JPH0688197A - Surface layer of dynamic and static vanes - Google Patents
Surface layer of dynamic and static vanesInfo
- Publication number
- JPH0688197A JPH0688197A JP4125240A JP12524092A JPH0688197A JP H0688197 A JPH0688197 A JP H0688197A JP 4125240 A JP4125240 A JP 4125240A JP 12524092 A JP12524092 A JP 12524092A JP H0688197 A JPH0688197 A JP H0688197A
- Authority
- JP
- Japan
- Prior art keywords
- layer
- dynamic
- static vanes
- coated
- surface layer
- 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.)
- Granted
Links
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明はガスタービンの高温化、
高効率化に対応可能な動・静翼表面層に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention
The present invention relates to a moving / stator blade surface layer that can be used for high efficiency.
【０００２】[0002]
【従来の技術】コンバインドサイクルプラントに代表さ
れる高効率化された最近の産業用ガスタービンのタービ
ン入口ガス温度の上昇は著しく１３００℃以上となって
いる。このような高温ガスに曝露される動・静翼に使用
される耐熱合金は精力的に研究開発が行なわれ、その許
容使用温度も年々上昇しているが、実用合金では８５０
〜９００℃程度である。このため、実機ガスタービンで
は薄肉化した内部空気冷却翼が用いられている。2. Description of the Related Art The temperature of the gas at the turbine inlet of a recent highly efficient industrial gas turbine represented by a combined cycle plant rises significantly to 1300 ° C. or more. Heat-resistant alloys used for moving and stationary blades exposed to such high-temperature gas have been energetically researched and developed, and the allowable operating temperature has been increasing year by year.
It is about 900 ° C. For this reason, a thin-walled internal air cooling blade is used in the actual gas turbine.
【０００３】一方、使用される燃料はＬＮＧ、副生ガス
や重油におよび最近では石炭を液化又はガス化して利用
することも研究されており、空気冷却翼の高温酸化や高
温腐食防止を目的として低圧プラズマ溶射法（以下、Ｖ
ＰＳという）によりＮｉＣｒＡｌＹ又はＣｏＮｉＣｒＡ
ｌＹなどの耐食合金のコーティングを施した後、ＺｒＯ
2 −Ｙ2 Ｏ3 を大気プラズマ溶射法（以下、ＡＰＳとい
う）でコーティングし、この遮熱効果を利用して基材合
金の温度を低下させ、その結果としてガス温度の高温化
に対処している。On the other hand, the fuel to be used is LNG, by-product gas or heavy oil, and recently, the use of liquefied or gasified coal has also been studied, with the aim of preventing high temperature oxidation and high temperature corrosion of air cooling blades. Low pressure plasma spraying method (hereinafter V
Depending on PS) NiCrAlY or CoNiCrA
After applying a corrosion resistant alloy coating such as LY, ZrO
2- Y 2 O 3 is coated by the atmospheric plasma spraying method (hereinafter referred to as APS), the temperature of the base alloy is lowered by utilizing this heat shielding effect, and as a result, the gas temperature is increased. There is.
【０００４】[0004]
【発明が解決しようとする課題】高温化されたガスター
ビンにおいて、直接燃焼ガスと接触する動・静翼はガス
温度の上昇にともなって酸化速度が増加し、前記のよう
な遮熱コーティングを行った場合でも燃料や燃焼空気よ
り高温腐食成分がもち込まれると、これらが最表層のＺ
ｒＯ2 −Ｙ2 Ｏ3 層を透過して中間層のＮｉＣｒＡｌＹ
又はＣｏＮｉＣｒＡｌＹまで到達し、これを腐食又は高
温酸化させる。このため中間層と最表層の境界部に腐食
又は酸化生成物ができ、これらは体積膨張を伴なうた
め、ＺｒＯ2−Ｙ2 Ｏ3 層が剥離することがしばしば見
受けられる。このため、より高温耐食、耐酸化性にすぐ
れたコーティングをもつ動・静翼の開発がまたれてい
る。In a gas turbine heated to a high temperature, the moving and stationary blades that come into direct contact with the combustion gas have an increased oxidation rate with an increase in the gas temperature. Even if the high temperature corrosive component is introduced from the fuel or combustion air, these will cause Z in the outermost layer.
The intermediate layer of NiCrAlY is transmitted through the rO 2 —Y 2 O 3 layer.
Alternatively, it reaches CoNiCrAlY and is corroded or oxidized at high temperature. As a result, corrosion or oxidation products are formed at the boundary between the intermediate layer and the outermost layer, and these are accompanied by volume expansion, so that it is often found that the ZrO 2 —Y 2 O 3 layer peels off. For this reason, the development of moving and stationary blades with coatings that are superior in high temperature corrosion resistance and oxidation resistance has been struggling.
【０００５】本発明は上記技術水準及び上記要望に応
じ、耐熱性、耐酸化性及び耐食性にすぐれた動・静翼の
表面層を提供しようとするものである。According to the above-mentioned state of the art and the above-mentioned demands, the present invention aims to provide a surface layer of a moving / stator blade having excellent heat resistance, oxidation resistance and corrosion resistance.
【０００６】[0006]
【課題を解決するための手段】本発明はＮｉＣｒＡｌＹ
又はＣｏＮｉＣｒＡｌＹ合金を低圧プラズマ溶射にてコ
ーティングした第１層、ＺｒＯ2 −Ｙ2 Ｏ3 を大気プラ
ズマ溶射してコーティングした第２層及び化学的蒸着又
は低圧プラズマ溶射にてコーティングした緻密なセラミ
ック層よりなる第３層からなる動・静翼表面層である。The present invention is directed to NiCrAlY.
Or a first layer coated with CoNiCrAlY alloy by low pressure plasma spraying, a second layer coated with ZrO 2 —Y 2 O 3 by atmospheric plasma spraying and a dense ceramic layer coated by chemical vapor deposition or low pressure plasma spraying It is a moving / stator blade surface layer consisting of a third layer.
【０００７】本発明は従来のものと同様に、中間層であ
るＮｉＣｒＡｌＹまたはＣｏＮｉＣｒＡｌＹとＺｒＯ2
−Ｙ2 Ｏ3 セラミック層をコーティングした構成は同一
であるが、本発明はさらに第３層として酸素透過量が少
なくなるようなセラミックよりなる材質（成分）、例え
ばＡｌ2 Ｏ3 ，Ｃｒ2 Ｏ3 ，ＭｇＯ，ＣａＯ，ＳｉＯ 2
などを選択し、これらを緻密にコーティングする手法、
例えば化学的蒸着法（ＣＶＤという）またはＶＰＳを採
用して付加したことに特徴があり、本発明の動・静翼表
面層はこれら３層をコーティングした後、熱処理するこ
とによって得られる。The present invention, like the prior art, uses an intermediate layer.
NiCrAlY or CoNiCrAlY and ZrO2
-Y2O3Same structure coated with ceramic layers
However, according to the present invention, as the third layer, the oxygen transmission amount is small.
Material (component) made of ceramic that disappears, for example
If Al2O3, Cr2O3, MgO, CaO, SiO 2
, Etc., and the method of coating these precisely,
For example, chemical vapor deposition (called CVD) or VPS is used.
It is characterized in that it is added by using
The surface layer should be heat treated after coating these three layers.
Obtained by.
【０００８】本発明の第１層であるＮｉＣｒＡｌＹは２
０〜２５ｗｔ％Ｃｒ，６〜８ｗｔ％Ａｌ，０．５〜１ｗ
ｔ％Ｙ，残部：Ｎｉよりなる合金が、ＣｏＮｉＣｒＡｌ
Ｙは２０〜２５ｗｔ％Ｃｒ，６〜８ｗｔ％Ａｌ，０．５
〜１ｗｔ％Ｙ，残部：Ｃｏ，ＮｉよりなりＣｏ／Ｎｉ比
が任意な合金が一般的に使用され、そのコーティングは
ＶＰＳで行われ、層厚は２０〜５０μｍである。The first layer of the present invention, NiCrAlY, is 2
0-25wt% Cr, 6-8wt% Al, 0.5-1w
t% Y, balance: Ni is an alloy consisting of CoNiCrAl
Y is 20 to 25 wt% Cr, 6 to 8 wt% Al, 0.5
An alloy consisting of ˜1 wt% Y, balance: Co, Ni and having an arbitrary Co / Ni ratio is generally used, the coating is performed by VPS, and the layer thickness is 20 to 50 μm.
【０００９】本発明の第２層であるＺｒＯ2 −Ｙ2 Ｏ3
セラミック層としては８〜２０ｗｔ％Ｙ2 Ｏ3 ，残部Ｚ
ｒＯ2 よりなる安定化ジルコニアが一般的に用いられ、
そのコーティングはＡＰＳで行われ、その層厚は一般的
に１００〜５００μｍである。The second layer of the present invention, ZrO 2 --Y 2 O 3
The ceramic layer is 8 to 20 wt% Y 2 O 3 , the balance Z
Stabilized zirconia consisting of rO 2 is commonly used,
The coating is performed with APS and the layer thickness is generally 100-500 μm.
【００１０】本発明の第３層である緻密なセラミック層
としては上述したものが使用されるが、第２層のＺｒＯ
2 −Ｙ2 Ｏ3 層の熱膨張率に近いものを選択して、熱膨
張率の差によって剥離、割れが生じ難くすることが好ま
しい。ＺｒＯ2 −Ｙ2 Ｏ3 の熱膨張率は１０×１０-6／
Ｋであるので、これに比較的に熱膨張率が近いＡｌ2Ｏ
3 （８．１×１０-6／Ｋ）、Ｃｒ2 Ｏ3 （８．７×１０
-6／Ｋ）などが好ましく、また、これらのコーティング
方法は酸素及び腐食性成分の透過を抑える目的で緻密な
膜とする必要からＣＶＤ，ＶＰＳを採用すべきである。
また、その層厚は一般的には１０〜５０μｍである。As the dense ceramic layer which is the third layer of the present invention, the above-mentioned ones are used, but the second layer of ZrO 2 is used.
It is preferable to select a material having a thermal expansion coefficient close to that of the 2- Y 2 O 3 layer so that peeling and cracking are less likely to occur due to the difference in thermal expansion coefficient. The thermal expansion coefficient of ZrO 2 —Y 2 O 3 is 10 × 10 −6 /
Since it is K, Al 2 O having a coefficient of thermal expansion relatively close to that of Al 2 O
3 (8.1 × 10 −6 / K), Cr 2 O 3 (8.7 × 10
-6 / K) and the like, and these coating methods should employ CVD and VPS because it is necessary to form a dense film for the purpose of suppressing permeation of oxygen and corrosive components.
The layer thickness is generally 10 to 50 μm.
【００１１】[0011]
【作用】本発明方法で製作した３層構造の表面層の遮熱
コーティングの作用は、最表面層の緻密セラミックコー
ティングが酸素又は腐食性成分を母材から隔離し、母材
の酸化、腐食を防止する。すなわち、ＺｒＯ2 −Ｙ2 Ｏ
3 は遮熱効果は有するが酸素透過性能が大きいため簡単
に酸素を母材まで移動させ、その結果、母材を酸化、腐
食させるが、本発明の第３層のコーティングにより外界
からの酸素、腐食性成分を遮断させることを可能とする
ほか、それ自身も遮熱効果を有するので表面層の耐熱性
も向上させる。The effect of the thermal barrier coating on the surface layer of the three-layer structure manufactured by the method of the present invention is that the dense ceramic coating of the outermost surface layer separates oxygen or corrosive components from the base material, and prevents oxidation and corrosion of the base material. To prevent. That is, ZrO 2 —Y 2 O
Although 3 has a heat shield effect, but has a large oxygen permeability, oxygen is easily moved to the base material, and as a result, the base material is oxidized and corroded. In addition to making it possible to block corrosive components, it also has a heat-shielding effect by itself, thus improving the heat resistance of the surface layer.
【００１２】本発明の動・静翼表面層による遮熱効果の
原理を図２に示す。図２において、ＴＢＣとは熱遮蔽コ
ーティング（ Thermal Barrer Coating ) を意味する。FIG. 2 shows the principle of the heat shield effect of the surface layer of the moving / stator blade of the present invention. In FIG. 2, TBC means a thermal barrier coating.
【００１３】[0013]
【実施例】本発明の実施例を図１によって説明する。図
１はガスタービン動・静翼材に用いられる耐熱合金ＥＣ
Ｙ７６８（Ｃｏベース）、ＩＮ７３８ＬＣ（Ｎｉベー
ス）の合金基材１に、先ずＶＰＳにてＮｉＣｒＡｌＹ
（２０〜２５ｗｔ％Ｃｒ，６〜８ｗｔ％Ａｌ，０．５〜
１ｗｔ％Ｙ，残部Ｎｉ）又はＣｏＮｉＣｒＡｌＹ（２０
〜２５ｗｔ％Ｃｒ，６〜８ｗｔ％Ａｌ，０．５〜１ｗｔ
％Ｙ，残部Ｃｏ，Ｎｉ、Ｃｏ／Ｎｉ比は任意）よりなる
２０〜５０μｍ厚の第１層２を形成し、その上にＡＰＳ
にてＺｒＯ2 −Ｙ2 Ｏ3 （Ｙ2 Ｏ3 ：８〜２０％、Ｚｒ
Ｏ2 ：残部）よりなる１００〜５００μｍ厚の第２層３
を形成し、さらにその上にＣＶＤ又はＶＰＳにてセラミ
ック層よりなる１０〜５０μｍ厚の第３層４を形成させ
た後、熱処理して動・静翼表面層を得た。Embodiment An embodiment of the present invention will be described with reference to FIG. Figure 1 is a heat-resistant alloy EC used for gas turbine dynamic and stationary vane materials.
Y768 (Co base), IN738LC (Ni base) alloy base material 1 is first coated with NiCrAlY by VPS.
(20-25 wt% Cr, 6-8 wt% Al, 0.5-
1 wt% Y, balance Ni) or CoNiCrAlY (20
-25 wt% Cr, 6-8 wt% Al, 0.5-1 wt
% Y, the balance Co, Ni, and the Co / Ni ratio are arbitrary), and a first layer 2 having a thickness of 20 to 50 μm is formed, and APS is formed thereon.
ZrO 2 -Y 2 O 3 (Y 2 O 3 at: 8 to 20%, Zr
O 2 : the remainder) 100 to 500 μm thick second layer 3
Was further formed, and a third layer 4 of a ceramic layer having a thickness of 10 to 50 μm was formed thereon by CVD or VPS, followed by heat treatment to obtain a moving / stator vane surface layer.
【００１４】その具体例を下記表１に示す。Specific examples thereof are shown in Table 1 below.
【表１】 [Table 1]
【００１５】上記具体例の動・静翼表面層及び第１層が
ＣｏＮｉＣｒＡｌＹ：５０μｍ、第２層がＺｒＯ2 −Ｙ
2 Ｏ3 ：２００μｍよりなるコーティング層の従来例
９、第１層がＮｉＣｒＡｌＹ：３０μｍ、第２層がＺｒ
Ｏ2 −Ｙ2 Ｏ3 ：２５０μｍよりなるコーティング層の
従来例１０を、９００℃（１５分間）と室温（１５分
間）の間のヒートサイクル試験によるコーティング層の
密着性確認試験結果を、まとめて図３に示す。図３よ
り、従来例９，１０では４５０〜５００サイクルでＺｒ
Ｏ2 −Ｙ2 Ｏ3 層が剥離したのに対し、本発明の具体例
では最低でも８５０サイクル（具体例８）の耐久性を示
し、具体例３，６などでは１０００サイクル以上の耐久
性を示した。In the above-mentioned specific example, the surface layer of the moving and stationary vanes and the first layer are CoNiCrAlY: 50 μm, and the second layer is ZrO 2 -Y.
Conventional example 9 of coating layer consisting of 2 O 3 : 200 μm, first layer is NiCrAlY: 30 μm, second layer is Zr
The conventional example 10 of the coating layer composed of O 2 —Y 2 O 3 : 250 μm was used to summarize the adhesion confirmation test results of the coating layer by the heat cycle test between 900 ° C. (15 minutes) and room temperature (15 minutes). As shown in FIG. From FIG. 3, in the conventional examples 9 and 10, Zr is 450-500 cycles.
While the O 2 —Y 2 O 3 layer was peeled off, the specific examples of the present invention showed durability of at least 850 cycles (specific example 8), and the specific examples 3 and 6 exhibited durability of 1000 cycles or more. Indicated.
【００１６】また、１０００℃大気中、５０００時間加
熱による高温酸化条件における高温酸化試験の結果を図
４に示す。この結果、従来例９，１０はＣｏＮｉＣｒＡ
ｌＹ又はＮｉＣｒＡｌＹとＺｒＯ2 −Ｙ2 Ｏ3 の界面に
１１〜１５μｍ厚さの酸化皮膜が生成したのに対し、本
発明ではその酸化皮膜は約２μｍ以下であって、酸素透
過防止効果が優れていることが確認された。FIG. 4 shows the result of a high temperature oxidation test under high temperature oxidation conditions by heating at 1000 ° C. in the atmosphere for 5000 hours. As a result, in Conventional Examples 9 and 10, CoNiCrA was used.
While an oxide film with a thickness of 11 to 15 μm was formed at the interface between 1Y or NiCrAlY and ZrO 2 —Y 2 O 3 , in the present invention, the oxide film has a thickness of about 2 μm or less, which is excellent in the effect of preventing oxygen permeation. Was confirmed.
【００１７】[0017]
【発明の効果】本発明の動・静翼表面層は３層構造を有
しているので、耐熱性、耐酸化性及び耐食性に優れてい
るものが得られる。Since the surface layer of the moving and stationary blades of the present invention has a three-layer structure, it is possible to obtain one having excellent heat resistance, oxidation resistance and corrosion resistance.
【図１】本発明の動・静翼表面層の構成の説明図FIG. 1 is an explanatory diagram of a structure of a moving / stator blade surface layer of the present invention.
【図２】本発明の動・静翼表面層による遮熱効果の説明
図FIG. 2 is an explanatory view of a heat shield effect by the surface layer of the moving / stator blade of the present invention.
【図３】本発明の動・静翼表面層のヒートサイクル試験
の結果を示す図表FIG. 3 is a chart showing the results of a heat cycle test of the surface layer of the moving and stationary blades of the present invention.
【図４】本発明の動・静翼表面層の高温酸化試験の結果
を示す図表FIG. 4 is a chart showing the results of a high temperature oxidation test of the surface layer of the moving and stationary blades of the present invention.
───────────────────────────────────────────────────── フロントページの続き (72)発明者 高橋 孝二 兵庫県高砂市荒井町新浜二丁目１番１号 三菱重工業株式会社高砂製作所内 (72)発明者 北井 敬人 兵庫県高砂市荒井町新浜二丁目１番１号 三菱重工業株式会社高砂製作所内 ─────────────────────────────────────────────────── ─── Continuation of front page (72) Inventor Koji Takahashi 2-1-1, Niihama, Arai-cho, Takasago-shi, Hyogo Mitsubishi Heavy Industries, Ltd. Takasago Works (72) Inventor Keito Kitai 2-chome, Niihama, Arai-cho, Takasago-shi, Hyogo No. 1 Mitsubishi Heavy Industries Takasago Plant
Claims (1)
合金を低圧プラズマ溶射にてコーティングした第１層、
ＺｒＯ2 −Ｙ2 Ｏ3 を大気プラズマ溶射してコーティン
グした第２層及び化学的蒸着又は低圧プラズマ溶射にて
コーティングした緻密なセラミック層よりなる第３層か
らなる動・静翼表面層。1. NiCrAlY or CoNiCrAlY
First layer coated with alloy by low pressure plasma spraying,
Second layer and the dynamic-stationary blade surface layer and a third layer made of a dense ceramic layer coated by a chemical vapor deposition or low pressure plasma spraying of the ZrO 2 -Y 2 O 3 was coated by air plasma spraying.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4125240A JP2977369B2 (en) | 1992-05-19 | 1992-05-19 | Moving and stationary blade surface layer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4125240A JP2977369B2 (en) | 1992-05-19 | 1992-05-19 | Moving and stationary blade surface layer |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH0688197A true JPH0688197A (en) | 1994-03-29 |
| JP2977369B2 JP2977369B2 (en) | 1999-11-15 |
Family
ID=14905263
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP4125240A Expired - Lifetime JP2977369B2 (en) | 1992-05-19 | 1992-05-19 | Moving and stationary blade surface layer |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2977369B2 (en) |
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| JP2007262447A (en) * | 2006-03-27 | 2007-10-11 | Mitsubishi Heavy Ind Ltd | Oxidation-resistant film and its deposition method, thermal barrier coating, heat-resistant member, and gas turbine |
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1992
- 1992-05-19 JP JP4125240A patent/JP2977369B2/en not_active Expired - Lifetime
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| JP2977369B2 (en) | 1999-11-15 |
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