JP2000263247A - Repair method of direction control crystal alloy parts - Google Patents
Repair method of direction control crystal alloy partsInfo
- Publication number
- JP2000263247A JP2000263247A JP11064112A JP6411299A JP2000263247A JP 2000263247 A JP2000263247 A JP 2000263247A JP 11064112 A JP11064112 A JP 11064112A JP 6411299 A JP6411299 A JP 6411299A JP 2000263247 A JP2000263247 A JP 2000263247A
- Authority
- JP
- Japan
- Prior art keywords
- crystal alloy
- repairing
- control crystal
- direction control
- child
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000013078 crystal Substances 0.000 title claims abstract description 50
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 47
- 239000000956 alloy Substances 0.000 title claims abstract description 47
- 238000000034 method Methods 0.000 title claims abstract description 28
- 230000008439 repair process Effects 0.000 title abstract description 14
- 238000009792 diffusion process Methods 0.000 claims abstract description 7
- 239000007791 liquid phase Substances 0.000 claims abstract description 7
- 238000005304 joining Methods 0.000 claims description 10
- 238000007493 shaping process Methods 0.000 claims description 5
- 239000000463 material Substances 0.000 description 25
- 238000003466 welding Methods 0.000 description 5
- 238000002844 melting Methods 0.000 description 4
- 230000008018 melting Effects 0.000 description 4
- 229910000990 Ni alloy Inorganic materials 0.000 description 2
- 229910000531 Co alloy Inorganic materials 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000007790 scraping Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
- B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
- B23P6/007—Repairing turbine components, e.g. moving or stationary blades, rotors using only additive methods, e.g. build-up welding
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
Abstract
(57)【要約】
【課題】 方向制御結晶合金部品の補修方法において、
補修歩留まりが良く、補修部分の結晶性も変えることな
く復元すること。
【解決手段】 方向制御結晶合金で形成された部品１の
摩耗部分１ａを補修する方法であって、前記部品の摩耗
前の寸法に応じて該部品と同じ方向制御結晶合金で形成
された子部品３を、液相拡散接合により前記摩耗部分に
接合し部品を摩耗前の寸法に回復させる。
(57) [Summary] [PROBLEMS] To repair a direction control crystal alloy part,
Good repair yield and restoration without changing the crystallinity of the repaired part. A method for repairing a worn portion (1a) of a part (1) formed of a direction-controlling crystal alloy, wherein the child part is formed of the same direction-controlling crystal alloy as the part according to the size of the part before wear. 3 is joined to the worn portion by liquid phase diffusion bonding to restore the part to its pre-wear dimensions.
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、一方向凝固結晶や
単結晶の合金、すなわち方向制御結晶合金で形成された
タービン翼等の摩耗部分を補修する方向制御結晶合金部
品の補修方法に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method for repairing a direction control crystal alloy component for repairing a worn portion such as a turbine blade formed of a directionally solidified crystal or a single crystal alloy, that is, a direction control crystal alloy.
【０００２】[0002]
【従来の技術】近年、ガスタービンに使用される高温セ
クション部品（タービン翼等）は、高温で高強度が得ら
れる一方向凝固結晶や単結晶、すなわち方向制御結晶の
合金で形成されることが多くなっている。これらの方向
制御結晶合金で形成された部品は、その使用環境におい
て摩耗した場合、オーバーホール等において元の寸法に
回復させるための補修を行う必要がある。従来の上記部
品における補修方法は、図２に示すように、例えばター
ビン翼１では、摩耗した翼先端部１ａに元の寸法に応じ
た寸法ｄだけ溶接により肉盛り２を行っていた。2. Description of the Related Art In recent years, high-temperature section components (turbine blades and the like) used in gas turbines are often formed of a directionally solidified crystal or a single crystal, that is, an alloy of a direction control crystal, which can obtain high strength at high temperatures. More. When parts formed of these direction control crystal alloys are worn in their use environment, it is necessary to perform repairs to recover the original dimensions due to overhaul or the like. As shown in FIG. 2, in the conventional repairing method for the above-mentioned parts, for example, in the turbine blade 1, the overlaid portion 2 is welded to the worn blade tip portion 1a by a dimension d corresponding to the original dimension.
【０００３】[0003]
【発明が解決しようとする課題】しかしながら、上記補
修方法では、母材側が方向制御結晶合金（一方向凝固結
晶合金や単結晶合金）であるため、肉盛り溶接によると
溶接性が悪く、母材側が割れやすくなる等、技術・技能
を駆使しても歩留まりが悪くなってしまうという不都合
があった。また、肉盛り溶接した補修部分の組織は、母
材の結晶性、すなわち方向制御結晶合金の結晶性とは異
なるため、機械的性質等が変わってしまう不都合があ
る。However, in the above repair method, since the base material side is a direction-controlling crystal alloy (unidirectionally solidified crystal alloy or single crystal alloy), the weldability is poor by overlay welding and the base material is poor. There was a disadvantage that the yield could be deteriorated even if technology and skills were used, for example, the side was easily broken. In addition, since the structure of the repaired portion welded by overlaying is different from the crystallinity of the base material, that is, the crystallinity of the direction control crystal alloy, there is an inconvenience that the mechanical properties and the like change.
【０００４】本発明は、前述の課題に鑑みてなされたも
ので、補修歩留まりが良く、補修部分の結晶性も変える
ことなく復元することができる方向制御結晶合金部品の
補修方法を提供することを目的とする。The present invention has been made in view of the above-mentioned problems, and an object of the present invention is to provide a method for repairing a directional control crystal alloy part which has a good repair yield and can be restored without changing the crystallinity of the repaired portion. Aim.
【０００５】[0005]
【課題を解決するための手段】本発明は、前記課題を解
決するため、以下の構成を採用した。すなわち、請求項
１記載の方向制御結晶合金部品の補修方法では、方向制
御結晶合金で形成された部品の摩耗部分を補修する方法
であって、前記部品の摩耗前の寸法に応じて該部品と同
じ方向制御結晶合金で形成された子部品を、液相拡散接
合により前記摩耗部分に接合し部品を摩耗前の寸法に回
復させる技術が採用される。The present invention has the following features to attain the object mentioned above. In other words, the method for repairing a direction control crystal alloy component according to claim 1 is a method for repairing a worn portion of a component formed of a direction control crystal alloy, wherein A technique is employed in which a child part formed of the same direction control crystal alloy is joined to the worn part by liquid phase diffusion bonding to recover the part to its dimension before wear.
【０００６】この方向制御結晶合金部品の補修方法で
は、部品の摩耗前の寸法に応じて該部品と同じ方向制御
結晶合金で形成された子部品を、液相拡散接合により摩
耗部分に接合し部品を摩耗前の寸法に回復させるので、
肉盛り溶接に比べて母材の割れ等が生じにくく、さらに
母材と同じ結晶性の子部品で補修されることから、補修
部分の結晶性が母材と同じになって同程度の機械的性質
が得られる。In this method of repairing a directional control crystal alloy part, a child part formed of the same directional control crystal alloy as the part according to the dimension before the part is worn is joined to the wear part by liquid phase diffusion bonding. To the dimensions before wear,
Compared to overlay welding, the base material is less likely to crack and is repaired with the same crystalline child parts as the base material, so the repaired parts have the same crystallinity as the base material and have the same mechanical properties. Properties are obtained.
【０００７】請求項２記載の方向制御結晶合金部品の補
修方法では、請求項１記載の方向制御結晶合金部品の補
修方法において、前記子部品の形状を予め決めて形成
し、前記接合前に前記摩耗部分を前記子部品の形状に応
じて削って整形する技術が採用される。According to a second aspect of the present invention, there is provided the method of repairing a directional control crystal alloy component according to the first aspect, wherein the shape of the child component is determined in advance, and the shape is formed before the joining. A technique of shaping and shaping the worn portion according to the shape of the child component is employed.
【０００８】この方向制御結晶合金部品の補修方法で
は、子部品の形状を予め決めて形成し、接合前に摩耗部
分を子部品の形状に応じて削って整形するので、母材側
を整形することにより、摩耗の度合いに応じて何種類も
形状の異なる子部品を用意する必要がない。In this method of repairing a direction-controlling crystal alloy component, the shape of the child component is determined in advance, and the abraded portion is cut and shaped according to the shape of the child component before joining, so that the base material side is shaped. Thus, there is no need to prepare several types of child parts having different shapes according to the degree of wear.
【０００９】請求項３記載の方向制御結晶合金部品の補
修方法では、請求項１または２記載の方向制御結晶合金
部品の補修方法において、前記部品は、タービン翼であ
る技術が採用される。According to a third aspect of the present invention, there is provided a method of repairing a directional control crystal alloy component according to the first or second aspect, wherein the component is a turbine blade.
【００１０】この方向制御結晶合金部品の補修方法で
は、部品がタービン翼であるので、該タービン翼の摩耗
しやすい翼先端部においても機械的性質を維持した補修
を行うことができる。In this method for repairing a direction-controlling crystal alloy component, since the component is a turbine blade, it is possible to perform repair while maintaining the mechanical properties even at the tip of the turbine blade that is easily worn.
【００１１】[0011]
【発明の実施の形態】以下、本発明に係る方向制御結晶
合金部品の補修方法の一実施形態を、図１を参照しなが
ら説明する。この図において、符号１はタービン翼、３
は子部品、４はインサート材である。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of a method for repairing a direction control crystal alloy component according to the present invention will be described below with reference to FIG. In this figure, reference numeral 1 denotes a turbine blade, 3
Is a child part, and 4 is an insert material.
【００１２】本実施形態の方向制御結晶合金部品の補修
方法は、図１に示すように、Ｎｉ合金やＣｏ合金の方向
制御結晶合金（一方向凝固結晶合金や単結晶合金）で形
成されたタービン翼（部品）１の翼先端部（摩耗部分）
１ａを補修する方法である。まず、図１の（ｃ）に示す
ような子部品３を、タービン翼１を形成する方向制御結
晶合金と同じ材質で形成するとともに、タービン翼１が
新製部品のときの寸法に応じた形状にして用意してお
く。この子部品３は、想定される摩耗部分の摩耗量より
も幅広に予め形成されており、その幅はｄ1と統一的に
決めておく。なお、本実施形態では、タービン翼１の摩
耗量は、４〜５ｍｍ程度と想定し、子部品３の幅ｄ
1は、この値よりも大きく設定される。As shown in FIG. 1, a method for repairing a direction-controlling crystal alloy component according to this embodiment is a turbine formed of a direction-controlling crystal alloy (unidirectionally solidified crystal alloy or single crystal alloy) such as a Ni alloy or a Co alloy. Tip of wing (part) 1 (wear part)
This is a method for repairing 1a. First, the child part 3 as shown in FIG. 1C is formed of the same material as the direction control crystal alloy forming the turbine blade 1 and has a shape corresponding to the dimensions when the turbine blade 1 is a new part. And prepare it. The child part 3 is wider preformed than the wear amount of the worn portion to be assumed, the width kept uniformly decided as d 1. In this embodiment, the wear amount of the turbine blade 1 is assumed to be about 4 to 5 mm, and the width d of the
1 is set larger than this value.
【００１３】そして、図１の（ａ）に示すように、摩耗
前の寸法、すなわち、タービン翼１が新製部品のときの
寸法から幅ｄ2だけ翼先端部１ａが摩耗した場合、図１
の（ｂ）に示すように、子部品３を溶接した際に元の寸
法になるように、翼先端部１ａを子部品３の幅ｄ1およ
び接合面に合わせて削り、整形する。さらに、削られた
翼先端部１ａ上にシート状または粉末状のインサート材
４を配する。なお、該インサート材４は、母材、すなわ
ちタービン翼１を形成する方向制御結晶合金の融点より
も低い融点を有する材料である。例えば、Ｎｉ合金系の
インサート材が用いられる。[0013] Then, as shown in FIG. 1 (a), the dimensions of the prior wear, that is, when the turbine blade 1 has dimensions of only the width d 2 wing tip 1a of the case of the new parts made is worn, FIG
As shown in the (b), so that the original dimensions when welding the child part 3, scraping blade tip 1a to the width d 1 and the bonding surface of the electronic component 3, shaping. Further, a sheet-like or powder-like insert material 4 is arranged on the shaved blade tip 1a. Note that the insert material 4 is a material having a melting point lower than the melting point of the base material, that is, the direction control crystal alloy forming the turbine blade 1. For example, a Ni alloy-based insert material is used.
【００１４】この後、子部材３を、液相拡散接合によっ
て翼先端部１ａに接合する。すなわち、インサート材４
を接合面の間に挟んだ状態で、子部材３と翼先端部１ａ
との接合面に圧力を加えながら、インサート材４の融点
以上で母材（タービン翼１を形成する方向制御結晶合
金）の融点よりも低い温度（接合温度）に加熱して一定
時間保持（等温保持）する。これによって、摩耗部分の
翼先端部１ａに結晶性が同じ子部品３が接合され、ター
ビン翼１は摩耗前の寸法に復元される。Thereafter, the child member 3 is joined to the blade tip 1a by liquid phase diffusion joining. That is, insert material 4
Is sandwiched between the joining surfaces, and the child member 3 and the blade tip 1a
While applying pressure to the joining surface with the base material, the material is heated to a temperature (joining temperature) that is equal to or higher than the melting point of the insert material 4 and lower than the melting point of the base material (the direction-controlling crystal alloy forming the turbine blade 1) and held for a certain time (isothermal). Hold. Thereby, the child part 3 having the same crystallinity is joined to the blade tip portion 1a of the worn portion, and the turbine blade 1 is restored to the dimension before the wear.
【００１５】本実施形態では、タービン翼１の摩耗前の
寸法に応じてタービン翼１と同じ方向制御結晶合金で形
成された子部品３を、液相拡散接合により摩耗部分であ
る翼先端部１ａに接合しタービン翼１を摩耗前の寸法に
回復させるので、肉盛り溶接に比べて母材に熱的なダメ
ージを与えにくく母材の割れ等が生じにくい。さらに、
タービン翼１と同じ結晶性の子部品３で補修されること
から、補修部分の結晶性が母材と同じになって同程度の
機械的性質が得られる。In the present embodiment, a child part 3 formed of the same direction control crystal alloy as the turbine blade 1 in accordance with the size of the turbine blade 1 before wear is attached to a blade tip 1a, which is a worn part by liquid phase diffusion bonding. And the turbine blade 1 is restored to the dimension before the wear, so that the base material is less likely to be thermally damaged than the overlay welding, and the base material is less likely to crack. further,
Since the repair is performed with the child component 3 having the same crystallinity as the turbine blade 1, the crystallinity of the repaired portion becomes the same as that of the base material, and the same mechanical properties can be obtained.
【００１６】また、子部品３の形状を予め決めて形成
し、接合前に摩耗した翼先端部１ａを子部品３の形状に
応じて削っておくので、摩耗の度合いに応じて何種類も
形状の異なる子部品３を用意する必要がない。Further, the shape of the child part 3 is determined in advance, and the worn tip portion 1a of the blade is shaved according to the shape of the child part 3 before joining. There is no need to prepare different child parts 3.
【００１７】なお、本発明は、次のような実施形態をも
含むものである。すなわち、上記実施形態では、方向制
御結晶合金部品としてタービン翼を補修したが、方向制
御結晶合金で形成されたものであれば、他の部品を補修
することに適用しても構わない。特に、補修後も機械的
性質が同等であることから、高温セクションに用いられ
る部品の補修に好適である。The present invention includes the following embodiments. That is, in the above embodiment, the turbine blade is repaired as the direction control crystal alloy component. However, the invention may be applied to repair other components as long as the component is formed of the direction control crystal alloy. In particular, since the mechanical properties are the same even after the repair, it is suitable for repairing parts used in high-temperature sections.
【００１８】[0018]
【発明の効果】本発明によれば、以下の効果を奏する。 （１）請求項１記載の方向制御結晶合金部品の補修方法
によれば、部品の摩耗前の寸法に応じて該部品と同じ方
向制御結晶合金で形成された子部品を、液相拡散接合に
より摩耗部分に接合し部品を摩耗前の寸法に回復させる
ので、肉盛り溶接に比べて母材の割れ等が生じにくく、
補修の歩留まりを向上させることができる。さらに、母
材と同じ結晶性の子部品で補修されることから、補修部
分の結晶性を変えることなく復元でき、補修前と同程度
の機械的性質が得られ、部品使用の延命化を図ることが
できる。According to the present invention, the following effects can be obtained. (1) According to the method for repairing a direction control crystal alloy part according to claim 1, a child part formed of the same direction control crystal alloy as the part according to the dimension before wear of the part is subjected to liquid phase diffusion bonding. Since it is joined to the worn part and the parts are restored to the dimensions before wear, cracking of the base material is less likely to occur compared to overlay welding,
The yield of repair can be improved. In addition, since it is repaired with a child part of the same crystallinity as the base material, it can be restored without changing the crystallinity of the repaired part, the same mechanical properties as before repair can be obtained, and the use of parts can be prolonged be able to.
【００１９】（２）請求項２記載の方向制御結晶合金部
品の補修方法によれば、子部品の形状を予め決めて形成
し、接合前に摩耗部分を子部品の形状に応じて削って整
形するので、摩耗の度合いに応じて何種類も形状の異な
る子部品を用意する必要がなく、一定の形状の子部品を
一種類用意するだけでよい。すなわち、補修において子
部品にかかるコストを低減することができる。(2) According to the method of repairing a direction-controlling crystal alloy part according to the second aspect, the shape of the child part is determined in advance and the worn part is shaved and shaped according to the shape of the child part before joining. Therefore, it is not necessary to prepare several types of child parts having different shapes according to the degree of wear, and it is only necessary to prepare one kind of child part having a fixed shape. That is, it is possible to reduce the cost of the child part in the repair.
【００２０】（３）請求項３記載の方向制御結晶合金部
品の補修方法によれば、部品がタービン翼であるので、
該タービン翼の摩耗しやすい翼先端部においても機械的
性質を維持した補修を行うことができ、高温燃焼ガス中
での耐熱性および強度を低下させずに再び使用に供する
ことができる。(3) According to the method for repairing a direction control crystal alloy component according to claim 3, since the component is a turbine blade,
Repair can be performed while maintaining the mechanical properties even at the tip of the turbine blade that is likely to be worn, and the turbine blade can be used again without lowering the heat resistance and strength in high-temperature combustion gas.
【図１】 本発明に係る方向制御結晶合金部品の補修方
法の一実施形態を工程順に示す概略側面図である。FIG. 1 is a schematic side view showing an embodiment of a method for repairing a direction control crystal alloy component according to the present invention in the order of steps.
【図２】 本発明に係る方向制御結晶合金部品の補修方
法の従来例を示す概略側面図である。FIG. 2 is a schematic side view showing a conventional example of a method for repairing a direction control crystal alloy component according to the present invention.
１ タービン翼（方向制御結晶合金部品） １ａ 翼先端部（摩耗部分） ３ 子部品 ４ インサート材 DESCRIPTION OF SYMBOLS 1 Turbine blade (direction control crystal alloy part) 1a Blade tip part (wear part) 3 Sub part 4 Insert material
Claims (3)
（１）の摩耗部分（１ａ）を補修する方法であって、 前記部品の摩耗前の寸法に応じて該部品と同じ方向制御
結晶合金で形成された子部品（３）を、液相拡散接合に
より前記摩耗部分に接合し部品を摩耗前の寸法に回復さ
せることを特徴とする方向制御結晶合金部品の補修方
法。1. A method for repairing a worn part (1a) of a part (1) formed of a direction-controlling crystal alloy, wherein the part is made of the same direction-controlling crystal alloy as the part according to the size of the part before wear. A method for repairing a direction-controlling crystal alloy part, comprising joining the formed child part (3) to the worn part by liquid phase diffusion bonding to recover the part to its dimension before wear.
補修方法において、 前記子部品（３）の形状を予め決めて形成し、 前記接合前に前記摩耗部分（１ａ）を前記子部品の形状
に応じて削って整形することを特徴とする方向制御結晶
合金部品の補修方法。2. The method for repairing a direction control crystal alloy component according to claim 1, wherein the shape of the child component (3) is determined in advance, and the worn portion (1a) is formed before the joining. A method for repairing a direction control crystal alloy part, characterized by shaping and shaping according to the shape.
金部品の補修方法において、 前記部品は、タービン翼（１）であることを特徴とする
方向制御結晶合金部品の補修方法。3. The method for repairing a directional control crystal alloy component according to claim 1, wherein the component is a turbine blade (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP11064112A JP2000263247A (en) | 1999-03-10 | 1999-03-10 | Repair method of direction control crystal alloy parts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP11064112A JP2000263247A (en) | 1999-03-10 | 1999-03-10 | Repair method of direction control crystal alloy parts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JP2000263247A true JP2000263247A (en) | 2000-09-26 |
Family
ID=13248676
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP11064112A Pending JP2000263247A (en) | 1999-03-10 | 1999-03-10 | Repair method of direction control crystal alloy parts |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2000263247A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1231010A1 (en) * | 2001-02-08 | 2002-08-14 | Siemens Westinghouse Power Corporation | Transient liquid phase bonding repair for turbine blades and vanes |
| EP1332824A3 (en) * | 2002-01-30 | 2005-04-20 | Hitachi Ltd. | Method for manufacturing turbine blade and manufactured turbine blade |
| JP2005201242A (en) * | 2003-11-14 | 2005-07-28 | General Electric Co <Ge> | How to repair a gas turbine rotor blade |
| EP1642667A1 (en) * | 2004-10-04 | 2006-04-05 | United Technologies Corporation | Transient liquid phase bonding using sandwich interlayers |
| WO2006076884A1 (en) * | 2005-01-20 | 2006-07-27 | Mtu Aero Engines Gmbh | Method for repairing turbine blades |
| CN100344396C (en) * | 2003-03-25 | 2007-10-24 | 西门子公司 | Process and apparatus for manufacturing a turbine component, turbine components and use of apparatus |
| JP2008128147A (en) * | 2006-11-22 | 2008-06-05 | Toshiba Corp | Gas turbine high temperature part repair method and gas turbine high temperature part |
| CN106573309A (en) * | 2014-08-18 | 2017-04-19 | 西门子能源公司 | A method for repairing a gas turbine engine blade tip |
| US10287896B2 (en) | 2013-09-17 | 2019-05-14 | United Technologies Corporation | Turbine blades and manufacture methods |
| US12296421B2 (en) | 2014-08-05 | 2025-05-13 | Energy Recovery, Inc. | Systems and methods for repairing fluid handling equipment |
-
1999
- 1999-03-10 JP JP11064112A patent/JP2000263247A/en active Pending
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1231010A1 (en) * | 2001-02-08 | 2002-08-14 | Siemens Westinghouse Power Corporation | Transient liquid phase bonding repair for turbine blades and vanes |
| EP1332824A3 (en) * | 2002-01-30 | 2005-04-20 | Hitachi Ltd. | Method for manufacturing turbine blade and manufactured turbine blade |
| US7690112B2 (en) * | 2003-03-25 | 2010-04-06 | Siemens Aktiengesellschaft | Process and apparatus for producing a turbine component, turbine component and use of the apparatus |
| CN100344396C (en) * | 2003-03-25 | 2007-10-24 | 西门子公司 | Process and apparatus for manufacturing a turbine component, turbine components and use of apparatus |
| EP1533071A3 (en) * | 2003-11-14 | 2005-12-21 | General Electric Company | Method for repairing gas turbine rotor blades |
| JP2005201242A (en) * | 2003-11-14 | 2005-07-28 | General Electric Co <Ge> | How to repair a gas turbine rotor blade |
| EP1642667A1 (en) * | 2004-10-04 | 2006-04-05 | United Technologies Corporation | Transient liquid phase bonding using sandwich interlayers |
| US7565996B2 (en) | 2004-10-04 | 2009-07-28 | United Technologies Corp. | Transient liquid phase bonding using sandwich interlayers |
| WO2006076884A1 (en) * | 2005-01-20 | 2006-07-27 | Mtu Aero Engines Gmbh | Method for repairing turbine blades |
| JP2008128147A (en) * | 2006-11-22 | 2008-06-05 | Toshiba Corp | Gas turbine high temperature part repair method and gas turbine high temperature part |
| US10287896B2 (en) | 2013-09-17 | 2019-05-14 | United Technologies Corporation | Turbine blades and manufacture methods |
| US11008875B2 (en) | 2013-09-17 | 2021-05-18 | Raytheon Technologies Corporation | Turbine blades and manufacture methods |
| US12296421B2 (en) | 2014-08-05 | 2025-05-13 | Energy Recovery, Inc. | Systems and methods for repairing fluid handling equipment |
| CN106573309A (en) * | 2014-08-18 | 2017-04-19 | 西门子能源公司 | A method for repairing a gas turbine engine blade tip |
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