CN114607700A - Vibration reduction and lubrication device suitable for aeroengine bearing - Google Patents
Vibration reduction and lubrication device suitable for aeroengine bearing Download PDFInfo
- Publication number
- CN114607700A CN114607700A CN202210309252.7A CN202210309252A CN114607700A CN 114607700 A CN114607700 A CN 114607700A CN 202210309252 A CN202210309252 A CN 202210309252A CN 114607700 A CN114607700 A CN 114607700A
- Authority
- CN
- China
- Prior art keywords
- damping
- bearing
- inner ring
- lubricating oil
- shock absorption
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000005461 lubrication Methods 0.000 title abstract description 8
- 238000013016 damping Methods 0.000 claims abstract description 75
- 239000010687 lubricating oil Substances 0.000 claims abstract description 47
- 239000003921 oil Substances 0.000 claims abstract description 42
- 241000555745 Sciuridae Species 0.000 claims abstract description 7
- 229910001069 Ti alloy Inorganic materials 0.000 claims abstract description 4
- 230000035939 shock Effects 0.000 claims description 33
- 238000010521 absorption reaction Methods 0.000 claims description 28
- 230000001050 lubricating effect Effects 0.000 claims description 18
- 239000007921 spray Substances 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
- 229910000831 Steel Inorganic materials 0.000 description 4
- 239000010959 steel Substances 0.000 description 4
- 230000000694 effects Effects 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 239000000463 material 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
- 238000013017 mechanical damping Methods 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
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
- 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
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Aviation & Aerospace Engineering (AREA)
- Rolling Contact Bearings (AREA)
- Support Of The Bearing (AREA)
Abstract
The invention belongs to the technical field of vibration reduction and lubrication of bearings of aero-engine systems, and provides a vibration reduction and lubrication device suitable for bearings of aero-engines. The device consists of a damping outer cavity, an inner cavity, a lubricating oil pipeline, a nozzle and an expansion 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 the rotation and reduce the abrasion of parts, the device is provided with a nozzle, a squirrel cage and other components which effectively lubricate and seal a bearing and a revolving system. The device adopts titanium alloy material, satisfies the high temperature environment, under the reliable prerequisite of using of long-life, does not obviously increase the volume and the weight of entire system.
Description
Technical Field
The invention belongs to the technical field of vibration reduction and lubrication of bearings of aero-engine systems, and provides a vibration reduction and lubrication device suitable for bearings of aero-engines.
Background
The main shaft bearing of the aero-engine and the gas turbine gradually evolves to an integrated structure from a standard structure of an early machine type, bearing materials are developed to new materials such as high-temperature steel, carburizing steel and future high-nitrogen steel fusion surface modification from standard bearing steel, and bearing vibration reduction devices matched with the bearing vibration reduction devices are updated and updated accordingly. The main forms of the devices for damping the bearings of the aeroengine are mechanical damping modes, such as damping rings, damping sleeves, damping sheets, damping springs, damping dampers and the like. In order to ensure reliable operation of aeroengine bearings and rotors, labyrinth seals and squirrel cage springs are applied to novel bearings, the requirements on vibration reduction and lubrication are higher, and the original vibration reduction system cannot meet the requirements of the novel bearings.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides a vibration damping and lubricating device suitable for an aeroengine bearing, which generates a damping oil film between a vibration damping action area and a rotating gear bearing to achieve the aim of vibration damping of the bearing, and lubricates the bearing and a rotary system through a lubricating system on the device.
The technical scheme of the invention is as follows:
a vibration damping and lubricating device suitable for an aircraft engine bearing comprising: n groups of lubricating oil units, four piston rings, a shock absorption outer ring with a trapezoidal section and a cylindrical shock absorption inner ring with the same length as the shaft;
two bearings are respectively arranged at two ends of the shaft; the outer end face 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 sealed area is formed between the two piston rings;
the shock attenuation outer loop is last to set up N group's lubricating oil unit along circumference equidistant, and every group lubricating oil unit includes: two lubricating oil pipelines and two nozzles; the two lubricating oil pipelines are symmetrically arranged on the outer side of the bevel edge of the shock absorption outer ring, and extend from the top end of the bevel edge of the shock absorption outer ring to the end face of the shock absorption inner ring; two nozzles are symmetrically arranged on the inner end surface of the damping inner ring close to the bearing, and spray lubricating oil from a lubricating oil pipeline to the bearing;
the damping inner ring is characterized in that a plurality of radial oil film oil inlets are symmetrically arranged at two ends of the damping inner ring, the oil film oil inlets communicate the lubricating oil pipeline with the annular sealed area, and an oil film is formed in the annular sealed area and used for damping.
Further, the nozzle sprays lubricating oil to the upper half part of the bearing roller in a direction of 35 degrees with the inner end surface of the damping inner ring.
Further, an outer layer cavity is formed between the shock absorption outer ring and the shock absorption inner ring, and an inner layer cavity is formed between the shock absorption inner ring and the bearing and the shaft; a plurality of lightening holes are formed in the shock absorption inner ring 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 section width of the annular closed area is 12mm, and the thickness is 5 mm.
Further, the lightening holes are arranged in two rows, and each row is twelve.
Further, the thickness of an oil film in the annular closed area is controlled by controlling the pressure of lubricating oil in the lubricating oil pipeline.
Furthermore, the damping inner ring and the bearing outer ring are in transition fit.
Furthermore, 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 formed respectively.
The invention has the following beneficial effects:
the invention utilizes the novel squirrel-cage structure to absorb shock, utilizes oil pressure to form an oil film on the outer ring of the bearing, absorbs a part of shock through the oil film, is particularly suitable for shock absorption and lubrication of a 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 lubricating apparatus according to an embodiment of the present invention;
FIG. 2 is an enlarged view of a portion of a bearing area of the vibration damping and lubricating apparatus of the present invention;
1-shaft, 2-bearing, 3-damping outer ring, 4-lubricating 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 example of the present invention and is provided to explain and illustrate the technical solutions of the present invention.
A vibration damping and lubricating device suitable for an aircraft engine bearing comprising: n groups of lubricating oil units, four piston rings, a shock absorption outer ring with a trapezoidal section and a cylindrical shock absorption inner ring with the same length as the shaft;
two bearings are respectively arranged at two ends of the shaft; the outer end face 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 sealed area is formed between the two piston rings;
the shock attenuation outer loop is last to set up N group's lubricating oil unit along circumference equidistant, and every group lubricating oil unit includes: two lubricating oil pipelines and two nozzles; the two lubricating oil pipelines are symmetrically arranged on the outer side of the bevel edge of the shock absorption outer ring, and extend from the top end of the bevel edge of the shock absorption outer ring to the end face of the shock absorption inner ring; two nozzles are symmetrically arranged on the inner end surface of the inner damping 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 from the inner end surface of the inner damping ring.
The damping inner ring is characterized in that a plurality of radial oil film oil inlets are symmetrically arranged at two ends of the damping inner ring, the oil film oil inlets communicate the lubricating oil pipeline with the annular sealed area, and an oil film is formed in the annular sealed area and used for damping. The thickness of an oil film in the annular closed area is controlled by controlling the pressure of lubricating oil in the lubricating oil pipeline.
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; a plurality of lightening holes are formed in the shock absorption inner ring 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 one
A vibration damping and lubricating device suitable for an aeroengine bearing is shown in the figures 1 and 2, and the whole device is composed of a trapezoidal vibration damping outer ring 3, an upper lubricating oil pipeline 4, a lower lubricating oil pipeline 4, four nozzles 5, a vibration damping inner ring 6 and four piston rings 7, wherein the upper lubricating oil pipeline and the lower lubricating oil pipeline are arranged along the inclined edge of the vibration damping outer ring, the two rows of vibration damping inner rings 6 and the two rows of vibration damping inner rings 7 are arranged between the two bearings, and the two rows of vibration damping inner rings have twenty-four lightening holes 10.
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 damping inner ring 6, and a closed oil film area 9 is formed between each bearing outer ring and the damping inner ring 6 by two piston rings 7. When the lubricating oil enters 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 purpose of vibration reduction is achieved by controlling the thickness of an oil film in the oil film area 10 through the inlet oil pressure; the other path of lubricating oil enters a nozzle 5 in the system and is sprayed out from the nozzle at an angle of 35 degrees and directly penetrates the bearing roller; the angle and the distance enable the lubricating oil to be sprayed 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 a rotary system are achieved.
Besides, except for oil film damping, an outer-layer cavity is formed between the damping outer ring 3 and the damping inner ring 6, an inner-layer cavity is formed between the damping inner ring and the bearing 2 and between the damping inner ring and the shaft 1, the whole device is in a squirrel cage structure through twenty-four lightening holes 10 in the damping inner ring 6, and the vibration of a system revolving body can be absorbed and transmitted through the structure, so that the damping purpose is achieved.
The device adopts titanium alloy material, satisfies the high temperature environment, under the reliable prerequisite of using of long-life, does not obviously increase the volume and the weight of entire system. The average casting thickness is 20mm, the weight of the whole device is about 9.5kG, and a welding structure is locally adopted.
The device is provided with an oil injection pipeline and lubricating squirrel cages 2-6, and is provided with an oil injection and return oil way which can lubricate a bearing and a revolving body.
As shown in figure 1, the lubricating oil enters the device from the oil inlet and then is divided into two paths, one path of the lubricating oil enters the bearing outer ring from the device to play a role in vibration reduction, and the other path of the lubricating oil enters the nozzle in the system to play a role in lubricating the bearing and the rotary system.
An oil film groove is arranged between the vibration reduction area of the device and the outer ring of the bearing, the size is 12mm in width and 5mm in thickness, and the vibration reduction value is about 2 g.
Lubricating oil which plays a role in vibration reduction enters the wear-resistant bush from the size of 12mm in width and 5mm in thickness, then enters the outer wall of the bearing from the small hole in the wear-resistant bush, so that an oil film 9 is generated between the bearing bush and the bearing, two piston rings are arranged between the bearing bush and the bearing in the front and back directions to control the thickness and pressure of the oil film, the oil film has a certain leakage amount, finally, 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 2 g.
Claims (8)
1. The utility model provides a damping and lubricating arrangement suitable for aeroengine bearing which characterized in that: the device comprises: n groups of lubricating oil units, four piston rings, a shock absorption outer ring with a trapezoidal section and a cylindrical shock absorption inner ring with the same length as the shaft;
two bearings are respectively arranged at two ends of the shaft; the outer end face 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 sealed area is formed between the two piston rings;
the shock attenuation outer loop is last to set up N group's lubricating oil unit along circumference equidistant, and every group lubricating oil unit includes: two lubricating oil pipelines and two nozzles; the two lubricating oil pipelines are symmetrically arranged on the outer side of the bevel edge of the shock absorption outer ring, and extend from the top end of the bevel edge of the shock absorption outer ring to the end face of the shock absorption inner ring; two nozzles are symmetrically arranged on the inner end surface of the damping inner ring close to the bearing, and spray lubricating oil from a lubricating oil pipeline to the bearing;
the damping inner ring is characterized in that a plurality of radial oil film oil inlets are symmetrically arranged at two ends of the damping inner ring, the oil film oil inlets communicate the lubricating oil pipeline with the annular sealed area, and an oil film is formed in the annular sealed area and used for damping.
2. A vibration damping and lubricating device suitable for aeroengine bearings according to claim 1, wherein: and the nozzle sprays lubricating oil to the upper half part of the bearing roller in a direction of 35 degrees from the inner end surface of the damping inner ring.
3. A vibration damping and lubricating device suitable for aeroengine bearings according to claim 1, wherein: an outer layer cavity is formed between the shock absorption outer ring and the shock absorption inner ring, and an inner layer cavity is formed between the shock absorption inner ring and the bearing and the shaft; a plurality of lightening holes are formed in the shock absorption inner ring 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 lubricating apparatus for an aircraft engine bearing according to claim 1, wherein: the cross section width of the annular closed area is 12mm, and the thickness is 5 mm.
5. A vibration damping and lubricating device suitable for aeroengine bearings according to claim 4, wherein: the lightening holes are arranged in two rows, and each row is twelve.
6. A vibration damping and lubricating device suitable for aeroengine bearings according to claim 1, wherein: the thickness of an oil film in the annular closed area is controlled by controlling the pressure of lubricating oil in the lubricating oil pipeline.
7. A vibration damping and lubricating device suitable for aeroengine bearings according to claim 1, wherein: the damping inner ring and the bearing outer ring are in transition fit.
8. A vibration damping and lubricating device suitable for aeroengine bearings according to claim 1, wherein: the shock absorption outer ring and the shock absorption inner ring are made of titanium alloy and are integrally formed or respectively formed and then welded into a whole.
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 true CN114607700A (en) | 2022-06-10 |
| CN114607700B CN114607700B (en) | 2023-11-24 |
Family
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) |
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 (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| DE3727151A1 (en) * | 1987-08-14 | 1989-02-23 | Skf Gmbh | STORAGE |
| JPH05346138A (en) * | 1992-06-12 | 1993-12-27 | Koyo Seiko Co Ltd | Torque transmission device |
| US20040062460A1 (en) * | 2002-10-01 | 2004-04-01 | Snecma Moteurs | Oil-damped rolling bearing |
| EP1431600A1 (en) * | 2002-12-20 | 2004-06-23 | Techspace Aero S.A. | Rolling bearing provided with a squeeze film for damping loads due to blade failure |
| US20080240632A1 (en) * | 2007-03-27 | 2008-10-02 | Honeywell International, Inc. | Support dampers for bearing assemblies and methods of manufacture |
| WO2012079879A1 (en) * | 2010-12-17 | 2012-06-21 | Schaeffler Technologies AG & Co. KG | Bearing cartridge for a turbocharger |
| US20150078696A1 (en) * | 2012-04-20 | 2015-03-19 | Schaeffler Technologies Gmbh & Co. Kg | Bearing unit for a turbocharger |
| CN104482056A (en) * | 2014-11-14 | 2015-04-01 | 中国南方航空工业(集团)有限公司 | Gas generator and aircraft engine with gas generator |
| CN204267598U (en) * | 2014-11-28 | 2015-04-15 | 哈尔滨广瀚燃气轮机有限公司 | With the returning type elastic support of film damper |
| US20160369652A1 (en) * | 2015-06-18 | 2016-12-22 | United Technologies Corporation | Bearing support damping |
| CN108204423A (en) * | 2018-03-14 | 2018-06-26 | 大连理工大学 | Corrugated foil type squeeze film damper |
| DE102017121419A1 (en) * | 2017-09-15 | 2019-03-21 | Schaeffler Technologies AG & Co. KG | storage unit |
| JP2019132391A (en) * | 2018-02-01 | 2019-08-08 | 本田技研工業株式会社 | Bearing device |
| US10753391B1 (en) * | 2019-04-05 | 2020-08-25 | Raytheon Technologies Corporation | Compact centering spring configuration, retention, and bladeout features |
| US20200284298A1 (en) * | 2019-03-04 | 2020-09-10 | Pratt & Whitney Canada Corp. | Method to seal damper cavity of multi-film oil damper |
| US20200300120A1 (en) * | 2019-03-18 | 2020-09-24 | Pratt & Whitney Canada Corp. | Method and system to supply oil to a multi-film oil damper |
| CN111963566A (en) * | 2020-08-19 | 2020-11-20 | 黄登亮 | Rolling steel ball abrasion-proof bearing |
| CN215334124U (en) * | 2021-03-23 | 2021-12-28 | 中国航发商用航空发动机有限责任公司 | Squeeze film damper and aircraft engine |
| CN113847412A (en) * | 2021-09-28 | 2021-12-28 | 中国航发湖南动力机械研究所 | Non-interrupted lubrication structure and lubrication method for planetary gear train |
-
2022
- 2022-03-25 CN CN202210309252.7A patent/CN114607700B/en active Active
Patent Citations (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| DE3727151A1 (en) * | 1987-08-14 | 1989-02-23 | Skf Gmbh | STORAGE |
| JPH05346138A (en) * | 1992-06-12 | 1993-12-27 | Koyo Seiko Co Ltd | Torque transmission device |
| US20040062460A1 (en) * | 2002-10-01 | 2004-04-01 | Snecma Moteurs | Oil-damped rolling bearing |
| EP1431600A1 (en) * | 2002-12-20 | 2004-06-23 | Techspace Aero S.A. | Rolling bearing provided with a squeeze film for damping loads due to blade failure |
| US20080240632A1 (en) * | 2007-03-27 | 2008-10-02 | Honeywell International, Inc. | Support dampers for bearing assemblies and methods of manufacture |
| WO2012079879A1 (en) * | 2010-12-17 | 2012-06-21 | Schaeffler Technologies AG & Co. KG | Bearing cartridge for a turbocharger |
| US20150078696A1 (en) * | 2012-04-20 | 2015-03-19 | Schaeffler Technologies Gmbh & Co. Kg | Bearing unit for a turbocharger |
| CN104482056A (en) * | 2014-11-14 | 2015-04-01 | 中国南方航空工业(集团)有限公司 | Gas generator and aircraft engine with gas generator |
| CN204267598U (en) * | 2014-11-28 | 2015-04-15 | 哈尔滨广瀚燃气轮机有限公司 | With the returning type elastic support of film damper |
| US20160369652A1 (en) * | 2015-06-18 | 2016-12-22 | United Technologies Corporation | Bearing support damping |
| DE102017121419A1 (en) * | 2017-09-15 | 2019-03-21 | Schaeffler Technologies AG & Co. KG | storage unit |
| JP2019132391A (en) * | 2018-02-01 | 2019-08-08 | 本田技研工業株式会社 | Bearing device |
| CN108204423A (en) * | 2018-03-14 | 2018-06-26 | 大连理工大学 | Corrugated foil type squeeze film damper |
| US20200284298A1 (en) * | 2019-03-04 | 2020-09-10 | Pratt & Whitney Canada Corp. | Method to seal damper cavity of multi-film oil damper |
| US20200300120A1 (en) * | 2019-03-18 | 2020-09-24 | Pratt & Whitney Canada Corp. | Method and system to supply oil to a multi-film oil damper |
| US10753391B1 (en) * | 2019-04-05 | 2020-08-25 | Raytheon Technologies Corporation | Compact centering spring configuration, retention, and bladeout features |
| CN111963566A (en) * | 2020-08-19 | 2020-11-20 | 黄登亮 | Rolling steel ball abrasion-proof bearing |
| CN215334124U (en) * | 2021-03-23 | 2021-12-28 | 中国航发商用航空发动机有限责任公司 | Squeeze film damper and aircraft engine |
| CN113847412A (en) * | 2021-09-28 | 2021-12-28 | 中国航发湖南动力机械研究所 | Non-interrupted lubrication structure and lubrication method for planetary gear train |
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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114607700B (en) | 2023-11-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2224103B1 (en) | Bearing support apparatus with squeeze film damper | |
| JP5080814B2 (en) | Gas turbine engine assembly, differential squeeze oil film damper bearing assembly, and gas turbine engine | |
| US10352195B2 (en) | Non-contacting seals for geared gas turbine engine bearing compartments | |
| US9951817B2 (en) | Integral oil damper and jet for lubrication of bearings and seals | |
| US9803743B2 (en) | Rotating assembly comprising a transmission member and an oil distribution system | |
| US20140300058A1 (en) | Sealing of turbine engine enclosures produced by brush seal and labyrinth | |
| EP3388719A1 (en) | Reduced friction intershaft seal assembly | |
| JP2017150484A (en) | Core differential bearing with centering spring and squeeze film damper | |
| CN104747602A (en) | High-speed lower lubricating device for bearing ring | |
| CN114607700B (en) | Vibration reduction and lubrication device suitable for aeroengine bearing | |
| CN203499731U (en) | High-temperature and high-speed floating ring air film sealing structure | |
| US10443443B2 (en) | Non-contacting seals for geared gas turbine engine bearing compartments | |
| CN210461382U (en) | Self-excitation type oil mist jet lubrication high-speed bearing | |
| EP3699447B1 (en) | Bearing for use in high speed application | |
| CN110594303B (en) | Sealing structure for bearing seat of high-speed horizontal screw machine | |
| CN108691657A (en) | Combustion engine and its lubricating and cooling system | |
| CN113154237B (en) | Coaxial contra-rotating helicopter transmission system lubricating structure and helicopter | |
| CN211287798U (en) | Self-adaptive high-durability floating sealing structure suitable for extreme conditions | |
| RU159639U1 (en) | DEVICE FOR SUPPLYING OIL TO A BEARING OF A GAS-TURBINE ENGINE ROTOR SUPPORT | |
| CN110425010B (en) | Vertical cantilever steam turbine | |
| EP3372793B1 (en) | Non-contacting seals for geared gas turbine engine bearing compartments | |
| KR100268578B1 (en) | Gang head for machine tool | |
| CN213775885U (en) | Variable-pitch oil cylinder lubricating device of wind turbine generator | |
| CN111089000A (en) | Self-adaptive high-durability floating sealing structure suitable for extreme conditions | |
| CN116906581A (en) | Aeroengine bearing sealing structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |