JPS63241118A - Manufacture of large-sized turbine blade - Google Patents
Manufacture of large-sized turbine bladeInfo
- Publication number
- JPS63241118A JPS63241118A JP7571387A JP7571387A JPS63241118A JP S63241118 A JPS63241118 A JP S63241118A JP 7571387 A JP7571387 A JP 7571387A JP 7571387 A JP7571387 A JP 7571387A JP S63241118 A JPS63241118 A JP S63241118A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- turbine blade
- forged
- die
- forging
- 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.)
- Pending
Links
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 12
- 238000005242 forging Methods 0.000 claims description 27
- 238000012937 correction Methods 0.000 claims description 4
- 238000000137 annealing Methods 0.000 abstract description 3
- 238000001816 cooling Methods 0.000 abstract description 2
- 229910000883 Ti6Al4V Inorganic materials 0.000 abstract 1
- 238000000034 method Methods 0.000 description 20
- 239000000047 product Substances 0.000 description 10
- 238000010438 heat treatment Methods 0.000 description 5
- 239000000463 material Substances 0.000 description 3
- 238000007796 conventional method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 239000011265 semifinished product Substances 0.000 description 2
- 229910000851 Alloy steel Inorganic materials 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 229910001067 superalloy steel Inorganic materials 0.000 description 1
Landscapes
- Forging (AREA)
Abstract
Description
【発明の詳細な説明】
（産業上の利用分野）
本発明は、三次元形状に複雑に捩れた大型薄肉の大型タ
ービン翼の製造方法に関するものである。DETAILED DESCRIPTION OF THE INVENTION (Industrial Application Field) The present invention relates to a method for manufacturing a large, thin-walled turbine blade that is complicatedly twisted into a three-dimensional shape.
（従来の技術及びその問題点）
火力や原子力タービンは年々大容量化してきており、ま
たその信顛性も一層強く要求されるようになってきてい
る。従って、近年高合金鋼や超合金鋼に加えて耐食性に
冨み、かつ軽量強靭な性質を有するチタン合金が前記タ
ービン用材料として使用されるようになってきた。(Prior art and its problems) Thermal power and nuclear power turbines are increasing in capacity year by year, and their reliability is also being required more and more. Therefore, in recent years, in addition to high alloy steel and superalloy steel, titanium alloys, which have excellent corrosion resistance and are lightweight and strong, have come to be used as materials for the turbine.
ところで、第４図（イ）に示すような三次元形状に複雑
に捩れた大型タービン翼ｌを製造するに際し、従来は以
下の如く行っていた。By the way, when manufacturing a large turbine blade l having a complicated three-dimensional shape as shown in FIG. 4(a), the conventional method was as follows.
すなわち従来は所要の大きさのインゴットを順次荒地鍛
造から仕上鍛造へと型鍛造した後所要の熱処理を施して
仕上げ加工し、製造していたのであるが、このうち型鍛
造の際従来は第４図（ロ）に矢印で示す方向にハンマー
もしくはプレスで鍛造していた為、翼根部２と翼先端部
３とで反対方向のスラスト力が作用し、これが鍛造機自
体に悪影響を及ぼすと同時に製品厚さ不同の原因にもな
っていた。なお第４図中４は中央部を示す。In other words, in the past, ingots of the required size were die-forged in sequence from rough forging to finish forging, and then subjected to the required heat treatment and finishing processing. Because forging was carried out with a hammer or press in the direction indicated by the arrow in Figure (B), thrust forces in opposite directions act on the blade root 2 and the blade tip 3, which has a negative effect on the forging machine itself and at the same time the product. This was also a cause of uneven thickness. Note that 4 in FIG. 4 indicates the central portion.
従って、従来は型鍛造品自体にある程度の寸法余肉を付
与し、機械加工やグラインダによって手入をしているの
が実状である。Therefore, in the past, the reality is that die forged products themselves are given a certain amount of extra dimension and are maintained by machining or grinding.
本発明はかかる問題点に鑑みて成されたものであり、全
断面に亘って均一な厚さ分布を確保すると共に製品の変
形や残留応力を完全に防止できる大型タービン翼の製造
方法を提供せんとするものである。The present invention has been made in view of these problems, and it is an object of the present invention to provide a method for manufacturing large turbine blades that can ensure uniform thickness distribution over the entire cross section and completely prevent product deformation and residual stress. That is.
（問題点を解決するための手段）
本発明は、三次元形状に複雑に槻れた大型タービン翼を
鍛造により製造する方法において、翼根から翼先端に亘
って水平状態を維持したまま型鍛造し、核型鍛造終了後
タービン翼に所要の捩り加工を施し、かかる状態下にお
いて強制拘束矯正を行った後拘束状態で熱処理すること
を要旨とするものである。(Means for Solving the Problems) The present invention is a method for manufacturing a large turbine blade having a complicated three-dimensional shape by forging. The gist of this method is to perform a required twisting process on the turbine blade after completion of core die forging, perform forced restraint correction under such conditions, and then heat treat the blade in the restrained state.
（作 用）
本発明に係る大型タービン翼の製造方法は、三次元形状
に複雑に捩れた大型タービン翼を鍛造により製造する方
法において、翼根から翼先端に亘って水平状態を維持し
たまま型鍛造し、核型鍛造終了後タービン翼に所要の捩
り加工を施し、かかる状態下において強制拘束矯正を行
った後拘束状態で熱処理するものであり、翼根から翼先
端に亘って水平状態を維持したまま型鍛造する為、荒地
の安定が極めて良好となると共に、型鍛造時におけるス
ラスト力の発生がない、また、本発明方法は、拘束状態
を維持して熱処理する為、変形や残留応力を完全に防止
した製品が得られる。(Function) The method for manufacturing a large turbine blade according to the present invention is a method for manufacturing a large turbine blade complicatedly twisted into a three-dimensional shape by forging. The turbine blade is forged, and after the nuclear die forging is completed, the turbine blade is subjected to the required twisting process, and after the blade is forcibly restrained and straightened under such conditions, it is heat treated in the restrained state, and the blade maintains a horizontal state from the blade root to the blade tip. Since die forging is carried out while the condition is still in place, the stability of the rough ground is extremely good, and no thrust force is generated during die forging.Furthermore, since the method of the present invention performs heat treatment while maintaining a restrained state, deformation and residual stress are reduced. A completely protected product is obtained.
（実 施 例）
以下本発明方法を第１図〜第３図に示す一実施例に基づ
いて説明する。なお、本実施例ではＴｉ −６ＡＪ−４
Ｖを用いて前述した第４図に示す形状の大型タービン翼
を製造する場合について説明する。(Example) The method of the present invention will be described below based on an example shown in FIGS. 1 to 3. Note that in this example, Ti-6AJ-4
A case in which a large turbine blade having the shape shown in FIG. 4 described above is manufactured using V will be described.
先ず、製造すべき大型タービン翼に必要な大きさのイン
ゴットを製造する。そして、このインゴットを鍛伸する
のであるが、Ｔｉ−６Ａｊ！−４Ｖは８５０℃以下では
変形抵抗が高く鍛造割れを発生しやすく、また９９０℃
以上の温度では材料の組織が（α＋β）域からβ域へと
変化して翼母材としては不適当となる為、適正なβ及び
（α＋β）域加工の組合わせによって鍛伸を行い、しか
る後、荒地鍛造を行う、この荒地鍛造は、適正な体積配
分を考慮して荒地を設計し、（α＋β）域で加工する。First, an ingot of a size necessary for the large turbine blade to be manufactured is manufactured. Then, this ingot is forged and stretched, but Ti-6Aj! -4V has high deformation resistance and tends to cause forging cracks below 850℃, and at 990℃
At temperatures above, the structure of the material changes from the (α+β) region to the β region, making it unsuitable for use as a blade base material. Therefore, forging is carried out using a combination of appropriate β and (α+β) region processing, and then After that, rough ground forging is performed. In this rough ground forging, the rough ground is designed taking into consideration appropriate volume distribution, and processed in the (α+β) area.
次に、水平飛打及び水平仕上打による型鍛造を行うので
あるが、これら型鍛造は第１図（イ）〜（ハ）に示すよ
うに大型タービン翼１の翼根部２（同図（イ））から翼
先端部３（同図（ハ））に亘って水平状態を維持した金
型を用いて（α＋β）域で同図矢印に示す方向から型鍛
造を行う。Next, die forging is performed by horizontal flying and horizontal finish striking, and these die forgings are performed as shown in Figures 1 (A) to (C). )) to the blade tip 3 ((c) in the same figure), die forging is performed from the direction shown by the arrow in the same figure in the (α+β) area using a die that maintains a horizontal state.
従って、丸断面荒地の安定が極めて良好で、均一な張り
が発生する為、歩留りが良好で厚さ寸法精度も良く、型
ずれの発生もない。Therefore, the stability of the round cross-section rough ground is extremely good, and uniform tension is generated, so the yield is good, the thickness dimensional accuracy is good, and mold deviation does not occur.
次に第２図に示す如く、翼根部２を固定し、翼長に亘っ
て所定の角度（α＋β）域の熱間で捩り加工を加える。Next, as shown in FIG. 2, the blade root portion 2 is fixed, and a hot twisting process is applied over the length of the blade at a predetermined angle (α+β).
この予備捩り加工によって次工程での成形型上での安定
が確保される。This preliminary twisting ensures stability on the mold in the next step.
そして、前記したように（α＋β）域で加熱され予備捩
り加工された半製品を捩り成形金型内に挿入して強制拘
束矯正を行い、この状態のままで３００℃以下になるま
で金型的冷却を施す、この段階で極めて三次元形状精度
に優れた半製品が得られる。Then, as mentioned above, the semi-finished product heated in the (α+β) region and pre-twisted is inserted into the twist molding mold, forced restraint correction is performed, and the mold is kept in this state until the temperature reaches 300℃ or less. At this stage of cooling, a semi-finished product with extremely high three-dimensional shape accuracy is obtained.
最後に７００〜７５０℃の範囲内で焼鈍を行うのである
が、本発明により製造する製品は大型薄肉形状のもので
ある為、製品形状を彫刻した上下金型で前記捩り成形加
工を施した半製品を拘束した状態で行う。かかる如く行
うことによって、変形や残留応力を完全に防止した製品
が得られることとなる。Finally, annealing is performed within the range of 700 to 750°C. Since the products manufactured by the present invention are large and thin-walled, the torsion-forming process is performed using upper and lower molds engraved with the product shape. Perform with the product restrained. By doing so, it is possible to obtain a product that is completely free from deformation and residual stress.
本発明方法により、下記第１表に示す成分のＴｉ−６Ａ
Ｊ−４Ｖを用いて大型タービン翼を製造した場合の金属
組織、機械的性質、寸法精度を夫々第３図、第２表及び
第３表に示す。By the method of the present invention, Ti-6A of the components shown in Table 1 below
The metal structure, mechanical properties, and dimensional accuracy of large turbine blades manufactured using J-4V are shown in FIG. 3, Table 2, and Table 3, respectively.
本実施例では鍛伸は９３０℃、また荒地鍛造、水平飛打
及び水平仕上打は９３０℃の温度で鍛造し、また予備捩
り加工は翼先端部を約８５°回転させて行った。そして
、捩り成形加工終了後３００℃迄冷却し、７０５℃で３
時間焼鈍して大型タービン翼を製造した。In this example, forging was carried out at a temperature of 930°C, and rough ground forging, horizontal flying and horizontal finishing were forging at a temperature of 930°C, and preliminary twisting was carried out by rotating the blade tip by approximately 85°. After the twist forming process was completed, it was cooled to 300°C, and then heated to 705°C for 30 minutes.
A large turbine blade was manufactured by time annealing.
第１表
単位二重量％
第２表
ＡＮＮ、７０５℃Ｘ ３ Ｈ４Ｆ Ｃ
第３表
上記第２表及び第３表、第３図から本発明方法の優秀さ
が明らかである。Table 1: Unit duplex weight % Table 2: ANN, 705° C.
（発明の効果）
以上説明したように本発明に係る大型タービン翼の製造
方法は、三次元形状に複雑に捩れた大型タービン翼を鍛
造により製造する方法において、翼根から翼先端に亘っ
て水平状態を維持したまま型鍛造し、核型鍛造終了後タ
ービン翼に所要の捩り加工を施し、かかる状態下におい
て強制拘束矯正を行った後拘束状態で熱処理するもので
あり、翼根から翼先端に亘って水平状態を維持したまま
型鍛造する為、荒地の安定が極めて良好となると共に、
型鍛造時におけるスラスト力の発生がない。(Effects of the Invention) As explained above, the method for manufacturing a large turbine blade according to the present invention is a method for manufacturing a large turbine blade complicatedly twisted into a three-dimensional shape by forging. The turbine blade is die-forged while maintaining its condition, and after the nuclear die forging is completed, the turbine blade is subjected to the required twisting process. Under such conditions, the turbine blade is forcibly restrained and straightened, and then heat-treated in the restrained state. Since die forging is performed while maintaining a horizontal state throughout, stability on rough ground is extremely good, and
No thrust force is generated during die forging.
また、本発明方法は、拘束状態を維持して熱処理する為
、変形や残留応力を完全に防止した製品が得られる。す
なわち本発明方法は、■単純形状の段階で精度よい塑性
加工を終える。■涙れ形状にした後、金型拘束矯正を実
施する。■拘束熱処理で変形、残留応力の防止を図る。Furthermore, since the method of the present invention performs heat treatment while maintaining a restrained state, a product can be obtained that completely prevents deformation and residual stress. That is, in the method of the present invention, precise plastic working is completed at the stage of (1) a simple shape. ■After forming the teardrop shape, perform mold restraint correction. ■Prevent deformation and residual stress through restraint heat treatment.
ことによって寸法精度向上と熱処理特性の確保、すなわ
ち残留応力の防止を図ったものである。This is intended to improve dimensional accuracy and ensure heat treatment characteristics, that is, to prevent residual stress.
第１図（イ）〜（ハ）は本発明方法の型鍛造時における
翼根部（イ）、中央部（ロ）及び翼先端部（ハ）の説明
図、第２図は予備捩り加工時の説明図、第３図は実験に
より得られた製品の金属組織図、第４図（イ）は大型タ
ービン翼の例示図面、（ロ）〜（ニ）は従来方法による
場合の第１図（イ）〜（ハ）と同様の図面である。
１は大型タービン翼、２は翼根部、３は翼先端部。
第１図
第２図
第３図
−５２のａFigures 1 (a) to (c) are explanatory diagrams of the blade root (a), center (b), and blade tip (c) during die forging using the method of the present invention, and Figure 2 is during preliminary twisting. An explanatory drawing, Fig. 3 is a metallographic diagram of the product obtained by the experiment, Fig. 4 (a) is an illustrative drawing of a large turbine blade, and (b) to (d) are Fig. 1 (i) when using the conventional method. ) to (c). 1 is a large turbine blade, 2 is a blade root, and 3 is a blade tip. Figure 1 Figure 2 Figure 3-52a
Claims (1)
により製造する方法において、翼根から翼先端に亘って
水平状態を維持したまま型鍛造し、該型鍛造終了後ター
ビン翼に所要の捩り加工を施し、かかる状態下において
強制拘束矯正を行った後拘束状態で熱処理することを特
徴とする大型タービン翼の製造方法。(1) In a method of manufacturing a large turbine blade with a complex twist into a three-dimensional shape by forging, the blade is die-forged while maintaining a horizontal state from the blade root to the blade tip, and after the die forging is completed, the required shape of the turbine blade is A method for producing a large turbine blade, which comprises twisting the blade, performing forced restraint correction under such conditions, and then heat-treating the blade under restraint.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP7571387A JPS63241118A (en) | 1987-03-27 | 1987-03-27 | Manufacture of large-sized turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP7571387A JPS63241118A (en) | 1987-03-27 | 1987-03-27 | Manufacture of large-sized turbine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS63241118A true JPS63241118A (en) | 1988-10-06 |
Family
ID=13584160
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP7571387A Pending JPS63241118A (en) | 1987-03-27 | 1987-03-27 | Manufacture of large-sized turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS63241118A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012043374A1 (en) | 2010-09-27 | 2012-04-05 | 日立金属株式会社 | Manufacturing method for blade material and manufacturing device for blade material |
| KR20130007994A (en) * | 2011-07-11 | 2013-01-21 | 미쯔비시 헤비 인더스트리즈 리미티드 | Method of producing turbine blade |
| CN103624107A (en) * | 2013-12-06 | 2014-03-12 | 天水锻压机床(集团)有限公司 | Flame straightening process for cutter blade of plate shearing machine |
-
1987
- 1987-03-27 JP JP7571387A patent/JPS63241118A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012043374A1 (en) | 2010-09-27 | 2012-04-05 | 日立金属株式会社 | Manufacturing method for blade material and manufacturing device for blade material |
| US9221095B2 (en) | 2010-09-27 | 2015-12-29 | Hitachi Metals, Ltd. | Manufacturing method for a blade material |
| KR20130007994A (en) * | 2011-07-11 | 2013-01-21 | 미쯔비시 헤비 인더스트리즈 리미티드 | Method of producing turbine blade |
| JP2013019294A (en) * | 2011-07-11 | 2013-01-31 | Daido Steel Co Ltd | Method for manufacturing turbine blade |
| CN103624107A (en) * | 2013-12-06 | 2014-03-12 | 天水锻压机床(集团)有限公司 | Flame straightening process for cutter blade of plate shearing machine |
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