CN108223580A - A kind of gas turbine coupling bomb branch film damper bearing arrangement - Google Patents
A kind of gas turbine coupling bomb branch film damper bearing arrangement Download PDFInfo
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- CN108223580A CN108223580A CN201810182776.8A CN201810182776A CN108223580A CN 108223580 A CN108223580 A CN 108223580A CN 201810182776 A CN201810182776 A CN 201810182776A CN 108223580 A CN108223580 A CN 108223580A
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- gas turbine
- elastic ring
- sleeve
- damper
- mouse cage
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- 230000008878 coupling Effects 0.000 title claims abstract description 22
- 238000010168 coupling process Methods 0.000 title claims abstract description 22
- 238000005859 coupling reaction Methods 0.000 title claims abstract description 22
- 238000007789 sealing Methods 0.000 claims abstract description 8
- 238000002347 injection Methods 0.000 claims abstract description 7
- 239000007924 injection Substances 0.000 claims abstract description 7
- 239000003921 oil Substances 0.000 description 28
- 239000007789 gas Substances 0.000 description 19
- 238000013461 design Methods 0.000 description 12
- 238000013016 damping Methods 0.000 description 11
- 239000010687 lubricating oil Substances 0.000 description 7
- 238000009826 distribution Methods 0.000 description 4
- 238000005461 lubrication Methods 0.000 description 4
- 238000005457 optimization Methods 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 230000000875 corresponding effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005538 encapsulation Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000010355 oscillation Effects 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 238000007514 turning Methods 0.000 description 2
- 238000012935 Averaging Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000006399 behavior Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000002596 correlated effect Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000002401 inhibitory effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 230000036961 partial effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000002441 reversible effect Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C32/00—Bearings not otherwise provided for
- F16C32/06—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings
- F16C32/0629—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings supported by a liquid cushion, e.g. oil cushion
- F16C32/064—Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings supported by a liquid cushion, e.g. oil cushion the liquid being supplied under pressure
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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
- 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
Abstract
The invention belongs to gas-turbine plant technical fields, and in particular to a kind of gas turbine coupling bomb branch film damper bearing arrangement, including mouse cage bearing block, damper housing, sleeve, elastic ring, locking nut, ball bearing, sealing ring and injection loop；Elastic ring is clamped between damper housing and sleeve, and elastic ring both ends are equipped with the sealing ring for controlling end draining；The flange end of mouse cage bearing block and the flange end of damper housing are connected by the stator casing of circumferentially uniformly distributed bolt and gas turbine to be fixed, the built-in ball bearing for having to support rotor and axle journal of the cantilever end of mouse cage bearing block；To tighten the simultaneously axial position of fixes sleeve and ball bearing, sleeve is engaged locking nut with mouse cage bearing block cantilever end.Improve the stability of film damper；Enable gas turbine rotor support system smoothly through each rank critical speed, and the even running under prevailing operating state.
Description
Technical field：
The invention belongs to gas-turbine plant technical fields, and in particular to a kind of gas turbine coupling bomb branch film damper axis
Hold system.
Background technology：
Squeeze film damper is a kind of new technology to grow up the 1960s, since its effectiveness in vibration suppression is notable, structure
Simply, it occupies little space, manufacture relatively easily, great attention is received in the eighties, and first answered in aero-engine
With, have become at present reduce naval vessel and industry gas turbine vibration, improve stability, extend the service life modular design.Rotor-
Support system by and close near critical speed when, amplitude is positively correlated with the critical angular velocity of amount of unbalance and rotor,
Damped coefficient of the reverse phase about rotor-support system.And it is fixed in engine general structure design, pass through change
Rotor structure（Diameter, pivot distance of axis etc.）Adjusting critical speed is often very difficult, and most effective and feasible method is to set
Maximum support and maximum support damping are counted out, coupling bomb branch Squeeze film damper bearing system is such a structure.
Traditional squeeze film damper quiet bias is larger and by transient impact compared with big load when embody compared with
Strong is non-linear so that the non-linear behaviors such as bistable state, non-coordinating precession occurs in system, is transported so as to endanger stablizing for rotor-support-foundation system
Row.The elastic circular structure of special designing is added in conventional damper by being easily transformed, can hinder coupling bomb branch oil film
Buddhist nun's device has certain Self-aligning ability, can also effectively improve the non-linear of conventional damper, improves gas turbine rotor system
The stability of system makes film damper be more widely used in the Project R＆D of gas turbine and the equipment supply of material.
Invention content：
The object of the present invention is to provide a kind of gas turbine coupling bomb branch film damper bearing arrangement, in the course of work, mouse
Cage bearing block can realize frequency modulation function to rotor-support system, and the working speed of entire rotor-support-foundation system is made to avoid facing as much as possible
Boundary's rotating speed reduces the bending vibration shape；Corresponding deformation occurs for the vibration that the elastic ring in film damper is suitable for rotor, absorbs vibration
Energy improves the stability of film damper so as to strengthen its shock proof ability；In addition elastic ring and squeeze film damper
Rubbing action between inner and outer rings, restriction loss of through-flow aperture etc. on elastic ring can improve the damping and amortization of damper
Can, enable gas turbine rotor-support system smoothly through each rank critical speed, and steadily transported under prevailing operating state
Row.
The technical solution adopted by the present invention is：A kind of gas turbine coupling bomb branch film damper bearing arrangement, including
Mouse cage bearing block, damper housing, sleeve, elastic ring, locking nut, ball bearing, sealing ring and injection loop；The elastic ring
It is clamped between damper housing and sleeve, elastic ring both ends are equipped with the sealing ring for controlling end draining；Form elastic ring
Formula squeeze film damper, then compose in parallel centering type coupling bomb branch film damper system with mouse cage bearing block；The mouse cage
The flange end of bearing block and the flange end of damper housing are connected by the stator casing of circumferentially uniformly distributed bolt and gas turbine
It is fixed, the built-in ball bearing for having to support rotor and axle journal of the cantilever end of mouse cage bearing block, and by pre- eccentric design come
Ensure rotor and the concentric of coupling bomb branch film damper system.The locking nut is tightening and fixes sleeve and rolling
The axial position of pearl bearing, sleeve are engaged with mouse cage bearing block cantilever end.
Further, the elastic ring for interior outer lug boss staggeredly and equally distributed tubular structure, inner convex platform with damping
The outer surface of device housing is engaged, and the inner surface of outer lug boss and sleeve is engaged, and elastic ring is equipped with throttle orifice；Elastic ring
Surface engagement of the inside and outside boss in damper transition cooperation can be used, can also be gap-matched, while need to pass through
Rotation stop positioning screw limitation elastic ring and the relative rotation of damper inner and outer rings are set.
Further, the throttle orifice is plain edition, gradual shrinkage or flaring type；What is formed between two neighboring boss is single
In oil film section, 1-4 throttle orifice can be arranged on elastic ring, pass parameters, distribution are carried out according to the running parameter of damper system
Design.
Further, mouse cage bearing block is cantilevered, and flange end is fixed on the stator casing of gas turbine, in cantilever end
Device ball bearing, locking nut and sleeve；Sleeve is fixed in the middle part of mouse cage, and ball bearing outer shroud is fixed on mouse cage tail portion, interior
Ring encapsulation rotates together on rotor journal with shaft.
Further, mouse cage bearing block is designed as the structure with pre- bias, forms centering type coupling bomb branch oil-film damping
Device system；According to real work parameter, coupling bomb branch film damper bearing arrangement is changed by mouse cage cage structure size
Support stiffness realizes frequency modulation function.
Further, when gas turbine works, lubricating oil enters the gap between elastic ring and damper housing, in foundation
Oil film flows into the gap between elastic ring and sleeve by several through-flow apertures Jing Guo optimization design on elastic ring, establishes
Outer oil film.When gas turbine works, elastic ring absorbs part rotor vibrational energy, generates periodically deforming, oil inside and outside extruding
Film, lubricating oil is flowed by through-flow aperture in multiple oil pockets of inside and outside oil film generates more throttles, improves the profit of oil film
Sliding situation, so as to improve the damping of resilient support squeeze film damper system.
Further, the cantilever end machining center line of mouse cage bearing block is slightly above the center line of flange end positioning surface, is turning
When son is static, the pre- eccentricity of mouse cage bearing block cantilever end can compensate deflection caused by the gravity of rotor, ensure to turn
The uniformity of oil film in sub- centering state and damper；The rigidity of mouse cage bearing block determines the magnitude of support system rigidity,
Main frequency modulation and supporting role are played in coupling elastic support structure.
Further, when gas turbine works, the oil supply tank of lubricating oil from damper housing provides lubricating oil for damper,
Side grooves install metallic packing ring to control the dredge oil amount at damper both ends, while are ball bearing oil jet lubrication；It is covering
Also the oil supplying hole that lubrication is provided to ball bearing is arranged on cylinder, injection loop.
Further, two kinds of conventional extruded film dampers are composed in parallel into the coupling of centering type by Structure Improvement Design
Bullet branch film damper system, and pass through the through-flow aperture of optimization design elasticity ring surface, the through-flow situation of oil film inside and outside improvement,
The damping of system is not only improved, improves the job stability of damper, and with good frequency modulation function.
Beneficial effects of the present invention：
（1）, it is small for damping existing for conventional extruded film damper, the problems such as job insecurity, it is proposed that it is a kind of will be traditional
Elastic support structure forms centering type coupling bomb branch film damper bearing arrangement by Curve guide impeller in parallel, and passes through and optimize it
The pass of middle elastic ring through flow hole and distribution are effectively improved the damping characteristic of support system, so as to improve the work of film damper
Make stability, and have preferable fm capacity；
（2）, propose by increasing the through-flow aperture with special-shaped pore structure and distribution in elastic ring surface, can be effectively improved
The lubrication state of oil film in damper, so as to improve the stability of elastic ring squeeze film damper work；On the other hand, it passes through
The pass and small pore size distribution for crossing optimization design can be effectively increased throttle, so as to improve the performance of damper；
（3）, can be applied to the combustion gas such as the higher industry of stability and reliability requirement to support system, naval vessel and aerospace
Turbine can also be improved the support construction for replacing existing gas turbine by structure, effectively reduce the generation that unit vibration transfinites, carry
High unit factory test success of the test rate；
（4）, in can make rotor-support system more smoothly through each rank critical speed to the Curve guide impeller of resilient support,
Even running or other high-speed rotating machine fields with particular/special requirement under working condition, including military affairs, the energy, electricity
The squeeze film damper parameter designing of power, traffic, environmental protection etc. is offered reference.
Description of the drawings：
Fig. 1 is the structure diagram of the present invention；
Fig. 2 is the structure diagram of elastic ring in the present invention；
Fig. 3 is the principle schematic of elastic ring squeeze film damper.
Specific embodiment：
With reference to each figure, a kind of gas turbine coupling bomb branch film damper bearing arrangement, including mouse cage bearing block 1, damper
Housing 2, sleeve 3, elastic ring 4, locking nut 5, ball bearing 6, sealing ring 7 and injection loop 8；The elastic ring 4 is clamped in resistance
Between Buddhist nun's device housing 2 and sleeve 3, for interior outer lug boss staggeredly and equally distributed tubular structure, inner convex platform 11 and damper shell
The outer surface transition cooperation of body 2, the circumferential oil supply tank of 2 outer surface of damper housing setting are simultaneously provided with oil supplying hole as film damper confession
Oil；Its outer lug boss 9 and the internal surface gaps of sleeve 3 coordinate；4 surface of elastic ring has the special-shaped small structure of special designing, should
Aperture is throttle orifice 10；The oil pocket both ends of film damper are equipped with sealing ring 7, to control end draining, form elastic circular
Squeeze film damper, then with mouse cage bearing block 1 by flanged joint on casing, compose in parallel centering type coupling bomb branch oil film
Damper.
The built-in ball bearing 6, locking nut 5 and set for having to support rotor and axle journal of the cantilever end of mouse cage bearing block 1
Cylinder 3, and the concentric of rotor and coupling bomb branch film damper system is ensured by pre- eccentric design；Sleeve 3, ball axis
It holds 6 to connect with 1 cantilever end close-fitting of mouse cage bearing block, locking nut 5 is tightening and 6 outer shroud of fixes sleeve 3 and ball bearing
Axial position, the inner ring interference encapsulation of ball bearing 6 on the axle journal of rotor and rotate together with；Injection loop 8, damper housing 2
And it is designed on sleeve 3 as 6 oil supplying hole of ball bearing.
When gas turbine works, lubricating oil enters the gap between elastic ring 4 and damper housing 2 from damper housing 2,
Oil film in foundation flows into the gap between elastic ring 4 and sleeve 3 by the damping hole on 4 surface of elastic ring, establishes outer oil film.When
When gas turbine works, elastic ring 4 generates periodically deforming and absorbs part rotor vibration strains energy, and oil film makes oil film inside and outside extruding
A part of rotor oscillation energy is absorbed, while throttle orifice 10 brings certain restriction loss, make the strain being stored in elastic ring 4
It can be released with slow speed, reach casing outside, and the partial vibration energy experienced a time averaging process, reduce
Vibration peak reduces the transmission power of rotor oscillation outside casing；Flowing of the lubricating oil between oil film inside and outside elastic ring 4 generates resistance
Buddhist nun is the non-linear increasing function of axle journal eccentricity, with amount of unbalance increase or the raising of rotating speed, corresponding increase is damped, to facing
Important inhibiting effect is played in the judder of boundary's rotary speed area.
The machining center line of 1 cantilever end of mouse cage bearing block is slightly above it and installs the center line of positioning surface, for ensureing rotor
Centering；The section of cage item close to rectangle, should make the radial rigidity of cage item be more than circumferential rigidity；The rigidity one of mouse cage bearing block 1
As be more than the rigidity of elastic ring 4, play main supporting role in coupling bomb branch structure, and the rigidity of elastic ring 4 can influence bullet
The damping of property ring type squeeze film damper；Therefore, the rigidity of decision design mouse cage bearing block 1 and elastic circular squeeze film
The damping of damper, then check the rigidity of elastic ring 4, it is ensured that system support stiffness is in the range of design value.
Outer oil film thickness should be followed in the design of elastic ring 4 and keeps one not less than interior oil film thickness, interior outer lug boss quantity
Cause, circumferentially uniform staggered principle；Lubricating oil can be from the nozzle opening of damper housing 2, the oil-through-hole of sleeve 3, shaft
Oil-through-hole, injection loop 8 etc. be ejected into multi-facetedly on ball bearing 6, efficiently realize lubrication cooling, increase the work of bearing arrangement
Make reliability.
Gas turbine adjustable guide vane control system driving linkage ring assemblies 1 are circumferentially rotated around gas turbine axis, due to turning
Arm 2 is integrally formed with adjustable guide vane 3 under the connection function of positioning screw 4, pivoted arm 2 and can be turned in the case where linkage ring assemblies 1 drive
Guide vane 3 can will be rotated around 3 axle journal of adjustable guide vane jointly；When adjustable guide vane 3 rotates, sliding block 1-4 free skatings in 2 open slot of pivoted arm
Dynamic, the size of 2 open slot of pivoted arm is determined according to the slewing area of adjustable guide vane 3.Elastomeric pad 6 and adjusting washer 7, which are arranged in, to be turned
Between 2 bottom of arm and casing 5, to adjust the radial position of adjustable guide vane 3, ensure that adjustable guide vane 3 can not be altered along axle journal direction
It is dynamic, improve adjustable guide vane rotation precision.
Claims (3)
1. a kind of gas turbine coupling bomb branch film damper bearing arrangement, it is characterised in that：Including mouse cage bearing block（1）、
Damper housing（2）, sleeve（3）, elastic ring（4）, locking nut（5）, ball bearing（6）, sealing ring（7）And injection loop（8）；
The elastic ring（4）It is clamped in damper housing（2）And sleeve（3）Between, elastic ring（4）Both ends are equipped with that end is controlled to let out
The sealing ring of oil（7）；The mouse cage bearing block（1）Flange end and damper housing（2）Flange end pass through it is circumferentially uniformly distributed
The connection of the stator casing of bolt and gas turbine is fixed, mouse cage bearing block（1）Cantilever end built-in support rotor and axis
The ball bearing of neck（6）；The locking nut（5）To tighten simultaneously fixes sleeve（3）And ball bearing（6）Axial position,
Sleeve（3）With mouse cage bearing block（1）Cantilever end is engaged.
2. a kind of gas turbine according to claim 1 coupling bomb branch film damper bearing arrangement, it is characterised in that：
The elastic ring（4）For interior outer lug boss staggeredly and equally distributed tubular structure, inner convex platform（11）With damper housing（2）'s
Outer surface is engaged, outer lug boss（9）With sleeve（3）Inner surface be engaged, elastic ring（4）It is equipped with throttle orifice（10）.
3. a kind of gas turbine according to claim 2 coupling bomb branch film damper bearing arrangement, it is characterised in that：
The throttle orifice（10）For plain edition, gradual shrinkage or flaring type.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810182776.8A CN108223580A (en) | 2018-03-06 | 2018-03-06 | A kind of gas turbine coupling bomb branch film damper bearing arrangement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810182776.8A CN108223580A (en) | 2018-03-06 | 2018-03-06 | A kind of gas turbine coupling bomb branch film damper bearing arrangement |
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| Publication Number | Publication Date |
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| CN108223580A true CN108223580A (en) | 2018-06-29 |
Family
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810182776.8A Pending CN108223580A (en) | 2018-03-06 | 2018-03-06 | A kind of gas turbine coupling bomb branch film damper bearing arrangement |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109185381A (en) * | 2018-09-30 | 2019-01-11 | 中南大学 | A kind of combined elastic ring squeeze film damper |
| CN110056571A (en) * | 2019-05-23 | 2019-07-26 | 中国船舶重工集团公司第七0三研究所 | A kind of gas turbine coupling two-way thrust film damper supporting system |
| CN110594305A (en) * | 2019-09-22 | 2019-12-20 | 中国航发沈阳发动机研究所 | Rotor journal end sealing and locking structure thereof |
| CN112469910A (en) * | 2018-07-26 | 2021-03-09 | 株式会社Ihi | Bearing structure |
| CN113503305A (en) * | 2021-08-03 | 2021-10-15 | 中国航发湖南动力机械研究所 | Long and thin flexible shaft structure of sectional type engine |
| CN113700732A (en) * | 2021-08-25 | 2021-11-26 | 中国科学院工程热物理研究所 | Gas turbine rotor support system based on sliding bearing and thrust disc |
| CN113833749A (en) * | 2020-06-23 | 2021-12-24 | 中国航发商用航空发动机有限责任公司 | Eccentric ring, aero-engine and aero-engine rotor eccentricity adjusting method |
| CN116255391A (en) * | 2023-05-15 | 2023-06-13 | 江苏儒豪精密机械有限公司 | Vibration reduction bearing with variable elastic corrugated ring |
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| CN207906294U (en) * | 2018-03-06 | 2018-09-25 | 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 |
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| CN102338158A (en) * | 2011-09-15 | 2012-02-01 | 西安交通大学 | Elastic ring and integral-type elastic ring damper utilizing same |
| CN102888903A (en) * | 2012-10-22 | 2013-01-23 | 株洲时代新材料科技股份有限公司 | Sleeved viscous damper capable of damping variable parameters and design method thereof |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112469910A (en) * | 2018-07-26 | 2021-03-09 | 株式会社Ihi | Bearing structure |
| CN112469910B (en) * | 2018-07-26 | 2022-04-19 | 株式会社Ihi | Bearing structure |
| CN109185381A (en) * | 2018-09-30 | 2019-01-11 | 中南大学 | A kind of combined elastic ring squeeze film damper |
| CN110056571A (en) * | 2019-05-23 | 2019-07-26 | 中国船舶重工集团公司第七0三研究所 | A kind of gas turbine coupling two-way thrust film damper supporting system |
| CN110056571B (en) * | 2019-05-23 | 2024-01-12 | 中国船舶重工集团公司第七0三研究所 | Coupled bidirectional thrust oil film damper supporting system for gas turbine |
| CN110594305A (en) * | 2019-09-22 | 2019-12-20 | 中国航发沈阳发动机研究所 | Rotor journal end sealing and locking structure thereof |
| CN113833749A (en) * | 2020-06-23 | 2021-12-24 | 中国航发商用航空发动机有限责任公司 | Eccentric ring, aero-engine and aero-engine rotor eccentricity adjusting method |
| CN113833749B (en) * | 2020-06-23 | 2023-08-08 | 中国航发商用航空发动机有限责任公司 | Eccentric ring, aeroengine and method for adjusting eccentric amount of aeroengine rotor |
| CN113503305A (en) * | 2021-08-03 | 2021-10-15 | 中国航发湖南动力机械研究所 | Long and thin flexible shaft structure of sectional type engine |
| CN113700732A (en) * | 2021-08-25 | 2021-11-26 | 中国科学院工程热物理研究所 | Gas turbine rotor support system based on sliding bearing and thrust disc |
| 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 |
| CN116255391A (en) * | 2023-05-15 | 2023-06-13 | 江苏儒豪精密机械有限公司 | Vibration reduction bearing with variable elastic corrugated ring |
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