CN114215614A - Engine rotor fulcrum supporting structure - Google Patents
Engine rotor fulcrum supporting structure Download PDFInfo
- Publication number
- CN114215614A CN114215614A CN202111551758.0A CN202111551758A CN114215614A CN 114215614 A CN114215614 A CN 114215614A CN 202111551758 A CN202111551758 A CN 202111551758A CN 114215614 A CN114215614 A CN 114215614A
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- Prior art keywords
- fulcrum
- mounting
- plate
- bearing
- outer ring
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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.)
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Links
- 238000007789 sealing Methods 0.000 claims description 40
- 238000009434 installation Methods 0.000 claims description 30
- 239000010687 lubricating oil Substances 0.000 claims description 23
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 19
- 229910002804 graphite Inorganic materials 0.000 claims description 19
- 239000010439 graphite Substances 0.000 claims description 19
- 230000004323 axial length Effects 0.000 claims description 7
- 239000007787 solid Substances 0.000 claims description 3
- 238000005299 abrasion Methods 0.000 abstract description 5
- 230000006835 compression Effects 0.000 description 5
- 238000007906 compression Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 2
- 239000003921 oil Substances 0.000 description 2
- 238000001816 cooling Methods 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000001050 lubricating effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
- F01D25/183—Sealing means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Rolling Contact Bearings (AREA)
Abstract
The application relates to the field of supporting of aero-engines, in particular to an engine rotor fulcrum supporting structure which is arranged between an engine rotor and a rear cover and comprises a fulcrum outer ring and a second force bearing component, wherein a mounting side plate is integrally combined on the fulcrum outer ring of a bearing, a first mounting ring plate is arranged on the second force bearing component and is matched with the mounting side plate through a seam allowance, threaded holes are formed in the first mounting ring plate and the mounting side plate, bolts and second nuts which are axially arranged are arranged at the threaded holes to fix the first mounting ring plate and the mounting side plate mutually, the deformation of the second force bearing component is mainly born by the mounting side plate, and the deformation influence on other positions of the fulcrum outer ring is small, so that the connection and positioning reliability of the fulcrum and the second force bearing component can be effectively improved, and the connection and stable positioning of the fulcrum outer ring and the second force bearing component in the full working condition range are ensured, the problems of outer ring looseness, bearing abrasion and the like are prevented.
Description
Technical Field
The application belongs to the field of aero-engine supporting, and particularly relates to an engine rotor fulcrum supporting structure.
Background
The supporting point of the aircraft engine comprises a main bearing, a bearing supporting structure (bearing seat), a lubricating oil feeding and returning structure for cooling and lubricating the bearing, a sealing structure for preventing lubricating oil from leaking into an airflow channel and high-temperature gas from leaking into a bearing cavity and the like. The engine fulcrum is mainly used for supporting the rotor and transferring the load of the rotor outwards, and the stable operation of the engine is directly influenced by the connection reliability of the fulcrum bearing and the first bearing component due to high rotating speed and large load of the fulcrum bearing.
The connection structure of the traditional fulcrum bearing outer ring and a first bearing component is shown in fig. 1, and the traditional fulcrum bearing outer ring 1 is generally a bearing outer ring without a mounting edge. The load of the engine rotor 10 is transmitted to the first force-bearing component 5 through the fulcrum bearing inner ring 4, the bearing roller 2, the retainer 3, the fulcrum bearing outer ring 1 and the fulcrum bearing outer ring 1. The fulcrum bearing outer ring 1 is connected with the first force bearing component 5 in a radial matching and axial pressing mode through the first nut 11. The lubricating oil nozzle 8 realizes bearing oil supply, and the graphite sealing component 6, the sealing runway 7 and the rear cover 9 realize lubricating oil sealing.
The fulcrum structure of the existing scheme is that a bearing outer ring ferrule is sleeved in a first bearing component, and fulcrum positioning and rotation prevention are realized through the radial matching tightness of an outer ring and the first bearing component and the axial pressing force of a first nut. In the working process, the ambient temperature around the fulcrum and the heating value of the bearing change along with the working condition of the engine, particularly the using working condition of a military engine is complex, and the radial deformation of the bearing outer ring and the bearing supporting structure is different, so that the radial matching and the axial compression state of the outer ring and the first bearing component can be changed. The radial fit tightness and axial pressing force control of the bearing outer ring and the bearing structure are technical difficulties of the prior technical scheme, and the radial fit tightness and axial pressing force control are improper to influence the radial positioning and axial pressing reliability of the bearing. If the radial fit tightness is smaller, the outer ring becomes loose, so that the problems of bearing abrasion and the like are caused, and the safe operation of the engine is influenced; if the radial fit tightness is larger, the assembly difficulty is brought, the radial clearance of the bearing is influenced, and the working reliability of the bearing is also influenced. Meanwhile, the axial pretightening force for axially compressing the first nut is limited by the thread stress, and the reliable positioning of the outer ring cannot be ensured.
Therefore, how to more effectively realize radial positioning and axial compression is a problem to be solved.
Disclosure of Invention
The application aims at providing an engine rotor fulcrum supporting structure to solve the problems that in the prior art, the bearing is slightly small in fit tightness with a second bearing component and bearing abrasion is easily caused, and the radial clearance of the bearing is influenced due to the fact that the bearing is large in fit tightness with the second bearing component.
The technical scheme of the application is as follows: the utility model provides an engine rotor fulcrum bearing structure, locates between engine rotor and the back lid, includes fulcrum outer loop and second load member, be equipped with annular installation sideboard on the fulcrum outer loop, the installation sideboard is located one side that the engine rotor was kept away from to the fulcrum outer loop, be equipped with first installation crown plate on the second load member, first installation crown plate pastes and cooperates through the tang with the installation crown plate, set up the screw hole that corresponds the setting on first installation crown plate and the installation crown plate, install the bolt that sets up along the engine axial in the screw hole, the head and the first installation crown plate of bolt paste, the nut that pastes with the installation crown plate is installed to the end of bolt, bolt and nut all have the multiunit and set up along the even interval of circumference of fulcrum outer loop.
Preferably, the mounting side plate is arranged on one side of the fulcrum outer ring away from the engine rotor.
Preferably, a lubricating oil flow path is arranged in the second force bearing component, the lubricating oil flow path comprises a radial flow path and an oblique flow path communicated with the radial flow path, a horizontal flow path is arranged in the lubricating oil nozzle, and the horizontal flow path and the oblique flow path are in mutual contact and are communicated with each other.
Preferably, a second mounting ring plate is arranged on the second force bearing component, an L-shaped mounting ring is arranged on the second mounting ring plate, the mounting ring comprises an axially arranged plate body and a radially arranged plate body which are connected with the second mounting ring plate, and the rear cover is connected with the radially arranged plate body of the mounting ring.
Preferably, the graphite sealing component is further included, an annular mounting block is arranged on the side wall of the second force-bearing component, the mounting block is of a solid structure, and the graphite sealing component is connected with the mounting block.
Preferably, graphite seal assembly includes sealed piece, locates the snap ring in the sealed piece outside, the snap ring pastes with the side of installation piece mutually, sealed piece pastes with the inboard limit of installation piece mutually, the axial length that the side to the snap ring that the installation piece one side was kept away from to sealed piece is greater than the axial length that the side to the snap ring that sealed piece is close to installation piece one side.
Preferably, the mounting block further comprises a sealing track which is L-shaped and connected with the sealing block, and one end of the sealing track, close to the second force bearing component, is positioned on the inner side of the mounting block.
The utility model provides an engine rotor fulcrum bearing structure, locate between engine rotor and the back lid, including fulcrum outer loop and second load-carrying member, through the installation sideboard of integrative combination on the fulcrum outer loop of bearing, set up first installation crown plate and installation sideboard and pass through the tang cooperation on the second load-carrying member, and set up the screw hole on first installation crown plate and installation sideboard, set up bolt and second nut along axial setting at the screw hole department and fix first installation crown plate and installation sideboard each other, the deflection of second load-carrying member is mainly born by the installation sideboard, the deformation influence that other positions of fulcrum outer loop received is less, therefore can effectively improve the connection of fulcrum outer loop and second load-carrying member, guarantee that the connection of full operating mode within range fulcrum outer loop and second load-carrying member and location are stable and reliable, prevent to appear not hard up the outer loop, bearing wear and the like.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic diagram of the overall structure of the background art;
fig. 2 is a schematic view of the overall structure of the present application.
1. A fulcrum bearing outer ring; 2. a bearing roller; 3. a holder; 4. a fulcrum bearing inner ring; 5. a first force-bearing member; 6. a graphite seal assembly; 7. sealing the runway; 8. a lubricating oil nozzle; 9. a rear cover; 10. an engine rotor; 11. a first nut; 12. installing a side plate; 13. a second force-bearing member; 14. a first mounting ring plate; 15. a second mounting ring plate; 16. a mounting ring; 17. a radial flow passage; 18. an oblique flow passage; 19. mounting blocks; 20. a sealing block; 21. a snap ring; 22. a bolt; 23. a fulcrum outer ring; 24. a second nut.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
A fulcrum supporting structure of an engine rotor is arranged between an engine rotor 10 and a rear cover 9, as shown in figure 2, a fulcrum bearing inner ring 4 and a bearing roller 2 are arranged between the engine rotor 10 and a fulcrum outer ring 23, the bearing roller 2 is arranged between the fulcrum bearing inner ring 4 and the fulcrum outer ring 23, a retainer 3 is arranged on the outer side of the bearing roller 2, and the fulcrum outer ring 23, the bearing roller 2, the retainer 3 and the fulcrum bearing inner ring 4 form a complete bearing.
The axial direction and the radial direction are the axial direction and the radial direction of the central line of the engine.
With reference to fig. 1, it can be known from analysis of the existing structure that, except for the inner side of the outer ring 1 of the fulcrum bearing, the left and right sides and the outer side of the outer ring 1 of the fulcrum bearing are both in contact with the first force-bearing member 5 or the first nut 11, and when the first force-bearing member 5 and the first nut 11 are deformed by heat, the outer ring 1 of the fulcrum bearing is greatly affected, which also brings about the problems of bearing wear and bearing radial play change. If after the bearing is stably positioned in the radial direction and pressed in the axial direction, the contact surface between the outer ring 1 of the fulcrum bearing and the first bearing component 5 is greatly reduced or is not contacted at all, so that the first bearing component 5 and the first nut 11 can not bring the problems of abrasion and radial play of the bearing to the bearing.
The specific design based on the thought is as follows: the engine rotor mounting structure is characterized in that an annular mounting side plate 12 arranged along the radial direction is arranged on the fulcrum outer ring 23, the mounting side plate 12 is located on one side, away from the engine rotor 10, of the fulcrum outer ring 23, a first mounting ring plate 14 is arranged on the second force bearing component 13, a connecting plate arranged along the radial direction is arranged on the first mounting ring plate 14, the radial connecting plate is attached to the mounting side plate 12 and matched with the mounting side plate through a spigot, threaded holes correspondingly arranged are formed in the first mounting ring plate 14 and the mounting side plate 12, bolts 22 arranged along the axial direction of the engine are installed in the threaded holes, the heads of the bolts 22 are attached to the first mounting ring plate 14, second nuts 24 attached to the mounting side plate 12 are installed at the tail ends of the bolts 22, and the bolts 22 and the second nuts 24 are arranged in multiple groups and evenly spaced along the circumferential direction of the fulcrum outer ring 23.
The annular mounting side plate 12 is arranged on the fulcrum outer ring 23, the mounting side plate 12 is connected with the second force bearing member 13, the second force bearing member 13 is matched with the spigot to realize radial positioning of the mounting side plate 12, the bolt 22 and the second nut 24 are used for axial compression of the mounting side plate 12, and radial positioning and axial compression of the fulcrum outer ring 23 are also realized.
The connecting positions of the existing first bearing member 5 and the fulcrum bearing outer ring 1 are all in spigot fit, the spigot fit is realized only by the first mounting ring plate 14 and the mounting side plate 12 of the fulcrum outer ring 23 and the second bearing member 13 of the invention, so the required interference is smaller, the bolt 22 axially compresses the fulcrum outer ring 23 through the mounting side plate 12, when the fulcrum outer ring 23 and the second bearing member 13 deform due to heating or other working conditions, the deformation generated by the second bearing member 13 is mainly borne by the mounting side plate 12 and the spigot structure, the radial deformation of other parts of the fulcrum outer ring 23 is influenced by the second bearing member 13 very little, the deformation of the fulcrum outer ring 23 is in the range that the bearing can bear, so the radial fit and the axial compression state of the fulcrum outer ring 23 and the second bearing member 13 cannot change, the radial fit tightness and the axial pressing force of the fulcrum outer ring 23 and the second bearing member 13 can be always ensured, the reliability of the connection of the fulcrum outer ring 23 and the second bearing member 13 is improved, the connection and the positioning of the fulcrum outer ring 23 and the second bearing member 13 in the whole working condition range are ensured to be stable and reliable, and the problems of outer ring looseness, bearing abrasion and the like are prevented; meanwhile, the radial fit tightness is smaller, so that the influence of the radial fit tightness of the outer ring on the working clearance of the bearing can be effectively reduced, and the assembly and decomposition manufacturability of the outer ring is improved.
In the invention, the connection tightness of the fulcrum outer ring 23 and the second bearing member 13 is greatly reduced, so that the space required by the supporting structure between the fulcrum outer ring 23 and the second bearing member 13 is also effectively reduced, the distances between the structures around the fulcrum outer ring 23 and the second bearing member 13 and the fulcrum outer ring 23 and the second bearing member 13 are also smaller, and the matching is also tighter.
Preferably, the mounting side plate 12 is arranged on the side of the fulcrum outer ring 23 far away from the engine rotor 10, so that the influence degree of the fulcrum outer ring 23 from other positions is further reduced, the fit tightness of the fulcrum outer ring 23 and the second force-bearing member 13 is smaller, the influence is smaller, and the performance of the fulcrum outer ring 23 per se is better maintained.
Preferably, the second force bearing member 13 is provided with a lubricating oil flow path therein, the lubricating oil flow path includes a radial flow path 17 and an oblique flow path 18 communicated with the radial flow path 17, the lubricating oil nozzle 8 is provided with a horizontal flow path therein, and the horizontal flow path and the oblique flow path 18 are in contact with each other and are communicated with each other. Because the space required by the first mounting ring plate 14 and the mounting side plate 12 is smaller, the design of the lubricating oil flow path can be closer to the fulcrum outer ring 23, compared with the existing flow path which is arranged in an inverted T shape, the flow path for arranging the radial flow path 17 and the oblique flow path 18 is shorter, compared with the existing flow path, the flow loss is smaller, and the lubricating oil nozzle 8 can supply oil to the bearing more efficiently.
Preferably, the second force-bearing member 13 is provided with a second mounting ring plate 15, the second mounting ring plate 15 is provided with an L-shaped mounting ring 16, the mounting ring 16 includes a first plate body axially arranged and a second plate body radially arranged, and the first plate body is connected with the second mounting ring plate 15, and the rear cover 9 is connected with the second plate body radially arranged and the mounting ring 16. Because the existing lubricating oil flow path is far away from the bearing, the rear cover needs to be attached to the outlet of the lubricating oil flow path on the first force bearing component, and the sealing effect on the lubricating oil flow path is achieved; and the lubricating oil flow path in the second force bearing component 13 is closer to the bearing now, and the back cover 9 is not needed to be closed, so that the back cover 9 only needs to support and close the whole structure, and the function of the back cover 9 is more stable due to less functions.
Preferably, the graphite sealing component 6 and the side wall of the second force bearing component 13 are provided with an annular mounting block 19, the mounting block 19 is a solid structure, and the graphite sealing component 6 is connected with the mounting block 19. Graphite seal assembly 6 plays the sealed effect of lubricating oil, because installation piece 19 is the entity structure, the cooperation can be inseparabler between graphite seal assembly 6 and the installation piece 19, and the sealed effect of lubricating oil is also better.
Preferably, the graphite sealing assembly 6 includes a sealing block 20 and a snap ring 21 disposed outside the sealing block 20, the snap ring 21 is attached to the side of the mounting block 19, the sealing block 20 is attached to the inner side of the mounting block 19, and the axial length from the side of the sealing block 20 away from the mounting block 19 to the snap ring 21 is greater than the axial length from the side of the sealing block 20 close to the mounting block 19 to the snap ring 21. Because the graphite sealing assembly 6 can play a better sealing role in cooperation with the mounting block 19, the side with the larger axial length of the sealing block 20 can be close to the engine rotor 10, so that the distance between the graphite sealing assembly 6 and the engine rotor 10 is smaller, and the graphite sealing assembly 6 is more stably fixed.
Preferably, the sealing device further comprises a sealing track 7, wherein the sealing track 7 is L-shaped, the sealing track 7 is connected with a sealing block 20, and one end of the sealing track 7, which is close to the second force bearing component 13, is positioned on the inner side of the mounting block 19. Because graphite seal assembly 6 is closer to engine rotor 10, the length of sealing runway 7 that supports graphite seal assembly 6 also shortens correspondingly, and sealing runway 7 is higher to graphite seal assembly 6's support intensity, and it is also better to the sealed effect of lubricating oil.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. The utility model provides an engine rotor fulcrum bearing structure, locates between engine rotor (10) and back lid (9), including fulcrum outer loop (23) and second load member (13), its characterized in that: an annular mounting side plate (12) is arranged on the fulcrum outer ring (23), the mounting side plate (12) is positioned on one side of the fulcrum outer ring (23) far away from the engine rotor (10), a first mounting ring plate (14) is arranged on the second bearing component (13), the first mounting ring plate (14) is attached to the mounting side plate (12) and matched with the mounting side plate through a seam allowance, the first mounting ring plate (14) and the mounting side plate (12) are provided with correspondingly arranged threaded holes, a bolt (22) arranged along the axial direction of the engine is arranged in the threaded hole, the head of the bolt (22) is attached to the first mounting ring plate (14), the tail end of the bolt (22) is provided with a second nut (24) which is attached to the mounting side plate (12), the bolts (22) and the second nuts (24) are provided with multiple groups and are uniformly arranged along the circumferential direction of the fulcrum outer ring (23) at intervals.
2. The engine rotor fulcrum support structure of claim 1, wherein: the mounting side plate (12) is arranged on one side, away from the engine rotor (10), of the fulcrum outer ring (23).
3. The engine rotor fulcrum support structure of claim 1, wherein: and a lubricating oil flow path is arranged in the second force bearing component (13), the lubricating oil flow path comprises a radial flow path (17) and an oblique flow path (18) communicated with the radial flow path (17), a horizontal flow path is arranged in the lubricating oil nozzle (8), and the horizontal flow path and the oblique flow path (18) are mutually contacted and communicated.
4. The engine rotor fulcrum support structure according to claim 3, wherein: be equipped with second installation crown plate (15) on second load member (13), be equipped with the collar (16) of L shape on second installation crown plate (15), collar (16) include the first plate body of the axial setting that links to each other with second installation crown plate (15), the second plate body of radial setting, back lid (9) link to each other with the second plate body of collar (16) radial setting.
5. The engine rotor fulcrum support structure according to claim 3, wherein: the bearing component is characterized by further comprising a graphite sealing component (6), an annular mounting block (19) is arranged on the side wall of the second bearing component (13), the mounting block (19) is of a solid structure, and the graphite sealing component (6) is connected with the mounting block (19).
6. The engine rotor fulcrum support structure of claim 5, wherein: graphite seal assembly (6) including sealed piece (20), locate snap ring (21) outside sealed piece (20), snap ring (21) paste mutually with the side of installation piece (19), sealed piece (20) paste mutually with the inboard limit of installation piece (19), sealed piece (20) are kept away from the side of installation piece (19) one side to the axial length of snap ring (21) and are greater than sealed piece (20) and are close to the side of installation piece (19) one side to the axial length of snap ring (21).
7. The engine rotor fulcrum support structure of claim 6, wherein: the bearing block is characterized by further comprising a sealing track (7), the sealing track (7) is L-shaped, the sealing track (7) is connected with a sealing block (20), and one end, close to the second force bearing component (13), of the sealing track (7) is located on the inner side of the mounting block (19).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111551758.0A CN114215614A (en) | 2021-12-17 | 2021-12-17 | Engine rotor fulcrum supporting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111551758.0A CN114215614A (en) | 2021-12-17 | 2021-12-17 | Engine rotor fulcrum supporting structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114215614A true CN114215614A (en) | 2022-03-22 |
Family
ID=80703590
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111551758.0A Pending CN114215614A (en) | 2021-12-17 | 2021-12-17 | Engine rotor fulcrum supporting structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114215614A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114575930A (en) * | 2022-05-06 | 2022-06-03 | 中国航发沈阳发动机研究所 | Supporting structure for intermediate fulcrum outer ring of engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100158699A1 (en) * | 2008-12-22 | 2010-06-24 | Jerzy Makuszewski | Rotor mounting system for gas turbine engine |
| US20160238137A1 (en) * | 2013-12-20 | 2016-08-18 | United Technologies Corporation | Seal runner |
| CN205714304U (en) * | 2016-04-20 | 2016-11-23 | 中国科学院工程热物理研究所 | A kind of electromotor low pressure rotor supporting structure |
| CN109281944A (en) * | 2018-10-19 | 2019-01-29 | 中国科学院工程热物理研究所 | The axial force pre-load arrangement of deep groove ball bearing in a kind of engine rotor fulcrum |
| CN110651103A (en) * | 2017-05-18 | 2020-01-03 | 赛峰航空器发动机 | Device for centering and rotationally guiding a turbine shaft pair, comprising means for axially retaining a bearing outer ring |
| US20200072081A1 (en) * | 2018-08-28 | 2020-03-05 | Safran Aircraft Engines | Turbomachine with axial force adjustment at a bearing |
| CN112161062A (en) * | 2020-09-27 | 2021-01-01 | 中国航发湖南动力机械研究所 | Combined sealing structure |
| CN112727994A (en) * | 2020-12-25 | 2021-04-30 | 中国船舶重工集团公司第七0三研究所 | Adjustable squeeze film damper |
-
2021
- 2021-12-17 CN CN202111551758.0A patent/CN114215614A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100158699A1 (en) * | 2008-12-22 | 2010-06-24 | Jerzy Makuszewski | Rotor mounting system for gas turbine engine |
| US20160238137A1 (en) * | 2013-12-20 | 2016-08-18 | United Technologies Corporation | Seal runner |
| CN205714304U (en) * | 2016-04-20 | 2016-11-23 | 中国科学院工程热物理研究所 | A kind of electromotor low pressure rotor supporting structure |
| CN110651103A (en) * | 2017-05-18 | 2020-01-03 | 赛峰航空器发动机 | Device for centering and rotationally guiding a turbine shaft pair, comprising means for axially retaining a bearing outer ring |
| US20200072081A1 (en) * | 2018-08-28 | 2020-03-05 | Safran Aircraft Engines | Turbomachine with axial force adjustment at a bearing |
| CN109281944A (en) * | 2018-10-19 | 2019-01-29 | 中国科学院工程热物理研究所 | The axial force pre-load arrangement of deep groove ball bearing in a kind of engine rotor fulcrum |
| CN112161062A (en) * | 2020-09-27 | 2021-01-01 | 中国航发湖南动力机械研究所 | Combined sealing structure |
| CN112727994A (en) * | 2020-12-25 | 2021-04-30 | 中国船舶重工集团公司第七0三研究所 | Adjustable squeeze film damper |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114575930A (en) * | 2022-05-06 | 2022-06-03 | 中国航发沈阳发动机研究所 | Supporting structure for intermediate fulcrum outer ring of engine |
| CN114575930B (en) * | 2022-05-06 | 2022-08-19 | 中国航发沈阳发动机研究所 | Supporting structure for intermediate fulcrum outer ring of engine |
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