JPH09157866A - Corrosion resistant and oxidation resistant coating film - Google Patents
Corrosion resistant and oxidation resistant coating filmInfo
- Publication number
- JPH09157866A JPH09157866A JP7312333A JP31233395A JPH09157866A JP H09157866 A JPH09157866 A JP H09157866A JP 7312333 A JP7312333 A JP 7312333A JP 31233395 A JP31233395 A JP 31233395A JP H09157866 A JPH09157866 A JP H09157866A
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- JP
- Japan
- Prior art keywords
- coating film
- oxidation
- corrosion
- base material
- resistant
- 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.)
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- Chemical Vapour Deposition (AREA)
- Coating By Spraying Or Casting (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、ガスタービンの動
・静翼やボイラのバーナ高温部品等に適用される耐食・
耐酸化コーティング膜に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a corrosion-resistant material applied to moving / stationary blades of gas turbines, burner high temperature parts of boilers, and the like.
The present invention relates to an oxidation resistant coating film.
【０００２】[0002]
【従来の技術】近年、ガスタービンは、高効率化のため
にタービン入口ガス温度の高温化が進むとともに、一方
では、よりよい経済性のために粗悪な燃料を使用する傾
向にある。また、ガスタービン特有の吸気により大気か
らの腐食性成分が混入する。2. Description of the Related Art In recent years, gas turbines have become increasingly high in turbine inlet gas temperature for higher efficiency, while on the other hand, there is a tendency to use poor fuel for better economic efficiency. Further, corrosive components from the atmosphere are mixed by the intake air peculiar to the gas turbine.
【０００３】これらの要因、即ち、高温化、粗悪燃料の
使用、大気からの腐食性成分の混入により、高温部品の
高温腐食と酸化が激しくなっているため、ガスタービン
の動・静翼には、より耐食・耐酸化性の優れたコーティ
ング膜が要求されるようになった。Due to these factors, that is, high temperature, use of poor fuel, and mixing of corrosive components from the atmosphere, high temperature corrosion and oxidation of high temperature parts are intensified. , A coating film with more excellent corrosion resistance and oxidation resistance has been required.
【０００４】従来のガスタービン動・静翼において、使
用される耐食・耐酸化コーティング膜には、図３
（ａ），（ｂ）に示すものがあった。以下にこれらの内
容について説明する。In the conventional gas turbine moving / stator blade, the corrosion / oxidation-resistant coating film used is as shown in FIG.
There are those shown in (a) and (b). These contents will be described below.
【０００５】図３（ａ）に示すものは、一般にＭＣｒＡ
ｌＹ（Ｍ：Ｃｏ，Ｎｉ，Ｆｅ単独元素、又は２種類の元
素）金属層２からなり、耐食・耐酸化性に富み、かつ母
材との相安定性が考慮されたコーティング膜であり、合
金粉末を低圧プラズマ溶射法によりＮｉ基合金もしくは
Ｃｏ基超合金（ＩＮ７８ＬＣ等）からなる母材１に溶射
して、形成されていた。What is shown in FIG. 3A is generally MCrA.
1Y (M: Co, Ni, Fe single element, or two kinds of elements) A metal layer 2 is a coating film which is rich in corrosion resistance and oxidation resistance, and in consideration of phase stability with the base metal. The powder was formed by spraying the powder onto the base material 1 made of a Ni-based alloy or a Co-based superalloy (IN78LC or the like) by a low pressure plasma spraying method.
【０００６】また、図３（ｂ）に示すものは、図３
（ａ）に示されたコーティング膜の耐食・耐酸化性を更
に改善するために、金属層２の上にＡｌ拡散浸透処理層
４が形成されていた。Further, the one shown in FIG.
In order to further improve the corrosion resistance and the oxidation resistance of the coating film shown in (a), the Al diffusion permeation treatment layer 4 was formed on the metal layer 2.
【０００７】[0007]
【発明が解決しようとする課題】従来のガスタービン動
・静翼に適用される耐食・耐酸化コーティング膜として
は、前記のように、図３（ａ），（ｂ）に示すものがあ
った。As described above, as the corrosion-resistant / oxidation-resistant coating film applied to the conventional gas turbine moving / stator blade, there are those shown in FIGS. 3 (a) and 3 (b). .
【０００８】図３（ａ）に示す従来のコーティング膜に
おいて、金属層を形成するＭＣｒＡｌＹは、母材との相
安定性（ＭＣｒＡｌＹと母材との境界及びその母材側に
脆弱な金属間化合物を生成しにくいこと）等の観点よ
り，Ｃｒ量は約３０％以下、Ａｌ量は約１５％以下に抑
えられていた。そのため、耐食・耐酸化性は十分ではな
かった。In the conventional coating film shown in FIG. 3 (a), MCrAlY forming the metal layer has phase stability with the base metal (intermetallic compound fragile at the boundary between the MCrAlY and the base metal and the base metal side). From the standpoint of difficulty in forming), the Cr content was suppressed to about 30% or less, and the Al content was suppressed to about 15% or less. Therefore, the corrosion resistance and oxidation resistance were not sufficient.
【０００９】図３（ｂ）に示す従来のコーティング膜に
おいては、より一層の耐食・耐酸化性の向上のためにＭ
ＣｒＡｌＹ金属層の上にＡｌ拡散浸透処理層が形成され
ており、著しく耐食・耐酸化性に優れるが、作業工程が
複雑なためコスト高となっていた。In the conventional coating film shown in FIG. 3B, in order to further improve the corrosion resistance and the oxidation resistance, M
An Al diffusion and permeation treatment layer is formed on the CrAlY metal layer, which is remarkably excellent in corrosion resistance and oxidation resistance, but the cost is high because the work process is complicated.
【００１０】本発明は、上記課題を解決するため、従来
のＭＣｒＡｌＹのみのコーティング膜よりも耐食・耐酸
化性に優れたコーティング膜をＡｌ拡散浸透処理層施工
のものと比較して安価に提供することを目的とする。In order to solve the above-mentioned problems, the present invention provides a coating film which is more excellent in corrosion resistance and oxidation resistance than the conventional coating film of MCrAlY only, at a lower cost as compared with the case of applying an Al diffusion permeation treatment layer. The purpose is to
【００１１】[0011]
（１）請求項１に記載の発明に係る耐食・耐酸化コーテ
ィング膜は、母材表面に設けられ耐食・耐酸化性に富む
Ａｌ2 Ｏ3 膜を生成するＮｉＡｌ単相合金層により形成
されたことを特徴としている。(1) The corrosion-resistant / oxidation-resistant coating film according to the invention of claim 1 is formed of a NiAl single-phase alloy layer which is provided on the surface of the base material and produces an Al 2 O 3 film rich in corrosion resistance / oxidation resistance. It is characterized by that.
【００１２】上記において、コーティング膜を形成する
ＮｉＡｌ単相合金層は、緻密なＡｌ 2 Ｏ3 膜を容易に生
成するため、従来のＭＣｒＡｌＹ金属層からなるコーテ
ィング膜の場合よりも耐食・耐酸化性に優れたコーティ
ング膜を得ることが可能となる。In the above, a coating film is formed
The NiAl single phase alloy layer is a dense Al TwoOThreeEasy to produce membrane
To form a conventional MCrAlY metal layer coating
A coating with better corrosion and oxidation resistance than the coating film
It is possible to obtain a ring film.
【００１３】（２）請求項２に記載の発明は、上記発明
（１）に記載の耐食・耐酸化コーティング膜において、
上記母材及びＮｉＡｌ単相合金層との密着性・相安定性
に富むＭＣｒＡｌＹ（Ｍ：Ｎｉ，Ｃｏ，Ｆｅの単独元素
２は２種類の元素）金属層が上記母材とＮｉＡｌ単相合
金層の間に設けられて形成されたことを特徴としてい
る。(2) The invention according to claim 2 is the corrosion-resistant / oxidation-resistant coating film according to the invention (1),
MCrAlY (M: Ni, Co, Fe is a single element 2 is two kinds of elements) metal layer having excellent adhesion and phase stability with the base material and the NiAl single-phase alloy layer. The metal layer is the base material and the NiAl single-phase alloy layer. It is characterized in that it is provided between and formed.
【００１４】上記においては、母材とＮｉＡｌ単相合金
層の間にＭＣｒＡｌＹ金属層が設けられているため、上
記発明（１）に比べて一層母材との密着性が向上し、均
一性が増加したコーティング膜を得ることが可能とな
る。In the above, since the MCrAlY metal layer is provided between the base material and the NiAl single phase alloy layer, the adhesion with the base material is further improved and the uniformity is improved as compared with the above-mentioned invention (1). It is possible to obtain an increased coating film.
【００１５】また、ＭＣｒＡｌＹ金属層とＮｉＡｌ合金
層は、低圧プラズマ溶射法による合金粉末の溶射により
継続して形成することができるため、従来のＭＣｒＡｌ
Ｙ金属層の上にＡｌ拡散浸透処理層が設けられて形成さ
れたコーティング膜と同等の品質のものをより安価に形
成することが可能となる。Further, since the MCrAlY metal layer and the NiAl alloy layer can be continuously formed by spraying the alloy powder by the low pressure plasma spraying method, the conventional MCrAlY layer and the NiAl alloy layer can be formed.
It is possible to inexpensively form a coating film having the same quality as the coating film formed by providing the Al diffusion / infiltration treatment layer on the Y metal layer.
【００１６】[0016]
【発明の実施の形態】本発明の実施の第１形態に係る耐
食・耐酸化コーティング膜について、図１により説明す
る。なお、本実施形態は、ガスタービン動・静翼に適用
されたものである。BEST MODE FOR CARRYING OUT THE INVENTION A corrosion / oxidation-resistant coating film according to a first embodiment of the present invention will be described with reference to FIG. The present embodiment is applied to a gas turbine moving / stator blade.
【００１７】図１に示す本実施形態においては、ガスタ
ービン動・静翼の母材１の表面に低圧プラズマ溶射法に
より４２〜５５原子％のＡｌを含むＮｉＡｌ単相合金層
３を形成し、これに１１２０±１５℃×２hrの窒素ガス
冷却、８４３±１５℃×２４hrの窒素ガス冷却からなる
後熱処理を施して、耐食・耐酸化コーティング膜を形成
している。In the embodiment shown in FIG. 1, a NiAl single phase alloy layer 3 containing 42 to 55 atomic% of Al is formed on the surface of a base material 1 of a gas turbine moving / stator blade by a low pressure plasma spraying method, This is subjected to a post heat treatment consisting of 1120 ± 15 ° C. × 2 hr nitrogen gas cooling and 843 ± 15 ° C. × 24 hr nitrogen gas cooling to form a corrosion / oxidation resistant coating film.
【００１８】上記において、コーティング膜は高濃度の
Ａｌを含有するＮｉＡｌ単相合金層３により形成され、
この合金層３は緻密なＡｌ2 Ｏ3 膜を容易に生成するた
め、優れた耐食・耐酸化性を有するコーティング膜を得
ることができた。In the above, the coating film is formed by the NiAl single phase alloy layer 3 containing a high concentration of Al,
Since the alloy layer 3 easily forms a dense Al 2 O 3 film, a coating film having excellent corrosion resistance and oxidation resistance could be obtained.
【００１９】なお、上記ＮｉＡｌ単相合金層３について
は、Ａｌの含有量を４２〜５５原子％に限定している
が、これはこの組織範囲でのみＮｉＡｌの単相合金が得
られるためであり、Ａｌが多いとＮｉＡｌ＋Ａｌの２相
合金、逆に少ないとＮｉＡｌ＋Ｎｉの２相合金となり、
２相合金になると高温での組織安定性に問題が生じるた
めである。In the NiAl single-phase alloy layer 3, the Al content is limited to 42 to 55 atomic%, because the NiAl single-phase alloy can be obtained only in this structure range. , If there is a large amount of Al, it becomes a NiAl + Al two-phase alloy, and conversely, if there is little Al, it becomes a NiAl + Ni two-phase alloy.
This is because a two-phase alloy causes a problem in structural stability at high temperatures.
【００２０】上記ＮｉＡｌ合金層３については、Ａｌが
少ないと延性を増して施工性の点で有利であるが、耐酸
化性を考えると多い方が優れるため、両者が両立する組
成を選ぶ必要がある。Regarding the NiAl alloy layer 3, when the amount of Al is small, the ductility is increased, which is advantageous in terms of workability. However, considering the oxidation resistance, the more the Al, the better. Therefore, it is necessary to select a composition compatible with both. is there.
【００２１】また、本実施形態では、ＮｉＡｌ合金層３
が形成された母材１について、１１２０±１５℃×２hr
及び８４３±１５℃×２４hrの窒素ガス冷却による後熱
処理を施しているが、これはＮｉＡｌ合金層３の母材１
との密着性を向上させ、均一なコーティング膜を得るた
めであり、母材１が溶体化熱処理を必要としない場合
は、前者の窒素ガス冷却は省略することができる。In this embodiment, the NiAl alloy layer 3 is also used.
1120 ± 15 ℃ × 2hr
And 843 ± 15 ° C. × 24 hr nitrogen gas cooling post heat treatment, which is the base material 1 of the NiAl alloy layer 3.
In order to improve the adhesiveness with and to obtain a uniform coating film, if the base material 1 does not require solution heat treatment, the former nitrogen gas cooling can be omitted.
【００２２】本発明の実施の第２形態に係る耐食・耐酸
化コーティング膜について、図２により説明する。図２
に示す本実施形態においては、ガスタービン動・静翼の
母材１の表面に低圧プラズマ溶射法により３１〜３２Ｎ
ｉ−２０〜３３Ｃｒ−７〜９Ａｌ−０．２５〜０．６５
Ｙ−残りＣｏ（重量％）のＣｏＮｉＣｒＡｌＹ金属層２
を形成した後、上記第１実施形態と同様にＮｉＡｌ単相
合金層３を形成し、後熱処理を施して、耐食・耐酸化コ
ーティング膜を形成している。A corrosion / oxidation-resistant coating film according to the second embodiment of the present invention will be described with reference to FIG. FIG.
In the present embodiment shown in FIG. 3, the surface of the base material 1 of the gas turbine moving / stationary blade is subjected to 31-32N by low pressure plasma spraying.
i-20-33Cr-7-9Al-0.25-0.65
Y—CoNiCrAlY metal layer 2 of remaining Co (wt%)
After the formation, the NiAl single phase alloy layer 3 is formed in the same manner as in the first embodiment, and post heat treatment is performed to form a corrosion / oxidation resistant coating film.
【００２３】上記においては、ＣｏＮｉＣｒＡｌＹ金属
層２は、上記母材１及びＮｉＡｌ単相合金層との密着性
・相安定性に富むため、均一で母材１との密着性が一層
向上したコーティング膜を得ることができた。In the above, the CoNiCrAlY metal layer 2 has a high degree of adhesion and phase stability with the base material 1 and the NiAl single phase alloy layer, so that it is uniform and has a further improved adhesion with the base material 1. I was able to get
【００２４】また、ＣｏＮｉＣｒＡｌＹ金属層２はＮｉ
Ａｌ単相合金層３と同じ低圧プラズマ溶射法により形成
されるため、ＣｏＮｉＣｒＡｌＹ金属層２を形成した
後、引き続いてＮｉＡｌ単相合金層３を形成することが
できるため、従来のＡｌ拡散浸透処理が施されたコーテ
ィング膜に比べて、工程の著しい簡素化、短縮が可能と
なった。The CoNiCrAlY metal layer 2 is made of Ni.
Since it is formed by the same low-pressure plasma spraying method as the Al single-phase alloy layer 3, the NiAl single-phase alloy layer 3 can be subsequently formed after the CoNiCrAlY metal layer 2 is formed. Compared with the applied coating film, the process can be significantly simplified and shortened.
【００２５】上記第１、第２実施形態に係る耐食・耐酸
化コーティング膜については、その性能確認のため、従
来のコーティング膜についてのものとともに、試料No１
〜６の試験片を製作し、酸化試験、高温腐食試験及びコ
スト評価を行っており、以下にその内容を説明する。For the corrosion-resistant / oxidation-resistant coating film according to the first and second embodiments, in order to confirm the performance thereof, a sample No. 1 was used together with the conventional coating film.
The test pieces of Nos. 6 to 6 were manufactured and subjected to an oxidation test, a high temperature corrosion test, and a cost evaluation. The contents will be described below.
【００２６】上記試験片は、直径１０mm×長さ５０mmの
円筒形状の母材（材質はＩＮ７３８ＬＣのＮｉ基合金）
にそれぞれコーティング膜を施したものであり、試料No
1 〜4 及びNo6 のコーティング膜については、表１に示
す組成の粉末（１５０μｍ以下）を表２に示す溶射条件
にて低圧プラズマ溶射法（ＬＰＰＳ）により溶射してそ
れぞれの膜厚の金属層２及び合金層３を形成した。The test piece is a cylindrical base material having a diameter of 10 mm and a length of 50 mm (the material is IN738LC Ni-based alloy).
Sample No.
For the coating films 1 to 4 and No. 6, the powder (150 μm or less) having the composition shown in Table 1 was sprayed by the low pressure plasma spraying method (LPPS) under the spraying conditions shown in Table 2, and the metal layer 2 of each thickness was formed. And the alloy layer 3 was formed.
【００２７】[0027]
【表１】 [Table 1]
【００２８】[0028]
【表２】 [Table 2]
【００２９】コーティング膜形成後は、１１２０±１５
℃×２hrの窒素ガス冷却、及び８４３±１５℃×２４hr
の窒素ガス冷却からなる後熱処理を実施し、コーティン
グ膜の母材との密着性及び均一化を図り、所要の材料強
度を有する試験片とした。After forming the coating film, 1120 ± 15
Nitrogen gas cooling at ℃ × 2hr, and 843 ± 15 ℃ × 24hr
After that, a post-heat treatment consisting of nitrogen gas cooling was carried out to achieve adhesion and uniformity of the coating film with the base material, and a test piece having the required material strength was obtained.
【００３０】試料No５については、ＣｏＮｉＣｒＡｌＹ
金属層を上述と同じ要領で形成した後、この試験片をＡ
ｌを含むＡｌ2 Ｏ3 粉末中に埋没し、１１００±１５℃
×１０hr、Ｈ2 ガスを流しながら処理し、Ａｌ拡散浸透
処理を行った。その後、母材の材料強度を確保するため
に１１２０±１５℃×２hrの窒素ガス冷却、８４３±１
５℃×２４hrの窒素ガス冷却からなる後熱処理を実施
し、試験片とした。For sample No. 5, CoNiCrAlY
After forming the metal layer in the same manner as above, this test piece was
embedded in Al 2 O 3 powder containing 1100 ± 15 ° C.
The treatment was performed for 10 hrs while flowing H 2 gas to perform Al diffusion permeation treatment. After that, in order to secure the material strength of the base material, 1120 ± 15 ° C. × 2 hr nitrogen gas cooling, 843 ± 1
A post heat treatment consisting of nitrogen gas cooling at 5 ° C. for 24 hours was carried out to obtain a test piece.
【００３１】なお、Ａｌ拡散浸透処理後は、Ａｌ拡散浸
透処理温度からの冷却速度が非常に遅いため、材質を回
復させる必要があり、１１２０±１５℃×２hrの窒素ガ
ス冷却、及び８４３±１５℃×２４hrの窒素ガス冷却か
らなる後熱処理は必須である。After the Al diffusion and permeation treatment, the cooling rate from the Al diffusion and permeation treatment temperature is very slow, so it is necessary to recover the material, and nitrogen gas cooling of 1120 ± 15 ° C. × 2 hr, and 843 ± 15. A post-heat treatment consisting of nitrogen gas cooling at 24 ° C. for 24 hours is essential.
【００３２】上記の試験片については、大気電気炉中加
熱（１１００±１５℃×１０００hr）による酸化試験を
行い、加熱後の試験片の重量を測定し、加熱前との差に
より酸化物生成による重量増加量を求めた。そして、各
試験片の重量増加量と試料No６の試験片のそれとの比を
求め、表３に示した。表３から、第１、第２実施形態に
係る試料No１〜４は、試料No６と比べて耐酸化性に優れ
ていることがわかる。The above test piece was subjected to an oxidation test by heating in an atmospheric electric furnace (1100 ± 15 ° C. × 1000 hr), and the weight of the test piece after heating was measured. The amount of weight increase was determined. Then, the ratio between the weight increase amount of each test piece and that of the test piece of sample No. 6 was determined and shown in Table 3. From Table 3, it can be seen that Sample Nos. 1 to 4 according to the first and second embodiments have better oxidation resistance than Sample No. 6.
【００３３】[0033]
【表３】 [Table 3]
【００３４】次に、同じく上記の試験片を用いて、高温
腐食試験を行った。即ち、腐食灰（Ｖ2 Ｏ5 ：Ｎａ2 Ｓ
Ｏ4 ＝８０：２０重量比）を２０mg/cm2の割合で試験片
全面に塗布し、８５０±１５℃×１００hrの大気中加熱
を行った（２０hr毎に腐食灰を塗布し、５サイクル計１
００hr）。試験後、湯でスケールを洗浄後重量測定し、
腐食試験前との差により、重量減量を求めた。そして、
各試験片の重量減量と試料No６のそれとの比を求め、表
３に示した。Next, a high temperature corrosion test was conducted using the above test piece. That is, corrosive ash (V 2 O 5 : Na 2 S
O 4 = 80: 20 weight ratio) was applied to the entire surface of the test piece at a rate of 20 mg / cm 2 and heated in the air at 850 ± 15 ° C. × 100 hr (corrosion ash was applied every 20 hr and 5 cycle meter) 1
00hr). After the test, weigh the scale after washing the scale with hot water,
The weight loss was calculated from the difference from that before the corrosion test. And
The ratio between the weight loss of each test piece and that of Sample No. 6 was determined and is shown in Table 3.
【００３５】表３から、第１、第２実施形態に係るいず
れの試料No１〜４とも試料No６より耐食性が優れている
ことがわかる。特に、試料No３は試料No５と同等の耐食
性を有することは注目してよい。From Table 3, it can be seen that any of Sample Nos. 1 to 4 according to the first and second embodiments has better corrosion resistance than Sample No. 6. Particularly, it may be noted that Sample No. 3 has the same corrosion resistance as Sample No. 5.
【００３６】試料No１〜試料No６のコーティングを施工
するに当たっては、それぞれコストを計算しており、そ
の結果は表３に示すとおりであり、第１，第２実施形態
に係る試料No１〜No４では、試料No６に比べて１〜１．
６倍であった。しかし、このコストアップはその性能向
上による動・静翼の寿命延長を考慮すると十分にカバー
できるものである。一方、試料No５はＡｌ拡散処理を実
施するために、著しいコストアップとなっていた。In applying the coating of Sample No. 1 to Sample No. 6, the cost was calculated respectively, and the results are as shown in Table 3. In Sample No. 1 to No. 4 according to the first and second embodiments, Compared with sample No.6, 1-1.
It was 6 times. However, this cost increase can be sufficiently covered in consideration of the life extension of the moving and stationary blades due to the performance improvement. On the other hand, since the sample No. 5 was subjected to Al diffusion treatment, the cost was significantly increased.
【００３７】以上、総合的に評価すると、第１，第２実
施形態に係るコーティング膜は、特性及びコスト的に優
れているものであることがわかった。As a result of comprehensive evaluation, it has been found that the coating films according to the first and second embodiments are excellent in characteristics and cost.
【００３８】[0038]
【発明の効果】本発明の耐食・耐酸化コーティング膜
は、Ａｌ2 Ｏ3 膜を生成するＮｉＡｌ単相合金層が母材
表面に設けられて形成されたことによって、従来のＭＣ
ｒＡｌＹ金属層からなるコーティング膜の場合よりも耐
食・耐酸化性に優れたコーティング膜を得ることが可能
となり、ＭＣｒＡｌＹ金属層を介して母材表面にＮｉＡ
ｌ単相合金層が形成されたことによって、母材との密着
性・均一性が一層増加するとともに、従来のＭＣｒＡｌ
Ｙ金属層の上にＡｌ拡散浸透処理層が設けられて形成さ
れたコーティング膜と同等の品質のものをより安価に形
成することが可能となる。The corrosion-resistant and oxidation-resistant coating film of the present invention is formed by forming a NiAl single-phase alloy layer for forming an Al 2 O 3 film on the surface of the base material.
It is possible to obtain a coating film having better corrosion resistance and oxidation resistance than the case of a coating film made of a rAlY metal layer, and NiA is formed on the surface of the base material via the MCrAlY metal layer.
l By forming a single-phase alloy layer, the adhesion and uniformity with the base material are further increased, and the conventional MCrAl
It is possible to inexpensively form a coating film having the same quality as the coating film formed by providing the Al diffusion / infiltration treatment layer on the Y metal layer.
【図１】本発明の実施の第１形態に係る耐食・耐酸化コ
ーティング膜の説明図である。FIG. 1 is an explanatory diagram of a corrosion-resistant / oxidation-resistant coating film according to a first embodiment of the present invention.
【図２】本発明の実施の第２形態に係る耐食・耐酸化コ
ーティング膜の説明図である。FIG. 2 is an explanatory diagram of a corrosion / oxidation resistant coating film according to a second embodiment of the present invention.
【図３】従来の耐食・耐酸化コーティング膜の説明図
で、（ａ）はその一例、（ｂ）は他の例の説明図であ
る。3A and 3B are explanatory views of a conventional corrosion-resistant / oxidation-resistant coating film, FIG. 3A is an example thereof, and FIG. 3B is an explanatory view of another example.
１ 母材 ２ ＣｏＮｉＣｒＡｌＹ金属層 ３ ＮｉＡｌ単相合金層 1 Base Material 2 CoNiCrAlY Metal Layer 3 NiAl Single Phase Alloy Layer
───────────────────────────────────────────────────── フロントページの続き (51)Int.Cl.6 識別記号 庁内整理番号 ＦＩ 技術表示箇所 Ｃ２３Ｃ 16/50 Ｃ２３Ｃ 16/50 ──────────────────────────────────────────────────続 き Continued on the front page (51) Int.Cl. 6 Identification code Agency reference number FI Technical display location C23C 16/50 C23C 16/50
Claims (2)
むＡｌ2 Ｏ3 膜を生成するＮｉＡｌ単相合金層により形
成されたことを特徴とする耐食・耐酸化コーティング
膜。1. A corrosion-resistant / oxidation-resistant coating film formed by a NiAl single-phase alloy layer which is provided on the surface of a base material and produces an Al 2 O 3 film rich in corrosion resistance / oxidation resistance.
ング膜において、上記母材及びＮｉＡｌ単相合金層との
密着性・相安定性に富むＭＣｒＡｌＹ金属層が上記母材
とＮｉＡｌ単相合金層の間に設けられて形成されたこと
を特徴とする耐食・耐酸化コーティング膜。2. The corrosion-resistant / oxidation-resistant coating film according to claim 1, wherein the MCrAlY metal layer having excellent adhesion and phase stability with the base material and the NiAl single phase alloy layer is the base material and the NiAl single phase alloy. A corrosion-resistant / oxidation-resistant coating film formed by being provided between layers.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP7312333A JPH09157866A (en) | 1995-11-30 | 1995-11-30 | Corrosion resistant and oxidation resistant coating film |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP7312333A JPH09157866A (en) | 1995-11-30 | 1995-11-30 | Corrosion resistant and oxidation resistant coating film |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH09157866A true JPH09157866A (en) | 1997-06-17 |
Family
ID=18027984
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP7312333A Withdrawn JPH09157866A (en) | 1995-11-30 | 1995-11-30 | Corrosion resistant and oxidation resistant coating film |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH09157866A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001234322A (en) * | 1999-12-20 | 2001-08-31 | United Technol Corp <Utc> | Turbine blade for gas turbine engine |
| EP1380672A1 (en) * | 2002-07-09 | 2004-01-14 | Siemens Aktiengesellschaft | Highly oxidation resistant component |
| EP1637622A1 (en) * | 2004-09-15 | 2006-03-22 | Man Turbo Ag | Process for application of a protective coating |
| KR100830648B1 (en) * | 1999-09-28 | 2008-05-20 | 제너럴 일렉트릭 캄파니 | A method for providing a protective coating on a metal-based substrate and an article having a protective coating on a metal-based substrate |
| WO2011010400A1 (en) * | 2009-07-22 | 2011-01-27 | 日鉄ハード株式会社 | Molten metal-resistant member and process for producing molten metal-resistant member |
-
1995
- 1995-11-30 JP JP7312333A patent/JPH09157866A/en not_active Withdrawn
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100830648B1 (en) * | 1999-09-28 | 2008-05-20 | 제너럴 일렉트릭 캄파니 | A method for providing a protective coating on a metal-based substrate and an article having a protective coating on a metal-based substrate |
| JP2001234322A (en) * | 1999-12-20 | 2001-08-31 | United Technol Corp <Utc> | Turbine blade for gas turbine engine |
| EP1380672A1 (en) * | 2002-07-09 | 2004-01-14 | Siemens Aktiengesellschaft | Highly oxidation resistant component |
| WO2004005581A1 (en) * | 2002-07-09 | 2004-01-15 | Siemens Aktiengesellschaft | Highly oxidation resistant component |
| US7368177B2 (en) | 2002-07-09 | 2008-05-06 | Siemens Aktiengesellschaft | Highly oxidation resistant component |
| EP2098615A1 (en) | 2002-07-09 | 2009-09-09 | Siemens Aktiengesellschaft | Highly oxidation resistant component |
| EP2098614A1 (en) | 2002-07-09 | 2009-09-09 | Siemens Aktiengesellschaft | Highly oxidation resistant component |
| EP1637622A1 (en) * | 2004-09-15 | 2006-03-22 | Man Turbo Ag | Process for application of a protective coating |
| US7736704B2 (en) | 2004-09-15 | 2010-06-15 | Man Turbo Ag | Process for applying a protective layer |
| WO2011010400A1 (en) * | 2009-07-22 | 2011-01-27 | 日鉄ハード株式会社 | Molten metal-resistant member and process for producing molten metal-resistant member |
| JP5647608B2 (en) * | 2009-07-22 | 2015-01-07 | 日鉄住金ハード株式会社 | Melt-resistant metal member and method for producing molten metal member |
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