CN113697099A - Repairing structure and method for damaged inner surface of helicopter root bushing - Google Patents
Repairing structure and method for damaged inner surface of helicopter root bushing Download PDFInfo
- Publication number
- CN113697099A CN113697099A CN202110656019.1A CN202110656019A CN113697099A CN 113697099 A CN113697099 A CN 113697099A CN 202110656019 A CN202110656019 A CN 202110656019A CN 113697099 A CN113697099 A CN 113697099A
- Authority
- CN
- China
- Prior art keywords
- bushing
- root
- bush
- paddle
- blade
- 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.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 13
- 230000001681 protective effect Effects 0.000 claims abstract description 28
- 230000008439 repair process Effects 0.000 claims abstract description 18
- 239000002131 composite material Substances 0.000 claims abstract description 15
- 238000001035 drying Methods 0.000 claims abstract description 10
- 239000000565 sealant Substances 0.000 claims abstract description 10
- 239000004677 Nylon Substances 0.000 claims abstract description 5
- 229920001778 nylon Polymers 0.000 claims abstract description 5
- 239000000853 adhesive Substances 0.000 claims description 10
- 230000001070 adhesive effect Effects 0.000 claims description 9
- 238000005520 cutting process Methods 0.000 claims description 9
- 241000143392 Oar Species 0.000 claims description 4
- 238000001514 detection method Methods 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 3
- 238000003754 machining Methods 0.000 claims description 2
- 206010028980 Neoplasm Diseases 0.000 claims 1
- 150000001875 compounds Chemical class 0.000 claims 1
- 238000010276 construction Methods 0.000 claims 1
- 239000000463 material Substances 0.000 claims 1
- 230000007797 corrosion Effects 0.000 abstract description 5
- 238000005260 corrosion Methods 0.000 abstract description 5
- 239000002184 metal Substances 0.000 abstract description 5
- 229910052751 metal Inorganic materials 0.000 abstract description 5
- 230000005540 biological transmission Effects 0.000 abstract description 3
- 238000009434 installation Methods 0.000 abstract description 3
- 150000002739 metals Chemical class 0.000 abstract description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000005498 polishing Methods 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 238000002791 soaking Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
- B64C27/48—Root attachment to rotor head
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Mechanical Engineering (AREA)
Abstract
The invention belongs to the technical field of repairing a composite material blade of a helicopter, and particularly relates to a repairing structure and a repairing method for a damaged inner surface of a blade root lining of a helicopter. The damaged inner surface of the lining has faults of pits, cracks, corrosion, deformation and the like, so that the stress and the force transmission of the root of the blade are influenced, and the fatigue life of the blade is shortened. The repair structure comprises a support bushing, an inner bushing and a protection washer, wherein the support bushing is inserted in the middle area of the propeller root bushing in a clearance fit manner, the inner bushing is arranged at two ends of the support bushing, and the inner bushing and the propeller root bushing are in interference fit; and protective gaskets are also arranged on the parts of the blade root bushings, which exceed the upper surface and the lower surface of the composite material blade. The damage fault of the inner surface of the bushing is eliminated by embedding the inner bushing; the nylon protective washer can prevent the end surfaces of the metal bushing and the hub from being worn; the non-drying sealant can effectively prevent corrosion between metals; the accurate assembly auxiliary fixtures of bush has guaranteed the installation accuracy of longitudinal symmetry type bush.
Description
Technical Field
The invention belongs to the technical field of repairing a composite material blade of a helicopter, and particularly relates to a repairing structure and a repairing method for a damaged inner surface of a blade root lining of a helicopter.
Background
The root of the blade is a key part for connecting the composite material blade and the hub, and is a region with the most complex stress of the blade, and the mass of the blade directly influences the load transmission and the fatigue life of the blade. The bushing is the most important part in the root area of the blade, and is a bridge for continuously transmitting the lift force obtained by the high-speed motion of the rotor blade to the helicopter body. If the lining is damaged, the inner surface has faults of pits, cracks, corrosion, deformation and the like, the stress and the force transmission of the root of the blade are influenced, and the fatigue life of the blade is reduced.
In order to consider factors such as flight safety, once the composite material root bushing has a problem of complaint failure, the existing processing method is to stop the failed blade and replace the failed blade with a new rotor blade. The processing mode is simple and direct, and although the use safety of the helicopter can be ensured, the resource is greatly wasted. The failed blade that is out of service is often not repaired effectively and may be disposed of.
Disclosure of Invention
The purpose of the invention is as follows: aiming at the existing problems, the stable and reliable repair structure and method for the damaged inner surface of the helicopter root bushing are provided.
The technical scheme of the invention is as follows: the repairing structure comprises a supporting bush, an inner bush and a protective washer, wherein the supporting bush is inserted in the middle area of the paddle root bush in a clearance fit manner, the inner bush is installed at two ends of the supporting bush, and the inner bush and the paddle root bush are in interference fit; and protective gaskets are also arranged on the parts of the blade root bushings, which exceed the upper surface and the lower surface of the composite material blade.
Further, the surface of the inner liner which is matched with the paddle root liner is also coated with a non-drying sealant.
Furthermore, the abutting surfaces of the protective washer and the upper surface and the lower surface of the composite paddle are coated with adhesive.
Further, the outer end face of the protective washer extends beyond the outer end face of the paddle root bushing.
Further, the height of the protective washer is no more than 0.5mm beyond the extent of the root bushing.
Further, the outer end face of the inner bushing must not exceed the outer end face of the root bushing.
Further, the outer end face of the inner liner has an invagination of no more than 0.5mm relative to the outer end face of the root liner.
Furthermore, the protective washer is made of nylon, the inner diameter of the protective washer is 0.5-1.0mm larger than the outer diameter of the end face of the paddle root bushing, and the outer diameter of the protective washer is 7-9mm larger than the outer diameter of the end face of the paddle root bushing.
The invention also provides a method for repairing the damaged inner surface of the helicopter root bushing, which utilizes the repairing structure and comprises the following steps:
the first step is as follows: inspecting the damaged area of the inner surface of the paddle root bushing, and determining the range of the damaged area;
the second step is that: according to the damage detection result, mechanically boring the paddle root bushing until the size of the paddle root bushing is processed until no damage area exists on the inner surface of the paddle root bushing, measuring the aperture a of the paddle root bushing, and calculating the boring cutting amount b;
the third step: processing an inner bushing and a support bushing, wherein the inner bushing meets the interference fit with the propeller root bushing; the supporting bush is in clearance fit with the paddle root bush;
the fourth step: installing an inner bushing and a support bushing in an inner hole of the paddle root bushing according to the repair structure;
the fifth step: polishing the surface of the composite material blade around the propeller root bushing to be rough, wiping the surface clean, adhering a protective gasket to the outer side of the propeller root bushing by using an adhesive, cleaning the adhesive nodules after curing, and polishing for transition;
and a sixth step: and (4) finishing boring according to the aperture size of the assembled bushing, and recovering to the size of the propeller root bushing before damage.
Furthermore, the interference magnitude of a matching pair of the inner bushing and the paddle root bushing is 0.06-0.08mm, and the wall thickness is 2-3mm greater than the boring cutting amount b; the clearance of the matching pair of the supporting bush and the paddle root bush is not more than 0.1mm at most, and the wall thickness is 1-2mm smaller than the bore hole cutting amount b.
The invention has the beneficial effects that: the damage fault of the inner surface of the bushing is eliminated by embedding the inner bushing; the nylon protective washer can prevent the end surfaces of the metal bushing and the hub from being worn; the non-drying sealant can effectively prevent corrosion between metals; the accurate assembly auxiliary fixtures of bush has guaranteed the installation accuracy of longitudinal symmetry type bush. The practice proves that the repair quality is reliable and stable.
Drawings
The illustrative examples, as well as a preferred mode of use, further objectives, and descriptions thereof, will best be understood by reference to the following detailed description of an example of the present invention when read in conjunction with the accompanying drawings, wherein:
FIG. 1 is a schematic view of a repair structure according to the present invention;
FIG. 2 is a schematic illustration of the installation of a repair structure embodying the present invention;
FIG. 3 is a tooling structure for implementing the repair structure of the present invention.
Wherein, 1-composite material blade, 2-blade root bushing, 3-support bushing, 4-inner bushing, 5-non-drying sealant, 6-protective gasket, and 7-adhesive
Detailed Description
The disclosed examples will be described more fully with reference to the accompanying drawings, in which some (but not all) of the disclosed examples are shown. Indeed, many different examples may be described and should not be construed as limited to the examples set forth herein. Rather, these examples are described so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
Referring to fig. 1, the stable and reliable repair structure for damaged inner surfaces of bushings provided by the invention comprises a composite blade 1, a blade root bushing 2, a support bushing 3, an inner bushing 4, a non-drying sealant 5, a protective washer 6 and an adhesive 7. Each of the root bushings 2 is equipped with two inner bushings 4 and one support bushing 3, respectively, the support bushing 3 being located in the middle of the two inner bushings 4; the assembly fit of the inner bushing 4 and the paddle root bushing 2 is interference fit, and the assembly fit of the support bushing 3 and the paddle root bushing 2 is clearance fit.
A layer of non-drying sealant 5 is coated on the matching surface of the inner bushing 4 and the propeller root bushing 2, so that the metal surface is protected from corrosion; the protective washer 6 is made of nylon and is annular in shape, the inner diameter of the protective washer is 0.5-1.0mm larger than the outer diameter of the end face of the paddle root bush 2, the outer diameter of the protective washer is 7-9mm larger than the outer diameter of the end face of the paddle root bush 2, and the height of the protective washer 6 after being bonded is slightly higher than the height of the end face of the paddle root bush 2 but not higher than 0.5 mm.
The protective washer 6 is adhered to the surface of the composite blade 1 and is positioned on the outer side of the end face of the blade root bushing 2 through the adhesive 7. The non-drying sealant 5 is preferably MF-1 (type J). The adhesive 7 is preferably EA9309.3NA.
In order to achieve the above-mentioned purpose, the present invention provides a stable and reliable method for repairing damaged inner surface of bushing, comprising:
the first step is as follows: inspecting the damaged area of the inner surface of the blade root lining 2, and determining the range of the damaged area;
the second step is that: according to the damage detection result, mechanically boring the paddle root bushing 2 until the inner surface of the bushing has no damaged area. After the machining is finished, the current hole diameter a of the propeller root bushing 2 is measured, and the boring cutting amount b is calculated.
The third step: the inner bush 4 and the support bush 3 are machined. The interference range of the interference fit pair formed by the outer diameter of the inner bushing 4 and the current aperture a of the paddle root bushing 2 is suggested to be 0.06-0.08mm, and the wall thickness is 2-3mm larger than the bore hole cutting amount b; the clearance of the clearance fit pair formed by the outer diameter of the supporting bush 3 and the current aperture a of the paddle root bush 2 is not more than 0.1mm at most, and the wall thickness is 1-2mm smaller than the bore hole cutting amount b.
The fourth step: two inner bushings 4 and one supporting bushing 3 are respectively assembled on each paddle root bushing 2, the supporting bushing 3 is located in the middle of the two inner bushings 4, and the inner bushings 4 and the paddle root bushings 2 are assembled through temperature difference to complete interference fit. When assembled, the end face of the inner bushing 4 must not be higher than the end face of the root bushing 2, allowing a maximum invagination of 0.5 mm.
The fifth step: the blade surface of the composite material 1 around the blade root bushing 2 is roughly polished and wiped clean, and the protective washer 6 is adhered to the periphery of the blade root bushing 2 by using EA9309.3NA adhesive. After curing, the nodules are cleaned and polished for transition.
And a sixth step: and (4) finishing boring according to the aperture size of the assembled bushing, and recovering to the size of the propeller root bushing 2 before damage.
When the inner bushing 4 is assembled with the propeller root bushing 2, a layer of MF-1(J type) non-drying sealant needs to be coated on the matching surface.
When neck bush 4 and the difference in temperature assembly of oar root bush 2, can use the accurate assembly auxiliary fixtures of neck bush, including depression bar 8, guide pin bushing 9, base 10.
The diameter of the pressure lever 8 is in clearance fit with the inner diameter of the guide sleeve 9, and the clearance of the matching pair is recommended to be 0.03-0.12 mm; the diameter of the pressure lever 8 is in clearance fit with the inner diameter of the inner bushing 4, and the clearance of a matching pair is recommended to be 0.05-0.12 mm; the outer diameter of the guide sleeve 9 is in clearance fit with the hole diameter a after the bushing is bored, and the clearance of a matching pair is recommended to be 0.03-0.08mm.
The precise assembly method of the inner bushing 4 comprises the following steps: the paddle root bushing 2 is horizontally placed on the end face of the base 10, and the pressing rod 8 can freely penetrate through a through hole in the base 10; the guide sleeve 9 is arranged on the paddle root lining 2 close to one side of the base, and can ensure that the pressure lever 8 can freely pass through; cooling the inner liner 4 in liquid nitrogen, soaking for 5-8 minutes after the inner liner is boiled vigorously and subsides, taking out, smearing a layer of MF-1(J type) non-drying sealant, sleeving the pressure rod 8, and pressing into the paddle root bush 2 quickly.
Different examples of the systems, devices, and methods disclosed herein include various components, features, and functions. It should be understood that the various examples of the systems, devices, and methods disclosed herein may include any of the components, features, and functions of any of the other examples of the systems, devices, and methods disclosed herein in any combination or sub-combination, and all such possibilities are intended to fall within the scope of the present invention.
The description of the different advantageous arrangements has been presented for purposes of illustration and description, but is not intended to be exhaustive or limited to the examples in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. Additionally, the different advantageous examples may describe different advantages as compared to other advantageous examples. The example or examples selected are chosen and described in order to best explain the principles of the examples, the practical application, and to enable others of ordinary skill in the art to understand the disclosure for various examples with various modifications as are suited to the particular use contemplated.
Claims (10)
1. The utility model provides a restoration structure after helicopter oar root bush internal surface damage, compound material paddle (1) before restoreing have the oar root bush (2) of running through the upper and lower surface at root integral type embedding, take place to adopt this restoration structure, its characterized in that after damaging to oar root bush (2): the repairing structure comprises a supporting bush (3), an inner bush (4) and a protective washer (6), wherein the supporting bush (3) is inserted in the middle area of the propeller root bush (2) in a clearance fit mode, the inner bush (4) is installed at two ends of the supporting bush (3), and the inner bush (4) is in interference fit with the propeller root bush (2); and a protective gasket (6) is also arranged on the part of the blade root lining (2) which exceeds the upper surface and the lower surface of the composite blade (1).
2. The repair structure of claim 1, wherein: the surface of the inner liner (4) which is matched with the paddle root liner (2) is also coated with a non-drying sealant (5).
3. The repair structure of claim 2, wherein: the abutting surfaces of the upper surface and the lower surface of the protective washer (6) and the composite paddle (1) are coated with adhesives (7).
4. The repair structure of any one of claims 1 to 3, wherein: the outer end face of the protection gasket (6) exceeds the outer end face of the paddle root bushing (2).
5. The repair structure of claim 4, wherein: the height of the protective washer (6) exceeds the range of the paddle root bushing (2) and is not higher than 0.5 mm.
6. The repair structure of any one of claims 1 to 3, wherein: the outer end face of the inner lining (4) does not exceed the outer end face of the propeller root lining (2).
7. The repair structure of claim 6, wherein: the outer end face of the inner bushing (4) has an invagination of no more than 0.5mm relative to the outer end face of the blade root bushing (2).
8. The repair structure of any one of claims 1 to 3, wherein: the protective washer (6) is made of nylon, the inner diameter of the protective washer is 0.5-1.0mm larger than the outer diameter of the end face of the paddle root bushing (2), and the outer diameter of the protective washer is 7-9mm larger than the outer diameter of the end face of the paddle root bushing (2).
9. A method of repairing damaged inner surfaces of helicopter root bushings using a repair construction according to any of claims 1 to 8, characterized in that it comprises the following steps:
the first step is as follows: inspecting the damaged area of the inner surface of the paddle root bushing (2) and determining the range of the damaged area;
the second step is that: according to the damage detection result, mechanically boring the paddle root bushing (2), machining the size until no damage area exists on the inner surface of the paddle root bushing (2), measuring the aperture a of the paddle root bushing (2), and calculating the boring cutting amount b;
the third step: processing an inner bushing (4) and a support bushing (3), wherein the inner bushing (4) is in interference fit with the propeller root bushing; the supporting bush (4) is in clearance fit with the paddle root bush (2);
the fourth step: installing an inner bushing (4) and a support bushing (3) in an inner hole of the paddle root bushing (2) according to the repair structure;
the fifth step: the surface of a composite material blade around the blade root bushing is polished roughly and cleaned, a protective gasket (6) is adhered to the outer side of the blade root bushing (2) by using an adhesive (7), and after the protective gasket is cured, the rubber tumors are cleaned and polished for transition;
and a sixth step: and (4) finishing boring according to the aperture size of the assembled bushing, and recovering to the size of the propeller root bushing before damage.
10. The repair method according to claim 9, characterized in that: the interference magnitude of a matching pair of the inner bushing (3) and the paddle root bushing is 0.06-0.08mm, and the wall thickness is 2-3mm greater than the boring cutting amount b; the clearance of the matching pair of the supporting bush (3) and the paddle root bush (2) is not more than 0.1mm at most, and the wall thickness is 1-2mm smaller than the bore hole cutting amount b.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110656019.1A CN113697099A (en) | 2021-06-11 | 2021-06-11 | Repairing structure and method for damaged inner surface of helicopter root bushing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110656019.1A CN113697099A (en) | 2021-06-11 | 2021-06-11 | Repairing structure and method for damaged inner surface of helicopter root bushing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113697099A true CN113697099A (en) | 2021-11-26 |
Family
ID=78648130
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110656019.1A Pending CN113697099A (en) | 2021-06-11 | 2021-06-11 | Repairing structure and method for damaged inner surface of helicopter root bushing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113697099A (en) |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0263713A1 (en) * | 1986-10-08 | 1988-04-13 | Chromalloy Gas Turbine Corporation | Method for repairing by solid state diffusion metal parts having damaged holes |
| US4872519A (en) * | 1988-01-25 | 1989-10-10 | Eastman Christensen Company | Drill string drill collars |
| DE10064611A1 (en) * | 2000-12-22 | 2002-06-27 | Ina Schaeffler Kg | Seal for bearing holder has bearing bush which can rotate relative to axially supported bush |
| US20040240991A1 (en) * | 2003-05-27 | 2004-12-02 | Bruce Robert W. | Variable stator vane bushings and washers |
| EP1967678A1 (en) * | 2007-03-07 | 2008-09-10 | Wilfried Nofen | Hinge |
| CN103350313A (en) * | 2013-05-31 | 2013-10-16 | 中钢集团邢台机械轧辊有限公司 | Repair technology of cold mold for centrifugal casting of roller |
| CN104551528A (en) * | 2013-10-21 | 2015-04-29 | 哈尔滨飞机工业集团有限责任公司 | Thermoelectric assembly method of composite blade embedded bushing |
| CN105436041A (en) * | 2014-09-19 | 2016-03-30 | 中石化胜利油建工程有限公司 | Steel-pipe internal-coating glass fiber reinforced plastic mouth-repairing apparatus |
| US20160102688A1 (en) * | 2014-10-08 | 2016-04-14 | Airbus Helicopters Deutschland GmbH | Composite laminate and load-introduction component for a load-introduction joint |
| CN108069031A (en) * | 2016-11-14 | 2018-05-25 | 昌河飞机工业（集团）有限责任公司 | A kind of structure and assembly technology of blade jointing |
| CN209274873U (en) * | 2018-11-05 | 2019-08-20 | 中国航空工业集团公司西安飞机设计研究所 | A kind of composite joint of embedded bushing component |
| CN110280968A (en) * | 2019-05-23 | 2019-09-27 | 中国人民解放军第五七一九工厂 | A kind of motor oil pump group composite material lining repairs dress method |
| CN110587541A (en) * | 2019-09-06 | 2019-12-20 | 北京星航机电装备有限公司 | Quick installation method for deep lining |
-
2021
- 2021-06-11 CN CN202110656019.1A patent/CN113697099A/en active Pending
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0263713A1 (en) * | 1986-10-08 | 1988-04-13 | Chromalloy Gas Turbine Corporation | Method for repairing by solid state diffusion metal parts having damaged holes |
| US4872519A (en) * | 1988-01-25 | 1989-10-10 | Eastman Christensen Company | Drill string drill collars |
| DE10064611A1 (en) * | 2000-12-22 | 2002-06-27 | Ina Schaeffler Kg | Seal for bearing holder has bearing bush which can rotate relative to axially supported bush |
| US20040240991A1 (en) * | 2003-05-27 | 2004-12-02 | Bruce Robert W. | Variable stator vane bushings and washers |
| EP1967678A1 (en) * | 2007-03-07 | 2008-09-10 | Wilfried Nofen | Hinge |
| CN103350313A (en) * | 2013-05-31 | 2013-10-16 | 中钢集团邢台机械轧辊有限公司 | Repair technology of cold mold for centrifugal casting of roller |
| CN104551528A (en) * | 2013-10-21 | 2015-04-29 | 哈尔滨飞机工业集团有限责任公司 | Thermoelectric assembly method of composite blade embedded bushing |
| CN105436041A (en) * | 2014-09-19 | 2016-03-30 | 中石化胜利油建工程有限公司 | Steel-pipe internal-coating glass fiber reinforced plastic mouth-repairing apparatus |
| US20160102688A1 (en) * | 2014-10-08 | 2016-04-14 | Airbus Helicopters Deutschland GmbH | Composite laminate and load-introduction component for a load-introduction joint |
| CN108069031A (en) * | 2016-11-14 | 2018-05-25 | 昌河飞机工业（集团）有限责任公司 | A kind of structure and assembly technology of blade jointing |
| CN209274873U (en) * | 2018-11-05 | 2019-08-20 | 中国航空工业集团公司西安飞机设计研究所 | A kind of composite joint of embedded bushing component |
| CN110280968A (en) * | 2019-05-23 | 2019-09-27 | 中国人民解放军第五七一九工厂 | A kind of motor oil pump group composite material lining repairs dress method |
| CN110587541A (en) * | 2019-09-06 | 2019-12-20 | 北京星航机电装备有限公司 | Quick installation method for deep lining |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4980241A (en) | Foil insert in a joint between machine components | |
| US6339878B1 (en) | Method of repairing an airfoil | |
| US7182579B2 (en) | Device and method for detachably connecting an impeller to a shaft | |
| US7980813B2 (en) | Fan outlet guide vane shroud insert repair | |
| US7047596B2 (en) | Structural bushing application for highly loaded composites lugs | |
| WO1996041068A1 (en) | Anti-fretting barrier | |
| CN102762336B (en) | A kind of method of repairing casing ledge | |
| CN101469801A (en) | On-line repair method for bellows | |
| US7434383B2 (en) | Bypass duct boss repair technology | |
| CN113697099A (en) | Repairing structure and method for damaged inner surface of helicopter root bushing | |
| CN108971881B (en) | Rotary mechanism abrasion repairing method | |
| US20110293409A1 (en) | Method of repairing a flange of a casing | |
| CN110280968B (en) | Repairing and assembling method for composite material bushing of engine lubricating oil pump set | |
| JP2001012208A (en) | Connection structure of turbine rotor blade and disk | |
| CN107923251B (en) | Gas turbine or compressor blade and rotor having a coating resistant to fretting in the region of the blade root | |
| EP3748125A1 (en) | Methods for repairing a multi-layer coated component | |
| CN212429538U (en) | Positioning structure of metal sealing ring | |
| CN217233648U (en) | Turbine shaft end fixing device | |
| US10801369B2 (en) | Intermediate casing of a turbine engine, provided with a sealing part at the arm/shroud interface | |
| CN217899007U (en) | High-bearing bronze flanging bushing | |
| CN212615885U (en) | Supporting roller bearing | |
| CN210909213U (en) | Dustproof device for precision numerical control lathe spindle | |
| CN213144922U (en) | Needle type cylinder | |
| CN115203765B (en) | Design method of balancing weight for low-cycle fatigue test of aero-engine rotor | |
| CN219755657U (en) | Multi-seal quick rotary joint |
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 |