JP2012236234A - Repaired structure - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a repaired structure that is excellent in workability and inexpensive.SOLUTION: The repaired structure H has a failure part (crack 30, 31, 40, 50) to which a clad brazing material sheet 1 including a sheet-like metallic plate and a clad layer formed of brazing material powder firmly fixed to at least one surface of the metallic plate, is patched.

Description

  The present invention relates to a repair structure, and more particularly to a repair structure in which a defect portion such as a crack or wear generated in a metal part is repaired.

  Conventionally, as a repair method for repairing cracked parts in metal parts and defective parts such as wear, a paste made of brazing powder is applied to the defective part and heated to sinter or melt to repair. There are a method of repairing by sticking a sintered sheet of brazing material and heating, and a method of repairing by sticking an amorphous brazing material sheet and heating.

  Also, as a method of repairing defect parts such as cracks generated in metal parts, removing the defect parts, filling the removed recess with alloy powder, forming a brazing material layer on the upper surface, and then sintering and repairing There is a repair method (see, for example, Patent Document 1).

Japanese Patent Laid-Open No. 11-43706

  However, the paste made from the brazing powder must be kneaded with the binder into a paste, and the ease of application to the defect site changes depending on the softness of the paste. There was a problem of workability such as the need to adjust the paste to hold the brazing material on the repair object.

  Also, in the repair method for attaching a sintered sheet of brazing material, when the object to be repaired has a complicated shape, the brazing material has poor workability, so that the above-mentioned sintering is performed on the defective part existing in the object to be repaired. There is a problem that it is difficult to apply the sheet by deforming it according to the shape of the object to be repaired.

  In addition, since the amorphous brazing sheet has an amorphous structure, it can be deformed such as bending according to the shape, but is expensive because it is technically difficult to manufacture the amorphous brazing sheet. There's a problem.

  In addition, the repair method described in Patent Document 1 has a step of removing a defective portion, and there is a problem that it cannot be applied to repair a fine scratch before becoming a crack or a member worn down due to wear. is there.

  The present invention has been made in view of the above problems, and an object thereof is to provide a repair structure having good workability and low cost.

In order to solve the above-mentioned problems, in the present invention, a defective part is provided, and a sheet-like base material is fixed to the defective part, and a powder having a brazing material composition is fixed to at least one surface of the base material. A configuration is adopted in which the repair structure is affixed with a clad sheet having a clad layer.
By adopting such a configuration, the repair structure is repaired by covering a defect site such as a crack or wear with a clad sheet having brazing properties.

Moreover, in this invention, the structure that the said clad sheet is deform | transformed corresponding to the shape of the said repair structure containing the said defect part is employ | adopted.
By adopting such a configuration, repair is performed with a clad sheet corresponding to the complex shape of the repair structure having a defect site.

Moreover, in this invention, the said base material employ | adopts the structure that it has a linear expansion coefficient substantially the same as the said repair structure.
By adopting such a configuration, when heated from the outside, the clad sheet having the base material expands in substantially the same manner as the repair structure, and therefore the repair structure receives the expansion amount from the clad sheet having the base material. It is possible to reduce the thermal stress generated due to the difference.

In the present invention, the base material is formed of the same material as the repair structure, The repair structure according to claim 9.
By adopting such a configuration, when heated from the outside, the clad sheet having the base material and the repair structure are made of the same material, so the heat generated due to the difference in expansion received by the repair structure The stress can be further reduced.

Moreover, in this invention, it has the some said defect part and employ | adopts the structure that the said clad sheet is affixed collectively.
By adopting such a configuration, a plurality of defect sites are repaired with a single clad sheet.

According to the present invention, the clad has a defect portion, and has a sheet-like base material on the defect portion and a clad layer formed by fixing a powder having a brazing material composition on at least one surface of the base material. The configuration is a repair structure to which a sheet is attached. Therefore, the repair structure is repaired by covering a defect site such as a crack or wear with a clad sheet having brazing properties. That is, without using an expensive amorphous brazing material sheet, the defect site is repaired with a clad sheet that has good workability and is inexpensive.
Therefore, according to the present invention, there is an effect that it is possible to form an inexpensive repair structure with good workability.

It is a perspective view of a clad brazing material sheet in an embodiment of the present invention. It is a block diagram of the manufacturing apparatus of the clad brazing material sheet in embodiment of this invention. It is a perspective view of the repair structure in embodiment of this invention. FIG. 4 is a cross-sectional view taken along line XX of FIG. 3 for explaining the process of the repair method for a curved surface according to the embodiment of the present invention. FIG. 4 is a cross-sectional view taken along line YY of FIG. 3 for explaining the process of the repair method at the acute angle tip portion according to the embodiment of the present invention. FIG. 4 is a cross-sectional view taken along the line ZZ in FIG. 3 for explaining the process of the repair method for the right-angled portion of the embodiment of the present invention. It is a perspective view of the repair structure in another embodiment of the present invention.

  Hereinafter, embodiments of the present invention will be described with reference to the drawings. In the following drawings, the same reference numerals are assigned to the same members. In order to facilitate understanding, the scales of these drawings are appropriately changed.

FIG. 1 shows a clad brazing material sheet (clad sheet) 1 used in the repair method of the present embodiment.
The clad brazing material sheet 1 is composed of a metal plate (base material) 21 and a clad layer 22 formed by fixing a brazing material powder (powder) 2 to be described later on one surface of the metal plate 21.

  The metal plate 21 is made of, for example, a metal such as a nickel base alloy, stainless steel, or copper processed into a sheet shape. In this embodiment, the structure of the metal plate 21 selects a nickel base alloy.

  The clad layer 22 is formed, for example, by sintering or melting a powder layer made of powder of brazing (BNi-5), nickel, chromium, and silicon. Therefore, the clad layer 22 has a brazing property.

  Next, the clad brazing material sheet 1 used in the repair method of the present embodiment will be described together with the manufacturing process of the clad brazing material sheet 1.

FIG. 2 is a configuration diagram of the manufacturing apparatus D for the clad brazing sheet 1.
The manufacturing apparatus D for the clad brazing material sheet 1 supplies a hopper 3A for storing a brazing material powder 2 having a brazing material composition and a brazing material powder 2 stored in the hopper 3A toward a peripheral surface of a rolling roller 4A to be described later. Belt feeder 5A, rolling rollers 4A and 4B for rolling brazing material powder 2 and metal plate 21 supplied to the peripheral surface of rolling roller 4A, and heating for heat-treating rolled brazing material powder 2 and metal plate 21 It has a furnace 6 and a collection roller 8 for winding up the clad brazing material sheet 1 formed after the heat treatment.

  The brazing material powder 2 is composed of a powder having a brazing material composition. In the present embodiment, the brazing material powder 2 is composed of a mixed powder of brazing (BNi-5) powder, nickel powder, chromium powder and silicon powder, which is the powder constituting the clad layer 22 described above.

  The hopper 3A stores the brazing powder 2 and has a hollow structure that gradually decreases in diameter as the cross-sectional shape goes downward, and supplies the brazing powder 2 toward the peripheral surface of the rolling roller 4A via the belt feeder 5A. It is the composition which makes it.

The belt feeder 5A is provided below the hopper 3A, and is configured to convey the brazing powder 2 supplied from the lower portion of the hopper 3A by being connected to a rotation drive mechanism (not shown) and driven to rotate. Further, the belt feeder 5A is configured such that the conveyance destination is located above the rolling roller 4A and the brazing material powder 2 is supplied onto the circumferential surface of the rolling roller 4A.
The belt feeder 5A has substantially the same width as that of the rolling roller 4A, and is configured to be able to supply the brazing material powder 2 uniformly over the width direction of the rolling roller 4A.

  The rolling rollers 4A and 4B are a pair and are provided below the belt feeder 5A. Moreover, rolling roller 4A, 4B is arrange | positioned so that a mutual surrounding surface may mutually oppose at a predetermined space | interval. And rolling roller 4A, 4B is the structure which rolls the member inserted between rolling roller 4A, 4B by rotationally driving with a rotation drive mechanism not shown.

  The heating furnace 6 is installed below the rolling rollers 4A and 4B. And the heating furnace 6 becomes a structure which heat-processes the brazing material powder 2 and the metal plate 21 which were rolled by the rolling rollers 4A and 4B inserted in the heating furnace 6 via the pulley 9. FIG.

  The collection roller 8 is supported so as to be rotationally driven by a rotational drive mechanism (not shown). And the collection | recovery roller 8 becomes a structure which winds up the clad brazing material sheet | seat 1 obtained through the process of the sintering process by the heating furnace 6. FIG.

Subsequently, the operation of the manufacturing apparatus D will be described.
The manufacturing apparatus D continuously feeds the brazing material powder 2 stored in the hopper 3A toward the circumferential surface of the rolling roller 4A through the belt feeder 5A connected to the lower portion of the hopper 3A over the width direction of the rolling roller 4A. To supply.

The rolling rollers 4A and 4B are rotationally driven at a predetermined distance so that the brazing material powder 2 supplied between the rolling rollers 4A and 4B is inserted between the rolling rollers 4A and 4B from below to be conveyed. The sheet-like metal plate 21 is rolled. By the rolling, the brazing powder 2 is fixed to the metal plate 21.
The metal plate 21 to which the brazing material powder 2 is fixed is inserted into the heating furnace 6 located below the rolling rollers 4A and 4B via a pulley 9.

The heating furnace 6 heats the brazing powder 2 fixed to the metal plate 21 to a temperature near the melting point of the brazing powder 2.
Then, the brazing material powder 2 heated in the heating furnace 6 is sintered or melted to form a layer, which is firmly fixed or welded to the surface of the metal plate 21, thereby forming a clad layer 22 having brazing properties. Is done.

The clad brazing material sheet 1 made of the metal plate 21 and the clad layer 22 manufactured by the above manufacturing process is recovered by being wound by the rotational drive of the recovery roller 8.
Note that the clad brazing material sheet 1 heated by the heating furnace 6 may be cooled by the recovery roller 8 after being cooled as necessary. Moreover, the clad layer 22 can also be provided with a function suitable for the use of the clad brazing material sheet 1 by appropriately adjusting the constituent ratio and type of constituent powder constituting the brazing material powder 2.

In the clad brazing material sheet 1 manufactured in this way, a clad layer 22 having brazing properties is formed on one surface (one surface) of the metal plate 21 over the entire surface. Accordingly, the clad brazing sheet 1 has a brazing property.
Since the clad layer 22 is firmly fixed to the metal plate 21, the clad layer 22 is processed while following the metal plate 21 when the clad brazing material sheet 1 is bent or extruded. Therefore, even if the shape of the clad brazing material sheet 1 is changed, the clad layer 22 is hardly dropped from the metal plate 21 or cracked.
That is, the clad brazing material sheet 1 can be said to have good workability because it has brazing properties and can change its shape.

  Next, the repair method of this embodiment using the clad brazing material sheet 1 having the above-described configuration will be described.

FIG. 3 is a perspective view of the repair structure H in the present embodiment.
The repair structure H is obtained by repairing cracks (defect portions) 30, 31, 40, and 50 generated in the turbine blade (repair target member) 100 with the clad brazing material sheet 1.

The turbine blade 100 is a member that obtains a rotational motion force by applying a fluid such as steam or gas to the airfoil portion 110. In the present embodiment, the turbine blade 100 is formed using a nickel-based alloy as a base material.
In a severe environment in which the turbine blade 100 is used, the turbine blade 100 is cracked 30 due to, for example, fatigue damage due to high temperature heat or load over a long period of time, damage due to collision of flying foreign matter, or the like. , 31, 40, 50 are generated.

The cracks 30 and 31 are curved surfaces of the turbine blade 100 and are cracks generated at the center on the airfoil portion 110. The crack 40 is a crack generated at the right tip of the airfoil 110. The crack 50 is a crack generated in the right-angled shape portion that is the corner of the holding portion 120 that holds the turbine blade 100.
The cracks 30, 31, 40, 50 are cracks having a width of 100 micrometers or less, for example.

  Next, a repair method for the cracks 30, 31, 40, and 50 will be described with reference to FIGS.

4A to 4C sequentially illustrate a repair method of the crack 30 using the clad brazing material sheet 1 on a curved surface such as on the airfoil portion 110 of the turbine blade 100.
FIGS. 5A to 5C sequentially illustrate a repair method for the crack 40 using the clad brazing material sheet 1 at a sharp pointed portion such as the right tip of the airfoil 110 of the turbine blade 100. Yes.
6 (A) to 6 (C) sequentially show a repair method of the crack 50 using the clad brazing material sheet 1 in a portion deformed at a right angle such as a right-angled shape portion of the holding portion 120 of the turbine blade 100. .

First, a method for repairing a curved surface shown in FIG. 4 will be described.
FIG. 4A shows a flat clad brazing material sheet 1 cut to an appropriate size corresponding to the size of the crack 30.
First, the flat clad brazing material sheet 1 is deformed in accordance with the shape of the turbine blade 100 including the crack 30. More specifically, the clad brazing material sheet 1 is bent into a shape having a curved surface having substantially the same curvature as the curvature of the airfoil 110 where the crack 30 is generated.
By the curvature, the clad brazing material sheet 1 can be brought into close contact with the turbine blade 100 in accordance with the shape of the airfoil portion 110 including the crack 30.

By being bent, a clad brazing material sheet 1 having a protruding shape on the metal plate 21 side as shown in FIG. 4B is formed.
Next, as shown in FIG. 4C, the curved clad brazing material sheet 1 is placed on the airfoil portion 110 so as to cover the crack 30 so that the clad layer 22 faces the crack 30.

Then, after the clad brazing material sheet 1 is placed, the clad brazing material sheet 1 is heated in a spot manner at a plurality of points along the edge of the clad brazing material sheet 1, and a part of the clad layer 22 is melted to obtain an airfoil portion. 110 is preliminarily brazed.
By the preliminary brazing, the clad brazing sheet 1 can be prevented from being displaced from the cracks 30 and from being peeled off.

Finally, the clad brazing material sheet 1 and the turbine blade 100 preliminarily brazed to the airfoil portion 110 of the turbine blade 100 are placed in a heating furnace such as a vacuum furnace or an atmospheric furnace, and the entire melting point of the cladding layer 22 is placed. (Eg, about 1080 ° C.).
By the heating, the clad layer 22 of the clad brazing material sheet 1 is melted over the whole, and the clad brazing material sheet 1 is firmly brazed to the airfoil portion 110 so as to cover the cracks 30.

The turbine blade 100 is repaired by covering the cracks 30 by the brazing and filling the gaps between the cracks.
Since the metal plate 21 and the turbine blade 100 of the clad brazing material sheet 1 are an alloy containing nickel as a main component, the clad brazing material sheet 1 having the metal plate 21, the turbine blade 100, and the like when heated in a heating furnace. Therefore, the displacement from the crack 30 caused by the difference in expansion amount, peeling, and the like can be suppressed.
In addition, the crack 31 which arose on the same curved surface will be repaired by the repair method similar to the above.

Next, a repair method at the acute angle tip shown in FIG. 5 will be described. The description of the same parts as the repair method in FIG. 4 is omitted.
First, the flat clad brazing material sheet 1 shown in FIG. 5A is deformed in accordance with the shape of the acute-angle tip portion of the airfoil portion 110 including the crack 40.
Here, as shown in FIG. 5 (B), the clad brazing material sheet 1 is preferably plastically deformed to an angle that is slightly more acute than the angle of the tip of the airfoil 110. This is because when the clad brazing material sheet 1 is placed so that the clad layer 22 covers the cracks 40, the sharp tip of the airfoil portion 110 can be held by using the elastic force due to the deformation. Therefore, deviation from the crack 40 of the clad brazing material sheet 1, peeling, etc. can be suppressed more reliably.

Then, as shown in FIG. 5C, after placing the clad brazing material sheet 1 deformed into an acute angle so that the clad layer 22 covers the cracks 40, it is heated in a spot manner and a part of the clad layer 22 is placed. Is preliminarily brazed to the sharp tip of the airfoil 110.
Finally, the clad brazing material sheet 1 and the turbine blade 100 preliminarily brazed to the acute angle tip of the airfoil portion 110 are placed in a heating furnace such as a vacuum furnace and heated, whereby the crack 40 is repaired. The

Next, the repair method in a right-angled part shown in FIG. 6 is demonstrated. Similarly, the description of the same part as the repair method in FIG. 4 is omitted.
First, the flat clad brazing material sheet 1 shown in FIG. 6A is deformed so as to correspond to the right-angled shape part of the holding part 120 including the crack 50. In this modification, it is preferable to process the clad brazing sheet 1 at a right angle using a right-angle shaped member.
By the deformation, a clad brazing material sheet 1 having a right angle shape shown in FIG. 6B is formed.

Then, after placing the clad brazing material sheet 1 deformed at a right angle as shown in FIG. 6C so that the clad layer 22 covers the cracks 50, it is heated in a spot manner to dissolve a part of the clad layer 22. By doing so, it is preliminarily brazed to the right-angled shape part of the holding part 120.
Finally, the clad brazing material sheet 1 and the turbine blade 100 preliminarily brazed to the right-angled shape portion of the holding portion 120 are placed in a heating furnace such as a vacuum furnace and heated to repair the crack 50. .

  The turbine blades 100 each having a plurality of clad brazing material sheets 1 preliminarily attached to each defective portion are collectively heated and brazed in a vacuum furnace, thereby repairing the plurality of defective portions in a single heating process. can do.

In the repair structure H repaired by the repair method, the cracks 30, 31, 40, and 50 are closed by sticking the clad brazing sheet 1.
Moreover, even if the repair structure H is exposed to high-temperature heat, the turbine blade 100 and the metal plate 21 of the clad brazing material sheet 1 are nickel-based alloys and are the same material. Therefore, the thermal stress produced by the difference in expansion between the turbine blade 100 and the metal plate 21 of the clad brazing sheet 1 can be reduced.
The repair structure H can be repaired and reinforced by affixing the clad brazing material sheet 1 to the thinned portion of the turbine blade 100 due to wear and overlaying it.

Therefore, according to the above-described embodiment, the sheet-like metal plate 21 and the brazing material powder 2 on at least one surface of the metal plate 21 are formed in the defective portion (cracks 30, 31, 40, 50) of the turbine blade 100. A clad brazing material sheet 1 having a brazing property is applied to a defect site such as a crack or abrasion by adopting a repairing method in which the clad brazing material sheet 1 having a clad layer 22 formed by adhering and adhering is applied and heated. The turbine blade 100 can be repaired by covering with and brazing by heating. That is, by using the clad brazing material sheet 1 having brazing properties, it is not necessary to separately use a brazing material, and it can be repaired by directly attaching it to a defective portion. Moreover, since the clad layer 22 fixed to the metal plate 21 follows the metal plate 21, the clad brazing material 1 sheet can be deformed according to the shape of the defective portion.
Therefore, according to this embodiment, there is an effect that a workability is good and an inexpensive repair method for a defective portion can be realized.

In the present embodiment, the clad brazing material sheet 1 is heated in a lump along the edge of the clad brazing material sheet 1 and the clad brazing material sheet 1 is held in the turbine blade 100 and then heated collectively. By adopting the repairing method, the clad brazing material sheet 1 can be preliminarily fixed to the turbine blade 100, and then the whole can be heated and brazed.
Therefore, there is an effect that it is possible to suppress the deviation from the defective portion of the clad brazing material sheet 1, the separation, and the like.

Further, in the present embodiment, for a plurality of defect portions, a method of repairing a plurality of clad brazing material sheets 1 collectively after holding the clad brazing material sheet 1 on the turbine blade 100 for each defect portion, respectively. By adopting, a plurality of defective parts can be repaired by one heating.
Therefore, there is an effect that the efficiency of the brazing heating process can be improved.

  Moreover, in this embodiment, it has a defective part by employ | adopting the repair method of sticking to the turbine blade 100, after deform | transforming the clad brazing material sheet | seat 1 corresponding to the shape of the turbine blade 100 containing a defective part. There is an effect that the clad brazing material sheet 1 corresponding to the complicated shape of the turbine blade 100 can be repaired.

  Moreover, in this embodiment, the clad brazing material sheet which has the metal plate 21 at the time of the heating which brazes to a defect site | part by employ | adopting the repair method that the metal plate 21 and the turbine blade 100 are formed with the same material. Since 1 and the turbine blade 100 are made of the same material, there is an effect that peeling, dropping, etc. caused by a difference in expansion amount can be more reliably prevented.

Moreover, according to this embodiment, it has a defective part, the sheet-like metal plate 21 in the defective part, and the clad layer 22 formed by fixing the brazing material powder 2 to at least one surface of the metal plate 21; By adopting the structure of the repair structure H to which the clad brazing material sheet 1 having affixed is applied, the repair structure H has the brazing performance of the brazing brazing material sheet 1 having a brazing property at a defect site such as a crack or wear. It is repaired by being covered with. That is, without using an expensive amorphous brazing material sheet, the defect site is repaired with the clad brazing material sheet 1 having good workability and low cost.
Therefore, according to the present invention, there is an effect that the repairability structure H can be formed with good workability and low cost.

  Moreover, in this embodiment, the clad brazing material sheet 1 adopts a configuration in which the clad brazing material sheet 1 is deformed in accordance with the shape of the repair structure H including the defect portion, so that the repair structure H having the defect portion is complicated. It is repaired with a clad brazing material sheet 1 corresponding to a specific shape.

  In the present embodiment, the metal plate 21 is formed of the same material as the repair structure H, so that when heated from the outside, the clad brazing sheet 1 having the metal plate 21 and the repair are provided. Since the structure H is made of the same material, the thermal stress generated by the difference in the expansion amount received by the repair structure H can be reduced.

  As mentioned above, although preferred embodiment of this invention was described referring drawings, this invention is not limited to the said embodiment. Various shapes, combinations, and the like of the constituent members shown in the above-described embodiments are examples, and various modifications can be made based on design requirements and the like without departing from the gist of the present invention.

  For example, in the above embodiment, it has been described that the repair target is the turbine blade 100. However, the present invention is not limited to the turbine blade 100, but can be widely applied to, for example, metal parts in general.

Further, for example, in the above-described embodiment, it has been described that the clad brazing sheet 1 is attached to each defective portion. However, the present invention is also applicable to a configuration in which the clad brazing material sheet 1 is affixed to a plurality of defect sites (cracks 30, 31, 40) as shown in FIG.
By adopting such a configuration, a plurality of defective portions (cracks 30, 31, 40) are repaired with a single clad brazing material sheet 1. Therefore, the process of cutting the clad brazing material sheet 1 in accordance with the shape of each defect site can be omitted, so that the repair process can be shortened.

Moreover, in the said embodiment, it demonstrated that the metal plate 21 and the turbine blade 100 were formed with the same material. However, the present invention can be applied even if the metal plate 21 and the turbine blade 100 have a substantially identical linear expansion coefficient.
By adopting such a repairing method, the clad brazing material sheet 1 having the metal plate 21 and the turbine blade 100 expand substantially in the same manner during heating to braze to the defective part, and therefore, peeling caused by a difference in expansion amount. , And can be prevented from falling off.
In addition, the repair structure H repaired by such a repair method expands the clad brazing material sheet 1 having the metal plate 21 substantially in the same manner as the repair structure H when heated from the outside. Can reduce the thermal stress caused by the difference in expansion received from the clad brazing sheet 1 having the metal plate 21.

  Further, in the above embodiment, it has been described that the clad brazing sheet 1 is preliminarily fixed to the turbine blade 100 by spot-heating along the edge of the clad brazing sheet 1. However, in the present invention, it is not always necessary to go through a step of preliminarily fixing the clad brazing material sheet 1 to the turbine blade 100 by heating in a spot manner. The present invention may have a configuration in which the clad brazing sheet 1 is separately fixed to the turbine blade 100 using a fixing member.

  Moreover, in the said embodiment, the manufacturing apparatus D demonstrated that the clad layer 22 of the brazing material sheet 1 was formed over the whole surface of the single side | surface of the metal plate 21. FIG. However, the manufacturing apparatus D of the present invention can also form the clad layer 22 over the entire surface of both surfaces of the metal plate 21. In this case, the manufacturing apparatus D operates the hopper 3B shown in FIG. 2 and the belt feeder 5B, and supplies the brazing material powder 2 to the peripheral surface of the rolling roller 4B, whereby the clad layer 22 is formed on both surfaces of the metal plate 21. Can be formed.

  Moreover, in the said embodiment, it demonstrated that the brazing material powder 2 was comprised from the mixed powder of brazing (BNi-5), nickel, chromium, and a silicon | silicone. However, the brazing material powder 2 in the present invention is not necessarily limited to the above configuration. For example, if the brazing material powder 2 is JIS standard BNi-2, the nickel (Ni) powder, the nickel-chromium (Ni-Cr) alloy powder, the nickel-boron (Ni-B) alloy powder, and the iron-chromium ( Fe-Cr) alloy powder, iron-nickel (Fe-Ni) alloy powder and iron-silicon (Fe-Si) alloy powder are mixed, and the total component ratio is nickel (Ni) as a base material component, 6 wt% or more and 8 wt% or less of chromium (Cr), 2.75 wt% or more and 3.5 wt% or less of boron (B), 2.5 wt% or more and 3.5 wt% or less of iron (Fe), silicon (Si ) May be blended so as to be 4 wt% or more and 5 wt% or less.

  DESCRIPTION OF SYMBOLS 1 ... Cladding brazing material sheet (cladding sheet), 2 ... Brazing material powder (powder), 21 ... Metal plate (base material), 22 ... Cladding layer, 30, 31, 40, 50 ... Crack (defect part), 100 ... Turbine Wing (member for repair), H ... repair structure

Claims (5)

  A clad sheet having a defective portion and having a sheet-like base material and a clad layer formed by fixing a powder having a brazing material composition on at least one surface of the base material is attached to the defective portion. A repair structure characterized by that.   The repair structure according to claim 1, wherein the clad sheet is deformed corresponding to a shape of the repair structure including the defective portion.   The repair structure according to claim 1, wherein the base material has substantially the same linear expansion coefficient as the repair structure.   The repair structure according to claim 3, wherein the base material is formed of the same material as the repair structure.   The repair structure according to any one of claims 1 to 4, wherein the repair structure has a plurality of the defect portions, and the clad sheet is pasted together.