixedly and butted to form an aviation oil-cooling high-rotating-speed motor shell, and an oil supply oil way for cooling a motor bearing is not arranged on the shell 5.
The hollow shaft 4 is arranged in the motor shell and is supported by a front group of bearings 3 and a rear group of bearings 3; an oil tank 10 is formed between the hollow shaft 4 and the motor shell; the bearing 3 is an angular contact ball bearing, an outer ring of the bearing 3 is matched with a motor shell through a bearing bush 2, an oil inlet groove and an oil inlet are formed in an inner ring of the bearing 3, and oil return cavities are formed between the front bearing installation position and the shell 5 and between the rear bearing installation position and the end cover 6.
The transmission end of the hollow shaft 4 is matched with the outer end of the shell 5 through a dynamic seal assembly 1; the hollow structure in the hollow shaft 4 is divided into two parts, one part is a mounting blind hole for connecting the transmission end with an external structure, the other part is an oil supply part, and the two parts are separated and not communicated with each other. The oil supply part is divided into an oil cavity and a mounting hole for mounting an oil nozzle 7, oil spray holes 8 pointing to an oil inlet of an inner ring of the bearing 3 are formed in the front end wall and the rear end wall of the oil cavity, and in order to meet the requirement of cooling capacity of the bearing, matching calculation is further carried out on the aperture of the oil spray holes, the included angle between the axis of the oil spray holes and the axis of a motor, the volume of the oil cavity in the hollow shaft and the pressure of oil inlet through the oil spray holes, so that the flow of cooling oil sprayed through the oil spray holes can meet the requirement of the cooling capacity of the bearing.
An oil return hole 9 communicating the oil return cavity and an oil tank 10 is formed in the lower portion of the motor shell.
During actual operation, cooling lubricating oil enters the end cover 6 from an external oil path, then enters an oil cavity of the hollow shaft 4 through the oil nozzle 7, is sprayed out from the oil spraying hole 8 of the hollow shaft 4 to spray oil and cool the balls of the bearing 3, the falling lubricating oil falls into the oil tank 10 through the oil return hole 9, and oil in the oil tank is pumped out to the external heat dissipation oil path for recycling through the oil return pump installed on the end cover 6.
After adopting this bearing cooling structure, can need not to design special oil circuit in motor casing and cool off the bearing, simple structure and cooling effect are good.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (3)
1. The utility model provides a cold high rotational speed aeronautical motor bearing cooling structure of oil which characterized in that: the device consists of a shell, an end cover, a hollow shaft and an oil nozzle;
the shell and the end cover are axially, hermetically, fixedly and butted to form an aviation oil-cooled high-rotation-speed motor shell, and an oil supply oil way for cooling a motor bearing is not arranged on the shell;
the hollow shaft is arranged in the motor shell and is supported by a front group of bearings and a rear group of bearings; an oil tank is formed between the hollow shaft and the motor shell; oil return cavities are arranged between the front bearing mounting position and the shell, and between the rear bearing mounting position and the end cover;
the transmission end of the hollow shaft is matched with the outer end of the shell through a dynamic sealing component; the hollow structure in the hollow shaft is divided into two parts, one part is a mounting blind hole for connecting the transmission end with the external structure, the other part is an oil supply part, and the two parts are separated and are not communicated with each other;
the oil supply part is divided into an oil cavity and a mounting hole for mounting an oil nozzle, oil spray holes pointing to an oil inlet of the bearing inner ring are formed in the front end wall and the rear end wall of the oil cavity, and an oil return hole for communicating the oil return cavity with the oil tank is formed in the lower portion of the motor shell;
cooling lubricating oil enters the end cover from the external oil path, then enters an oil cavity of the hollow shaft through the oil nozzle, is sprayed out from an oil spraying hole of the hollow shaft to carry out oil spraying and cooling on balls of the bearing, the falling lubricating oil falls into an oil tank through an oil return hole, and oil in the oil tank is pumped out to the external heat dissipation oil path for recycling by an oil return pump arranged on the end cover.
2. The oil-cooled high-speed aero-motor bearing cooling structure as claimed in claim 1, wherein: the bearing is an angular contact ball bearing, the outer ring of the bearing is matched with the motor shell through a bearing bush, and the inner ring of the bearing is provided with an oil inlet groove and an oil inlet; the oil spray hole points to the oil inlet of the bearing inner ring.
3. The oil-cooled high-speed aero-motor bearing cooling structure as claimed in claim 1, wherein: for satisfying the bearing cooling capacity demand, carry out the matching calculation to the aperture of nozzle opening, nozzle opening axis and motor axis contained angle, hollow shaft inner oil pocket volume, through the pressure of nozzle opening oil feed for can satisfy the bearing cooling capacity demand through nozzle opening spun cooling fluid flow.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111284279.7A CN113964999A (en) | 2021-11-01 | 2021-11-01 | Oil cooling high-rotation-speed aviation motor bearing cooling structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111284279.7A CN113964999A (en) | 2021-11-01 | 2021-11-01 | Oil cooling high-rotation-speed aviation motor bearing cooling structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113964999A true CN113964999A (en) | 2022-01-21 |
Family
ID=79468675
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111284279.7A Pending CN113964999A (en) | 2021-11-01 | 2021-11-01 | Oil cooling high-rotation-speed aviation motor bearing cooling structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113964999A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117469194A (en) * | 2023-12-28 | 2024-01-30 | 诺顿风机(潍坊)有限公司 | Novel intelligent monitoring's special bearing box of axial fan |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2458236C1 (en) * | 2011-04-26 | 2012-08-10 | Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") | Method of operating aircraft gas turbine engine |
| CN203416114U (en) * | 2013-08-15 | 2014-01-29 | 浙江凯利达防爆机电有限公司 | Motor used for oil pump |
| CN204205841U (en) * | 2014-11-17 | 2015-03-11 | 陕西航空电气有限责任公司 | A kind of cooling structure of aerogenerator |
| CN105162286A (en) * | 2015-10-14 | 2015-12-16 | 沈阳航天新光集团有限公司 | Shaft hole cooling and lubricating system |
| CN109327113A (en) * | 2018-10-29 | 2019-02-12 | 深圳市泉胜新技术开发有限公司 | A kind of oil-cooled motor cooling device |
| CN210123921U (en) * | 2019-06-28 | 2020-03-03 | 长城汽车股份有限公司 | Electric machine |
| CN113422474A (en) * | 2021-05-14 | 2021-09-21 | 珠海格力电器股份有限公司 | Bearing cooling structure, driving motor and new energy automobile |
| CN113507187A (en) * | 2021-07-09 | 2021-10-15 | 南京航空航天大学 | Efficient aeroengine oil cooling system |
-
2021
- 2021-11-01 CN CN202111284279.7A patent/CN113964999A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2458236C1 (en) * | 2011-04-26 | 2012-08-10 | Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") | Method of operating aircraft gas turbine engine |
| CN203416114U (en) * | 2013-08-15 | 2014-01-29 | 浙江凯利达防爆机电有限公司 | Motor used for oil pump |
| CN204205841U (en) * | 2014-11-17 | 2015-03-11 | 陕西航空电气有限责任公司 | A kind of cooling structure of aerogenerator |
| CN105162286A (en) * | 2015-10-14 | 2015-12-16 | 沈阳航天新光集团有限公司 | Shaft hole cooling and lubricating system |
| CN109327113A (en) * | 2018-10-29 | 2019-02-12 | 深圳市泉胜新技术开发有限公司 | A kind of oil-cooled motor cooling device |
| CN210123921U (en) * | 2019-06-28 | 2020-03-03 | 长城汽车股份有限公司 | Electric machine |
| CN113422474A (en) * | 2021-05-14 | 2021-09-21 | 珠海格力电器股份有限公司 | Bearing cooling structure, driving motor and new energy automobile |
| CN113507187A (en) * | 2021-07-09 | 2021-10-15 | 南京航空航天大学 | Efficient aeroengine oil cooling system |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117469194A (en) * | 2023-12-28 | 2024-01-30 | 诺顿风机(潍坊)有限公司 | Novel intelligent monitoring's special bearing box of axial fan |
| CN117469194B (en) * | 2023-12-28 | 2024-03-08 | 诺顿风机(潍坊)有限公司 | Bearing box special for intelligent monitoring axial flow fan |
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