CN111575476B - Laser shock peening method for blade edge - Google Patents
Laser shock peening method for blade edge Download PDFInfo
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- CN111575476B CN111575476B CN202010276224.0A CN202010276224A CN111575476B CN 111575476 B CN111575476 B CN 111575476B CN 202010276224 A CN202010276224 A CN 202010276224A CN 111575476 B CN111575476 B CN 111575476B
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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
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Abstract
The invention discloses a method for laser shock peening of a blade edge, and belongs to the field of laser shock peening. Modeling; planning an impact strengthening area and a track route; treating the blade to be processed; laser shock peening: and starting from a laser impact track route which is closest to one side edge of the blade to be processed on the blade to be processed by using a high-energy nanosecond pulse laser beam, performing impact strengthening in a point-by-point and strip-by-strip mode, wherein in each laser impact track route, the high-energy nanosecond pulse laser beam emitted by a laser head is vertical to a strengthening point of the blade to be processed, the lap joint rate between adjacent points is unchanged, and the laser head is enabled to intermittently advance along a curve track of the laser impact track route. The laser shock peening method considers the change condition of the laser shock peening track curvature of the edge of the blade and the setting of the fixed lap ratio parameter, so that the consistency of the laser shock peening effect of the edge of the blade can be applied to the laser shock peening of various blades of an aircraft engine.
Description
Technical Field
The invention relates to the technical field of laser shock peening, in particular to a method for laser shock peening of a blade edge.
Background
Laser shock peening is a material surface strengthening technology, and is mainly characterized in that a laser beam with ultrahigh power and ultrashort pulse width passes through a transparent constraint layer to act on an absorption layer coated on the surface of a metal target material, and the absorption layer is rapidly gasified under the action of laser energy to form high-temperature and high-pressure plasma. Due to the confinement of the confinement layer, the plasma generates a super-strong shock wave to the metal surface. When the peak pressure of the shock wave exceeds the Hugoniot elastic limit of the material, the surface layer of the material is subjected to plastic deformation and microstructure change. After laser impact is finished, residual compressive stress with a certain depth is generated in the impact region due to the reaction of the material, so that the comprehensive mechanical property of the metal material is improved, and particularly, the foreign object damage resistance of the material is effectively improved.
The aero-engine can suck sundries such as sand, fragments, birds, hailstones and the like in the air in the working process, and tiny damage is caused to the engine blades. The influence of foreign object damage is one of the main problems of the blades of the aircraft engine, when the blades are in failure, light parts such as deformation and corrosion can influence the performance, heavy parts such as block falling and breaking can damage a gas compressor and even the engine, and fire and airplane crash can be caused.
The damage parts of foreign objects of the blade are intensively distributed at the edge position, and in order to ensure that the laser shock strengthening effect of the edge part of the blade is consistent, the variable curvature structural characteristics of the edge part of the blade must be considered. The application numbers are: the invention patent of CN201410428081.5 relates to a device and a method for laser shock strengthening of thin-wall blade edges, which mainly utilize the similarity principle to keep the motion track of laser spots synchronous with a backup block by adjusting the motion of a laser head, thereby realizing the laser shock strengthening of the thin-wall blade edges. The method only considers the curve change of the edge part, does not consider the curve change condition of the impact strengthening track of the edge of the blade and the setting of the fixed lap ratio parameter to adjust the arc length value of the central point of the impact facula, and has poor consistency of the laser impact strengthening effect of the edge of the blade and larger stress gradient.
Disclosure of Invention
In order to overcome the defects, the invention aims to provide a blade edge laser shock strengthening method, which adopts a high-energy nanosecond pulse laser beam to shock and strengthen the edge position of a blade in a point-by-point mode, each track route is consistent with the curve of the edge route of the blade, the uniformity of the shock effect is ensured by the consistent lap joint of each track route, and the consistency of the strengthening effect of the whole blade edge shock area is further ensured.
In order to solve the technical problems, the technical scheme adopted by the invention is as follows:
a method for blade edge laser shock peening, comprising the following steps:
a. modeling: obtaining a model of the blade to be processed by a reverse reconstruction technology;
b. planning an impact reinforcement area and a track route: the laser shock strengthening method comprises the following steps that the width L of a laser shock strengthening area, the diameter D of laser spots and a fixed lap joint rate parameter m are obtained, the number of laser shock track routes is n, the n laser shock track routes are distributed at equal intervals from the edge of a blade to be machined to the middle of the surface of the blade to be machined, the curvature of the laser shock track routes is the curvature of the surface of the blade, and n is a minimum positive integer satisfying (n-1) Dm ≧ L;
c. treating the blade to be processed: sequentially coating an absorption layer and a constraint layer on a strengthening area of the blade to be processed;
d. laser shock peening: performing impact strengthening in a point-by-point mode by using a high-energy nanosecond pulse laser beam from a laser impact track route which is closest to one side edge of a blade to be processed on the blade to be processed, completing impact strengthening along the laser impact track route, and then starting impact strengthening from an adjacent laser impact track route in a point-by-point mode until all the laser impact track routes are completed in a point-by-point mode, wherein the lap joint rate between the adjacent laser impact track routes is the same as that between adjacent points in one laser impact track route; in each laser impact track route, a high-energy nanosecond pulse laser beam emitted by the laser head is vertical to a strengthening point of the blade to be processed, the lap joint rate (coincidence rate) between adjacent points is unchanged, and the laser head intermittently travels along a curve track of the laser impact track route.
Further, in the step a, the blade root point of one side edge of the blade to be processed is taken as an origin O, the point pointing to the same side of the blade tip is taken as the positive direction of the x axis, the blade root point departing from the other side is taken as the positive direction of the y axis, and the positive direction of the z axis is determined according to the rule of a right-hand coordinate system.
Further, in the step b, the width L of the laser shock peening area is 6-34mm, and the distance between the laser shock peening area and one side edge of the blade to be processed is 0.5 mm.
Further, in the step b, the distance from the laser shock peening area to the blade root of the blade to be processed is 30% of the length of the blade to be processed.
Further, in the step b, when the laser spot diameter D =2mm, n = 7; when D =4mm, then n = 4; when D =6mm, then n = 3; when D =8mm, then n = 3.
Further, in the step d, the parameters of the high-energy nanosecond pulsed laser beam are as follows: the laser energy E is 5-10J, the laser pulse width tau is 8-16ns, the laser spot diameter D is 2-8mm, and the laser pulse frequency F is 1-20 Hz.
Further, in the step d, after laser strengthening is completed at a certain laser strengthening center point (x 1, y1, z 1) on the laser shock trajectory route by a laser spot generated by a high-energy nanosecond pulse laser beam emitted by the laser head, a lap length circle is drawn by taking the point as a center and the radius length as Dm, and an intersection point of the lap length circle and the shock advancing direction of the laser shock trajectory route is a next laser strengthening center point (x 2, y2, z 2), and the positional relation between adjacent laser strengthening center points is as follows:
in the step d, the laser head is clamped on a manipulator, and the manipulator strengthens the laser head from the laser to the central point (x)1,y1,z1) Move to the next laser-intensified central point (x)2,y2,z2) And the manipulator adjusts the angle of the laser head according to the curvature of the next laser strengthening circle center point, so that the high-energy nanosecond pulse laser beam emitted by the laser head is vertical to the strengthening point of the blade to be processed.
Further, in the step a, relevant technicians acquire data of the surface of the blade to be processed in an image recognition mode to obtain three-dimensional geometric data of the blade to be processed; and then, performing point cloud data splicing, characteristic boundary extraction and data simplification on the three-dimensional geometric data of the blade to be processed, and constructing a three-dimensional CAD model of the blade to be processed through reverse modeling software.
Further, in the step c, the absorption layer is a black adhesive tape or black paint, and the constraint layer is a flowing deionized water film or glass.
The invention has the beneficial effects that: the method comprehensively considers the change condition of the curvature of the impact strengthening track of the blade edge and the setting of the fixed lap ratio parameter, combines the number n of track routes and the fixed lap ratio parameter m, adopts high-energy nanosecond pulse laser beams to impact and strengthen the position of the blade edge in a point-by-point mode, ensures the uniformity of the impact effect by the consistent lap joint of each track route, further ensures the consistency of the strengthening effect of the whole blade edge impact area, and can be applied to the field of laser impact strengthening of various blade edges of aero-engines.
Drawings
The invention is further described with the aid of the accompanying drawings, in which the embodiments do not constitute any limitation, and for a person skilled in the art, without inventive effort, further drawings may be obtained from the following figures:
FIG. 1 is a schematic diagram of a three-dimensional CAD model and the creation of an xyz coordinate system of the present invention;
FIG. 2 is a schematic diagram of the positions of adjacent laser-enhanced points of the laser shock trajectory path shown in FIG. 1.
In the figure: 1. a laser shock peening region on one side; 2. laser shock strengthening area on the other side; 3. next laser strengthening center point; 4. the lap length is round; 5. laser strengthening a central point; 6 impact advance direction; 7. the laser impacts the trajectory path.
Detailed Description
In order to make those skilled in the art better understand the technical solution of the present invention, the following detailed description of the present invention is provided with reference to the accompanying drawings and specific embodiments, and it is to be noted that the embodiments and features of the embodiments of the present application can be combined with each other without conflict.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper surface", "lower surface", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "forward", "reverse", "axial", "radial", "circumferential", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience of description and for simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention.
Example 1
As shown in fig. 1 and 2, a method for laser shock peening of a blade edge includes the following steps:
a. modeling: the method comprises the following steps that related technicians acquire data of the surface of a blade to be processed in an image recognition mode to obtain three-dimensional geometric data of the blade to be processed; secondly, after point cloud data splicing, characteristic boundary extraction and data simplification are carried out on the three-dimensional geometric data of the blade to be processed, a model of the blade to be processed is obtained through reverse modeling software through a reverse reconstruction technology, and a three-dimensional CAD model of the blade to be processed is constructed; taking a blade root point at one side edge of the blade to be processed as an original point O, pointing to the same side blade tip point as the positive direction of an x axis, and deviating from the blade root point at the other side as the positive direction of a y axis, and determining the positive direction of a z axis according to the rules of a right-hand coordinate system;
b. planning an impact reinforcement area and a track route: in a laser shock strengthening area 1 on one side of a blade to be processed, the width L, the laser spot diameter D and a fixed lap ratio parameter m are calculated, the number of laser shock track routes is n, the n laser shock track routes are distributed at equal intervals from the edge of the blade to be processed to the middle part of the surface of the blade to be processed, the curvature of the laser shock track routes is the curvature of the surface of the blade, and n is a minimum positive integer which meets the condition that (n-1) Dm is not less than L; the width L of the laser shock strengthening area is 6mm, the distance between the laser shock strengthening area and the edge of one side of the blade to be processed is 0.5mm, and the distance between the laser shock strengthening area and the blade root of the blade to be processed is 30% of the length of the blade to be processed. D =4mm, then n = 4. The setting of the laser shock peening fixed lap joint rate parameter m of the edge of the blade to be machined is determined by a related technician according to the experience of laser shock peening, referring to a general optional range and testing the blade to be tested.
c. Treating the blade to be processed: sequentially coating an absorption layer and a constraint layer on a strengthening area of the blade to be processed; the absorption layer is a black adhesive tape, and the restraint layer is a flowing deionized water film.
d. Laser shock peening: performing impact strengthening in a point-by-point mode by using a high-energy nanosecond pulse laser beam from a laser impact track route which is closest to one side edge of a blade to be processed on the blade to be processed, completing impact strengthening along the laser impact track route, and then starting impact strengthening from an adjacent laser impact track route in a point-by-point mode until all the laser impact track routes are completed in a point-by-point mode, wherein the lap joint rate between the adjacent laser impact track routes is the same as that between adjacent points in one laser impact track route; in each laser impact track route, a high-energy nanosecond pulse laser beam emitted by the laser head is vertical to a strengthening point of the blade to be processed, the lap joint rate (coincidence rate) between adjacent points is unchanged, and the laser head intermittently travels along a curve track of the laser impact track route.
Specifically, the parameters of the high-energy nanosecond pulsed laser beam are as follows: the laser energy E is 5J, the laser pulse width tau is 8ns, the laser spot diameter D is 2mm, and the laser pulse frequency F is 1 Hz. The coordinate of a laser spot generated by a high-energy nanosecond pulse laser beam emitted by the laser head at a certain laser strengthening central point 5 on a laser impact track path is (x)1,y1,z1) After laser strengthening is finished, drawing a lap length circle 4 by taking the point as the center of a circle and the radius length as Dm, wherein the intersection point of the lap length circle 4 and the impact advancing direction 6 of the laser impact track route 7 is the next laser strengthening central point 3, and the coordinate of the next laser strengthening central point is (x)2,y2,z2) And the position relation between adjacent laser strengthening central points is as follows:
the particular movement of the laser head is such that the laser head is clamped on a robot, the robot intensifying the laser head from the laser to the center point (x)1,y1,z1) Move to the next laser-intensified central point (x)2,y2,z2) And the manipulator adjusts the angle of the laser head according to the curvature of the next laser strengthening circle center point, so that the high-energy nanosecond pulse laser beam emitted by the laser head is vertical to the strengthening point of the blade to be processed.
And after laser shock peening of the laser shock peening area 1 on one side of the blade to be machined is completed, laser shock peening is performed on the laser shock peening area 2 on the other side of the blade to be machined, and after the laser shock peening on the two sides is completed, the laser shock peening of the blade is completed.
Example 2
A method for blade edge laser shock peening, comprising the following steps:
a. modeling: the method comprises the following steps that related technicians acquire data of the surface of a blade to be processed in an image recognition mode to obtain three-dimensional geometric data of the blade to be processed; secondly, after point cloud data splicing, characteristic boundary extraction and data simplification are carried out on the three-dimensional geometric data of the blade to be processed, a model of the blade to be processed is obtained through reverse modeling software through a reverse reconstruction technology, and a three-dimensional CAD model of the blade to be processed is constructed; taking a blade root point at one side edge of the blade to be processed as an original point O, pointing to the same side blade tip point as the positive direction of an x axis, and deviating from the blade root point at the other side as the positive direction of a y axis, and determining the positive direction of a z axis according to the rules of a right-hand coordinate system;
b. planning an impact reinforcement area and a track route: the laser shock strengthening method comprises the following steps that the width L of a laser shock strengthening area, the diameter D of laser spots and a fixed lap joint rate parameter m are obtained, the number of laser shock track routes is n, the n laser shock track routes are distributed at equal intervals from the edge of a blade to be machined to the middle of the surface of the blade to be machined, the curvature of the laser shock track routes is the curvature of the surface of the blade, and n is a minimum positive integer satisfying (n-1) Dm ≧ L; the width L of the laser shock strengthening area is 10mm, and the distance between the laser shock strengthening area and the edge of one side of the blade to be processed is 0.5mm; the distance between the laser shock strengthening area and the blade root of the blade to be processed is 30% of the length of the blade to be processed. Laser spot diameter D =2mm, then n = 7. According to the FOD damage statistical data of the leaves, the following results are obtained: the distribution density of the damage positions shows an obvious increasing trend along the leaf height; in the area with the blade height more than 80% away from the blade root, the damage distribution is relatively concentrated, and the total damage in the area accounts for more than 50% of the total damage of the statistics; in the area 30-80% of the blade height away from the blade root, the damage distribution is relatively uniform, and the damage number in each interval respectively accounts for about 10% of the total damage amount in statistics; the number of damage is relatively sparse in a region within 30% of the blade height from the blade root, and the cumulative total damage in this region accounts for about 10% of the statistical total damage. The width size of the damage is 0.5-34.5mm, and the number of gap damage with damage width distributed in 0.5-6.0mm is about 80% of the total amount of gap damage.
c. Treating the blade to be processed: sequentially coating an absorption layer and a constraint layer on a strengthening area of the blade to be processed; the absorption layer is black paint, and the restraint layer is glass.
d. Laser shock peening: performing impact strengthening in a point-by-point mode by using a high-energy nanosecond pulse laser beam from a laser impact track route which is closest to one side edge of a blade to be processed on the blade to be processed, completing impact strengthening along the laser impact track route, and then starting impact strengthening from an adjacent laser impact track route in a point-by-point mode until all the laser impact track routes are completed in a point-by-point mode, wherein the lap joint rate between the adjacent laser impact track routes is the same as that between adjacent points in one laser impact track route; in each laser impact track route, a high-energy nanosecond pulse laser beam emitted by the laser head is vertical to a strengthening point of the blade to be processed, the lap joint rate (coincidence rate) between adjacent points is unchanged, and the laser head intermittently travels along a curve track of the laser impact track route.
Specifically, the parameters of the high-energy nanosecond pulsed laser beam are as follows: the laser energy E is 10J, the laser pulse width tau is 16ns, the laser spot diameter D is 8mm, and the laser pulse frequency F is 20 Hz. A laser spot generated by a high-energy nanosecond pulse laser beam emitted by a laser head is at a certain laser strengthening central point (x) on a laser impact track route1,y1,z1) After laser strengthening is finished, drawing a lap length circle by taking the point as the center of a circle and the radius length as Dm, wherein the intersection point of the lap length circle and the impact advancing direction of the laser impact track route is the next laser strengthening center point (x)2,y2,z2) And the position relation between adjacent laser strengthening central points is as follows:
the particular movement of the laser head is such that the laser head is clamped on a robot, the robot intensifying the laser head from the laser to the center point (x)1,y1,z1) Move to the next laser-intensified central point (x)2,y2,z2) And the manipulator adjusts the angle of the laser head according to the curvature of the next laser strengthening circle center point, so that the high-energy nanosecond pulse laser beam emitted by the laser head is vertical to the strengthening point of the blade to be processed.
Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction. Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
Claims (6)
1. A method for blade edge laser shock peening is characterized by comprising the following steps:
a. modeling: obtaining a model of the blade to be processed by a reverse reconstruction technology;
b. planning an impact reinforcement area and a track route: the laser shock strengthening method comprises the following steps that the width L of a laser shock strengthening area, the diameter D of laser spots and a fixed lap joint rate parameter m are obtained, the number of laser shock track routes is n, the n laser shock track routes are distributed at equal intervals from the edge of a blade to be machined to the middle of the surface of the blade to be machined, the curvature of the laser shock track routes is the curvature of the surface of the blade, and n is a minimum positive integer satisfying (n-1) Dm ≧ L;
c. treating the blade to be processed: sequentially coating an absorption layer and a constraint layer on a strengthening area of the blade to be processed;
d. laser shock peening: performing impact strengthening in a point-by-point mode by using a high-energy nanosecond pulse laser beam from a laser impact track route which is closest to one side edge of a blade to be processed on the blade to be processed, completing impact strengthening along the laser impact track route, and then starting impact strengthening from an adjacent laser impact track route in a point-by-point mode until all the laser impact track routes are completed in a point-by-point mode, wherein the lap joint rate between the adjacent laser impact track routes is the same as that between adjacent points in one laser impact track route; in each laser impact track route, a high-energy nanosecond pulse laser beam emitted by a laser head is vertical to a strengthening point of the blade to be processed, the lap joint rate between adjacent points is unchanged, and the laser head intermittently travels along a curve track of the laser impact track route;
in the step b, the width L of the laser shock strengthening area is 6-34mm, the distance between the laser shock strengthening area and the edge of one side of the blade to be processed is 0.5mm, and the distance between the laser shock strengthening area and the blade root of the blade to be processed is 30% of the length of the blade to be processed;
the laser shock peening of the step d comprises the following specific steps:
a laser spot generated by a high-energy nanosecond pulse laser beam emitted by a laser head is at a certain laser strengthening central point (x) on a laser impact track route1,y1,z1) After laser strengthening is finished, drawing a lap length circle by taking the point as the center of a circle and the radius length as Dm, wherein the intersection point of the lap length circle and the impact advancing direction of the laser impact track route is the next laser strengthening center point (x)2,y2,z2) And the position relation between adjacent laser strengthening central points is as follows:
d, clamping the laser head on a manipulator, and strengthening the laser head by the manipulator from a laser to a central point (x)1,y1,z1) Move to the next laser-intensified central point (x)2,y2,z2) The manipulator adjusts according to the curvature of the next laser strengthening circle center pointAnd the angle of the laser head is adjusted, so that the high-energy nanosecond pulse laser beam emitted by the laser head is vertical to the strengthening point of the blade to be processed.
2. The method of blade edge laser shock peening according to claim 1, wherein: in the step a, the root point of one side edge of the blade to be processed is taken as an original point O, the point pointing to the same side of the blade tip is taken as the positive direction of an x axis, the root point departing from the other side of the blade is taken as the positive direction of a y axis, and the positive direction of a z axis is determined according to the rules of a right-hand coordinate system.
3. The method of blade edge laser shock peening according to claim 1, wherein: in the step b, when the laser spot diameter D is 2mm, n is 7; when D is 4mm, n is 4; when D is 6mm, n is 3; when D is 8mm, n is 3.
4. The method of blade edge laser shock peening according to claim 1, wherein: in the step d, the parameters of the high-energy nanosecond pulse laser beam are as follows: the laser energy E is 5-10J, the laser pulse width tau is 8-16ns, the laser spot diameter D is 2-8mm, and the laser pulse frequency F is 1-20 Hz.
5. The method of blade edge laser shock peening according to claim 1, wherein: in the step a, relevant technicians acquire data of the surface of the blade to be processed in an image recognition mode to obtain three-dimensional geometric data of the blade to be processed; and then, performing point cloud data splicing, characteristic boundary extraction and data simplification on the three-dimensional geometric data of the blade to be processed, and constructing a three-dimensional CAD model of the blade to be processed through reverse modeling software.
6. The method of blade edge laser shock peening according to claim 1, wherein: in the step c, the absorption layer is a black adhesive tape or black paint, and the restraint layer is a flowing deionized water film or glass.
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