CN115074719A - Composite repairing method for cracks around holes of ordnance casting integral part based on cold spraying additive - Google Patents
Composite repairing method for cracks around holes of ordnance casting integral part based on cold spraying additive Download PDFInfo
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- CN115074719A CN115074719A CN202210727519.4A CN202210727519A CN115074719A CN 115074719 A CN115074719 A CN 115074719A CN 202210727519 A CN202210727519 A CN 202210727519A CN 115074719 A CN115074719 A CN 115074719A
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- cold spraying
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- ordnance
- cracks around
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- 238000010288 cold spraying Methods 0.000 title claims abstract description 25
- 239000000654 additive Substances 0.000 title claims abstract description 15
- 230000000996 additive effect Effects 0.000 title claims abstract description 15
- 238000005266 casting Methods 0.000 title claims abstract description 15
- 238000000034 method Methods 0.000 title claims abstract description 15
- 239000002131 composite material Substances 0.000 title claims abstract description 10
- 230000008439 repair process Effects 0.000 claims abstract description 17
- 238000007689 inspection Methods 0.000 claims abstract description 9
- 229910000838 Al alloy Inorganic materials 0.000 claims abstract description 7
- 238000001514 detection method Methods 0.000 claims abstract description 6
- 238000001125 extrusion Methods 0.000 claims abstract description 6
- 238000003754 machining Methods 0.000 claims abstract description 6
- 238000004040 coloring Methods 0.000 claims abstract description 5
- 238000009434 installation Methods 0.000 claims abstract description 5
- 238000012544 monitoring process Methods 0.000 claims abstract description 5
- 239000003973 paint Substances 0.000 claims abstract description 5
- 239000007789 gas Substances 0.000 claims description 11
- 239000000843 powder Substances 0.000 claims description 10
- 239000000463 material Substances 0.000 claims description 9
- 238000004458 analytical method Methods 0.000 claims description 8
- 229910052751 metal Inorganic materials 0.000 claims description 7
- 239000002184 metal Substances 0.000 claims description 7
- 238000004364 calculation method Methods 0.000 claims description 4
- 238000009826 distribution Methods 0.000 claims description 4
- 238000012545 processing Methods 0.000 claims description 4
- 238000012795 verification Methods 0.000 claims description 4
- 238000011156 evaluation Methods 0.000 claims description 3
- 239000001307 helium Substances 0.000 claims description 3
- 229910052734 helium Inorganic materials 0.000 claims description 3
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims description 3
- 230000008901 benefit Effects 0.000 abstract description 6
- 239000011159 matrix material Substances 0.000 abstract description 3
- 208000037656 Respiratory Sounds Diseases 0.000 abstract description 2
- 230000000295 complement effect Effects 0.000 abstract description 2
- 150000001875 compounds Chemical class 0.000 abstract description 2
- 238000012423 maintenance Methods 0.000 abstract description 2
- 239000011148 porous material Substances 0.000 abstract description 2
- 238000005259 measurement Methods 0.000 abstract 1
- 239000007921 spray Substances 0.000 description 5
- 238000000151 deposition Methods 0.000 description 3
- 239000002245 particle Substances 0.000 description 3
- 230000008021 deposition Effects 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000010200 validation analysis Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/02—Coating starting from inorganic powder by application of pressure only
- C23C24/04—Impact or kinetic deposition of particles
- C23C24/045—Impact or kinetic deposition of particles by trembling using impacting inert media
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/10—Formation of a green body
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/60—Treatment of workpieces or articles after build-up
- B22F10/66—Treatment of workpieces or articles after build-up by mechanical means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y10/00—Processes of additive manufacturing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y40/00—Auxiliary operations or equipment, e.g. for material handling
- B33Y40/20—Post-treatment, e.g. curing, coating or polishing
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
- G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces
Abstract
The invention relates to the technical field of military aviation maintenance, in particular to a composite repairing method for cracks around a hole of a ordnance casting integral part based on cold spraying additive, which realizes the repairing of the local size of the crack and the performance of a matrix material by using a series of steps of crack removal, flaw detection, size measurement, cold spraying repair, X-ray inspection, machining, flaw detection (surface coloring and internal X-ray), paint repair, lining installation, assembly and core inspection, first part identification, assembly and monitoring; the installation adopts the bush to improve the extrusion strength and the assembly interchangeability of pore wall, and the two compound advantages are complementary, have realized the restoration to high strength aluminum alloy whole piece hole angle crackle, have effectively reduced the disability rate of whole piece, have improved cycle economic benefits and the rate of reuse of whole piece.
Description
Technical Field
The invention relates to the technical field of military aviation maintenance, in particular to a composite repairing method for cracks around holes of a ordnance casting integral part based on cold spraying additive.
Background
The universal hanger for the weapon system needs to adopt an integral casting part structure, the failure rate of the high-strength aluminum alloy integral part hole corner cracks is high, the cracks cannot be repaired by adopting single high-heat-cycle welding, the rejection rate is high, the rejection cost is increased, the purchase period is prolonged, and the use and equipment availability is influenced.
Cold spray, also known as cold gas dynamic spray, is a material deposition technique based on gas dynamics. High-speed gas (He, N2, Ar, air or mixed gas thereof) (the gas temperature is lower than 800 ℃) heated to a certain temperature carries micrometer-scale (5-50 mu m) spray particles, the spray particles are accelerated by a Laval nozzle and then impact a matrix at a high speed (300-1200 m/s) under the condition of complete solid state, and when the particles exceed the deposition critical speed, the continuous accumulation deposition of the material is realized through violent plastic deformation during collision.
Therefore, the composite repairing method for the cracks around the holes of the ordnance casting integral part based on cold spraying additive needs to be designed, the technical problems are solved, the crack failure rate of the high-strength aluminum alloy integral part is reduced through a unique cold spraying process and quality inspection verification after repair, the equipment integrity and the periodic economic benefit are guaranteed, and the method has the popularization significance of similar products.
Disclosure of Invention
The invention aims to provide a composite repairing method for cracks around a hole of a ordnance casting integral part based on cold spraying additive, which aims to solve the problems in the background technology.
In order to achieve the purpose, the invention provides the following technical scheme: a composite repairing method for cracks around holes of ordnance casting integral parts based on cold spraying additive comprises the following steps:
s1: repairability evaluation, namely, finite element calculation of the stress distribution of the whole fork ear hole stress analysis and residual strength analysis;
s2: removing cracks around the fork ear hole of the integral part to be repaired, and measuring the size around the hole to be repaired after flaw detection;
s3: using high-pressure power gas to perform material increase repair on the periphery of the hole to be repaired by using high-strength metal powder in a cold spraying mode;
s4: carrying out X-ray inspection on the cold spraying additive repairing part to confirm whether unrepaired points exist at the cold spraying part;
s5: machining the repaired part to adapt the size of the repaired part to the size of the integral part;
s6: the repaired part after mechanical processing is inspected again in a surface coloring and internal X-ray mode;
s7: after the repaired part is subjected to paint repair, a bushing is installed, so that the extrusion strength and assembly interchangeability of the hole wall are improved;
s8: and performing first piece identification after assembly verification, and monitoring and using after assembly.
The high pressure motive gas in S3 is helium.
The high-strength metal powder in S3 is aluminum alloy 7075 powder.
Compared with the prior art, the method has the advantages that the local size of the crack and the performance of the matrix material are repaired in the modes of fork ear hole stress analysis, crack removal, cold spraying material increase, machining and lining; the installation adopts the bush to improve the extrusion strength and the assembly interchangeability of pore wall, and the two compound advantages are complementary, have realized the restoration to high strength aluminum alloy whole piece hole angle crackle, have effectively reduced the disability rate of whole piece, have improved cycle economic benefits and the rate of reuse of whole piece.
Drawings
FIG. 1 is a schematic representation of the post repair quality inspection and validation criteria of the present invention;
FIG. 2 is a schematic representation of a pre-and post-repair object of the present invention;
FIG. 3 is a schematic view of a comparative dominance analysis of the liner/cold spray composite repair of the present invention with various aspects;
FIG. 4 is a schematic representation of a pre-repair hole perimeter embodiment of the present invention;
FIG. 5 is a schematic representation of a hole perimeter after repair in accordance with the present invention;
FIG. 6 is a schematic view of the overall hanger casting structure of the present invention;
fig. 7 is a schematic view of the bushing structure of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1 to 7, the present invention provides a technical solution: a composite repairing method for cracks around holes of ordnance casting integral parts based on cold spraying additive comprises the following steps:
s1: repairability evaluation, namely, finite element calculation of the stress distribution of the whole fork ear hole stress analysis and residual strength analysis;
s2: removing cracks around the fork ear hole of the integral part to be repaired, and measuring the size around the hole to be repaired after flaw detection;
s3: using high-pressure power gas to perform material increase repair on the periphery of the hole to be repaired by using high-strength metal powder in a cold spraying mode;
s4: carrying out X-ray inspection on the cold spraying additive repairing position to confirm whether an unrepaired point exists at the cold spraying position;
s5: machining the repaired part to adapt the size of the repaired part to the size of the integral part;
s6: the repaired part after mechanical processing is inspected again in a surface coloring and internal X-ray mode;
s7: after the repaired part is subjected to paint repair, a bush is installed, so that the extrusion strength and assembly interchangeability of the hole wall are improved;
s8: and performing first piece identification after assembly verification, and monitoring and using after installation.
The high pressure motive gas in S3 is helium.
The high-strength metal powder in S3 is aluminum alloy 7075 powder.
Example (b):
firstly, analyzing the stress around the fork ear hole of the cast integral piece and analyzing the residual strength, judging the finite element calculation of the total stress distribution, repairing the whole piece when the stress condition is met, removing cracks at the positions with cracks around the hole of the integral piece, measuring the size of the hole circumference after removing flaw detection inspection, repairing the hole circumference by a cold spraying material increasing mode by using high-strength metal powder, confirming that the spraying is completely covered by X-ray inspection, then machining the positions around the repaired hole to ensure that the size of the repaired hole is matched with the integral piece, due to the mechanical processing, it is necessary to check again by means of surface coloring and internal X-ray whether new cracks are generated at the repaired site, and (3) after paint repair is carried out on the repaired position, installing the bushing, improving the extrusion strength and assembly interchangeability of the hole wall, and finally, assembling, and monitoring and using after the assembling is finished after the first piece identification is needed.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
The invention integrally solves the problems of high purchase time and high cost caused by high rejection rate of the general hanger integral casting structure of the weapon system due to the hole angle cracks, can repair the hole angle cracks of the integral casting structure by a unique cold spraying additive repair method, is product repair as new, and has time cost of only one tenth and price cost of only two fifths compared with the time cost of purchasing new products.
Claims (3)
1. A composite repairing method for cracks around holes of ordnance casting integral parts based on cold spraying additive is characterized by comprising the following steps:
s1: repairability evaluation, namely, finite element calculation of the stress distribution of the whole fork ear hole stress analysis and residual strength analysis;
s2: removing cracks around the fork ear hole of the integral part to be repaired, and measuring the size around the hole to be repaired after flaw detection;
s3: using high-pressure power gas to perform material increase repair on the periphery of the hole to be repaired by using high-strength metal powder in a cold spraying mode;
s4: carrying out X-ray inspection on the cold spraying additive repairing position to confirm whether an unrepaired point exists at the cold spraying position;
s5: machining the repaired part to adapt the size of the repaired part to the size of the integral piece;
s6: the repaired part after mechanical processing is inspected again in a surface coloring and internal X-ray mode;
s7: after the repaired part is subjected to paint repair, a bushing is installed, so that the extrusion strength and assembly interchangeability of the hole wall are improved;
s8: and performing first piece identification after assembly verification, and monitoring and using after installation.
2. The method for compositely repairing the cracks around the holes of the ordnance casting monolithic piece based on the cold spraying additive material of claim 1, wherein the high-pressure motive gas in the S3 is helium.
3. The method for compositely repairing the cracks around the holes of the ordnance casting monolithic piece based on the cold spraying additive material of claim 1, wherein the high-strength metal powder in the S3 is aluminum alloy 7075 powder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210727519.4A CN115074719A (en) | 2022-06-25 | 2022-06-25 | Composite repairing method for cracks around holes of ordnance casting integral part based on cold spraying additive |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210727519.4A CN115074719A (en) | 2022-06-25 | 2022-06-25 | Composite repairing method for cracks around holes of ordnance casting integral part based on cold spraying additive |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115074719A true CN115074719A (en) | 2022-09-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210727519.4A Pending CN115074719A (en) | 2022-06-25 | 2022-06-25 | Composite repairing method for cracks around holes of ordnance casting integral part based on cold spraying additive |
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| Country | Link |
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| CN (1) | CN115074719A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116957857A (en) * | 2023-09-19 | 2023-10-27 | 中国建筑西南设计研究院有限公司 | Building restoration method and device and electronic equipment |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070031591A1 (en) * | 2005-08-05 | 2007-02-08 | TDM Inc. | Method of repairing a metallic surface wetted by a radioactive fluid |
| EP2011964A1 (en) * | 2007-07-06 | 2009-01-07 | United Technologies Corporation | Corrosion protective coating through cold spray |
| CN110480254A (en) * | 2019-08-03 | 2019-11-22 | 国营芜湖机械厂 | A kind of restorative procedure of aircraft fuel system alusil alloy shell cast defect |
| CN112643033A (en) * | 2020-11-23 | 2021-04-13 | 合肥通用机械研究院有限公司 | Additive manufacturing and repairing method for build-up welding cracks of hydrogenation reactor |
| CN114318323A (en) * | 2021-12-10 | 2022-04-12 | 国营芜湖机械厂 | Method for repairing local damage of aircraft skin surface in situ through cold spraying |
-
2022
- 2022-06-25 CN CN202210727519.4A patent/CN115074719A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070031591A1 (en) * | 2005-08-05 | 2007-02-08 | TDM Inc. | Method of repairing a metallic surface wetted by a radioactive fluid |
| EP2011964A1 (en) * | 2007-07-06 | 2009-01-07 | United Technologies Corporation | Corrosion protective coating through cold spray |
| CN110480254A (en) * | 2019-08-03 | 2019-11-22 | 国营芜湖机械厂 | A kind of restorative procedure of aircraft fuel system alusil alloy shell cast defect |
| CN112643033A (en) * | 2020-11-23 | 2021-04-13 | 合肥通用机械研究院有限公司 | Additive manufacturing and repairing method for build-up welding cracks of hydrogenation reactor |
| CN114318323A (en) * | 2021-12-10 | 2022-04-12 | 国营芜湖机械厂 | Method for repairing local damage of aircraft skin surface in situ through cold spraying |
Non-Patent Citations (1)
| Title |
|---|
| 阿•伊•延多古尔: "飞机结构零组件设计", 航空工业出版社, pages: 304 - 305 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116957857A (en) * | 2023-09-19 | 2023-10-27 | 中国建筑西南设计研究院有限公司 | Building restoration method and device and electronic equipment |
| CN116957857B (en) * | 2023-09-19 | 2024-01-16 | 中国建筑西南设计研究院有限公司 | Building restoration method and device and electronic equipment |
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