CN112503096B - Bearing and bearing outer ring integrated structure - Google Patents
Bearing and bearing outer ring integrated structure Download PDFInfo
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- CN112503096B CN112503096B CN202011367852.6A CN202011367852A CN112503096B CN 112503096 B CN112503096 B CN 112503096B CN 202011367852 A CN202011367852 A CN 202011367852A CN 112503096 B CN112503096 B CN 112503096B
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- outer ring
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- cage bar
- bearing outer
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- 241000555745 Sciuridae Species 0.000 claims abstract description 33
- 238000005096 rolling process Methods 0.000 claims abstract description 8
- 230000002093 peripheral effect Effects 0.000 claims abstract description 3
- 238000009529 body temperature measurement Methods 0.000 claims description 5
- 238000009434 installation Methods 0.000 claims description 4
- 238000012545 processing Methods 0.000 description 9
- 238000000034 method Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 5
- 238000013461 design Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000001125 extrusion Methods 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
- 238000003466 welding 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
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
- F16C33/30—Parts of ball or roller bearings
- F16C33/58—Raceways; Race rings
- F16C33/581—Raceways; Race rings integral with other parts, e.g. with housings or machine elements such as shafts or gear wheels
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
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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
- F16C19/02—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows
- F16C19/04—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for radial load mainly
- F16C19/06—Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for radial load mainly with a single row or balls
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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
- F16C33/00—Parts of bearings; Special methods for making bearings or parts thereof
- F16C33/30—Parts of ball or roller bearings
- F16C33/58—Raceways; Race rings
- F16C33/583—Details of specific parts of races
- F16C33/585—Details of specific parts of races of raceways, e.g. ribs to guide the rollers
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Rolling Contact Bearings (AREA)
Abstract
The application provides a bearing and bearing inner race integrated configuration, the bearing includes bearing inner race 12, bearing inner race integrated configuration 11, holder 14 and a plurality of rolling ball 13, wherein: the bearing inner ring 12 is a groove type double-half ferrule with a Golde curvature, a circle of drawing groove is formed on the outer peripheral side of the bearing inner ring 12, a retainer 14 is arranged on the outer circumference of the bearing inner ring 12, a bearing outer ring integrated structure 11 is arranged on the outer circumference of the retainer 14, and a rolling ball 13 is arranged in an inner cavity formed by the bearing inner ring 12, the retainer 14 and the bearing outer ring integrated structure 11; the bearing outer ring integrated structure 11 comprises a bearing outer ring 110, a mounting edge 111, a first section of squirrel cage bar 112a, a second section of squirrel cage bar 112b, a supporting spoke plate 113, a boss 114 and a temperature measuring hole 115, wherein: one end of the first section of cage bar 112a is connected to the bearing outer ring 110, and the other end of the first section of cage bar 112a is connected to the lower end of the supporting web 113; one end of said second section cage bar 112b is connected to the upper end of the support web 113.
Description
Technical Field
The invention belongs to the field of aircraft engines and gas turbines, and particularly relates to a bearing and a bearing outer ring integrated structure.
Background
The supporting system of the aero-engine and the gas turbine mainly supports the engine rotor, transfers axial and radial loads, provides proper supporting rigidity for the engine rotor and meets the dynamic design requirements of the engine rotor system.
With the continuous development of the technology of aero-engines and gas turbines, higher and higher requirements are put forward on bearings and supporting structures, the bearings and the supporting structures are required to complete the functions of the bearings and the supporting structures under complex working condition environments, and the requirements of light weight and high reliability are met.
The current bearing support structure of an aircraft engine and a gas turbine is shown in figure 1 and generally comprises a bearing 1, a squirrel cage 2, a bearing seat 3 and a casing 4. The existing supporting structure has the advantages that all parts are designed independently and connected through screws and bolts. The existing supporting structure has the disadvantages of more parts, complex structure and heavy weight. Although there are some documents and patents that attempt to integrate the bearing outer ring with the squirrel cage for current aircraft engine and gas turbine support structures, as in the article: the skid rate analysis (Zhengzhuki) of a certain squirrel cage elastic support integrated ball bearing retainer relates to a squirrel cage elastic support and bearing outer ring integrated structure, and the structure has the problems that the processing of the outer circumference of the bearing outer ring and squirrel cage bars is difficult, the processing precision is difficult to meet the requirements of an aeroengine and a gas turbine, the processing cost is high and the like; the patent: a bearing unit (CN 201297208Y) with an extrusion oil film groove and a squirrel cage elastic support structure relates to a bearing unit structure with an extrusion oil film groove and a squirrel cage elastic support structure, the outer circumference of the outer ring of the bearing and the squirrel cage bars of the structure are easy to process, but the required axial space is larger, and the axial space of the bearings of an aero-engine and a gas turbine which are generally arranged on a compressor and a turbine shaft is limited.
The temperature of the outer ring of the bearing can only be indirectly measured in an engine by the existing bearing, mainly because the outer ring of the bearing cannot be fixed with a thermocouple in a welding mode due to current corrosion. The temperature thermocouple is usually installed on the bearing seat near the side end face of the bearing outer ring. The mode causes inaccurate measurement of the temperature of the bearing, the working performance of the bearing cannot be accurately judged, and the working reliability of the engine is influenced.
Disclosure of Invention
The purpose of the invention is as follows: the bearing outer ring integrated structure can meet the requirements of light weight and high reliability of a high thrust-weight ratio engine. Meanwhile, a hole capable of being provided with a temperature thermocouple is designed on the end face of the outer ring, so that the problem of inaccurate temperature measurement of the bearing of the aeroengine is solved, and the working reliability of the bearing is improved.
The application provides a bearing and bearing inner race integrated configuration, the bearing includes bearing inner race 12, bearing inner race integrated configuration 11, holder 14 and a plurality of rolling ball 13, wherein:
the bearing inner ring 12 is a groove type double-half ferrule with a Golde curvature, a circle of drawing groove is formed on the outer peripheral side of the bearing inner ring 12, a retainer 14 is arranged on the outer circumference of the bearing inner ring 12, a bearing outer ring integrated structure 11 is arranged on the outer circumference of the retainer 14, and a rolling ball 13 is arranged in an inner cavity formed by the bearing inner ring 12, the retainer 14 and the bearing outer ring integrated structure 11;
the bearing outer ring integrated structure 11 comprises a bearing outer ring 110, a mounting edge 111, a first section of cage bar 112a, a second section of cage bar 112b, a supporting web 113, a boss 114 and a temperature measuring hole 115, wherein:
one end of the first section of cage bar 112a is connected to the bearing outer ring 110, and the other end of the first section of cage bar 112a is connected to the lower end of the supporting web 113; one end of the second section of cage bar 112b is connected to the upper end of the supporting web 113, and the other end of the second section of cage bar 112b is connected to the mounting edge 111;
the side end face of the bearing outer ring 110 is provided with N bosses 114;
the side end surface of the bearing outer ring 110 is provided with M temperature measuring holes 115.
Specifically, the M temperature measuring holes 115 are uniformly distributed on the end surface of the bearing outer ring 110.
Specifically, the N bosses 114 are uniformly distributed on the side end surface of the bearing outer ring 110, and the bosses 114 and the temperature measuring holes 115 are located on the same side end surface of the bearing outer ring 110.
Specifically, the temperature measuring hole 115 is not larger than phi 1.5 mm.
Specifically, the number of cage bars of the first-stage cage bar 112a and the second-stage cage bar 112b and the cage bar length L2 are equal, and each cage bar of the first-stage cage bar 112a and the second-stage cage bar 112b corresponds to each other and is in the same radial plane; the cross section of the cage bars of the first section of cage bars 112a and the second section of cage bars 112b is fan-shaped or rectangular.
Specifically, the radial distance H between the upper surface of the first section of cage bar 112a and the lower surface of the second section of cage bar 112b is not less than 8mm, and the distance L1 from the inner side surface of the support web 113 to the mounting edge 111 is not more than 5H.
Specifically, the shortest distance L3 from the bottom of the temperature measuring hole 115 to the bearing outer ring raceway 110a is not less than 3 mm.
Specifically, the mounting edge 111 is located on the right side of the bearing outer ring 110, and a distance L4 from the mounting edge 111 to the bearing outer ring 110 is not less than 2 mm.
The invention has the beneficial effects that: in the embodiment of the invention, the high integration of the bearing outer ring structure (the outer ring, the bearing seat and the squirrel cage structure are integrated), the number of parts is reduced, the axial occupied space is reduced, the processing precision is improved, the processing cost can be reduced by 20-25%, the structure weight is reduced by 10-15%, and the structural reliability of the system is improved.
In the embodiment of the invention, the temperature measuring hole is designed on the side end face of the bearing outer ring, so that the temperature measuring thermocouple is installed closer to the raceway of the bearing outer ring, the problem of inaccurate temperature measurement of the conventional bearing outer ring is solved, and the working reliability of the bearing is improved.
In the embodiment of the invention, the side end face of the bearing outer ring is provided with the boss which is matched with the groove on the casing, so that the squirrel cage bar is protected from being subjected to overlarge unbalanced load and failure, and the working reliability of the squirrel cage bar is improved.
Drawings
FIG. 1 is a schematic view of a prior art mounting for an aircraft engine bearing and support structure.
FIG. 2 is a schematic view of the installation of the bearing and support structure for an aircraft engine of the present invention.
Fig. 3 is a front perspective view of a bearing outer ring integrated structure according to an embodiment of the invention.
Fig. 4 is a reverse perspective view of the bearing outer ring integrated structure in an embodiment of the invention.
Fig. 5 is a sectional view of a bearing outer ring integrated structure according to an embodiment of the present invention.
In the figure: the structure of the bearing comprises a bearing 1, a squirrel cage structure 2, a bearing seat 3, a casing 4, a rotor shaft 5, a bearing outer ring 11, a bearing outer ring 110, a mounting edge 111, a first section of squirrel cage bar 112a, a second section of squirrel cage bar 112b, a bearing web 113, a boss 114, a temperature measuring hole 115, a groove 41, a bearing inner ring 12, a rolling ball 13, a retainer 14 and a bearing outer ring raceway 110 a.
Detailed Description
The invention is further described in the following description with reference to specific embodiments and the accompanying drawings, in which more details are set forth to provide a thorough understanding of the invention, but it will be apparent that the invention can be practiced in many other ways than those specifically described herein, and that a person skilled in the art can make similar generalizations and deductions as to the practice of the invention without departing from the spirit of the invention, and therefore the scope of the invention should not be limited by the contents of this specific embodiment.
It should be noted that fig. 1-5 are intended as examples only and are not intended to be drawn to scale and should not be construed as limiting the scope of the invention as it is actually claimed.
As shown in fig. 3 and 4, the bearing-outer-ring integrated structure 11 includes a bearing outer ring 110, a mounting edge 111, a support web 113, a first section of cage bars 112a, a second section of cage bars 112b, the first section of cage bars 112a are connected to the bearing outer ring 110 at one end thereof and connected to the lower end of the support web 113 at the other end thereof, the second section of cage bars 112b are connected to the upper end of the support web 113 at one end thereof and connected to the mounting edge 111 at the other end thereof.
As shown in fig. 2, which is a schematic view of the installation of the bearing 1 containing the bearing outer ring integrated structure 11 in fig. 3 in the aeroengine, compared with the existing bearing and supporting structure (fig. 1), the bearing outer ring locking nut, the bearing seat and the connecting piece of the bearing seat and the squirrel cage structure are omitted, the number of parts is reduced, the structural weight is reduced to the maximum extent, the installation space is saved, and meanwhile, the bearing outer ring integrated structure 11 enables the disassembly and maintenance to be simpler, and the assembly and the maintainability are improved.
In fig. 2, the bearing inner ring 12 is mounted on the rotor shaft 5, and the rolling elements 13 and the cage 14 are located between the bearing inner ring 12 and the bearing outer ring integrated structure 11. The axial load and part of the radial load of the rotor 5 are transmitted to the bearing outer ring integrated structure 11. The mounting edge 111 of the outer ring integrated structure 11 is connected with the engine bearing case 4 through bolts and nuts, and transmits load to the bearing case 4.
In fig. 3 to 4, the first end cage bar 112a and the second end cage bar 112b are formed by processing in the same process, as many cage bars as possible are adopted on the premise of process permission, the cross section of the cage bar is fan-shaped or rectangular, the length L2, the width and the thickness of the cage bar can be adjusted according to needs, and then the strength and the rigidity of the cage bar are changed to meet the engine rotor dynamics requirements.
In fig. 3, N bosses 114 are uniformly arranged on the end face of the bearing outer ring 110, and the bosses 114 are matched with the grooves 41 on the casing 4 (as shown in fig. 2), so as to protect the squirrel cage bars, avoid the failure of the squirrel cage bars due to an excessive unbalanced load, and improve the reliability of the squirrel cage bars.
In fig. 3 to 5, M temperature measuring holes 115 not greater than phi 1.5 are uniformly distributed on the end surface of the bearing outer ring 110, and the temperature measuring holes 115 and the boss 114 are located on the same end surface of the bearing outer ring 110. The temperature thermocouple is inserted into the temperature measuring hole 115 to measure the temperature of the outer ring of the bearing, so that the problem that the temperature measurement is inaccurate due to the fact that the temperature measuring point of the conventional thermocouple is far away from the outer ring of the bearing is solved, and the working reliability of the bearing is improved.
In fig. 5, the shortest distance L3 from the bottom of the temperature measuring hole 115 to the bearing outer ring raceway 110a is not less than 3mm, so as to ensure the strength of the bearing outer ring raceway.
In fig. 5, the radial distance H between the upper surface of the first section of cage bars 112a and the lower surface of the second section of cage bars 112b is not less than 8mm, the distance L1 from the inner side surface of the support web 113 to the mounting edge 111 is not more than 5H, and the mounting edge 111 is located to the right of the bearing outer ring 110, and the distance L4 from the bearing outer ring 110 is not less than 2 mm. So as to facilitate the processing of the annular cavity between the two sections of the squirrel cage bars and the outer circumference of the outer ring of the bearing.
Although the present invention has been disclosed in terms of the preferred embodiment, it is not intended to limit the invention, and variations and modifications may be made by one skilled in the art without departing from the spirit and scope of the invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.
In summary, the invention belongs to the technical field of design of bearings and supporting structures of aero-engines and gas turbines, and particularly relates to an integrated structure of a bearing and an outer ring. The bearing outer ring integrated structure 11 comprises a bearing outer ring 110, a mounting edge 111, a support web 113 and two sections of cage bars 112, wherein the first section of cage bar 112a is connected to the bearing outer ring 110 at one end and is connected to the support web 113 at the other end, and the second section of cage bar 112b is connected to the support web 113 at one end and is connected to the mounting edge 111 at the other end. Through the high integration (outer lane, bearing frame, squirrel cage structure fuse into an organic whole) to bearing inner race structure, the part number reduces, and the structure becomes compact to easily processing practices thrift the cost, and weight reduction is convenient for engine maintenance, can promote system's reliability. The bearing outer ring 110 is provided with N bosses formed on the side end face of the bearing outer ring, so that the squirrel cage bar is protected in the working process, and the working reliability of the squirrel cage bar is improved; m temperature measuring holes are formed in the side end face of the bearing, and a temperature measuring thermocouple is arranged in each temperature measuring hole to monitor the temperature of the bearing when working, so that the working reliability of the bearing is improved.
According to the integrated structure of the bearing outer ring of the aero-engine and the gas turbine, the outer ring, the bearing seat and the squirrel cage are integrated, the problem of axial design space limitation of the bearing and the supporting structure of the aero-engine is solved, the structure is easy to process, and the processing precision is easy to meet the requirement; and can reduce part quantity, lighten structural weight, the dismouting of being convenient for is maintained to satisfy high thrust-weight ratio engine light in weight, high reliability requirement. Meanwhile, a hole capable of being provided with a temperature thermocouple is designed on the end face of the outer ring, so that the problem of inaccurate temperature measurement of the bearing of the aero-engine is solved, and the working reliability of the bearing is improved.
Claims (4)
1. The utility model provides a bearing and bearing inner race integrated configuration, characterized in that, the bearing includes bearing inner race (12), bearing inner race integrated configuration (11), holder (14) and a plurality of rolling spheroid (13), wherein:
the bearing inner ring (12) is a groove type double-half ferrule with a Golde curvature, a circle of drawing groove is formed on the outer peripheral side of the bearing inner ring (12), a retainer (14) is arranged on the outer circumference of the bearing inner ring (12), a bearing outer ring integrated structure (11) is arranged on the outer circumference of the retainer (14), and a rolling ball (13) is arranged in an inner cavity formed by the bearing inner ring (12), the retainer (14) and the bearing outer ring integrated structure (11);
bearing inner race integrated configuration (11) include bearing inner race (110), installation limit (111), first section squirrel cage strip (112a), second section squirrel cage strip (112b), supporting web (113), boss (114), temperature measurement hole (115), wherein:
one end of the first section of the squirrel cage bar (112a) is connected to the bearing outer ring (110), and the other end of the first section of the squirrel cage bar (112a) is connected to the lower end of the supporting web plate (113); one end of the second section of the squirrel cage bar (112b) is connected to the upper end of the supporting web plate (113), and the other end of the second section of the squirrel cage bar (112b) is connected to the mounting edge (111);
n bosses (114) are arranged on the side end surface of the bearing outer ring (110);
m temperature measuring holes (115) are formed in the side end face of the bearing outer ring (110);
the M temperature measuring holes (115) are uniformly distributed on the side end face of the bearing outer ring (110);
the N bosses (114) are uniformly distributed on the side end face of the bearing outer ring (110), and the bosses (114) and the temperature measuring holes (115) are positioned on the same side end face of the bearing outer ring (110); the boss (114) is matched with the groove (41) on the casing (4) to protect the squirrel cage bar and prevent the squirrel cage bar from being invalid due to overlarge unbalanced load;
the temperature measuring hole (115) is not more than phi 1.5 mm;
the number of cage bars of the first section of cage bar (112a) and the second section of cage bar (112b) and the length L2 of the cage bar are equal, and each cage bar of the first section of cage bar (112a) and the second section of cage bar (112b) is corresponding and in the same radial plane; the cross section of the cage bars of the first section of cage bar (112a) and the second section of cage bar (112b) is fan-shaped or rectangular.
2. The bearing and bearing outer ring integrated structure according to claim 1, characterized in that the radial distance H between the upper surface of the first section of cage bar (112a) and the lower surface of the second section of cage bar (112b) is not less than 8mm, and the distance L1 from the inner side surface of the supporting web (113) to the mounting edge (111) is not more than 5H value.
3. The bearing and bearing outer ring integrated structure according to claim 1, wherein the shortest distance L3 from the bottom of the temperature measuring hole (115) to the bearing outer ring raceway (110a) is not less than 3 mm.
4. The bearing and bearing cup assembly of claim 1, wherein the mounting edge 111 is located at the right side of the bearing cup 110, and the distance L4 from the mounting edge 111 to the bearing cup 110 is not less than 2 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011367852.6A CN112503096B (en) | 2020-11-27 | 2020-11-27 | Bearing and bearing outer ring integrated structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011367852.6A CN112503096B (en) | 2020-11-27 | 2020-11-27 | Bearing and bearing outer ring integrated structure |
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| Publication Number | Publication Date |
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| CN112503096A CN112503096A (en) | 2021-03-16 |
| CN112503096B true CN112503096B (en) | 2022-09-20 |
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| CN202011367852.6A Active CN112503096B (en) | 2020-11-27 | 2020-11-27 | Bearing and bearing outer ring integrated structure |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115539145B (en) * | 2022-08-24 | 2024-10-01 | 中国航发湖南动力机械研究所 | Axial load measurement integrated squirrel-cage elastic support and measurement method |
| CN115789104B (en) * | 2022-12-26 | 2023-06-02 | 北京航空航天大学 | A squirrel cage-bearing integrated structure with adjustable stiffness |
| CN116380337B (en) * | 2023-06-05 | 2023-09-05 | 中国航发四川燃气涡轮研究院 | Axial force calibration device of squirrel-cage stress ring composite structure |
Family Cites Families (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH1130224A (en) * | 1997-07-14 | 1999-02-02 | Ntn Corp | Crankshaft supporting structure of internal combustion engine |
| DE102012221369A1 (en) * | 2012-11-22 | 2014-05-22 | Schaeffler Technologies Gmbh & Co. Kg | roller bearing |
| CN203100949U (en) * | 2013-03-26 | 2013-07-31 | 新昌县产品质量监督检验所 | Rolling bearing friction moment measuring device under low-speed medium-heavy load |
| FR3013387B1 (en) * | 2013-11-20 | 2015-11-20 | Snecma | BEARING SUPPORT HAVING A GEOMETRY FACILITATING THE EVACUATION OF FOUNDRY CORES |
| US9933017B2 (en) * | 2013-12-20 | 2018-04-03 | United Technologies Corporation | Bearing supports |
| CN103742529A (en) * | 2013-12-28 | 2014-04-23 | 瓦房店轴承集团有限责任公司 | Cylindrical roller bearing with punched outer ring without inner ring |
| US9784128B2 (en) * | 2014-04-24 | 2017-10-10 | United Technologies Corporation | Systems and methods for engine bearings |
| CN205315485U (en) * | 2016-01-12 | 2016-06-15 | 中国航空动力机械研究所 | Two -row ball bearing |
| CN108980202A (en) * | 2017-06-01 | 2018-12-11 | 中国航发湖南动力机械研究所 | A kind of roller bearing |
| CN107514428A (en) * | 2017-10-24 | 2017-12-26 | 无锡民联汽车零部件有限公司 | The large size bearing of insertion-type thermocouple thermometric |
| CN108080925B (en) * | 2017-12-26 | 2019-12-24 | 中国航发四川燃气涡轮研究院 | Device and method for disassembling outer ring of roller bearing in annular cavity |
| CN110005545B (en) * | 2019-02-21 | 2020-08-18 | 西安航天动力研究所 | Squirrel-cage elastic supporting bearing cavity structure |
| FR3094048B1 (en) * | 2019-03-18 | 2021-04-23 | Skf Aerospace France | Connecting element, and method of manufacturing a ring for such a connecting element |
| CN110486375B (en) * | 2019-07-30 | 2024-11-29 | 重庆青山工业有限责任公司 | Integrated sealed bearing device |
-
2020
- 2020-11-27 CN CN202011367852.6A patent/CN112503096B/en active Active
Non-Patent Citations (1)
| Title |
|---|
| 某鼠笼弹支一体化球轴承保持架打滑率分析;郑向凯等;《轴承》;20200405(第04期);全文 * |
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