JPH0724563Y2 - Turbine blade structure - Google Patents
Turbine blade structureInfo
- Publication number
- JPH0724563Y2 JPH0724563Y2 JP11976589U JP11976589U JPH0724563Y2 JP H0724563 Y2 JPH0724563 Y2 JP H0724563Y2 JP 11976589 U JP11976589 U JP 11976589U JP 11976589 U JP11976589 U JP 11976589U JP H0724563 Y2 JPH0724563 Y2 JP H0724563Y2
- Authority
- JP
- Japan
- Prior art keywords
- blade
- turbine
- circumferential direction
- gap
- key
- 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 - Lifetime
Links
Description
【考案の詳細な説明】 産業上の利用分野 本考案は、蒸気タービン等に適用されるタービン動翼構
造に関する。TECHNICAL FIELD The present invention relates to a turbine rotor blade structure applied to a steam turbine or the like.
従来の技術 従来、この種のタービン動翼構造として、例えば第9図
〜第12図に示す構成のものが知られている。2. Description of the Related Art Conventionally, as this type of turbine rotor blade structure, for example, a structure shown in FIGS. 9 to 12 is known.
すなわち、タービンロータディスク1の外周部に、周方
向に沿って蟻溝状の動翼取付け用の溝2が設けられてい
る。動翼は複数の動翼エレメントの集合によって構成さ
れ、その動翼エレメントは大部分を占める同一形状の普
通翼エレメント3と、少数の特種翼エレメント4,5,6と
からなっている。各動翼エレメント3,4,5,6は、それぞ
れタービンロータディスク1の溝2に嵌合される翼根部
3a,4a,5a,6aと、この各翼根部3a,4a,5a,6aから立上る翼
本体部3b,4b,5b,6bと、更にこの各翼本体部3b,4b,5b,6b
の先端に一体的に設けられ最終的にリング状に組合せら
れる棚部3c,4c,5c,6cとからなっている。普通翼エレメ
ント3の翼根部3aの周方向両端部は平坦に形成されてい
るが、特種翼エレメント4,5,6の翼根部4a,5a,6aの互い
に対向する端面には相互に噛合するセレーション4a′,5
a′,6a′が形成されている。That is, the dovetail-shaped groove 2 for attaching the moving blade is provided along the circumferential direction on the outer peripheral portion of the turbine rotor disk 1. The rotor blade is constituted by a set of a plurality of rotor blade elements, and the rotor blade element is composed of a common blade element 3 having the same shape which occupies most of the rotor blade elements, and a small number of special blade elements 4, 5, and 6. Each rotor blade element 3, 4, 5, 6 is a blade root portion fitted in the groove 2 of the turbine rotor disk 1, respectively.
3a, 4a, 5a, 6a, and the wing body 3b, 4b, 5b, 6b rising from each wing root 3a, 4a, 5a, 6a, and further each wing body 3b, 4b, 5b, 6b
It is composed of shelves 3c, 4c, 5c, 6c which are integrally provided at the tip of and are finally combined in a ring shape. The blade roots 3a of the normal blade element 3 are formed flat at both ends in the circumferential direction, but the blade roots 4a, 5a, 6a of the special blade elements 4, 5 and 6 have serrations that mesh with each other at their opposing end surfaces. 4a ′, 5
a ', 6a' are formed.
そして、組立て時においては、まず多数の普通翼エレメ
ント3の翼根部3aをタービンロータディスク1の溝2に
周方向に沿って挿入しながら順送りして植込み、最終的
に特種翼エレメント4,5,6の翼根部4a,5a,6aを植込ん
で、セレーション4a′,5a′,6a′を噛合させる。この
後、タービンロータディスク1の外周部に設けた開口部
1aを介して、第11図に示すように、翼根部類似形状のキ
ー7を、特種類翼エレメント4,5、6を挾む配置で普通
翼エレメント3の翼根部3a間に例えば一対打込み、これ
により各動翼エレメント3,4,5,6を周方向に圧接させて
翼止構造を得る。At the time of assembly, first, the blade root portions 3a of a large number of ordinary blade elements 3 are inserted into the groove 2 of the turbine rotor disk 1 in the circumferential direction while being sequentially fed, and finally the special blade elements 4, 5, The blade roots 4a, 5a, 6a of 6 are implanted to engage the serrations 4a ', 5a', 6a '. After this, the opening provided on the outer peripheral portion of the turbine rotor disk 1
As shown in FIG. 11, a key 7 having a blade root-similar shape is inserted through the blade 1a between the blade roots 3a of the normal blade element 3 with the special-type blade elements 4, 5 and 6 interposed therebetween, as shown in FIG. As a result, the respective blade elements 3, 4, 5 and 6 are pressed against each other in the circumferential direction to obtain the blade stop structure.
また、第12図に示すように、キー7の打込みによって、
動翼エレメントの棚部間に間隙8が生じるが、従来では
第12図に示すように、その間隙8に接続片9を挿入して
溶接部10により棚部3cに溶着固定して、これにより蒸気
等のタービン駆動流体の半径方向の漏洩防止を図ってい
る。Also, as shown in FIG. 12, by pressing the key 7,
A gap 8 is formed between the shelves of the blade elements, but conventionally, as shown in FIG. 12, a connecting piece 9 is inserted into the gap 8 and welded and fixed to the shelves 3c by a welding portion 10. This is intended to prevent radial leakage of turbine driving fluid such as steam.
考案が解決しようとする課題 このように、上述した従来のタービン動翼構造では、キ
ーの打込みによって生じる動翼エレメントの棚部間の間
隙を溶接手段で閉塞するので、種々の不都合がある。例
えば、溶接による動翼エレメントへの熱的悪影響を防止
するために作業が複雑となったり、事後的に焼鈍等の面
倒な熱処理が必要となったりする。また、動翼エレメン
トには溶接不適当な材料を使用できないため、適用材料
に制約を受ける。さらに、地熱発電プラント等の蒸気タ
ービンに適用した場合、溶接部が地熱雰囲気による応力
腐蝕割れの原因になる等である。DISCLOSURE OF THE INVENTION Problems to be Solved by the Invention As described above, the conventional turbine moving blade structure described above has various disadvantages because the gap between the shelves of the moving blade elements caused by driving the key is closed by the welding means. For example, the work is complicated in order to prevent a thermal adverse effect on the rotor blade element due to welding, and a troublesome heat treatment such as annealing is required afterwards. In addition, since a material unsuitable for welding cannot be used for the blade element, there are restrictions on the applicable material. Further, when it is applied to a steam turbine of a geothermal power plant or the like, the welded portion causes stress corrosion cracking due to the geothermal atmosphere.
本考案はこのような事情に鑑みてなされたもので、棚部
間に生じる間隙の閉塞に溶接を省略でき、組立て作業お
よび事後処理等の簡便化が図れるとともに、使用材料の
選択幅が拡大でき、かつ応力腐蝕割れの原因除去等にも
有効なタービン動翼構造を提供することを目的とする。The present invention has been made in view of such circumstances, and the welding can be omitted to close the gap between the shelves, the assembling work and the post-treatment can be simplified, and the selection range of the used material can be expanded. It is also an object of the present invention to provide a turbine blade structure that is effective for removing the cause of stress corrosion cracking.
課題を解決するための手段 本考案は、前記の目的を達成するために、タービンロー
タディスクの外周部に周方向に沿う溝を設け、この溝に
複数の動翼エレメントの各翼根部を嵌合させるとともに
相互に接合状態で周方向に配列し、かつ最終的に翼根部
間にキーを挿入して翼止力を得るタービン動翼構造にお
いて、前記キーの挿入によって前記動翼エレメント外周
部の棚部間に発生する周方向に沿う間隙を、その間隙部
で対向する動翼エレメントの棚部の対峙部分に形成した
軸方向に沿う溝に接続片を打込むことにより閉塞したも
のである。Means for Solving the Problems In order to achieve the above-mentioned object, the present invention provides a groove along the circumferential direction on the outer peripheral portion of a turbine rotor disk, and fits each blade root portion of a plurality of blade elements into this groove. In the turbine rotor blade structure, which is arranged in the circumferential direction in a state of being joined to each other and finally obtains a blade stopping force by inserting a key between the blade roots, by inserting the key, a shelf on the outer peripheral portion of the blade element is provided. A gap formed along the circumferential direction between the portions is closed by driving a connecting piece into a groove along the axial direction formed in the facing portion of the shelf of the blade element that opposes the gap portion.
作用 このような手段によれば、キーの挿入によって動翼エレ
メント外周部の棚部間に発生する周方向に沿う間隙を、
その間隙部で対向する動翼エレメントの棚部の対峙部分
に形成した軸方向に沿う溝に接続片を打込むことにより
閉塞するようにしたので、従来行なわれていた接続片の
溶接が省略でき、組立て作業および事後処理等の簡便化
が図れるとともに、使用材料の選択幅が拡大でき、かつ
応力腐蝕割れの原因も除去される。By such means, by inserting the key, a gap along the circumferential direction generated between the shelves of the outer peripheral portion of the blade element,
Since the connecting piece is closed by driving it into the groove along the axial direction formed in the facing portion of the shelf portion of the moving blade element facing in the gap portion, the welding of the connecting piece which has been conventionally performed can be omitted. In addition, the assembling work and the post-treatment can be simplified, the selection range of materials to be used can be expanded, and the cause of stress corrosion cracking can be eliminated.
実施例 以下、本考案に係るタービン動翼構造の実施例について
図面を参照して説明する。Embodiments Embodiments of a turbine blade structure according to the present invention will be described below with reference to the drawings.
第1図〜第3図に本考案の一実施例を示している。1 to 3 show an embodiment of the present invention.
これらの図において、タービンロータディスク11の外周
部に、周方向に沿って蟻溝状の動翼取付け用の溝12が設
けられている。動翼は複数の動翼エレメントの集合によ
って構成され、その動翼エレメントは、大部分を占める
同一形状の普通翼エレメント13と、少数の特種翼エレメ
ント14,15とからなっている。各動翼エレメント13,14,1
5は、それぞれタービンロータディスク11の溝12に嵌合
される翼根部13a,14a,15aと、この各翼根部13a,14a,15a
から立上がる翼本体部13b,14b,15bと、更にこの各翼本
体部13b,14b,15bの先端に一体的に設けられ最終的にリ
ング状に組合わせられる棚部13c,14c,15cとからなって
いる。In these figures, a dovetail-shaped groove 12 for attaching a moving blade is provided along the circumferential direction on the outer peripheral portion of a turbine rotor disk 11. The rotor blade is composed of a set of a plurality of rotor blade elements, and the rotor blade element is composed of a common blade element 13 having the same shape which occupies the majority, and a small number of special blade elements 14 and 15. Each blade element 13,14,1
5 are blade roots 13a, 14a, 15a fitted into the grooves 12 of the turbine rotor disk 11, and the blade roots 13a, 14a, 15a.
From the blade main body 13b, 14b, 15b rising from the, and further the shelf 13c, 14c, 15c integrally provided at the tip of each blade main body 13b, 14b, 15b and finally combined in a ring shape Has become.
普通エレメント13の棚部13cの周方向両端部は平坦に形
成されているが、特種翼エレメント14,15の棚部14c,15c
の互いに対峙する端面部には軸方向に沿う溝16,17が形
成されている。Although the circumferential ends of the shelf 13c of the ordinary element 13 are formed flat, the shelves 14c and 15c of the special blade elements 14 and 15 are formed.
Grooves 16 and 17 extending along the axial direction are formed in the end face portions of each other facing each other.
また、翼根部類似形状のキー18が備えられるとともに、
特種翼エレメント14,15の棚部14c,15cの溝16,17に嵌合
し得る突条19aを両側縁中央部に形成した略直方体状の
接続片19が備えられている。この接続片19の厚さは棚部
14c,15cの厚さと一致している。Also, with the key 18 having a shape similar to the blade root,
There is provided a substantially rectangular parallelepiped-shaped connecting piece 19 in which ridges 19a which can be fitted into the grooves 16 and 17 of the shelves 14c and 15c of the special blade elements 14 and 15 are formed in the central portions on both side edges. The thickness of this connecting piece 19 is the shelf
It matches the thickness of 14c and 15c.
しかして、組立時においては、まず多数の普通翼エレメ
ント13の翼根部13aをタービンロータディスク11の溝12
に周方向に沿って挿入しながら順送りして植込み、最終
的に特種翼エレメント14,15の翼根部14a,15aを植込む。
この後、タービンロータディスク11の外周部に設けた開
口部11aを介して、キー18を、特種翼エレメント14,15の
翼根部14a,15a間に打込み、これにより各動翼エレメン
ト13,14,15を周方向に圧接させて翼止構造を得る。Then, at the time of assembly, first, the blade roots 13a of a large number of ordinary blade elements 13 are connected to the grooves 12 of the turbine rotor disk 11.
While being inserted along the circumferential direction, the blades are sequentially fed and implanted, and finally the blade root portions 14a and 15a of the special blade elements 14 and 15 are implanted.
After that, the key 18 is driven between the blade roots 14a, 15a of the special blade elements 14, 15 through the opening 11a provided in the outer peripheral portion of the turbine rotor disk 11, whereby each blade element 13, 14, 15 is pressed in the circumferential direction to obtain a wing stop structure.
この場合、キー18の打込みによって、特種翼エレメント
14,15の棚部14c,14c間に間隙20が生じる。そこで、この
間隙20に接続片19を軸方向に沿って挿入し、この接続片
19の両側縁に形成した突条19aを特種翼エレメント14,15
の棚部14c,15cの溝16,17に嵌合させる。これにより、特
種翼エレメント14,15の棚部14c,15c間の間隙20を閉塞
し、蒸気等のタービン駆動流体の半径方向の漏洩防止を
図る。そして最終的に、接続片19と面接触してこの接続
片を安定して挾む棚部14c,15cの軸方向両側縁部を、そ
の接続片19の両端部に対して簡単にかしめることにより
係止部21とし、これにより接続片19を固定する。In this case, by pressing the key 18, the special wing element
A gap 20 is formed between the shelves 14c of 14 and 15. Therefore, the connection piece 19 is inserted into the gap 20 along the axial direction, and the connection piece 19 is inserted.
The ridges 19a formed on both side edges of the 19 are special wing elements 14, 15
It is fitted into the grooves 16 and 17 of the shelves 14c and 15c. This closes the gap 20 between the shelves 14c, 15c of the special blade elements 14, 15 to prevent radial leakage of turbine driving fluid such as steam in the radial direction. And finally, it is possible to easily caulk the both axial ends of the shelf portions 14c, 15c, which are in surface contact with the connection piece 19 and stably sandwich the connection piece 19, with respect to both ends of the connection piece 19. As a result, the locking portion 21 is formed, and thus the connection piece 19 is fixed.
このような実施例の構成によると、棚部の間隙閉塞手段
として溶接を必要としないので、組立て作業および事後
処理等の簡便化が図れるとともに、使用材料の選択幅が
拡大でき、かつ応力腐蝕割れの原因も除去できる。しか
も、接続片19を確実に棚部14c,15cに固定でき、充分な
振動強度が得られるとともに、ダンパー効果が得られる
ようになる。よって、構成の簡略化およびタービン運転
性能の向上等に大きく寄与できる。According to the configuration of such an embodiment, since welding is not required as the gap closing means of the shelf portion, the assembling work and the post-treatment can be simplified, and the selection range of the used material can be expanded, and the stress corrosion cracking can be performed. The cause of can be removed. In addition, the connection piece 19 can be reliably fixed to the shelves 14c, 15c, sufficient vibration strength can be obtained, and the damper effect can be obtained. Therefore, it is possible to greatly contribute to simplification of the configuration and improvement of turbine operating performance.
なお、前記実施例では、接続片19を、棚部14c,15cの厚
さと一致する略直方体状で両側縁中央部に突条19aを有
するものとしたが、本考案はこのようなものに限られな
い。In the above embodiment, the connection piece 19 has a substantially rectangular parallelepiped shape that matches the thickness of the shelves 14c, 15c and has the protrusions 19a at the central portions of both side edges, but the present invention is not limited to this. I can't.
例えば、第4図および第5図に示すように、接続片19
を、棚部14c,15cよりも厚さの小さい直方体状のものと
してもよい。このような構成によると、重量軽減により
接続片19に作用する遠心力を減少することができる。For example, as shown in FIG. 4 and FIG.
May have a rectangular parallelepiped shape having a smaller thickness than the shelves 14c, 15c. According to such a configuration, the centrifugal force acting on the connection piece 19 can be reduced by reducing the weight.
また、第6図および第7図に示すように、棚部14c,15c
の対峙する面を径方向に傾斜させて間隙20を軸方向外側
が小径となるテーパ状とし、この間隙20のテーパと一致
するテーパ付の接続片19を用いるようにしてもよい。こ
のような構成によると、遠心力によるダンパー効果が一
層向上できる。Also, as shown in FIGS. 6 and 7, the shelves 14c, 15c
The surfaces facing each other may be inclined in the radial direction so that the gap 20 has a taper shape having a small diameter on the outside in the axial direction, and a tapered connecting piece 19 that matches the taper of the gap 20 may be used. With such a configuration, the damper effect due to the centrifugal force can be further improved.
さらに、第8図に示すように、接続片19を棚部14c,15c
よりも厚さが小さく、かつテーパ付とすれば、遠心力の
減少とダンパー効果の向上とが図れる。Further, as shown in FIG. 8, the connecting piece 19 is attached to the shelves 14c and 15c.
If the thickness is smaller than that and the taper is used, the centrifugal force can be reduced and the damper effect can be improved.
考案の効果 以上述べたように、本考案によれば、タービン動翼に係
る組立て作業および事後処理等の簡便化が図れるととも
に、使用材料の選択幅が拡大でき、かつ応力腐蝕割れの
原因も除去でき、構成の簡略化およびタービン運転性能
の向上等に大きく寄与できる等の効果が奏される。Effects of the Invention As described above, according to the present invention, the assembling work and post-treatment of the turbine rotor blade can be simplified, the selection range of materials used can be expanded, and the cause of stress corrosion cracking can be eliminated. Therefore, it is possible to make an effect such that the structure is simplified and the turbine operating performance is improved.
第1図は本考案に係るタービン動翼構造の一実施例を示
す斜視図、第2図は径方向側面図、第3図は軸方向側面
図、第4図は本考案の他の実施例を示す翼端部の軸方向
側面図、第5図は第4図に使用する接続片の斜視図、第
6図は本考案のさらに他の実施例を示す翼端部の軸方向
側面図、第7図は第6図に使用する接続片の斜視図、第
8図は本考案のさらに異なる実施例を示す翼端部の軸方
向側面図、第9図は従来例を示す斜視図、第10図は第9
図に示す動翼エレメントを示す分解斜視図、第11図は組
立て途中状態を示す軸方向側面図、第12図は組立て後の
状態を示す軸方向側面図である。 11……タービンロータディスク、12……溝、13,14,15…
…動翼エレメント、13a,14a,15a……翼根部、13b,14b,1
5b……翼本体部、13c,14c,15c……棚部、16,17……棚部
の溝、18……キー、19……接続片。FIG. 1 is a perspective view showing one embodiment of a turbine blade structure according to the present invention, FIG. 2 is a radial side view, FIG. 3 is an axial side view, and FIG. 4 is another embodiment of the present invention. Fig. 5 is a side view in the axial direction of the blade tip, Fig. 5 is a perspective view of the connecting piece used in Fig. 4, and Fig. 6 is a side view in the axial direction of the blade tip showing still another embodiment of the present invention. FIG. 7 is a perspective view of a connecting piece used in FIG. 6, FIG. 8 is an axial side view of a blade tip showing a further different embodiment of the present invention, and FIG. 9 is a perspective view showing a conventional example. 10 is the ninth
FIG. 11 is an exploded perspective view showing the rotor blade element shown in the figure, FIG. 11 is an axial side view showing an intermediate state of assembly, and FIG. 12 is an axial side view showing the state after assembly. 11 …… Turbine rotor disk, 12 …… Groove, 13,14,15…
… Blade element, 13a, 14a, 15a …… Blade root, 13b, 14b, 1
5b …… Wing body, 13c, 14c, 15c …… Shelf, 16,17 …… Slot groove, 18 …… Key, 19 …… Connecting piece.
Claims (1)
に沿う溝を設け、この溝に複数の動翼エレメントの各翼
根部を嵌合させるとともに相互に接合状態で周方向に配
列し、かつ最終的に翼根部間にキーを挿入して翼止力を
得るタービン動翼構造において、前記キーの挿入によっ
て前記動翼エレメント外周部の棚部間に発生する周方向
に沿う間隙を、その間隙部で対向する動翼エレメントの
棚部の対峙部分に形成した軸方向に沿う溝に接続片を打
込むことにより閉塞してなることを特徴とするタービン
動翼構造。1. A turbine rotor disk is provided with a groove along the circumferential direction on an outer peripheral portion thereof. The blade roots of a plurality of moving blade elements are fitted into the groove and are arranged in the circumferential direction in a mutually joined state, and finally. In a turbine moving blade structure in which a key is inserted between blade roots to obtain blade stopping force, a gap along the circumferential direction generated between the ledges of the outer peripheral portion of the moving blade element due to the insertion of the key is defined by the gap portion. The turbine blade structure is characterized in that the blade is closed by driving a connecting piece into a groove along the axial direction that is formed in the facing portion of the shelf portion of the blade element facing each other.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP11976589U JPH0724563Y2 (en) | 1989-10-16 | 1989-10-16 | Turbine blade structure |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP11976589U JPH0724563Y2 (en) | 1989-10-16 | 1989-10-16 | Turbine blade structure |
Publications (2)
Publication Number | Publication Date |
---|---|
JPH0359401U JPH0359401U (en) | 1991-06-12 |
JPH0724563Y2 true JPH0724563Y2 (en) | 1995-06-05 |
Family
ID=31667868
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP11976589U Expired - Lifetime JPH0724563Y2 (en) | 1989-10-16 | 1989-10-16 | Turbine blade structure |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPH0724563Y2 (en) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2003014529A1 (en) * | 2001-08-03 | 2003-02-20 | Hitachi, Ltd. | Turbine moving vane |
DE102009052883A1 (en) * | 2009-11-13 | 2011-05-19 | Mtu Aero Engines Gmbh | Coupling element for mechanical coupling of blades and rotor |
-
1989
- 1989-10-16 JP JP11976589U patent/JPH0724563Y2/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
JPH0359401U (en) | 1991-06-12 |
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