CN115890129A

CN115890129A - Repairing process method for thin-wall frame type parts of airplane

Info

Publication number: CN115890129A
Application number: CN202211418245.7A
Authority: CN
Inventors: 陈素明; 何坤; 岳珊; 张颖; 颜家维
Original assignee: AVIC Xian Aircraft Industry Group Co Ltd
Current assignee: AVIC Xian Aircraft Industry Group Co Ltd
Priority date: 2022-11-14
Filing date: 2022-11-14
Publication date: 2023-04-04

Abstract

A repair process method of thin-wall frame type parts of an airplane comprises the following steps that 1) the thin-wall structure of the parts has defects, and 1) the defective parts are arranged to form an open gap which is convenient to repair; 2) Chamfering the edge of the open notch to form a blunt edge structure, so as to increase the wettability of the molten metal; 3) Adding process patches on two sides of the edge of the open notch, wherein the material of the process patches is the same as that of the part, and the edge shape of the process patches is matched with that of the open notch, so that the edge of the process patches is completely attached to the two sides of the edge of the open notch, and a repair notch with the thickness larger than the wall thickness of the part is formed; 4) Repairing the repair gap to completely close the repair gap; 5) And (4) machining the repaired gap part, and removing redundant process allowance to enable the repaired gap part to be consistent with the theoretical structure of the part.

Description

Repairing process method for thin-wall frame type parts of airplane

Technical Field

The invention belongs to the technical field of metallurgy, and relates to a repair process method for thin-wall frame type parts of an airplane.

Background

The large titanium alloy thin-wall frame type part of the airplane has the advantages of large overall dimension, thin wall thickness and high precision requirement, once the part is collided, falls off a cutter, has metallurgical defects and the like in a finish machining stage, the part can be directly scrapped, huge economic loss is caused, and the matching period of models is seriously influenced. At present, the existing laser cladding repair technology is primarily applied to the repair of blanks and rough-machined parts, but for the repair of fine-machined parts, no machining allowance exists, the wall thickness of the parts is generally about 2mm, secondary defects such as deformation, undercut and the like can occur in the repair process of the parts, and the requirements of model development cannot be met. Therefore, a repair technology is urgently needed to solve the problem of repairing the damage of thin-wall frame parts of the airplane, so that the production cost of the parts is saved, and the model matching period is ensured.

Disclosure of Invention

In order to meet the requirement of aircraft production and overcome the defects of the prior art, the method is used for greatly reducing the repair deformation of the parts by optimizing the process design on the basis of the existing laser cladding repair process, solving the problem of undercut after the parts are repaired and finally realizing the high-precision repair of the thin-wall frame parts of the aircraft. The technology is also suitable for repairing other materials like structural products.

A repair process method for thin-wall frame type parts of an airplane, which have defects on the thin-wall structure, is characterized by comprising the following steps: 1) The defect part is regulated to form an open gap convenient for repairing; 2) Chamfering the edge of the open gap to form a truncated structure, so as to increase the wettability of the molten metal; 3) Adding process patches on two sides of the edge of the open gap, wherein the material of the process patches is the same as that of the part, and the edge shape of the process patches is matched with that of the edge of the open gap, so that the edge of the process patches is completely attached to two sides of the edge of the open gap to form a repair gap with the thickness larger than the wall thickness of the part; 4) Repairing the repair gap to completely close the repair gap; 5) And (4) machining the repaired gap part, and removing redundant process allowance to enable the repaired gap part to be consistent with the theoretical structure of the part.

The repair process method for the thin-wall frame type parts of the airplane is characterized in that in the step 4), when the repair gap is repaired, the temperature around the repair gap is not higher than 100 ℃, and the parts are prevented from deforming.

The repairing process method of the thin-wall frame type part of the airplane is characterized in that in the step 4), copper radiating blocks are respectively attached to the side walls of the parts on the two sides of the repaired notch.

The repairing process method for the thin-wall frame type part of the airplane is characterized in that in the step 4), the repairing gap is repaired in a defect repairing mode through an additive repairing method.

The beneficial effect of this application lies in: the method and the device can realize high-precision repair of damaged parts of titanium alloy thin-wall frames, the repaired parts basically have no deformation, the repair area of the machined and finished parts has no undercut and color difference, the repair precision of the parts is high, the surface quality is good, and the high-precision repair requirement of the titanium alloy thin-wall frame parts is met.

Drawings

FIG. 1 is a schematic view of a defective hole in a web of a thin-wall frame type part of an airplane.

FIG. 2 is a schematic diagram illustrating the defect hole of FIG. 1 being processed to form an open notch.

FIG. 3 is a schematic view of a process patch and a copper heat sink added to an open gap.

Fig. 4 is a schematic diagram of repair gap repair by an additive repair method.

The numbering in the figures illustrates: 1 part, 2 defects, 3 open gaps, 4 process patches, 5 radiating blocks and 6 repair gaps.

Detailed Description

Referring to the attached drawings, the repair process method for the thin-wall frame type part of the airplane has the defect 2 on the thin-wall structure of the part 1, wherein the defect 2 in the embodiment is a hole formed by operation error, and the defect hole on the web plate of the thin-wall frame type part needs to be repaired in order to save the part 1 and ensure the integrity of the part. The method comprises the following steps:

(1) And (3) defective part regularizing treatment: processing the defect 2 into an open gap 3 convenient for repairing, so that the repairing equipment can move freely without interference; the opening gap 3 is a trapezoidal opening, and the inclination angle of the edge of the trapezoidal opening ranges from 45 degrees to 70 degrees;

(2) Chamfering edges: chamfering the edge of the open notch 3 to form a fillet structure, so that the wettability of molten metal is improved;

(3) Adding a process patch 4: manufacturing a process patch 4 made of the same material along with the shape by taking the edge of the open notch 3 as a reference, wherein the process patch 4 is tightly attached to the periphery of the edge of the open notch 3, the thickness of the process patch 4 is 1-2 times of the wall thickness of a defective part, the width of the process patch 4 is 2-3 times of the heat affected zone, and the process patch 4 is fixed by using the material made of the same material as the part through spot welding or using other fixing methods which do not influence the material performance;

(4) Repairing the defect: based on the laser cladding repair technology, the repair gap 6 is repaired by a material increase repair method, so that the repair gap 6 is completely closed. In the repairing process, the side walls of the parts on the two sides of the repairing gap 6 can be respectively attached with a copper radiating block 5, so that the temperature around the repairing gap is not higher than 100 ℃, and the deformation of the parts is reduced. Other cooling methods such as air cooling and the like can be adopted to accelerate the heat dissipation of the matrix and reduce the deformation of the parts.

(5) And (3) machining: and (4) machining the position of the repaired notch 6, and removing redundant process allowance to ensure that the repaired notch is consistent with the theoretical structure of the part.

Claims

1. A repair process method for thin-wall frame type parts of an airplane, which have defects on the thin-wall structure, is characterized by comprising the following steps: 1) The defect part is structured to form an open gap which is convenient to repair; 2) Chamfering the edge of the open notch to form a blunt edge structure, so as to increase the wettability of the molten metal; 3) Adding process patches on two sides of the edge of the open gap, wherein the material of the process patches is the same as that of the part, and the edge shape of the process patches is matched with that of the edge of the open gap, so that the edge of the process patches is completely attached to two sides of the edge of the open gap to form a repair gap with the thickness larger than the wall thickness of the part; 4) Repairing the repair gap to completely close the repair gap; 5) And (4) machining the repaired gap part, and removing redundant process allowance to enable the repaired gap part to be consistent with the theoretical structure of the part.

2. The aircraft thin-wall frame part repair process method according to claim 1, wherein in the step 4), when the repair gap is repaired, the temperature around the repair gap is not higher than 100 ℃ so as to prevent the part from deforming.

3. The aircraft thin-wall frame part repair process method according to claim 2, wherein in the step 4), a copper radiating block is respectively attached to the part side walls on two sides of the repair gap.

4. The aircraft thin-wall frame part repair process method according to claim 2, wherein in the step 4), repair gap repair is performed through an additive repair method.