JP3175965B2 - Method of manufacturing nozzle blade for steam turbine - Google Patents
Method of manufacturing nozzle blade for steam turbineInfo
- Publication number
- JP3175965B2 JP3175965B2 JP06039692A JP6039692A JP3175965B2 JP 3175965 B2 JP3175965 B2 JP 3175965B2 JP 06039692 A JP06039692 A JP 06039692A JP 6039692 A JP6039692 A JP 6039692A JP 3175965 B2 JP3175965 B2 JP 3175965B2
- Authority
- JP
- Japan
- Prior art keywords
- nozzle blade
- casting
- nozzle
- steam turbine
- deformation
- 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 - Fee Related
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Description
【０００１】[0001]
【産業上の利用分野】本発明は蒸気タービン用の中空ノ
ズル翼の製造方法に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method for manufacturing a hollow nozzle blade for a steam turbine.
【０００２】[0002]
【従来の技術及び発明が解決しようとする課題】一般
に、蒸気タービン用のノズル翼は、ブロック材からの削
り出し、精密鋳造による鋳造、或は鋳造などの手段によ
り製造され、内部が中実で三次元的に複雑な形状を有す
る図９に示すような中実翼１として形成されている。2. Description of the Related Art Generally, a nozzle blade for a steam turbine is manufactured by a method such as cutting from a block material, casting by precision casting, or casting, and has a solid inside. It is formed as a solid wing 1 as shown in FIG. 9 having a three-dimensionally complex shape.
【０００３】ところが、このような中実翼１は重量が重
く、材料歩留まりが悪くコスト高であるという問題点が
あるとともに、重量が重いことによりハンドリングが大
変で、製造に手間がかかるとともに、それを取り扱う作
業員には過大な労力がかかるという問題がある。[0003] However, such a solid wing 1 has the problems that it is heavy, the material yield is low and the cost is high. In addition, handling is difficult due to the heavy weight, and it takes time and effort to manufacture. There is a problem that the worker who handles the work requires excessive labor.
【０００４】そこで、ノズル翼の軽減化を図るため図１
０に示すような中空ノズル翼が開発されている。すなわ
ち、この中空ノズル翼２は、所定形状の背板３及び腹板
４をプレス加工により熱間曲げ形成した後、それらの前
端縁部及び後端縁部を互いに溶接５によって結合し、両
板間に中空部６を形成することによって形成されてい
る。To reduce the number of nozzle blades, FIG.
A hollow nozzle vane as shown in FIG. That is, the hollow nozzle blade 2 is formed by hot bending a back plate 3 and a belly plate 4 of a predetermined shape by press working, and then joining their front edge and rear edge to each other by welding 5 to form both plates. It is formed by forming a hollow portion 6 between them.
【０００５】ところで、このような中空ノズル翼におい
ては、背板３と腹板４の曲げ成形の段階で高精度のプロ
フィール加工を行なったとしても、後工程の結合のため
の溶接による熱変形のために精度が悪化し、多大の修正
工数を必要とする等の問題がある。また、プレス加工に
より熱間曲げ成形するということで、温度を８００℃近
くまで上げる必要があり、使用材料の焼戻し温度近く、
また材料によっては焼戻し温度以上で熱間曲げ成形する
場合もあり、使用上信頼性の面で不安があった。本発明
はこのような点に鑑み、上記従来技術の欠点を除去し
て、高精度の蒸気タービン用ノズル翼を安価に製造する
ことができる製造法を得ることを目的とする。In such a hollow nozzle blade, even if high-precision profile processing is performed at the stage of bending the back plate 3 and the belly plate 4, thermal deformation due to welding for connection in a later process is required. However, there is a problem that accuracy is deteriorated and a large number of correction man-hours are required. In addition, it is necessary to raise the temperature to nearly 800 ° C. by performing hot bending by press working, which is close to the tempering temperature of the material used.
Further, depending on the material, hot bending may be performed at a temperature equal to or higher than the tempering temperature, and there is a concern about reliability in use. SUMMARY OF THE INVENTION In view of the foregoing, an object of the present invention is to provide a manufacturing method capable of manufacturing a high-precision steam turbine nozzle blade at a low cost by eliminating the above-mentioned disadvantages of the prior art.
【０００６】[0006]
【課題を解決するための手段】上記目的を達成するた
め、請求項１に係る発明は、消失模型を用いた精密鋳造
によって、内部が中空であり、長手方向において２分割
または３分割以上に分割するとともに各ノズル翼片の腹
側の肉厚を厚くし、背側の肉厚を薄くしたノズル翼片を
製造し、各ノズル翼片を上記分割面で溶接することによ
り一体結合することを特徴とする。Means for Solving the Problems To achieve the above object, the invention according to claim 1 is characterized in that the inside is hollow and divided into two or three or more in the longitudinal direction by precision casting using a vanishing model. In addition, the thickness of the belly side of each nozzle wing is increased, and the thickness of the back side is reduced to manufacture the nozzle wings, and the nozzle wings are integrally joined by welding at the divided surface. And
【０００７】請求項２に係る発明は、請求項１に係る発
明において、各ノズル翼片内部に、精密鋳造時に生じる
鋳造変形を防止する変形防止用リブを鋳造の状態におい
て予め設けることを特徴とする。According to a second aspect of the present invention, in the first aspect of the present invention, a deformation preventing rib for preventing casting deformation occurring at the time of precision casting is provided in advance in each nozzle blade piece in a casting state. I do.
【０００８】請求項３に係る発明は、請求項１に係る発
明において、各ノズル翼片の溶接すべき端部に、鋳造時
に盛り上げ部を設け、この盛り上げ部により溶接による
変形を矯正することを特徴とする。According to a third aspect of the present invention, in the first aspect of the invention, a raised portion is provided at the end of each nozzle blade piece to be welded at the time of casting, and the raised portion corrects deformation due to welding. Features.
【０００９】請求項４に係る発明は、消失模型を用いた
精密鋳造によって、内部が中空であり、長手方向に２分
割または３分割以上に分割ノズル翼片を、精密鋳造段階
で、所定の厚さのセラミックスの薄膜を所定の位置に取
り付けて鋳造し、冷却後上記セラミックスの薄膜を取り
除くことにより、ドレン吸込用のスリットを形成して製
造するとともに、各ノズル翼片を上記分割面で溶接する
ことにより一体結合することを特徴とする。According to a fourth aspect of the present invention, there is provided a precision casting using a vanishing model, in which the inside of the nozzle is hollow and divided into two or three or more in the longitudinal direction. A ceramic thin film is attached at a predetermined position and cast, and after cooling, the ceramic thin film is removed to form a slit for drain suction, and each nozzle blade piece is welded at the above-mentioned divided surface. It is characterized by being integrally joined.
【００１０】[0010]
【作用】消失模型を用いた精密鋳造法を使用すること
で、蒸気タービン用ノズル翼の複雑な断面形状を精度良
く再現することができ、多大の修正工数を必要とするこ
となく中空ノズル翼を形成することができ、また、ノズ
ル翼片の腹側の肉厚を厚くし、背側の肉厚を薄くするこ
とにより、凝固段階で引っ張りが生じた場合にも変形が
生じることがない。しかも、長手方向において２分割ま
たは３分割以上に分割したノズル翼片を製造することに
より、押し湯効果の現象による鋳造欠陥の発生が防止さ
れる。[Function] By using a precision casting method using a vanishing model, a complicated cross-sectional shape of a nozzle blade for a steam turbine can be accurately reproduced, and a hollow nozzle blade can be used without requiring a large number of correction man-hours. In addition, by increasing the thickness on the ventral side and decreasing the thickness on the dorsal side of the nozzle blade piece, deformation does not occur even when tension occurs in the solidification stage. In addition, by producing the nozzle blade piece divided into two or three or more in the longitudinal direction, the occurrence of casting defects due to the phenomenon of the feeder effect is prevented.
【００１１】また、ノズル翼の内部にリブを設けた場合
には、精密鋳造時に生ずる鋳造変形を防止でき、さら
に、ノズル翼片の溶接すべき端部に鋳造時に盛り上げ部
を設けることにより、溶接による変形を防止できる。ま
たセラミックの薄膜によってドレン吸込み用スリットを
形成する場合には、後工程での熱の発生を伴うスリット
加工が不要となる。When ribs are provided inside the nozzle blade, casting deformation that occurs at the time of precision casting can be prevented. Further, by forming a raised portion at the end of the nozzle blade piece to be welded at the time of casting, welding can be achieved. Deformation can be prevented. In addition, when the drain suction slit is formed by a ceramic thin film, it is not necessary to perform slit processing involving generation of heat in a later step.
【００１２】[0012]
【実施例】以下、図１乃至図８を参照して本発明の実施
例について説明する。蒸気タービン用ノズル翼の断面形
状は、蒸気を効率良く流すためにその断面プロフィール
が選定されており、複雑な形状をしている。そのためノ
ズル翼は高精度で作る必要があり、この複雑な断面を精
度良く再現するために、本発明においては消失模型を用
いたセラミックシェルモールドによる精度鋳造法を用い
る。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described below with reference to FIGS. The cross-sectional profile of the nozzle blade for a steam turbine is selected to have a complicated cross-sectional profile in order to flow steam efficiently. Therefore, it is necessary to make the nozzle blade with high precision. In order to accurately reproduce this complicated cross section, the present invention uses a precision casting method using a ceramic shell mold using a vanishing model.
【００１３】ところが、蒸気タービン用ノズル翼の長さ
は最終段で、長いものでは１３２０．８ｍｍにもなり、
このような長いものには上記消失模型を用いたセラミッ
クシェルモールド法は適用が困難である。また適用した
としても蒸気タービン用ノズル翼には長さ方向にテーパ
が付くとともに、多少捩れた形状をした複雑な形状をし
ていることから、凝固の段階で生ずる変形及び長くなる
ことによる先端部への押し湯効果の減少による鋳造欠陥
の発生のため、上記複雑な形状のノズル翼を一体で精度
良く再現するのは非常に困難である。However, the length of the nozzle blade for the steam turbine is the last stage.
It is difficult to apply the ceramic shell molding method using the vanishing model to such a long product. Even if it is applied, the nozzle blades for steam turbines are tapered in the length direction and have a somewhat twisted and complex shape, so the tip that is caused by the deformation occurring during the solidification stage and becoming longer Due to the occurrence of casting defects due to a decrease in the feeder effect, it is very difficult to accurately reproduce the nozzle wing having the complicated shape as described above.
【００１４】そこで、本発明においてはノズル翼の長手
軸線に直交する面でノズル翼を２分割又は３分割以上に
分割した形状の中空状のノズル翼片を上記精密鋳造法に
よって作成し、その後各ノズル翼片を各分割面で溶接に
よって一体化する。Therefore, in the present invention, a hollow nozzle blade piece having a shape in which the nozzle blade is divided into two or three or more in a plane perpendicular to the longitudinal axis of the nozzle blade is formed by the above-mentioned precision casting method, and thereafter each nozzle blade is formed. The nozzle wings are integrated by welding at each division surface.
【００１５】ところで、上記分割面の位置は、前記鋳造
品の凝固の段階で生ずる変形及び押し湯効果の減少によ
る鋳造欠陥を考慮した位置に設けられ、また、ノズル翼
の背板及び腹板の板厚は押し湯効果と重量の重ね合いに
よって決定されるが、押し湯効果を持たせるためには厚
い方がいいが、あまり厚いと重量が増えてしまうので、
従来の板と同じ程度の３ｍｍ〜６ｍｍで製造できるよう
に分割される。By the way, the position of the dividing surface is provided in consideration of a casting defect due to a deformation occurring at the stage of solidification of the cast product and a decrease in a feeder effect, and a back plate and a belly plate of a nozzle blade are provided. The plate thickness is determined by the overlap between the hot water effect and the weight, but it is better to have a hot water effect, but if it is too thick, the weight increases.
It is divided so that it can be manufactured in the same order of 3 mm to 6 mm as a conventional plate.
【００１６】すなわち、図１は上述のようにして分割面
１０ａ，１０ｂを決定して、チップ側ノズル翼とルート
側ノズル翼との２つのノズル翼片１１，１２に、ノズル
翼の長手軸線に直交する平面で２分割した状態を示して
おり、この各ノズル翼片１１，１２を製作するために
は、まず図面に従い各ノズル翼片用の金型を製作し、こ
の各金型にろう又は合成樹脂或は発砲樹脂等を射出成形
し、中空ノズル翼片の消失模型を製作する。That is, in FIG. 1, the dividing surfaces 10a and 10b are determined as described above, and the two nozzle blade pieces 11 and 12 of the tip-side nozzle blade and the root-side nozzle blade are attached to the longitudinal axis of the nozzle blade. This figure shows a state of being divided into two by an orthogonal plane. In order to manufacture each of the nozzle blades 11, 12, first, a mold for each nozzle blade is manufactured according to the drawing, and a wax or Injection molding of synthetic resin or foaming resin, etc., to produce a vanishing model of the hollow nozzle blade piece.
【００１７】そこで、この模型の周りにセラミック耐火
物を被覆し、周りだけを薄く覆ったセラミックシェル鋳
型を作り、該消失模型を溶出或は燃焼消失させて鋳型を
作り、その後上記鋳型にノズル翼片の溶湯を注湯するこ
とによって、前記ノズル翼片１１，１２を製作する。Therefore, a ceramic shell mold is formed by coating a ceramic refractory around the model and thinly covering only the periphery. The mold is made by dissolving or burning out the disappearance model, and then the nozzle blade is added to the mold. The nozzle blade pieces 11 and 12 are manufactured by pouring a piece of molten metal.
【００１８】その後、上記ノズル翼片１１，１２の分割
面を溶接によって一体に連結し、一本の中空ノズル翼を
形成する。Thereafter, the divided surfaces of the nozzle blade pieces 11 and 12 are integrally connected by welding to form one hollow nozzle blade.
【００１９】ところで、鋳造時における凝固の段階で生
ずる断面の変化を防止するために、図２に示すように、
ノズル翼片１１，１２の中空部内に適宜リブを設けるこ
とができる。すなわち、断面形状の大きいところは２本
または３本以上、断面形状の小さいところは１本という
ように変形防止用のリブ１３ａ，１３ｂ，１３ｃを設け
ることができる。この各リブの厚さは、変形防止のため
の必要な剛性と、凝固の際に鋳造欠陥を生じさせない厚
さとしなければならないことは勿論である。また、各分
割面は図３に示すように溶接結合部１４によって長さ方
向に一体結合されるが、この場合溶接による変形が生じ
る。この変形は図４に示すように落ち込みによる変形Ｃ
である。そこで、各ノズル翼片１１，１２の溶接すべき
端部に、図５に示すように、鋳造時に盛り上げ部１５
ａ，１５ｂを設け、この盛り上げ部１５ａ，１５ｂによ
って鋳造段階での溶接による落ち込み変形分を矯正す
る。このような矯正によって、継ぎ目の断面形状を高精
度で再現でき、タービン性能に対する影響を無くするこ
とができる。By the way, in order to prevent a change in the cross section that occurs at the stage of solidification during casting, as shown in FIG.
Ribs can be appropriately provided in the hollow portions of the nozzle blade pieces 11 and 12. That is, the ribs 13a, 13b, and 13c for preventing deformation can be provided such that two or three or more sections have a large cross-sectional shape and one section has a small cross-sectional shape. Needless to say, the thickness of each rib must be a rigidity required for preventing deformation and a thickness that does not cause casting defects during solidification. Further, as shown in FIG. 3, the divided surfaces are integrally connected in the length direction by the welding connection portion 14, but in this case, deformation due to welding occurs. This deformation is as shown in FIG.
It is. Therefore, as shown in FIG. 5, the raised portions 15 are formed at the ends of the nozzle blade pieces 11 and 12 to be welded.
a, 15b are provided, and the raised portions 15a, 15b correct the falling deformation caused by welding at the casting stage. By such correction, the cross-sectional shape of the seam can be reproduced with high accuracy, and the influence on turbine performance can be eliminated.
【００２０】ノズル翼の各断面形状に関しては、変形防
止用リブ１３ａ，１３ｂ，１３ｃを配置してその変形を
防止するが、凝固の段階で生ずる断面のわずかな変形に
対しては、予めその変形分を見込んだ形状にして鋳造す
ることによって、その分を矯正することができ、高精度
でプロフィールを再現できる。すなわち、上記凝固の段
階で、腹側と背側の断面方向の長さの違いでどうしても
背側に引張られてしまうので、図６に示すように、引張
りが生じた場合にも変形しないように腹側の肉厚ｔａを
背側の肉厚ｔｂより厚くすることが有効である。With respect to each cross-sectional shape of the nozzle blade, deformation preventing ribs 13a, 13b, 13c are arranged to prevent the deformation. By casting in a shape that allows for the amount, the amount can be corrected and the profile can be reproduced with high precision. In other words, in the coagulation stage, the fibers are inevitably pulled to the dorsal side due to the difference in the length in the cross-sectional direction between the ventral side and the dorsal side. Therefore, as shown in FIG. It is effective to make the thickness ta on the abdomen thicker than the thickness tb on the back.
【００２１】また、この蒸気タービン用中空ノズル翼を
製造するに当っては、オーステナイト系ステンレス材料
を使用する。従来はフェライト系ステンレス鋼またはマ
ルテンサイト系ステンレス鋼が使用されていたが、これ
らの材料は所定の強度をもたせるためには鋳造後に熱処
理が必要であり、また他の部材との溶接の後に、応力除
去焼純が必要であるためコスト高となる。そこで、上述
のようにオーステナイト系ステンレス鋼を使用すると、
セラミックシェルモールド法で製作するため、鋳造後の
冷却が早く、十分な強度がこの段階で得られ、後に溶体
化処理を必要とせず、また溶接に対し、予熱、後熱処理
が不要であり、製作上、工数を削減でき、さらに熱処理
による変形を防止することもできる。In manufacturing the hollow nozzle blade for the steam turbine, an austenitic stainless steel material is used. Conventionally, ferritic stainless steel or martensitic stainless steel has been used.However, these materials require heat treatment after casting in order to have a predetermined strength. The cost is high because removal incineration is required. Therefore, when using austenitic stainless steel as described above,
Since it is manufactured by the ceramic shell mold method, cooling after casting is fast, sufficient strength is obtained at this stage, no solution treatment is required later, and no preheating and post heat treatment is required for welding, manufacturing In addition, the number of steps can be reduced, and deformation due to heat treatment can be prevented.
【００２２】また、材料特性面からは、オーステナイト
系ステンレス鋼ということで、浸蝕に対し、すぐれた特
性を有しており、湿り蒸気中で使用される最終段ノズル
翼に要求される必要な特性をもっている。侵蝕性が優れ
ているということは、長時間にわたり、プロフィール精
度が維持されていることを意味し、効率の低下を防ぎ、
高効率を長時間に亘り維持することができる。この材料
は線膨張係数が大きいというデメリットがあるが、使用
される温度域がせいぜい１００℃以内であることから、
特に使用上の制限はなく、この面からオーステナイト系
ステンレス鋼の使用は蒸気タービン用ノズル翼として問
題はない。In terms of material properties, the austenitic stainless steel has excellent resistance to erosion, and is a necessary property required for the last stage nozzle blade used in wet steam. Have. Excellent erosion means that profile accuracy is maintained for a long time, preventing a decrease in efficiency,
High efficiency can be maintained for a long time. This material has the disadvantage of a large linear expansion coefficient, but since the temperature range used is at most 100 ° C,
There is no particular restriction on the use, and from this aspect, the use of austenitic stainless steel does not pose a problem as a nozzle blade for a steam turbine.
【００２３】また、最近蒸気タービンの性能向上を図る
ため、特に湿り蒸気中で使用される段落での蒸気中に含
まれるドレンに対して、積極的にそのドレンを排除して
ドレンによる性能低下の影響を極力少くするために、翼
面にスリットを設けて、このスリットからドレンを吸込
む方式の中空ノズル翼が使用される場合が多い。Further, in order to improve the performance of a steam turbine recently, particularly, the drain contained in the steam in the paragraph used in wet steam is actively removed to reduce the performance degradation due to the drain. In order to reduce the influence as much as possible, a hollow nozzle blade of a type in which a slit is provided in the blade surface and the drain is sucked through the slit is often used.
【００２４】このスリットは、従来中空ノズル翼が出来
た時点で、レーザ加工等により設けられているが、中空
ノズル翼完成後に加工するため、さらに熱が加わり、熱
変形が生じ断面のプロフィールが崩れてしまう可能性が
ある。そこで、本発明においては、鋳造時に図７に示す
ように、スリットの幅に等しいセラミックスの薄膜１６
を所定の位置に設置しこの状態で鋳造する。そして、冷
却した後にこのセラミックスの薄膜１６を取り除くこと
によって、図８に示すようにスリット１７を設けた中空
ノズル翼とすることができる。Conventionally, this slit is formed by laser processing or the like when the hollow nozzle blade is formed. However, since the slit is processed after the completion of the hollow nozzle blade, heat is further applied, thermal deformation occurs, and the profile of the cross section collapses. Could be Therefore, in the present invention, at the time of casting, as shown in FIG.
Is set at a predetermined position and casting is performed in this state. Then, by removing the ceramic thin film 16 after cooling, a hollow nozzle blade having a slit 17 as shown in FIG. 8 can be obtained.
【００２５】このようにして、後加工でスリット１７の
加工が不要になるため、製造工数の削減と共に、熱変形
が生じることもなく、高精度でスリット付の中空ノズル
翼を作ることができる。そして、このようにして製作し
た中空ノズル翼は、最後に出口部１８を機械加工して完
成する。In this manner, since the slit 17 is not required in the post-processing, the number of manufacturing steps can be reduced, and a hollow nozzle blade with a slit can be manufactured with high accuracy without causing thermal deformation. The hollow nozzle blade manufactured in this manner is completed by finally machining the outlet portion 18.
【００２６】[0026]
【発明の効果】以上説明したように、本発明において
は、消失模型を用いた精密鋳造によって、長手方向に２
分割または３分割以上に分割した中空ノズル翼片を製造
し、各ノズル翼片を上記分割面で溶接することにより一
体結合したので、プロフィール精度の高い蒸気タービン
用ノズル翼を製造することができ、従来のように断面形
状修正のための工数が不要となり、約１５〜２０％の工
数低減となる。また、材料歩留まりは約４５％改善で
き、トータルコストの低減及び省資源的にも大きな効果
を奏する。また、ノズル翼片の腹側の肉厚を厚くし、背
側の肉厚を薄くしてあるため、鋳造時における凝固の段
階で引っ張りが生じた場合にも変形が生じることがな
い。さらに鋳造段階でスリットを設けることもでき、後
工程での熱の発生を伴うスリット加工が不要となり、プ
ロフィール精度を崩すことなくスリット加工を行なうこ
とができる。As described above, according to the present invention, precision casting using a vanishing model is performed in the longitudinal direction.
Since the hollow nozzle blade pieces divided or divided into three or more sections are manufactured and each nozzle blade piece is integrally joined by welding at the above-mentioned divided surface, it is possible to manufacture a steam turbine nozzle blade with high profile accuracy, Unlike the conventional case, the man-hour for correcting the cross-sectional shape is unnecessary, and the man-hour is reduced by about 15 to 20%. In addition, the material yield can be improved by about 45%, and a great effect is achieved in terms of reduction in total cost and resource saving. In addition, since the thickness of the nozzle blade piece on the belly side is increased and the thickness on the back side is reduced, deformation does not occur even if tension occurs during the solidification stage during casting. Further, a slit can be provided in the casting stage, so that a slit process involving generation of heat in a later process is not required, and the slit process can be performed without deteriorating the profile accuracy.
【図１】本発明に係わる中空ノズル翼の２分割構造の説
明図。FIG. 1 is an explanatory view of a two-part structure of a hollow nozzle blade according to the present invention.
【図２】本発明による中空ノズル翼のリブ配列の説明
図。FIG. 2 is an explanatory view of a rib arrangement of a hollow nozzle blade according to the present invention.
【図３】本発明による２分割構造の中空ノズル翼の溶接
結合した状態を示す図。FIG. 3 is a view showing a state in which a hollow nozzle blade having a two-part structure according to the present invention is welded and connected.
【図４】溶接結合部の溶接変形説明図。FIG. 4 is an explanatory diagram of welding deformation of a welded joint.
【図５】溶接変形を防止するための分割断面部の断面形
状を示す図。FIG. 5 is a view showing a sectional shape of a divided sectional portion for preventing welding deformation.
【図６】鋳造変形を考慮した本発明に係わる２分割断面
部の断面形状を示す図。FIG. 6 is a view showing a cross-sectional shape of a two-part cross section according to the present invention in consideration of casting deformation.
【図７】スリット形成方法説明図。FIG. 7 is an explanatory view of a slit forming method.
【図８】本発明に係わるスリット付中空ノズル翼の外形
図。FIG. 8 is an outline drawing of a hollow nozzle blade with a slit according to the present invention.
【図９】従来の中空ノズル翼を示す斜視図。FIG. 9 is a perspective view showing a conventional hollow nozzle blade.
【図１０】従来の中空ノズル翼の一例を示す断面図。FIG. 10 is a sectional view showing an example of a conventional hollow nozzle blade.
１０ａ，１０ｂ 分割面 １１，１２ ノズル翼片 １３ａ，１３ｂ，１３ｃ リブ １４ 溶接結合部 １５ａ，１５ｂ 盛り上げ部 １６ セラミックスの薄膜 １７ スリット 10a, 10b Dividing surface 11, 12 Nozzle blade piece 13a, 13b, 13c Rib 14 Welded joint 15a, 15b Raised portion 16 Ceramic thin film 17 Slit
───────────────────────────────────────────────────── フロントページの続き (72)発明者 新 津 啓 二 新潟県上越市港町２−25−１ 大平洋特 殊鋳造株式会社 直江津製造所内 (56)参考文献 特開 昭59−66948（ＪＰ，Ａ) 特開 昭58−214602（ＪＰ，Ａ) 特開 昭59−54704（ＪＰ，Ａ) 特開 昭57−179306（ＪＰ，Ａ) 特開 昭61−250303（ＪＰ，Ａ) 特開 昭60−177932（ＪＰ，Ａ) 特開 昭56−156403（ＪＰ，Ａ) 実開 昭60−143102（ＪＰ，Ｕ) 朝倉書店「粉末冶金・溶接」（昭和44 年２月５日発行) コロナ社「最新溶接工学」（昭和46年 ８月10日発行) (58)調査した分野(Int.Cl.7，ＤＢ名) F01D 9/00 ──────────────────────────────────────────────────続 き Continuing from the front page (72) Inventor Keiji Niitsu 2-25-1 Minatomachi, Joetsu City, Niigata Prefecture Inside the Naoetsu Works of Taiheiyo Special Casting Co., Ltd. (56) References JP-A-59-66948 (JP, A) JP-A-58-214602 (JP, A) JP-A-59-54704 (JP, A) JP-A-57-179306 (JP, A) JP-A-61-250303 (JP, A) JP-A Sho 60 -1777932 (JP, A) JP-A-56-156403 (JP, A) JP-A-60-143102 (JP, U) Asakura Shoten “Powder metallurgy and welding” (published on February 5, 1969) Corona “ Latest Welding Engineering ”(August 10, 1971) (58) Fields investigated (Int. Cl. 7 , DB name) F01D 9/00
Claims (4)
が中空であり、長手方向に２分割または３分割以上に分
割するとともに各ノズル翼片の腹側の肉厚を厚くし、背
側の肉厚を薄くしたノズル翼片を製造し、各ノズル翼片
を上記分割面で溶接することにより一体結合することを
特徴とする、蒸気タービン用ノズル翼の製造方法。1. A precision casting using a vanishing model, the inside of which is hollow, is divided into two or three or more in the longitudinal direction and the thickness of the ventral side of each nozzle blade piece is increased.
A method for manufacturing a nozzle blade for a steam turbine, comprising: manufacturing a nozzle blade having a reduced thickness on a side thereof; and welding the nozzle blades together at the division surface to thereby integrally join the nozzle blades.
鋳造変形を防止する変形防止用リブを鋳造の状態におい
て予め設けることを特徴とする、請求項１記載の蒸気タ
ービン用ノズル翼の製造方法。2. A deformation preventing rib for preventing casting deformation occurring at the time of precision casting in each nozzle blade piece in a state of casting.
The method for manufacturing a nozzle blade for a steam turbine according to claim 1, wherein the nozzle blade is provided in advance .
に盛り上げ部を設け、この盛り上げ部により溶接による
変形を矯正することを特徴とする、請求項１記載の蒸気
タービン用ノズル翼の製造方法。3. The casting of the end of each nozzle blade piece to be welded
Is provided with a raised portion, and the raised portion is used for welding.
The method according to claim 1, wherein the deformation is corrected .
が中空であり、長手方向に２分割または３分割以上に分
割ノズル翼片を、精密鋳造段階で、所定の厚さのセラミ
ックスの薄膜を所定の位置に取り付けて鋳造し、冷却後
上記セラミックスの薄膜を取り除くことにより、ドレン
吸込用のスリットを形成して製造するとともに、各ノズ
ル翼片を上記分割面で溶接することにより一体結合する
ことを特徴とする、蒸気タービン用ノズル翼の製造方
法。4. The internal structure is manufactured by precision casting using a vanishing model.
Is hollow and divided into two or three or more in the longitudinal direction.
In the precision casting stage , the split nozzle blades are cast by mounting a ceramic thin film of a predetermined thickness at a predetermined position, and after cooling, remove the ceramic thin film to form a slit for drain suction and manufacture. And each nose
A method for manufacturing a nozzle blade for a steam turbine, wherein the blade pieces are integrally joined by welding at the divided surfaces .
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP06039692A JP3175965B2 (en) | 1992-03-17 | 1992-03-17 | Method of manufacturing nozzle blade for steam turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP06039692A JP3175965B2 (en) | 1992-03-17 | 1992-03-17 | Method of manufacturing nozzle blade for steam turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH05263605A JPH05263605A (en) | 1993-10-12 |
| JP3175965B2 true JP3175965B2 (en) | 2001-06-11 |
Family
ID=13140960
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP06039692A Expired - Fee Related JP3175965B2 (en) | 1992-03-17 | 1992-03-17 | Method of manufacturing nozzle blade for steam turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3175965B2 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9729005B2 (en) | 2012-06-18 | 2017-08-08 | Hirokazu Noguchi | Fluorescent LED lighting device and lighting on/off mode switching method therefor |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR102049818B1 (en) * | 2017-09-29 | 2019-11-29 | (주)영광공작소 | Manufacturing method of blade |
-
1992
- 1992-03-17 JP JP06039692A patent/JP3175965B2/en not_active Expired - Fee Related
Non-Patent Citations (2)
| Title |
|---|
| コロナ社「最新溶接工学」（昭和４６年８月１０日発行） |
| 朝倉書店「粉末冶金・溶接」（昭和４４年２月５日発行） |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9729005B2 (en) | 2012-06-18 | 2017-08-08 | Hirokazu Noguchi | Fluorescent LED lighting device and lighting on/off mode switching method therefor |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH05263605A (en) | 1993-10-12 |
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