JP4930265B2 - Part joining method and wing part repair method - Google Patents

Description

  The present invention relates to a method for joining a component that joins a second member to the tip of a base projecting from a first member, and a method for repairing a wing component that repairs a wing component in which a blade and a disk are integrally formed.

  For example, in a gas turbine engine used for an aircraft or the like, air sucked from an upstream intake port is compressed by passing through a compressor, and the compressed air is mixed with fuel and burned in a combustor. Thus, high-temperature and high-pressure combustion gas is generated, and an output is obtained by rotating the downstream turbine while the combustion gas expands.

  In compressors and turbines, a plurality of bladed disks each having a plurality of blades attached to the outer periphery of the disk at intervals are used. This bladed disk is generally detachably attached to the disk by fitting the dovetail part of the blade into the slot part of the disk. Recently, a bladed disk called “blisk” in which a blade and a disk are integrally formed has been developed. This blisk has advantages such as higher mechanical strength and reduced weight compared to conventional bladed disks.

  On the other hand, the blisk has a drawback that the damaged blade cannot be easily replaced when the blade is damaged because the blade and the disk are integrally formed. Specifically, with blisk, if the blade damage is relatively minor, the defect can be removed by blending, etc., but if it is necessary to replace the damaged blade, replace the blisk itself. There is a problem that the cost for repairing increases.

  Therefore, a method for exchanging only blades damaged by blisks has been proposed (see, for example, Patent Document 1). Specifically, in this Patent Document 1, after removing a damaged blade so that a short column protruding from the disk remains, a collar physically separated from the disk is arranged around the short column, and this color is used. A method is described in which a collar is removed after a replacement blade is joined to a tip of a protected short column by linear friction welding.

However, when such a collar is arranged around the short column and the replacement blade is joined to the tip of the short column protected by this collar by linear friction welding, the joint between the short column and the replacement blade, particularly In some cases, defects due to poor bonding may occur at the leading edge or trailing edge side of the blade.
JP 2005-351272 A

The present invention has been proposed in view of such conventional circumstances, and the object thereof is to generate defects due to poor bonding when the second member is joined to the tip of the base protruding from the first member. It is an object of the present invention to provide a method for joining parts that can prevent the above.
It is another object of the present invention to provide a method for repairing a wing component that makes it possible to appropriately repair a wing component in which a blade and a disk are integrally formed using such a method.

  As a result of intensive studies to solve the above problems, the inventors of the present invention, when joining the replacement blade (second member) to the tip of the base protruding from the disk (first member), The gap formed between the support member and the support member was found to be the main cause of defects due to poor bonding at the joint between the base and the replacement blade, particularly at the front or rear edge of the blade. The knowledge that the above-mentioned problems can be solved by filling in has been obtained.

That is, the present invention provides the following means.
(1) A method for joining components in which a second member is joined to a tip of a base projecting from a first member,
Attaching a support member surrounding the base to the first member;
Filling a gap formed between the base and the support member;
Joining the second member to the tip of the base by a friction welding method;
And a step of removing the support member.
(2) The method for joining parts according to (1), wherein linear friction welding is used as the friction welding method.
(3) The method for joining parts according to (1) or (2), wherein any one of a welding method, a solid phase joining method, a brazing method, and an adhesive method is used as a method for filling the gap. .
(4) The method for joining parts according to (3), wherein any one of TIG welding, MIG welding, laser welding, and electron beam welding is used as the welding method.
(5) The method for joining parts according to (3) above, wherein friction stir welding is used as the solid phase joining method.
(6) A method of repairing a wing part for repairing a wing part in which a blade and a disk are integrally formed,
After removing the damaged blade from the plurality of blades protruding from the outer peripheral surface of the disk so that the base portion remains, using the method according to any one of (1) to (5), A repair method of a wing part, characterized in that a replacement blade is joined to the base of the blade.

  As described above, in the method for joining parts according to the present invention, before joining the second member to the tip of the base projecting from the first member, the gap formed between the base and the support member is filled in advance. Thus, it is possible to suppress the occurrence of defects due to poor bonding when the second member is joined to the tip of the base portion by friction welding.

  Therefore, in the method for repairing a wing component according to the present invention, by using such a method, a defect due to poor bonding occurs at the joint portion between the base portion and the replacement blade, particularly at the front edge or the rear edge side of the blade. It is possible to prevent. As a result, it is possible to appropriately repair the wing component in which the blade and the disk are integrally formed, and it is not necessary to replace the wing component itself, so that the cost for repair can be reduced. Is possible.

Hereinafter, a method for joining parts and a method for repairing wing parts to which the present invention is applied will be described in detail with reference to the drawings.
In this embodiment, as a method for joining parts to which the present invention is applied, a case where a blisk 1 (blade part) as shown in FIG. 1 is repaired (a wing part repair method to which the present invention is applied) will be described as an example. To do.

  For example, as shown in FIG. 1, the blisk 1 is a disk with a blade in which a disk 2 and a blade 3 are integrally formed. The disk 2 has a plurality of blades 3 protruding from the outer peripheral surface 2a at intervals. They are arranged side by side in the circumferential direction. Examples of the material of the blisk 1 include Ti-6Al-4V and Inconel 718 (trade name, manufactured by Inco). The disk 2 and the blade 3 are generally made of the same material.

  When repairing (replacing) the damaged blade 3A among the plurality of blades 3 protruding from the outer peripheral surface 2a of the disk 2, first, the damaged blade 3A is cut as shown in FIGS. And remove. At this time, since the disk 2 is a component that requires extremely high reliability, the disk 2 was damaged in order to avoid directly joining a replacement blade 3B, which will be described later, to the outer peripheral surface 2a of the disk 2 and to exert a thermal effect. The blade 3A is preferably not removed from the base but removed leaving the base 2A protruding from the outer peripheral surface 2a of the disk 2.

  Next, as shown in FIG. 3, a pair of support members 4 </ b> A and 4 </ b> B surrounding the periphery of the base portion 2 </ b> A are attached to the disk 2. Each of the pair of support members 4A and 4B has a bottom wall 4a and a side wall 4b. When the both end portions of the side walls 4b are abutted on the outer peripheral surface 2a of the disk 2, the periphery of the base portion 2A is formed. It has a surrounding structure. Further, the bottom wall 4a of the support members 4A and 4B has a shape in which the surface facing the outer peripheral surface 2a of the disk 2 corresponds to the outer peripheral surface 2a of the disk 2 so as to be in close contact with the outer peripheral surface 2a of the disk 2. Yes. On the other hand, the side walls 4b of the support members 4A and 4B have a shape in which the surface facing the side surface of the base portion 2A corresponds to the side surface of the base portion 2A so as to be in close contact with one or the other side surface of the base portion 2A.

  The support members 4 </ b> A and 4 </ b> B fix the bottom wall 4 </ b> A to the outer peripheral surface 2 a of the disk 2 using a welding method such as TIG welding. Further, as a method of fixing the support members 4A and 4B to the disk 2, friction stir welding or the like can be used.

  Next, as shown in FIG. 5, a gap S generated between the base 2A and the support members 4A and 4B is filled. Specifically, the end portions on the front edge and the rear edge side of the blade 3 are each narrowed toward the tip. For this reason, a gap S as shown in FIG. 4 is generated between the base 2A and the support members 4A and 4B. In the present invention, for example, such a gap S is filled in advance using a welding method such as TIG welding, MIG welding, laser welding, or electron beam welding (the hole filling portion B shown in FIG. 5 is formed). .

  Further, as a method of filling the gap S, it is preferable to use a solid phase bonding method in addition to the above-described welding method, and specifically, it is preferable to use friction stir welding. This friction stir welding is a solid-phase bonding that uses plastic flow without melting the base material, and has the advantages that it does not cause the quality change of the material accompanying the bonding and can minimize the heat effect. ing. As a method for filling the gap S, for example, a brazing method for filling the gap S with a brazing material such as titanium brazing or silver brazing, an adhesive method for filling the gap S with an adhesive, or the like can be used.

  Further, after filling the gap S, the upper surface of the base 2 and the side walls 4b of the support members 4A and 4B are subjected to machining such as polishing so that the upper surfaces thereof are flush with each other (the same height). It is preferable.

  Next, as shown in FIG. 6, the replacement blade 3B is joined to the tip of the base 2A by a friction welding method. Specifically, in the present invention, linear friction welding is used as the friction welding method. This linear friction joining is a method in which the replacement blade 3B is pressed against the tip surface of the base 2A protected by the support members 4A and 4B while reciprocating in the surface, and the members are softened by the friction heat generated at that time and joined. is there. Thereby, as shown in FIG. 7, the front-end | tip of base 2A and the replacement | exchange blade 3B will be in the state joined by abutting each other's joint surface. Further, when linear friction welding is used, the altered portion (undesirable phase as mechanical characteristics) generated when the gap S described above is filled by welding or the like can be discharged as burrs outside the bonding interface K. Therefore, the tip of the base 2A and the replacement blade 3B can be joined more firmly.

Next, as shown in FIG. 8, after joining, the support members 4A and 4B are removed by machining or the like. Further, after the support members 4A and 4B are removed, burrs are removed and finishing is performed.
By passing through the above processes, the damaged blade 3A among the plurality of blades 3 protruding from the outer peripheral surface 2a of the disk 2 can be repaired.

  As described above, in the component joining method to which the present invention is applied, before joining the replacement blade 3B (second member) to the tip of the base 2A protruding from the disk 2 (first member), the base 2A and By preliminarily filling the gap S generated between the support members 4A and 4B, it is possible to suppress the occurrence of defects due to poor bonding when the replacement blade 3B is joined to the tip of the base 2A by friction welding. is there.

  Therefore, in the repair method of the wing parts to which the present invention is applied, by using such a method, the joint portion between the base portion 2A and the replacement blade 3B, particularly the end portion on the front edge or the rear edge side of the blade 3 is caused by poor joint. It is possible to prevent the occurrence of defects. As a result, it is possible to appropriately repair the blisk 1 (blade part) in which the blade 3 and the disk 2 are integrally formed, and it is not necessary to replace the blisk 1 itself. Costs can be reduced.

  In addition, although the joining method of the components which applied this invention can be used suitably when repairing the said blisk 1, it is limited to the case where the replacement | exchange blade 3B is joined to the front-end | tip of the base 2A protruded from the disk 2 mentioned above. First, it can be widely applied when the second member is joined to the tip of the base protruding from the first member.

FIG. 1 is a perspective view showing a main part of a blisk. FIG. 2 is a view for explaining a blisk repair process, and is a cross-sectional view showing a state where a damaged blade is removed. FIG. 3 is a view for explaining the blisk repair process shown in FIG. 1 and is a cross-sectional view showing a state in which a support member is attached. FIG. 4 is a view for explaining the blisk repair process shown in FIG. 1 and is a plan view showing a state in which a gap is generated between the base and the support member. FIG. 5 is a diagram for explaining the blisk repair process shown in FIG. 1 and is a plan view showing a state in which a gap is filled. FIG. 6 is a view for explaining the blisk repair process shown in FIG. 1 and is a cross-sectional view showing a state in which the replacement blade is joined to the tip of the base portion by friction welding. FIG. 7 is a view for explaining the blisk repair process shown in FIG. 1, and is a cross-sectional view showing a state in which the replacement blade is joined to the tip of the base. FIG. 8 is a view for explaining the blisk repair process shown in FIG. 1, and is a cross-sectional view showing a state where the support member is removed.

Explanation of symbols

  DESCRIPTION OF SYMBOLS 1 ... Blisk (blade part) 2 ... Disk (1st member) 2A ... Base part 3 ... Blade 3A ... Damaged blade 3B ... Replacement blade (2nd member) 4A, 4B ... Support member S ... Gap B ... Embedded part K ... Bonding interface

Claims (6)

A method for joining components, in which a second member is joined to a tip of a base projecting from a first member,
Attaching a support member surrounding the base to the first member;
Filling a gap formed between the base and the support member;
Joining the second member to the tip of the base by a friction welding method;
And a step of removing the support member.   The method of joining parts according to claim 1, wherein linear friction welding is used as the friction welding method.   The method for joining parts according to claim 1 or 2, wherein any one of a welding method, a solid phase joining method, a brazing method, and an adhesive method is used as a method for filling the gap.   4. The method for joining parts according to claim 3, wherein any one of TIG welding, MIG welding, laser welding, and electron beam welding is used as the welding method.   4. The component joining method according to claim 3, wherein friction stir welding is used as the solid phase joining method. A method for repairing a wing part in which a wing part in which a blade and a disk are integrally formed is repaired,
After removing the damaged blade from the plurality of blades protruding from the outer peripheral surface of the disk so that the base portion remains, the base portion of the blade is used by using the method according to any one of claims 1 to 5. A method for repairing wing parts, characterized in that a replacement blade is joined to the blade.

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