JPS614808A - Moving blade for high pressure steam turbine - Google Patents
Moving blade for high pressure steam turbineInfo
- Publication number
- JPS614808A JPS614808A JP59125078A JP12507884A JPS614808A JP S614808 A JPS614808 A JP S614808A JP 59125078 A JP59125078 A JP 59125078A JP 12507884 A JP12507884 A JP 12507884A JP S614808 A JPS614808 A JP S614808A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- insertion hole
- final
- parts
- blades
- 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.)
- Granted
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
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
- F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【発明の詳細な説明】
産業上の利用分野
本発明は高圧蒸気タービン動翼の改良に関するものであ
る。DETAILED DESCRIPTION OF THE INVENTION Field of the Invention This invention relates to improvements in high pressure steam turbine rotor blades.
従来の技術
高圧蒸気タービンで使用されるタービン動翼０３．０４
は第６図〜第９図に示す如くＴ型翼根０８が使用される
ことが多い、この翼根０８は加工が簡単で翼植込みが簡
単なことなどの利益が多い。その植込み方法を説明する
と、第９図のタービンディスク側の翼溝０１の中間の挿
入孔０２にタービンの翼根０８を挿入し、翼０３を第１
１図の矢印の方向に押して順次並べる。最後の一本の翼
を残した状態を第１２図に示すと左側の他方の翼０３の
シュラウド部Ｓが挿入孔０２に突出しており、このまま
では最後の翼を挿入することができない。Prior Art Turbine rotor blades used in high pressure steam turbines 03.04
As shown in FIGS. 6 to 9, a T-shaped blade root 08 is often used. This blade root 08 has many advantages such as being easy to process and easy to install. To explain the installation method, the blade root 08 of the turbine is inserted into the intermediate insertion hole 02 of the blade groove 01 on the turbine disk side in FIG.
Push in the direction of the arrow in Figure 1 to line them up in order. FIG. 12 shows a state in which the last blade remains. The shroud portion S of the other left wing 03 protrudes into the insertion hole 02, and the last wing cannot be inserted in this state.
発明が解決しようとする問題点
上記の如（最後の翼０４を挿入孔に挿入することができ
ない。そのため第８図に示す如（翼０３のシュラウド部
（斜線部）０５を切断して挿入孔を確保し、その挿入孔
に最終埋込具０４を植込んでいる。従って隣接翼０３の
一部を切断することにより完全な翼が一枚なくなる。又
最終埋込具０４を植込まずに歯数の状態で使用する場合
もある。Problems to be Solved by the Invention As described above (the last blade 04 cannot be inserted into the insertion hole. Therefore, as shown in FIG. is secured, and the final implant 04 is implanted in the insertion hole.Therefore, by cutting a part of the adjacent wing 03, there is no complete wing.Also, without implanting the final implant 04, Sometimes it is used with a certain number of teeth.
問題点を解決するための手段
本発明は、上述の問題を解決するために、次のような手
段を採っている。Means for Solving the Problems The present invention takes the following measures in order to solve the above-mentioned problems.
タービンディスク側の翼溝に挿入孔から隣のタービン翼
を挿入したものにおいて、最終翼を縦に２分割し、これ
らを前記挿入孔に挿入した後複数のボルトにより固着す
る。In a structure in which an adjacent turbine blade is inserted through an insertion hole into a blade groove on the turbine disk side, the final blade is vertically divided into two parts, which are inserted into the insertion hole and then fixed with a plurality of bolts.
実施例
本発明を添付図面の実施例により説明する。第１図〜第
５図において隣接具３（多数の翼も同様で説明を省略す
る）の翼根８をタービンディスク側の翼溝１に挿入孔２
（第４図、第９図）から挿入し順次ずらして並べる。最
終植込具４を縦に２分割して複雑な形状の方を４１とし
、簡単な形状の方を４“とし、両方の分割翼の切断面を
５とし、両方の翼を固着するねじ孔６．６′を複数個設
ける。Embodiments The present invention will be explained by way of embodiments shown in the accompanying drawings. 1 to 5, the blade root 8 of the adjacent tool 3 (the same applies to a large number of blades, and the explanation is omitted) is inserted into the blade groove 1 on the turbine disk side through the insertion hole 2.
Insert them starting from (Figures 4 and 9) and arrange them sequentially. The final implant 4 is divided vertically into two parts, the one with the more complicated shape is designated as 41, the one with the simpler shape is designated as 4'', the cut surface of both divided wings is designated as 5, and the screw holes for fixing both wings are made. 6. Provide multiple 6'.
そのねじ孔６．６′に螺着するボルトを７とし、翼の翼
根を８とし、シュラウドを９とする。The bolt screwed into the screw hole 6.6' is numbered 7, the blade root of the wing is numbered 8, and the shroud is numbered 9.
最終植込具４０２分割した一方４′の翼根８を前記挿入
孔２に挿入し、次に他方４“を挿入し、両者をボルト７
により固着し、溝１を少しずらして翼根８が溝１から抜
けないようにする。ボルト７の数は翼の大きさにより適
宜変える。Insert the blade root 8 of one 4' of the final implant 402 into the insertion hole 2, then insert the other 4'', and connect both with the bolt 7.
The groove 1 is slightly shifted to prevent the blade root 8 from coming out of the groove 1. The number of bolts 7 is changed as appropriate depending on the size of the wing.
作用
多数の翼３はＴ型翼根８を挿入孔２から入れ溝１をずら
してＴ型翼根８が溝１から抜げないようにする。最終植
込具４は縦に分割して形状の複雑な一方４′と形状の簡
単な他方４“とじ、一方４′を隣接具３との干渉を回避
して植込み、他方４“を植込む。その後両者をボルトに
より固着する。In the multiple blades 3, the T-shaped blade root 8 is inserted into the insertion hole 2 and the groove 1 is shifted to prevent the T-shaped blade root 8 from coming out from the groove 1. The final implant 4 is divided vertically, and one 4' with a complicated shape and the other 4" with a simple shape are tied together. One 4' is implanted while avoiding interference with the adjacent implant 3, and the other 4" is implanted. . After that, both are fixed with bolts.
発明の効果
植込翼を２分割することにより最終翼の植込みを可能と
し、タービン全周に完全な翼を植込むことが可能である
。又分割された２個を互いにボルトで締付けることによ
り強度低下を防ぎ、かつ振動発生時に摩擦による制振効
果が期待できる。Effects of the Invention By dividing the implanted blade into two parts, the final blade can be implanted, and a complete blade can be implanted all around the turbine. Furthermore, by tightening the two divided pieces together with bolts, a decrease in strength can be prevented, and a damping effect due to friction can be expected when vibration occurs.
第１図は本発明の動翼の斜視図、第２図は動翼の平面図
、第３図は２分割したタービンの斜視図、第４図は挿入
孔の斜視図、第５図は挿入孔に分割した翼を挿入した状
態を示す斜視図、第６図以下は従来例を示し、第６図は
動翼の斜視図、第７寵児た図、第１１図は翼の埋込みを
始めた状態の図、第１２図は最後の１本の翼を残した状
態の図、第１３図は第１２図の８部を切断して挿入孔を
確保した状態の図。
１・・翼溝、２・・挿入孔、３・・隣接具、４・・最終
植込具、４／・・一方の植込翼、４“・・他方の植込翼
、５・・切断面、６・・ねじ孔、７・・ボルト、８・―
翼根、９・−シュラウド。
第１図
第？図Figure 1 is a perspective view of the rotor blade of the present invention, Figure 2 is a plan view of the rotor blade, Figure 3 is a perspective view of the turbine divided into two parts, Figure 4 is a perspective view of the insertion hole, and Figure 5 is the insertion hole. A perspective view showing the divided blade inserted into the hole, Figure 6 and the following show the conventional example, Figure 6 is a perspective view of the rotor blade, No. 7 is a popular view, and Figure 11 is when the blade has started to be embedded. Figure 12 is a diagram with the last blade remaining, and Figure 13 is a diagram with the insertion hole secured by cutting off part 8 of Figure 12. 1...Blade groove, 2...Insertion hole, 3...Adjacent tool, 4...Final implantation tool, 4/...One implantation wing, 4''...Other implantation wing, 5...Cutting Surface, 6...screw hole, 7...bolt, 8...
Wing root, 9.-Shroud. Figure 1 No.? figure
Claims (1)
たものにおいて、最終翼を縦に２分割し、これらを前記
挿入孔に挿入した後複数のボルトにより固着してなる高
圧蒸気タービンの動翼。In a high-pressure steam turbine in which an adjacent blade is inserted into a blade groove on the turbine disk side through an insertion hole, the final blade is vertically divided into two parts, which are inserted into the insertion hole and then fixed with a plurality of bolts. Wings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP59125078A JPS614808A (en) | 1984-06-20 | 1984-06-20 | Moving blade for high pressure steam turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP59125078A JPS614808A (en) | 1984-06-20 | 1984-06-20 | Moving blade for high pressure steam turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS614808A true JPS614808A (en) | 1986-01-10 |
| JPH0425407B2 JPH0425407B2 (en) | 1992-04-30 |
Family
ID=14901283
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP59125078A Granted JPS614808A (en) | 1984-06-20 | 1984-06-20 | Moving blade for high pressure steam turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS614808A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4784571A (en) * | 1987-02-09 | 1988-11-15 | Westinghouse Electric Corp. | Apparatus and method for reducing blade flop in steam turbine |
| US4907459A (en) * | 1988-03-15 | 1990-03-13 | Mitsubishi Denki Kabushiki Kaisha | Vortex flow meter |
| US4938074A (en) * | 1988-03-17 | 1990-07-03 | Mitsubishi Denki Kabushiki Kaisha | Vortex flow meter |
| US5109703A (en) * | 1989-08-21 | 1992-05-05 | Mitsubishi Denki K.K. | Vortex flow meter |
| US5511948A (en) * | 1994-02-18 | 1996-04-30 | Kabushiki Kaisha Toshiba | Rotor blade damping structure for axial-flow turbine |
| WO2001057365A1 (en) * | 1998-09-14 | 2001-08-09 | General Electric Company | Means for securing a bucket to a turbine wheel and methods of installation |
| EP1757772A2 (en) * | 2005-08-24 | 2007-02-28 | General Electric Company | Stacked steampath for steam turbines |
| KR100785544B1 (en) * | 2000-02-03 | 2007-12-12 | 제너럴 일렉트릭 캄파니 | Means for securing a bucket to a turbine wheel and methods of installation |
-
1984
- 1984-06-20 JP JP59125078A patent/JPS614808A/en active Granted
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4784571A (en) * | 1987-02-09 | 1988-11-15 | Westinghouse Electric Corp. | Apparatus and method for reducing blade flop in steam turbine |
| US4907459A (en) * | 1988-03-15 | 1990-03-13 | Mitsubishi Denki Kabushiki Kaisha | Vortex flow meter |
| US4938074A (en) * | 1988-03-17 | 1990-07-03 | Mitsubishi Denki Kabushiki Kaisha | Vortex flow meter |
| US5109703A (en) * | 1989-08-21 | 1992-05-05 | Mitsubishi Denki K.K. | Vortex flow meter |
| US5511948A (en) * | 1994-02-18 | 1996-04-30 | Kabushiki Kaisha Toshiba | Rotor blade damping structure for axial-flow turbine |
| WO2001057365A1 (en) * | 1998-09-14 | 2001-08-09 | General Electric Company | Means for securing a bucket to a turbine wheel and methods of installation |
| KR100785544B1 (en) * | 2000-02-03 | 2007-12-12 | 제너럴 일렉트릭 캄파니 | Means for securing a bucket to a turbine wheel and methods of installation |
| EP1757772A2 (en) * | 2005-08-24 | 2007-02-28 | General Electric Company | Stacked steampath for steam turbines |
| EP1757772A3 (en) * | 2005-08-24 | 2010-12-29 | General Electric Company | Stacked steampath for steam turbines |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH0425407B2 (en) | 1992-04-30 |
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