High-pressure compressor rotor blade collaborative repairing method based on MBD technology

Abstract

The invention relates to the technical field of aero-engine maintenance, in particular to a high-pressure compressor rotor blade collaborative repair method based on model definition, which comprises blade identity recognition, blade fault inspection, pre-welding polishing, laser cleaning, welding, post-welding polishing, profile polishing and profile detection. According to the method, the MBD technology is used for building contents such as product modeling, basic resource library establishment, data transmission and standard specification, the repair precision and efficiency are improved, and data tracing and standardized management in the repair process are achieved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine maintenance, and in particular to a method for repairing rotor blades of an aircraft engine high-pressure compressor. Background Art

[0002] The high-pressure compressor is a key component of an aircraft engine. During long-term operation, its rotor blades are prone to high blade wear, pits, cracks and other faults due to high temperature, high pressure, high-speed airflow and erosion by foreign objects. These faults will cause the aerodynamic performance of the blades to decline, affecting the overall efficiency and safety of the engine. In the current field of aircraft engine maintenance, traditional repair methods have problems such as low efficiency and poor precision. The surface state of the blades is easily changed during the repair process. There is a lack of full-surface inspection methods for the blades, making it difficult to ensure the original performance of the blades. Summary of the invention

[0003] In view of the above problems, the present invention provides a collaborative repair method for high-pressure compressor rotor blades based on model definition (MBD) technology.

[0004] The technical solution adopted is a coordinated repair method for high-pressure compressor rotor blades based on MBD technology, comprising the following steps: S1. Leaf identification; S2. Blade fault inspection; S3. According to the blade fault information, determine whether the blade needs to be extended and repaired; S4. Grinding of blades to be extended before welding; S5. Blade laser cleaning; S6. Blade tip surfacing; S7. Grinding of blades after welding; S8. Blade surface polishing; S9. Blade profile inspection.

[0005] Furthermore, in S1, after the service life of the engine overhaul expires, the disassembled high-pressure compressor rotor blades are subjected to blade identity identification, and the blade furnace batch number is visually identified at the blade tenon portion.

[0006] Furthermore, in S2, the height measured by laser is compared with the normal blade height to identify blade fault information.

[0007] Furthermore, in S3, based on the fault information of the blade, it is determined whether the blade needs to be extended and repaired. If the wear on the blade tip exceeds the normal height, it needs to be extended, and the wear amount is >1.2mm. If the wear on the blade tip does not exceed the normal height, it does not need to be extended, that is, the wear amount is: 0~1.2mm.

[0008] Furthermore, in S4, a robotic arm is used to clamp the blade to be extended, position the blade tenon, and grind the blade tip to a standard height of 1.5 mm before welding.

[0009] Furthermore, in S5, the blade tip portion to be welded is laser cleaned to remove the oxide layer within 1.5 mm from the blade tip after grinding before welding.

[0010] Furthermore, in S6, micro-arc plasma welding was used, the welding current was controlled at 25-30 A, the welding head moving speed was 0.5 mm / s, and the welding path was automatically set according to the blade profile in the MBD model, and the blade tip was surfacing with a thickness of 2.5 mm.

[0011] Furthermore, in S7, the blade after tip surfacing is received, and the blade is ground to a standard blade height using an automatic belt grinding device according to the process parameters in the MBD model, and most of the welding residues on the blade basin, blade back, intake edge, and exhaust edge are removed.

[0012] Furthermore, the step size between the blade basin and blade back surfacing material and the blade substrate is ≤0.1 mm, and the step size between the intake edge and exhaust edge surfacing material and the substrate is ≤1.5 mm.

[0013] Furthermore, in S8, the blade after post-welding grinding is received, and according to the blade surface parameters in the MBD model, the blade surface is polished and polished using a closed-loop detection automatic polishing device to ensure a smooth transition between the surfacing material and the blade substrate on the blade basin, blade back, intake edge, and exhaust edge, thereby ensuring the aerodynamic performance of the blade.

[0014] Furthermore, in S9, the blade after the surface polishing is received, and the blade surface is scanned by using a blue light non-contact measuring device to verify whether the blade surface meets the requirements of the MBD model.

[0015] Furthermore, in S1, it is necessary to establish a database of single blades based on the identified blade furnace batch number as the unique identity of the single blade.

[0016] The beneficial effects of the present invention are: 1. Improve repair accuracy: By using MBD technology, the original design data of the blade and the parameters in the repair process can be accurately combined to ensure that each step in the repair process can be carried out in accordance with the design intent, thereby improving the accuracy of the repair.

[0017] 2. Improve repair efficiency: The automation and digitalization process based on MBD technology can reduce manual operation errors, shorten the repair cycle and improve production efficiency.

[0018] 3. Realize data traceability and standardized management: Through the application of MBD technology, all data in the repair process can be recorded and traced, which is convenient for quality management and management review. At the same time, standardized repair process and parameter settings help to achieve standardized management of the repair process. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 A flowchart of the collaborative repair method for high pressure compressor rotor blades based on model definition; Figure 2 The actual object and model diagram of the high-pressure compressor rotor blade; Figure 3 This is a schematic diagram of the measurement points for the high-pressure compressor rotor blade height; Figure 4 This is a diagram illustrating the repair process of high-pressure compressor rotor blades. DETAILED DESCRIPTION

[0020] The following describes the embodiments of the present invention through specific examples, and those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict.

[0021] It should be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present invention, and thus the drawings only show components related to the present invention rather than being drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout may also be more complicated.

[0022] like Figure 1 As shown, in this embodiment, a high-pressure compressor rotor blade collaborative repair method based on MBD technology is provided, comprising the following steps: S1. Leaf identification; S2. Blade fault inspection; S3. According to the blade fault information, determine whether the blade needs to be extended and repaired; S4. Grinding of blades to be extended before welding; S5. Blade laser cleaning; S6. Blade tip surfacing; S7. Grinding of blades after welding; S8. Blade surface polishing; S9. Blade profile inspection.

[0023] In the specific implementation scenario, the following steps are included: S1. After the engine overhaul service life expires, the disassembled high-pressure compressor rotor blades are identified, and the blade furnace batch number is visually identified at the blade tenon. The identified blade furnace batch number is used as the unique identity of a single blade, and a database of single blades is established.

[0024] S2. The height of the disassembled high-pressure compressor rotor blades is measured by laser measurement. Each blade has 5 height measurement points (such as Figure 3 as shown).

[0025] S3. Determine whether the blade needs to be extended based on the measured height information. If the tip wear value of any of the five measuring points exceeds 1.2 mm, extension repair is required. If the wear values ​​of the five measuring points are all within the range of 0 to 1.2 mm, extension repair is not performed.

[0026] S4. Establish a mathematical relationship between the blade height after being polished by the sand belt and the sand belt wear thickness. According to the blade height information transmitted in step S2, the polishing program is automatically set in combination with the sand belt wear thickness. The blade is polished to a standard height of 1.5 mm, and the sand belt wear thickness is used to automatically determine whether the sand belt needs to be replaced.

[0027] S5. Laser clean the blade tip where cladding is to be performed to remove the oxide layer within 1.5 mm from the blade tip after grinding before welding, so that the metallic luster is exposed.

[0028] S6. Micro-arc plasma welding is adopted, the welding current is controlled at 25~30A, the welding head moving speed is 0.5mm / s, the welding wire feeding speed is 2mm / s, and the welding path is automatically set according to the blade profile in the MBD model, and the blade tip is surfacing with a thickness of 2.5mm.

[0029] S7. Receive the blade after tip surfacing, use automatic belt grinding equipment to establish a mathematical relationship between the blade height that has been polished by the belt and the belt wear thickness, automatically set the grinding program based on the belt wear thickness, grind the blade tip surfacing area to a standard height of 1mm, and remove most of the welding residues on the blade basin, blade back, intake edge, and exhaust edge. Automatically determine whether the belt needs to be replaced based on the belt wear thickness. The step size between the blade basin and blade back surfacing material and the blade substrate is ≤0.1mm, and the step size between the intake edge and exhaust edge surfacing material and the substrate is ≤1.5mm.

[0030] S8. Receive the blades after post-welding grinding, and perform blade surface polishing and polishing using closed-loop detection automatic polishing equipment according to the blade surface parameters in the MBD model to ensure a smooth transition between the surfacing material and the blade substrate on the blade basin, blade back, intake edge, and exhaust edge, and to ensure the aerodynamic performance of the blades. Establish a mathematical relationship between the number of blades that have been polished by the grinding wheel and the grinding wheel wear thickness, and automatically determine whether the grinding wheel needs to be replaced based on the grinding wheel wear thickness.

[0031] S9. Use a blue light non-contact measuring device to scan the three-dimensional surface data of the repaired blade to verify whether the blade surface meets the MBD model requirements and record it in the database of the single blade.

[0032] The purpose of this design is to provide a collaborative repair method for high-pressure compressor rotor blades based on model definition. The technology based on model definition (MBD) integrates non-geometric information such as design information, process information, manufacturing information, and attributes into the three-dimensional model to provide support for the full life cycle management of the product; by using MBD technology, the original design data of the blade and the parameters in the repair process can be accurately combined to ensure that each step in the repair process can be carried out according to the design intent, thereby improving the accuracy of the repair. The automated and digitalized process based on MBD technology can reduce manual operation errors, shorten the repair cycle, and improve production efficiency. Through the application of MBD technology, all data in the repair process can be recorded and traced, which is convenient for quality management and management review. At the same time, standardized repair processes and parameter settings help to achieve standardized management of the repair process.

[0033] Finally, it should be noted that the above are only preferred embodiments of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, it is still possible for those skilled in the art to modify the technical solutions described in the aforementioned embodiments, or to make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A high-pressure compressor rotor blade collaborative repair method based on MBD technology, characterized in that: The following steps are involved: S1. Leaf identification; S2. Blade fault inspection; S3. According to the blade fault information, determine whether the blade needs to be extended and repaired; S4. Grinding of blades to be extended before welding; S5. Blade laser cleaning; S6. Blade tip surfacing; S7. Grinding of blades after welding; S8. Blade surface polishing; S9. Blade profile inspection.

2. The MBD-based high-pressure compressor rotor blade coordinated repair method according to claim 1, characterized in that: In S1, after the engine overhaul service life expires, the disassembled high-pressure compressor rotor blades are identified, and the blade furnace batch number is visually identified at the blade tenon.

3. The MBD-based high-pressure compressor rotor blade coordinated repair method according to claim 1, characterized in that: In S2, the height measured by laser is compared with the normal blade height to identify blade fault information.

4. The MBD-based high-pressure compressor rotor blade coordinated repair method according to claim 1, characterized in that: In S3, based on the fault information of the blade, it is determined whether the blade needs to be extended and repaired. If the blade tip wear exceeds the normal height, it needs to be extended, and the wear amount is >1.2mm. If the blade tip wear does not exceed the normal height, it does not need to be extended, that is, the wear amount is: 0~1.2mm.

5. The MBD-based high-pressure compressor rotor blade coordinated repair method according to claim 1, characterized in that: In S4, a robotic arm is used to clamp the blade to be extended, position the blade tenon, and grind the blade tip to the standard height of 1.5 mm before welding.

6. The MBD-based high-pressure compressor rotor blade coordinated repair method according to claim 1, characterized in that: In S5, the blade tip to be welded is laser cleaned to remove the oxide layer within 1.5 mm from the blade tip after grinding before welding.

7. The MBD-based coordinated repair method for high-pressure compressor rotor blades according to claim 1, characterized in that: In S6, micro-arc plasma welding is used, the welding current is controlled at 25~30A, the welding head movement speed is 0.5mm / s, and the welding path is automatically set according to the blade profile in the MBD model, and the blade tip is welded to a thickness of 2.5mm.

8. The MBD-based high-pressure compressor rotor blade coordinated repair method according to claim 1, characterized in that: In S7, the blade after tip surfacing is received, and the blade is ground to the standard blade height using automatic belt grinding equipment according to the process parameters in the MBD model, and most of the welding residues on the blade basin, blade back, intake edge, and exhaust edge are removed.

9. The MBD-based coordinated repair method for high-pressure compressor rotor blades according to claim 1, characterized in that: In S8, the blades are received after post-welding grinding, and according to the blade surface parameters in the MBD model, the closed-loop detection automatic polishing equipment is used to perform blade surface polishing and polishing to ensure a smooth transition between the surfacing material and the blade substrate on the blade basin, blade back, intake edge, and exhaust edge, thereby ensuring the aerodynamic performance of the blade.

10. The MBD-based high-pressure compressor rotor blade coordinated repair method according to claim 1, characterized in that: In S9, the blade after surface polishing is received, and the blade surface is scanned using a blue light non-contact measurement device to verify whether the blade surface meets the requirements of the MBD model.

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