JP2012229639A - Method for repairing turbine high-temperature component, gas turbine moving blade and gas turbine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a method for repairing a turbine high-temperature component.SOLUTION: The method for repairing the turbine high-temperature component including a plate-like member made of a metal and having an upper surface, a first side surface and a second side surface, includes: a step of chamfering a portion between the upper surface and the first side surface of the plate-like member, and forming chamfered surfaces having the first and second borders with respect to the respective first side surface and upper surface; a step of forming a first built-up portion by built-up welding a side closer to the first side surface than the middle part of the first and second borders as a first target position on the chamfered surface; a step of forming a second built-up portion by built-up welding on the upper surface by defining a portion between the second border and third border of the upper surface and the second side surface as a second target position; a step of forming a third built-up portion by built-up welding on the first built-up portion by defining a portion between the first border and the first target position as a third target position; and a step of forming a fourth built-up portion by built-up welding on the second built-up portion by defining the portion between the second and third border as a fourth target position.

Description

  The present invention relates to a method for repairing a turbine high-temperature component, a gas turbine blade, and a gas turbine.

  In a gas turbine, the combustion efficiency can be improved by increasing the combustion temperature. Therefore, in the 1990s, the mainstream of the stationary blade inlet gas temperature was 1100 ° C, but since the 2000s, models of 1300 ° C and 1500 ° C have been developed and put into operation. A tip squealer is disposed at the tip of the gas turbine blade. The tip squealer is subject to wear due to high temperature oxidation and erosion by being exposed to high temperature combustion gas and sliding with the shroud segment on the opposite surface. When wear occurs in the chip squealer, the chip squealer is repaired and reused (for example, see Patent Document 1). For example, the tip squealer can be repaired by overlay welding such as TIG (Tungusten Inert Gas) welding or laser welding.

JP 2006-233965 A

The shape of the chip squealer after repair needs to be substantially the same as the shape of the chip squealer before use. For this reason, in the repair of the chip squealer, the width of the chip squealer after repair is made equal to the width of the chip squealer before use by grinding the surplus portion after the build-up more than the width of the chip squealer. .
The tip squealer of an aircraft gas turbine blade has a relatively narrow width, and therefore can be built up more than the tip squealer width in one build-up. However, in industrial gas turbines, the width of the chip squealer is wide, and it is difficult to build up more than the width of the chip squealer in one build-up. In addition, because of the wettability of the metal, it is difficult to build up the chip squealer beyond the width of the chip squealer, even if it is built up aiming at the edge of the chip squealer.
In view of the above, it is an object of the present invention to provide a method for repairing a turbine high-temperature component that is compatible with relatively wide components.

  A method for repairing a high-temperature turbine component according to one aspect of the present invention is a method for repairing a high-temperature turbine component including a plate-like member made of metal and having an upper surface, first and second side surfaces, Chamfering between an upper surface and a first side surface to form a chamfered surface having first and second boundary lines for the first side surface and the upper surface, and the first and second surfaces. Forming the first build-up portion by overlay welding on the chamfered surface with the first side face as the first target position from the middle of the boundary line; and the second boundary Forming a second built-up portion by overlay welding on the top surface, with a line between the upper surface and the third boundary line of the second side surface as a second target position And a first aiming position between the first boundary line and the first aiming position as a third aiming position. Next, a process of forming a third build-up portion by build-up welding, and a portion between the second and third boundary lines as a fourth target position, the meat is formed on the second build-up portion. And a step of forming and forming a fourth built-up portion.

  ADVANTAGE OF THE INVENTION According to this invention, the repair method of the turbine high temperature components which aimed at the comparatively wide components can be provided.

1 is a perspective view illustrating a gas turbine blade 10. 2 is a cross-sectional view illustrating a cross-sectional shape of a chip squealer 12. FIG. It is a figure showing an example of the constituent material of gas turbine blade 10 (chip squealer 12). It is a flowchart showing an example of the repair procedure of the tip squealer 12 which concerns on 1st Embodiment. It is sectional drawing showing the cross-sectional state of the tip squealer 12 repaired in the procedure shown in FIG. It is sectional drawing showing the cross-sectional state of the tip squealer 12 repaired in the procedure shown in FIG. It is sectional drawing showing the cross-sectional state of the tip squealer 12 repaired in the procedure shown in FIG. It is sectional drawing showing the cross-sectional state of the tip squealer 12 repaired in the procedure shown in FIG. It is sectional drawing showing the cross-sectional state of the tip squealer 12 repaired in the procedure shown in FIG. It is sectional drawing showing the cross-sectional state of the tip squealer 12 repaired in the procedure shown in FIG. It is sectional drawing showing the cross-sectional state of the chip | tip squealer 12 welded by the repair procedure which concerns on the comparative example of this invention. It is a flowchart showing an example of the repair procedure of the tip squealer 12 which concerns on 2nd Embodiment. It is sectional drawing showing the cross-sectional state of the tip squealer 12 repaired in the procedure shown in FIG. 2 is an enlarged photograph of a cross-sectional structure of a welded portion after build-up welding according to Example 1. FIG. It is an enlarged photograph of the section structure of the welding part after build-up welding concerning a comparative example.

Hereinafter, embodiments of the present invention will be described in detail with reference to the drawings.
(First embodiment)
FIG. 1 is a perspective view showing a gas turbine blade (robot) 10 for an industrial gas turbine. FIG. 2 is a cross-sectional view showing a cross-sectional shape of the chip squealer 12 along the line AA in FIG. The gas turbine blade 10 includes a gas turbine blade body 11 and a tip squealer 12. The tip squealer 12 is disposed at the tip of the gas turbine blade body 11 and has an upper surface 13, an outer peripheral surface 14, and an inner peripheral surface 15.
In addition, hatching is abbreviate | omitted in sectional drawing (FIG. 2, and subsequent FIG. 5A-5F, FIG. 6, FIG. 8) for legibility.

A Ni-base superalloy is used as a constituent material of the gas turbine blade 10 (chip squealer 12). The Ni-base superalloy is an alloy in which a γ ′ phase (Ni ₃ Al phase) is precipitated and strengthened, and has durability at high temperatures. As shown in FIG. 3, GTD-111, IN738LC, or the like can be used as a constituent material (Ni-base superalloy) of the gas turbine blade 10 (chip squealer 12).

  As described above, by using an industrial gas turbine, the tip squealer 12 is worn, and the need for repair arises.

  Hereinafter, a repair method of the chip squealer 12 will be described. FIG. 4 is a flowchart showing an example of a repair procedure for the chip squealer 12 according to the first embodiment. 5A to 5F are cross-sectional views showing a cross-sectional state of the chip squealer 12 to be repaired by the procedure shown in FIG. This repair method is suitable for repairing a relatively wide chip squealer 12 such as an industrial gas turbine.

(1) Chamfer (Step S11, FIG. 5A)
A chamfer is formed between the upper surface 13 and the outer peripheral surface 14 of the chip squealer 12. As a result, a chamfered surface 16 having first and second boundary lines L1 and L2 is formed on the outer peripheral surface 14 and the upper surface 13, respectively.

  After that, as shown in the next step S12 and after, build-up welding is performed in one layer and two passes. Laser welding using a laser as a heat source for welding and metal powder as a filler metal for welding can be used. In laser welding, the laser irradiation direction is usually the vertical direction of the upper surface 13 (the chip squealer 12 is set up vertically).

  Here, the angle θ formed by the chamfered surface 16 and the outer peripheral surface 14 is preferably 45 ° or more (less than 90 °). The metal powder can be efficiently used during laser welding. When the angle θ is smaller than 45 °, the metal powder is easily spilled from the chamfered surface 16, and the amount of the metal powder that is not used for welding increases.

  The width W1 along the upper surface 13 of the chamfered surface 16 is preferably ¼ or more and ½ or less of the width W of the chip squealer 12. By doing so, it is easy to build up a wider width than the original width W of the chip squealer 12.

(2) Overlay welding to the chamfered surface 16 (step S12, FIG. 5B)
Overlay welding is performed on the chamfered surface 16. That is, welding on the chamfered surface 16 is performed so as to make a round along the outer peripheral surface 14 (first-pass welding), and the first build-up portion N1 is formed. At this time, welding is performed with the outer peripheral surface 14 side as the first target position T1 from the middle of the first and second boundary lines L1 and L2. This is to prevent the outer shape on the outer peripheral surface 14 side of the first build-up portion N1 from being inside the original width W of the chip squealer 12.

(3) Overlay welding to the upper surface 13 (step S13, FIG. 5C)
Overlay welding is performed on the upper surface 13. That is, welding is performed on the upper surface 13 so as to make a round along the inner peripheral surface 15 (second pass welding), and the second build-up portion N2 is formed. At this time, welding is performed with the second boundary line L2 and the third boundary line L3 between the upper surface 13 and the inner peripheral surface 15 as the second target position T2.

  Here, the supply amount of the filler material per unit length when forming the second build-up portion N2 is per unit length when forming the first build-up portion N1 (step S12). It is preferable that the amount is larger than the amount of the filler material supplied at. The supply amount of the filler material is adjusted in correspondence with the width W1 along the upper surface 13 of the chamfered surface 16 being not less than 1/4 and not more than 1/2 of the width W of the chip squealer 12. That is, in the present embodiment, the supply amount of the filler material per unit length when forming the even-numbered built-up portion is the same as that per unit length when forming the odd-numbered built-up portion. The amount is preferably larger than the supply amount of the filler material.

(4) Build-up welding to the first build-up portion N1 (step S14, FIG. 5D)
Overlay welding is performed on the first overlaid portion N1. That is, welding is performed on the first build-up portion N1 so as to make a round along the outer peripheral surface 14 (third pass welding), and the third build-up portion N3 is formed. At this time, welding is performed by setting the space between the first boundary line L1 and the first target position T1 as the third target position T3. This means that the third aiming position T3 is closer to the outer peripheral surface 14 than the first aiming position T1. This is to prevent the outer shape on the outer peripheral surface 14 side of the third build-up portion N3 from being inside the original width W of the chip squealer 12.

(5) Overlay welding to the second overlaid portion N2 (step S15, FIG. 5E)
Overlay welding is performed on the second overlaid portion N2. That is, welding is performed on the second build-up portion N2 so as to make a round along the inner peripheral surface 15 (welding in the fourth pass), and the fourth build-up portion N4 is formed. At this time, welding is performed with the fourth target position T4 between the second and third boundary lines L2 and L3.

  Here, it is preferable that the fourth aiming position T4 is closer to the inner circumferential surface 15 than the second aiming position T2. This is to prevent the outer shape of the fourth built-up portion N3 on the inner peripheral surface 15 side from being inside the original width W of the chip squealer 12.

  Further, when the fourth build-up portion N4 is formed, the supply amount of the filler material per unit length forms the first and third build-up portions N1 and N3 (steps S12 and S14). It is preferable that it is larger than the supply amount of the filler material per unit length of)). The supply amount of the filler material is adjusted in correspondence with the width W1 along the upper surface 13 of the chamfered surface 16 being not less than 1/4 and not more than 1/2 of the width W of the chip squealer 12.

Thereafter, steps S14 and S15 are repeated as appropriate, and one-layer two-pass build-up welding is performed (FIG. 5F).
That is, build-up welding is performed on the third build-up portion N3 to form the fifth build-up portion N5. Similarly, on the fourth build-up portion N4, on the fifth build-up portion N5, and on the sixth build-up portion N6, the build-up welds N6 and the seventh meat are respectively welded. A raised portion N7 and an eighth raised portion N8 are formed.

At this time, the fifth and seventh aiming positions T5 and T7 at the time of forming the fifth and seventh built-up portions N5 and N7 are the same as the third aiming position T3 and the first boundary line L1. 1 and the target position T1. That is, the target positions (third, fifth, and seventh target positions T3, T5, and T7) in the third and subsequent odd-numbered passes are closer to the outer peripheral surface 14 side than the first target position T1. This is to prevent the outer shape of the third, fifth, and seventh build-up portions N3, N5, and N7 on the outer peripheral surface 14 side from being inside the original width W of the chip squealer 12.
The target positions (third, fifth, and seventh target positions T3, T5, and T7) in the third and subsequent odd-numbered passes may be the same.

In addition, the sixth and eighth aiming positions T6 and T8 when the sixth and eighth overlaid portions N6 and N8 are formed are inner peripheral surfaces from the second aiming position T2 in the same manner as the fourth aiming position T4. 15 side. That is, the target positions (fourth, sixth, and eighth target positions T4, T6, and T8) in the fourth and subsequent even-numbered passes are on the inner peripheral surface 15 side from the second target position T2. This is because the outer shape of the fourth, sixth, and eighth build-up portions N4, N6, and N8 on the inner peripheral surface 15 side does not become inside the original width W of the chip squealer 12.
Note that the target positions (fourth, sixth, and eighth target positions T4, T6, and T8) in the fourth and subsequent even-numbered passes may be the same.

  As described above, the chip squealer 12 is repaired by grinding the portion (excess portion) protruding from the original width W of the chip squealer 12 after overlay welding to the chip squealer 12.

  Thus, by welding after chamfering the tip squealer 12, the tip squealer of the turbine blade of the industrial gas turbine that is wider than the aircraft gas turbine is built up and repaired beyond its original width (tip squealer width). it can.

  In the above description, the outer peripheral surface 14 of the chip squealer 12 is chamfered, but the same effect can be obtained by chamfering the inner peripheral surface 15 of the chip squealer 12.

(Comparative example)
FIG. 6 is a cross-sectional view illustrating a cross-sectional state of the tip squealer 12 that is build-up welded by the repair procedure according to the comparative example of the present invention.
In this comparative example, the chip squealer 12 is not chamfered, and is subjected to build-up welding in one layer and two passes to form first to eighth build-up portions N1 to N8 on the upper surface 13 of the chip squealer 12.

  As shown in FIG. 6, the first to eighth build-up portions N1 to N8 tend to taper, and the outer width of the first to eighth build-up portions N1 to N8 is the original width of the chip squealer 12. It is narrower than W. For this reason, with this repair method, it is difficult to reproduce the shape of the chip squealer 12 before use.

(Second Embodiment)
A second embodiment of the present invention will be described.
FIG. 7 is a flowchart illustrating an example of a repair procedure of the chip squealer 12 according to the second embodiment. FIG. 8 is a cross-sectional view showing a cross-sectional state of the tip squealer 12 repaired by the procedure shown in FIG.

(1) Chamfer (step S21)
A chamfer is formed between the upper surface 13 and the outer peripheral surface 14 and the inner peripheral surface 15 of the chip squealer 12. As a result, a chamfered surface 16a having first and second boundary lines L1 and L2 is formed on the outer peripheral surface 14 and the upper surface 13, respectively. Further, chamfered surfaces 16b having third and fourth boundary lines L3 and L4 are formed on the inner peripheral surface 15 and the upper surface 13, respectively. After that, as shown in the next step S22 and subsequent steps, build-up welding is performed in one layer and three passes.

(2) Overlay welding to the chamfered surfaces 16a and 16b (step S22)
Overlay welding is performed on the chamfered surfaces 16a and 16b. That is, welding is performed on the chamfered surface 16a so as to make a round along the outer peripheral surface 14 (first-pass welding), and the first build-up portion N1 is formed. Further, welding is performed on the chamfered surface 16b so as to make a round along the inner peripheral surface 15 (second pass welding), and a second build-up portion N2 is formed.

  At this time, the first pass welding is performed with the outer peripheral surface 14 side as the first target position T1 from the middle of the first and second boundary lines L1 and L2. Further, the second pass welding is performed with the inner peripheral surface 15 side as the second target position T2 from the middle of the third and fourth boundary lines L3 and L4. This is to prevent the outer shape on the outer peripheral surface 14 side of the first build-up portion N1 and the outer shape on the inner peripheral surface 15 side of the second build-up portion N2 from being inside the original width W of the chip squealer 12.

(3) Build-up welding to the upper surface 13 and the first and second build-up portions N1, N2 (step S23)
Overlay welding is performed on the upper surface 13 and the first and second build-up portions N1 and N2 (third pass welding) to form a third build-up portion N3. At this time, welding is performed with the middle between the second and fourth boundary lines L2 and L4 as the third target position T3.

(4) Build-up welding to the first and second build-up portions N1, N2 (step S24)
On the first and second build-up portions N1 and N2, build-up welding is performed (welding in the fourth and fifth passes) to form fourth and fifth build-up portions N4 and N5. At this time, welding between the first boundary line L1 and the first target position T1 is performed with the fourth target position T4 as the fourth target position T4. Further, the fifth pass welding is performed with the fifth target position T5 between the third boundary line L3 and the second target position T2. This means that the fourth aiming position T4 is closer to the outer peripheral surface 14 than the first aiming position T1, and the fifth aiming position T5 is closer to the inner peripheral face 15 than the second aiming position T2. To do. This is to prevent the outer shapes on the outer peripheral surface 14 side and the inner peripheral surface 15 side of the fourth and fifth built-up portions N4 and N5 from being inside the original width W of the chip squealer 12.

(5) Build-up welding to third build-up part N3 (step S25)
Overlay welding is performed on the third overlaid portion N3 (sixth pass welding) to form a sixth overlaid portion N6. At this time, welding is performed with the middle of the second and fourth boundary lines L2 and L4 as the sixth target position T6. The sixth target position T6 may be the same as the third target position T3.

Thereafter, steps S24 and S25 are repeated as appropriate, and one-layer three-pass build-up welding is performed (FIG. 8).
That is, build-up welding is performed on each of the fourth and fifth build-up portions N4 and N5 to form seventh and eighth build-up portions N7 and N8. On the sixth build-up portion N6, the ninth build-up portion N9 is formed by build-up welding. Similarly, the tenth, eleventh, and twelfth build-up portions N10, N11, and N12 are formed on the seventh, eighth, and ninth build-up portions N7, N8, and N9 by welding. Is done.

At this time, the seventh and tenth target positions T7 and T10 when the seventh and tenth overlaid portions N7 and N10 are formed are the same as the fourth target position T4 and the first boundary line L1. 1 and the target position T1. This is to prevent the outer shape on the outer peripheral surface 14 side of the fourth, seventh, and tenth overlaid portions N4, N7, and N10 from being inside the original width W of the chip squealer 12.
However, the seventh and tenth target positions T7 and T10 may be the same as the fourth target position T4.

Further, the eighth and eleventh aim positions T8 and T11 when the eighth and eleventh overlaid portions N8 and N11 are formed are the inner peripheral surfaces from the second aim position T2 in the same manner as the fifth aim position T5. 15 side. This is to prevent the outer shape of the fifth, eighth, and eleventh built-up portions N5, N8, and N10 on the inner peripheral surface 15 side from being inside the original width W of the chip squealer 12.
However, the eighth and eleventh aim positions T8 and T11 may be the same as the fifth aim position T5.

  As described above, the chip squealer 12 is repaired by grinding the portion (excess portion) protruding from the original width W of the chip squealer 12 after overlay welding to the chip squealer 12.

  Thus, by welding after chamfering the tip squealer 12, the tip squealer of the turbine blade of the industrial gas turbine that is wider than the aircraft gas turbine is built up and repaired beyond its original width (tip squealer width). it can.

Example 1
As shown in FIG. 5F of the first embodiment, an actual use blade material is used as the material to be welded, a powder equivalent to GTD-111 is used as the filler material, and a YAG laser is used with a maximum build-up thickness of 4 mm. Four layers of overlay welding were performed in two layers. As welding conditions, the laser output was 400 W, the welding speed was 150 mm / min, the welding atmosphere was an argon atmosphere, and the spot diameter was 4 mm.

  FIG. 9 shows a photograph of the cross-sectional structure of the weld after overlay welding (before finishing). On the chip squealer 12, the built-up portions N1 to N8 are formed. It can be seen that the width of the built-up portions N1 to N8 is equal to or greater than the chip squealer width W.

  In addition, the broken line which shows the upper surface 13 represents the state before welding. During the formation of the build-up portions N1 and N2 (first and second passes), a part of the upper surface 13 of the chip squealer 12 is melted, and the boundary of the upper surface 13 is different before and after welding. This situation is the same in FIG.

(Comparative Example 1)
The welded material is the actual blade material, the filler material is GTD-111 equivalent powder, the maximum overlay thickness is 4 mm, and a YAG laser is used, as shown in FIG. Went. As welding conditions, the laser output was 400 W, the welding speed was 150 mm / min, the welding atmosphere was an argon atmosphere, and the spot diameter was 4 mm.

  FIG. 10 shows a cross-sectional structure of the welded portion after the overlaying and before finishing. On the chip squealer 12, the built-up portions N1 to N8 are formed. It can be seen that the width of the built-up portions N1 to N8 is narrower than the chip squealer width W. That is, every time the overlay is performed, the overlay width becomes narrow, and a predetermined chip squealer width W cannot be obtained.

(Other embodiments)
Embodiments of the present invention are not limited to the above-described embodiments, and can be expanded and modified. The expanded and modified embodiments are also included in the technical scope of the present invention.
(1) Applicable when chamfering either the outer peripheral surface 14 side or the inner peripheral surface 15 side of the chip squealer 12 or both.

(2) In the above embodiment, the repair target is the chip squealer 12. On the other hand, the repair target is made of metal and can be a plate-like member having an upper surface and first and second side surfaces. If this plate-like member is used as a reference, the chip squealer 12 has a cylindrical shape with one of the first and second side surfaces as an inner peripheral surface and the other as an outer peripheral surface.

(3) In the above-described embodiment, one-pass overlay welding to the chamfered surface 16 and the upper surface 13 and three-pass overlay welding to the chamfered surfaces 16 a and 16 b and the upper surface 13 are performed. On the other hand, build-up welding of 3 passes or more to the chamfered surface 16 and the upper surface 13 and build-up welding of 4 passes or more to the chamfered surfaces 16a and 16b and the upper surface 13 are also possible. For example, one-pass three-pass build-up welding with one pass on the chamfered surface 16 and two passes on the top surface 13, and one-pass four-pass build-up welding with one pass on the chamfered surfaces 16 a and 16 b and two passes on the top surface 13 are possible. .

L1-L3 boundary line N1-N8 Overlaying portion 10 Gas turbine blade 11 Gas turbine blade main body 12 Chip squealer 13 Upper surface 14 Outer surface 15 Inner surface 16 Chamfered surface

Claims (13)

A method for repairing a turbine high-temperature component made of metal and including a plate-like member having an upper surface and first and second side surfaces,
Chamfering between the upper surface and the first side surface of the plate-like member to form a chamfered surface having first and second boundary lines with respect to the first side surface and the upper surface, respectively;
A step of forming a first build-up part by performing build-up welding on the chamfered surface with the first side face side as a first target position from the middle of the first and second boundary lines. When,
A second build-up is carried out on the upper surface by setting the second boundary line, and between the upper surface and the third boundary line of the second side surface as a second target position. Forming a part;
A third build-up part is formed by welding on the first build-up part, with the first aim line between the first boundary line and the first aim position as a third aim position. And a process of
A step of forming a fourth built-up portion by performing build-up welding on the second built-up portion with the second and third boundary lines as a fourth target position;
A method for repairing a high-temperature turbine component comprising: The method for repairing a high-temperature turbine component according to claim 1, wherein the fourth aiming position is arranged closer to the second side surface than the second aiming position. A fifth build-up part is formed by overlay welding on the third build-up part, with the first boundary line and the first aim position as a fifth aim position. And a process of
Forming a sixth built-up portion by performing build-up welding on the fourth built-up portion as a sixth target position between the second and third boundary lines;
The turbine high-temperature component repair method according to claim 1, further comprising: The turbine high-temperature component repair method according to claim 1, wherein an angle formed between the chamfered surface and the first side surface is 45 ° or more and less than 90 °. The turbine high-temperature component according to any one of claims 1 to 4, wherein a width of the chamfered surface along the upper surface is ¼ or more and ½ or less of a width of the plate-like member. Repair method. The supply amount of the filler material per unit length in the step of forming the second and fourth build-up portions is per unit length in the step of forming the first and third build-up portions. 6. The method of repairing a high-temperature turbine component according to claim 5, wherein the amount of the filler material is larger than the amount of the filler material supplied at the turbine. A method for repairing a turbine high-temperature component made of metal and including a plate-like member having an upper surface and first and second side surfaces,
Chamfering between the upper surface and the first side surface of the plate-shaped member to form a first chamfered surface having first and second boundary lines with respect to the first side surface and the upper surface, respectively. ,
Chamfering between the upper surface and the second side surface of the plate-like member to form a second chamfered surface having third and fourth boundary lines with respect to the second side surface and the upper surface, respectively. ,
From the middle of the first and second boundary lines, the first side face side is set as the first aiming position, and the first chamfered surface is welded on the first chamfered surface to Forming, and
From the middle of the third and fourth boundary lines, the second side surface side is set as the second aiming position, and the second chamfered surface is welded on the second chamfered surface to Forming, and
A step of forming a third build-up part by performing build-up welding on the upper surface with the second and fourth boundary lines as a third target position;
A fourth build-up part is formed on the first build-up part by welding between the first boundary line and the first aim position as a fourth aim position. And a process of
A fifth build-up portion is formed by welding on the second build-up portion, with the fifth target position between the third boundary line and the second aim position. And a process of
A step of forming a sixth built-up portion by performing build-up welding on the third built-up portion with a sixth target position between the second and third boundary lines;
A method for repairing a high-temperature turbine component comprising: The method for repairing a high-temperature turbine component according to claim 1, wherein a laser is used as a heat source for the welding. The turbine high-temperature component repairing method according to claim 8, wherein the laser irradiation direction is a direction perpendicular to the upper surface. The method for repairing a high-temperature turbine component according to claim 1, wherein a powder is used as a filler material for the welding. 11. The turbine according to claim 1, wherein the plate-shaped member has a cylindrical shape in which one of the first and second side surfaces is an inner peripheral surface and the other is an outer peripheral surface. How to repair hot parts.   A gas turbine rotor blade repaired by using the turbine high-temperature component repair method according to claim 1.   A gas turbine comprising the gas turbine rotor blade according to claim 12.

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