CN114233409B - Rigidity repairable supporting structure for rotor with blade loss fault - Google Patents
Rigidity repairable supporting structure for rotor with blade loss fault Download PDFInfo
- Publication number
- CN114233409B CN114233409B CN202111577604.9A CN202111577604A CN114233409B CN 114233409 B CN114233409 B CN 114233409B CN 202111577604 A CN202111577604 A CN 202111577604A CN 114233409 B CN114233409 B CN 114233409B
- Authority
- CN
- China
- Prior art keywords
- rotor
- rigidity
- core actuating
- supporting
- repairable
- 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.)
- Active
Links
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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
- F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
-
- 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
- F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Wind Motors (AREA)
Abstract
The invention discloses a rigidity repairable supporting structure of a rotor aiming at the loss of a blade and the fault, which comprises a supporting outer frame, a supporting outer frame and a supporting outer frame, wherein the supporting outer frame provides installation space for a core actuating element and provides partial supporting rigidity; the core actuating element is designed based on a chiral honeycomb structure and is used for providing partial supporting rigidity for a rotor system, bearing impact energy generated by blade loss and recovering the original structural characteristics after large deformation; the outer support frame is fixed to the support cone shell through a flange edge and supports the rotor system.
Description
Technical Field
The invention belongs to the field of variable-rigidity supporting structures of rotors, and particularly relates to a rigidity repairable supporting structure of a rotor aiming at a blade loss fault.
Background
For aircraft engines, the safety design problem of the rotor system when the blade is lost is one of the core problems concerned by international airworthiness certification. The loss of the blades, especially the loss of the fan blades, can bring huge unbalance to a rotor system, and when the rotor system decelerates to pass through a critical rotating speed, a series of catastrophic failures such as shaft seizure, shaft breakage, turbine disk burst and the like are inevitably caused by overlarge vibration deformation. In order to avoid such rotor faults, a special structural design needs to be designed to ensure the flight safety of the airplane. In international commercial high bypass ratio turbofan engines, fusible weak link design similar to fuses is adopted at the front support points of the fans, and the turbofan engines are passive fusing support structures. Although the existing fusing support structure can reduce the transient amplitude and safe deceleration of the rotor at the moment of blade loss, the shearing of the support structure is accompanied with transverse step impact, and the working load of only two remaining fulcrum bearings is overlarge when the rotor rotates at the windmill speed, so that the stability of a rotor system is greatly weakened.
Disclosure of Invention
The invention solves the problems: the defect that the supporting rigidity cannot be recovered after a conventional fusing supporting structure is sheared is overcome, the rigidity-recoverable supporting structure for the rotor with the blade loss fault is provided, the rotor is not damaged after the rotor bears the huge impact energy of the blade loss, the initial supporting rigidity can be recovered, and the purpose that the rotor system can still stably and safely operate after the blade loss occurs is achieved.
The scheme adopted by the invention is as follows: a stiffness repairable support structure of a rotor for a blade loss failure, comprising: a supporting outer frame and a core actuating element; the supporting outer frame comprises a mounting shell and a reentry type squirrel cage, provides partial supporting rigidity for the rotor, is used for mounting a core actuating element and can limit the radial amplitude of the rotor; the core actuating element is designed based on a chiral honeycomb unit cell structure, provides partial supporting rigidity for the rotor, and can be actively adjusted; the rigidity repairable supporting structure can bear the loss impact of the blades without damage, fracture and damage, and the core actuating element is restored to the original structural shape by heating, so that the structural repair and rigidity restoration are realized, and the stability and safety of the rotor are improved.
The circumferences of the core actuating elements are distributed in the mounting grooves at equal intervals, the number of the core actuating elements is even, and the radial support rigidity at the rotor fulcrum is ensured to be uniformly distributed.
The core actuating component and the reentry type squirrel cage are in a parallel relation, and the proportion of the supporting rigidity of the core actuating component and the reentry type squirrel cage is determined according to the vibration characteristics of the rotor.
The structural form of the chiral honeycomb unit cell is a polygonal structure and is formed by connecting a cylinder and a rib plate; the polygonal structure comprises a triangle, a quadrangle, a pentagon, a hexagon, a heptagon or an octagon; adjusting and designing geometric design parameters of the width of a ribbed plate, the radius of a cylinder, the thickness of the single cell and the radius of a fillet at the joint of the ribbed plate and the cylinder according to requirements; and the core actuating element adjusts the circumferential component layer number and the radial component layer number of the chiral honeycomb unit cell according to the requirement.
The mounting shell is provided with limiting blocks, the limiting blocks are distributed on the mounting shell along the circumferential direction, the middle of the mounting shell is hollowed to reduce the structural weight, an installation space is provided for the core actuating element, the circumferential displacement of the core actuating element is limited, the supporting rigidity of the variable-rigidity supporting structure is ensured to be relatively uniform along the circumferential direction after the core actuating element is subjected to large deformation, and the large deformation refers to the maximum allowable radial deformation of the supporting position in the safety design of the rotor; the radial length of the limiting block is adjusted according to design requirements, the core actuating assembly is protected, and damage caused by the fact that the amplitude of the rotor exceeds the maximum allowable radial deformation are prevented.
After the rigidity-repairable supporting structure is subjected to impact load generated by blade loss, the radial rigidity of the core actuating assembly is the characteristic of slope decline in the large deformation process, so that the instantaneous change of the supporting rigidity of the rotor is avoided; the core actuating element can not be broken in the large deformation process, and the subsequent functional use of the core actuating element is ensured; the core actuating component is made of shape memory alloy, and structural characteristics and rigidity characteristics of the core actuating element are repaired in a heating mode after large deformation occurs.
Compared with the prior art, the invention has the following advantages: the rigidity-repairable supporting structure disclosed by the invention has the advantages that after the blades of the rotor are lost, the supporting structure deforms after being impacted, so that the supporting rigidity of the rotor is reduced, the critical rotating speed of the rotor is reduced, and the rotor can safely pass through the critical rotating speed. The invention can bear the loss impact of the blade without damage, fracture and damage, can make the core actuating element restore to the original structural shape by heating in the stable windmill running state, realizes the structural restoration and the rigidity restoration, redistributes the bearing load of each fulcrum, improves the stability and the safety of the rotor, and ensures the safe landing of the airplane. The core actuating element adopted by the invention has the characteristic of high damping, can replace the traditional squeeze film damper of an aircraft engine, has no oil supply requirement, and has a simpler structure. The invention can also be applied to a rotor system which operates normally, realizes the mutual conversion between martensite and austenite of the shape memory alloy by a heating and cooling mode, actively adjusts the supporting rigidity of the supporting structure, timely changes the critical rotating speed of the rotor, and realizes the 'no resonance peak' transcritical of the rotor. The core actuating element has the advantages of simple structure, wide rigidity change range and strong designability, can meet the requirements of different aircraft engines, has no oil supply requirement, and has simpler structure.
Drawings
The accompanying drawings, which are included to provide a further understanding of the disclosure and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the disclosure and together with the description serve to explain the principles of the disclosure;
FIG. 1 is a 3/4 cut-away view of the three-dimensional structure of the present invention;
FIG. 2 is an installation diagram of the present invention in an aircraft engine;
FIG. 3 is an overall view (left) and a partial view (right) of the mounting housing of the present invention;
FIG. 4 is an overall view of the reentry squirrel cage of the present invention;
FIG. 5 is a topology of chiral honeycomb cells constituting a core actuating element;
FIG. 6 is a bivalve split structure based on the expansion of a quadrilateral chiral honeycomb unit cell structure;
fig. 7 is a three-cell split structure based on the expansion of a quadrilateral chiral honeycomb cell structure.
Detailed Description
The present disclosure will be described in further detail with reference to the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limitations of the present disclosure. It should be further noted that, for the convenience of description, only the portions relevant to the present disclosure are shown in the drawings.
It should be noted that the embodiments and features of the embodiments disclosed in the present disclosure may be combined with each other without conflict. The present disclosure will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
As shown in fig. 1-7, the rigidity repairable supporting structure for a rotor with a blade loss fault disclosed by the invention comprises an outer elastic ring 1, a reentrant squirrel cage 2, a mounting bolt 3, an inner elastic ring 4, a fastening bolt 5, a bearing end cover 6, a core actuating element 7 and a mounting shell 8.
The mounting example disclosed by the invention is shown in FIG. 2, and a flange edge of a mounting shell is connected with a supporting cone shell 9 by mounting bolts 10; the rotor 11 is mounted in a bearing 12, the bearing 12 is mounted in a bearing seat 20 of the reentry squirrel cage 2, and the axial displacement of the bearing 12 is limited by a bearing end cover 6.
The variable stiffness supporting structure with repairable stiffness comprises two parts, namely a supporting outer frame and a core actuating element.
The outer support frame comprises an outer elastic ring 1, a return type squirrel cage 2, a mounting bolt 3, an inner elastic ring 4, a fastening bolt 5, a bearing end cover 6 and a mounting shell 8. The flange 22 of the folding mouse cage 2 and the flange 13 of the mounting shell 8 are connected through the mounting bolts 3 to form a main body of a supporting outer frame.
The mounting case 8 is shown in fig. 3 in a whole view and a partial view. The core activating element 7 is mounted in the mounting slot 15 between the stops 16. One mounting groove 15 can mount two core activation elements 7 and limit the axial displacement of the core activation elements 7 by means of the outer elastic ring 1, the inner elastic ring 4, the bearing end cover 6 and the spacer ribs 14. The stop blocks 16 serve to limit the circumferential displacement of the core actuating element 7 and the radial amplitude of the rotor 11. The outer elastic ring 1 is mounted in the groove 18, and the groove 19 provides sufficient radial displacement space for the inner elastic ring 4.
The overall view of the reentry squirrel cage 2 is shown in fig. 4. The inner resilient ring 4 is mounted in the groove 21 and limits the axial movement of the core activation element 7.
The topology of the triangular chiral cell to the octagonal chiral cell constituting the core actuating element is shown in FIG. 5, and the details of (a), (b), (c), (d), (e), (f), etc. in FIG. 5 will be described. The core actuating element can also adopt a unit cell structure with more than octagonal. Based on the single cell structure, the split structure of the core actuating element can be obtained by periodically expanding a plurality of single cell structures.
Taking a quadrilateral chiral honeycomb unit cell structure as an example, fig. 6 shows an expanded two-cell split structure, fig. 7 shows an expanded three-cell split structure, and fig. 6 and 7 are explained. Similarly, a full-circle core actuating element can also be obtained in the same manner of development.
The specific working process of the embodiment of the invention is as follows: the reentry type squirrel cage 2 and the mounting shell 8 are connected into a whole by bolts. The core activation element 7 is mounted in a positive manner in all mounting slots 15 close to the flange edge 13, and the inner elastic ring 4 is then used to limit the axial displacement of the mounted core activation element 7. The core activation element 7 is then mounted in a reversed manner in the mounting groove 15 remote from the flange edge 13, the axial displacement of which is limited by the outer elastic ring 1. The modifiable stiffness support structure is then connected to the outer cone shell 9 via the flange 17. Finally, the rotor 11 is mounted on the bearing 12, the bearing 12 is mounted in the bearing seat 20 of the reentry cage 2, and the bearing end cover 6 is adopted to limit the axial displacement of the bearing 12 and the core actuating element 7.
Under normal working conditions, the rigidity provided by the core actuating element and the reentry type squirrel cage is large enough, the stress deformation is in an elastic range, the plastic deformation cannot occur, and the rotor system can be effectively supported. In the speed increasing and reducing process, the elastic modulus of the core actuating element can be changed in a heating or cooling mode, the supporting rigidity is changed to adjust the critical rotating speed of the rotor system, and the purpose that the rotor is 'free of resonance peaks' and is over-critical is achieved.
When the blade is lost, the core actuating element is compressed and deformed under the action of impact energy, the supporting rigidity of the core actuating element is rapidly reduced, and phase change strain is generated, so that the supporting rigidity of the rotor system at the fulcrum is reduced, the critical rotating speed is reduced, the rotor can pass through the critical rotating speed at the lower critical rotating speed, and the aim of safely reducing the rotating speed of the windmill is fulfilled.
When the energy lost by the blades is too large, the bearing seat of the turn-back type squirrel cage is contacted with the limiting block, so that the vibration of the rotor is limited, the rotor is protected from shaft breakage, and the core actuating element is protected from being crushed and broken.
In the wind turbine rotation speed stage, the vibration energy of the rotor decreases, and the support reaction force of the variable-stiffness support structure decreases. At this time, the core actuating element 7 is heated by means of energization or hot air flow to restore the original shape and the original support rigidity, thereby achieving the purpose of repairing the support rigidity of the present invention and improving the operation stability of the rotor system.
The above description is only for the specific embodiment of the present invention, but the scope of the present invention 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 invention are included in the scope of the present invention.
Claims (6)
1. A stiffness repairable support structure of a rotor for a blade loss failure, comprising: a supporting outer frame and a core actuating element; the supporting outer frame comprises a mounting shell and a reentry type squirrel cage, provides partial supporting rigidity for the rotor, is used for mounting a core actuating element and can limit the radial amplitude of the rotor; the core actuating element is designed based on a chiral honeycomb unit cell structure, provides partial supporting rigidity for the rotor, and can be actively adjusted; the rigidity repairable supporting structure can bear the loss impact of the blades without damage, fracture and damage, and the core actuating element is restored to the original structural shape by heating, so that the structural repair and rigidity restoration are realized, and the stability and safety of the rotor are improved.
2. The stiffness repairable support structure of claim 1, wherein: the core actuating elements are circumferentially distributed in the mounting grooves at equal intervals, the number of the core actuating components is even, and the radial support rigidity at the rotor fulcrum is ensured to be uniformly distributed.
3. The stiffness repairable support structure of claim 1, wherein: the core actuating component and the reentry type squirrel cage are in a parallel relation, and the proportion of the supporting rigidity of the core actuating component and the reentry type squirrel cage is determined according to the vibration characteristics of the rotor.
4. The stiffness repairable support structure of claim 1, wherein: the structural form of the chiral honeycomb unit cell is a polygonal structure and is formed by connecting a cylinder and a rib plate; the polygonal structure comprises a triangle, a quadrangle, a pentagon, a hexagon, a heptagon or an octagon; adjusting and designing geometric design parameters of the width of a ribbed plate, the radius of a cylinder, the thickness of the single cell and the radius of a fillet at the joint of the ribbed plate and the cylinder according to requirements; and the core actuating component adjusts the circumferential component layer number and the radial component layer number of the chiral honeycomb unit cell according to the requirement.
5. The stiffness repairable support structure of claim 1, wherein: the mounting shell is provided with limiting blocks, the limiting blocks are distributed on the mounting shell along the circumferential direction, the middle of the mounting shell is hollowed to reduce the structural weight, an installation space is provided for the core actuating component, the circumferential displacement of the core actuating component is limited, the supporting rigidity of the variable-rigidity supporting structure is ensured to be relatively uniform along the circumferential direction after the core actuating component is subjected to large deformation, and the large deformation refers to the maximum allowable radial deformation of the supporting position in the safety design of the rotor; the radial length of the limiting block is adjusted according to design requirements, the core actuating assembly is protected, and damage caused by the fact that the amplitude of the rotor exceeds the maximum allowable radial deformation are prevented.
6. The stiffness repairable support structure of claim 1, wherein: after the stiffness repairable support structure is subjected to impact load generated by blade loss, the radial stiffness of the core actuating assembly is the characteristic of slope descending in the large deformation process, so that the instantaneous change of the rotor support stiffness is avoided; the core actuating element can not be broken in the large deformation process, and the subsequent functional use of the core actuating element is ensured; the core actuating component is made of shape memory alloy, and the structural characteristics and rigidity characteristics of the core actuating element are repaired in a heating mode after large deformation occurs.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111577604.9A CN114233409B (en) | 2021-12-22 | 2021-12-22 | Rigidity repairable supporting structure for rotor with blade loss fault |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111577604.9A CN114233409B (en) | 2021-12-22 | 2021-12-22 | Rigidity repairable supporting structure for rotor with blade loss fault |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114233409A CN114233409A (en) | 2022-03-25 |
| CN114233409B true CN114233409B (en) | 2023-03-24 |
Family
ID=80760993
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111577604.9A Active CN114233409B (en) | 2021-12-22 | 2021-12-22 | Rigidity repairable supporting structure for rotor with blade loss fault |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114233409B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105822366A (en) * | 2016-04-20 | 2016-08-03 | 中国科学院工程热物理研究所 | Low-pressure rotor supporting structure of engine with fusing design |
| CN107780984A (en) * | 2016-08-31 | 2018-03-09 | 中国航发商用航空发动机有限责任公司 | Can be failed rotor support structure and aero-engine |
| CN108071429A (en) * | 2016-11-17 | 2018-05-25 | 中国航发商用航空发动机有限责任公司 | Can fail rotor support structure and aero-engine |
| CN109583062A (en) * | 2018-11-20 | 2019-04-05 | 东北大学 | A kind of endless-ringlock elastic support structure stiffness optimization design method |
| CN110500146A (en) * | 2018-05-17 | 2019-11-26 | 中国航发商用航空发动机有限责任公司 | The rotor support structure that fails of aero-engine |
| CN111746443A (en) * | 2020-06-29 | 2020-10-09 | 南京航空航天大学 | Novel three-dimensional chiral negative Poisson ratio multicellular energy absorption structure |
| CN112049814A (en) * | 2019-06-06 | 2020-12-08 | 中国航发商用航空发动机有限责任公司 | Fan rotor support system and bearing support device that can lose efficacy of aeroengine |
| CN113565792A (en) * | 2021-07-21 | 2021-10-29 | 中国航空发动机研究院 | Elastic supporting structure |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9777592B2 (en) * | 2013-12-23 | 2017-10-03 | Pratt & Whitney Canada Corp. | Post FBO windmilling bumper |
-
2021
- 2021-12-22 CN CN202111577604.9A patent/CN114233409B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105822366A (en) * | 2016-04-20 | 2016-08-03 | 中国科学院工程热物理研究所 | Low-pressure rotor supporting structure of engine with fusing design |
| CN107780984A (en) * | 2016-08-31 | 2018-03-09 | 中国航发商用航空发动机有限责任公司 | Can be failed rotor support structure and aero-engine |
| CN108071429A (en) * | 2016-11-17 | 2018-05-25 | 中国航发商用航空发动机有限责任公司 | Can fail rotor support structure and aero-engine |
| CN110500146A (en) * | 2018-05-17 | 2019-11-26 | 中国航发商用航空发动机有限责任公司 | The rotor support structure that fails of aero-engine |
| CN109583062A (en) * | 2018-11-20 | 2019-04-05 | 东北大学 | A kind of endless-ringlock elastic support structure stiffness optimization design method |
| CN112049814A (en) * | 2019-06-06 | 2020-12-08 | 中国航发商用航空发动机有限责任公司 | Fan rotor support system and bearing support device that can lose efficacy of aeroengine |
| CN111746443A (en) * | 2020-06-29 | 2020-10-09 | 南京航空航天大学 | Novel three-dimensional chiral negative Poisson ratio multicellular energy absorption structure |
| CN113565792A (en) * | 2021-07-21 | 2021-10-29 | 中国航空发动机研究院 | Elastic supporting structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114233409A (en) | 2022-03-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP3205840B1 (en) | Rotor support system with shape memory alloy components for a gas turbine engine | |
| US4149824A (en) | Blade containment device | |
| CN107975425B (en) | Load reduction assembly for gas turbine engine | |
| RU2478800C2 (en) | Guide element of shaft in turbomachine | |
| JP4815080B2 (en) | Method and apparatus for supporting an unbalanced rotor assembly | |
| US6079200A (en) | Ducted fan gas turbine engine with fan shaft frangible connection | |
| US8262353B2 (en) | Decoupler system for rotor assemblies | |
| US8167531B2 (en) | Method and apparatus for supporting rotor assemblies during unbalances | |
| US10634007B2 (en) | Rotor support system having a shape memory alloy | |
| CN105822366A (en) | Low-pressure rotor supporting structure of engine with fusing design | |
| US10077663B2 (en) | Gas turbine engine rotor stack assembly | |
| US20110048029A1 (en) | Turbomachine core coupling assembly | |
| EP3349336B1 (en) | Maintaining double feed induction generator wye ring | |
| CN111894737B (en) | Rotor support structure and gas turbine | |
| CN114233409B (en) | Rigidity repairable supporting structure for rotor with blade loss fault | |
| EP2155555B1 (en) | A mounting element for a gas turbine engine, and a structure and an aircraft with such a mounting element | |
| US20190170012A1 (en) | Method and device for connecting fan rotor to low pressure turbine rotor | |
| US20020070558A1 (en) | Windmill having speed-sensitive control system | |
| JP2012233474A (en) | Turbine engine and load reduction device thereof | |
| CN112049814B (en) | Fan rotor support system and bearing support device that can lose efficacy of aeroengine | |
| US7026736B2 (en) | Turbine generator vibration damper system | |
| JP2002303104A (en) | Combined cycle power generating facility, and its installing method | |
| CN209781044U (en) | Fan rotor support system | |
| US11542820B2 (en) | Turbomachinery blade and method of fabricating | |
| CN115822780A (en) | Supporting conical wall, fan rotor supporting structure and supporting conical wall installation method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |