JPH0424525B2 - - Google Patents
Info
- Publication number
- JPH0424525B2 JPH0424525B2 JP57079114A JP7911482A JPH0424525B2 JP H0424525 B2 JPH0424525 B2 JP H0424525B2 JP 57079114 A JP57079114 A JP 57079114A JP 7911482 A JP7911482 A JP 7911482A JP H0424525 B2 JPH0424525 B2 JP H0424525B2
- Authority
- JP
- Japan
- Prior art keywords
- corrosion
- layer
- laser beam
- turbine blade
- welding
- 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.)
- Expired - Lifetime
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
【発明の詳細な説明】
〔発明の技術分野〕
本発明は火力，原子力及び地熱発電用タービン
のような湿り蒸気中で使用されるタービン羽根の
製造方法に関するものである。DETAILED DESCRIPTION OF THE INVENTION [Technical Field of the Invention] The present invention relates to a method for manufacturing turbine blades used in wet steam, such as turbines for thermal, nuclear, and geothermal power generation.
火力発電用蒸気タービンの低圧最終段などの如
く湿り蒸気の範囲気中で使用される羽根は、蒸気
中の水滴の衝突によつて羽根面が侵食されるのを
防止する目的で、第１図，第２図および第３図に
示すように羽根１の先端部の蒸気流入端に耐食性
材料より成る防食片２が取りつけられている。
Blades used in humid steam, such as in the low-pressure final stage of a steam turbine for thermal power generation, are designed to prevent the blade surface from being eroded by collisions with water droplets in the steam, as shown in Figure 1. As shown in FIGS. 2 and 3, a corrosion-resistant piece 2 made of a corrosion-resistant material is attached to the steam inflow end of the tip of the blade 1. As shown in FIGS.
12クロムマルテンサイト系ステンレス鋼より成
るタービン羽根１とインコネル６２５等の防食片
２は従来銀ろう付、あるいはTIG溶接，電子ビー
ム溶接等によつて接合されているが、しかし、こ
れ等の溶接には次の様な欠点がある。即ち、第４
図に示すように、矢印の方向に溶接を行なつてゆ
くと、タービン羽根１の母材の熱膨張係数と防食
片２の材料の熱膨張係数とに差があることによつ
て溶接中あるいは溶接後に防食片２がそり返り充
分な溶接が行なえない。従つて第５図に示すよう
に、あらかじめ溶接線の数ケ所を仮止め溶接して
おき、充分な拘束を与えてから本溶接を行なつて
いた。しかし、これでは溶接後に大きな残留応力
が生じ、この残留応力と蒸気中に含まれる塩素イ
オンにより、タービン運転中に防食片および防食
片２の近傍のタービン羽根に応力腐食割れが発生
し、タービンの運転に重大な影響を及ぼし大きな
問題点となつている。この応力腐食割れは強力な
拘束力による残留応力に起因するもので、防食片
２の取付けを溶接によつて行なつている限り避け
られない。 The turbine blade 1 made of 12 chromium martensitic stainless steel and the anti-corrosion piece 2 made of Inconel 625 are conventionally joined by silver brazing, TIG welding, electron beam welding, etc. has the following drawbacks: That is, the fourth
As shown in the figure, when welding is carried out in the direction of the arrow, there is a difference between the coefficient of thermal expansion of the base material of the turbine blade 1 and that of the material of the anti-corrosion piece 2. The anti-corrosion piece 2 warps after welding, making it impossible to perform sufficient welding. Therefore, as shown in FIG. 5, the weld line was temporarily welded at several locations in advance, and the actual welding was performed after sufficient restraint was applied. However, this creates a large residual stress after welding, and due to this residual stress and chlorine ions contained in the steam, stress corrosion cracking occurs in the anti-corrosion piece and the turbine blades near the anti-corrosion piece 2 during turbine operation, resulting in damage to the turbine. This has become a major problem as it has a serious impact on driving. This stress corrosion cracking is caused by residual stress due to the strong restraining force, and is unavoidable as long as the corrosion protection piece 2 is attached by welding.
また、レーザビームを用いて表面層を焼入れし
た硬化層を得て応力腐食割れを防ぐ方法が知られ
ているが、タービン羽根は水滴の衝突に対する羽
根前縁の耐食性や耐摩耗性が要求され、この焼入
れによる硬化層のみでは防ぐことができない異常
摩耗が時々発生してタービンの運転に重大な影響
を及ぼし、これも大きな問題点となつている。 Additionally, a method is known in which the surface layer is quenched using a laser beam to obtain a hardened layer to prevent stress corrosion cracking. Abnormal wear, which cannot be prevented by the hardening layer alone, sometimes occurs and has a serious effect on turbine operation, which is also a major problem.
本発明は上記の点に鑑みなされたもので、溶接
施工を伴なわない方法によつて防食性を持たせ、
応力腐食割れの発生がなく、かつ耐食性，耐摩耗
性に優れたタービン羽根の製造方法を提供するこ
とを目的とする。
The present invention was made in view of the above points, and provides corrosion resistance by a method that does not involve welding.
The object of the present invention is to provide a method for manufacturing a turbine blade that does not cause stress corrosion cracking and has excellent corrosion resistance and wear resistance.
上記目的を達成するため本発明による方法は、
初めにタービン羽根の蒸気流入側の縁にレーザビ
ームを照射して表面層を溶融した後急冷して焼入
層を形成し、次に、前記焼入れ層の表面にニツケ
ル合金、コバルト合金、金属炭化物系合金から選
ばれた一種類の粉末を塗布した後、レーザビーム
を照射して溶融させてクラツデイング層を形成す
ることを特徴とするのである。
In order to achieve the above object, the method according to the present invention includes:
First, a laser beam is irradiated on the edge of the steam inflow side of the turbine blade to melt the surface layer and then rapidly cooled to form a hardened layer. Next, nickel alloy, cobalt alloy, and metal carbide are applied to the surface of the hardened layer. The feature is that after applying one type of powder selected from a series of alloys, a laser beam is irradiated to melt it and form a cladding layer.
以下、図面により本発明の一実施例を説明す
る。第６図に示すように羽根先端部の蒸気流入側
の縁に倣して、第３図の防食片２に相当する部分
にレーザビーム吸収剤３を塗布した後レーザビー
ム４を照射して焼入れ層５を形成する。焼入れ深
さを深く、且つ均一にする方法としてセグメント
ミラー等が一般的に用いられており、幅広で均一
な深さを得ることができる。
An embodiment of the present invention will be described below with reference to the drawings. As shown in Fig. 6, a laser beam absorbent 3 is applied to the portion corresponding to the anti-corrosion piece 2 in Fig. 3, following the edge of the blade tip on the steam inflow side, and then the laser beam 4 is irradiated to harden it. Form layer 5. A segment mirror or the like is generally used as a method of making the hardening depth deep and uniform, and it is possible to obtain a wide and uniform depth.
この焼入れ層５は、残留応力に起因する応力腐
食割れには有効であるが、耐食性は充分でない。
そこで、さらに羽根表面の耐食性を増すために、
焼入れ層にニツケル合金、コバルト合金、金属炭
化物系合金から選ばれた一種類の粉末を第６図に
示すのと同様に塗布する。次に、この塗布した部
分にレーザビーム４を照射してレーザによるクラ
ツデイング層又は合金層６を形成する。このクラ
ツデイング層の厚さは耐熱防食粉末の塗布厚さと
レーザビームの出力，照射速度等により任意に制
御することができる。第９図は12クロムマルテン
サイト系ステンレス鋼の表面に、レーザビームを
出力12KW、照射速度1200ｍ／分の条件で照射し
て焼入れ層を形成し、その後焼入れ層の表面にニ
ツケル合金粉末をアルコール溶液で1.0mm厚さ塗
布後、レーザビームを出力8KW、照射速度2000
mm／分の条件で照射してクラツデイング層を形成
させた場合の表面からの深さと硬度との関係を示
す実験結果の一例である。すなわち、レーザビー
ムの照射によりニツケル合金のクラツデイング層
は約0.8mm得られ、このクラツデイング層はニツ
ケル合金であるので非常に高い防食性能および耐
応力腐食割れ性能を有している。しかもこのクラ
ツデイング層の内部の焼入れ層もロツクウエル硬
度RC52で1.2mmの深さが得られており、硬化層深
さも充分である。 Although this hardened layer 5 is effective against stress corrosion cracking caused by residual stress, it does not have sufficient corrosion resistance.
Therefore, in order to further increase the corrosion resistance of the blade surface,
One type of powder selected from nickel alloy, cobalt alloy, and metal carbide alloy is applied to the hardened layer in the same manner as shown in FIG. Next, the coated portion is irradiated with a laser beam 4 to form a laser cladding layer or alloy layer 6. The thickness of this cladding layer can be arbitrarily controlled by adjusting the coating thickness of the heat-resistant and anti-corrosion powder, the output of the laser beam, the irradiation speed, etc. Figure 9 shows a hardened layer formed by irradiating the surface of 12 chromium martensitic stainless steel with a laser beam at an output of 12 KW and an irradiation speed of 1200 m/min. After that, nickel alloy powder is applied to the surface of the hardened layer in an alcohol solution. After coating 1.0mm thick, the laser beam output is 8KW and the irradiation speed is 2000.
This is an example of experimental results showing the relationship between depth from the surface and hardness when a cladding layer is formed by irradiation at a rate of mm/min. That is, a nickel alloy cladding layer of about 0.8 mm was obtained by laser beam irradiation, and since this cladding layer is a nickel alloy, it has very high corrosion protection performance and stress corrosion cracking resistance. Moreover, the hardened layer inside this cladding layer has a Rockwell hardness of R C 52 and a depth of 1.2 mm, and the hardened layer depth is also sufficient.
さらに、レーザビームはタービン羽根の前縁の
加熱と、表面層の極く浅い部分の溶融のみである
ので、焼入れ層とクラツデイング層を形成させて
もタービン羽根が変形することはない。したがつ
て、従来法では防食片をTIG溶接、電子ビーム溶
接等の溶融溶接をするので、その場合の変形を押
えるための充分な仮付けによる拘束応力の発生に
より、残留応力が生じ応力腐食割れの原因となる
が、本発明では仮付けによる拘束応力は発生しな
いのでタービン運転中に応力腐食割れが発生する
ことはない。またニツケル合金によるクラツデイ
ング層を有し腐食成物の侵食に対しても高い耐食
性を有しているので、タービン羽根の異常摩耗等
には特に有効である。 Furthermore, since the laser beam only heats the leading edge of the turbine blade and melts a very shallow portion of the surface layer, the turbine blade will not be deformed even if the hardened layer and cladding layer are formed. Therefore, in the conventional method, corrosion-proofing pieces are fusion welded by TIG welding, electron beam welding, etc., and in that case, residual stress is generated due to sufficient tacking to suppress deformation, resulting in stress corrosion cracking. However, in the present invention, stress corrosion cracking does not occur during turbine operation because restraint stress is not generated due to temporary attachment. Furthermore, since it has a cladding layer made of a nickel alloy and has high corrosion resistance against corrosion by corrosive products, it is particularly effective against abnormal wear of turbine blades.
また、レーザビームの照射は極めて短時間（５
〜６秒）であるので、２回作業を行なつても従来
法に比較して著しい工数の短縮が図られる。 In addition, the laser beam irradiation is extremely short (5
~6 seconds), so even if the work is performed twice, the number of man-hours can be significantly reduced compared to the conventional method.
以上述べた如く本発明によれば、タービン運転
中に応力腐食割れ発生の恐れがなく、かつ耐食
性，耐摩耗性の優れたタービン羽根を容易に提供
できるという効果が得られる。
As described above, according to the present invention, it is possible to easily provide a turbine blade that is free from stress corrosion cracking during turbine operation and has excellent corrosion resistance and wear resistance.
第１図は従来の防食片の形状を示す斜視図、第
２図は塑性加工した防食片の形状を示す斜視図、
第３図は従来の防食片を備えたタービン羽根を示
す斜視図、第４図および第５図は従来の防食片を
タービン羽根に溶接固着する際の溶接過程を示す
斜視図、第６図は本発明の方法に従つて製作され
たタービン羽根の一例を示す斜視図、第７図は第
６図のＣ−Ｃ矢視断面図、第８図は第７図のＡ−
Ａ矢視断面図、第９図は本発明による羽根の表面
からの深さと硬度との関係を示す曲線図である。
１……タービン羽根、４……レーザビーム、５
……焼入れ層、６……クラツデイング層。
Fig. 1 is a perspective view showing the shape of a conventional anti-corrosion piece, Fig. 2 is a perspective view showing the shape of a plastically worked anti-corrosion piece,
Fig. 3 is a perspective view showing a turbine blade equipped with a conventional anti-corrosion piece, Figs. 4 and 5 are perspective views showing the welding process when welding and fixing a conventional anti-corrosion piece to the turbine blade, and Fig. 6 is A perspective view showing an example of a turbine blade manufactured according to the method of the present invention, FIG. 7 is a sectional view taken along the line C-C in FIG. 6, and FIG.
A sectional view taken along arrow A and FIG. 9 are curve diagrams showing the relationship between the depth from the surface of the blade and the hardness according to the present invention. 1... Turbine blade, 4... Laser beam, 5
...Quenching layer, 6...Kurazding layer.
Claims (1)
ーザビームを照射して表面層を溶融した後急冷し
て焼入れ層を形成し、次に前記焼入れ層の表面に
ニツケル合金，コバルト合金，金属炭化物系合金
から選ばれた一種類の粉末を塗布した後レーザビ
ームを照射して溶融させてクラツデイング層を形
成すことを特徴とするタービン羽根の製造方法。1. First, a laser beam is irradiated on the edge of the steam inlet side of the turbine blade to melt the surface layer, and then the surface layer is rapidly cooled to form a hardened layer.Next, nickel alloy, cobalt alloy, and metal carbide are applied to the surface of the hardened layer. A method for manufacturing a turbine blade, which comprises applying one type of powder selected from a series of alloys and then melting the powder by irradiating it with a laser beam to form a cladding layer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP7911482A JPS58197403A (en) | 1982-05-13 | 1982-05-13 | Turbine blade and method of manufacturing thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP7911482A JPS58197403A (en) | 1982-05-13 | 1982-05-13 | Turbine blade and method of manufacturing thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS58197403A JPS58197403A (en) | 1983-11-17 |
| JPH0424525B2 true JPH0424525B2 (en) | 1992-04-27 |
Family
ID=13680879
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP7911482A Granted JPS58197403A (en) | 1982-05-13 | 1982-05-13 | Turbine blade and method of manufacturing thereof |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS58197403A (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6079103A (en) * | 1983-09-15 | 1985-05-04 | ウエスチングハウス エレクトリック コ−ポレ−ション | Method for imparting wear-resistant surfaces to steam turbine blades |
| GB0504576D0 (en) * | 2005-03-05 | 2005-04-13 | Alstom Technology Ltd | Turbine blades and methods for depositing an erosion resistant coating on the same |
| KR101680498B1 (en) | 2012-09-21 | 2016-11-28 | 미츠비시 히타치 파워 시스템즈 가부시키가이샤 | Method for welding erosion-resistant metal material, and turbine blade |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5477806A (en) * | 1977-12-02 | 1979-06-21 | Hitachi Ltd | Turbine blade |
| JPS588202A (en) * | 1981-07-07 | 1983-01-18 | Mitsubishi Heavy Ind Ltd | Rotor blade reinforcement method for steam turbine |
-
1982
- 1982-05-13 JP JP7911482A patent/JPS58197403A/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| JPS58197403A (en) | 1983-11-17 |
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