CN110056571B - Coupled bidirectional thrust oil film damper supporting system for gas turbine - Google Patents
Coupled bidirectional thrust oil film damper supporting system for gas turbine Download PDFInfo
- Publication number
- CN110056571B CN110056571B CN201910436248.5A CN201910436248A CN110056571B CN 110056571 B CN110056571 B CN 110056571B CN 201910436248 A CN201910436248 A CN 201910436248A CN 110056571 B CN110056571 B CN 110056571B
- Authority
- CN
- China
- Prior art keywords
- thrust
- bearing seat
- gas turbine
- oil film
- squirrel cage
- 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.)
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- 230000002457 bidirectional effect Effects 0.000 title claims abstract description 30
- 241000555745 Sciuridae Species 0.000 claims abstract description 32
- 230000008878 coupling Effects 0.000 claims abstract description 10
- 238000010168 coupling process Methods 0.000 claims abstract description 10
- 238000005859 coupling reaction Methods 0.000 claims abstract description 10
- 238000007789 sealing Methods 0.000 claims description 7
- 230000000712 assembly Effects 0.000 claims description 4
- 238000000429 assembly Methods 0.000 claims description 4
- 239000003921 oil Substances 0.000 description 51
- 239000010687 lubricating oil Substances 0.000 description 6
- 239000011159 matrix material Substances 0.000 description 4
- 238000009434 installation Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
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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
-
- 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
- F16C17/00—Sliding-contact bearings for exclusively rotary movement
- F16C17/04—Sliding-contact bearings for exclusively rotary movement for axial load only
-
- 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
- F16C21/00—Combinations of sliding-contact bearings with ball or roller bearings, for exclusively rotary movement
-
- 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
- F16F15/0237—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 involving squeeze-film damping
-
- 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
- F16C2360/00—Engines or pumps
- F16C2360/23—Gas turbine engines
-
- 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
- F16F2222/00—Special physical effects, e.g. nature of damping effects
- F16F2222/12—Fluid damping
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Aviation & Aerospace Engineering (AREA)
- Support Of The Bearing (AREA)
Abstract
A coupling bidirectional thrust oil film damper supporting system for a gas turbine relates to a coupling bidirectional thrust oil film damper supporting system, in particular to a coupling bidirectional thrust oil film damper supporting system for a gas turbine. The invention aims to solve the problem that the service life of a roller bearing is greatly reduced due to the increased bidirectional axial force of marine and industrial gas turbines. The invention comprises a squirrel cage bearing seat, a roller bearing and a bolt, and also comprises a thrust disc assembly and an oil retainer, wherein a damper is sleeved on the squirrel cage bearing seat, the squirrel cage bearing seat is sleeved on the thrust disc assembly, the roller bearing and the oil retainer are arranged in a cantilever end of the squirrel cage bearing seat, and the damper is arranged on a stator component of the compressor through the bolt. The invention belongs to the field of energy power.
Description
Technical Field
The invention relates to a coupling bidirectional thrust oil film damper supporting system, in particular to a coupling bidirectional thrust oil film damper supporting system for a gas turbine, and belongs to the field of energy and power.
Background
The front supporting part of the high-pressure compressor of the traditional medium-sized gas turbine is supported by only adopting a ball bearing with larger diameter to be matched with an oil film damper, and the structure is simpler. The ball bearing is capable of bearing large radial force and axial force, but can only bear small axial force due to the limitations of the structure and the materials. When the gas turbine is used as a master machine to design a larger power machine type, the axial force is increased along with the power increase, the service life of the ball bearing is greatly reduced, and the use requirement is not met, and because the position is subjected to bidirectional axial force, a new supporting system which can realize bidirectional thrust and reduce the vibration of the gas turbine is required to be redesigned.
Disclosure of Invention
The invention aims to solve the problem that the service life of a roller bearing is greatly reduced due to the increased bidirectional axial force of a marine and industrial gas turbine, and further provides a coupled bidirectional thrust oil film damper supporting system for the gas turbine.
The technical scheme adopted by the invention for solving the problems is as follows: the invention comprises a squirrel cage bearing seat, a roller bearing and a bolt, and also comprises a thrust disc assembly and an oil retainer, wherein a damper is sleeved on the squirrel cage bearing seat, the squirrel cage bearing seat is sleeved on the thrust disc assembly, the roller bearing and the oil retainer are arranged in a cantilever end of the squirrel cage bearing seat, and the damper is arranged on a stator component of the compressor through the bolt.
Further, the thrust disc assembly comprises a thrust disc, a front thrust pad matrix, a high-pressure front thrust bearing seat, a rear thrust pad matrix and a high-pressure rear thrust bearing seat, wherein the high-pressure front thrust bearing seat and the front thrust pad matrix are sequentially arranged in front of the thrust disc from front to back, and the rear thrust pad matrix and the high-pressure rear thrust bearing seat are sequentially arranged behind the thrust disc from front to back.
Further, the thrust disc assembly further comprises nine sets of tile assemblies, each set of tile assembly comprises two main supporting blocks and four elastic supporting plates, two elastic supporting plates and one main supporting block are sequentially arranged between the front thrust tile base body and the high-pressure front thrust bearing seat from outside to inside, and two elastic supporting plates and one main supporting block are sequentially arranged between the rear thrust tile base body and the high-pressure rear thrust bearing seat from outside to inside.
Further, the invention also includes a moving ring mounted on the outer side of the inner roller bearing ring.
Further, the invention also comprises a bushing which is sleeved on the roller bearing, and the bushing is positioned between the outer surface of the roller bearing and the inner surface of the squirrel cage bearing seat.
Further, the invention also comprises a ring nut arranged between the inner ring of the roller bearing and the thrust disk
Further, the invention also comprises a pin which is arranged on the inner side surface of the thrust disc.
Furthermore, the invention also comprises two sealing rings which are sleeved on the outer wall of the squirrel cage bearing seat side by side. .
The beneficial effects of the invention are as follows: the bearing system can reduce the vibration of the gas turbine while bearing larger bidirectional axial force, and solves the problem that the service life of the ball bearing in the traditional damper bearing structure is reduced because the ball bearing cannot bear larger axial force; the invention can simultaneously realize bidirectional thrust of the front supporting position and reduce vibration of the gas turbine, and meets the service life requirement of the roller bearing.
Drawings
Fig. 1 is a schematic view of the assembly of the present invention.
Detailed Description
The first embodiment is as follows: referring to fig. 1, the embodiment is described as a coupled bidirectional thrust oil film damper supporting system for a gas turbine, which includes a squirrel cage bearing seat 6, a roller bearing 11, a bolt 15, a thrust disk assembly and a slinger 9, wherein a damper 18 is sleeved on the squirrel cage bearing seat 6, the squirrel cage bearing seat 6 is sleeved on the thrust disk assembly, the roller bearing 11 and the slinger 9 are mounted in a cantilever end of the squirrel cage bearing seat 6, and the damper 18 is mounted on a compressor stator component through the bolt 15.
In the embodiment, the oil retainer 9 is arranged in the cantilever end of the squirrel cage bearing seat 6 through a nut 7 and a stop washer 8; the squirrel cage bearing seat 6, the roller bearing 11, the oil retainer ring, the nut 7 and the stop washer 8 form an oil film damper supporting system together, and the concentric state of the rotor and the coupled bidirectional thrust oil film damper supporting system is ensured through the pre-eccentric design.
In the embodiment, the machining center line of the cantilever end of the squirrel-cage bearing seat 6 is slightly higher than the center line of the installation positioning surface of the squirrel-cage bearing seat, so that the centering of the rotor is ensured.
In this embodiment, the damper 18 returns oil through a plurality of shaped grooves and holes at the upper part below the right end, and a plurality of semicircular holes and a plurality of shaped grooves are formed above and below the inlet position of the cantilever end to increase the oil return effect.
When the gas turbine works, the gap between the damper and the squirrel-cage bearing seat is filled with lubricating oil, the end part of the sealing ring is controlled to drain oil, and the cantilever end of the specially designed squirrel-cage bearing seat is internally provided with a roller bearing, a nut, a stop washer and an oil retainer which are used for supporting a rotor and a shaft neck, so that an oil film damper supporting system is formed together, and the concentric state of the rotor and the coupled bidirectional thrust oil film damper supporting system is ensured through the pre-eccentric design. The high-pressure rear thrust bearing is fixedly arranged on the squirrel cage bearing seat through bolts, and the thrust disc and the roller bearing are tightly pressed through collar nuts, so that a coupled bidirectional thrust oil film damper supporting system is formed.
The second embodiment is as follows: referring to fig. 1, a thrust disc assembly of a coupled bidirectional thrust oil film damper support system for a gas turbine according to the present embodiment includes a thrust disc 1, a front thrust pad body 2, a high-pressure front thrust bearing housing 3, a rear thrust pad body 4, and a high-pressure rear thrust bearing housing 5, wherein the high-pressure front thrust bearing housing 3 and the front thrust pad body 2 are sequentially mounted in front of the thrust disc 1 from front to back, and the rear thrust pad body 4 and the high-pressure rear thrust bearing housing 5 are sequentially mounted in rear of the thrust disc 1 from front to back.
In the present embodiment, the thrust disc 1 and the roller bearing 11 are pressed together to form a coupled bidirectional thrust oil film damper support system.
In this embodiment, the oil enters the ring groove through the oil supply hole on the housing of the squirrel cage bearing seat 6, the oil is sprayed onto the roller bearing 11 through the internal oil path and the nozzle, the oil is sprayed onto the upper surface of the bushing through the internal oil path and flows out through the gap between the left end of the bushing 12 and the squirrel cage bearing seat 6, the oil is sprayed onto the thrust pad through the thrust bearing nozzle through the internal oil path, and the oil is returned through the plurality of special grooves at the lower part of the flange surface.
Other components and connection relationships are the same as those of the first embodiment.
And a third specific embodiment: referring to fig. 1, the thrust disc assembly of the coupling bidirectional thrust oil film damper supporting system for a gas turbine according to the present embodiment further includes nine sets of pad assemblies, each set of pad assemblies includes two main supporting blocks 17 and four elastic supporting blocks 16, two elastic supporting blocks 16 and one main supporting block 17 are sequentially disposed between the front pad body 2 and the high-pressure front thrust bearing block 3 from outside to inside, and two elastic supporting blocks 16 and one main supporting block 17 are sequentially disposed between the rear pad body 4 and the high-pressure rear thrust bearing block 5 from outside to inside.
Other components and connection relationships are the same as those of the second embodiment.
The specific embodiment IV is as follows: the coupled bidirectional thrust oil film damper support system for a gas turbine according to the present embodiment further includes a moving ring 10, and the moving ring 10 is mounted on an outer side surface of an inner ring of a roller bearing 11, described with reference to fig. 1.
Other components and connection relationships are the same as those of the first embodiment.
Fifth embodiment: the coupled bidirectional thrust oil film damper supporting system for a gas turbine according to the present embodiment further includes a bushing 12, wherein the bushing 12 is sleeved on the roller bearing 11, and the bushing 12 is located between the outer surface of the roller bearing 11 and the inner surface of the squirrel cage bearing seat 6, as described in connection with fig. 1.
In the present embodiment, the lubricating oil is sprayed onto the roller bearing 11 through the oil passage inside the ring groove by the nozzle; the lubricating oil is sprayed to the upper surface of the bushing 12 through an oil way in the ring groove, and flows out through a gap of 0.5mm between the left end of the bushing 12 and the squirrel cage bearing seat 6; oil return is performed through a plurality of special-shaped grooves at the lower part of the flange surface.
Other components and connection relationships are the same as those of the first embodiment.
Specific embodiment six: the coupled bidirectional thrust oil film damper support system for a gas turbine according to the present embodiment further includes a ring nut 13, and the ring nut 13 is disposed between the inner ring of the roller bearing 11 and the thrust disk 1, as described in the present embodiment with reference to fig. 1.
In the present embodiment, the thrust disc 1 and the roller bearing 11 are compressed by the collar nut 13, so as to form a coupled bidirectional thrust oil film damper supporting system.
Other components and connection relationships are the same as those of the first or second embodiment.
Seventh embodiment: the coupled bidirectional thrust oil film damper support system for a gas turbine according to the present embodiment further includes a pin 14, and the pin 14 is mounted on the inner side surface of the thrust disk 1, described with reference to fig. 1.
Other components and connection relationships are the same as those of the first embodiment.
Eighth embodiment: referring to fig. 1, the supporting system of the coupling bidirectional thrust oil film damper for the gas turbine according to the present embodiment further includes two sealing rings 19, where the two sealing rings 19 are sleeved on the outer wall of the squirrel cage bearing seat 6 side by side.
In this embodiment, the seal ring 19 is made of metal to control the oil leakage amount at both ends of the damper 18, thereby forming an oil film damper system.
Other components and connection relationships are the same as those of the first embodiment.
Principle of operation
During operation of the gas turbine, the stator component in the transition section supplies oil to the high-pressure front thrust bearing, and an oil wedge is formed in the axial direction so as to bear forward axial force. The squirrel cage bearing seat is supplied with oil through an oil supply pipe arranged on the stator component, the lubricating oil enters an inner annular groove through a squirrel cage bearing seat shell, the high-pressure rear thrust bearing is supplied with oil through a nozzle arranged on the high-pressure rear thrust bearing seat, and an oil wedge is formed in the axial direction and used for bearing the backward axial force. The lubricating oil enters a gap between the lubricating oil and the damper through an annular groove oil way, the grooves on the two sides are provided with metal sealing rings to control the oil leakage quantity at the two ends of the damper, and part of rotor vibration energy is absorbed through extrusion of an oil film. The processing center line of the cantilever end of the squirrel cage bearing seat is slightly higher than the center line of the installation positioning surface of the squirrel cage bearing seat, so that the centering of the rotor is ensured.
The present invention is not limited to the preferred embodiments, but is capable of modification and variation in detail, and other embodiments, such as those described above, of making various modifications and equivalents will fall within the spirit and scope of the present invention.
Claims (3)
1. The utility model provides a gas turbine is with coupling two-way thrust oil film damper braced system, it includes squirrel cage bearing frame (6), roller bearing (11) and bolt (15), its characterized in that: the coupling bidirectional thrust oil film damper supporting system for the gas turbine further comprises a thrust disc assembly, an oil retainer ring (9), a movable ring (10), a bushing (12) and a ring nut (13), wherein the thrust disc assembly comprises a thrust disc (1), a front thrust pad base body (2), a high-pressure front thrust bearing seat (3), a rear thrust pad base body (4) and a high-pressure rear thrust bearing seat (5) and nine sets of pad assemblies, each set of pad assembly comprises two main supporting blocks (17) and four elastic supporting plates (16), a damper (18) is sleeved on a squirrel cage bearing seat (6), the squirrel cage bearing seat (6) is sleeved on the thrust disc assembly, a roller bearing (11) and the oil retainer ring (9) are arranged in a cantilever end of the squirrel cage bearing seat (6), the damper (18) is arranged on a stator part of the gas compressor through bolts (15), the high-pressure front thrust bearing seat (3) and the front thrust pad base body (2) are sequentially arranged in front of the thrust disc (1) from front to back, the rear thrust pad base body (4), the high-pressure front thrust pad base body (5) and the high-pressure rear thrust pad base body (5) are sequentially arranged between the front of the two main supporting plates (17) and the front thrust pad (16) in sequence, two elastic support plates (16) and a main support block (17) are sequentially arranged between the rear thrust pad base body (4) and the high-pressure rear thrust bearing seat (5) from outside to inside, the movable ring (10) is installed on the outer side face of the inner ring of the roller bearing (11), the bushing (12) is sleeved on the roller bearing (11), the bushing (12) is located between the outer surface of the roller bearing (11) and the inner surface of the squirrel cage bearing seat (6), and the ring nut (13) is arranged between the inner ring of the roller bearing (11) and the thrust disc (1).
2. The coupled bi-directional thrust oil film damper support system for a gas turbine of claim 1, wherein: the coupled bidirectional thrust oil film damper supporting system for the gas turbine further comprises a pin (14), wherein the pin (14) is arranged on the inner side surface of the thrust disc (1).
3. The coupled bi-directional thrust oil film damper support system for a gas turbine of claim 1, wherein: the coupling bidirectional thrust oil film damper supporting system for the gas turbine also comprises two sealing rings (19), wherein the two sealing rings (19) are sleeved on the outer wall of the squirrel cage bearing seat (6) side by side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910436248.5A CN110056571B (en) | 2019-05-23 | 2019-05-23 | Coupled bidirectional thrust oil film damper supporting system for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910436248.5A CN110056571B (en) | 2019-05-23 | 2019-05-23 | Coupled bidirectional thrust oil film damper supporting system for gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110056571A CN110056571A (en) | 2019-07-26 |
| CN110056571B true CN110056571B (en) | 2024-01-12 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910436248.5A Active CN110056571B (en) | 2019-05-23 | 2019-05-23 | Coupled bidirectional thrust oil film damper supporting system for gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110056571B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113700732B (en) * | 2021-08-25 | 2023-09-05 | 中国科学院工程热物理研究所 | Gas turbine rotor supporting system based on sliding bearing and thrust disc |
| CN115370612B (en) * | 2022-09-29 | 2023-04-21 | 江西中发天信航空发动机科技有限公司 | Axial-flow compressor rotor structure of aero-engine |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1485773A (en) * | 1973-11-16 | 1977-09-14 | Mannesmann Ag | Hydraulically loaded axial thrust bearing for a shaft provided with a thrust collar more particularly for ship transmission apparatus |
| JPH07208335A (en) * | 1994-01-14 | 1995-08-08 | Mitsubishi Heavy Ind Ltd | Supporting device for rotor |
| JP2002070853A (en) * | 2000-08-29 | 2002-03-08 | Mitsubishi Heavy Ind Ltd | High damping thrust bearing |
| CN201288687Y (en) * | 2008-10-21 | 2009-08-12 | 山东颜山泵业有限公司 | Water lubricating high thrust bearing for submerged generator |
| WO2014147878A1 (en) * | 2013-03-19 | 2014-09-25 | 三菱重工業株式会社 | Rotary shaft supporting structure |
| CN105179461A (en) * | 2015-09-18 | 2015-12-23 | 哈尔滨电气动力装备有限公司 | Water-lubricating bidirectional working thrust bearing device |
| CN108223580A (en) * | 2018-03-06 | 2018-06-29 | 中船重工龙江广瀚燃气轮机有限公司 | A kind of gas turbine coupling bomb branch film damper bearing arrangement |
| CN209875729U (en) * | 2019-05-23 | 2019-12-31 | 中国船舶重工集团公司第七0三研究所 | Coupling bidirectional thrust oil film damper supporting system for gas turbine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP5232909B2 (en) * | 2009-02-25 | 2013-07-10 | 三菱重工業株式会社 | Thrust bearing oil nozzle |
-
2019
- 2019-05-23 CN CN201910436248.5A patent/CN110056571B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1485773A (en) * | 1973-11-16 | 1977-09-14 | Mannesmann Ag | Hydraulically loaded axial thrust bearing for a shaft provided with a thrust collar more particularly for ship transmission apparatus |
| JPH07208335A (en) * | 1994-01-14 | 1995-08-08 | Mitsubishi Heavy Ind Ltd | Supporting device for rotor |
| JP2002070853A (en) * | 2000-08-29 | 2002-03-08 | Mitsubishi Heavy Ind Ltd | High damping thrust bearing |
| CN201288687Y (en) * | 2008-10-21 | 2009-08-12 | 山东颜山泵业有限公司 | Water lubricating high thrust bearing for submerged generator |
| WO2014147878A1 (en) * | 2013-03-19 | 2014-09-25 | 三菱重工業株式会社 | Rotary shaft supporting structure |
| CN105179461A (en) * | 2015-09-18 | 2015-12-23 | 哈尔滨电气动力装备有限公司 | Water-lubricating bidirectional working thrust bearing device |
| CN108223580A (en) * | 2018-03-06 | 2018-06-29 | 中船重工龙江广瀚燃气轮机有限公司 | A kind of gas turbine coupling bomb branch film damper bearing arrangement |
| CN209875729U (en) * | 2019-05-23 | 2019-12-31 | 中国船舶重工集团公司第七0三研究所 | Coupling bidirectional thrust oil film damper supporting system for gas turbine |
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| CN110056571A (en) | 2019-07-26 |
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