JPH10195629A - Gas turbine blade and method for forming film thereon - Google Patents
Gas turbine blade and method for forming film thereonInfo
- Publication number
- JPH10195629A JPH10195629A JP35024796A JP35024796A JPH10195629A JP H10195629 A JPH10195629 A JP H10195629A JP 35024796 A JP35024796 A JP 35024796A JP 35024796 A JP35024796 A JP 35024796A JP H10195629 A JPH10195629 A JP H10195629A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- gas turbine
- oxide film
- film
- thickness
- 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- Withdrawn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
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- Turbine Rotor Nozzle Sealing (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、ガスタービンにお
いて、後段動翼に適用される高温燃焼ガスに対する耐蝕
性表面処理に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a corrosion-resistant surface treatment for a high-temperature combustion gas applied to a downstream rotor blade in a gas turbine.
【０００２】[0002]
【従来の技術】発電用ガスタービンにおいては、ランニ
ングコスト低減のため、低質燃料を使用することが近年
の傾向にあり、タービン翼は従来に比べて高温腐食環境
にある場合が多い。2. Description of the Related Art In a gas turbine for power generation, there is a recent tendency to use a low-quality fuel in order to reduce running costs, and turbine blades are often in a high-temperature corrosive environment as compared with the conventional case.
【０００３】通常ガスタービンは油燃料１ｋｇに対して
燃焼用空気は約５０ｍ3 を要し、この多量の空気を大気
から吸い込むため、設置位置が工場地帯や海岸の周辺の
ような場合にあっては、大気中のナトリウム（Ｎａ）や
塩素（Ｃｌ）等の微量の腐食成分も、タービン翼の高温
腐食の原因となっている。In general, a gas turbine requires about 50 m 3 of combustion air for 1 kg of oil fuel. Since a large amount of air is sucked from the atmosphere, the gas turbine is installed in a factory area or near a coast. In addition, trace amounts of corrosive components such as sodium (Na) and chlorine (Cl) in the atmosphere also cause high-temperature corrosion of turbine blades.
【０００４】従って従来のこのような使用環境にあるガ
スタービンでは、ガス温度が高く腐食性の厳しい前段翼
には、耐高温腐食性皮膜材がコーティング（被覆、皮膜
処理）されてきた。例えば、その代表的なものとして
は、被覆材として、コバルト（Ｃｏ）、ニッケル（Ｎ
ｉ）、クロム（Ｃｒ）、アルミニウム（Ａｌ）又は／及
びイットリウム（Ｙ）等の合金粉末を選び、プラズマ溶
射等により皮膜形成をすることで対応している。Accordingly, in a conventional gas turbine in such a use environment, a high-temperature corrosion-resistant coating material has been coated (coated, coated) on a front-stage blade having a high gas temperature and severe corrosiveness. For example, typical examples thereof include cobalt (Co), nickel (N
i), an alloy powder such as chromium (Cr), aluminum (Al) and / or yttrium (Y) is selected, and a film is formed by plasma spraying or the like.
【０００５】[0005]
【発明が解決しようとする課題】しかしながら前記した
ような従来のコーティングは一般にコストが高く、かつ
溶射装置の容器容量の制約から、形状寸法の大きい後段
の大型翼には適用が困難であり、Ｎｉ基超耐熱合金のＵ
ｄｉｍｅｔ５２０（商品名）の鍛造翼では、機械加工後
のアルミナ（Ａｌ2 Ｏ3 ）粒子によるショットプラスト
の最終製造工程を以て、また、ＩＮ７３８ＬＣ（商品
名）の真空精密鋳造翼では、真空熱処理の最終製造工程
を以てそれぞれ実機に供せられていた。However, the conventional coating as described above is generally expensive and is difficult to apply to a large-sized blade at a later stage having a large shape and size due to the limitation of the capacity of the container of the thermal spraying apparatus. Base super heat resistant alloy U
The forged wing of dimet 520 (trade name) has a final manufacturing process of shot plasts using alumina (Al 2 O 3 ) particles after machining, and the vacuum precision casting wing of IN738LC (trade name) has final production of vacuum heat treatment. Each process was provided to the actual machine.
【０００６】しかも近年全国的に大気環境が悪化した状
況下にあっては、ガスタービンは非常に厳しい高温腐蝕
環境に置かれており、前段のタービン翼のみならず、後
段のタービン翼においても、結晶粒界に腐食性成分が侵
入し、粒界を弱化して亀裂を生じさせるという顕著な腐
食損傷を発生させるおそれがあり、後段タービン翼の耐
高温腐食性の向上は強く望まれるようになって来てい
る。[0006] In recent years, in a situation where the atmospheric environment has deteriorated nationwide, gas turbines are placed in a very severe high-temperature corrosive environment, and not only in the preceding turbine blades but also in the subsequent turbine blades. Corrosive components may enter the grain boundaries and cause significant corrosion damage, which weakens the grain boundaries and causes cracks.Therefore, it is strongly desired to improve the high-temperature corrosion resistance of the subsequent turbine blades. Are coming.
【０００７】本発明はこのようなニーズに応えて、耐高
温腐食性に優れた表面処理を施した後段動翼及び同後段
動翼の表面処理である皮膜形成方法を提供することを課
題とするものである。SUMMARY OF THE INVENTION [0007] An object of the present invention is to provide a post-stage moving blade having a surface treatment excellent in high-temperature corrosion resistance and a method for forming a film which is a surface treatment of the post-stage moving blade in response to such needs. Things.
【０００８】[0008]
【課題を解決するための手段】本発明は前記した課題を
解決するべくなされたものであり、翼表面に厚さ１μｍ
以上のクロム酸化物皮膜を形成したガスタービン翼を提
供し、ガスタービン翼の、特に好ましくは後段の翼の表
面に、１ｍμ以上の厚さにクロム酸化物皮膜を積極的に
形成し、同皮膜により翼基材の高温腐食の開始時期を大
巾に遅らせるようにしたものである。SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned problems, and has a thickness of 1 .mu.m on a blade surface.
Provided is a gas turbine blade having the above chromium oxide film formed thereon, wherein a chromium oxide film is positively formed to a thickness of 1 mμ or more on the surface of the gas turbine blade, particularly preferably the latter stage blade. This significantly delays the start of high-temperature corrosion of the blade base material.
【０００９】また、本発明は、翼表面に厚さ１μｍ〜３
μｍのクロム酸化物皮膜を形成したガスタービン翼を提
供し、ガスタービン翼の、特に好ましくは後段の翼の表
面に形成するクロム酸化物皮膜の厚さは少なくとも１μ
ｍ、そして最高３μｍの範囲とし、この特定された厚さ
の皮膜により翼基材の高温腐食の開始時期を大巾に遅ら
せるようにしたものである。Further, according to the present invention, a thickness of 1 μm to 3 μm
A gas turbine blade provided with a chromium oxide film having a thickness of at least 1 μm is provided on the surface of the gas turbine blade, particularly preferably on the surface of a subsequent blade.
m, and up to 3 μm, with the specified thickness of the coating significantly delaying the onset of hot corrosion of the blade substrate.
【００１０】また、本発明は、翼表面にクロム酸化物皮
膜を施すガスタービン翼の皮膜形成方法において、 ２１≦（Ｔ＋２７３）×（２０＋ｌｏｇ10ｔ）×１０-3 〔但し、加熱処理時間ｔは；０．５≦ｔ≦４０[Hr]〕 を満たす温度Ｔ〔℃〕にて大気中で加熱処理するように
したガスタービン翼の皮膜形成方法を提供し、前記関係
式を満す温度Ｔと加熱処理時間ｔとの関連に於てガスタ
ービン翼の表面に形成される皮膜により、翼基材の高温
腐食の開始時期を大巾に遅らせるようにしたものであ
る。Further, the present invention provides a method for forming a film of a gas turbine blade in which a chromium oxide film is formed on a blade surface, wherein 21 ≦ (T + 273) × (20 + log 10 t) × 10 −3 [where the heat treatment time t is A method for forming a coating film on a gas turbine blade at a temperature T [° C.] that satisfies 0.5 ≦ t ≦ 40 [Hr] ]. The coating formed on the surface of the gas turbine blade in relation to the heat treatment time t greatly delays the start of high-temperature corrosion of the blade base material.
【００１１】[0011]
【発明の実施の形態】本発明の実施の一形態を図に基づ
いて説明する。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS One embodiment of the present invention will be described with reference to the drawings.
【００１２】図１に示すように、ガスタービンの後段動
翼、具体的には第４段動翼２（基材：Ｎｉ基超合金であ
るＵｄｉｍｅｔ５２０（商品名））をショットプラスト
を行い表面の油脂や付着物を除去したあと、大気加熱炉
１に装入した。As shown in FIG. 1, a rear stage rotor blade of a gas turbine, specifically, a fourth stage rotor blade 2 (base material: Udimet 520 (trade name), which is a Ni-base superalloy) is shot-plasted to perform surface blasting. After removing fats and oils and deposits, the mixture was charged into the atmospheric heating furnace 1.
【００１３】ここで用いたＵｄｉｍｅｔ５２０（商品
名）合金の化学組成は次表の通りである。The chemical composition of Udimet 520 (trade name) alloy used here is as shown in the following table.
【００１４】[0014]
【表１】 [Table 1]
【００１５】そして処理した動翼２は、長さが８００ｍ
ｍ以上ある長大翼であり、真空プラズマ溶射の適用は困
難なものである。また、大気加熱炉１は、実際の加熱処
理を出来るだけ模擬するために均熱域が高さ１ｍ，幅１
ｍ，奥行き３ｍの大型のものを使用した。The processed rotor blade 2 has a length of 800 m.
m or more, and it is difficult to apply vacuum plasma spraying. The atmosphere heating furnace 1 has a soaking zone of 1 m in height and 1 m in width in order to simulate the actual heat treatment as much as possible.
m, 3 m depth.
【００１６】この動翼２は７５０℃に加熱して３時間保
持することにより、タービン翼の表面に厚さ約１μｍの
耐食性のある強固な酸化クロム（Ｃｒ2 Ｏ3 ）の保護皮
膜を形成した。The moving blade 2 was heated to 750 ° C. and maintained for 3 hours to form a strong corrosion-resistant and strong chromium oxide (Cr 2 O 3 ) protective film having a thickness of about 1 μm on the surface of the turbine blade. .
【００１７】図２に前記翼２（ａ図参照）の断面の一部
（ｂ図参照）を拡大して前記酸化処理により形成した酸
化クロム（Ｃｒ2 Ｏ3 ）保護皮膜を概念的に表示した
（ｃ図参照）。母材（基材）上面に全域に亘って１μｍ
またはそれ以上の皮膜が形成されていることがわかる。FIG. 2 conceptually shows a chromium oxide (Cr 2 O 3 ) protective film formed by the oxidation treatment by enlarging a part (see FIG. 2B) of the cross section of the blade 2 (see FIG. 2A). (See figure c). 1 μm over the entire surface of the base material (base material)
Or it turns out that the film of more than that is formed.
【００１８】なお、前記した大気加熱条件（７５０℃、
３時間）の設定根拠は、以下の通りである。The above-mentioned atmospheric heating conditions (750 ° C.,
The reason for setting 3 hours) is as follows.
【００１９】Ｕｄｉｍｅｔ５２０（商品名）合金におけ
る大気加熱条件と酸化皮膜厚さの関係は図３に示すよう
になっている。同図３において横軸はラーソン・ミラー
・パラメータ（Ｌａｒｓｏｎ Ｍｉｌｌｅｒ Ｐａｒａ
ｍｅｔｅｒ 以下、ＬＭＰと略す）で、これは温度Ｔ
（℃）と時間ｔ（Ｈｒ）とのパラメータで、温度が高い
ほど、また時間が長いほどこのＬＭＰは大きくなる。FIG. 3 shows the relationship between the atmospheric heating conditions and the thickness of the oxide film in Udimet 520 (trade name) alloy. In FIG. 3, the horizontal axis represents the Larson Miller parameter.
(hereinafter abbreviated as LMP), which is the temperature T
With the parameters of (° C.) and time t (Hr), the higher the temperature and the longer the time, the larger the LMP.
【００２０】一般に酸化被膜の厚さは、このＬＭＰによ
り整理でき、所望の厚さの酸化被膜を得るには、ＬＭＰ
さえ合わせておけばよい。In general, the thickness of the oxide film can be controlled by the LMP.
You only have to match.
【００２１】耐食性の皮膜として明確な効果を得るため
には、酸化皮膜の厚さを１μｍ以上とする条件、即ち、
ＬＭＰが２１以上を選ぶ必要がある。この関係を数式で
整理すると、次の様になる。In order to obtain a clear effect as a corrosion-resistant film, the thickness of the oxide film must be 1 μm or more, ie,
It is necessary to select LMP of 21 or more. This relationship can be summarized as follows.
【００２２】 ＬＭＰ＝（Ｔ＋２７３）（２０＋ｌｏｇ10ｔ）×１０-3 ここでＴは温度℃、ｔは加熱処理時間Ｈｒである。LMP = (T + 273) (20 + log 10 t) × 10 −3 where T is temperature ° C and t is heat treatment time Hr.
【００２３】前記したように、酸化皮膜の厚さを１μｍ
とすると、ＬＭＰは２１となるので、前記数式において
ＬＭＰを２１としてＴとｔの関係を求めると、例えば、
７００℃で約４０時間、７５０℃で約３時間、８００℃
で約０．５時間という関係がある。As described above, the thickness of the oxide film is 1 μm
Then, since LMP is 21, the relationship between T and t is determined by setting LMP to 21 in the above equation.
About 40 hours at 700 ° C, about 3 hours at 750 ° C, 800 ° C
There is a relationship of about 0.5 hours.
【００２４】一方、Ｕｄｉｍｅｔ５２０（商品名）合金
の通常の熱処理における最終時効処理は、通常７６０℃
にて行われるため、酸化処理条件はこの最終時効処理温
度以下であり、かつ経済的に短時間で実施できる条件で
ある必要がある。この理由から本実施例のＵｄｉｍｅｔ
５２０（商品名）合金の場合、７５０℃×３Ｈｒが最も
好ましい条件と見られる。On the other hand, the final aging treatment in the usual heat treatment of Udimet 520 (trade name) alloy is usually 760 ° C.
Therefore, the oxidation treatment conditions must be lower than or equal to the final aging treatment temperature and can be carried out economically in a short time. For this reason, the Udimet of this embodiment is
In the case of 520 (trade name) alloy, 750 ° C. × 3 hours is considered to be the most preferable condition.
【００２５】なお、これら動翼材料と酸化処理条件の組
み合わせは、翼材質や翼形状の違いを考慮して、適宜、
適切なものを選択することが出来ることは勿論である。The combination of the blade material and the oxidation treatment conditions is appropriately determined in consideration of the difference in blade material and blade shape.
Of course, it is possible to select an appropriate one.
【００２６】前記のようにして形成した皮膜の耐高温腐
食性の確認を、本実施の形態による酸化皮膜を施した試
験片と従来の無処理の試験片及び酸化皮膜を形成するが
その厚さを１μｍよりも薄くした試験片とを溶融塩中の
浸漬腐食試験にて実施した（基材はいずれも、Ｕｄｉｍ
ｅｔ５２０（商品名）合金）。The high temperature corrosion resistance of the film formed as described above was confirmed by determining the test piece provided with the oxide film according to the present embodiment, the conventional untreated test piece and the oxide film. And a test piece having a thickness of less than 1 μm was subjected to an immersion corrosion test in a molten salt (all substrates were Udim
et520 (trade name) alloy).
【００２７】即ち、腐食性の溶融塩（４０％ＣａＳ
Ｏ4 ，４０％Ｎａ2 ＳＯ4 ，１０％ＮａＣｌ，１０％Ｚ
ｎＣｌ2 ）の中に試験片を浸漬した状態で、加速腐食試
験を実施しその結果を次の表にとりまとめた。That is, a corrosive molten salt (40% CaS
O 4 , 40% Na 2 SO 4 , 10% NaCl, 10% Z
An accelerated corrosion test was performed with the test piece immersed in nCl 2 ), and the results were summarized in the following table.
【００２８】[0028]
【表２】 [Table 2]
【００２９】本実施の形態による厚さ１μｍ以上の酸化
皮膜を持つ酸化処理材は、無処理材（比較材）の約１
／２〜１／３倍の重量減少であった。The oxidized material having an oxide film having a thickness of 1 μm or more according to the present embodiment is about 1% of the untreated material (comparative material).
The weight was reduced by a factor of ２〜 to １ ／.
【００３０】また、酸化皮膜は持つがその厚さが１μｍ
より薄い場合（比較材）、無処理のものよりも重量減
少は少ないものの、その効果は低いことがわかった。Further, although it has an oxide film, its thickness is 1 μm.
When the thickness was thinner (comparative material), it was found that the weight loss was smaller than that of the untreated material, but the effect was low.
【００３１】また、試験後の試験片の断面を観察する
と、無処理材では粒界浸食が著しかったのに対し、本実
施の形態による厚さ１μｍ以上の酸化皮膜を持つ酸化処
理材は粒界浸食が軽微であり、浸食深さで無処理材の約
１／１０程度であった。When the cross section of the test piece after the test was observed, the grain boundary erosion was remarkable in the untreated material, whereas the oxidized material having an oxide film having a thickness of 1 μm or more according to the present embodiment was found to have a grain boundary erosion. The erosion was slight, and the erosion depth was about 1/10 of the untreated material.
【００３２】なお、ここでは熱処理するタービン翼２は
鍛造翼をイメージして説明したが、これは鋳造翼であっ
ても実質的に同一である。ただ、詳しく言えば鍛造翼の
場合は鍛造における最終工程のショットブラスト処理を
経て完成したものを大気中加熱処理を行い翼表面にクロ
ム酸化物の皮膜を形成するか、鋳造（精密鋳造）翼の場
合には最終工程の真空熱処理のうち最後の時効熱処理を
大気中で行い、その後は前記と全て同様に翼表面にクロ
ム酸化皮膜を形成することになる。Here, the turbine blade 2 to be subjected to the heat treatment has been described as a forged blade, but this is substantially the same even if it is a cast blade. However, to be more specific, in the case of forged blades, the ones that have been completed through shot blasting in the final step of forging are subjected to heat treatment in the air to form a chromium oxide film on the blade surface, or to use casting (precision casting) blades. In this case, the last aging heat treatment among the vacuum heat treatments in the final step is performed in the air, and thereafter, a chromium oxide film is formed on the blade surface in the same manner as described above.
【００３３】[0033]
【発明の効果】以上、本発明によれば、耐高温腐食性に
優れたＣｒ2 Ｏ3 表面被膜を表面処理により形成した後
段動翼により、腐食損傷の防止を図ることができ、ひい
ては、ガスタービンの信頼性・耐久性の向上に寄与する
ものである。As described above, according to the present invention, corrosion damage can be prevented by the latter stage blade having a Cr 2 O 3 surface coating excellent in high-temperature corrosion resistance formed by a surface treatment. This contributes to the improvement of the reliability and durability of the turbine.
【図１】本発明の実施の一形態に係る翼の表面処理工程
の概要を示し、（ａ）は処理されるタービン翼の斜視
図、（ｂ）は大気加熱炉内２の処理状況の説明図。FIG. 1 shows an outline of a blade surface treatment step according to an embodiment of the present invention, in which (a) is a perspective view of a turbine blade to be treated, and (b) is a description of a treatment situation in an atmosphere heating furnace 2; FIG.
【図２】図１の工程で処理された翼の皮膜の概念を示
し、（ａ）は皮膜を形成されたタービン翼の斜視図、
（ｂ）は（ａ）のＢ−Ｂ断面の説明図、（ｃ）は（ｂ）
の要部を拡大した皮膜の概念図。FIG. 2 shows the concept of a blade coating treated in the step of FIG. 1, wherein (a) is a perspective view of a turbine blade having the coating formed thereon,
(B) is an explanatory view of the BB section of (a), (c) is (b)
The conceptual diagram of the film which expanded the principal part of.
【図３】大気加熱条件（ＬＭＰ）と皮膜の厚さとの関係
を示す説明図。FIG. 3 is an explanatory diagram showing the relationship between atmospheric heating conditions (LMP) and the thickness of a film.
１ 大気加熱炉 ２ タービン翼 1 Atmospheric heating furnace 2 Turbine blade
Claims (3)
皮膜を形成したことを特徴とするガスタービン翼。1. A gas turbine blade having a chromium oxide film having a thickness of 1 μm or more formed on a blade surface.
化物皮膜を形成したことを特徴とするガスタービン翼。2. A gas turbine blade having a chromium oxide film having a thickness of 1 μm to 3 μm formed on a blade surface.
ービン翼の皮膜形成方法において、 ２１≦（Ｔ＋２７３）×（２０＋ｌｏｇ10ｔ）×１０-3 〔但し、加熱処理時間ｔは；０．５≦ｔ≦４０[Hr]〕 を満たす温度Ｔ〔℃〕にて大気中で加熱処理することを
特徴とするガスタービン翼の皮膜形成方法。3. A gas turbine blade coating method for forming a chromium oxide film on a blade surface, comprising: 21 ≦ (T + 273) × (20 + log 10 t) × 10 −3 [where the heat treatment time t is 0.5 ≦ t ≦ 40 [Hr] ]. A method for forming a coating film on a gas turbine blade, wherein the heating treatment is performed in the atmosphere at a temperature T [° C.].
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP35024796A JPH10195629A (en) | 1996-12-27 | 1996-12-27 | Gas turbine blade and method for forming film thereon |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP35024796A JPH10195629A (en) | 1996-12-27 | 1996-12-27 | Gas turbine blade and method for forming film thereon |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH10195629A true JPH10195629A (en) | 1998-07-28 |
Family
ID=18409218
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP35024796A Withdrawn JPH10195629A (en) | 1996-12-27 | 1996-12-27 | Gas turbine blade and method for forming film thereon |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH10195629A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6352041B1 (en) * | 2001-02-13 | 2002-03-05 | United Microelectronics Corp. | Method for preventing corrosion of a furnace |
| JP2006283759A (en) * | 2005-03-31 | 2006-10-19 | General Electric Co <Ge> | Turbine constituent and its manufacturing method |
-
1996
- 1996-12-27 JP JP35024796A patent/JPH10195629A/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6352041B1 (en) * | 2001-02-13 | 2002-03-05 | United Microelectronics Corp. | Method for preventing corrosion of a furnace |
| JP2006283759A (en) * | 2005-03-31 | 2006-10-19 | General Electric Co <Ge> | Turbine constituent and its manufacturing method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A300 | Withdrawal of application because of no request for examination |
Free format text: JAPANESE INTERMEDIATE CODE: A300 Effective date: 20040302 |