Method for laser strengthening repair of easily damaged part of gas compressor blade and related equipment

Abstract

The invention belongs to the technical field of surface treatment after combined machining of parts, and relates to a method and related equipment for laser strengthening repair of easily-damaged parts of a gas compressor blade, a laser shock strengthening technology is adopted, the strength of the easily-damaged parts of a blade tip of the blade is enhanced, and the residual tensile stress of the blade is changed into residual compressive stress on the premise that the roughness is not changed. The invention provides a method for improving the surface integrity of the blade in order to ensure that the blade subjected to laser pulse shock peening treatment does not influence the flow field distribution of the working environment of the blade and under the condition that the surface roughness of the blade is not changed, the stress resistance is enhanced, the surface integrity of a part is improved, and the blade tip corner falling fault is reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of surface treatment after component assembly processing, and relates to a method for laser strengthening and repairing a vulnerable part of a compressor blade and related equipment. Background Art

[0002] During use, aircraft engine compressor blades experience reduced fatigue strength due to resonance, making them susceptible to fatigue fracture. Blade tip failures are a frequent area of ​​failure. Blade tip failures are considered a serious engine failure and, in severe cases, can penetrate the casing, causing significant damage. These failures are generally classified as critical.

[0003] Blade fatigue is related to its surface condition, such as residual stress distribution and roughness. Blades are typically shot-peened in their original component state. After being assembled into a rotor, the blade tips are ground during the balancing process. Due to limited conditions, the blade tip surfaces are only manually polished and rounded, without undergoing other surface treatments such as shot peening. At this point, the residual stress on the blade surface is tensile. Therefore, enhancing the blade tip's surface stress resistance and improving its surface integrity are crucial for reducing blade tip corner failures. Summary of the Invention

[0004] In response to the problems existing in the prior art, the present invention provides a method and related equipment for laser strengthening repair of vulnerable parts of compressor blades. It adopts a blade tip surface strengthening process to improve the surface fatigue strength of vulnerable parts of the compressor blade tip, enhance the stress resistance, reduce the fatigue fracture rate, and improve the surface integrity of the blade. It is an innovative process approach.

[0005] The present invention is achieved through the following technical solutions: A method for laser strengthening and repairing a vulnerable part of a compressor blade, comprising: According to the compressor blade material, a test sample is made and the residual stress on the surface of the test sample before laser shock is measured; Impact tests were performed on the test specimens at different power densities to obtain the relationship between laser power density and residual compressive stress value and depth; Laser shock peening technology is used to laser strengthen the test samples by controlling and adjusting the rectangular laser uniform pulse spot size, the number of laser pulse shocks and the laser pulse strengthening path; The surface residual stress and depth of the laser shock peening overlap area of ​​the test specimen after testing; as well as the depth of the laser shock peening mark; According to the laser strengthening parameters of the test specimen after strengthening treatment, the blade tip is subjected to laser shock strengthening treatment, and the residual stress and roughness are measured for verification.

[0006] Preferably, the relationship between the laser power density and the residual compressive stress value and depth is: after the test specimen is laser shock strengthened, the greater the laser power density, the greater the depth of the residual compressive stress implanted in the test specimen.

[0007] Preferably, the laser shock peening technology is used to perform laser peening treatment on the test sample by controlling and adjusting the uniform rectangular laser pulse spot size, specifically: At the same laser power density, the laser shock peening treatment was performed on the test sample by changing the size of the rectangular uniform laser pulse spot. Preferably, the laser shock peening technology is used to laser-strengthen the test sample by controlling and adjusting the number of laser pulse shocks, specifically: By keeping the rectangular uniform laser pulse spot size and power density constant and changing the number of laser pulse shocks, the test sample was subjected to laser shock peening treatment. Preferably, the laser shock peening technology is used to laser-peen the test sample by controlling and adjusting the laser pulse strengthening path, specifically: The rectangular uniform laser pulse spot size, power density and number of laser pulse impacts are controlled to remain unchanged. By changing the laser pulse impact path, the test sample is subjected to laser shock peening treatment. Preferably, the path includes a bow-shaped, edge-to-center direction and unidirectional scanning path; Preferably, under different laser shock power densities, the laser shock peening test specimen is subjected to a step profiler to measure the depth of the laser shock mark.

[0008] Preferably, the blade tip is subjected to laser shock peening treatment according to the laser peening parameters of the test sample after the peening treatment, specifically: Based on the laser strengthening parameters of the laser pulse shock peening test specimen, the blade tip rectangular uniform laser shock peening path, laser shock area, rectangular laser pulse area, laser pulse power density and pulse shock frequency were determined, as well as the laser shock energy variation in the laser shock peening transition area on the blade tip side. The blade tip was then laser shock peened. Preferably, the laser strengthening parameters of the test sample include energy density, spot shape, spot size, pulse width, overlap rate and impact mode of laser strengthening.

[0009] A device related to laser enhanced repair of easily damaged parts of compressor blades is based on a method for laser enhanced repair of easily damaged parts of compressor blades.

[0010] Compared with the prior art, the present invention has the following beneficial technical effects: This patent proposes a method for improving the surface integrity of compressor blades while the rotor is in a working state, and a method for laser cladding repair of vulnerable areas of compressor blades. Laser shock peening (LPP) is proposed to enhance the strength of the vulnerable blade tip. While maintaining the same roughness, the residual tensile stress in the blade is converted to residual compressive stress, enhancing stress resistance, improving the surface integrity of the part, and reducing blade tip chipping failures. To ensure that the blades treated with laser pulse shock peening do not affect the flow field distribution in their operating environment, a method for improving blade surface integrity is proposed without changing the blade surface roughness. This innovative process improves the fatigue strength and stress resistance of the vulnerable areas of the compressor blade tip, reduces fatigue fracture rates, and improves blade surface integrity. The patented method utilizes different laser cladding parameters based on the size of the compressor blade chip and the material grade. The high-pressure shock waves generated by laser irradiation on the metal surface induce changes in the residual compressive stress and microstructure within the material, forming a stronger induced residual compressive stress layer than traditional mechanical shot peening. This enhances stress resistance, improves the surface integrity of the part, and reduces blade chipping failures.

[0011] Furthermore, the present invention adopts laser shock peening technology, which uses high-pressure shock waves generated by laser irradiation on the surface of metal materials to induce changes in residual compressive stress and microstructure within the material, forming an induced residual compressive stress layer that is stronger than traditional mechanical shot peening. This effectively improves the stress state on the blade surface, thereby significantly improving the blade's stress resistance and reducing the risk of fatigue fracture during use. Furthermore, the present invention achieves effective modification of residual stress on the blade surface by rationally selecting laser strengthening parameters (energy density, spot shape, spot size, pulse width, overlap rate, and impact method) without changing the surface roughness of the blade. This overcomes the limitation of traditional shot peening technology that can only generate residual compressive stress on the surface, and significantly improves the overall strength of the blade. Furthermore, the present invention achieves precise control of residual compressive stress on the blade surface by optimizing the process parameters of laser shock, including laser power density, rectangular uniform pulse spot size, number of laser pulse shocks, and laser pulse strengthening path, thereby improving the safety, reliability, and process accuracy of laser shock. Furthermore, the present invention is particularly suitable for surface treatment of compressor rotor blades, and can effectively improve the surface fatigue strength of the blade tip that is easily damaged, reduce the probability of blade tip failure, and extend the service life of the compressor blades; Furthermore, the method of the present invention is simple to operate, the process parameters are easy to control, and it has good repeatability and reproducibility, can realize batch production, and has strong practical value and promotion and application prospects. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for use in the embodiments. It should be understood that the following drawings only illustrate certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying any creative work.

[0013] Figure 1 Schematic diagram of the laser shock path; Figure 2 is a curve of the laser power density, the residual compressive stress in the σx direction, and the residual compressive stress depth in the embodiment; Figure 3 1 is a curve of the laser power density, the residual compressive stress in the σz direction, and the residual compressive stress depth in the embodiment. DETAILED DESCRIPTION

[0014] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings herein can be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present invention provided in the drawings is not intended to limit the scope of the claimed invention, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0015] The present invention is particularly directed to providing a method for laser strengthening and repairing a vulnerable portion of a compressor blade. This method achieves this objective through the following steps: Step 1: Prepare a test sample according to the blade material and test the residual stress on the surface of the test sample before laser shock. Step 2: Analysis of the relationship between laser power density, residual compressive stress, and residual compressive stress depth: Measure the residual compressive stress and residual compressive stress depth on the surface of the laser impact area of ​​the test specimen at different power densities; Step 3: Study the effect of the rectangular uniform laser pulse spot size on the laser strengthening effect of the test sample. Under the same laser power density, change the size of the rectangular uniform laser pulse spot and perform laser shock strengthening on the test sample.

[0016] Step 4: Study the effect of the number of laser pulse shocks on the laser strengthening effect of the test sample: control the rectangular uniform laser pulse spot size and power density unchanged, change the number of laser pulse shock strengthening, and perform laser shock strengthening treatment on the test sample.

[0017] Step 5, study the effect of laser pulse strengthening path on the laser strengthening effect of the test sample: control other laser pulse shock strengthening parameters unchanged, change the laser pulse strengthening path, and perform laser shock strengthening on the test sample. The laser shock path is a bow-shaped path, from the edge of the test sample to the center, from left to right, etc. Figure 1 .

[0018] Step 6: Analysis of surface residual stress in the overlapping area of ​​laser shock spots: Test the relationship between stress distribution and depth in the overlapping area of ​​laser shock spots; Step 7: Measuring the depth of the laser shock peening mark: When using high laser power densities for shock peening, shock peening marks are produced on the material surface, ultimately affecting the blade tip surface finish (roughness) and the flow field distribution in the operating environment. Different laser shock power densities correspond to different blade tip surface finishes. Test specimens were shock peened at different laser shock power densities, and the depth of the laser shock mark was measured using a step profiler.

[0019] Step 8. According to the blade material and design requirements, reasonably select laser strengthening parameters (energy density, spot shape, spot size, pulse width, overlap rate, impact method) for strengthening treatment to achieve the strengthening depth and strength and measure the residual stress and roughness for verification.

[0020] The step 1 includes: Step 101: Select a test sample material that matches the blade material to ensure the homogeneity of the material; Step 102: Surface treatment is performed on the test sample to ensure that the surface is clean and free of impurities. Step 103: Use laser shock equipment to perform laser shock treatment on the test sample to obtain residual stress data before laser shock. The step 2 includes: Step 201: setting laser parameters of different power densities; Step 202: Perform laser shock treatment on each power density value to obtain surface residual compressive stress data of the laser shock area; Step 203: measuring the residual compressive stress depth in the laser shock area; Step 204: plot the measured data into a curve to analyze the relationship between power density, residual compressive stress and depth.

[0021] The step 3 includes: Step 301: Setting parameters of rectangular uniform laser pulse spots of different sizes; Step 302: Perform laser shock treatment on each spot size at the same laser power density; Step 303: measuring the surface residual stress distribution after laser shock processing; Step 304: Analyze the effect of the spot size on the laser enhancement effect. The step 4 includes: Step 401, setting different laser pulse impact times; Step 402: performing laser shock processing for each shock number at the same spot size and power density; Step 403: measuring the surface residual stress change after laser shock processing; Step 404: Analyze the influence of the number of impacts on the laser strengthening effect. The step 5 includes: Step 501: Design laser pulse intensification routes of different paths; Step 502: Perform laser shock peening on each path while keeping other laser parameters unchanged. Step 503: measuring the laser enhancement effects of different paths; Step 504: Analyze the influence of the laser shock path on the laser strengthening effect. The step 6 includes: Step 601: Designing an overlapping layout of laser spots; Step 602: Perform laser shock treatment to obtain stress distribution data of the overlapping area; Step 603: Analyze the effect of laser spot overlap on stress distribution. The step 7 includes: Step 701: Select laser parameters with different power densities; Step 702: Perform laser shock peening to obtain mark depth data; Step 703: Analyze the relationship between laser power density and mark depth. The step 8 includes: Step 801: Determine basic parameters for laser strengthening based on the mechanical properties and design requirements of the blade material. Step 802: Optimize the laser parameters based on the test results to ensure that the strengthening depth meets the design requirements; Step 803: Perform verification tests on the optimized parameters to confirm whether they meet the process requirements.

[0022] Example 1, The compressor rotor blades of a certain aircraft are made of LY2 aluminum alloy and are prone to blade tip chipping. Small chipping can be repaired with filing, but larger chipping poses a risk of damaging subsequent stage blades and degrading engine performance. This failure affects normal engine operation but does not pose a safety risk. Rectangular uniform laser pulse shock treatment was used to ensure that the laser treatment did not alter the blade tip surface roughness, ensuring that the treated sample did not affect the flow field distribution in the operating environment.

[0023] 1) Test specimens were made from LY2 aluminum alloy blades and the residual stress on their surfaces was measured before laser shock treatment. The results are shown in Table 1. The results indicate that residual tensile stress existed on the surface of the test specimens before laser shock treatment.

[0024] Table 1 Surface residual stress of the test specimen before laser shock

[0025] 2) Analysis of the relationship between laser power density, residual compressive stress and residual compressive stress depth: The curves of laser power density, residual compressive stress and residual compressive stress depth are as follows: Figure 2 、 Figure 3 As shown in Figure 2, after laser shock peening, the greater the laser power density, the greater the depth of the residual compressive stress implanted in the test specimen. Even at the lowest laser energy of 2J, the depth of the residual compressive stress implanted in the test specimen exceeded 1.2mm.

[0026] 3) The effect of rectangular uniform laser pulse spot size on the laser peening effect on test specimens was investigated. Laser shock peening was performed on the test specimens at the same laser power density, varying the rectangular uniform laser pulse spot size. The surface residual compressive stress distribution and residual compressive stress depth in the impacted area of ​​the test specimens were measured for different rectangular spot sizes (see Table 2).

[0027] Table 2 Residual compressive stresses generated by impact strengthening with different laser pulse areas and the same laser power density

[0028] At the same laser shock power density, changes in the size of the rectangular laser uniform pulse spot also affect the magnitude and depth of the residual compressive stress in the laser shock strengthened area. The larger the laser shock spot area, the greater the surface residual stress and the residual stress depth.

[0029] 4) Study on the influence of the number of laser pulse impacts on the laser strengthening effect of the test sample: The rectangular uniform laser pulse spot size and power density were kept constant, and the number of laser pulse impact strengthening was changed. The test sample was laser shock strengthened with a single impact, three impacts, and five impacts respectively. The results showed that when the laser impact energy density and spot area remained unchanged, the surface residual stress and residual stress depth increased significantly with the increase in the number of laser pulse impacts.

[0030] 5) Study on the Effect of Laser Pulse Peening Path on the Laser Peening Results of Test Samples: Laser shock peening was performed on test samples while varying the laser pulse peening path while keeping other laser pulse peening parameters constant. The results showed that the surface residual stress generated by the unidirectional laser shock path was greater than that generated by the bow-shaped laser shock path. The surface residual stress generated by the unidirectional laser shock path was less affected by the material texture than that generated by the bow-shaped laser shock path.

[0031] 6) Analysis of surface residual stress in the overlapping area of ​​laser shock spots: In the laser shock peening test specimen test, the overlap rate of laser pulse spots was 3-5%. The surface residual stress and residual stress depth in the overlapping area of ​​laser shock spots were basically the same as those in the non-overlapping area of ​​laser shock spots.

[0032] 7) Measurement of Laser Shock Peening Mark Depth: When high laser power density is used for shock peening, shock peening marks are produced on the material surface, ultimately affecting the blade tip surface finish (roughness) and the flow field distribution in its operating environment. Different laser shock power densities correspond to different blade tip surface finishes. With increasing laser power density and the number of shocks, the depth of the laser shock peening mark increases, as does the average roughness Ra. When the laser energy is 6J and the number of shocks is 3, the deepest laser shock peening mark is 32.216μm. When the laser energy is 4J and the number of shocks is 5, the maximum roughness Ra is 1.358μm. When the laser energy is 3J and the number of shocks is 5, the average surface roughness Ra of the sample is 0.803μm.

[0033] 8) Based on the test parameters of the laser pulse shock peening test sample, the path of the rectangular uniform laser shock peening of the blade tip, the laser shock area, the area of ​​the rectangular laser pulse, the power density of the laser pulse and the frequency of the pulse shock, as well as the laser shock energy change in the laser shock peening transition area on the side of the blade tip are determined, and the blade tip is laser shocked.

[0034] The blade tip surface was laser-shock-peened using a 3J laser pulse energy, a 3.5×4mm laser spot area, 1 laser shock cycle, and a unidirectional laser shock path. To prevent sudden stress changes, the lateral surface adjacent to the tip served as the laser shock transition zone. Laser pulse energy, half the shock energy (1.5J), was used in this transition zone to ensure minimal surface roughness and maintain flow distribution within the blade's operating environment. The laser spot area and number of shock cycles remained constant, while the lateral surface adjacent to the tip was laser-shock-peened for a length of 3cm. The laser shock path was unidirectional, running from the tip edge toward the blade root.

[0035] Table 3 Roughness measurement data of blade before and after laser shock peening

[0036] The residual compressive stress distribution and residual compressive stress depth on the blade tip surface before and after laser shock treatment were measured, as well as the surface residual stress distribution in the laser shock strengthened transition zone on the blade tip side.

[0037] Table 4 Residual stress measurement data after laser shock processing of blade tip

[0038] Table 5 Surface residual stress of the side part adjacent to the blade end after laser shock processing

[0039] After rectangular uniform laser pulse shock peening treatment, residual compressive stress with a depth of 1.2 mm is implanted at the tip of the blade.

[0040] Six blades were laser-shock-peened using rectangular uniform laser pulses. Three-dimensional coordinate measurement was used to measure the morphological changes of the six blades before and after pulsed laser shock peening. After treatment, the largest morphological changes were located at the blade tips, with a maximum deformation of 0.070 mm, which is within the blade's morphological tolerance.

[0041] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0042] It should be noted that the terms "first", "second", etc. in the description and claims of the present invention and the above-mentioned drawings are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present invention described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions. For example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0043] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integrated connection; it can be a mechanical connection, an electrical connection, or a communication connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal connection of two elements or the interaction relationship between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances. When a component is referred to as being "fixed to" another component, it can be directly on the other component or there can also be an intermediate component. When a component is considered to be "connected" to another component, it can be directly connected to the other component or there can be an intermediate component at the same time. When a component is considered to be "set on" another component, it can be directly set on the other component or there can be an intermediate component at the same time.

[0044] In the present invention, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Furthermore, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is lower in level than the second feature.

[0045] It will be understood that when used in this specification and the appended claims, the terms “comprises” and “comprising” indicate the presence of described features, integers, steps, operations, elements and / or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components and / or groups thereof.

[0046] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one skilled in the art to which this invention pertains. The terms used in this specification of the present invention are for the purpose of describing specific embodiments only and are not intended to limit the present invention. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0047] The above description is only a preferred embodiment of the present invention and does not limit the present invention in any form. Any ordinary technician in this industry can smoothly implement the present invention as shown in the drawings and described above. However, any equivalent changes, modifications and evolutions made by technicians familiar with this profession without departing from the scope of the technical solution of the present invention using the technical content disclosed above are all equivalent embodiments of the present invention. At the same time, any equivalent changes, modifications and evolutions made to the above embodiments based on the essential technology of the present invention are still within the scope of protection of the technical solution of the present invention.

Claims

1. A method for laser strengthening and repairing the easily damaged parts of compressor blades, characterized in that: include, According to the compressor blade material, a test sample is made and the residual stress on the surface of the test sample before laser shock is measured; Impact tests were performed on the test specimens at different power densities to obtain the relationship between laser power density and residual compressive stress value and depth; Laser shock peening technology is used to laser strengthen the test samples by controlling and adjusting the rectangular laser uniform pulse spot size, the number of laser pulse shocks and the laser pulse strengthening path; The surface residual stress and depth of the laser shock peening overlap area of ​​the test specimen after testing; as well as the depth of the laser shock peening mark; According to the laser strengthening parameters of the test sample after strengthening treatment, the blade tip is subjected to laser shock strengthening treatment, and the residual stress and roughness are measured for verification to ensure that the surface roughness of the blade tip remains unchanged.

2. The method for laser strengthening and repairing the easily damaged parts of compressor blades according to claim 1 is characterized in that: The relationship between the laser power density and the residual compressive stress value and depth is: after the test sample is laser shock strengthened, the greater the laser power density, the greater the depth of the residual compressive stress implanted in the test sample.

3. The method for laser strengthening and repairing the easily damaged parts of compressor blades according to claim 1 is characterized in that: Laser shock peening technology is used to control and adjust the uniform rectangular laser pulse spot size to perform laser peening on the test sample. Specifically: At the same laser power density, the test sample was subjected to laser shock peening by changing the size of the rectangular uniform laser pulse spot.

4. The method for laser strengthening and repairing the easily damaged parts of compressor blades according to claim 1 is characterized in that: Laser shock peening technology is used to laser strengthen the test sample by controlling and adjusting the number of laser pulse shocks. Specifically: By keeping the rectangular uniform laser pulse spot size and power density unchanged and changing the number of laser pulse shocks, the test sample was subjected to laser shock peening treatment.

5. The method for laser strengthening and repairing the easily damaged parts of compressor blades according to claim 1 is characterized in that: Laser shock peening technology is used to control and adjust the laser pulse strengthening path to perform laser strengthening treatment on the test sample. Specifically: The rectangular uniform laser pulse spot size, power density and number of laser pulse impacts are kept unchanged, and the laser pulse impact path is changed to perform laser shock peening on the test sample.

6. The method for laser strengthening and repairing the easily damaged part of a compressor blade according to claim 5, characterized in that: The paths include bow-shaped, edge-to-center and unidirectional scanning paths.

7. The method for laser strengthening and repairing the easily damaged part of a compressor blade according to claim 1 is characterized in that: At different laser shock power densities, the depth of the laser shock mark on the laser shock peening test specimen is measured using a step profiler.

8. The method for laser strengthening and repairing the easily damaged part of a compressor blade according to claim 1 is characterized in that: According to the laser strengthening parameters of the test sample after strengthening, the blade tip is subjected to laser shock strengthening treatment, specifically: According to the laser strengthening parameters of the laser pulse shock strengthening test specimen, the path of the rectangular uniform laser shock strengthening of the blade tip, the laser shock area, the area of ​​the rectangular laser pulse, the power density of the laser pulse and the frequency of the pulse shock, as well as the laser shock energy change in the laser shock strengthening transition area on the side of the blade tip are determined, and the blade tip is laser shocked.

9. The method for laser strengthening and repairing the easily damaged part of a compressor blade according to claim 8, characterized in that: The laser strengthening parameters of the test sample include the energy density, spot shape, spot size, pulse width, overlap rate and impact mode of the laser strengthening.

10. A device for laser strengthening and repairing the easily damaged parts of a compressor blade, based on the method for laser strengthening and repairing the easily damaged parts of a compressor blade according to any one of claims 1 to 9.

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