CN114857181A - Lubricating structure of large-ratio power spline for aero-engine transmission device - Google Patents
Lubricating structure of large-ratio power spline for aero-engine transmission device Download PDFInfo
- Publication number
- CN114857181A CN114857181A CN202210520845.8A CN202210520845A CN114857181A CN 114857181 A CN114857181 A CN 114857181A CN 202210520845 A CN202210520845 A CN 202210520845A CN 114857181 A CN114857181 A CN 114857181A
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- Prior art keywords
- oil
- spline
- dam
- rubber
- lubricating
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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
Links
- 230000005540 biological transmission Effects 0.000 title claims abstract description 28
- 230000001050 lubricating effect Effects 0.000 title claims abstract description 23
- 239000003921 oil Substances 0.000 claims abstract description 69
- 229920001971 elastomer Polymers 0.000 claims abstract description 50
- 238000005461 lubrication Methods 0.000 claims abstract description 23
- 239000010687 lubricating oil Substances 0.000 claims abstract description 18
- 230000000903 blocking effect Effects 0.000 claims abstract description 10
- 229920002449 FKM Polymers 0.000 claims description 2
- 230000007704 transition Effects 0.000 claims description 2
- 230000008676 import Effects 0.000 claims 1
- 238000002347 injection Methods 0.000 abstract description 9
- 239000007924 injection Substances 0.000 abstract description 9
- 238000007599 discharging Methods 0.000 abstract description 5
- 230000007547 defect Effects 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 2
- 229920001973 fluoroelastomer Polymers 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
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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
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D3/00—Yielding couplings, i.e. with means permitting movement between the connected parts during the drive
- F16D3/02—Yielding couplings, i.e. with means permitting movement between the connected parts during the drive adapted to specific functions
- F16D3/06—Yielding couplings, i.e. with means permitting movement between the connected parts during the drive adapted to specific functions specially adapted to allow axial displacement
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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
- F16H57/045—Lubricant storage reservoirs, e.g. reservoirs in addition to a gear sump for collecting lubricant in the upper part of a gear case
- F16H57/0454—Sealings between different partitions of a gearing or to a reservoir
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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
- F16H57/0456—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
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
-
- 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
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
- F16J15/3268—Mounting of sealing rings
-
- 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
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
- F16J15/3284—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings characterised by their structure; Selection of materials
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Details Of Gearings (AREA)
Abstract
The invention provides a lubricating structure of a large-specific-power spline for an aircraft engine transmission device, which comprises an inner spline shaft and an outer spline shaft which are arranged in a matched mode, wherein a dovetail groove is formed in one end, close to a lubricating oil inlet, of the inner spline shaft, an oil discharge hole for discharging lubricating oil is formed in the other end of the inner spline shaft, a rubber oil blocking dam for blocking oil is arranged in the dovetail groove, and the inner diameter of the rubber oil blocking dam is smaller than the small diameter of the outer spline. The lubricating structure has the advantages that the oil supply injection point is close to the spline, and the defect that the lubricating effect is influenced by the long injection distance of the existing structure is overcome; the oil supply and the oil return are on different sides, so that a lubricating flow path is smooth, and chip removal is not influenced; the other side in the hollow shaft can be designed into a closed structure and then other structures are installed, and spline lubrication is not affected.
Description
Technical Field
The invention belongs to the technical field of transmission devices in gas turbine engines, and particularly relates to a lubricating structure of a large-ratio power spline for an aircraft engine transmission device.
Background
The spline torque transmission generates extrusion stress on the tooth surface, the spline is meshed with the deflection to generate relative slip, and the extrusion stress is multiplied by the relative slip speed to obtain the specific work of the spline. The high-performance aircraft engine adopts a combined pump as a driving pump, the power of a single pump is high, the rotating speed is high, the specific work of a connecting spline is high, active oil supply is needed to lubricate the connecting spline so as to solve the problem of spline abrasion caused by high-speed heavy load, and the connecting spline is difficult to actively supply oil for lubrication due to compact space and assembly.
The existing spline oil supply lubrication structure is shown in fig. 5, an oil path is arranged on a transmission shell, a spline is sprayed for lubrication, sprayed lubricating oil passes through one end of a transmission hollow shaft, reaches the vicinity of a spline meshing part from the inside of the hollow shaft, and reaches a meshing tooth surface under the action of centrifugal force, a spline relief groove and a convex shoulder are arranged in the hollow shaft, the lubricating oil is collected through the spline relief groove, and the convex shoulder forms an oil dam; and a rubber ring is arranged on the shaft at the other end of the spline to isolate fuel oil from being mixed with lubricating oil. However, this structure has the following problems: 1) due to other limiting conditions, the lubricating oil injection outlet is far away from the spline meshing part, and the lubricating effect of the spline is influenced; 2) the side of the hollow shaft inside, which is close to the oil injection, must be open to provide a passage for the oil injection, and if the side must be closed due to other functional requirements, the structure cannot be used; 3) oil supply and oil return for spline lubrication are on the same side, and therefore abrasive dust discharge is affected.
Disclosure of Invention
In order to solve the above problems, an object of the present invention is to provide a structure for lubricating under a ring with a rubber dam, so as to overcome the problems that the lubrication effect is affected by the unavoidable injection distance, the chip removal is affected by the oil supply and oil return on the same side, and the side of the hollow shaft inside near the oil injection must be open.
In order to achieve the above object, the present invention provides the following technical solution, and provides a lubrication structure for a large specific power spline of an aircraft engine transmission device, where the lubrication structure includes an internal spline shaft and an external spline shaft that are cooperatively arranged, one end of the internal spline shaft near a lubricating oil inlet is provided with a dovetail groove, the other end is provided with an oil discharge hole for discharging lubricating oil, a rubber oil dam for stopping oil is arranged in the dovetail groove, and an inner diameter of the rubber oil dam is smaller than a small diameter of the external spline.
The lubricating structure for the large-specific-power spline of the aircraft engine transmission device is also characterized in that the dovetail groove is 2-4mm deep; the section taper angle is 18-22 degrees; the width of the groove opening is 2-4 mm.
The lubricating structure for the large-specific-power spline of the aircraft engine transmission device is also technically characterized in that the rubber oil dam is made of fluororubber.
The lubricating structure of the large-ratio power spline for the transmission device of the aircraft engine is further characterized in that the upper part 41 of the rubber oil dam for assembling with the dovetail groove is rectangular, and the lower part 42 for blocking oil is provided with an approximate V-shaped section.
The lubricating structure of the large-specific-power spline for the transmission device of the aero-engine, provided by the invention, is also technically characterized in that the upper part and the lower part of the transition joint 43 of the rubber oil dam are circular arc-shaped, and the inner diameter part 44 of the lower part of the rubber oil dam is circular arc-shaped.
The lubricating structure for the large-specific-power spline of the aircraft engine transmission device is also technically characterized in that the width of the rectangle at the upper part of the rubber oil dam is not less than the width of the opening of the dovetail groove, and the height of the rectangle at the upper part of the rubber oil dam is less than the depth of the dovetail groove.
The lubricating structure of the large-specific-power spline for the transmission device of the aero-engine, provided by the invention, is also technically characterized in that the width of the rectangular section at the upper part of the rubber oil dam is 3-5 mm; the height is 2-2.5 mm; the cone angle of the V-shaped section at the lower part of the rubber oil dam is 14-16 degrees; the circular arc fillet at the inner diameter of the lower part of the rubber oil dam is R0.3-R0.8mm; the fillet of the joint of the upper part and the lower part of the rubber oil dam is R1.5-R2.5mm.
Advantageous effects
According to the lubricating structure for the large specific power spline of the aircraft engine transmission device, the oil supply injection point is close to the spline, and the defect that the lubricating effect is influenced by the long injection distance of the existing structure is overcome; the oil supply and the oil return are on different sides, so that a lubricating flow path is smooth, and chip removal is not influenced; the other side in the hollow shaft can be designed into a closed structure and then other structures are installed, and spline lubrication is not affected.
Drawings
FIG. 1 is a schematic structural diagram of a lubrication structure for a high-ratio power spline of an aircraft engine transmission according to an embodiment of the invention.
FIG. 2 is a schematic diagram illustrating an assembly deformation of a dam in a lubrication structure of a high-ratio power spline for an aircraft engine transmission according to an embodiment of the invention.
FIG. 3 is a schematic cross-sectional view of a dam in a lubrication configuration for a high ratio power spline of an aircraft engine transmission provided in an embodiment of the present invention.
FIG. 4 is a schematic cross-sectional view of a dovetail groove of an inner spline gear shaft in a lubrication structure of a high-ratio power spline for an aircraft engine transmission provided by an embodiment of the invention.
Fig. 5 shows a conventional spline lubrication structure.
Detailed Description
The present invention is further described in detail with reference to the drawings and examples, but it should be understood that these embodiments are not intended to limit the present invention, and those skilled in the art should understand that the functional, methodological, or structural equivalents of these embodiments or substitutions may be included in the scope of the present invention.
In the description of the embodiments of the present invention, it should be understood that the terms "central", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only used for convenience in describing and simplifying the description of the present invention, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicit to a number of indicated technical features. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the invention, the meaning of "a plurality" is two or more unless otherwise specified.
The terms "mounted," "connected," and "coupled" are to be construed broadly and may, for example, be fixedly coupled, detachably coupled, or integrally coupled; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art through specific situations.
As shown in fig. 1-4, the present embodiment provides a lubrication structure for a large specific power spline of an aircraft engine transmission device, the lubrication structure includes an internal spline shaft 1 and an external spline shaft 2 that are cooperatively arranged, one end of the internal spline shaft 1 near a lubricating oil inlet is provided with a dovetail groove 3, the other end is provided with an oil discharge hole for discharging lubricating oil, a rubber oil dam 4 for blocking oil is arranged in the dovetail groove 3, and an inner diameter of the rubber oil dam 4 is smaller than a small diameter of the external spline.
In the above embodiment, the rubber dam 4 has a certain oil blocking height to form an under-ring lubrication structure; the external spline shaft 2 can be deformed when being assembled into the internal spline shaft 1, so that the external spline shaft 2 can be pushed in, and the internal diameter of the rubber oil dam 4 recovers the original value after being pushed in; the other end of the internal spline shaft 1 is provided with an oil discharge hole; when the gear shaft operates, lubricating oil is sprayed out by the nozzle and falls onto the outer spline shaft 2, the rotating outer spline shaft 2 throws the lubricating oil into the inner spline shaft 1, the rubber oil dam 4 forms a ring lower lubricating cavity, the lubricating oil forms dynamic pressure on the rotating outer spline shaft 2, flows to a spline meshing part, lubricates the spline meshing surface and is discharged from an oil discharging hole in the inner spline shaft 1.
In some embodiments, the depth of the dovetail groove 3 is 2-4 mm; the section taper angle is 18-22 degrees; the width of the groove opening is 2-4 mm. The depth of the dovetail groove 3 ensures that the rubber oil dam 4 is not separated during assembly, and simultaneously ensures that the wall thickness of the gear shaft meets the strength requirement. The opening width of the dovetail groove 3 is adjusted so that the sectional area of the dovetail groove 3 is substantially the same as the rectangular sectional area of the rubber dam 4.
In some embodiments, the rubber dam 4 is made of fluororubber. The viton may be deformed to effect the spline fit.
In some embodiments, the upper portion 41 of the rubber dam 4 for fitting with the dovetail groove 3 is rectangular, and the lower portion 42 for blocking oil is provided with an approximately V-shaped cross section. The upper and lower joints 43 of the rubber dam 4 are circular arc-shaped, and the lower inner diameter 44 is circular arc-shaped. The structure can be used for preventing the rubber oil dam 4 from being separated in the assembling process, and the rubber oil dam 4 is arranged in the dovetail groove 3 to be deformed and has certain tightness. The height and the width of the rectangular section are matched with the size of the dovetail groove 3 on the internal spline gear shaft, so that the sectional area of the groove is basically equal to the rectangular sectional area of the oil dam; the size of the V-shaped section ensures that the axial assembling force applied during the assembling of the external spline shaft cannot be too large, and simultaneously ensures that the rubber oil dam 4 cannot be damaged to lose the oil blocking function. The inner diameter of the V-shaped section needs to be slightly smaller than the small diameter of the external spline, and the V-shaped section has a certain oil blocking height, so that a lower lubricating structure is formed.
In some embodiments, the width of the rectangle of the upper portion 41 of the rubber dam is not smaller than the opening width of the dovetail groove 3, and the height of the rectangle of the upper portion 41 of the rubber dam is smaller than the groove depth of the dovetail groove 3.
In some embodiments, the width of the rectangular cross section of the upper portion 41 of the rubber dam is 3-5 mm; the height is 2-2.5 mm; the cone angle of the 42V-shaped section at the lower part of the rubber oil dam is 14-16 degrees; the circular arc fillet of the inner diameter part 44 at the lower part of the rubber oil dam is R0.3-R0.8mm; the fillet of the connection part 43 of the upper part and the lower part of the rubber oil retaining dam is R1.5-R2.5mm.
In the above embodiment, after the rubber dam 4 is prepared, finite element analysis as shown in fig. 2 is performed to evaluate the deformation and stress of the rubber dam 4 during the virtual assembly of the male spline shaft 2 into the female spline shaft 1 to determine whether the rubber dam 4 is separated and broken during the assembly, and if the separation or breakage occurs, the relevant geometric dimensions are adjusted.
In some embodiments, the outer diameter of the oil dam is phi 32-phi 34mm, the inner diameter of the oil dam is phi 21-phi 23mm, the width of the rectangular section is 3-5mm, the height of the rectangular section is 2-2.5mm, the taper angle of the V-shaped section is 14-16 degrees, the fillet of the junction of the rectangular section and the V-shaped section is R1.5-R2.5mm, the fillet of the inner diameter of the V-shaped section is R0.3-R0.8mm, the inner diameter of a dovetail groove on the internal spline gear shaft is phi 27.25-phi 29.25mm, the groove depth is 2-4mm, the taper angle of the section is 18-22 degrees, and the groove opening width is 2-4 mm.
The working process is as follows:
after the external spline shaft 2 is assembled into the internal spline shaft 1, when the gear shaft operates, the lubricating oil is sprayed by the nozzle and falls onto the external spline shaft 2, the rotating external spline shaft 2 throws the lubricating oil into the internal spline shaft 1, the rubber oil dam 4 forms a lubricating cavity under a ring, the lubricating oil forms dynamic pressure on the rotating external spline shaft 2, flows to the spline meshing part, lubricates the spline meshing surface and is discharged by the oil discharging hole in the internal spline shaft 1.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention. The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (7)
1. The utility model provides a lubricating structure that is used for big power spline of aeroengine transmission, a serial communication port, lubricating structure is including the internal spline axle and the external spline axle that the cooperation set up, the one end that internal spline axle is close to the lubricating oil import is opened there is the dovetail, and the other end is equipped with the oil drain hole that is used for the discharge lubricating oil, be equipped with the rubber oil dam that is used for keeping off oil in the dovetail, the internal diameter of rubber oil dam is less than the path of external spline.
2. The lubrication structure for a high specific power spline of an aircraft engine transmission according to claim 1, wherein said dovetail grooves are 2-4mm deep; the section taper angle is 18-22 degrees; the width of the groove opening is 2-4 mm.
3. The lubrication structure for a high specific power spline of an aircraft engine transmission as defined in claim 1, wherein said rubber dam is made of viton.
4. The lubrication structure for a high specific power spline of an aircraft engine transmission according to claim 1, wherein an upper portion of said rubber dam for fitting with a dovetail groove is rectangular, and a lower portion for blocking oil is provided with an approximately V-shaped section.
5. The lubrication structure of a high specific power spline for an aircraft engine transmission according to claim 4, wherein the upper and lower transition points of the rubber dam are circular arc shaped, and the lower inner diameter is circular arc shaped.
6. The lubrication structure for a high specific power spline of an aircraft engine transmission according to claim 4, wherein a width of the upper rectangle of the rubber dam is not less than a width of the opening of said dovetail groove, and a height of the upper rectangle of the rubber dam is less than a depth of the groove of said dovetail groove.
7. The lubrication structure for a high specific power spline of an aircraft engine transmission according to claim 5, wherein the width of the rectangular section of the upper portion of the rubber dam is 3-5 mm; the height is 2-2.5 mm; the cone angle of the V-shaped section at the lower part of the rubber oil dam is 14-16 degrees; the circular arc fillet at the inner diameter of the lower part of the rubber oil dam is R0.3-R0.8mm; the fillet of the switching part of the upper part and the lower part of the rubber oil retaining dam is R1.5-R2.5mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210520845.8A CN114857181A (en) | 2022-05-12 | 2022-05-12 | Lubricating structure of large-ratio power spline for aero-engine transmission device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210520845.8A CN114857181A (en) | 2022-05-12 | 2022-05-12 | Lubricating structure of large-ratio power spline for aero-engine transmission device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114857181A true CN114857181A (en) | 2022-08-05 |
Family
ID=82636735
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210520845.8A Pending CN114857181A (en) | 2022-05-12 | 2022-05-12 | Lubricating structure of large-ratio power spline for aero-engine transmission device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114857181A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040157970A1 (en) * | 2003-02-12 | 2004-08-12 | Reuben Sarkar | Controlled release of perfluoropolyether antifoam additives from compounded rubber |
| CN103671853A (en) * | 2012-09-18 | 2014-03-26 | 南车戚墅堰机车车辆工艺研究所有限公司 | Lubricating structure of rotating spline |
| CN205605793U (en) * | 2016-04-25 | 2016-09-28 | 哈尔滨东安发动机（集团）有限公司 | Spline lubricating structure |
| CN113513575A (en) * | 2021-04-29 | 2021-10-19 | 中国航发沈阳发动机研究所 | Spline connection lubricating structure |
-
2022
- 2022-05-12 CN CN202210520845.8A patent/CN114857181A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040157970A1 (en) * | 2003-02-12 | 2004-08-12 | Reuben Sarkar | Controlled release of perfluoropolyether antifoam additives from compounded rubber |
| CN103671853A (en) * | 2012-09-18 | 2014-03-26 | 南车戚墅堰机车车辆工艺研究所有限公司 | Lubricating structure of rotating spline |
| CN205605793U (en) * | 2016-04-25 | 2016-09-28 | 哈尔滨东安发动机（集团）有限公司 | Spline lubricating structure |
| CN113513575A (en) * | 2021-04-29 | 2021-10-19 | 中国航发沈阳发动机研究所 | Spline connection lubricating structure |
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Application publication date: 20220805 |
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