CN114607700B - Vibration reduction and lubrication device suitable for aeroengine bearing - Google Patents
Vibration reduction and lubrication device suitable for aeroengine bearing Download PDFInfo
- Publication number
- CN114607700B CN114607700B CN202210309252.7A CN202210309252A CN114607700B CN 114607700 B CN114607700 B CN 114607700B CN 202210309252 A CN202210309252 A CN 202210309252A CN 114607700 B CN114607700 B CN 114607700B
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- Prior art keywords
- damping
- bearing
- inner ring
- oil
- outer ring
- Prior art date
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- 238000005461 lubrication Methods 0.000 title claims abstract description 20
- 238000013016 damping Methods 0.000 claims abstract description 80
- 241000555745 Sciuridae Species 0.000 claims abstract description 8
- 229910001069 Ti alloy Inorganic materials 0.000 claims abstract description 4
- 239000003921 oil Substances 0.000 claims description 55
- 239000010687 lubricating oil Substances 0.000 claims description 26
- 230000001050 lubricating effect Effects 0.000 claims description 6
- 239000007921 spray Substances 0.000 claims description 6
- 238000007789 sealing Methods 0.000 claims description 5
- 230000007704 transition Effects 0.000 claims description 3
- 239000000956 alloy Substances 0.000 abstract description 2
- 238000005299 abrasion Methods 0.000 abstract 1
- 230000035939 shock Effects 0.000 description 9
- 238000010521 absorption reaction Methods 0.000 description 7
- 229910000831 Steel Inorganic materials 0.000 description 4
- 239000010959 steel Substances 0.000 description 4
- 239000000463 material Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005255 carburizing Methods 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- IJGRMHOSHXDMSA-UHFFFAOYSA-N nitrogen Substances N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C19/00—Bearings with rolling contact, for exclusively rotary movement
- F16C19/52—Bearings with rolling contact, for exclusively rotary movement with devices affected by abnormal or undesired conditions
- F16C19/527—Bearings with rolling contact, for exclusively rotary movement with devices affected by abnormal or undesired conditions related to vibration and noise
-
- 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
- F16C35/04—Rigid support of bearing units; Housings, e.g. caps, covers in the case of ball or roller bearings
- F16C35/06—Mounting or dismounting of ball or roller bearings; Fixing them onto shaft or in housing
-
- 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
- F16C37/007—Cooling of bearings of rolling 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
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/023—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using fluid means
- F16F15/0232—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using fluid means with at least one gas spring
-
- 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
- F16N—LUBRICATING
- F16N1/00—Constructional modifications of parts of machines or apparatus for the purpose of lubrication
-
- 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
- F16N—LUBRICATING
- F16N21/00—Conduits; Junctions; Fittings for lubrication apertures
- F16N21/02—Lubricating nipples
-
- 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
- F16N—LUBRICATING
- F16N21/00—Conduits; Junctions; Fittings for lubrication apertures
- F16N21/04—Nozzles for connection of lubricating equipment to nipples
Abstract
The invention belongs to the technical field of vibration reduction and lubrication of aero-engine system bearings, and provides a vibration reduction and lubrication device suitable for aero-engine bearings. The device consists of a damping outer cavity, an inner cavity, an oil pipeline, a nozzle and a piston ring. The vibration energy of the bearing and the rotary gear is absorbed by adjusting the gap between the inner cavity of the device and the outer ring of the bearing and utilizing the elastic characteristic and the viscous characteristic of an oil film. In order to reduce the high temperature generated by the revolving body during rotation and reduce the abrasion of parts, the device is provided with a nozzle, a squirrel cage and other parts to effectively lubricate and seal the bearing and the revolving system. The device adopts titanium alloy material, and under the premise of meeting high-temperature environment, long-life reliable use, the volume and weight of the whole system are not obviously increased.
Description
Technical Field
The invention belongs to the technical field of vibration reduction and lubrication of aero-engine system bearings, and provides a vibration reduction and lubrication device suitable for aero-engine bearings.
Background
The main shaft bearing of the aeroengine and the gas turbine gradually evolves from a standard structure of an early model to an integrated structure, bearing materials are developed from standard bearing steel to new materials such as high-temperature steel, carburizing steel, fusion surface modification of future high-nitrogen steel and the like, and a bearing vibration damper matched with the new materials is updated. The main forms of devices used for vibration reduction of aero-engine bearings are mechanical vibration reduction modes, such as vibration reduction rings, vibration reduction sleeves, vibration reduction sheets, vibration reduction springs, vibration reduction dampers and the like. In order to reliably operate an aeroengine bearing and a rotator, a novel bearing integrating labyrinth seal and a squirrel cage spring support is applied nowadays, the vibration reduction and lubrication requirements are higher, and the original vibration reduction system cannot adapt to the requirements of the novel bearing.
Disclosure of Invention
The invention aims to: the invention provides a vibration reduction and lubrication device suitable for an aeroengine bearing, which generates a damping oil film between a vibration reduction action area and a rotary gear bearing to achieve the purpose of vibration reduction of the bearing, and lubricates the bearing and a rotary system through a lubrication system on the device.
The technical scheme of the invention is as follows:
a vibration damping and lubrication device suitable for an aero-engine bearing, comprising: the device comprises N groups of lubricating oil units, four piston rings, a damping outer ring with a trapezoid cross section and a cylindrical damping inner ring with the same length as a shaft;
two ends of the shaft are respectively provided with a bearing; the outer end surface of the bearing outer ring is connected with the damping inner ring, and the middle part of the damping inner ring is connected with the damping outer ring; two piston rings are arranged between each bearing outer ring and each damping inner ring, and an annular sealing area is formed between the two piston rings;
n sets of lubricating oil units are arranged on the shock-absorbing outer ring at equal intervals along the circumferential direction, and each set of lubricating oil unit comprises: two oil lines, two nozzles; the two lubricating oil pipelines are symmetrically arranged on the outer side of the inclined edge of the damping outer ring, and extend from the top end of the inclined edge of the damping outer ring to the end face of the damping inner ring; two nozzles are symmetrically arranged on the inner end surface of the damping inner ring and close to the bearing, and the nozzles spray the lubricating oil from the lubricating oil pipeline to the bearing;
and a plurality of radial oil film oil inlets are symmetrically arranged at two ends of the damping inner ring, the oil film oil inlets are used for communicating the oil pipeline with the annular closed area, and an oil film is formed in the annular closed area for damping.
Further, the nozzle sprays lubricating oil to the upper half part of the bearing roller in a direction of 35 degrees relative to the inner end surface of the damping inner ring.
Further, an outer-layer cavity is formed between the damping outer ring and the damping inner ring, and an inner-layer cavity is formed between the damping inner ring and the bearing and the shaft; the damping inner ring is provided with a plurality of lightening holes at equal intervals along the circumferential direction, so that a squirrel cage structure is formed between the outer layer cavity and the inner layer cavity.
Further, the cross-sectional width of the annular sealing region is 12mm, and the thickness is 5mm.
Further, the lightening holes are arranged in two rows of twelve holes each.
Further, the oil film thickness in the annular closed region is controlled by controlling the oil pressure of the oil line.
Further, the shock absorption inner ring is in transition fit with the bearing outer ring.
Further, the damping outer ring and the damping inner ring are made of titanium alloy, and are integrally formed or welded into a whole after being respectively formed.
The invention has the following beneficial effects:
the invention utilizes the self novel squirrel cage structure to absorb shock, forms an oil film on the outer ring of the bearing by utilizing oil pressure, absorbs a part of shock by the oil film, is particularly suitable for shock absorption and lubrication of the high-speed revolving body, and has obvious shock absorption effect and simple structure.
Drawings
FIG. 1 is a cross-sectional view of a vibration damping and lubrication apparatus according to an embodiment of the present invention;
FIG. 2 is an enlarged view of a portion of a bearing area of a vibration damping and lubrication device according to an embodiment of the present invention;
1-shaft, 2-bearing, 3-damping outer ring, 4-oil pipeline, 5-nozzle, 6-damping inner ring, 7-piston ring,
8-oil film oil inlet, 9-oil film area and 10-lightening hole.
Detailed Description
This section is an embodiment of the present invention for explaining and explaining the technical solution of the present invention.
A vibration damping and lubrication device suitable for an aero-engine bearing, comprising: the device comprises N groups of lubricating oil units, four piston rings, a damping outer ring with a trapezoid cross section and a cylindrical damping inner ring with the same length as a shaft;
two ends of the shaft are respectively provided with a bearing; the outer end surface of the bearing outer ring is connected with the damping inner ring, and the middle part of the damping inner ring is connected with the damping outer ring; two piston rings are arranged between each bearing outer ring and each damping inner ring, and an annular sealing area is formed between the two piston rings;
n sets of lubricating oil units are arranged on the shock-absorbing outer ring at equal intervals along the circumferential direction, and each set of lubricating oil unit comprises: two oil lines, two nozzles; the two lubricating oil pipelines are symmetrically arranged on the outer side of the inclined edge of the damping outer ring, and extend from the top end of the inclined edge of the damping outer ring to the end face of the damping inner ring; two nozzles are symmetrically arranged on the inner end surface of the shock absorption inner ring close to the bearing, and the nozzles spray lubricating oil to the upper half part of the bearing roller in a direction of 35 degrees with the inner end surface of the shock absorption inner ring.
And a plurality of radial oil film oil inlets are symmetrically arranged at two ends of the damping inner ring, the oil film oil inlets are used for communicating the oil pipeline with the annular closed area, and an oil film is formed in the annular closed area for damping. The oil film thickness in the annular closed region is controlled by controlling the oil pressure of the oil line.
An outer-layer cavity is formed between the damping outer ring and the damping inner ring, and an inner-layer cavity is formed between the damping inner ring and the bearing and the shaft; the damping inner ring is provided with a plurality of lightening holes at equal intervals along the circumferential direction, so that a squirrel cage structure is formed between the outer layer cavity and the inner layer cavity.
Example 1
The structure of the vibration damping and lubricating device suitable for the aeroengine bearing is shown in figures 1 and 2, and the whole device consists of a trapezoid vibration damping outer ring 3, an upper oil pipeline 4, a lower oil pipeline 4, four nozzles 5, a vibration damping inner ring 6 with twenty-four weight reducing holes 10 arranged in two rows between two bearings and four piston rings 7.
The two ends of the shaft 1 are connected through bearings 2, and the bearings are in interference fit with the shaft. The two bearing outer rings are in transition fit with the inner wall of the shock absorption inner ring 6, and each bearing outer ring is formed by a sealed oil film region 9 between the bearing outer ring and the shock absorption inner ring 6 through two piston rings 7. After entering the lubricating oil pipeline 4, the lubricating oil is divided into two paths, one path enters the bearing outer ring through the oil film oil inlet 8, and the oil film thickness of the oil film region 10 is controlled through the inlet oil pressure so as to achieve the vibration reduction purpose; the other path of lubricating oil enters a nozzle 5 in the system, and is sprayed out of the nozzle at an angle of 35 degrees to directly spray the bearing roller; the angle and the distance enable the lubricating oil to splash to the upper half part of the bearing roller, and when the roller rotates, the lubricating oil covers the whole rolling body, so that the lubricating and cooling effects of the bearing and the rotary system are achieved.
Besides, except for oil film damping, an outer cavity is formed between the damping outer ring 3 and the damping inner ring 6, an inner cavity is formed between the damping inner ring and the bearing 2 as well as between the damping inner ring and the shaft 1, and twenty-four weight reducing holes 10 on the damping inner ring 6 are used for enabling the whole device to be of a squirrel cage structure, and vibration of a system revolving body can be absorbed and transmitted through the structure, so that the purpose of damping is achieved.
The device adopts titanium alloy material, and under the premise of meeting high-temperature environment, long-life reliable use, the volume and weight of the whole system are not obviously increased. The casting average thickness is 20mm, the weight of the whole device is about 9.5kG, and a welding structure is adopted locally.
The device is provided with an oil injection pipeline and a lubricating squirrel cage 2-6, and is provided with an oil injection return oil way, so that a bearing and a revolving body can be lubricated.
In the figure 1, the lubricating oil enters the device from the oil inlet and then is divided into two paths, one path enters the outer ring of the bearing from the device to achieve the purpose of vibration reduction, and the other path enters the internal nozzle of the system to achieve the lubricating effect of the bearing and the rotary system.
An oil film groove is formed between the vibration reduction area of the device and the outer ring of the bearing, the size is 12mm wide, the thickness is 5mm, and the vibration reduction value is about 2g.
The lubricating oil with vibration reduction function enters the wear-resistant bushing from the size of 12mm and the thickness of 5mm, then enters the outer wall of the bearing from the small hole on the wear-resistant bushing, so that an oil film 9 is generated between the bearing bushing and the bearing, two piston rings are arranged between the bearing bushing and the bearing front and back to control the thickness and the pressure of the oil film, a certain leakage amount is provided, finally, the reduced vibration energy is calculated according to the viscosity characteristic and the elastic coefficient of the oil film, and the vibration reduction value is about 2g.
Claims (8)
1. Damping and lubricating arrangement suitable for aeroengine bearing, its characterized in that: the device comprises: the device comprises N groups of lubricating oil units, four piston rings, a damping outer ring with a trapezoid cross section and a cylindrical damping inner ring with the same length as a shaft;
two ends of the shaft are respectively provided with a bearing; the outer end surface of the bearing outer ring is connected with the damping inner ring, and the middle part of the damping inner ring is connected with the damping outer ring; two piston rings are arranged between each bearing outer ring and each damping inner ring, and an annular sealing area is formed between the two piston rings;
n sets of lubricating oil units are arranged on the shock-absorbing outer ring at equal intervals along the circumferential direction, and each set of lubricating oil unit comprises: two oil lines, two nozzles; the two lubricating oil pipelines are symmetrically arranged on the outer side of the inclined edge of the damping outer ring, and extend from the top end of the inclined edge of the damping outer ring to the end face of the damping inner ring; two nozzles are symmetrically arranged on the inner end surface of the damping inner ring and close to the bearing, and the nozzles spray the lubricating oil from the lubricating oil pipeline to the bearing;
and a plurality of radial oil film oil inlets are symmetrically arranged at two ends of the damping inner ring, the oil film oil inlets are used for communicating the oil pipeline with the annular closed area, and an oil film is formed in the annular closed area for damping.
2. The vibration damping and lubrication device for an aeroengine bearing according to claim 1, wherein: the nozzle sprays lubricating oil to the upper half part of the bearing roller in a direction of 35 degrees relative to the inner end surface of the damping inner ring.
3. The vibration damping and lubrication device for an aeroengine bearing according to claim 1, wherein: an outer-layer cavity is formed between the damping outer ring and the damping inner ring, and an inner-layer cavity is formed between the damping inner ring and the bearing and the shaft; the damping inner ring is provided with a plurality of lightening holes at equal intervals along the circumferential direction, so that a squirrel cage structure is formed between the outer layer cavity and the inner layer cavity.
4. The vibration damping and lubrication device for an aeroengine bearing according to claim 1, wherein: the cross-sectional width of the annular sealing area is 12mm, and the thickness is 5mm.
5. A vibration damping and lubricating device for an aero-engine bearing according to claim 3, wherein: the lightening holes are arranged in two rows of twelve holes each.
6. The vibration damping and lubrication device for an aeroengine bearing according to claim 1, wherein: the oil film thickness in the annular closed region is controlled by controlling the oil pressure of the oil line.
7. The vibration damping and lubrication device for an aeroengine bearing according to claim 1, wherein: and the damping inner ring is in transition fit with the bearing outer ring.
8. The vibration damping and lubrication device for an aeroengine bearing according to claim 1, wherein: the damping outer ring and the damping inner ring are made of titanium alloy, and are integrally formed or welded into a whole after being respectively formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210309252.7A CN114607700B (en) | 2022-03-25 | 2022-03-25 | Vibration reduction and lubrication device suitable for aeroengine bearing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210309252.7A CN114607700B (en) | 2022-03-25 | 2022-03-25 | Vibration reduction and lubrication device suitable for aeroengine bearing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114607700A CN114607700A (en) | 2022-06-10 |
| CN114607700B true CN114607700B (en) | 2023-11-24 |
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ID=81866313
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210309252.7A Active CN114607700B (en) | 2022-03-25 | 2022-03-25 | Vibration reduction and lubrication device suitable for aeroengine bearing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114607700B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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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| GB2107002A (en) * | 1981-10-02 | 1983-04-20 | Rolls Royce | Journal bearing |
| US4781077A (en) * | 1986-12-19 | 1988-11-01 | Massachusetts Institute Of Technology | Stable intershaft squeeze film damper |
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Also Published As
| Publication number | Publication date |
|---|---|
| CN114607700A (en) | 2022-06-10 |
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