CN112593072A - Fastening hole processing and reinforcing method - Google Patents
Fastening hole processing and reinforcing method Download PDFInfo
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- CN112593072A CN112593072A CN202011457490.XA CN202011457490A CN112593072A CN 112593072 A CN112593072 A CN 112593072A CN 202011457490 A CN202011457490 A CN 202011457490A CN 112593072 A CN112593072 A CN 112593072A
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- fastening hole
- diameter
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- positioning small
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D10/00—Modifying the physical properties by methods other than heat treatment or deformation
- C21D10/005—Modifying the physical properties by methods other than heat treatment or deformation by laser shock processing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B35/00—Methods for boring or drilling, or for working essentially requiring the use of boring or drilling machines; Use of auxiliary equipment in connection with such methods
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D11/00—Process control or regulation for heat treatments
Abstract
The invention discloses a fastening hole processing and strengthening method, which comprises the following steps: (1) determining the diameter D of the positioning small hole according to the diameter D of the fastening hole1Drilling a positioning small hole in the center of the opening area of the fastening hole of the workpiece; (2) accurately positioning the workpiece through the positioning small holes, sequentially laying an absorption layer and a constraint layer on the front surface and the back surface of the workpiece from inside to outside, measuring symmetrical impact areas, and performing laser impact strengthening on the impact areas; (3) and after the laser shock peening process is finished, reaming the positioning small hole or reaming the positioning small hole and then reaming the positioning small hole to obtain the fastening hole with the diameter of D. The fastening hole processing and strengthening method forms reasonable residual compressive stress distribution around the hole structure, improves the fatigue resistance of the hole structure, and improves the service life and the safety performance of the member with the hole.
Description
Technical Field
The invention relates to the field of laser surface machining and mechanical machining, in particular to a technology and a method for machining fastening holes or mounting holes and prolonging service life of surface strengthening in the fields of aviation, aerospace, high-speed rail, nuclear power and the like.
Background
At present, all key parts in the structures of the aircraft and the engine are mostly connected in a riveting and bolt mode, a plurality of hole structures need to be processed during part production, and the hole structures are easy to generate fatigue failure under alternating load in the service process. The existing research shows that the stress distribution state of the pore structure is improved by strengthening the surface of the pore structure, so that the fatigue crack can be effectively delayed, and the service life and the overall safety of the porous member are improved.
The traditional strengthening method mainly comprises mechanical shot blasting and cold extrusion strengthening. In the mechanical shot blasting process, the movement track of the shot cannot be accurately controlled, so that the strengthening effect is usually unstable, the roughness of the impact surface is reduced, and microcracks are easily generated. In addition, because the projectile launching device is fixed in size and has poor flexibility, it is not possible to reinforce holes with a small diameter. The cold extrusion strengthening process flow is complex, the requirement on the strength of the mandrel is high, and the aperture precision is reduced in the extrusion process. When the small hole is strengthened, the core shaft is easy to break and cannot be pulled out, and the production efficiency is seriously reduced.
The laser shock strengthening technology is to utilize shock waves generated by high-energy laser beams to strengthen the processing surface of a material, and can form larger residual compressive stress on the surface of the material and a certain depth, thereby effectively inhibiting the fatigue crack from growing. However, when the processed hole structure is subjected to impact strengthening treatment, the hole corner area is easy to collapse, and the service life of the hole structure is shortened; the special laser reflection device can be used for impact strengthening of the inner wall of the hole, but the size of the hole diameter can be influenced, the precision of the hole structure is reduced, and the inner wall of the small-diameter fastening hole cannot be strengthened. Therefore, when various hole structures are subjected to laser shock strengthening, a process of firstly carrying out shock and then carrying out hole opening is mainly adopted, and the required fastening holes are directly machined after single-side or double-side shock strengthening is usually carried out on a plate which is not subjected to any machining. However, in the aerospace field, the size of the perforated member is large, the number of the holes is large, and if a common process of punching before punching is adopted, the problems of large area of a punching area, difficulty in positioning and the like exist, and the production efficiency is reduced. In actual production, the processing flow of the fastening holes is special, positioning small holes are usually required to be pre-opened, and then the positioning small holes are reamed one by one to obtain the fastening holes with required apertures, but no corresponding laser shock strengthening method exists at present.
Disclosure of Invention
Therefore, the invention mainly aims at the defects of a fastening hole strengthening process and a flow in the machining process of the porous member in the aerospace field, and provides a fastening hole machining strengthening method so as to form a reasonable residual pressure field in a hole structure region and improve the service life and the safety performance of the porous member.
The invention relates to a fastening hole processing and strengthening method, which comprises the following steps:
(1) determining the diameter D of the positioning small hole according to the diameter D of the fastening hole1Drilling a positioning small hole in the center of the opening area of the fastening hole of the workpiece;
(2) accurately positioning the workpiece through the positioning small holes, sequentially laying an absorption layer and a constraint layer on the front surface and the back surface of the workpiece from inside to outside, measuring symmetrical impact areas, and performing laser impact strengthening on the impact areas;
(3) and after the laser shock peening process is finished, reaming the positioning small hole or reaming the positioning small hole and then reaming the positioning small hole to obtain the fastening hole with the diameter of D.
The invention adopts the technical scheme that the method has the beneficial effects that: according to the fastening hole processing and strengthening method, the positioning small holes are formed in the positions of the holes according to the hole diameters of the fastening holes, then laser shock strengthening is carried out on the symmetrical positions of the front surface and the back surface of a workpiece through the positioning small holes, reasonable residual compressive stress distribution is formed around the hole structures, the fastening holes with high precision and smooth inner walls are obtained through a hole expanding or reaming process, the fatigue resistance of the hole structures is improved, and the service life and the safety performance of the porous component are improved.
Preferably, the diameter D of the fastening hole in the step (1) is 2-40 mm, and the diameter D of the positioning small hole1Is 1/4-1/2 of the diameter D of the fastening hole.
The purpose of processing the positioning small holes is to facilitate the construction operation and the accurate positioning of a factory, accurately position the laser shock strengthening areas of the front and back surfaces of the workpiece and ensure the uniform distribution of the residual compressive stress field.
Preferably, the central axis of the positioning small hole in the step (1) is coincident with the central axis of the fastening hole.
Preferably, the impact area in the step (2) is a square impact area with the side length being 2-5 times of the diameter D of the fastening hole or a circular impact area with the diameter being 2-5 times of the diameter D of the fastening hole, and the center of the impact area coincides with the center of the positioning small hole.
Preferably, the absorption layer is aluminum foil or black paint, is used for improving the laser absorptivity of the surface of the material, and has a thickness of 30-200 μm.
Preferably, the restriction layer is a water flow flowing at a constant speed, and the thickness of a water layer of the water flow is 2-8 mm.
Preferably, the parameters of the laser shock peening process in the step (2) are as follows: the diameter of a laser spot is 2-10 mm, the single pulse energy is 2J-80J, and the overlapping rate of the laser spot is 10-80%.
Preferably, the laser spot size and the single pulse energy are specifically selected according to the thickness of the workpiece plate and the aperture of the positioning small hole, when the thickness of the workpiece plate or the aperture of the positioning small hole is larger, the larger spot diameter is preferably selected, the single pulse energy is properly increased, and the laser shock peening action depth and the laser shock peening efficiency are improved.
Preferably, the laser shock peening can be separately performed on the front surface and the back surface of the workpiece sequentially or simultaneously in the step (2), and the shock peening times are 1-5 times.
Preferably, in the step (3), if the requirement on the precision of the inner wall of the final fastening hole is not high, a reamer with the diameter of the fastening hole D is selected to process the small positioning hole into the final fastening hole; if the precision requirement of the inner wall of the fastening hole is high, selecting a reamer with the diameter being 0.1-0.5 mm smaller than the diameter D of the fastening hole to enlarge the aperture of the positioning small hole, and then selecting a reamer with the diameter being the diameter D of the fastening hole to carry out final reaming, so as to obtain the fastening hole with high quality of the inner wall.
Compared with the prior art, the method for processing and strengthening the fastening hole has the following beneficial effects:
(1) the method for processing and strengthening the fastening holes provided by the invention better conforms to the production flow of the actual factory hole structure, and the method can process and strengthen the fastening holes with different apertures only by conventional hole forming and laser strengthening equipment, thereby reducing the equipment and production cost.
(2) The invention can obtain the residual compressive stress field which is symmetrically distributed by accurately controlling the front and back surface impact strengthening areas through the positioning small holes. Especially when a workpiece with larger size and more holes is processed, the positioning small holes can be used for quickly and accurately carrying out laser shock strengthening on the front surface and the back surface of the hole structure, and the production efficiency is improved.
(3) According to the invention, after laser shock strengthening, a reaming process or a reaming and reaming process is required, so that the fastening hole with higher precision and inner wall quality can be obtained.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
FIG. 1 is a schematic view of the process of fastening hole processing and laser shock peening according to the present invention.
FIG. 2 is a schematic diagram of the square laser shock peening range of the present invention.
FIG. 3 is a schematic diagram of the circular laser shock peening range of the present invention.
In the figure, 1, a workpiece, 2, a positioning small hole, 3, a fastening hole opening area, 4, a fastening hole central axis, 5, a laser beam, 6, a constraint layer, 7, an absorption layer, 8, a fastening hole, 9, a square impact area, 10, a laser spot, 11 and a circular impact area.
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.
The invention relates to a fastening hole processing and strengthening method, which comprises the following steps as shown in figure 1 (A represents a front surface and B represents a back surface):
(1) determining the diameter D of the positioning small hole 2 according to the diameter D of the fastening hole 81Drilling a positioning small hole 2 in the center of a fastening hole opening area 3 of the workpiece 1;
(2) accurately positioning through the positioning small holes 2, sequentially laying an absorption layer 7 and a constraint layer 6 on the front surface and the back surface of the workpiece 1 from inside to outside, measuring symmetrical impact areas, and performing laser impact strengthening on the impact areas;
(3) and after the laser shock peening process is finished, reaming the positioning small hole 2 or reaming and then reaming to obtain a fastening hole 8 with the diameter D.
In order to further optimize the technical scheme, the diameter D of the fastening hole 8 in the step (1) is 2-40 mm, and the diameter D of the positioning small hole 21Is 1/4-1/2 of the diameter D of the fastening hole 8.
In order to further optimize the technical scheme, the central axis of the positioning small hole 2 in the step (1) and the central axis 4 of the fastening hole need to be ensured to be coincident.
In order to further optimize the technical scheme, as shown in fig. 2 and fig. 3, in the step (2), the impact area is a square impact area 9 with the side length being 2-5 times of the diameter D of the fastening hole 8 or a circular impact area 11 with the diameter being 2-5 times of the diameter D of the fastening hole 8, and the center of the impact area coincides with the center of the positioning small hole 2.
In order to further optimize the technical scheme, the absorption layer 7 is aluminum foil or black paint, and the thickness is 30-200 μm.
In order to further optimize the technical scheme, the restraint layer 6 is water flow flowing at a constant speed, and the thickness of a water layer of the water flow is 2-8 mm.
In order to further optimize the technical scheme, the parameters of the laser shock peening process in the step (2) are as follows: the diameter of a laser spot 10 is 2-10 mm, the single pulse energy is 2J-80J, and the overlapping rate of the laser spot is 10-80%.
In order to further optimize the technical scheme, the size of the laser spot 10 and the single pulse energy are specifically selected according to the thickness of the workpiece 1 and the aperture of the positioning small hole 2, when the thickness of the workpiece 1 or the aperture of the positioning small hole 2 is larger, the larger spot diameter is preferentially selected, and the single pulse energy is appropriately increased.
In order to further optimize the technical scheme, the front side and the back side of the workpiece 1 can be subjected to laser shock strengthening separately and sequentially or simultaneously in the step (2), and the shock strengthening times are 1-5 times.
In order to further optimize the technical scheme, in the step (3), if the requirement on the precision of the inner wall of the final fastening hole 8 is not high, a reamer with the diameter of the fastening hole 8D is selected to process the small positioning hole 2 into the final fastening hole 8; if the precision requirement of the inner wall of the fastening hole 8 is high, a reamer with the diameter being 0.1-0.5 mm smaller than the diameter D of the fastening hole 8 is selected to enlarge the aperture of the positioning small hole 2, and then a reamer with the diameter being the diameter D of the fastening hole 8 is selected to carry out final reaming.
The fastening hole processing reinforcing method of the present invention will be described in detail with reference to fig. 1 to 3 and the specific embodiment.
The first embodiment is as follows:
in this example, 2219C10S aluminum alloy plate with the thickness of 5mm is adopted, and a fastening hole 8 with the diameter of 4mm needs to be opened. As shown in the attached figure 1, the diameter of a positioning small hole 2 is determined to be 1mm according to the diameter of a fastening hole 8, and then the positioning small hole 2 with the diameter of 1mm is drilled in the center of a fastening hole opening area 3, so that the central axis of the positioning small hole 2 is enabled to be coincident with the central axis 4 of the fastening hole.
After the positioning small holes 2 are processed, black paint with the thickness of 60 mu m is sprayed on the front surface and the back surface of the aluminum alloy workpiece 1 to serve as an absorption layer 7, the absorption rate of the workpiece on laser energy is enhanced, and a water flow layer with the thickness of 3mm and flowing at a constant speed is selected to serve as a constraint layer 6. Then the workpiece is positioned by the positioning small holes 2, symmetrical laser impact areas are measured on the front surface and the back surface of the workpiece 1, and the laser impact areas are square impact areas 9 with the side length of 20mm, as shown in the attached figure 2. As shown in fig. 1, an arrow a represents an emitted laser beam 5, and the laser shock peening process parameters are as follows: the diameter of a laser spot 10 is 4mm, the single pulse energy is 10J, and the spot overlapping rate is 60%. After 2 times of impact reinforcement is completed on the front square impact area 9, 2 times of impact reinforcement is performed on the back square impact area 9. In this case, the compressive residual stress is formed on the front and back surfaces and in the thickness direction of the workpiece 1.
After the laser shock strengthening process is finished, a reaming drill bit with the diameter of 3.8mm is selected to enlarge the aperture of the positioning small hole 2, a reaming drill bit with the diameter of 4mm is selected to ream, and a fastening hole 8 with high precision and hole wall quality is obtained by removing a proper amount of inner wall metal.
Example two:
in this example, a TC4 titanium alloy plate with a thickness of 10mm is used, and a fastening hole with a diameter of 40mm needs to be formed. As shown in the attached figure 1, the diameter of a positioning small hole is determined to be 10mm according to the diameter of a fastening hole, and then the positioning small hole 2 with the diameter of 10mm is drilled in the center of a fastening hole opening area 3, so that the central axis of the positioning small hole 2 is enabled to be coincident with the central axis 4 of the fastening hole.
After the positioning small holes 2 are processed, aluminum foils with the thickness of 200 mu m are attached to the front surface and the back surface of the titanium alloy workpiece 1 to serve as absorption layers 7, the absorption rate of the workpiece to laser energy is enhanced, and a water flow layer with the thickness of 8mm and flowing at a constant speed is selected to serve as a constraint layer 6. Then the workpiece is positioned by the positioning small holes 2, symmetrical laser impact areas are measured on the front surface and the back surface of the workpiece 1, and the laser impact areas are circular impact areas 11 with the diameter of 80mm, as shown in figure 3. As shown in fig. 1, an arrow a represents an emitted laser beam 5, and the laser shock peening process parameters are as follows: the diameter of a laser spot 10 is 10mm, the single pulse energy is 80J, and the spot overlapping rate is 30%. And simultaneously, 5 times of laser shock strengthening is carried out on the circular shock regions 11 on the front surface and the back surface of the workpiece 1, so that large and symmetrically distributed residual compressive stress can be formed on the front surface, the back surface and the thickness direction of the workpiece 1.
After the laser shock strengthening process is finished, a reaming bit with the diameter of 39.5mm is selected to enlarge the aperture of the positioning small hole 2, a reaming bit with the diameter of 40mm is selected to ream, and a fastening hole 8 with high precision and hole wall quality is obtained by removing a proper amount of inner wall metal.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A fastening hole processing and reinforcing method is characterized by comprising the following steps:
(1) determining the diameter D of the positioning small hole (2) according to the diameter D of the fastening hole (8)1Drilling a positioning small hole (2) in the center of the fastening hole opening area (3) of the workpiece (1);
(2) accurately positioning through the positioning small holes (2), sequentially laying an absorption layer (7) and a constraint layer (6) on the front surface and the back surface of the workpiece (1) from inside to outside, measuring symmetrical impact areas, and performing laser impact reinforcement on the impact areas;
(3) and after the laser shock peening process is finished, reaming the positioning small hole (2) or reaming and then reaming to obtain a fastening hole (8) with the diameter of D.
2. A fastening hole processing and reinforcing method as claimed in claim 1, wherein the diameter D of the fastening hole (8) in the step (1) is 2-40 mm, and the diameter D of the positioning small hole (2)1Is 1/4-1/2 of the diameter D of the fastening hole (8).
3. The fastening hole processing and reinforcing method as claimed in claim 1, wherein the central axis of the positioning small hole (2) in the step (1) is coincident with the central axis (4) of the fastening hole.
4. The fastening hole processing and reinforcing method as claimed in claim 1, wherein the impact area in the step (2) is a square impact area (9) with the side length being 2-5 times of the diameter D of the fastening hole (8) or a circular impact area (11) with the diameter being 2-5 times of the diameter D of the fastening hole (8), and the center of the impact area coincides with the center of the positioning small hole (2).
5. Fastening hole processing reinforcement method according to claim 1 or 4, characterized in that the absorption layer (7) is aluminum foil or black paint, and the thickness is 30 μm to 200 μm.
6. A fastening hole processing and reinforcing method as defined in claim 1 or 4, wherein the restriction layer (6) is a water flow flowing at a constant speed, and the thickness of the water layer of the water flow is 2 mm-8 mm.
7. The fastening hole processing and reinforcing method as claimed in claim 1, wherein the parameters of the laser shock peening process in the step (2) are as follows: the diameter of the laser spot (10) is 2-10 mm, the single pulse energy is 2J-80J, and the overlapping rate of the laser spot is 10-80%.
8. The method for strengthening fastening hole machining according to claim 7, wherein the size of the laser spot (10) and the single pulse energy are specifically selected according to the thickness of the workpiece (1) and the diameter of the positioning small hole (2), and when the thickness of the workpiece (1) or the diameter of the positioning small hole (2) is large, the diameter of the laser spot is selected to be large, and the single pulse energy is increased appropriately.
9. The method for processing and strengthening the fastening hole according to claim 1, wherein the laser shock peening can be performed on the front surface and the back surface of the workpiece (1) separately and sequentially or simultaneously in the step (2), and the shock peening times are 1-5 times.
10. The fastening hole processing and reinforcing method as claimed in claim 1, wherein in the step (3), if the precision requirement of the inner wall of the final fastening hole (8) is not high, a reamer with the diameter of D of the fastening hole (8) is selected to process the positioning small hole (2) into the final fastening hole (8); if the precision requirement of the inner wall of the fastening hole (8) is high, a reamer with the diameter being 0.1-0.5 mm smaller than the diameter D of the fastening hole (8) is selected to enlarge the aperture of the positioning small hole (2), and then a reaming drill with the diameter being the diameter D of the fastening hole (8) is selected to carry out final reaming.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114250356A (en) * | 2021-12-16 | 2022-03-29 | 江苏大学 | Method for improving fatigue performance of mechanical connecting piece of fiber metal laminated plate |
| CN114682932A (en) * | 2022-04-14 | 2022-07-01 | 强一半导体（苏州）有限公司 | Method for laser processing through hole suitable for green ceramic chip |
| WO2022220987A1 (en) * | 2021-04-14 | 2022-10-20 | Kondex Corporation | Fatigue improved harvester component via laser shock peening |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022220987A1 (en) * | 2021-04-14 | 2022-10-20 | Kondex Corporation | Fatigue improved harvester component via laser shock peening |
| CN114250356A (en) * | 2021-12-16 | 2022-03-29 | 江苏大学 | Method for improving fatigue performance of mechanical connecting piece of fiber metal laminated plate |
| CN114250356B (en) * | 2021-12-16 | 2023-08-29 | 江苏大学 | Method for improving fatigue performance of fiber metal laminate mechanical connector |
| CN114682932A (en) * | 2022-04-14 | 2022-07-01 | 强一半导体（苏州）有限公司 | Method for laser processing through hole suitable for green ceramic chip |
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