JPH0432546A - Method for repairing moving blade of gas turbine - Google Patents
Method for repairing moving blade of gas turbineInfo
- Publication number
- JPH0432546A JPH0432546A JP2135249A JP13524990A JPH0432546A JP H0432546 A JPH0432546 A JP H0432546A JP 2135249 A JP2135249 A JP 2135249A JP 13524990 A JP13524990 A JP 13524990A JP H0432546 A JPH0432546 A JP H0432546A
- Authority
- JP
- Japan
- Prior art keywords
- gas turbine
- thermal spraying
- thickness
- turbine rotor
- pressure plasma
- 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
- 238000000034 method Methods 0.000 title claims description 13
- 230000008439 repair process Effects 0.000 claims abstract description 14
- 238000005260 corrosion Methods 0.000 claims abstract description 12
- 230000007797 corrosion Effects 0.000 claims abstract description 12
- 238000009792 diffusion process Methods 0.000 claims abstract description 9
- 238000010438 heat treatment Methods 0.000 claims abstract description 6
- 238000007750 plasma spraying Methods 0.000 claims description 11
- 239000000956 alloy Substances 0.000 claims description 8
- 229910045601 alloy Inorganic materials 0.000 claims description 8
- 238000007751 thermal spraying Methods 0.000 abstract description 12
- 239000000463 material Substances 0.000 abstract description 10
- 238000003754 machining Methods 0.000 abstract description 3
- 239000000853 adhesive Substances 0.000 abstract description 2
- 230000001070 adhesive effect Effects 0.000 abstract description 2
- 239000010953 base metal Substances 0.000 abstract description 2
- 238000005422 blasting Methods 0.000 abstract description 2
- 229910002441 CoNi Inorganic materials 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 9
- 238000005530 etching Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 239000002245 particle Substances 0.000 description 3
- 229910003266 NiCo Inorganic materials 0.000 description 2
- UCKMPCXJQFINFW-UHFFFAOYSA-N Sulphide Chemical compound [S-2] UCKMPCXJQFINFW-UHFFFAOYSA-N 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- -1 0oNi Inorganic materials 0.000 description 1
- NINIDFKCEFEMDL-UHFFFAOYSA-N Sulfur Chemical compound [S] NINIDFKCEFEMDL-UHFFFAOYSA-N 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000012733 comparative method Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000002244 precipitate Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 229910052717 sulfur Inorganic materials 0.000 description 1
- 239000011593 sulfur Substances 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)
- Coating By Spraying Or Casting (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は、ガスタービン動翼の硫化腐食減肉部等の補修
に好適なガスタービン動翼補修方法に関する。DETAILED DESCRIPTION OF THE INVENTION [Industrial Application Field] The present invention relates to a gas turbine rotor blade repair method suitable for repairing sulfide corrosion thinning portions of gas turbine rotor blades.
Ｎ溶接性超高合金からなるガスタービン動翼が、タービ
ン運転復硫化腐食等にて翼前縁部が減肉した場合には、
従来、溶接することにより、溶接熱影響部近傍の粒界に
γ′相が析出しクラックが発生することから、溶接によ
る補修は行わすに廃却し、新翼と取替えている。If the leading edge of a gas turbine rotor blade made of an ultra-high N weldability alloy is thinned due to turbine operation resulfide corrosion, etc.
Conventionally, when welding, the γ' phase precipitates at the grain boundaries near the weld heat affected zone and cracks occur, so welding repairs are discarded immediately and replaced with new blades.
しかしながら、通常、ガスタービン動翼に用いられる材
料は耐熱性の高いことが要求されるため、！［容接性超
高合金が採用されることが多くその材料費が高いぼかり
てなく、動翼への加工費も含めると１本当たりの単価は
かなりの価格となることから、運転後に廃却新翼取替え
することは非常にコスト高となる。However, the materials used for gas turbine rotor blades are usually required to have high heat resistance! [Ultra-high-conductivity alloys are often used, and their material costs are high, and the cost per blade is quite high when processing costs are included. Replacing the new wing would be extremely costly.
本発明は、このような事情に鑑みて提案されたもので、
緻密な層が形成されるとともに付着強度か大きい境界層
が得られる補修部をもってガスタービン動翼の補修が可
能となり、新翼取替えと比べてコストが安くなるガスタ
ービン動翼補修方法を提供することを目的とする。The present invention was proposed in view of these circumstances, and
To provide a gas turbine rotor blade repair method that enables repair of a gas turbine rotor blade with a repair part in which a dense layer is formed and a boundary layer with high adhesion strength is obtained, and the cost is lower than that of replacing a new blade. With the goal.
そのために本発明は、難溶接性超高合金からなるガスタ
ービン動翼の腐食減肉部分に対し、腐食減肉域を完全に
除去したうえで減圧プラズマ溶射にてＭ Ｃｒ Ａ ｎ
Ｙを肉盛溶射した後、拡散熱処理を施しプロファイル
仕上げを加えて補修することを特徴とする。For this purpose, the present invention completely removes the corrosion thinning area of a gas turbine rotor blade made of a difficult-to-weld ultra-high alloy, and then applies M Cr An by low pressure plasma spraying.
The feature is that after overlaying with Y, a diffusion heat treatment is performed and a profile finish is added for repair.
本発明ガスタービン動翼補修方法においては、減圧プラ
ズマ溶射を用いることにより、粒子間の結合か機械的結
合であるため、難溶接性超高合金母材を溶融することな
く肉盛でき、かつその後の熱処理にて溶射層と母材間に
粒子の拡散現象が生し、通常の溶射膜に比べて付着強度
が向上する。また減圧プラズマ溶射を用いているため、
非常に緻密な組織が得られる。In the gas turbine rotor blade repair method of the present invention, by using low-pressure plasma spraying, bonding between particles or mechanical bonding is possible, so that hard-to-weld ultra-high alloy base material can be overlaid without melting, and after During the heat treatment, a particle diffusion phenomenon occurs between the sprayed layer and the base material, resulting in improved adhesion strength compared to normal sprayed coatings. In addition, since low pressure plasma spraying is used,
A very dense tissue is obtained.
本発明ガスタービン動翼補修方法の一実施例を図面につ
いて説明すると、第１図は本発明方法を工程順に示し、
同図（１）、 （■）はそれぞれ溶射前のガスタービ
ン動翼の斜視図、同図（Ｉ［Ｉ）は同図（ＩＩ）の■−
■に沿った横断面を示しくＡ）は横断面図、（Ｂ）は（
Ａ）のＢ部拡大図、同図（ＩＶ）、 （Ｖ）はそれぞ
れ溶射後のガスタービン動翼の斜視図、第２図は溶射材
Ｍ Ｃｒ Ａ ｊ！ Ｙの成分組成の説明図、第３図は
減圧プラズマ溶射条件の説明図、第４図は溶射層のミク
ロ組織を示しくＡ）はノーエツチングの組織図、（Ｂ）
はエツチング後の組織図、第５図は溶射層の付着強度の
説明図である。An embodiment of the gas turbine rotor blade repair method of the present invention will be explained with reference to the drawings. Fig. 1 shows the method of the present invention in the order of steps;
Figures (1) and (■) are respectively perspective views of the gas turbine rotor blades before thermal spraying, and figure (I [I) is ■-- of figure (II).
A) is a cross-sectional view, and (B) is a cross-sectional view along ■.
An enlarged view of part B in A), (IV) and (V) are respectively perspective views of the gas turbine rotor blade after thermal spraying, and Figure 2 shows the thermal sprayed material M Cr A j! An explanatory diagram of the component composition of Y, Fig. 3 is an explanatory diagram of the low-pressure plasma spraying conditions, Fig. 4 shows the microstructure of the sprayed layer, A) is a no-etching structure diagram, (B)
is a diagram of the structure after etching, and FIG. 5 is an explanatory diagram of the adhesion strength of the sprayed layer.
まず第１図（１）において、Ｎ溶接性超高合金（例えば
ｌＮ７３８ＬＣ）からなるガスタービン動翼１は、運転
後に門前縁部が硫化腐食等にて腐食減肉２しており、ま
ずこの腐食減肉２域をグリントブラストにて除去し、腐
食減肉２域が完全に除去できたが否かはサルファープリ
ントにて確認する。First, in Fig. 1 (1), a gas turbine rotor blade 1 made of an ultra-high N weldable alloy (for example, IN738LC) has thinning 2 of the leading edge of the gate due to sulfide corrosion after operation. The 2nd area of reduced thickness was removed by glint blasting, and the sulfur print was used to confirm whether the 2nd area of reduced thickness due to corrosion was completely removed.
その後、第１図（ＩＩ）において、溶射前準備として減
肉部を機械加工３により成形する。Thereafter, in FIG. 1 (II), the thinned portion is formed by machining 3 in preparation for thermal spraying.
なおこの際は同図（１）に示すように、加工溝の端部ば
Ｒ５以上にし、面取り角度は４５゜以上にとる。In this case, as shown in FIG. 1 (1), the edge of the machined groove should be R5 or more, and the chamfer angle should be 45° or more.
次いで、第１図（ＩＶ）において、翼面より０．１ｍｍ
以上厚く、ＭＣｒＡ＃Ｙ （Ｍ：ＮｉＣｏ、０ｏＮｉ、
ＮｉＣｏ、Ｆｅ等）を減圧プラズマ溶射にて肉盛溶射４
する。なお溶射材ＭｃｒＡｘｙの成分組成及び減圧プラ
ズマ条件を例示すると、第２図及び第３図の通りである
。Next, in Figure 1 (IV), 0.1 mm from the wing surface.
thicker than MCrA#Y (M: NiCo, 0oNi,
NiCo, Fe, etc.) using low pressure plasma spraying 4
do. The composition of the thermal spray material McrAxy and the reduced pressure plasma conditions are illustrated in FIGS. 2 and 3.
そして、この肉盛溶射４を形成後に、ガスタービン動翼
１を真空雰囲気炉内に装入し、０．０１〜０．０２ Ｔ
ｏｒｒまで真空引き後、０．１〜０．２ Ｔｏｒｒまで
Ｎ２封入し、炉内を加熱する。After forming this overlay thermal spraying 4, the gas turbine rotor blade 1 is placed in a vacuum atmosphere furnace and heated to 0.01 to 0.02 T.
After evacuation to 0.3 Torr, N2 is filled to 0.1 to 0.2 Torr and the inside of the furnace is heated.
母材の溶体化温度１時間（例えばｌＮ７３８ＬＣてあれ
ばｌ １２ Ｑ ’ｃ ｘ ２ ｈ ｒ−ｆ＆、８４３
’ｃ ｘ ２４ ｈ ｒ ）乙こて保持した後、Ｎ２を
１０００ Ｔｏｒｒ程度封入し、急冷する。Solution temperature of base metal for 1 hour (for example, if lN738LC, l 12 Q 'c x 2 h r-f&, 843
'c x 24 hr) After holding with a trowel, N2 is filled at about 1000 Torr and rapidly cooled.
これにより、母材と溶射材との間に相互拡散が止し拡散
層ができるので、付着強度が向上する。This prevents mutual diffusion between the base material and the sprayed material and forms a diffusion layer, thereby improving adhesion strength.
最後に第１図（Ｖ）に示すように、翼の図面通りにプロ
ファイル面を仕上げ加工し、これにより補修は完了する
。Finally, as shown in FIG. 1(V), the profiled surface of the blade is finished according to the drawing, thereby completing the repair.
このようにして形成された肉盛溶射４の溶射層の金属組
織の状態、接合強度の具体例を第４図、第５図について
説明すると、第４図は、Ｎ１ＣｏＣｒＡＡＹを減圧プラ
ズマ溶射した溶射層のミクロ組織で、（Ａ）はノーエツ
チング状ｓ、 （Ｂ）はエツチング後の状態を示し、
気孔、空隙の殆んどない緻密な層が形成されている。Specific examples of the state of the metal structure and bonding strength of the sprayed layer of the overlay thermal spray 4 formed in this manner will be explained with reference to FIGS. 4 and 5. FIG. The microstructure of (A) shows the no-etched state, (B) shows the state after etching,
A dense layer with almost no pores or voids is formed.
また第５図は、大気プラズマ溶射による比較方法と減圧
プラズマ溶射による本発明方法について、ＪＩＳに基づ
く溶射層の付着力試験結果を示し、比較方法では付着強
度５ｋｇ／ｆ１２であるのに対し、本発明方法では接着
剤強度を上回っており付着強度が高い。その理由は溶射
層の緻密性と熱処理による拡散層の影響である。Furthermore, Figure 5 shows the adhesion test results of thermal sprayed layers based on JIS for the comparative method using atmospheric plasma spraying and the present invention method using reduced pressure plasma spraying. The inventive method has a high adhesion strength that exceeds the adhesive strength. The reason for this is the denseness of the sprayed layer and the influence of the diffusion layer caused by heat treatment.
かくして、この方法によれば次の効果が奏せられる。Thus, this method provides the following effects.
（１）難溶接性超高合金からなるガスタービン動翼の補
修が可能である。(1) It is possible to repair gas turbine rotor blades made of a difficult-to-weld ultra-high alloy.
（２）斯界取替えと比べてコストがかなり安くなる。(2) The cost is considerably lower than that of field replacement.
（３）減圧プラズマ溶射を用いるため、補修部に気孔、
空隙が殆んど存在しない緻密な層ができる。(3) Since low-pressure plasma spraying is used, there are no pores in the repaired area.
A dense layer with almost no voids is formed.
（４）溶射後の熱処理により境界層に粒子拡散層ができ
るため、通常の溶射膜に比べて付着強度が上がる。(4) Since a particle diffusion layer is formed in the boundary layer by heat treatment after thermal spraying, adhesion strength is increased compared to a normal thermal sprayed film.
（５）腐食されやすい領域にＭＣｒＡＩＩＹをコーティ
ングするため、耐食性が向上する。(5) Corrosion resistance is improved because MCrAIIY is coated on areas that are prone to corrosion.
要するに本発明によれば、Ｈ溶接性超高合金からなるガ
スタービン動翼の腐食減肉部分に対し、腐食減肉域を完
全に除去したうえて減圧プラズマ溶射にてＭ Ｃｒ Ａ
Ｅ Ｙを肉盛溶射した後、拡散熱処理を施しプロファ
イル仕上げを加えて補修することにより、緻密な層が形
成されるとともに付着強度が大きい境界層が得られる補
修部をもってガスタービン動翼の補修が可能となり、斯
界取替えと比べてコストが安くなるガスタービン動翼補
修方法を得るから、本発明は産業上極めて有益なもので
ある。In short, according to the present invention, after completely removing the corrosion thinning area of a gas turbine rotor blade made of a super-high H weldability alloy, M Cr A is applied by low pressure plasma spraying.
After the E The present invention is of great industrial benefit because it provides a gas turbine rotor blade repair method that is possible and less costly than field replacement.
第１図は本発明ガスタービン動翼補修方法の一実施例に
おける本発明方法を工程順に示し、同図（Ｉ）、 （
ＩＩ）はそれぞれ溶射前のガスタービン動翼の斜視図、
同図（ＩＩＩ）は同図（ＩＩ）のＩＩＩ−Ｉ［１に沿っ
た横断面を示しくＡ）は横断面図、（Ｂ）は（Ａ）のＢ
部拡大図、同図（ＩＶ）、 （Ｖ）はそれぞれ溶射後
のガスタービン動翼の斜視図、第２図は溶射材ＭＣｒＡ
βＹの成分組成の説明図、第３図は減圧プラズマ溶射条
件の説明図、第４図は溶射層のミクロ組織を示しくＡ）
はノーエツチングの組織図、（Ｂ）はエツチング後の組
織図、第５図は溶射層の付着強度の説明図である。
１・・・ガスタービン動翼、２・・・腐食減肉、３・・
・機械加工、４・・・肉盛溶射。
（Ｉ）
第７図
代理人 弁理士 塚 本 正 文
第
図
第
図
第４図
（Ａ）
第５図
占
搏羞判ぼｆｆｒFIG. 1 shows the method of the present invention in the order of steps in an embodiment of the gas turbine rotor blade repair method of the present invention.
II) is a perspective view of a gas turbine rotor blade before thermal spraying, and
Figure (III) shows a cross section along III-I [1 of Figure (II); A) is a cross section; (B) is B of (A)
(IV) and (V) are respectively perspective views of gas turbine rotor blades after thermal spraying, and Figure 2 is an enlarged view of the thermal sprayed material MCrA.
An explanatory diagram of the component composition of βY, Fig. 3 is an explanatory diagram of the low-pressure plasma spraying conditions, and Fig. 4 shows the microstructure of the sprayed layer.A)
(B) is a structure diagram after etching, and FIG. 5 is an explanatory diagram of adhesion strength of the sprayed layer. 1... Gas turbine rotor blade, 2... Corrosion thinning, 3...
・Machining, 4... Overlay thermal spraying. (I) Figure 7 Agent Patent Attorney Masa Tsukamoto Figure 4 (A) Figure 5
Claims (1)
うえで減圧プラズマ溶射にて ＭＣｒＡｌＹを肉盛溶射した後、拡散熱処理を施しプロ
ファイル仕上げを加えて補修することを特徴とするガス
タービン動翼補修方法。[Claims] After completely removing the corrosion thinning area of a gas turbine rotor blade made of a difficult-to-weld ultra-high alloy, and then overlaying MCrAlY by low-pressure plasma spraying, A gas turbine rotor blade repair method characterized by performing diffusion heat treatment and adding profile finishing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2135249A JPH0432546A (en) | 1990-05-28 | 1990-05-28 | Method for repairing moving blade of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2135249A JPH0432546A (en) | 1990-05-28 | 1990-05-28 | Method for repairing moving blade of gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH0432546A true JPH0432546A (en) | 1992-02-04 |
Family
ID=15147298
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2135249A Pending JPH0432546A (en) | 1990-05-28 | 1990-05-28 | Method for repairing moving blade of gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0432546A (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6001761A (en) * | 1994-09-27 | 1999-12-14 | Nippon Shokubai Co., Ltd. | Ceramics sheet and production method for same |
| US6228510B1 (en) | 1998-12-22 | 2001-05-08 | General Electric Company | Coating and method for minimizing consumption of base material during high temperature service |
| EP1122329A1 (en) * | 2000-02-07 | 2001-08-08 | General Electric Company | A method of providing a protective coating on a metal substrate, and related articles |
| EP1162284A1 (en) * | 2000-06-05 | 2001-12-12 | Alstom (Switzerland) Ltd | Process of repairing a coated component |
| WO2002103075A1 (en) * | 2001-06-13 | 2002-12-27 | Mitsubishi Heavy Industries, Ltd. | Method for repairing ni base alloy component |
| JP2007040303A (en) * | 2005-08-01 | 2007-02-15 | General Electric Co <Ge> | Method of restoring part of turbine structural element |
| EP2366488A1 (en) * | 2010-03-19 | 2011-09-21 | Siemens Aktiengesellschaft | Method for reconditioning a turbine blade with at least one platform |
| US20130136948A1 (en) * | 2010-06-02 | 2013-05-30 | Friedhelm Schmitz | Alloy, protective layer and component |
| US20140220384A1 (en) * | 2011-09-12 | 2014-08-07 | Siemens Aktiengesellschaft | Alloy, protective layer and component |
| US20140220379A1 (en) * | 2011-08-09 | 2014-08-07 | Siemens Aktiengesellschaft | Alloy, protective layer and component |
| JP2014189830A (en) * | 2013-03-27 | 2014-10-06 | Mitsubishi Heavy Ind Ltd | Fatigue life recovery heat-treatment method |
| US20140342186A1 (en) * | 2011-09-12 | 2014-11-20 | Siemens Aktiengesellschaft | Layer system with double mcralx metallic layer |
| JP2014532112A (en) * | 2011-08-10 | 2014-12-04 | スネクマ | Method for producing a protective reinforcement for the leading edge of a blade |
-
1990
- 1990-05-28 JP JP2135249A patent/JPH0432546A/en active Pending
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6001761A (en) * | 1994-09-27 | 1999-12-14 | Nippon Shokubai Co., Ltd. | Ceramics sheet and production method for same |
| US6228510B1 (en) | 1998-12-22 | 2001-05-08 | General Electric Company | Coating and method for minimizing consumption of base material during high temperature service |
| EP1122329A1 (en) * | 2000-02-07 | 2001-08-08 | General Electric Company | A method of providing a protective coating on a metal substrate, and related articles |
| EP1162284A1 (en) * | 2000-06-05 | 2001-12-12 | Alstom (Switzerland) Ltd | Process of repairing a coated component |
| US6569492B2 (en) | 2000-06-05 | 2003-05-27 | Alstom Ltd | Process for repairing a coated component |
| WO2002103075A1 (en) * | 2001-06-13 | 2002-12-27 | Mitsubishi Heavy Industries, Ltd. | Method for repairing ni base alloy component |
| US7172787B2 (en) | 2001-06-13 | 2007-02-06 | Mitsubishi Heavy Industries, Ltd. | Method of repairing a Ni-base alloy part |
| JP2007040303A (en) * | 2005-08-01 | 2007-02-15 | General Electric Co <Ge> | Method of restoring part of turbine structural element |
| EP2366488A1 (en) * | 2010-03-19 | 2011-09-21 | Siemens Aktiengesellschaft | Method for reconditioning a turbine blade with at least one platform |
| WO2011113833A1 (en) * | 2010-03-19 | 2011-09-22 | Siemens Aktiengesellschaft | Method for reprocessing a turbine blade having at least one platform |
| US20130136948A1 (en) * | 2010-06-02 | 2013-05-30 | Friedhelm Schmitz | Alloy, protective layer and component |
| US20140220379A1 (en) * | 2011-08-09 | 2014-08-07 | Siemens Aktiengesellschaft | Alloy, protective layer and component |
| US11092034B2 (en) * | 2011-08-09 | 2021-08-17 | Siemens Energy Global Gmbh & Co, Kg | Alloy, protective layer and component |
| JP2014532112A (en) * | 2011-08-10 | 2014-12-04 | スネクマ | Method for producing a protective reinforcement for the leading edge of a blade |
| US9664201B2 (en) | 2011-08-10 | 2017-05-30 | Snecma | Method of making protective reinforcement for the leading edge of a blade |
| US20140220384A1 (en) * | 2011-09-12 | 2014-08-07 | Siemens Aktiengesellschaft | Alloy, protective layer and component |
| US20140342186A1 (en) * | 2011-09-12 | 2014-11-20 | Siemens Aktiengesellschaft | Layer system with double mcralx metallic layer |
| US9556748B2 (en) * | 2011-09-12 | 2017-01-31 | Siemens Aktiengesellschaft | Layer system with double MCrAlX metallic layer |
| US11092035B2 (en) * | 2011-09-12 | 2021-08-17 | Siemens Energy Global GmbH & Co. KG | Alloy, protective layer and component |
| JP2014189830A (en) * | 2013-03-27 | 2014-10-06 | Mitsubishi Heavy Ind Ltd | Fatigue life recovery heat-treatment method |
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