CN109555846B - Cooling and lubricating structure of central cone transmission mechanism of aircraft engine - Google Patents
Cooling and lubricating structure of central cone transmission mechanism of aircraft engine Download PDFInfo
- Publication number
- CN109555846B CN109555846B CN201811372773.7A CN201811372773A CN109555846B CN 109555846 B CN109555846 B CN 109555846B CN 201811372773 A CN201811372773 A CN 201811372773A CN 109555846 B CN109555846 B CN 109555846B
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- China
- Prior art keywords
- lubricating oil
- bearing
- oil guide
- guide hole
- bevel gear
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- 230000005540 biological transmission Effects 0.000 title claims abstract description 33
- 238000001816 cooling Methods 0.000 title claims abstract description 22
- 230000001050 lubricating effect Effects 0.000 title claims abstract description 17
- 239000010687 lubricating oil Substances 0.000 claims abstract description 70
- 238000005096 rolling process Methods 0.000 claims abstract description 6
- 238000005507 spraying Methods 0.000 claims abstract description 3
- 238000005461 lubrication Methods 0.000 claims description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
Images
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
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/04—Features relating to lubrication or cooling or heating
- F16H57/0456—Lubrication by injection; Injection nozzles or tubes therefor
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- 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
- F16H—GEARING
- F16H57/00—General details of gearing
- F16H57/04—Features relating to lubrication or cooling or heating
- F16H57/0412—Cooling or heating; Control of temperature
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Shafts, Cranks, Connecting Bars, And Related Bearings (AREA)
- General Details Of Gearings (AREA)
Abstract
A cooling and lubricating structure of a central cone transmission mechanism of an aircraft engine comprises a driven bevel gear, an accessory case transmission rod, a ball bearing, a rolling rod bearing, a shell, a flow guide distance sleeve and a nozzle; the guide distance sleeve is fixedly sleeved at the sleeve end of the driven bevel gear, the guide distance sleeve is positioned between the ball bearing and the roller bearing, and the axial distance between the ball bearing and the roller bearing is limited by the guide distance sleeve; the nozzle is arranged on the shell, and the lubricating oil spraying direction of the nozzle faces the ball bearing retainer; a lubricating oil guide groove is formed in the guide distance sleeve, a first lubricating oil guide hole is formed in the groove wall on the inner side of the lubricating oil guide groove, a second lubricating oil guide hole is formed in the bottom of the lubricating oil guide groove, and an orifice at the outer end of the second lubricating oil guide hole is communicated with the roller bearing; the width of the groove opening of the lubricating oil guide groove is larger than the distance between the inner ring and the outer ring of the ball bearing; and a third lubricating oil flow guide hole is formed in the sleeve end barrel body of the driven bevel gear, the outer end orifice of the third lubricating oil flow guide hole is communicated with the first lubricating oil flow guide hole, and the inner end orifice of the third lubricating oil flow guide hole is communicated with the spline.
Description
Technical Field
The invention belongs to the technical field of manufacturing of parts of an aero-engine, and particularly relates to a cooling and lubricating structure of a central cone transmission mechanism of the aero-engine.
Background
In the central cone transmission mechanism of the aircraft engine, each bearing mainly bears radial and axial loads, and the performance of a transmission system of the aircraft engine can be directly influenced by the lubricating and cooling effects of each bearing.
However, the internal space of the shell of the central cone transmission mechanism of the aircraft engine is very limited, which brings great inconvenience to the nozzle design, and due to the limitation of the space structure, the designed nozzle often cannot directly spray lubricating oil onto the bearing, thereby causing unsatisfactory cooling and lubricating effects.
In addition, for a driven bevel gear in the center cone transmission mechanism of the aircraft engine, the driven bevel gear and a transmission rod of an engine accessory casing are in spline fit to transmit working torque. However, the spline is not provided with a specific cooling measure at present, so that heat generated when the spline transmits working torque cannot be dissipated in time, and certain damage is caused to the spline.
For the cooling and lubricating structure of the existing aircraft engine central cone transmission mechanism, the bearing on the driven bevel gear needs to be cooled and lubricated through two nozzles, and because the two nozzles are required to be arranged in the shell of the central cone transmission mechanism, the processing difficulty of the shell is increased, and the flow and flow direction requirements of the nozzles are difficult to guarantee.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a cooling and lubricating structure of a central cone transmission mechanism of an aircraft engine, which can meet the cooling and lubricating requirements of a bearing only by one nozzle, not only simplifies the design and processing difficulty of a shell of the central cone transmission mechanism, but also can cool a spline between a driven bevel gear and an engine accessory case transmission rod.
In order to achieve the purpose, the invention adopts the following technical scheme: a cooling and lubricating structure of a central cone transmission mechanism of an aircraft engine comprises a driven bevel gear, an accessory case transmission rod, a ball bearing, a rolling rod bearing, a shell, a flow guide distance sleeve and a nozzle; the driven bevel gear is fixedly sleeved on the accessory case transmission rod, and the working torque is transmitted between the driven bevel gear and the accessory case transmission rod through a spline; the ball bearing is fixedly sleeved at the sleeve end of the driven bevel gear through a bearing inner ring, and a bearing outer ring of the ball bearing is fixedly connected with the shell; the roller bearing is fixedly sleeved at the sleeve end of the driven bevel gear through a bearing inner ring, and a bearing outer ring of the roller bearing is fixedly connected with the shell; the guide distance sleeve is fixedly sleeved at the sleeve end of the driven bevel gear, the guide distance sleeve is positioned between the ball bearing and the roller bearing, and the axial distance between the ball bearing and the roller bearing is limited by the guide distance sleeve; the nozzle is arranged on the shell, and the lubricating oil spraying direction of the nozzle faces to a bearing retainer of the ball bearing.
And a lubricating oil guide groove is formed in the guide distance sleeve, a first lubricating oil guide hole is formed in the inner side groove wall of the lubricating oil guide groove, a second lubricating oil guide hole is formed in the bottom of the lubricating oil guide groove, and an outer end orifice of the second lubricating oil guide hole is communicated with the rolling rod bearing.
The width of the groove opening of the lubricating oil guide groove is larger than the distance between the inner ring and the outer ring of the ball bearing.
And a sleeve end cylinder body of the driven bevel gear is provided with a third lubricating oil guide hole, an outer end orifice of the third lubricating oil guide hole is communicated with the first lubricating oil guide hole, and an inner end orifice of the third lubricating oil guide hole is communicated with the spline.
The invention has the beneficial effects that:
the cooling and lubricating structure of the aero-engine central cone transmission mechanism can meet the cooling and lubricating requirements of the bearing only by one nozzle, not only simplifies the design and processing difficulty of the central cone transmission mechanism shell, but also can cool the spline between the driven bevel gear and the engine accessory case transmission rod.
Drawings
FIG. 1 is a schematic view of a cooling and lubricating structure of a central cone transmission mechanism of an aircraft engine according to the invention;
FIG. 2 is a schematic structural view of a guide distance sleeve of the present invention;
in the figure, 1-driven bevel gear, 2-accessory case transmission rod, 3-ball bearing, 4-rolling rod bearing, 5-shell, 6-guide distance sleeve, 7-nozzle, 8-spline, 9-lubricating oil guide groove, 10-first lubricating oil guide hole, 11-second lubricating oil guide hole, 12-third lubricating oil guide hole.
Detailed Description
The invention is described in further detail below with reference to the figures and the specific embodiments.
As shown in fig. 1 and 2, a cooling and lubricating structure of a central cone transmission mechanism of an aircraft engine comprises a driven bevel gear 1, an accessory case transmission rod 2, a ball bearing 3, a roller bearing 4, a shell 5, a flow guide distance sleeve 6 and a nozzle 7; the driven bevel gear 1 is fixedly sleeved on the accessory case transmission rod 2, and working torque is transmitted between the driven bevel gear 1 and the accessory case transmission rod 2 through a spline 8; the ball bearing 3 is fixedly sleeved at the sleeve end of the driven bevel gear 1 through a bearing inner ring, and a bearing outer ring of the ball bearing 3 is fixedly connected with the shell 5; the roller bearing 4 is fixedly sleeved at the sleeve end of the driven bevel gear 1 through a bearing inner ring, and a bearing outer ring of the roller bearing 4 is fixedly connected with the shell 5; the guide distance sleeve 6 is fixedly sleeved at the sleeve end of the driven bevel gear 1, the guide distance sleeve 6 is positioned between the ball bearing 3 and the roller bearing 4, and the axial distance between the ball bearing 3 and the roller bearing 4 is limited by the guide distance sleeve 6; the nozzle 7 is provided on the housing 5, and the oil jetting direction of the nozzle 7 is directed toward the bearing retainer of the ball bearing 3.
The guide distance sleeve 6 is provided with a lubricating oil guide groove 9, the inner side groove wall of the lubricating oil guide groove 9 is provided with a first lubricating oil guide hole 10, the bottom of the lubricating oil guide groove 9 is provided with a second lubricating oil guide hole 11, and the outer end orifice of the second lubricating oil guide hole 11 is communicated with the roller bearing 4.
The width of the notch of the lubricating oil diversion groove 9 is larger than the distance between the inner ring and the outer ring of the ball bearing 3.
A third lubricating oil guide hole 12 is formed in the sleeve end cylinder of the driven bevel gear 1, an outer end orifice of the third lubricating oil guide hole 12 is communicated with the first lubricating oil guide hole 10, and an inner end orifice of the third lubricating oil guide hole 12 leads to the spline 8.
The following describes one application of the present invention with reference to the accompanying drawings:
the lubricating oil is firstly sprayed out from the nozzle 7, the sprayed lubricating oil directly enters the ball bearing 3 to provide cooling and lubrication for the ball bearing 3, and in the process of cooling or lubricating the ball bearing 3, the redundant lubricating oil can further flow into the lubricating oil guide groove 9 of the guide distance sleeve 6 through the bearing retainer.
The lubricating oil collected in the lubricating oil guide groove 9 is more and more, the lubricating oil in the lubricating oil guide groove 9 firstly flows out through the second lubricating oil guide hole 11, and the flowing lubricating oil directly enters the roller bearing 4 to provide cooling and lubrication for the roller bearing 4.
When the liquid level in the lubricating oil guiding groove 9 exceeds the height of the first lubricating oil guiding hole 10, the lubricating oil in the lubricating oil guiding groove 9 enters the third lubricating oil guiding hole 12 through the first lubricating oil guiding hole 10 and then flows out from the inner end orifice of the third lubricating oil guiding hole 12, and the flowing lubricating oil directly flows to the spline 8 to provide cooling for the spline 8.
The embodiments are not intended to limit the scope of the present invention, and all equivalent implementations or modifications without departing from the scope of the present invention are intended to be included in the scope of the present invention.
Claims (3)
1. The utility model provides an aeroengine central cone drive mechanism's cooling lubrication structure which characterized in that: the device comprises a driven bevel gear, an accessory casing transmission rod, a ball bearing, a rolling rod bearing, a shell, a flow guide distance sleeve and a nozzle; the driven bevel gear is fixedly sleeved on the accessory case transmission rod, and the working torque is transmitted between the driven bevel gear and the accessory case transmission rod through a spline; the ball bearing is fixedly sleeved at the sleeve end of the driven bevel gear through a bearing inner ring, and a bearing outer ring of the ball bearing is fixedly connected with the shell; the roller bearing is fixedly sleeved at the sleeve end of the driven bevel gear through a bearing inner ring, and a bearing outer ring of the roller bearing is fixedly connected with the shell; the guide distance sleeve is fixedly sleeved at the sleeve end of the driven bevel gear, the guide distance sleeve is positioned between the ball bearing and the roller bearing, and the axial distance between the ball bearing and the roller bearing is limited by the guide distance sleeve; the nozzles are arranged on the shell, the number of the nozzles is one, and the lubricating oil spraying direction of the nozzles faces to a bearing retainer of the ball bearing; and a lubricating oil guide groove is formed in the guide distance sleeve, a first lubricating oil guide hole is formed in the inner side groove wall of the lubricating oil guide groove, a second lubricating oil guide hole is formed in the bottom of the lubricating oil guide groove, and an outer end orifice of the second lubricating oil guide hole is communicated with the rolling rod bearing.
2. The cooling and lubricating structure of the central cone transmission mechanism of the aircraft engine as claimed in claim 1, wherein: the width of the groove opening of the lubricating oil guide groove is larger than the distance between the inner ring and the outer ring of the ball bearing.
3. The cooling and lubricating structure of the central cone transmission mechanism of the aircraft engine as claimed in claim 1, wherein: and a sleeve end cylinder body of the driven bevel gear is provided with a third lubricating oil guide hole, an outer end orifice of the third lubricating oil guide hole is communicated with the first lubricating oil guide hole, and an inner end orifice of the third lubricating oil guide hole is communicated with the spline.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811372773.7A CN109555846B (en) | 2018-11-19 | 2018-11-19 | Cooling and lubricating structure of central cone transmission mechanism of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811372773.7A CN109555846B (en) | 2018-11-19 | 2018-11-19 | Cooling and lubricating structure of central cone transmission mechanism of aircraft engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109555846A CN109555846A (en) | 2019-04-02 |
| CN109555846B true CN109555846B (en) | 2021-08-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811372773.7A Active CN109555846B (en) | 2018-11-19 | 2018-11-19 | Cooling and lubricating structure of central cone transmission mechanism of aircraft engine |
Country Status (1)
| Country | Link |
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| CN (1) | CN109555846B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112049923B (en) * | 2020-09-07 | 2022-11-25 | 中国航发贵阳发动机设计研究所 | Lubricating structure with lubricating oil distribution function |
| CN112049924B (en) * | 2020-09-07 | 2022-09-02 | 中国航发贵阳发动机设计研究所 | Reuse lubricating oil lubricating structure |
| CN113513575B (en) * | 2021-04-29 | 2023-12-19 | 中国航发沈阳发动机研究所 | Spline connection lubricating structure |
| CN114718991A (en) * | 2022-03-25 | 2022-07-08 | 中国航发哈尔滨东安发动机有限公司 | Rotating speed and steering conversion device |
| CN115899230B (en) * | 2023-02-01 | 2025-06-03 | 中国航发湖南动力机械研究所 | Lubrication structure in engine transmission system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6332455Y2 (en) * | 1983-12-23 | 1988-08-30 | ||
| EP2194296A2 (en) * | 2008-12-05 | 2010-06-09 | Kawasaki Jukogyo Kabushiki Kaisha | Lubricating system for gear train |
| CN203614723U (en) * | 2013-12-12 | 2014-05-28 | 中航商用航空发动机有限责任公司 | Oil distribution device and gear shaft provided with oil distribution device |
| CN206439380U (en) * | 2016-12-12 | 2017-08-25 | 中国燃气涡轮研究院 | Oil supply structure under a kind of high speed shaft carrier ring |
| CN108087533A (en) * | 2017-11-29 | 2018-05-29 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of gas turbine central cone transmission device flow deflector structure |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5119905A (en) * | 1991-10-28 | 1992-06-09 | General Motors Corporation | Accessory drive spline lubrication system for a turbine engine reduction gear box |
| US8997937B2 (en) * | 2012-07-25 | 2015-04-07 | Bell Helicopter Textron Inc. | Direct drive rotation device for passively moving fluid |
-
2018
- 2018-11-19 CN CN201811372773.7A patent/CN109555846B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6332455Y2 (en) * | 1983-12-23 | 1988-08-30 | ||
| EP2194296A2 (en) * | 2008-12-05 | 2010-06-09 | Kawasaki Jukogyo Kabushiki Kaisha | Lubricating system for gear train |
| CN203614723U (en) * | 2013-12-12 | 2014-05-28 | 中航商用航空发动机有限责任公司 | Oil distribution device and gear shaft provided with oil distribution device |
| CN206439380U (en) * | 2016-12-12 | 2017-08-25 | 中国燃气涡轮研究院 | Oil supply structure under a kind of high speed shaft carrier ring |
| CN108087533A (en) * | 2017-11-29 | 2018-05-29 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of gas turbine central cone transmission device flow deflector structure |
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| Publication number | Publication date |
|---|---|
| CN109555846A (en) | 2019-04-02 |
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