JPS6232201A - Structure of cascade of rotary blades in axial flow rotary machine - Google Patents
Structure of cascade of rotary blades in axial flow rotary machineInfo
- Publication number
- JPS6232201A JPS6232201A JP17107485A JP17107485A JPS6232201A JP S6232201 A JPS6232201 A JP S6232201A JP 17107485 A JP17107485 A JP 17107485A JP 17107485 A JP17107485 A JP 17107485A JP S6232201 A JPS6232201 A JP S6232201A
- Authority
- JP
- Japan
- Prior art keywords
- rotor
- blades
- welding
- blade
- connecting block
- 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
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【発明の詳細な説明】
〔発明の利用分野〕
本発明は、タービンロータの外周に放射状に植込まれる
多数の動翼に係り、特に、動翼の剛性を大きくする翼群
の製法に関する。DETAILED DESCRIPTION OF THE INVENTION [Field of Application of the Invention] The present invention relates to a large number of rotor blades embedded radially around the outer periphery of a turbine rotor, and particularly to a method for manufacturing a blade group that increases the rigidity of the rotor blades.
通常、軸流回転機械のロータディスクと動翼は個々に製
作され、かつ、動翼は一本ずつ製作され、タービン研究
会編（三宝社刊）、ア・ヴ工・シチェクリャエフ、べ・
ニス・トロヤノフスキー共著、永島俊三部訳、蒸気ター
ビン−理論と構造−に記載されているように、稲々の方
法でロータディスクに取付固定される。代表的な動翼植
込部の形式にｉｄＴ形、鞍形、フォーク形、のこ歯形、
クリスマス・ツリー形、クリスマス・ツリー形円弧植込
方式等がある。このような種々の方法によりロータディ
スクに取付固定された個々の動翼は、剛性を増すために
、シュラクト板やレーシングワイヤによシ連結され翼群
を構成することが多い。このように、翼群を構成するこ
とにより、剛性を増すので、翼に加わる流体による翼の
曲げ応力、あるいは、振動応力を低くすることができる
。しかし、しばしばこの連結部材であるシュラウド板及
びレーシングワイヤが破損することがある。さらには、
連結部材を取付けることにより、遠心力がより大きくな
シロータデイスク植込部の応力を大きくし、植込部が破
損することがある。Usually, the rotor disk and rotor blades of axial flow rotating machines are manufactured individually, and the rotor blades are manufactured one by one.
As described in Steam Turbine - Theory and Structure, co-authored by Nis Troyanovsky, translated by Shunzo Nagashima, it is attached and fixed to the rotor disk using the same method. Typical rotor blade implant types include idT type, saddle type, fork type, sawtooth type,
There are Christmas tree-shaped, Christmas tree-shaped arc planting methods, etc. In order to increase rigidity, the individual rotor blades attached and fixed to the rotor disk by these various methods are often connected by shracto plates or racing wires to form a blade group. By configuring the blade group in this way, the rigidity is increased, so that the bending stress or vibration stress of the blade due to the fluid applied to the blade can be reduced. However, the shroud plate and the lacing wire, which are the connecting members, often break. Furthermore,
By attaching the connecting member, the stress on the implanted portion of the rotor disk, where the centrifugal force is greater, is increased, and the implanted portion may be damaged.
この欠点を補う方法の一つとして、前述の公知例にも述
べられているように植込部と同様に、厚いシュラウドも
動翼と一体で削シ出し、植込後互いに溶接することがあ
る。この場合、ロータディスクに植込んだ後での溶接作
業となるため、作業性が悪く多大の作業時間を要し、溶
接による残留応力が残る欠点があった。As described in the above-mentioned known example, one way to compensate for this drawback is to cut out the thick shroud together with the rotor blade and weld them together after implantation, similar to the implanted part. . In this case, since the welding work is performed after the rotor disk is implanted, the workability is poor and a large amount of work time is required, and residual stress remains due to welding.
’＜゛、、一本発明の目的は、個々に削シ出された動翼
を、・−１７
０−タデイスクに植込む前に溶接により翼群構造とし、
信頼性の高い動翼々群を提供することにある。'<゛,, An object of the present invention is to weld the rotor blades cut out individually into a blade group structure before implanting them into a ・-170-ta disk.
The objective is to provide a highly reliable moving blade group.
本発明の動翼々群は、個々の動翼には植込部を形成せず
、連結ブロックＶＣ溶接により固定し、ざらに、シュラ
ウドを溶接して翼群を構成し、溶接による残留応力を除
去するため、熱処理後、連結ブロックにフォーク形の植
込溝とビン孔ヲ加工ｔ。The rotor blade group of the present invention does not form an embedded part in each rotor blade, but is fixed by connecting block VC welding, and the shroud is roughly welded to form the blade group, thereby eliminating residual stress due to welding. To do this, after heat treatment, we machined fork-shaped planting grooves and bottle holes in the connecting block.
翼群としてロータディスクに植込むことを特徴とする。It is characterized by being embedded in the rotor disk as a group of wings.
以下、本発明の実施例を図面によシ説明する。 Embodiments of the present invention will be described below with reference to the drawings.
第２図は本発明の動翼１の斜視図である。シュラウド２
及び根元接合部３は動翼１と一体で削り出されており、
シュラウド２ｖＣは隣接する動翼のシュラウドと溶接す
るための開先１２が設けられている。また、根元溶接面
１１にも開先が設けられている。FIG. 2 is a perspective view of the rotor blade 1 of the present invention. shroud 2
and the root joint part 3 is cut out integrally with the rotor blade 1,
The shroud 2vC is provided with a groove 12 for welding to the shroud of an adjacent rotor blade. Further, the root welding surface 11 is also provided with a groove.
第３図は動翼１を連結する連結ブロック４の斜視図であ
る。動翼１を溶接する外周面１３は幅方向（軸方向）の
中央部が半径が大きく、両側を小さくして溶接開先が設
けられている。ロータディスク９（第４図に図示）へ植
込むための、一点鎖線で示した植込溝７及びビン孔８は
動翼１の溶接前には加工されていないか、もしくは、仕
上代を十分残した下加工が行なわれている。FIG. 3 is a perspective view of the connecting block 4 that connects the rotor blades 1. The outer circumferential surface 13 to which the rotor blade 1 is welded has a large radius at the center in the width direction (axial direction), and has a small radius on both sides to provide welding grooves. The implantation groove 7 and bottle hole 8 shown by the dashed line for implantation into the rotor disk 9 (shown in FIG. 4) are not machined before welding the rotor blade 1, or the finishing allowance is sufficient The rest of the preliminary work is being done.
第１図は本発明における翼群構造の斜視図であり、五本
の翼群の例を示す。本翼群は、第１図に示した動翼１ａ
から動翼１ｅまでの五本の翼をたばねた後、第２図に示
した連結ブロック４ｖｃ溶接されて形成される。溶接は
電子ビーム溶接等で行なわれ連結ブロック４と溶接部５
、隣接翼のカバーと溶接部６で行なわれている。溶接後
、翼群は熱処理され、残留応力が除去されるが、小ブロ
ックの翼群毎に熱処理できるので、作業性も良く熱処理
も完全に行なうことができる。次に、ロータディスク９
・＼の植込み溝７とビン孔８の加工を行う。FIG. 1 is a perspective view of the blade group structure according to the present invention, showing an example of five blade groups. This blade group consists of the rotor blade 1a shown in FIG.
After the five blades from 1 to 1e are tied together, the connecting block 4vc shown in FIG. 2 is welded to form the connecting block 4vc. Welding is performed by electron beam welding etc., and the connecting block 4 and the welded part 5 are welded together.
This is done at the welding section 6 with the cover of the adjacent wing. After welding, the blade group is heat-treated to remove residual stress, and since the heat treatment can be performed on a small block-by-blade group, the workability is good and the heat treatment can be performed completely. Next, rotor disk 9
・Machining the implant groove 7 and bottle hole 8.
第４図は翼群のロータディスク９・＼の植込み状態を示
す斜視図である。溶接部５．６は植込み前には加工され
平坦になっている。１群状態での植込みとなるため、植
込部はフォークタイプになっており、半径方向外周から
ロータディスク９へ植込まれ、ビン孔８に対応してディ
スクに設けられている孔へビン１０を打込むことによっ
て固定される。FIG. 4 is a perspective view showing the installed state of the rotor disk 9 of the blade group. The welded part 5.6 is machined and flattened before implantation. Since the implantation is done in one group, the implantation part is of a fork type, and is implanted into the rotor disk 9 from the outer periphery in the radial direction, and the bins 10 are inserted into the holes provided in the disk corresponding to the bin holes 8. It is fixed by driving in.
第５図及び第６図は、他の実施例の翼群をロータディス
ク９へ植込んだ状態を示す斜視図である。5 and 6 are perspective views showing the state in which the blade group of another embodiment is embedded in the rotor disk 9. FIG.
第５図は第４図に示した溶接式７ユラウドに変えて、イ
ンテグラルカバー１４、テノン１５を備えた動翼１をシ
ュラウド板１６で連結した翼群であり、溶接代シュラウ
ドに比べて強度的に若干余裕がある場合に用いられるこ
とがある。Fig. 5 shows a blade group in which rotor blades 1 equipped with an integral cover 14 and a tenon 15 are connected by a shroud plate 16 instead of the welded type 7 rotor shown in Fig. 4. It may be used when there is some leeway.
第６図はより長い動翼１７に適用し九−例であり、連結
ブロックに溶接されたより長い動翼１７は、翼先端部で
シュラウド１８、途中でレーシングワイヤ１９ｖｃよシ
連結された翼群である。FIG. 6 shows an example of applying a longer rotor blade 17, and the longer rotor blade 17 welded to the connection block is a blade group connected by a shroud 18 at the blade tip and a racing wire 19vc in the middle. be.
これらの実施例によれば、翼群毎に分割されており熱処
理を完全に行うことが可能であり、溶接による残留応力
を除去することができ、７ユラウド及びレーシングワイ
ヤの信頼性を向上はせることができる。また、植込部は
一体で形成された連結ブロック４であるため、各動翼［
作用する遠心力は各ピン１０Ｖｃ分散され、互いに保持
し合うため、一本づつの植込法に比べて植込部の応力を
十分小さくできる効果がある。According to these examples, since the blades are divided into blade groups, it is possible to perform complete heat treatment, and the residual stress caused by welding can be removed, improving the reliability of the 7-Road and racing wires. be able to. In addition, since the implanted portion is the integrally formed connecting block 4, each rotor blade [
The centrifugal force acting on each pin is dispersed by 10 Vc and the pins are held together, which has the effect of sufficiently reducing the stress at the implanted portion compared to the method of implanting one pin at a time.
他の効果として、シュラウド及びレーシングワイヤの溶
接作業がしやすく、作業時間を短縮できる。植込部の溝
形状がフォークタイプで最も単純な形状であるので、動
翼及びロータディスクの植込溝の加工を大巾に短縮でき
る。Another effect is that the shroud and lacing wire can be easily welded and the working time can be shortened. Since the groove shape of the implanted portion is the simplest shape of the fork type, the machining of the implanted grooves of the rotor blade and rotor disk can be greatly shortened.
なお、セラミックス等の精密鋳造材料及び鋳造技術が進
歩した場合には、複数枚の動翼４群を溶接なしｖｃ精密
鋳造で製作することにより、より苛酷な条件で運転する
ことができる動翼４群を提供することができる。In addition, if precision casting materials such as ceramics and casting technology advance, the moving blades 4 can be operated under more severe conditions by manufacturing the 4 groups of moving blades using VC precision casting without welding. group can be provided.
本発明によれば、シュラウド及びレーシングワイヤの残
留応力の除去及び植込部の応力を減少させることができ
るので転流回転機械の動翼の信頼性の向上に貢献すると
ころ多大である。According to the present invention, residual stress in the shroud and lacing wire can be removed and stress in the implanted portion can be reduced, which greatly contributes to improving the reliability of the rotor blades of commutation rotary machines.
第１図は本発明の一実施例の斜視図、第２図は第１図の
動翼の斜視図、第３図は第１図の連結ブロックの斜視図
、第４図は本実施例の翼群をロータディスクに植込んだ
斜視図、第５図及び第６図は他の実施例の翼群をロータ
ディスクに植込んだ斜視図である。Fig. 1 is a perspective view of one embodiment of the present invention, Fig. 2 is a perspective view of the moving blade of Fig. 1, Fig. 3 is a perspective view of the connecting block of Fig. 1, and Fig. 4 is a perspective view of the rotor blade of this embodiment. FIGS. 5 and 6 are perspective views showing blade groups of other embodiments installed in the rotor disk. FIGS.
Claims (1)
込まれる動翼において、 複数枚の前記動翼の根元接合部を連結ブロックに溶接し
、前記ロータディスクに植込む前に翼群を構成したこと
を特徴とする軸流回転機の動翼翼群構造。 ２、前記連結ブロックに複数の周方向植込溝及び前記ロ
ータディスクに固定するためのピン孔を設けたことを特
徴とする特許請求の範囲第１項記載の軸流回転機の動翼
翼群構造。[Claims] 1. In a rotor blade that is implanted radially around the outer periphery of a rotor disk of an axial flow rotating machine, root joints of a plurality of rotor blades are welded to a connecting block, and the rotor blade is implanted in the rotor disk. A rotor blade group structure of an axial flow rotary machine, characterized in that a blade group is configured in the front. 2. The rotor blade group structure for an axial flow rotary machine according to claim 1, wherein the connecting block is provided with a plurality of circumferential implant grooves and pin holes for fixing to the rotor disk. .
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17107485A JPS6232201A (en) | 1985-08-05 | 1985-08-05 | Structure of cascade of rotary blades in axial flow rotary machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP17107485A JPS6232201A (en) | 1985-08-05 | 1985-08-05 | Structure of cascade of rotary blades in axial flow rotary machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS6232201A true JPS6232201A (en) | 1987-02-12 |
Family
ID=15916536
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP17107485A Pending JPS6232201A (en) | 1985-08-05 | 1985-08-05 | Structure of cascade of rotary blades in axial flow rotary machine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS6232201A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH02221772A (en) * | 1989-02-22 | 1990-09-04 | Arai Pump Mfg Co Ltd | Retainer for peripheral metal fitting type oil seal |
| US5100296A (en) * | 1990-04-09 | 1992-03-31 | Westinghouse Electric Corp. | Steam turbine integral control stage blade group |
| JP2004036546A (en) * | 2002-07-04 | 2004-02-05 | Mitsubishi Heavy Ind Ltd | Steam turbine partition plate |
| US7798779B2 (en) * | 2006-03-02 | 2010-09-21 | Hitachi, Ltd. | Steam turbine blade, and steam turbine and steam turbine power plant using the blade |
| RU2599689C2 (en) * | 2014-08-13 | 2016-10-10 | Андрей Витальевич Билан | Packages of working blades with combined shanks |
-
1985
- 1985-08-05 JP JP17107485A patent/JPS6232201A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH02221772A (en) * | 1989-02-22 | 1990-09-04 | Arai Pump Mfg Co Ltd | Retainer for peripheral metal fitting type oil seal |
| US5100296A (en) * | 1990-04-09 | 1992-03-31 | Westinghouse Electric Corp. | Steam turbine integral control stage blade group |
| JP2004036546A (en) * | 2002-07-04 | 2004-02-05 | Mitsubishi Heavy Ind Ltd | Steam turbine partition plate |
| US7798779B2 (en) * | 2006-03-02 | 2010-09-21 | Hitachi, Ltd. | Steam turbine blade, and steam turbine and steam turbine power plant using the blade |
| RU2599689C2 (en) * | 2014-08-13 | 2016-10-10 | Андрей Витальевич Билан | Packages of working blades with combined shanks |
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