JP2003342617A - REPAIRED HIGH-TEMPERATURE COMPONENT MADE OF HEAT- RESISTANT ALLOY, REPAIRED GAS-TURBINE BLADE MADE OF Ni- BASED HEAT RESISTANT ALLOY, METHOD FOR REPAIRING GAS- TURBINE BLADE OF Ni-BASED HEAT RESISTANT ALLOY, AND METHOD FOR REPAIRING GAS-TURBINE BLADE MADE OF HEAT RESISTANT ALLOY - Google Patents
REPAIRED HIGH-TEMPERATURE COMPONENT MADE OF HEAT- RESISTANT ALLOY, REPAIRED GAS-TURBINE BLADE MADE OF Ni- BASED HEAT RESISTANT ALLOY, METHOD FOR REPAIRING GAS- TURBINE BLADE OF Ni-BASED HEAT RESISTANT ALLOY, AND METHOD FOR REPAIRING GAS-TURBINE BLADE MADE OF HEAT RESISTANT ALLOYInfo
- Publication number
- JP2003342617A JP2003342617A JP2002158056A JP2002158056A JP2003342617A JP 2003342617 A JP2003342617 A JP 2003342617A JP 2002158056 A JP2002158056 A JP 2002158056A JP 2002158056 A JP2002158056 A JP 2002158056A JP 2003342617 A JP2003342617 A JP 2003342617A
- Authority
- JP
- Japan
- Prior art keywords
- resistant alloy
- heat
- base
- turbine blade
- gas turbine
- 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.)
- Withdrawn
Links
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
- B23P6/005—Repairing turbine components, e.g. moving or stationary blades, rotors using only replacement pieces of a particular form
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、ガスタービン、ジ
ェットエンジンなどの高温環境において腐食と酸化性雰
囲気中で使用される耐熱合金製補修高温部品とその補修
方法に関するものである。とくに、高温環境において高
応力の変動負荷が作用するＮｉ基耐熱合金製補修ガスタ
ービン翼に関するものである。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a heat resistant alloy repairing high temperature component used in a corrosive and oxidizing atmosphere in a high temperature environment such as a gas turbine and a jet engine, and a repairing method therefor. In particular, the present invention relates to a repair gas turbine blade made of a Ni-base heat-resistant alloy, which is subject to a high stress fluctuating load in a high temperature environment.
【０００２】[0002]
【従来の技術】高温環境において腐食と酸化性雰囲気中
で使用されるＮｉ基耐熱合金製高温部品の材料として
は、Ｃｏ、Ｃｒ、Ｍｏ、Ｗ、Ａｌなどを固溶元素として
多量含有し、溶体化処理での固溶強化を主な強化機構と
する固溶強化型Ｎｉ基耐熱合金と、γ’相｛Ｎｉ3（Ａ
ｌ，Ｔｉ）｝の析出強化およびＭｏ、Ｗ等による固溶強
化を兼備える析出強化型Ｎｉ基耐熱合金が用いられてい
る。高温強度、高温耐酸化性および高温耐食性に優れた
特性が要求されるガスタービン動翼の材料としては、析
出強化型Ｎｉ基耐熱合金が適している。2. Description of the Related Art Ni-base heat-resistant alloy high temperature parts used in a corrosive and oxidizing atmosphere in a high temperature environment contain a large amount of Co, Cr, Mo, W, Al, etc. as solid solution elements. Solution strengthened Ni-based heat-resistant alloys whose main strengthening mechanism is solid solution strengthening during aging treatment, and γ'phase {Ni 3 (A
The precipitation-strengthened Ni-base heat-resistant alloy having both precipitation strengthening of (1, Ti)} and solid solution strengthening of Mo, W, etc. is used. Precipitation-strengthened Ni-based heat-resistant alloys are suitable as materials for gas turbine blades, which require high-temperature strength, high-temperature oxidation resistance, and high-temperature corrosion resistance.
【０００３】例えば、特公平１―５９３４４号公報に
は、重量％で、Ｃｒ７〜１３％、Ｃｏ３５％以下、Ｍｏ
８％以下、Ｎｂ３％以下、Ｗ１４％以下、Ｔａ６％以
下、Ａｌ４〜７％、Ｔｉ０．５〜６％（ただし、Ａｌ＋
Ｔｉ６．５〜１０．５％）、Ｖ０．２〜１．５％、Ｚｒ
０．２％以下、Ｈｆ０．７〜５％、Ｃ０．０２〜０．５
％、Ｂ０．００２〜０．２％を含有し、残部Ｎｉおよび
不可避不純物からなる組成を有することを特徴とする、
高温強度、高温耐酸化性および高温耐食性に優れたＮｉ
基耐熱合金およびそのＮｉ基耐熱合金からなるガスター
ビン翼として用いられることが記載されている。For example, Japanese Examined Patent Publication No. 1-59344 discloses that, by weight, Cr 7 to 13%, Co 35% or less, and Mo.
8% or less, Nb 3% or less, W 14% or less, Ta 6% or less, Al 4 to 7%, Ti 0.5 to 6% (however, Al +
Ti 6.5 to 10.5%), V 0.2 to 1.5%, Zr
0.2% or less, Hf 0.7 to 5%, C 0.02 to 0.5
%, B 0.002 to 0.2%, and a composition comprising the balance Ni and unavoidable impurities.
Ni with excellent high temperature strength, high temperature oxidation resistance and high temperature corrosion resistance
It is described to be used as a gas turbine blade made of a base heat resistant alloy and its Ni base heat resistant alloy.
【０００４】また、米国特許第３４５９５４５号公報に
は、重量％で、Ｃｒ１５〜１８％、Ｃｏ８〜１１％、Ｍ
ｏ０．７５〜２．２％、Ｗ１．８〜３％、Ｔａ１〜３
％、Ａｌ３〜４％、Ｔｉ３〜４％（ただし、Ａｌ＋Ｔｉ
７．５％以下）、Ｚｒ０．０１〜０．２％、Ｂ０．０１
〜０．０５％を含有し、残部Ｎｉおよび不可避不純物か
らなる組成を有することを特徴とするＮｉ基耐熱合金お
よびそのＮｉ基耐熱合金からなるガスタービン翼として
用いられることが記載されている。In US Pat. No. 3,459,545, Cr is 15 to 18%, Co is 8 to 11%, and M is M.
o0.75 to 2.2%, W1.8 to 3%, Ta1 to 3
%, Al3-4%, Ti3-4% (however, Al + Ti
7.5% or less), Zr0.01 to 0.2%, B0.01
It is described that it is used as a gas turbine blade made of a Ni-base heat-resistant alloy and its Ni-base heat-resistant alloy, characterized in that it has a composition of ˜0.05% and the balance is Ni and unavoidable impurities.
【０００５】Ｎｉ基耐熱合金製高温部品であるガスター
ビン翼に亀裂、欠けや酸化減肉などの損傷が発生した場
合、通常、ガスタービン翼と同一組成からなる溶加材で
損傷部を溶接補修を行うか、異なる組成のろう材を用い
てろう付け補修を行うか、新ガスタービン翼と交換する
ことが行われる。When a gas turbine blade, which is a high-temperature Ni-base heat-resistant alloy component, is damaged, such as cracks, chips, or oxidation thinning, the damaged portion is usually repaired by welding with a filler material having the same composition as the gas turbine blade. Or a braze repair using a brazing material having a different composition, or replacement with a new gas turbine blade.
【０００６】[0006]
【発明が解決しようとする課題】しかしながら、Ｎｉ基
耐熱合金のγ’相の量が多くなると高温強度は高くなる
が、靭性は低下し高温割れ感受性が高くなる。したがっ
て、γ’相の量が多い前述したガスタービン翼材のＮｉ
基耐熱合金と同一組成の溶加材を用いて溶接補修した場
合、溶接金属は高温から急速に凝固するために高温割れ
を生じる問題があった。高温割れを心配して高温強度を
犠牲にして溶接性の良い溶加材を用いて溶接補修した場
合やガスタービン翼より融点の低い組成のろう材を用い
てろう付け補修を行った場合、高温環境において溶接金
属やろう付け部の強度が低く、ガスタービン翼母材の特
性が発揮できない問題があった。損傷部を度々補修する
代わりに、新ガスタービン翼と交換するやり方がある
が、ガスタービン翼は非常に高価であり、部分的に損傷
が発生したガスタービン翼を新ガスタービン翼で交換す
るのは経済的に問題がある。However, when the amount of the γ'phase of the Ni-base heat-resistant alloy increases, the high temperature strength increases, but the toughness decreases and the hot cracking susceptibility increases. Therefore, the amount of the γ'phase is large, the Ni of the gas turbine blade material described above is used.
When welding repair is performed using a filler material having the same composition as the base heat-resistant alloy, the weld metal rapidly solidifies from a high temperature, causing a problem of hot cracking. If you are worried about hot cracking and sacrificing high temperature strength to repair by welding using a filler material with good weldability or brazing repair using a brazing material with a composition lower than the melting point of the gas turbine blade, In the environment, the strength of the weld metal and the brazed part was low, and there was a problem that the characteristics of the gas turbine blade base material could not be exhibited. Although there is a method of replacing the damaged part with new gas turbine blades instead of frequently repairing it, gas turbine blades are very expensive, and partially damaged gas turbine blades are replaced with new gas turbine blades. Is financially problematic.
【０００７】本発明は、このような問題点を解消するた
めになされたもので、耐熱合金製であって、溶解鋳造材
からなる高温部品基体と、高温割れがなく基体と同レベ
ルの優れた高温強度の焼結材からなる健全な高温部品補
修部を有し、高温部品基体と高温部品補修部とが冶金的
に接合されている耐熱合金製補修高温部品の提供を目的
とする。また、高温部品であるＮｉ基耐熱合金製補修ガ
スタービン翼であって、ガスタービン翼基体と補修部が
同一組成のＮｉ基耐熱合金であるＮｉ基耐熱合金製補修
ガスタービン翼の提供を目的とする。また、これらＮｉ
基耐熱合金製補修高温部品とガスタービン翼の補修方法
の提供を目的とする。The present invention has been made in order to solve the above problems, and it is made of a heat-resistant alloy and has a high-temperature component base made of a melt-cast material, and has the same level of high-temperature cracking as the base. An object of the present invention is to provide a heat resistant alloy repair high temperature part having a sound high temperature part repair part made of a sintered material of high temperature strength, and a high temperature part base and a high temperature part repair part being metallurgically joined. Another object of the present invention is to provide a repair gas turbine blade made of a Ni-base heat-resistant alloy, which is a high temperature component, and a repair gas turbine blade made of a Ni-base heat-resistant alloy, which is a Ni-base heat-resistant alloy having the same composition as the gas turbine blade base body. To do. In addition, these Ni
An object of the present invention is to provide a repair method for a base heat resistant alloy repairing high temperature component and a gas turbine blade.
【０００８】[0008]
【課題を解決するための手段】本発明者らは、耐熱合金
製高温部品の損傷部の補修のためには、高温部品の補修
部を高温部品の基体と同一組成の耐熱合金の材料で構成
することが重要であり、その補修手段として放電プラズ
マ焼結法を適用することに着目し、高温割れがなく、高
温強度を有する耐熱合金製補修高温部品とその補修方法
を発明するに至った。In order to repair a damaged part of a high temperature component made of a heat resistant alloy, the present inventors constructed the repaired part of the high temperature component with a material of a heat resistant alloy having the same composition as the base of the high temperature component. It was important to pay attention to the application of the spark plasma sintering method as the repairing means, and the inventors have invented a heat resistant alloy repairing high temperature component having no high temperature cracking and high temperature strength, and a repairing method thereof.
【０００９】本発明はかかる知見に基づいてなされたも
のであって、耐熱合金製補修高温部品であって、溶解鋳
造材からなる高温部品基体と焼結材からなる高温部品補
修部（ａ）とを有し、前記高温部品基体と前記高温部品
補修部（ａ）とが冶金的に接合されていることを特徴と
する耐熱合金製補修高温部品である。また本発明は、耐
熱合金製補修高温部品であって、溶解鋳造材からなる高
温部品の第１基体と、溶解鋳造材からなる高温部品の第
２基体と、焼結材からなる高温部品補修部（ｂ）とを有
し、前記高温部品の第１基体と前記高温部品の第２基体
が前記高温部品補修部（ｂ）を介して冶金的に接合され
ていることを特徴とする耐熱合金製補修高温部品を提供
する。以上の耐熱合金製補修高温部品において、前記基
体と前記高温部品補修部（ａ）、または前記第１基体、
前記第２基体および前記高温部品補修部（ｂ）が同一組
成のＮｉ基耐熱合金とすることができる。また、前記耐
熱合金としては析出強化型、酸化物分散強化型等の種々
のＮｉ基耐熱合金を適用することができる。また、以上
の耐熱合金製補修高温部品は、Ｎｉ基耐熱合金に限ら
ず、Ｃｏ基耐熱合金、その他の耐熱合金に適用すること
もできる。The present invention has been made on the basis of the above findings, and is a heat resistant alloy repairing high temperature component comprising a high temperature component base made of a melt-cast material and a high temperature component repairing part (a) made of a sintered material. And a high temperature component base and the high temperature component repair part (a) are metallurgically joined together. Further, the present invention is a heat resistant alloy repairing high temperature component, wherein a first base body of a high temperature component made of a melt cast material, a second base body of a high temperature component made of a melt cast material, and a high temperature component repairing part made of a sintered material. (B), wherein the first base body of the high temperature component and the second base body of the high temperature component are metallurgically joined via the high temperature component repairing portion (b). Provide repair high temperature parts. In the above repair high temperature component made of heat resistant alloy, the base and the high temperature component repair part (a), or the first base,
The second base and the high temperature component repair part (b) may be made of a Ni-base heat resistant alloy having the same composition. As the heat resistant alloy, various Ni-based heat resistant alloys such as precipitation strengthening type and oxide dispersion strengthening type can be applied. Further, the above-mentioned heat-resistant alloy repair high-temperature component can be applied not only to Ni-based heat-resistant alloys but also to Co-based heat-resistant alloys and other heat-resistant alloys.
【００１０】本発明が対象とする具体的な用途の１つと
してガスタービン翼がある。したがって本発明は、Ｎｉ
基耐熱合金から構成され、溶解鋳造材からなるガスター
ビン翼基体と焼結材からなるガスタービン翼補修部
（ａ）を有し、前記ガスタービン翼基体と前記ガスター
ビン翼補修部（ａ）とが冶金的に接合されていることを
特徴とするＮｉ基耐熱合金製補修ガスタービン翼を提供
する。さらに本発明は、Ｎｉ基耐熱合金製であって、溶
解鋳造材からなるガスタービン翼の第１基体と、溶解鋳
造材からなるガスタービン翼の第２基体と、焼結材から
なるガスタービン翼補修部（ｂ）とを有し、前記ガスタ
ービン翼の第１基体と前記ガスタービン翼の第２基体が
前記ガスタービン翼補修部を介して冶金的に接合されて
いることを特徴とするＮｉ基耐熱合金製補修ガスタービ
ン翼をも提供する。以上のＮｉ基耐熱合金製補修ガスタ
ービン翼においても、前記基体と前記ガスタービン翼補
修部（ａ）、または前記第１基体、前記第２基体および
前記ガスタービン翼補修部（ｂ）が同一組成のＮｉ基耐
熱合金であることが望ましい。また、前記Ｎｉ基耐熱合
金としては、析出強化型Ｎｉ基耐熱合金または酸化物分
散強化型Ｎｉ基耐熱合金を用いることができる。One of the specific applications targeted by the present invention is a gas turbine blade. Therefore, the present invention
A gas turbine blade base made of a melt-cast material and a gas turbine blade repair part (a) made of a sintered material, which is made of a base heat-resistant alloy; and the gas turbine blade base and the gas turbine blade repair part (a). There is provided a repair gas turbine blade made of a Ni-base heat-resistant alloy characterized by being metallurgically bonded to each other. Further, the present invention relates to a gas turbine blade made of a Ni-base heat-resistant alloy, the first base body of a gas turbine blade made of a melt-cast material, the second base body of a gas turbine blade made of a melt-cast material, and a gas turbine blade made of a sintered material. And a repair part (b), wherein the first base body of the gas turbine blade and the second base body of the gas turbine blade are metallurgically bonded via the gas turbine blade repair part. We also provide repair gas turbine blades made of base heat resistant alloy. Also in the above Ni-based heat-resistant alloy repair gas turbine blade, the base and the gas turbine blade repair section (a), or the first base, the second base, and the gas turbine blade repair section (b) have the same composition. It is desirable that the above Ni-based heat-resistant alloy is used. Further, as the Ni-based heat resistant alloy, a precipitation strengthened Ni-based heat resistant alloy or an oxide dispersion strengthened Ni-based heat resistant alloy can be used.
【００１１】以上の耐熱合金製補修高温部品を得るため
の好適な方法を本発明は提供する。すなわち本発明の耐
熱合金製高温部品の補修方法は、耐熱合金製高温部品の
基体の損傷部に耐熱合金製粉末を収容した補修部材を装
填する工程と、前記補修部材を前記基体の損傷部に加圧
しながら放電プラズマ焼結して前記耐熱合金製粉末を焼
結すると同時に前記基体の損傷部と焼結された補修部材
とを冶金的に接合する工程と、得られた接合体を熱処理
する工程と、を備えたことを特徴とする。また本発明
は、耐熱合金製高温部品の基体の損傷部を機械的に除去
して加工面を形成する工程と、耐熱合金製粉末を収容し
た補修部材を前記基体の加工面に装填する工程と、前記
補修部材を前記基体の加工面に加圧しながら放電プラズ
マ焼結して前記耐熱合金製粉末を焼結すると同時に前記
基体の加工面と焼結された補修部材とを冶金的に接合す
る工程と、得られた接合体を熱処理する工程と、を備え
たことを特徴とする耐熱合金製高温部品の補修方法を提
供する。The present invention provides a suitable method for obtaining the above-mentioned high temperature repair parts made of heat resistant alloy. That is, the method for repairing a heat-resistant alloy high-temperature component of the present invention comprises a step of loading a repair member containing a heat-resistant alloy powder into a damaged portion of the base of the heat-resistant alloy high-temperature component, and the repair member to the damaged portion of the base. A step of metallurgically joining the damaged part of the base body and the sintered repair member at the same time as sintering the heat-resistant alloy powder by performing discharge plasma sintering while pressurizing, and a step of heat-treating the obtained joined body. And are provided. Further, the present invention comprises a step of mechanically removing a damaged portion of a base body of a heat resistant alloy high temperature part to form a processed surface, and a step of loading a repair member containing a heat resistant alloy powder on the processed surface of the base body. A step of sintering the heat-resistant alloy powder by performing discharge plasma sintering while pressurizing the repair member to the machined surface of the base body, and at the same time metallurgically joining the machined surface of the base body and the sintered repair member. And a step of heat-treating the obtained bonded body, which provides a method for repairing a high-temperature component made of a heat-resistant alloy.
【００１２】前述したＮｉ基耐熱合金製補修ガスタービ
ン翼を得るための好適な方法を本発明は提供する。すな
わち本発明のＮｉ基耐熱合金製ガスタービン翼の補修方
法は、Ｎｉ基耐熱合金製ガスタービン翼の基体の損傷部
にＮｉ基耐熱合金製粉末を収容した補修部材を装填する
工程と、前記補修部材を前記基体の損傷部に加圧しなが
ら放電プラズマ焼結して前記Ｎｉ基耐熱合金製粉末を焼
結すると同時に前記基体の損傷部と焼結された補修部材
とを冶金的に接合する工程と、得られた接合体を熱処理
する工程と、を備えることを特徴とする。また本発明
は、Ｎｉ基耐熱合金製ガスタービン翼の基体の損傷部を
機械的に除去して加工面を形成する工程と、Ｎｉ基耐熱
合金製粉末を収容した補修部材を前記基体の加工面に装
填する工程と、前記補修部材を前記基体の加工面に加圧
しながら放電プラズマ焼結して前記Ｎｉ基耐熱合金製粉
末を焼結すると同時に前記基体の加工面と焼結された補
修部材とを冶金的に接合する工程と、得られた接合体を
熱処理する工程と、を備えることを特徴とするＮｉ基耐
熱合金製ガスタービン翼の補修方法も提供する。さらに
本発明は、動翼基体に損傷部を有する溶解鋳造材からな
るＮｉ基耐熱合金製ガスタービン動翼の遮熱コーティン
グ層を除去する工程と、下地コーティング層を剥離する
工程と、前記損傷部を機械的に除去して加工面を形成す
る工程と、カーボンシートで前記溶解鋳造材からなるＮ
ｉ基耐熱合金製ガスタービン動翼の基体と同一組成のＮ
ｉ基耐熱合金製粉末を収容した補修部材を前記基体の加
工面に装填する工程と、前記補修部材を前記基体の加工
面に加圧しながら放電プラズマ焼結して前記Ｎｉ基耐熱
合金製粉末を焼結すると同時に前記基体の加工面と焼結
された補修部材とを冶金的に接合する工程と、得られた
接合体を熱処理する工程と、前記熱処理された接合体に
下地コーティング層および遮熱コーティング層を順次被
覆する工程と、を備えることを特徴とするＮｉ基耐熱合
金製ガスタービン動翼の補修方法をも提供する。The present invention provides a suitable method for obtaining the aforementioned Ni-base heat resistant alloy repair gas turbine blade. That is, a method for repairing a Ni-based heat-resistant alloy gas turbine blade according to the present invention comprises a step of loading a repair member containing a Ni-based heat-resistant alloy powder on a damaged portion of a base of a Ni-based heat-resistant alloy gas turbine blade, and the above-mentioned repair. A step of sintering the Ni-base heat-resistant alloy powder by performing discharge plasma sintering while applying pressure to the damaged portion of the base body, and at the same time metallurgically joining the damaged portion of the base body and the sintered repair member. And a step of heat-treating the obtained joined body. The present invention also provides a step of mechanically removing a damaged portion of a base body of a Ni-base heat-resistant alloy gas turbine blade to form a machined surface, and a repair member containing a Ni-base heat-resistant alloy powder for providing a machined surface of the base body. And a step of loading the repair member onto the machined surface of the base body to sinter the Ni-base heat-resistant alloy powder while sintering the Ni-based heat-resistant alloy powder, and at the same time, the repaired member sintered to the machined surface of the base body. There is also provided a method of repairing a gas turbine blade made of a Ni-base heat-resistant alloy, the method including: a step of metallurgically joining the article and a step of heat-treating the obtained joined body. Further, the present invention provides a step of removing the heat barrier coating layer of the Ni-based heat-resistant alloy gas turbine blade made of a melt-cast material having a damaged portion on the moving blade base body, a step of peeling the underlying coating layer, and the damaged portion. To form a machined surface by mechanically removing the carbon,
N-based alloy having the same composition as the base body of the i-base heat-resistant alloy gas turbine blade
a step of loading a repair member containing an i-base heat-resistant alloy powder on the machined surface of the base body; and discharge plasma sintering while pressing the repair member on the machined surface of the base body to produce the Ni-base heat-resistant alloy powder. A step of metallurgically joining the processed surface of the base body and the sintered repair member at the same time as sintering, a step of heat-treating the obtained joined body, an undercoating layer and a heat shield on the heat-treated joined body. Also provided is a method of repairing a gas turbine blade made of a Ni-base heat-resistant alloy, which comprises the step of sequentially coating coating layers.
【００１３】[0013]
【発明の実施の形態】以下、本発明の耐熱合金製補修高
温部品およびその補修方法の実施の形態について、添付
図面を参照して説明する。なお、この実施の形態により
本発明が限定されるものではない。BEST MODE FOR CARRYING OUT THE INVENTION Embodiments of a heat resistant alloy repairing high temperature component and a repairing method thereof according to the present invention will be described below with reference to the accompanying drawings. The present invention is not limited to this embodiment.
【００１４】（実施の形態１）図１はＮｉ基耐熱合金製
高温部品であるガスタービン翼１０について、遠心力が
かかり損傷し易い部位である翼上端に一部欠けが生じた
場合の補修ガスタービン翼の構成を示す斜視図である。
ガスタービン翼１０の基体１１である母材としては、高
温強度の高い溶解鋳造材である析出強化型Ｎｉ基耐熱合
金が好ましい。図４の斜視図に示す如くガスタービン翼
１０の基体１１に欠けＡなどの損傷が発生した場合、損
傷部に例えばカーボンシート（図示せず）でＮｉ基耐熱
合金製粉末を収容した補修部材を配置する。なお、カー
ボンシートはあくまで一例であり、電極からの放電電流
が通過し得るものであればよい。(Embodiment 1) FIG. 1 shows a repair gas for a gas turbine blade 10 which is a high temperature component made of a Ni-base heat-resistant alloy when a part of the upper end of the blade, which is a portion which is easily damaged by centrifugal force, is damaged. It is a perspective view which shows the structure of a turbine blade.
The base material of the base 11 of the gas turbine blade 10 is preferably a precipitation-strengthened Ni-based heat-resistant alloy which is a melt-cast material having high strength at high temperature. As shown in the perspective view of FIG. 4, when the base body 11 of the gas turbine blade 10 is damaged such as a chip A, a repair member containing a Ni-based heat-resistant alloy powder in a carbon sheet (not shown) is provided in the damaged portion. Deploy. Note that the carbon sheet is just an example, and may be any sheet that allows the discharge current from the electrode to pass through.
【００１５】この補修部材を基体１１の損傷部に加圧し
ながら押し付けた電極（図示せず）から放電電流を印加
して放電プラズマ焼結を行い、Ｎｉ基耐熱合金製粉末を
焼結すると同時に基体１１の損傷部と焼結された補修部
材とが接合されて、溶解鋳造材からなるガスタービン翼
基体と焼結材からなるガスタービン翼補修部とが冶金的
に接合されたＮｉ基耐熱合金製補修ガスタービン翼が得
られる。補修部材は大電流パルス通電時の放電による高
熱とジュール熱により、極めて熱効率よく緻密化焼結さ
れている。なお、損傷部の酸化層を除去したり、補修部
材を装填し易いように、欠けＡの損傷部を機械的に除去
して加工面を形成するようにしてもよい。A discharge current is applied from an electrode (not shown) pressed against the damaged portion of the base 11 while pressing the repair member to perform spark plasma sintering to sinter the Ni-base heat-resistant alloy powder and at the same time to the base. The Ni-based heat-resistant alloy, in which the damaged portion 11 and the sintered repair member are joined, and the gas turbine blade base body made of the melt-cast material and the gas turbine blade repair portion made of the sintered material are metallurgically joined A repair gas turbine blade is obtained. The repair member is densified and sintered with extremely high thermal efficiency due to the high heat and Joule heat generated by the discharge when a large current pulse is applied. The damaged portion of the chip A may be mechanically removed to form the processed surface so that the oxide layer of the damaged portion can be easily removed or the repair member can be easily loaded.
【００１６】（実施の形態２）図２はＮｉ基耐熱合金製
高温部品であるガスタービン翼１０について、遠心力が
かかり損傷し易い部位である翼上端に大きな欠けの損傷
が生じた場合の補修ガスタービン翼の構成を示す斜視図
である。損傷部が大きい場合には、図１のように損傷部
全体に補修部材１２を充填するのではなくて、ガスター
ビン翼１０の損傷部の一部と同一形状のクーポン（溶解
鋳造材）を用意して、ガスタービン翼１０の第２基体１
１１として利用して、装填する補修部材１２の量を少な
くし、焼結効率を高めることができる。(Embodiment 2) FIG. 2 shows repair of a gas turbine blade 10 which is a high temperature component made of a Ni-base heat-resistant alloy, when a large chip damage is generated at the blade upper end, which is a portion easily damaged by centrifugal force. It is a perspective view which shows the structure of a gas turbine blade. If the damaged portion is large, instead of filling the entire damaged portion with the repair member 12 as shown in FIG. 1, prepare a coupon (melt casting material) having the same shape as a part of the damaged portion of the gas turbine blade 10. Then, the second base body 1 of the gas turbine blade 10
It can be used as 11 to reduce the amount of the repair member 12 to be loaded and improve the sintering efficiency.
【００１７】ガスタービン翼１０の第１基体１１０の損
傷部にカーボンシート（図示せず）でＮｉ基耐熱合金製
粉末を収容した補修部材１２とガスタービン翼１０の第
２基体（クーポン）１１１を配置し、ガスタービン翼１
０の第２基体１１１を押し付けて、補修部材１２をガス
タービン翼１０の第１基体１１０の損傷部に加圧しなが
ら電極から放電電流を印加して放電プラズマ焼結を行
い、Ｎｉ基耐熱合金製粉末を焼結すると同時に基体１１
の損傷部と焼結された補修部材１２とが接合されて、溶
解鋳造材からなるガスタービン翼１０の第１基体１１０
と第２基体１１１が焼結材からなるガスタービン翼補修
部を介して冶金的に接合されたＮｉ基耐熱合金製補修ガ
スタービン翼が得られる。なお、補修部材を装填し易い
ように、損傷部を機械的に除去して加工面を形成するよ
うにしてもよい。In the damaged portion of the first base 110 of the gas turbine blade 10, a repair member 12 containing a Ni-base heat-resistant alloy powder in a carbon sheet (not shown) and a second base (coupon) 111 of the gas turbine blade 10 are provided. Place the gas turbine blade 1
No. 2 base 111 is pressed to press the repair member 12 against the damaged portion of the first base 110 of the gas turbine blade 10 to apply a discharge current from the electrode to perform spark plasma sintering, At the same time as sintering the powder, the base 11
Of the gas turbine blade 10 made of a melt-cast material, in which the damaged portion of the gas turbine and the repair member 12 that has been sintered are joined together.
A repair gas turbine blade made of a Ni-base heat-resistant alloy, in which the second base 111 is metallurgically joined via the gas turbine blade repair section made of a sintered material, is obtained. In addition, the damaged portion may be mechanically removed to form the processed surface so that the repair member can be easily loaded.
【００１８】（実施の形態３）図３はＮｉ基耐熱合金製
高温部品であるガスタービン翼１０について、翼の頂部
に亀裂などの損傷が生じた場合の補修ガスタービン翼の
構成を示す斜視図である。亀裂が生じた翼の頂部の損傷
部を一度機械的に削除してガスタービン翼１０の基体１
１に加工面を形成し、加工面の上に薄い翼チップシンニ
ング部を形成するようにカーボンシート（図示せず）で
Ｎｉ基耐熱合金製粉末を収容した補修部材１２を装填
し、この補修部材１２を基体１１に加圧しながら電極か
ら放電電流を印加して放電プラズマ焼結を行い、Ｎｉ基
耐熱合金製粉末を焼結すると同時に基体１１の加工面と
焼結された補修部材１２とが接合される。(Embodiment 3) FIG. 3 is a perspective view showing the structure of a repaired gas turbine blade of a gas turbine blade 10 which is a high temperature component made of a Ni-base heat-resistant alloy when damage such as cracks occurs at the top of the blade. Is. The damaged portion at the top of the blade where the crack has occurred is mechanically removed once, and the base body 1 of the gas turbine blade 10 is removed.
1 is formed with a processed surface, and a repair member 12 containing Ni-base heat-resistant alloy powder is loaded on a carbon sheet (not shown) so as to form a thin blade tip thinning portion on the processed surface. A discharge current is applied from an electrode while pressurizing 12 to the substrate 11, and discharge plasma sintering is performed to sinter the Ni-based heat-resistant alloy powder, and at the same time, the machined surface of the substrate 11 and the sintered repair member 12 are joined. To be done.
【００１９】以上により、溶解鋳造材からなるガスター
ビン翼基体と焼結材からなるガスタービン翼補修部（翼
チップシンニング部）とが冶金的に接合されたＮｉ基耐
熱合金製補修ガスタービン翼が得られる。前述した実施
の形態において、ガスタービン翼１０の基体１１、第１
基体１１０、第２基体１１１と補修部材１２が同一組成
のＮｉ基耐熱合金であることが好ましく、また、析出強
化型Ｎｉ基耐熱合金であることが好ましい。さらに、補
修部材１２として用いる粉末は焼結により収縮して緻密
化するために、元の翼形状より大きめに充填するのが好
ましい。As described above, a repair gas turbine blade made of a Ni-base heat-resistant alloy in which a gas turbine blade base body made of a melt-cast material and a gas turbine blade repair portion (blade tip thinning portion) made of a sintered material are metallurgically joined together is provided. can get. In the above-described embodiment, the base 11 of the gas turbine blade 10 and the first
The base 110, the second base 111, and the repair member 12 are preferably Ni-based heat-resistant alloys having the same composition, and are preferably precipitation-strengthened Ni-based heat-resistant alloys. Further, since the powder used as the repair member 12 shrinks and becomes densified by sintering, it is preferable to fill the powder in a size larger than the original blade shape.
【００２０】本発明のＮｉ基耐熱合金製補修高温部品お
よびその補修方法について、Ｎｉ基耐熱合金製ガスター
ビン動翼の具体的な実施例を参照してさらに詳述する。
図４に示すような小さな欠けＡの損傷部を生じたＮｉ基
耐熱合金製ガスタービン動翼について、放電プラズマ焼
結法を適用して図１に示す構成のＮｉ基耐熱合金製補修
ガスタービン動翼を作製した。補修処理をする前処理と
して、損傷部を有するガスタービン動翼の遮熱コーティ
ング層を除去し、その後溶体化の熱処理をした後、下地
コーティング層を剥離した。The Ni-based heat-resistant alloy repairing high temperature component and the repairing method of the present invention will be described in more detail with reference to specific examples of Ni-base heat-resistant alloy gas turbine rotor blades.
A Ni-based heat-resistant alloy repaired gas turbine blade having the configuration shown in FIG. 1 is formed by applying the spark plasma sintering method to a Ni-base heat-resistant alloy gas turbine blade having a small damaged portion A as shown in FIG. Wings were made. As a pretreatment for the repair treatment, the heat shield coating layer of the gas turbine rotor blade having a damaged portion was removed, and after heat treatment for solution treatment, the undercoating layer was peeled off.
【００２１】溶解鋳造材であるガスタービン動翼の基体
１１と補修部材１２の粉末は、同一組成のＮｉ基耐熱合
金であり、析出強化型のＩＮ-７３８ＬＣ（スペシャル
メタル社の商標）を用いた。組成の例を表１に示す。補
修部材１２として、平均粒径が２２μｍ、最大粒径が４
０μｍのＩＮ-７３８ＬＣ製粉末を用いた。補修用の粉
末は損傷部への充填時に形状を維持できるように、０．
２ｍｍ厚のカーボンシートに収容して使用した。The powder of the base 11 and the repair member 12 of the gas turbine blade, which is a melt-cast material, is a Ni-base heat-resistant alloy having the same composition, and precipitation strengthening type IN-738LC (trademark of Special Metal Co., Ltd.) was used. . An example of the composition is shown in Table 1. The repair member 12 has an average particle size of 22 μm and a maximum particle size of 4
A 0 μm IN-738LC powder was used. The powder for repair is 0. so that the shape can be maintained when the damaged part is filled.
It was housed in a 2 mm thick carbon sheet and used.
【００２２】[0022]
【表１】 [Table 1]
【００２３】損傷部を機械的に削除したガスタービン動
翼の基体１１に、カーボンシートでＩＮ-７３８ＬＣ粉
末を収容した補修部材１２を配置し、この補修部材１２
を基体１１の加工面に、表２に示すように３０〜９０Ｍ
Ｐａで加圧しながら押し付けた電極から放電電流を印加
して焼結部が１０００〜１１００℃になるようにした。
放電プラズマ焼結を行い、ＩＮ-７３８ＬＣ粉末を焼結
すると同時に溶解鋳造材からなる基体１１と焼結された
補修部材１２とが接合されて、溶解鋳造材からなるガス
タービン動翼基体と焼結材からなるガスタービン動翼補
修部とが冶金的に接合されたＩＮ-７３８ＬＣのＮｉ基
耐熱合金製補修ガスタービン動翼が得られた。次に、得
られた接合体を後加工により所定の形状に加工し、１１
２０℃、２時間溶体化処理後、８４３℃、２４時間時効
処理する熱処理を施し、その後、耐熱性を高めるために
基体の母材１１とセラミック系の遮熱コーティング層の
間の熱膨張係数を有し、基体１１の母材より高温耐食耐
酸化性に優れた特性を有するＣｏＮｉＣｒＡｌＹ合金の
下地コーティング層を低圧プラズマ溶射で被覆し、続い
て、熱伝導性が低く、熱膨張が大きく、かつ高温で安定
性に優れた部分安定化ＺｒＯ2の遮熱コーティング層を
大気プラズマ溶射で被覆した。A repair member 12 containing a carbon sheet containing IN-738LC powder is arranged on a base 11 of a gas turbine blade in which a damaged portion is mechanically removed.
On the processed surface of the substrate 11 as shown in Table 2
A discharge current was applied from the electrode pressed while applying pressure at Pa so that the temperature of the sintered portion was 1000 to 1100 ° C.
The spark plasma sintering is performed to sinter the IN-738LC powder, and at the same time, the base body 11 made of the melt cast material and the sintered repair member 12 are joined, and the base body 11 made of the melt cast material is sintered. A repair gas turbine blade made of a Ni-base heat-resistant alloy of IN-738LC, which was metallurgically bonded to a gas turbine blade repair section made of a material, was obtained. Next, the obtained joined body is processed into a predetermined shape by post-processing, and 11
After solution treatment at 20 ° C. for 2 hours, heat treatment of aging treatment at 843 ° C. for 24 hours is performed, and thereafter, in order to enhance heat resistance, the coefficient of thermal expansion between the base material 11 of the substrate and the ceramic thermal barrier coating layer is adjusted. The base coating layer of CoNiCrAlY alloy, which has a higher temperature corrosion resistance and oxidation resistance than the base material of the base 11, is coated by low pressure plasma spraying, and subsequently has low thermal conductivity, large thermal expansion, and high temperature. The thermal barrier coating layer of partially stabilized ZrO 2 having excellent stability was coated by atmospheric plasma spraying.
【００２４】次に、図５に示す形状の試験片を上記で得
られたガスタービン動翼から切り出して、高温引張り試
験を行った。なお、切り出し部分は溶解鋳造材（母材）
と焼結材との境界部分であり、また試験温度は、８５０
℃とした。試験結果を表２に示す。接合温度が１０００
℃のＮｏ．１は、母材の２６．１％の引張り強さしか得
られない。また接合温度１０５０℃のＮｏ．２も母材の
３３．１％と引張り強さは低い。なお、母材引張り強さ
とは、前述した熱処理を施した溶解鋳造材の引張り強さ
である。Next, a test piece having the shape shown in FIG. 5 was cut out from the gas turbine rotor blade obtained above, and a high temperature tensile test was conducted. The cut-out part is a melt cast material (base material)
And the sintered material, and the test temperature is 850
℃ was made. The test results are shown in Table 2. Joining temperature is 1000
C. No. No. 1 can only obtain a tensile strength of 26.1% of the base material. In addition, No. 2 also has a low tensile strength of 33.1% of the base material. The base material tensile strength is the tensile strength of the melt-cast material that has been subjected to the heat treatment described above.
【００２５】[0025]
【表２】 [Table 2]
【００２６】接合温度が１１００℃の場合は、加圧力が
３０ＭＰａでは、接合時間が９０分までは、Ｎｏ．３〜
６に示すように母材引張り強さの８０％以下の強度しか
得ることができないが、接合時間を２４０分とすること
により、Ｎｏ．７に示すように母材引張り強さの８０％
を超える。さらに、加圧力を６０及び９０ＭＰａと向上
させると、接合時間は９０分でＮｏ．８および９に示す
ように母材引張り強さの８０％以上を満足した。表２の
Ｎｏ．１、６及び７の顕微鏡写真をそれぞれ図６、７及
び図８に示す。なお、図６〜図８において、左半分が母
材、右半分が焼結材である。図６（Ｎｏ．１）及び図７
（Ｎｏ．６）については、接合条件が適切でないため、
焼結組織が充填していないことがわかる。また、適性条
件で施工された図８（Ｎｏ．７）の場合は、焼結組織は
緻密化している。また、溶接補修時に生じる高温割れも
発生していない。放電プラズマ焼結法を適用した本発明
によれば、ホットプレス法や熱間静水圧法などの他の焼
結法に比べ、設備費用が安く、省スペースで、焼結スピ
ードも早く、短時間で緻密化した健全な補修部を形成で
きた。なお、以上では特定組成のＮｉ基耐熱合金の例に
ついて説明したが、本発明は上記組成のＮｉ基耐熱合金
に限定されず、例えばＣｏ基耐熱合金に適用できること
は言うまでもない。また、用途もタービン動翼に限定さ
れるものではなく、各種の耐熱合金製部品に適用できる
ことは言うまでもない。When the joining temperature is 1100 ° C. and the joining pressure is 30 MPa, the joining time is 90 minutes or less. 3-
As shown in Fig. 6, only 80% or less of the tensile strength of the base material can be obtained, but by setting the joining time to 240 minutes, No. 80% of the tensile strength of the base metal as shown in 7
Over. Further, when the applied pressure was increased to 60 and 90 MPa, the joining time was 90 minutes and the welding time was No. As shown in 8 and 9, 80% or more of the tensile strength of the base material was satisfied. No. of Table 2 Micrographs of 1, 6 and 7 are shown in FIGS. 6, 7 and 8, respectively. 6 to 8, the left half is the base material and the right half is the sintered material. FIG. 6 (No. 1) and FIG.
Regarding (No. 6), since the joining conditions are not appropriate,
It can be seen that the sintered structure is not filled. Further, in the case of FIG. 8 (No. 7) which was constructed under the appropriate conditions, the sintered structure is densified. In addition, hot cracking that occurs during welding repair has not occurred. According to the present invention to which the spark plasma sintering method is applied, the equipment cost is low, the space is small, the sintering speed is fast, and the time is short as compared with other sintering methods such as the hot pressing method and the hot isostatic pressing method. It was possible to form a dense and sound repair part. Although an example of a Ni-based heat-resistant alloy having a specific composition has been described above, it goes without saying that the present invention is not limited to the Ni-based heat-resistant alloy having the above composition, and can be applied to, for example, a Co-based heat-resistant alloy. Needless to say, the application is not limited to the turbine rotor blade, and can be applied to various heat resistant alloy parts.
【００２７】[0027]
【発明の効果】以上説明したように、本発明によれば、
耐熱合金製高温部品に損傷が発生した場合、補修部を基
体と同一組成の焼結材からなる耐熱合金で冶金的に接合
した耐熱合金製補修高温部品を得ることができる。ま
た、溶解鋳造材からなるＮｉ基耐熱合金製の基体と、高
温割れがなく、基体と同レベルの優れた高温強度の焼結
材からなる健全な補修部を有するＮｉ基耐熱合金製補修
ガスタービン動翼を新翼と交換する場合に比べて低コス
トで提供できる。また、補修部材の焼結に放電プラズマ
焼結法を適用することにより、ホットプレスなどの他の
焼結法と比較して、低コストの装置で短時間で緻密化し
た補修部を形成でき、新翼と同レベルの性能を有するＮ
ｉ基耐熱合金製補修ガスタービン動翼を提供できる。As described above, according to the present invention,
When the heat-resistant alloy high-temperature component is damaged, a heat-resistant alloy repaired high-temperature component can be obtained in which the repaired portion is metallurgically bonded with a heat-resistant alloy made of a sintered material having the same composition as the substrate. Further, a Ni-based heat-resistant alloy repair gas turbine having a Ni-base heat-resistant alloy base made of a melt-cast material and a sound repair part made of a sintered material having no high-temperature cracking and the same high-temperature strength as the base. It can be provided at a lower cost than when the moving blade is replaced with a new blade. Further, by applying the spark plasma sintering method to the sintering of the repair member, compared to other sintering methods such as hot pressing, it is possible to form a densified repair portion in a short time with a low-cost device, N with the same level of performance as new wings
It is possible to provide a repair gas turbine blade made of an i-based heat-resistant alloy.
【図１】 本発明にかかる実施の形態１の補修ガスター
ビン翼を示す斜視図である。FIG. 1 is a perspective view showing a repair gas turbine blade of a first embodiment according to the present invention.
【図２】 本発明にかかる実施の形態２の補修ガスター
ビン翼を示す斜視図である。FIG. 2 is a perspective view showing a repair gas turbine blade according to a second embodiment of the present invention.
【図３】 本発明にかかる実施の形態３の補修ガスター
ビン翼を示す斜視図である。FIG. 3 is a perspective view showing a repair gas turbine blade according to a third embodiment of the present invention.
【図４】 翼の一部に欠けなどの損傷が発生したガスタ
ービン翼を示す斜視図である。FIG. 4 is a perspective view showing a gas turbine blade in which damage such as chipping has occurred in a part of the blade.
【図５】 引張り試験を実施したときの試験片形状であ
る。FIG. 5 is a shape of a test piece when a tensile test is performed.
【図６】 表２のＮｏ．１による補修ガスタービン動翼
の基体と補修部の境界部のミクロ組織を示す顕微鏡写真
である。FIG. 6 No. of Table 2 2 is a micrograph showing a microstructure of a boundary portion between a base body and a repaired portion of a repaired gas turbine blade according to No. 1.
【図７】 表２のＮｏ．６による補修ガスタービン動翼
の基体と補修部の境界部のミクロ組織を示す顕微鏡写真
である。7 is a table No. 2 shown in FIG. 6 is a micrograph showing a microstructure of a boundary portion between a base body and a repair portion of a repair gas turbine blade according to No. 6;
【図８】 表２のＮｏ．７による補修ガスタービン動翼
の基体と補修部の境界部のミクロ組織を示す顕微鏡写真
である。FIG. 8 No. of Table 2 9 is a micrograph showing a microstructure of a boundary portion between a base of a repaired gas turbine rotor blade according to No. 7 and a repaired portion.
１０…ガスタービン翼、１１…基体、１２…補修部材、
１１０…第１基体、１１１…第２基体、Ａ…欠け10 ... Gas turbine blade, 11 ... Base, 12 ... Repair member,
110 ... First substrate, 111 ... Second substrate, A ... Chip
───────────────────────────────────────────────────── フロントページの続き (51)Int.Cl.7 識別記号 ＦＩ テーマコート゛(参考） Ｃ２２Ｆ 1/10 Ｃ２２Ｆ 1/10 Ａ Ｆ０１Ｄ 5/28 Ｆ０１Ｄ 5/28 Ｆ０２Ｃ 7/00 Ｆ０２Ｃ 7/00 Ｃ Ｄ // Ｃ２２Ｆ 1/00 ６１１ Ｃ２２Ｆ 1/00 ６１１ ６２７ ６２７ ６２８ ６２８ ６４０ ６４０Ｂ ６５０ ６５０Ａ ６５０Ｃ ６５０Ｄ ６５１ ６５１Ｂ ６８７ ６８７ (72)発明者 上村 好古 兵庫県高砂市荒井町新浜２丁目１番１号 三菱重工業株式会社高砂製作所内 Ｆターム(参考） 3G002 EA04 EA05 EA06 4K018 AA09 BA04 CA00 EA21 FA08 FA21 JA22 KA07 KA12 ─────────────────────────────────────────────────── ─── Continuation of front page (51) Int.Cl. 7 Identification code FI theme code (reference) C22F 1/10 C22F 1/10 A F01D 5/28 F01D 5/28 F02C 7/00 F02C 7/00 C D // C22F 1/00 611 C22F 1/00 611 627 627 628 628 628 640 640B 650 650A 650C 650D 651 651B 687 687 (72) Inventor Uemura Yoshiko Niihama Niihama, Niihama, Takasago, Hyogo Prefecture Takasago Factory F-term (reference) 3G002 EA04 EA05 EA06 4K018 AA09 BA04 CA00 EA21 FA08 FA21 JA22 KA07 KA12
Claims (11)
鋳造材からなる高温部品基体と焼結材からなる高温部品
補修部（ａ）とを有し、前記高温部品基体と前記高温部
品補修部（ａ）とが冶金的に接合されていることを特徴
とする耐熱合金製補修高温部品。1. A repair high temperature component made of a heat resistant alloy, comprising a high temperature component base made of a melt-cast material and a high temperature component repair part (a) made of a sintered material, and the high temperature component base and the high temperature component repair. A heat resistant alloy repairing high temperature component, characterized in that it is metallurgically bonded to the part (a).
鋳造材からなる高温部品の第１基体と、前記溶解鋳造材
からなる高温部品の第２基体と、焼結材からなる高温部
品補修部（ｂ）とを有し、前記高温部品の第１基体と前
記高温部品の第２基体が前記高温部品補修部（ｂ）を介
して冶金的に接合されていることを特徴とする耐熱合金
製補修高温部品。2. A repair high temperature component made of a heat resistant alloy, the first base being a high temperature component made of a melt cast material, the second base being a high temperature component made of the melt cast material, and a high temperature component repair made of a sintered material. Part (b), wherein the first base body of the high temperature component and the second base body of the high temperature component are metallurgically joined via the high temperature component repairing part (b). Manufacturing and repairing high temperature parts.
（ａ）、または前記第１基体、前記第２基体および前記
高温部品補修部（ｂ）が同一組成の耐熱合金であること
を特徴とする請求項１または請求項２に記載の耐熱合金
製補修高温部品。3. The high temperature component base and the high temperature component repair part (a), or the first substrate, the second substrate and the high temperature component repair part (b) are heat-resistant alloys having the same composition. The repair high temperature component made of the heat resistant alloy according to claim 1 or 2.
材からなるガスタービン翼基体と焼結材からなるガスタ
ービン翼補修部（ａ）を有し、前記ガスタービン翼基体
と前記ガスタービン翼補修部（ａ）とが冶金的に接合さ
れていることを特徴とするＮｉ基耐熱合金製補修ガスタ
ービン翼。4. A gas turbine blade base made of a melt-cast material and a gas turbine blade repairing part (a) made of a sintered material, which are made of a Ni-base heat-resistant alloy, and have the gas turbine blade base and the gas turbine blade. A repair gas turbine blade made of a Ni-base heat-resistant alloy, which is metallurgically bonded to the repair part (a).
からなるガスタービン翼の第１基体と、前記溶解鋳造材
からなるガスタービン翼の第２基体と、焼結材からなる
ガスタービン翼補修部（ｂ）とを有し、前記ガスタービ
ン翼の第１基体と前記ガスタービン翼の第２基体が前記
ガスタービン翼補修部（ｂ）を介して冶金的に接合され
ていることを特徴とするＮｉ基耐熱合金製補修ガスター
ビン翼。5. A gas turbine blade made of a Ni-base heat-resistant alloy, the first base body of a gas turbine blade made of a melt-cast material, the second base body of a gas turbine blade made of the melt-cast material, and a gas turbine made of a sintered material. A first base body of the gas turbine blade and a second base body of the gas turbine blade are metallurgically joined via the gas turbine blade repair section (b). A repair gas turbine blade made of Ni-based heat resistant alloy.
ビン翼補修部（ａ）、または前記第１基体、前記第２基
体および前記ガスタービン翼補修部（ｂ）が同一組成の
耐熱合金であることを特徴とする請求項４または請求項
５に記載のＮｉ基耐熱合金製補修ガスタービン翼。6. The heat resistant alloy having the same composition in the gas turbine blade base and the gas turbine blade repair section (a) or in the first base, the second base and the gas turbine blade repair section (b). A repair gas turbine blade made of a Ni-base heat-resistant alloy according to claim 4 or claim 5.
に耐熱合金製粉末を収容した補修部材を装填する工程
と、前記補修部材を前記基体の損傷部に加圧しながら放
電プラズマ焼結して前記耐熱合金製粉末を焼結すると同
時に前記基体の損傷部と焼結された補修部材とを冶金的
に接合する工程と、得られた接合体を熱処理する工程
と、を備えたことを特徴とする耐熱合金製高温部品の補
修方法。7. A step of loading a repairing member containing a powder of heat-resistant alloy into a damaged portion of a base of a heat resistant alloy repairing high temperature component, and performing discharge plasma sintering while pressing the repairing member onto the damaged portion of the base. Sintering the heat-resistant alloy powder at the same time, and metallurgically joining the damaged part of the base body and the sintered repair member, and heat-treating the obtained joined body. Method for repairing high temperature parts made of heat resistant alloy.
を機械的に除去して加工面を形成する工程と、耐熱合金
製粉末を収容した補修部材を前記基体の加工面に装填す
る工程と、前記補修部材を前記基体の加工面に加圧しな
がら放電プラズマ焼結して前記耐熱合金製粉末を焼結す
ると同時に前記基体の加工面と焼結された補修部材とを
冶金的に接合する工程と、前記接合体を熱処理する工程
と、を備えたことを特徴とする耐熱合金製高温部品の補
修方法。8. A step of mechanically removing a damaged portion of a base body of a heat resistant alloy repairing high temperature part to form a machined surface, and a step of loading a repair member containing a heat resistant alloy powder on the machined surface of the base body. And, while pressurizing the repair member to the machined surface of the base body to perform spark plasma sintering to sinter the heat-resistant alloy powder, and at the same time to metallurgically bond the machined surface of the base body and the sintered repair member. A method of repairing a high temperature component made of a heat resistant alloy, comprising: a step; and a step of heat treating the joined body.
の損傷部にＮｉ基耐熱合金製粉末を収容した補修部材を
装填する工程と、前記補修部材を前記基体の損傷部に加
圧しながら放電プラズマ焼結して前記Ｎｉ基耐熱合金製
粉末を焼結すると同時に前記基体の損傷部と焼結された
補修部材とを冶金的に接合する工程と、得られた接合体
を熱処理する工程と、を備えることを特徴とするＮｉ基
耐熱合金製ガスタービン翼の補修方法。9. A step of loading a repair member containing a powder of Ni-base heat-resistant alloy into a damaged portion of a base body of a gas turbine blade made of a Ni-base heat-resistant alloy, and discharging while pressing the repair member to the damaged portion of the base body. Plasma sintering to sinter the Ni-based heat-resistant alloy powder, and at the same time metallurgically bond the damaged part of the base body and the sintered repair member; and heat-treat the obtained bonded body. A method for repairing a Ni-based heat-resistant alloy gas turbine blade, comprising:
体の損傷部を機械的に除去して加工面を形成する工程
と、前記Ｎｉ基耐熱合金製粉末を収容した補修部材を前
記基体の加工面に装填する工程と、前記補修部材を前記
基体の加工面に加圧しながら放電プラズマ焼結して前記
Ｎｉ耐熱合金製粉末を焼結すると同時に前記基体の加工
面と焼結された補修部材とを冶金的に接合する工程と、
得られた接合体を熱処理する工程と、を備えることを特
徴とするＮｉ基耐熱合金製ガスタービン翼の補修方法。10. A step of mechanically removing a damaged portion of a base body of a Ni-base heat-resistant alloy gas turbine blade to form a machined surface, and a repair member containing the Ni-base heat-resistant alloy powder for processing the base body. A step of loading the surface of the base, and a process of pressing the repair member onto the working surface of the base body to sinter the Ni heat-resistant alloy powder while sintering the Ni heat-resistant alloy powder, and at the same time, the repair member sintered with the working surface of the base body. Metallurgically joining the
A method of repairing a gas turbine blade made of a Ni-base heat-resistant alloy, comprising the step of heat-treating the obtained joined body.
からなるＮｉ基耐熱合金製ガスタービン動翼の遮熱コー
ティング層を除去する工程と、下地コーティング層を剥
離する工程と、前記損傷部を機械的に除去して加工面を
形成する工程と、前記溶解鋳造材からなるＮｉ基耐熱合
金製ガスタービン動翼の基体と同一組成のＮｉ基耐熱合
金製粉末を収容した補修部材を前記基体の加工面に装填
する工程と、前記補修部材を前記基体の加工面に加圧し
ながら放電プラズマ焼結して前記Ｎｉ耐熱合金製粉末を
焼結すると同時に前記基体の加工面と焼結された補修部
材とを冶金的に接合する工程と、得られた接合体を熱処
理する工程と、前記熱処理された接合体に下地コーティ
ング層および遮熱コーティング層を順次被覆する工程
と、を備えることを特徴とする耐熱合金製ガスタービン
動翼の補修方法。11. A step of removing a thermal barrier coating layer of a Ni-based heat-resistant alloy gas turbine rotor blade made of a melt-cast material having a damaged portion on a blade base body, a step of peeling a base coating layer, and the damaged portion. And a repair member containing a Ni-base heat-resistant alloy powder having the same composition as the base body of the Ni-base heat-resistant alloy gas turbine blade made of the above-mentioned melt-cast material. And a step of loading the repaired member onto the machined surface of the base body to sinter the Ni heat-resistant alloy powder while simultaneously sintering the Ni heat-resistant alloy powder to repair the sintered body and the machined surface of the base body. It is characterized by comprising a step of metallurgically joining the members, a step of heat-treating the obtained joined body, and a step of successively coating the heat-treated joined body with a base coating layer and a thermal barrier coating layer. Repair method for gas turbine blades made of heat-resistant alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2002158056A JP2003342617A (en) | 2002-05-30 | 2002-05-30 | REPAIRED HIGH-TEMPERATURE COMPONENT MADE OF HEAT- RESISTANT ALLOY, REPAIRED GAS-TURBINE BLADE MADE OF Ni- BASED HEAT RESISTANT ALLOY, METHOD FOR REPAIRING GAS- TURBINE BLADE OF Ni-BASED HEAT RESISTANT ALLOY, AND METHOD FOR REPAIRING GAS-TURBINE BLADE MADE OF HEAT RESISTANT ALLOY |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2002158056A JP2003342617A (en) | 2002-05-30 | 2002-05-30 | REPAIRED HIGH-TEMPERATURE COMPONENT MADE OF HEAT- RESISTANT ALLOY, REPAIRED GAS-TURBINE BLADE MADE OF Ni- BASED HEAT RESISTANT ALLOY, METHOD FOR REPAIRING GAS- TURBINE BLADE OF Ni-BASED HEAT RESISTANT ALLOY, AND METHOD FOR REPAIRING GAS-TURBINE BLADE MADE OF HEAT RESISTANT ALLOY |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JP2003342617A true JP2003342617A (en) | 2003-12-03 |
Family
ID=29773592
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2002158056A Withdrawn JP2003342617A (en) | 2002-05-30 | 2002-05-30 | REPAIRED HIGH-TEMPERATURE COMPONENT MADE OF HEAT- RESISTANT ALLOY, REPAIRED GAS-TURBINE BLADE MADE OF Ni- BASED HEAT RESISTANT ALLOY, METHOD FOR REPAIRING GAS- TURBINE BLADE OF Ni-BASED HEAT RESISTANT ALLOY, AND METHOD FOR REPAIRING GAS-TURBINE BLADE MADE OF HEAT RESISTANT ALLOY |
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