Point-by-point laser cladding repair method for edge notch of thin-walled titanium alloy blade of aircraft

Abstract

This application belongs to the field of aircraft maintenance technology, specifically relating to a method for point-by-point laser cladding repair of edge notches on thin-walled titanium alloy blades for aircraft. The method includes: using a point-by-point laser cladding repair process, along the blade length direction, according to the shape of the edge notch, laser cladding the notch location point by point, and filling the notch layer by layer upwards to repair the edge notch; and grinding the repaired surface at the edge notch location to ensure it matches the overall shape of the blade surface. By employing a point-by-point laser cladding repair process combined with a simple grinding process, in-situ repair of blade edge notches can be achieved, significantly saving materials and maintenance time, and possessing both economic efficiency and timeliness.

Description

Technical Field

[0001] This application belongs to the field of aircraft maintenance technology, specifically relating to a method for point-by-point laser cladding repair of edge notches on thin-walled titanium alloy blades of aircraft. Background Technology

[0002] Aircraft blades are typically made of titanium alloy with thin walls, such as engine fans and compressor blades. They operate in extremely harsh environments, constantly subjected to high temperatures, high pressure loads, and high-speed rotation, making them highly susceptible to chipping at the edges.

[0003] Currently, in-situ repair of aircraft blades with chips at the edges is difficult, and they are mostly replaced directly, which is time-consuming, costly, and wastes resources significantly, which is inconsistent with the concept of sustainable development. Therefore, this application is submitted. Summary of the Invention

[0004] The purpose of this application is to provide a method for point-by-point laser cladding repair of edge notches on aircraft thin-walled titanium alloy blades. The method uses laser repair technology to repair aircraft blades with notches at the edges in situ, thereby extending the service life of the blades and overcoming or mitigating at least one of the known technical defects.

[0005] A method for point-by-point laser cladding repair of edge notches on thin-walled titanium alloy blades for aircraft includes:

[0006] Using a point-by-point laser cladding repair process, along the length of the blade, the material is filled layer by layer upwards according to the shape of the blade edge notch and the notch position is laser cladding point by point to achieve the repair of the blade edge notch;

[0007] The surface at the edge of the blade is polished to make it consistent with the overall shape of the blade surface.

[0008] According to at least one embodiment of this application, in the above-described method for repairing edge gaps of thin-walled titanium alloy blades for aircraft by point-by-point laser cladding, the edge gaps of the blades are repaired by point-by-point laser cladding repair process, and the powder / wire material is consistent with the material of the blades.

[0009] According to at least one embodiment of this application, in the above-mentioned method for point-by-point laser cladding repair of edge notches on thin-walled titanium alloy blades for aircraft, a model of the edge notch is established to simulate the repair process of point-by-point laser cladding. The laser power, scanning speed, and powder / filament feeding amount are determined so that the repair material properties at the edge notch location are close to those of the raw material properties and the heat-affected zone and deformation of the blade are minimized.

[0010] According to at least one embodiment of this application, in the above-described method for repairing edge notches of thin-walled titanium alloy blades for aircraft by point-by-point laser cladding, the edge notches of the blades are repaired by point-by-point laser cladding repair process, and the laser power is ≤500w.

[0011] According to at least one embodiment of this application, in the above-described method for repairing edge notches of thin-walled titanium alloy blades for aircraft by point-by-point laser cladding, the edge notches of the blades are repaired by point-by-point laser cladding repair process, with a scanning speed ≤300mm / min and a powder / wire feeding amount ≤80g / h.

[0012] This application has at least the following beneficial technical effects:

[0013] This invention provides a method for point-by-point laser cladding repair of edge notches on thin-walled titanium alloy blades for aircraft. The method employs point-by-point laser cladding repair technology combined with a simple grinding process to achieve in-situ repair of edge notches on the blades. This method can significantly save materials and repair time, and is both economical and efficient. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of point-by-point laser cladding repair of edge notches on thin-walled titanium alloy blades for aircraft, provided in an embodiment of this application.

[0015] Figure 2 yes Figure 1 A magnified view of a portion of the image.

[0016] To better illustrate this embodiment, some content in the accompanying drawings may be omitted, enlarged, or reduced. They are for illustrative purposes only and should not be construed as limiting the scope of this application. Detailed Implementation

[0017] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0018] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The word "comprising" as used in this application description indicates that the concept preceding the word encompasses the concepts listed following the word and their equivalents, without excluding other related concepts.

[0019] Laser repair technology has advantages such as high equipment flexibility, stable and high precision of heat source, and good material cladding performance. It can be applied to in-situ repair of notches in thin-walled titanium alloy blade structures. Based on this, this application provides a point-by-point laser cladding repair method for edge notches of aircraft thin-walled titanium alloy blades. This method is used to repair aircraft blades with notches at the edge in situ, avoiding direct replacement, shortening the maintenance cycle, and reducing costs and resource waste.

[0020] Point-by-point laser cladding technology includes laser powder feeding, laser wire melting, and other laser manufacturing processes.

[0021] Given the thinness of thin-walled titanium alloy blades in aircraft and the absence of external space along their length, a point-by-point laser cladding repair process is employed. Along the blade's length, based on the shape of the edge notch, material is laser-clad layer by layer upwards to fill the notch, thus repairing the edge notch. Figures 1-2 As shown.

[0022] The edge gaps of the blade are repaired using a point-by-point laser cladding repair process, and the powder / filament material is the same as the blade material.

[0023] The key process parameters that need to be controlled when repairing the edge gaps of the blade using point-by-point laser cladding repair technology include laser power, scanning speed, and powder / filament feeding amount.

[0024] By establishing a model of the notch at the blade edge, the point-by-point laser cladding repair process can be simulated to repair the notch at the blade edge. The goal is to ensure that the repair material at the notch location has properties close to those of the original material, and minimizes the heat-affected zone and deformation of the blade. In this way, the laser power, scanning speed, and powder / filament feeding amount can be determined.

[0025] Typically, process parameters such as laser power ≤500W, scanning speed ≤300mm / min, and powder / filament feed rate ≤80g / h can be used. Using lower laser power can prevent melting through and ablation of excessively thin blades, reduce the heat-affected zone and deformation of the blades, and prevent over-melting during the repair process by using lower scanning speed and powder / filament feed rate. This ensures that the performance of the repair material at the edge notch of the blade is close to that of the original material, thus guaranteeing good control of the defect.

[0026] The surface at the edge of the blade is polished to make it consistent with the overall shape of the blade surface.

[0027] The above-described embodiment discloses a point-by-point laser cladding repair method for edge notches of thin-walled titanium alloy blades for aircraft. This method employs a point-by-point laser cladding repair process combined with a simple grinding process to achieve in-situ repair of edge notches on the blades. It can significantly save materials and maintenance time, and is both economical and timely.

[0028] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A method for repairing an edge crack of a thin-walled titanium alloy blade of an aircraft by point-by-point laser cladding, characterized in that, include: Using a point-by-point laser cladding repair process, along the length of the blade, the material is filled layer by layer upwards according to the shape of the blade edge notch and the notch position is laser cladding point by point to achieve the repair of the blade edge notch; The surface at the edge of the blade is polished to make it consistent with the overall shape of the blade surface.

2. The method of claim 1, wherein, The edge gaps of the blade are repaired using a point-by-point laser cladding repair process, and the powder / filament material is the same as the blade material.

3. The method of claim 1, wherein, By establishing a model of the notch at the blade edge, the point-by-point laser cladding repair process is simulated to repair the notch at the blade edge. The goal is to ensure that the repair material at the notch location has properties close to those of the original material, and minimizes the heat-affected zone and deformation of the blade. The laser power, scanning speed, and powder / filament feed rate are then determined.

4. The method of claim 1, wherein, The edge gaps of the blades were repaired using a point-by-point laser cladding repair process with a laser power of ≤500w.

5. The aerospace aircraft thin-walled titanium alloy blade edge notch point-by-point laser cladding repair method according to claim 4, characterized in that, The edge gaps of the blades were repaired using a point-by-point laser cladding repair process, with a scanning speed of ≤300mm / min and a powder / filament feeding rate of ≤80g / h.

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