JPS61164002A - Turbine blade - Google Patents

Turbine blade

Info

Publication number
JPS61164002A
JPS61164002A JP486185A JP486185A JPS61164002A JP S61164002 A JPS61164002 A JP S61164002A JP 486185 A JP486185 A JP 486185A JP 486185 A JP486185 A JP 486185A JP S61164002 A JPS61164002 A JP S61164002A
Authority
JP
Japan
Prior art keywords
piece
preventing piece
corrosion preventing
fitting
corrosion
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
Application number
JP486185A
Other languages
Japanese (ja)
Inventor
Kenichi Okuno
研一 奥野
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Toshiba Corp
Original Assignee
Toshiba Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Toshiba Corp filed Critical Toshiba Corp
Priority to JP486185A priority Critical patent/JPS61164002A/en
Publication of JPS61164002A publication Critical patent/JPS61164002A/en
Pending legal-status Critical Current

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

PURPOSE:To well attach a corrosion preventing piece while prevent excessive stress from acting on the corrosion preventing piece, by dividing the corrosion preventing piece to be attached to a blade element main unit along its longitudinal direction while forming a male and a female part fitting to each other in a butt end part of each corrosion preventing piece. CONSTITUTION:A blade element main unit 1, if it reaches a part of predetermined height from the root, applies a twist so as to rapidly contract the sectional shape. Here a corrosion preventing piece, provided in a leading edge part of the blade element main unit 1, is divided into an upper and a bottom part 7, 8 in the part of said predeter mined height. And the upper part corrosion preventing piece 7, integrally providing in its one side a fitting male part 9 further forming a protrusive small piece 11 in the fitting male part 9, is attached in a condition being left as it is to the leading edge part of the blade element main unit 1 through a connection part 3. While the bottom part corrosion preventing piece 8 provides in its one side a fitting female part 10 further forms a cavity groove 12, fitting the protrusive small piece 11, in the fitting female part 10. In this way, a turbine blade can both well attach the corro sion preventing piece to the blade element and prevent excessive stress from acting on the corrosion preventing piece.

Description

【発明の詳細な説明】 ［発明の技術分野］ 本発明は、タービン羽根（ユ係り、特（ユそのｌｉｌ、
素前縁部２ユ被着される防食片を分割形Ｃ：よること（
二よって防食片（二作用する応力を極力緩和せしめよう
とするタービン羽根の改良Ｃ−関する。Detailed Description of the Invention [Technical Field of the Invention] The present invention relates to a turbine blade
Separate the anti-corrosion piece to be applied to the front edge 2 parts.
2. Corrosion-preventing pieces (2) Improvements to turbine blades in which the stress acting on the blades is to be alleviated as much as possible.

［発明の技術的背景］ 近時、蒸気タービンは、出力の増加の一途を辿り、これ
（−比例して最終段落（：位置する動翼も長翼となって
いる。ところが、その翼長に比例する割合には作動蒸気
の温度・圧力が高まらず、このため作動蒸気が最終段落
近傍（二型ると、水滴があられれ、いわゆる蒸気・水滴
の２相流となって動翼をまともＣ；攻撃することがある
。この場合の水筒の動きを子細Ｃ２分析すると、水滴は
蒸気（二もまして比重が高いために、その速度が遅く、
このため１回転中の動翼の前縁部腹側というよりもむし
ろその背側に衝突する傾向が強い。[Technical Background of the Invention] In recent years, the output of steam turbines has continued to increase, and the rotor blades located there have also become longer blades. The temperature and pressure of the working steam do not increase at a proportional rate, and as a result, the working steam near the final stage (in type 2, water droplets form, so-called two-phase flow of steam and water droplets, and the rotor blades are heated to a normal C). A detailed C2 analysis of the movement of the water bottle in this case reveals that the water droplets are vapor (moreover, their speed is slow due to their high specific gravity;
For this reason, there is a strong tendency to collide with the dorsal side of the leading edge of the rotor blade during one revolution rather than the ventral side thereof.

上記背側に水滴が衝突すると、これが長年の運転（ユよ
って繰り返され、つい１ユＦ′ｉ動翼の侵食を誘発する
要因の一つになっている。When water droplets collide with the dorsal side, this is repeated over many years of operation, and is one of the factors that induces erosion of the F'i rotor blade.

従来、水滴による侵食を防止するため、タービン羽根は
、第５図に示されるように、翼素本体（１）の前＃！部
（ユ、別個に作製する防食片（２）を接合部（３）で溶
接被着し、これ１ユよって水滴からの攻撃を防止してい
る。そして、防食片（２１１！、水滴からのまともな攻
撃（−も抗し得るよう、耐食、耐熱を有する材料、例え
ば高クロム鋼が使用されている。Conventionally, in order to prevent erosion by water droplets, turbine blades are placed in front of the blade body (1) as shown in FIG. A separately prepared anti-corrosion piece (2) is welded to the joint (3) to prevent attacks from water droplets. Corrosion- and heat-resistant materials, such as high-chromium steel, are used to withstand a reasonable attack.

［背景技術の問題点］ ところで、動翼の前縁部（ユ被着される防食片（２）は
、第５図でも理解されるように、翼素本体（１）の長手
方向に沿って設けられているためＩ′−１翼素が回転中
に捩り戻り〔アンツイスト〕があると、これ（ユつれて
過度な応力が生起することがある。すなわち、タービン
羽根は、その根元から先端に向って徐々（ユ捩りが加え
られており、この捩り度合Ｃ二よって作動蒸気のエネル
ギを有効１−引き出し、それを動力Ｃ；変換せしめてい
る。このような捩り形状に見合うようＣ：、防食片（２
）ハ翼素本体ｔｔ＋の前線部（ユ溶接被着されているも
のであり、上述捩り戻りによって防食片（２）は、第６
図シー示されるよう（二、クラック（４）が発生し、つ
いには接合部（３）ないしは翼素本体（１）にまでそれ
が伸長するおそれがある。このように、クラックが発生
すると、当然ながらタービン羽根飛散という１大事故に
至らしめる〇 一方、近時、発電設備に対する要望は、多様化し、とｎ
ｔ二伴いタービン羽根の断面形状ならびＣ：捩り度合も
多様化しており、従来のように、ｊ！素本体の長手方向
ｆユ沿って防食片を被着するとは限らず、例えばＷＪ７
図（二足されるようζユ、翼素本体（１）の根元からあ
る高さＨを境（ユ捩り角度を特殊な角度（−してその断
面形状をがらりと変えるものがある。このような形状を
有するタービン羽根は、＃！８図示のよう１ユ従来形状
の防食片（２）をそのまま翼素本体（Ｉｌｌ−被着でき
ず、自ずと加工技術上、溶接技術上の困難性を招来し、
また出来上り寸法精度艦−もバラツキを有する等の問題
がある。[Problems in the Background Art] By the way, as can be understood from FIG. Because of this, if the I'-1 blade element twists back during rotation, excessive stress may occur due to untwisting of the I'-1 blade element during rotation. A twist is gradually applied to the engine, and the degree of twist C effectively extracts the energy of the working steam and converts it into power C. Anti-corrosion piece (2
) The front part of the blade element main body tt+ (Y) is welded and the anti-corrosion piece (2) is
As shown in the figure (2), there is a risk that a crack (4) will occur and eventually extend to the joint (3) or the blade element body (1). 〇On the other hand, recently, requests for power generation equipment have become diversified.
With t2, the cross-sectional shape of the turbine blade and the degree of twist are also diversifying, and as in the past, j! It is not always necessary to cover the anti-corrosion piece along the longitudinal direction f of the element body, for example, WJ7
There are some types that completely change the cross-sectional shape by changing the torsion angle at a special angle (-), which is a certain height H from the root of the wing element body (1). For turbine blades with a shape of death,
There are also problems such as variations in the finished dimensional accuracy of the ships.

［発明の目的］ 本発明は、上記の事情ｌ：照してなされ友ものでおって
、翼素の断面形状の種類を問わすに防食片が良好（：被
着でき、しかも防食には過度な応力が発生しないよう（
ユその形状（ユ改良を加えｔタービン羽根を提供するこ
とを目的とする。[Purpose of the Invention] The present invention has been made in view of the above-mentioned circumstances (1), and provides a good anti-corrosion piece regardless of the type of cross-sectional shape of the wing element. To prevent stress from occurring (
The purpose is to provide a turbine blade with an improved shape.

［発明の概要コ 本発明は、（１）防食片を分割すること。（２）分割さ
れ次防食片の一側は嵌合雄部を有すること。（３）分割
された他の防食片の一側は嵌合雌部を有すること。（４
）嵌合雄部は突出小片を一体的（−有すること。[Summary of the Invention] The present invention includes (1) dividing the anticorrosion piece. (2) One side of the divided anti-corrosion piece shall have a mating male part. (3) One side of the other divided anti-corrosion piece has a fitting female part. (4
) The mating male part shall have an integral (-) protruding small piece.

（５）嵌合雌部は凹陥溝を有すること。(5) The female fitting part shall have a concave groove.

を特徴とし、この構成１ユよって翼素本体の捩り戻りの
重力を抑制するようになし、過度の応力発生を防止する
ととも（−１防食片を翼素本体（ユ容易（ユ被着し易い
ようにするものである。This configuration suppresses the gravity of twisting and returning of the blade element body, and prevents the generation of excessive stress. It is intended to do so.

［発明の実施例］ 以下（一本発明の好ましい実施例を添付図を参照して説
明する。[Embodiments of the Invention] A preferred embodiment of the present invention will be described below with reference to the accompanying drawings.

第１図ないし第２図１−おいて、符号（１１は翼素本体
を示し、この翼素本体＋１１は根元からある高さＨに至
ると、その断面形状は急激（：縮小されるように拘りが
加えられている。上記翼素本体（１）の前縁部（二は防
食片（力、（８）がおる高さＨを境（二分割されている
。ここ（−分割された防食片の一方を上部防食片（力と
し１．また他の防食片を下部防食片（８）と。In Figures 1 to 2 1-, the reference numeral (11) indicates a blade element body, and when this blade element body +11 reaches a certain height H from the root, its cross-sectional shape suddenly (: shrinks). The front edge of the wing element body (1) (2 is the corrosion protection piece (force); One of the pieces is called the upper anti-corrosion piece (1), and the other piece is called the lower anti-corrosion piece (8).

便宜上杵すると、上部防食片（力の一側は、これと一体
的に嵌合雄部（９）を有する。この嵌合雄部（９）は、
突出小片αυを形成し、このまま翼素本体（１１の前縁
部に接合部（３）を介して溶接被着されている。他方。For convenience, when punched, the upper anti-corrosion piece (one side of the force has a mating male part (9) integrally therewith. This mating male part (9)
A protruding small piece αυ is formed and is welded to the leading edge of the blade element body (11) via the joint (3).

下部防食片ｆ８１　Ｈ、その−側Ｃ二嵌合雌部（１（Ｉ
を有しており、この嵌合雌部（ＩＩｒｉ凹陥溝凹陥溝削
２されている０ 上記下部防食片（８）を翼素本体（１）１ユ被着する（
二当っては、先ず、上述突出小片（１１）ｌユ凹陥溝（
１１ユ嵌め込み、ついで接合部（３）を介して溶接被着
する。し友がって、突出小片ａυと凹陥溝ｄりとの嵌合
は、若干移動できるよう（ユなっているから、翼素本体
（１）（ユ捩り戻りの変艶があられれても、当該接触部
位の摩擦作用（ユよってその動きけ吸収できるよう（ユ
なる。Lower anti-corrosion piece f81 H, its - side C two fitting female parts (1 (I
This fitting female part (IIri recessed groove 2) is covered with the lower corrosion protection piece (8) on the wing element body (1).
First, the above-mentioned protruding small piece (11) and the recessed groove (
11 is fitted and then welded through the joint (3). Therefore, the fit between the protruding small piece aυ and the recessed groove d can be moved slightly (because it is curved, the wing element body (1)) (even if there is some deformation due to twisting back), The frictional action of the contact area absorbs the movement.

第３図ないし第４図は、本発明の他の実施例を示し、Ｉ
ｌ、素本体（１）の前縁部（ユ被着する防食片（２）を
複数（二分割するものであって、この場合の防食片（２
）　、　（２＋相互の嵌合部も突出小片（１１Ｊと凹陥
溝ａ力を有しており、これによって上述のように、翼素
本体の捩り戻りの動きによる過度な応力発生を抑制し。3-4 show other embodiments of the invention,
l, A plurality of anti-corrosion pieces (2) are attached to the front edge of the main body (1).
), (2+ The mutual fitting portion also has a protruding small piece (11J) and a concave groove a force, which suppresses the generation of excessive stress due to the twisting and returning movement of the blade element body as described above.

ている。ing.

［発明の効果］ 以上説明し念ように、本発明は、タービン羽根の前縁部
に被着する防食片を分割してなり、また分割する防食片
相互に嵌合雄部と嵌合雌部を有するから、いかなる断面
形状を有するタービン羽根であってもその被着は容易と
なることはもとより、防食片相互の嵌合部は若干移動で
きるようになっているのでタービン羽根（ユ捩り戻りの
現象が生起しても、これを摩擦によって吸収でき、その
結果。[Effects of the Invention] As explained above, the present invention consists of dividing a corrosion protection piece that is attached to the leading edge of a turbine blade, and also having a male part and a female part that fit into each other between the divided corrosion protection pieces. This makes it easy to adhere to turbine blades of any cross-sectional shape, and the mating parts of the anti-corrosion pieces can be moved slightly, making it easier to prevent the turbine blades from twisting back. Even if a phenomenon occurs, it can be absorbed by friction, and as a result.

防食片１ユ過度な応力が作用しない等すぐれ几利点を有
するＣC has excellent advantages such as no excessive stress acting on the anti-corrosion piece.

【図面の簡単な説明】[Brief explanation of the drawing]

第１図に本発明の一実施例を示す概略斜視図。 第２図に第１図の概略全体組立図、第３図σ本発明の他
の実施例を示す概略全体組立図、第４図は第３図の漿略
部分図、第５図は従来の実施例を示す概略図、第６図は
防食片に侵食が発生することを説明する図、第７図は断
面形状を異にするタービン羽根の概略組立図、第８図ｆ
′ｉ第７図の防食片の概略形状を示す図である。 １・・・翼素本体　　　　２．７．８・・・防食片９・
・・嵌合雄部　　　　ｌＯ・・・嵌合雌部１１・・・突
出小片　　　　１２・・・凹陥溝代理人　弁理士　則　
近　憲　佑（ほか１名）第１図 第２図 第３図　　　第４図 第７図 第８図FIG. 1 is a schematic perspective view showing an embodiment of the present invention. 2 is a schematic overall assembly diagram of FIG. 1, FIG. 3 is a schematic overall assembly diagram showing another embodiment of the present invention, FIG. 4 is a partial partial diagram of FIG. 3, and FIG. 5 is a conventional assembly diagram. A schematic diagram showing an embodiment; FIG. 6 is a diagram explaining the occurrence of corrosion in the anti-corrosion piece; FIG. 7 is a schematic assembly diagram of turbine blades with different cross-sectional shapes; FIG. 8 f
'i is a diagram showing a schematic shape of the anti-corrosion piece shown in FIG. 7; 1... Wing element body 2.7.8... Anti-corrosion piece 9.
...Mating male part lO...Mating female part 11...Protruding small piece 12...Concave groove Agent Patent attorney rules
Kensuke Chika (and 1 other person) Figure 1 Figure 2 Figure 3 Figure 4 Figure 7 Figure 8

Claims (2)

【特許請求の範囲】[Claims] （１）翼素前縁部の形状に見合うように防食片を分割し
、その分割された防食片を翼素本体の長手方向に沿つて
被着するとともに、分割された防食片の一側に嵌合雄部
を形成し、また分割された他の防食片の一側に嵌合雌部
を削成することを特徴とするタービン羽根。(1) Divide the anti-corrosion piece to match the shape of the leading edge of the wing element, attach the divided anti-corrosion piece along the longitudinal direction of the wing element body, and attach it to one side of the divided anti-corrosion piece. A turbine blade characterized in that a male fitting part is formed and a female fitting part is cut on one side of another divided anti-corrosion piece. （２）嵌合雄部は突出小片を形成するとともに、嵌合雌
部は凹陥溝を削成していることを特徴とする特許請求の
範囲第１項記載のタービン羽根。(2) The turbine blade according to claim 1, wherein the male fitting part forms a protruding small piece, and the female fitting part has a concave groove cut therein.
JP486185A 1985-01-17 1985-01-17 Turbine blade Pending JPS61164002A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP486185A JPS61164002A (en) 1985-01-17 1985-01-17 Turbine blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP486185A JPS61164002A (en) 1985-01-17 1985-01-17 Turbine blade

Publications (1)

Publication Number Publication Date
JPS61164002A true JPS61164002A (en) 1986-07-24

Family

ID=11595455

Family Applications (1)

Application Number Title Priority Date Filing Date
JP486185A Pending JPS61164002A (en) 1985-01-17 1985-01-17 Turbine blade

Country Status (1)

Country Link
JP (1) JPS61164002A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6109873A (en) * 1998-06-17 2000-08-29 United Technologies Corporation Shield for masking a flow directing assembly
FR2954200A1 (en) * 2009-12-23 2011-06-24 Snecma PROCESS FOR MAKING A TURBOMACHINE METAL TURBINE REINFORCEMENT
US20150218953A1 (en) * 2014-02-06 2015-08-06 Rolls-Royce Plc Leading edge protector
JP2016089832A (en) * 2014-10-29 2016-05-23 アルストム テクノロジー リミテッドＡＬＳＴＯＭ Ｔｅｃｈｎｏｌｏｇｙ Ｌｔｄ Rotor blade with edge protection member

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6109873A (en) * 1998-06-17 2000-08-29 United Technologies Corporation Shield for masking a flow directing assembly
FR2954200A1 (en) * 2009-12-23 2011-06-24 Snecma PROCESS FOR MAKING A TURBOMACHINE METAL TURBINE REINFORCEMENT
WO2011076890A1 (en) * 2009-12-23 2011-06-30 Snecma Method for creating metal reinforcement for a turbine engine blade
CN102686356A (en) * 2009-12-23 2012-09-19 斯奈克玛 Method for producing a metal reinforcement for a turbine engine blade
US9199345B2 (en) 2009-12-23 2015-12-01 Snecma Method for producing a metal reinforcement for a turbine engine blade
US20150218953A1 (en) * 2014-02-06 2015-08-06 Rolls-Royce Plc Leading edge protector
EP2905424A1 (en) * 2014-02-06 2015-08-12 Rolls-Royce plc Gas turbine component with leading edge protector
US9689269B2 (en) 2014-02-06 2017-06-27 Rolls-Royce Plc Leading edge protector
JP2016089832A (en) * 2014-10-29 2016-05-23 アルストム テクノロジー リミテッドＡＬＳＴＯＭ Ｔｅｃｈｎｏｌｏｇｙ Ｌｔｄ Rotor blade with edge protection member

Similar Documents

Publication Publication Date Title
US4621979A (en) Fan rotor blades of turbofan engines
US4824328A (en) Turbine blade attachment
US5494408A (en) Bucket to wheel dovetail design for turbine rotors
EP0985801B1 (en) Blade configuration for steam turbine
JP4008015B2 (en) Dovetail joint
US10190423B2 (en) Shrouded blade for a gas turbine engine
US4692976A (en) Method of making scalable side entry turbine blade roots
RU2303703C2 (en) Dovetail joint of turbine rotor blade and wheel
GB2359341A (en) Turbine vane and blade
CA2054077A1 (en) Stationary blade design for l-oc row
JPS61164002A (en) Turbine blade
US6435833B1 (en) Bucket and wheel dovetail connection for turbine rotors
GB2106192A (en) Turbomachine blade
EP1559870B1 (en) Shrouded rotor blade for a turbomachine
JPS5776208A (en) Turbine vane
DE112018000945B4 (en) turbocharger
JPH0133765Y2 (en)
JPH06117201A (en) Assembly method for turbine moving blade
EP0353447A1 (en) Side-entry grooves for mounting turbine blades
JPS6149103A (en) Turbine rotor blade linking equipment
CN112283162B (en) Compressor rotor blade and design method thereof
JPS6033712B2 (en) Marine propulsion device
JP2002266602A (en) Rotor blade for steam turbine
JPS6153402A (en) Structure of turbine wheel of turbocharger for internal-combustion engine
JPH04123302U (en) rotor blade