CN111549214A - Laser shock strengthening device for tenon part of airplane blade - Google Patents
Laser shock strengthening device for tenon part of airplane blade Download PDFInfo
- Publication number
- CN111549214A CN111549214A CN202010473851.3A CN202010473851A CN111549214A CN 111549214 A CN111549214 A CN 111549214A CN 202010473851 A CN202010473851 A CN 202010473851A CN 111549214 A CN111549214 A CN 111549214A
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- blade
- falcon
- laser
- tool
- airplane
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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
Abstract
The invention discloses a laser shock strengthening device for tenon parts of airplane blades, which comprises: the workpiece clamp is used for clamping the airplane blade to be strengthened; the tool is transparent, the matching part of the tool is matched with the tenon part of the airplane blade, and the tool is assembled on the tenon part of the airplane blade after the tenon part of the airplane blade to be strengthened is sprayed with absorption paint; a first robot arm for driving the workpiece holder; the laser head of the laser is used for laser shock peening of the falcon part of the airplane blade. The strengthening effect is easy to guarantee based on the invention.
Description
Technical Field
The invention relates to a laser shock strengthening device for tenon parts of airplane blades.
Background
The aircraft blade is the especially important functional unit in aviation field, because aircraft engine operating temperature is than higher, and operating pressure ratio is great, thereby the blade falcon portion that is as blade and impeller hub connection position extremely easily appears tiredly thereby initiation crackle and finally lead to the blade to become invalid. The laser shock peening has remarkable effects on the aspects of prolonging the fatigue life of materials, inhibiting crack initiation, improving abrasion resistance and the like as a novel surface treatment technology, but because the tenon position of the blade is narrow and has a curved surface shape, a laser is difficult to process a narrow curved surface position when a traditional method is used for processing, and certain difficulty exists.
Chinese patent document CN103468925A discloses a laser shock peening method and device for blade mortise bottom surface plane, which makes more detailed description on laser shock peening in the background section and proposes a laser shock peening method based on water constraint layer. Firstly, shaping by laser, and projecting strip-shaped light spots by a laser; and auxiliary, a flow guide injection device and a water pumping device are adopted to respectively control the water flow parameters of the water inlet end and the water outlet end of the bottom of the mortise, and a uniform water restraint layer is formed in the bottom of the mortise.
Water restraint is the main restraint mode of current laser strengthening, because the water restraint layer adopts flowing water to form, and the thickness of water layer is difficult to accomplish evenly, influences the processing effect. Also because of this, the above-mentioned patent document CN103468925A attempts to form a uniform water confinement layer in the bottom of the mortise by means of a flow-directing injection device and a water pumping device through relatively complicated control. However, in any control method, the flowing water inevitably generates ripples, thereby generating different reflectivity and refractive index for the light, and the processing effect is still greatly influenced.
Disclosure of Invention
The invention aims to provide a laser shock strengthening device for a falcon part of an airplane blade, which is easy to ensure the strengthening effect.
In an embodiment of the invention, there is provided an aircraft blade falcon laser shock peening apparatus comprising:
the workpiece clamp is used for clamping the airplane blade to be strengthened;
the tool is transparent, the matching part of the tool is matched with the tenon part of the airplane blade, and the tool is assembled on the tenon part of the airplane blade after the tenon part of the airplane blade to be strengthened is sprayed with absorption paint;
a first robot arm for driving the workpiece holder;
the laser head of the laser is used for laser shock peening of the falcon part of the airplane blade.
Optionally, the tool is a K9 glass plate.
Optionally, a 3D scanner and a 3D printer are provided to print out the K9 glass panel through the 3D printer after scanning the aircraft blade falcon to be strengthened.
Optionally, providing a sealed chamber;
correspondingly, the first mechanical arm, the laser, the tool and the workpiece clamp are all positioned in the closed cabin;
and providing a tool fixture and a driving mechanism thereof for the tool for assembling the tool on the tenon part of the airplane blade to be strengthened.
Optionally, the closed cabin is provided with an air inlet and an air outlet, wherein the air outlet is provided with an air exhaust fan;
a second mechanical arm is arranged in the closed cabin, and the second mechanical arm is loaded with a nozzle for absorbing paint spraying and a pipe thereof;
correspondingly, the air inlet is positioned on one side wall, the air outlet is positioned on the side wall opposite to the side wall, the nozzle is positioned on the side of the air outlet in the direction of the air inlet opposite to the air outlet, and the laser is positioned on the side of the air inlet.
Optionally, the extraction fan is provided with filtering means.
Optionally, the driving mechanism is a two-dimensional driving mechanism, and the two-dimensional driving mechanism comprises a first horizontal guide rail and a second horizontal guide rail running on the first horizontal guide rail and perpendicular to the first horizontal guide rail;
correspondingly, a guide rail sliding block is arranged on the second horizontal guide rail, and the tool clamp is arranged on the guide rail sliding block.
Optionally, the work holder has an upper clamp arm and a lower clamp arm to hold end faces of the blade falcon in the tongue groove direction in the up-down direction.
Optionally, the upper and lower jawarms each correspond to a side link of a parallelogram mechanism.
Optionally, the laser head of the laser is mounted on a vertically arranged linear motion mechanism.
In the embodiment of the invention, after the tenon of the blade is sprayed with the absorption paint, the transparent tool is assembled, and the transparent tool can have relatively uniform thickness and relatively high surface quality, so that the generated transmissivity and refractive index are basically consistent under the condition of determining the incident angle, and the laser strengthening effect is easily ensured.
Drawings
FIG. 1 is a schematic structural diagram of a laser shock peening device for a falcon part of an airplane blade in one embodiment.
FIG. 2 is a flow chart of a laser shock peening process for a falcon of an aircraft blade in one embodiment.
FIG. 3 is a schematic structural diagram of an aircraft blade clamping robot in an embodiment.
In the figure: 1. the automatic glass cutting machine comprises a base plate, 2 blades, 3 a base, 4 a workpiece clamp, 5a falcon, 6 a mechanical arm, 7 side walls, 8 a filtering and exhausting fan, 9 a guide rail, 10 a guide rail, 11 a nozzle, 12 a mechanical arm, 13 a tooling clamp, 14 a tooling, 15 a laser head, 16 a mechanical arm, 17 a driving motor, 18 a lead screw, 19 a nut seat, 20 a contour scanning part, 21 a processing K9 glass tooling part, 22 a paint spraying part, 23 a laser strengthening part, 24 a workpiece clamp seat, 25a driver, 26 a four-bar mechanism, 27 an upper clamp arm and 28 a lower clamp arm.
Detailed Description
The arrangement shown in figure 1 is provided with a laser shock peening apparatus for aircraft blade falcon which is relatively complete and adapted to automatically perform laser peening, it being understood that for example falcon 5 of blade 2 it is often necessary to spray an absorption paint, for example a black paint, prior to laser peening, and that the spray painting itself may be performed separately.
Likewise, for example, the fixture 14 may also be separately fabricated and separately assembled to the falcon 5 of the blade 2, and thus, in embodiments of the present invention, more implementations may be provided with additional configuration without forming an essential feature if a greater rate of automation is not considered.
In the most basic implementation, compared with a new constraint configuration in a traditional constraint mode, the laser shock strengthening device for the falcon part of the airplane blade serving as a basic model at least comprises a workpiece clamp 4, a tool 14, a first mechanical arm and a laser. The tool 14 is a necessary component for realizing the constraint.
Wherein, regarding work holder 4, owing to need laser shock strengthening's only falcon 5 of blade 2 to be the part that has the falcon groove on the falcon 5, and blade 2 is individual great, longer, and the position that can the clamping is more, in the structure shown in fig. 1 and 3, the clamping position is two terminal surfaces of falcon 5, two terminal surfaces in the falcon groove direction on falcon 5 promptly, and this position of centre gripping can avoid blade 2 because of the produced inflection of self weight to the influence of falcon 5 position precision, thereby is favorable to the accurate drive of the feed of laser head 15 or arm 6.
In contrast to the form of the restriction formed by the water flow layer, in the embodiment of the present invention, a solid restriction is used, and specifically, in the embodiment of the present invention, a special tool 14 is configured and made of a transparent material, and the tool 14 may be, for example, glass, preferably colorless optical glass, such as crown-type and flint-type glass, and preferably K9 glass.
The matching part of the tool 14 is a part matched with the falcon part 5, in the embodiment of the invention, for constraint, the necessary configuration is that the matching part is matched with the surface shape of the falcon part 5, or the matching part is tightly jointed with the falcon part 5, so that the tool 14 is assembled on the plane blade falcon part after the plane blade falcon part to be strengthened is sprayed with the absorption paint, and the laser strengthening dynamic generated after the laser penetrates through the tool 14 and acts on the absorption paint is constrained by the tool 14.
This constraint is evident, for example, in the case of K9 glass, which has mirror quality and, as an optical glass, has a uniform refractive index and reflectivity, so that the uniformity of the effect of laser strengthening is easily ensured.
With respect to the first robot arm, i.e., the robot arm 6 shown in fig. 1, the workpiece holder 4 is mounted at the drive end of the robot arm 6 so that the motion of the blade 2 can be driven.
It can be understood that the movement form which needs to be adapted to the laser strengthening of the falcon 5 is determined, and the determined movement form determines the movement form adapting relation between the laser head 15 and the mechanical arm 6, in other words, the controllable movement form of the falcon 5 can be realized by the mechanical arm 6 alone, or the mechanical arm 6 is matched with the movement form of the laser head 15, and the matching of the movement form belongs to the common movement form matching in the field of machining, and is not described herein again.
For the laser, as the laser strengthening technology is mature and the type selection is relatively simple, in the embodiment of the invention, a neodymium glass laser is adopted, and accordingly, the laser head 15 of the laser is used for laser impact strengthening of the falcon part of the airplane blade.
Here, further describing the tooling 14, firstly, since the aircraft engine belongs to a precision device, the consistency of the aircraft blade is relatively good, in other words, the structural consistency of the falcon part 5 is very good, which determines that one set of tooling 14 can be used for different blades 2, and in addition, different tooling 14 can be used for different pieces or different groups of blades 2 in consideration of the service life.
In preferred embodiments, a dedicated fixture 14 is provided for each falcon 5, in that there are machining tolerances and some dimensional differences between the different blades. Meanwhile, the deformation of the used blades may be different, resulting in poor consistency thereof.
For example, the K9 glass may be printed by a 3D printer, and therefore, in an embodiment of the present invention, a 3D scanner and a 3D printer (not shown) are provided to print out the K9 glass plate by the 3D printer after scanning the tenons of the aircraft blades to be strengthened.
Obviously, the 3D scanner needs to be located at the side of the mechanical arm 6, the mechanical arm 6 has an original parking position, and after the workpiece, that is, the blade 2, is clamped, the workpiece can be scanned, and the online scanning can eliminate the position error caused by the assembly error, so that the automatic scanning device has better automatic completeness, that is, is suitable for the precise driving of the tool clamp 15.
The scanning of 3D scanner can automatic modeling, and automatic modeling is the required model of 3D printer, and the 3D printer can print the frock 14 of the K9 glass material of predetermined thickness according to this model.
In the embodiment of the present invention, a closed chamber is provided to facilitate the control of the process, and in the embodiment shown in fig. 1, the closed chamber comprises a bottom plate 1, four side walls 7 and a top plate, wherein the bottom plate 1 may be a floor of a field.
Furthermore, the first robot arm, i.e. the robot arm 6, should be located inside the closed chamber, and for the laser, the body thereof may be located outside the closed chamber, and in the embodiment of the present invention, unless otherwise specified, for example, the laser, the portion thereof for directly acting on the workpiece is necessarily located inside the closed chamber, and further, the structural portion of the optical path is at least partially located inside the closed chamber, and for the sake of simplicity of description, the laser is directly specified to be located inside the closed chamber.
The tool 14 and the workpiece holder 4 are parts which are necessarily located in a closed chamber.
The tooling fixture 14 is further provided with a tooling fixture 13 and a driving mechanism thereof for fitting on the falcon of the aircraft blade to be strengthened. In the configuration shown in fig. 1, the drive mechanism to which the tooling fixture 13 is adapted is a planar two-degree-of-freedom drive mechanism, represented in fig. 1 as having a horizontal rail 9 and a horizontal rail 10, the horizontal rails being perpendicular or orthogonal to each other.
The guide rail 10 is constructed on a guide rail slider of the guide rail 9 and can be driven by a nut screw mechanism, and a driving component adopts a servo motor.
The work fixture 13 is a guide rail slider on the guide rail 10 or a guide rail slider mounted on the guide rail 10, and a nut screw mechanism is also used for driving the work fixture, and a servo motor is also used as a driving component.
Further, in order to achieve better automation, that is, as many steps as possible can be completed in the sealed chamber, an air inlet and an air outlet are formed in the sealed chamber, wherein an air exhaust fan is installed at the air outlet to exhaust the waste air in the sealed chamber.
In addition, the air inlet is used for exhausting air from the air outlet recently, so that equipment in the closed cavity can be cooled.
Further, a second robot arm, i.e., a robot arm 12 shown in fig. 1, which carries a nozzle 11 for absorbing paint spray and its piping is installed in the sealed chamber.
Due to the existence of the mechanical arm 6 and the possibility of having more degrees of freedom of the mechanical arm 6, the degree of freedom of the mechanical arm 12 may be relatively small, and even only one degree of freedom, such as a degree of freedom of linear motion, may be provided, and only the nozzle 11 is horizontally moved to a position close to the mechanical arm 6, and the posture of the mechanical arm 6 is adjusted to be in a state where the nozzle 11 can spray the blade 2 loaded thereon.
Because of the existence of a plurality of mechanical arms, the degree of freedom of part of the mechanical arms is relatively less, so that the whole workload is lightened.
In a preferred embodiment, the air inlet is located on a side wall, the air outlet is located on a side wall opposite to the side wall, the nozzle 11 is located on the side where the air outlet is located in the direction in which the air inlet is opposite to the air outlet, and the laser is located on the side where the air inlet is located.
The air outlet can be provided with a fan which can adopt a conventional air exhaust fan, the exhausted waste gas can be provided with additional equipment for treatment, and the treated waste gas can be exhausted into the atmosphere.
In other implementations, the extraction fan is provided with filtering means, forming a filtering extraction fan 8 as shown in fig. 1.
In the structure shown in fig. 3, the work holder 4 has upper and lower clamp arms 27 and 28 for holding both end faces of the blade falcon in the tongue and groove direction in the up-down direction.
Due to the very small dimensional tolerances of the same type of aircraft blade, it is very easy to establish a surface contact fit when the upper and lower clamping arms 27, 28 are properly clamped against the tongue 5.
In some embodiments, one of the upper and lower jawarms 27, 28 may be characterized as a static arm and the other as a movable arm, wherein the support surface of the static arm is horizontal, facilitating rapid positioning of the blade 2.
Especially, the static arm can be provided with a positioning part at the root part so as to position the blade 2 in the length direction of the blade 2, and the static clamp arm is favorable for quickly and accurately positioning the blade 2.
In the preferred embodiment, the lower jawarms 28 are static arms.
In addition, in other embodiments, both the upper and lower clamp arms 27, 28 may be configured as a boom structure, which is suitable for automatically performing clamping, and when the tool holder 13 moves horizontally, for example, if the position of the stationary arm is determined, the horizontal movement may cause movement interference, so that the workpiece cannot be accurately placed.
For a structural configuration of a movable arm and a fixed arm, the movable arm can be mounted on the fixed arm by adopting a hinge, the movement form of the movable arm is very simple, and for example, a cylinder body can be adopted for direct driving, and a triangular mechanism is formed between the cylinder body and the movable arm and between the cylinder body and the fixed arm.
In the configuration shown in fig. 3, the upper and lower jawarms 27, 28 each constitute a side link for a parallelogram mechanism, which can be driven by means of a single drive 25, which is a basic knowledge in the mechanical field and will not be described further.
In addition, the laser head 15 of the laser is mounted on a vertically arranged linear motion mechanism for the sake of convenience of adjustment according to the operation mode.
Fig. 2 shows an airplane blade falcon laser strengthening impact method, after a workpiece, namely a blade 2 is clamped, the steps of advanced profile scanning 20, namely scanning the falcon 5 through a 3D scanner to generate modeling, then calling a modeling processing K9 glass tool 21, simultaneously processing the tool 14, spraying 22 the falcon 5, and sequentially, further installing the tool 14 on the falcon 5, and calling a laser processing procedure to carry out laser strengthening 23 on the falcon 5.
Claims (10)
1. An aircraft blade falcon laser shock peening apparatus, characterized by, includes:
the workpiece clamp is used for clamping the airplane blade to be strengthened;
the tool is transparent, the matching part of the tool is matched with the tenon part of the airplane blade, and the tool is assembled on the tenon part of the airplane blade after the tenon part of the airplane blade to be strengthened is sprayed with absorption paint;
a first robot arm for driving the workpiece holder;
the laser head of the laser is used for laser shock peening of the falcon part of the airplane blade.
2. The aircraft blade falcon laser impact strengthening device of claim 1, wherein the tooling is a K9 glass plate.
3. An aircraft blade falcon laser impact strengthening device of claim 2, wherein a 3D scanner and a 3D printer are provided to print out the K9 glass sheet by the 3D printer after scanning the aircraft blade falcon to be strengthened.
4. An aircraft blade falcon laser shock peening apparatus as claimed in claim 1 wherein a sealed compartment is provided;
correspondingly, the first mechanical arm, the laser, the tool and the workpiece clamp are all positioned in the closed cabin;
and providing a tool fixture and a driving mechanism thereof for the tool for assembling the tool on the tenon part of the airplane blade to be strengthened.
5. The laser shock peening apparatus for airplane blade falcon part according to claim 4, wherein the closed cabin is provided with an air inlet and an air outlet, and wherein an air exhaust fan is installed at the air outlet;
a second mechanical arm is arranged in the closed cabin, and the second mechanical arm is loaded with a nozzle for absorbing paint spraying and a pipe thereof;
correspondingly, the air inlet is positioned on one side wall, the air outlet is positioned on the side wall opposite to the side wall, the nozzle is positioned on the side of the air outlet in the direction of the air inlet opposite to the air outlet, and the laser is positioned on the side of the air inlet.
6. An aircraft blade falcon laser shock peening apparatus as claimed in claim 5 wherein said extraction fan is provided with a filter means.
7. The aircraft blade falcon laser shock peening apparatus of claim 4 wherein the drive mechanism is a two dimensional drive mechanism including a first horizontal rail and a second horizontal rail running on and perpendicular to the first horizontal rail;
correspondingly, a guide rail sliding block is arranged on the second horizontal guide rail, and the tool clamp is arranged on the guide rail sliding block.
8. An aircraft blade falcon laser shock peening apparatus as claimed in claim 1 wherein the work holder has upper and lower clamp arms for holding end faces of the blade falcon in the up and down direction in the falcon groove direction.
9. The aircraft blade tenon laser shock peening apparatus of claim 8 wherein the upper tong arm and the lower tong arm are each a side link of a parallelogram mechanism.
10. An aircraft blade falcon laser shock peening apparatus as claimed in claim 1 wherein the laser head of the laser is mounted on a vertically disposed linear motion mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010473851.3A CN111549214A (en) | 2020-05-29 | 2020-05-29 | Laser shock strengthening device for tenon part of airplane blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010473851.3A CN111549214A (en) | 2020-05-29 | 2020-05-29 | Laser shock strengthening device for tenon part of airplane blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111549214A true CN111549214A (en) | 2020-08-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010473851.3A Pending CN111549214A (en) | 2020-05-29 | 2020-05-29 | Laser shock strengthening device for tenon part of airplane blade |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2610001A (en) * | 2021-08-16 | 2023-02-22 | Univ Qingdao Technology | Automated LSP process equipment system for aero-engine blade |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109226983A (en) * | 2018-10-18 | 2019-01-18 | 扬州镭奔激光科技有限公司 | The laser impact intensified absorption protective layer coating unit of blade of aviation engine and method |
| CN109371223A (en) * | 2019-01-02 | 2019-02-22 | 济南大学 | Rolling bearing circle laser reinforcing device |
| CN109504849A (en) * | 2018-12-29 | 2019-03-22 | 广东镭奔激光科技有限公司 | Impeller high inclination-angle laser shock in oblique angle Spatial Energy Distribution of Laser Beam compensation method |
| US20190271059A1 (en) * | 2013-10-31 | 2019-09-05 | Ningbo Institute Of Materials Technology & Engineering, Chinese Academy Of Sciences | Laser Shock Peening Apparatus for Surface of Workpiece, and Laser Shock Peening Method |
-
2020
- 2020-05-29 CN CN202010473851.3A patent/CN111549214A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20190271059A1 (en) * | 2013-10-31 | 2019-09-05 | Ningbo Institute Of Materials Technology & Engineering, Chinese Academy Of Sciences | Laser Shock Peening Apparatus for Surface of Workpiece, and Laser Shock Peening Method |
| CN109226983A (en) * | 2018-10-18 | 2019-01-18 | 扬州镭奔激光科技有限公司 | The laser impact intensified absorption protective layer coating unit of blade of aviation engine and method |
| CN109504849A (en) * | 2018-12-29 | 2019-03-22 | 广东镭奔激光科技有限公司 | Impeller high inclination-angle laser shock in oblique angle Spatial Energy Distribution of Laser Beam compensation method |
| CN109371223A (en) * | 2019-01-02 | 2019-02-22 | 济南大学 | Rolling bearing circle laser reinforcing device |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2610001A (en) * | 2021-08-16 | 2023-02-22 | Univ Qingdao Technology | Automated LSP process equipment system for aero-engine blade |
| GB2610001B (en) * | 2021-08-16 | 2023-12-13 | Univ Qingdao Technology | Automated LSP process equipment system for aero-engine blade |
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Application publication date: 20200818 |
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