JPH11336501A - Turbine rotor blade - Google Patents
Turbine rotor bladeInfo
- Publication number
- JPH11336501A JPH11336501A JP14350698A JP14350698A JPH11336501A JP H11336501 A JPH11336501 A JP H11336501A JP 14350698 A JP14350698 A JP 14350698A JP 14350698 A JP14350698 A JP 14350698A JP H11336501 A JPH11336501 A JP H11336501A
- Authority
- JP
- Japan
- Prior art keywords
- snubber cover
- blade
- trailing edge
- cover
- leading edge
- 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
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、タービン動翼に係
り、特に制振力を向上させたタービン動翼に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a turbine rotor blade, and more particularly to a turbine rotor blade having improved damping force.
【０００２】[0002]
【従来の技術】最近の蒸気タービンでは、高出力化を求
めてその作動流体としての蒸気を超高圧、超高温化する
研究開発が進められており、これに伴ってタービン最終
段落に植設するタービン動翼を長翼化させる研究開発も
同時に行われている。2. Description of the Related Art In recent steam turbines, research and development for increasing the output of steam as an ultra-high pressure and ultra-high temperature in pursuit of high output have been promoted. Research and development to increase the length of the turbine blades are also being conducted.
【０００３】タービン動翼を長翼化させる場合、蒸気に
実質的な仕事をさせる翼有効部は、１ｍを超える翼高に
なり、これに伴ってルート部（翼根元部）からチップ部
（翼先端部）にかけて蒸気の流線に対応させて翼断面を
変化させていた翼捩りも大きくなる。この翼捩りは、タ
ービン動翼の運転中に発生する遠心力により捩り戻りが
ある。この捩り戻りを巧みに利用してタービン動翼の運
転中に発生する振動を抑制する制振構造形のタービン動
翼が数多く提案されており、そのうち代表的なものとし
て図１０に示すものがある。[0003] When a turbine blade is made longer, a blade effective portion for causing steam to substantially perform work has a blade height exceeding 1 m, and accordingly, a root portion (blade root portion) to a tip portion (blade). The blade torsion, which changes the blade cross section corresponding to the streamline of steam toward the tip portion, also increases. This blade torsion may return due to centrifugal force generated during operation of the turbine blade. A number of turbine blades having a damping structure have been proposed which skillfully utilize this torsional return to suppress vibrations generated during the operation of the turbine blades, of which a typical one is shown in FIG. .
【０００４】タービン動翼は、タービン軸１の周方向に
沿って植設された翼植込み部２と、蒸気に実質的な仕事
をさせる翼有効部３と、翼有効部３の先端部４から一体
に削り出されたスナッバカバー５を備えた構成になって
いる。[0004] The turbine rotor blade includes a blade implant portion 2 installed along the circumferential direction of the turbine shaft 1, a blade effective portion 3 that causes steam to perform substantial work, and a tip portion 4 of the blade effective portion 3. The snubber cover 5 is integrally cut out.
【０００５】また、タービン動翼は、翼植込み部２ａ，
２ｂをタービン軸１の周方向に沿って列状に植設し、翼
有効部３ａ，３ｂを、そのルート部からチップ部にかけ
て蒸気の流線に対応させて翼断面を変化させる翼捩りを
加えるとともに、一方の先端部４ａのスナッバカバー５
ａと隣の先端部４ｂのスナッバカバー５ｂとを遊嵌配置
させている。[0005] Further, the turbine blade has a blade implant 2a,
2b are arranged in rows along the circumferential direction of the turbine shaft 1, and the blade effective portions 3a and 3b are subjected to blade torsion that changes the blade cross section from the root portion to the tip portion so as to correspond to the steam flow line. At the same time, the snubber cover 5 of the one end 4a
a and the snubber cover 5b of the adjacent tip 4b are loosely fitted.
【０００６】このような構成を備えたタービン動翼は、
組立て当初、図１１に示すように、一方の先端部４ａの
前縁６ａから外側に向って突き出した前縁スナッバカバ
ー５ａ1 と、その後縁７ａから前縁スナッバカバー５ａ
1 と反対の外側に向って突き出た後縁スナッバカバー５
ａ2 と、隣の先端部４ｂの前縁６ｂから外側に向って突
き出た前縁スナッバカバー５ｂ1 と、その後縁７ｂから
前縁スナッバカバー５ｂ1 の反対の外側に向って突き出
た後縁スナッバカバー５ｂ2 とのうち、一方の前縁スナ
ッバカバー５ａ1 の端面８ａと隣の後縁スナッバカバー
５ｂ2 の端面８ｂとの間に隙間Ｄを形成しておき、運転
中、遠心力により翼有効部３ａ，３ｂに捩り戻り（以下
アンツイストと記す）が発生すると、図１２に示すよう
に、一方の前縁スナッバカバー５ａ1 の端面８ａと隣の
後縁スナッバカバー５ｂ2 の端面８ｂとを互いに面接触
させている。A turbine blade having such a configuration is
Initially, as shown in FIG. 11, a leading edge snubber cover 5a1 protruding outward from a leading edge 6a of one tip 4a, and a leading edge snubber cover 5a extending from a trailing edge 7a.
Trailing edge snubber cover 5 protruding toward the outside opposite to 1
a2, a leading edge snubber cover 5b1 projecting outward from the leading edge 6b of the adjacent tip 4b, and a trailing edge snubber cover 5b2 projecting outward from the trailing edge 7b opposite to the leading edge snubber cover 5b1. Of these, a gap D is formed between the end face 8a of one leading edge snubber cover 5a1 and the end face 8b of the adjacent trailing edge snubber cover 5b2, and the centrifugal force causes the effective blade portions 3a, 3b to twist during operation. When the return (hereinafter referred to as "untwist") occurs, as shown in FIG. 12, the end face 8a of the one front edge snubber cover 5a1 and the end face 8b of the adjacent rear edge snubber cover 5b2 are brought into surface contact with each other.
【０００７】このように、従来のタービン動翼では、一
方の前縁スナッバカバー５ａ1 の端面８ａと隣の後縁ス
ナッバカバー５ｂ2 の端面８ｂとを互いに面接触させ、
この面接触に基づく摩擦力を巧みに利用して振動を効果
的に抑制していた。As described above, in the conventional turbine blade, the end face 8a of one leading edge snubber cover 5a1 and the end face 8b of the adjacent trailing edge snubber cover 5b2 are brought into surface contact with each other,
Vibration was effectively suppressed by skillfully utilizing the frictional force based on this surface contact.
【０００８】[0008]
【発明が解決しようとする課題】従来、一方の前縁スナ
ッバカバー５ａ1 の端面８ａと隣の後縁スナッバカバー
５ｂ2 の端面８ｂとの組立て当初の隙間Ｄは、大き過ぎ
るとアンツイストに基づく面接触をさせることができ
ず、逆に小さ過ぎると面接触に基づく拘束力が強過ぎて
翼有効部３とスナッバカバー５との結合部分に過度な応
力を発生させるので経験上から割り出してその数値を設
定していた。Conventionally, when the gap D between the end face 8a of one leading edge snubber cover 5a1 and the end face 8b of the adjacent trailing edge snubber cover 5b2 is too large, the surface contact based on untwist is too large. On the contrary, if it is too small, the binding force based on the surface contact is too strong and excessive stress is generated at the joint between the effective wing portion 3 and the snubber cover 5, so that it is empirically determined and the numerical value is calculated. Was set.
【０００９】しかし、蒸気タービンの超高圧化、超高温
化に伴ってタービン動翼が従来に較べてより一層長翼化
すると、一方の前縁スナッバカバー５ａ1 の端面８ａと
隣の後縁スナッバカバー５ｂ2 の端面８ｂとの隙間Ｄ
は、従来の寸法を、長翼化の寸法に単に対応させてスケ
ールアップさせただけでは設計値通りの制振効果を発揮
させることができない問題点があった。[0009] However, if the turbine blade becomes longer than before in accordance with the ultra-high pressure and ultra-high temperature of the steam turbine, the end face 8a of one leading edge snubber cover 5a1 and the trailing edge snubber cover next to it will be used. Gap D between 5b2 and end face 8b
However, there is a problem that the vibration suppression effect as designed cannot be exerted simply by scaling up the conventional dimensions to the dimensions of the longer blades.
【００１０】他方、タービン動翼は、長翼化と並行して
翼性能の向上が求められているが、この翼性能の向上の
点からスナッバカバー５を考察してみると、スナッバカ
バー５に幾つかの問題点がある。On the other hand, turbine blades are required to have improved blade performance in parallel with longer blade length. Considering the improvement in blade performance, the snubber cover 5 is considered. There are several problems.
【００１１】まず、第１に、翼有効部３とスナッバカバ
ー５との結合部分に応力の増加がある。First, there is an increase in stress at the joint between the wing effective portion 3 and the snubber cover 5.
【００１２】タービン動翼の長翼化に伴ってスナッバカ
バー５の結合部に働く遠心力がより一層増加するととも
に、運転中に発生するアンツイストが加わり、その結合
部分に過度な応力が発生する。このため、タービン動翼
は、図１３に示すように、翼有効部３（３ａ，３ｂ）と
後縁スナッバカバー５ａ2 （５ｂ2 ）との結合部分ＪＰ
に遠心力Ｆ1 とアンツイストの力Ｆ2 が加わって、後縁
スナッバカバー５ａ2（５ｂ2 ）が図示の実線の位置か
ら図示の破線の位置に変位するとともに、パネル振動モ
ードの節ＶＭも図示の一点鎖線のように変化し、高応力
場になり、強度維持と、制振効果とが従来に較べて低く
なる問題点がある。As the length of the turbine blade increases, the centrifugal force acting on the joint of the snubber cover 5 further increases, and an untwist generated during operation is applied, so that excessive stress is generated at the joint. . For this reason, as shown in FIG. 13, the turbine rotor blade has a connecting portion JP between the blade effective portion 3 (3a, 3b) and the trailing edge snubber cover 5a2 (5b2).
A centrifugal force F1 and an untwisting force F2 are applied to the rear end, so that the trailing edge snubber cover 5a2 (5b2) is displaced from the position indicated by the solid line in FIG. And a high stress field occurs, and there is a problem that the strength maintenance and the vibration damping effect are lower than before.
【００１３】第２に、前縁スナッバカバー５ａ1 の端面
８ａと隣の後縁スナッバカバー５ｂ2 の端面８ｂとの組
立て当初の隙間Ｄの設定が難しい。Second, it is difficult to set the clearance D at the time of assembling the end face 8a of the leading edge snubber cover 5a1 and the end face 8b of the adjacent trailing edge snubber cover 5b2.
【００１４】タービン動翼の長翼化によりアンツイスト
変形が大きくなるだけでなく、遠心力による翼有効部３
の倒れが従来に較べて大きくなる。すなわち、運転時、
翼有効部３は、タービン軸１の中心を通る半径方向の重
心位置関係、剛性分布、蒸気力等の影響を受けて、例え
ば、図１４に示すように、腹側９から背側１０の回転Ｒ
Ｖに沿う方向（タービン軸１の周方向）、つまり実線で
示す位置から破線で示す位置に変位し、同時に、前縁ス
ナッバカバー５ａ1 （５ｂ1 ）および後縁スナッバカバ
ー５ａ2 （５ｂ2 ）も実線で示す位置から破線で示す位
置に変位する。このとき、前縁スナッバカバー５ａ1
（５ｂ1 ）および後縁スナッバカバー５ａ2 （５ｂ2 ）
のケーシング１１に対する隙間Ｄ1 ，Ｄ2 は、図１５に
示すように、前縁スナッバカバー５ａ1 （５ｂ1 ）の隙
間Ｄ1 の方が後縁スナッバカバー５ａ2 （５ｂ2 ）の隙
間Ｄ2 に較べて相対的に大きくなる。Not only does the untwist deformation increase due to the long blades of the turbine blade, but also the effective blade portion 3 due to centrifugal force.
Of the vehicle becomes larger than before. That is, when driving,
The blade effective portion 3 is affected by the positional relationship of the center of gravity in the radial direction passing through the center of the turbine shaft 1, the rigidity distribution, the steam force, and the like, and, for example, as shown in FIG. R
In the direction along V (the circumferential direction of the turbine shaft 1), that is, from the position shown by the solid line to the position shown by the broken line, the leading edge snubber cover 5a1 (5b1) and the trailing edge snubber cover 5a2 (5b2) are also shown by the solid line. Displaced from the position to the position indicated by the broken line. At this time, the leading edge snubber cover 5a1
(5b1) and trailing edge snubber cover 5a2 (5b2)
As shown in FIG. 15, the gaps D1 and D2 of the front edge snubber cover 5a1 (5b1) are relatively larger than the gap D2 of the rear edge snubber cover 5a2 (5b2). .
【００１５】一般に、回転部と静止部との隙間は、起動
運転中の過度現象を考慮し、変形の一番大きい部分、具
体的には後縁スナッバカバー５ａ2 （５ｂ2 ）を基準に
し、その後縁スナッバカバー５ａ2 （５ｂ2 ）のケーシ
ング１１に対する隙間が最小となるように設定してい
る。このため、タービン動翼が長翼化すると、ケーシン
グ１１に対する前縁スナッバカバー５ａ1 （５ｂ1 ）の
隙間Ｄ1 が大きくなり、蒸気漏れが増加し、翼性能を低
下させる要因になる。In general, the gap between the rotating portion and the stationary portion is determined based on the portion having the largest deformation, specifically, the trailing edge snubber cover 5a2 (5b2) in consideration of the transient phenomenon during the starting operation. The snubber cover 5a2 (5b2) is set so that the gap with respect to the casing 11 is minimized. For this reason, when the turbine blade becomes longer, the clearance D1 between the leading edge snubber cover 5a1 (5b1) and the casing 11 becomes larger, which increases steam leakage and lowers blade performance.
【００１６】また、タービン動翼は、図１４に示すよう
に、一方の前縁スナッバカバー５ａ1 （５ｂ1 ）および
後縁スナッバカバー５ａ2 （５ｂ2 ）が実線の位置から
破線の位置に変化すると、隣の後縁スナッバカバー５ｂ
2 との間に段差ができて風損としての損失になり、翼性
能の低下になる。Further, as shown in FIG. 14, when one leading edge snubber cover 5a1 (5b1) and trailing edge snubber cover 5a2 (5b2) change from a solid line position to a broken line position, as shown in FIG. Trailing edge snubber cover 5b
2 and a step is created, resulting in a loss as windage loss, and impaired wing performance.
【００１７】第３に、蒸気中に含まれる水滴のスナッバ
カバー５に対する侵食現象、すなわちエロージョンがあ
る。このエロージョンは、タービン動翼をスナッバカバ
ー構造にした場合、従来の翼カバーと異なって水滴との
衝突面積が増加するので特有の問題点になる。Third, there is an erosion phenomenon, ie, erosion, of the water droplets contained in the steam on the snubber cover 5. This erosion is a particular problem when the turbine blade has a snubber cover structure because the collision area with water droplets increases unlike the conventional blade cover.
【００１８】タービン動翼が長翼化すると、その周速は
大きくなり、蒸気に含まれる水滴のスナッバカバー５へ
の衝突速度も高くなる。また、タービン動翼は、運転
中、図１６に示すように、回転ＲＶの方向に対し、隣の
後縁スナッバカバー５ｂ2 の端面８ｂが一方の前縁スナ
ッバカバー５ａ1 の端面８ａよりも外側に向って変位
し、段差部分１２ができる。一方、蒸気ＳＴは、軸方向
に沿って流れる際、タービン動翼の遠心力の影響を受け
て軌跡線ＴＲに沿って流れる。このため、段差部分１２
には、より多くの水滴が衝突する。As the length of the turbine blade increases, the peripheral speed increases, and the speed of collision of water droplets contained in the steam with the snubber cover 5 also increases. Also, during operation, as shown in FIG. 16, during operation, the end face 8b of the adjacent trailing edge snubber cover 5b2 faces more outward than the end face 8a of one leading edge snubber cover 5a1 in the direction of rotation RV. Displaced to form a stepped portion 12. On the other hand, when the steam ST flows along the axial direction, it flows along the trajectory line TR under the influence of the centrifugal force of the turbine blade. For this reason, the step 12
More water drops collide.
【００１９】段差部分１２により多くの水滴が衝突する
と、前縁スナッバカバー５ａ1 は、フレッティング現象
が生じ易くなる。このフレッティング現象は、前縁スナ
ッバカバー５ａ1 を摩耗させ、摩擦力を減退させて制振
能力を低下させる一方、クラックの発生を誘発する要因
になる。When many water droplets collide with the step portion 12, the front edge snubber cover 5a1 is liable to cause the fretting phenomenon. The fretting phenomenon causes the leading edge snubber cover 5a1 to be worn and the frictional force to be reduced to reduce the vibration damping ability, while causing a crack to be generated.
【００２０】そして、第４に、タービン動翼の長翼化に
伴って遠心力を低く抑えるために、翼断面、特に先端部
の翼断面の厚みを薄く設計する場合、パネル振動が発生
する。このパネル振動は、既に図１３でも説明したよう
に、翼断面の薄い部分、特に後縁部分の翼有効部３と後
縁スナッバカバー５ａ2 との結合部分ＪＰまで延びるパ
ネル振動モードの節ＶＭを基準に振動が発生する。この
ため、翼有効部３と後縁スナッバカバー５ａ2 との結合
部分ＪＰは、高応力場になり、クラックを発生させ易い
環境下になっている。Fourth, panel vibration occurs when the blade section, especially the tip section is designed to be thin in order to keep the centrifugal force low as the length of the turbine blade increases. As described above with reference to FIG. 13, this panel vibration is based on the node VM of the panel vibration mode extending to the thin portion of the blade section, particularly the connecting portion JP between the trailing edge portion 3 and the trailing edge snubber cover 5a2. Vibration occurs. For this reason, the joint portion JP between the effective blade portion 3 and the trailing edge snubber cover 5a2 has a high stress field and is in an environment where cracks are easily generated.
【００２１】このように、タービン動翼を長翼化する場
合、スナッバカバー５には、幾つかの問題点があり、何
らかの改善策が必要とされていた。As described above, when the length of the turbine blade is increased, the snubber cover 5 has several problems, and some improvement is required.
【００２２】本発明は、このような考察結果に基づいて
なされたもので、翼の強度を高い状態に維持させること
と相俟って、振動の抑制および翼性能の向上を図ったタ
ービン動翼を提供することを目的とする。The present invention has been made on the basis of such considerations, and, in combination with maintaining the strength of the blade at a high level, has been designed to suppress vibration and improve blade performance. The purpose is to provide.
【００２３】[0023]
【課題を解決するための手段】本発明に係るタービン動
翼は、上記目的を達成するために、請求項１に記載した
ように、タービン軸の周方向に沿って列状に配置した翼
有効部の先端部の前縁に前縁スナッバカバーを、その後
縁に後縁スナッバカバーを備えたタービン動翼におい
て、一方の前縁スナッバカバーを、隣の後縁スナッバカ
バーよりも、上記タービン軸の中心を通る半径方向の外
側に向って高く設定したものである。According to the present invention, there is provided a turbine rotor blade according to the present invention, wherein the blade effective blades are arranged in a row along a circumferential direction of a turbine shaft. In a turbine rotor blade provided with a leading edge snubber cover at the leading edge of the leading end of the portion and a trailing edge snubber cover at the trailing edge, one leading edge snubber cover is attached to the turbine shaft more than the neighboring trailing edge snubber cover. It is set high toward the outside in the radial direction passing through the center.
【００２４】また、本発明に係るタービン動翼は、上記
目的を達成するために、請求項２に記載したように、タ
ービン軸の周方向に沿って列状に配置した翼有効部の先
端部の前縁に前縁スナッバカバーを、その後縁に後縁ス
ナッバカバーを備えたタービン動翼において、一方の前
縁スナッバカバーを、隣の後縁スナッバカバーよりも、
上記タービン軸の中心を通る半径方向の内側に向って延
びるように設定したものである。According to a second aspect of the present invention, there is provided a turbine rotor blade according to the present invention, wherein a tip portion of an effective blade portion is arranged in a row along a circumferential direction of a turbine shaft. In the turbine rotor blade having a leading edge snubber cover at the leading edge and a trailing edge snubber cover at the trailing edge, one leading edge snubber cover is more than the neighboring trailing edge snubber cover.
It is set so as to extend inward in the radial direction passing through the center of the turbine shaft.
【００２５】また、本発明に係るタービン動翼は、上記
目的を達成するために、請求項３に記載したように、タ
ービン軸の周方向に沿って列状に配置した翼有効部の先
端部の前縁に前縁スナッバカバーを、その後縁に後縁ス
ナッバカバーを備えたタービン動翼において、隣の後縁
スナッバカバーの厚みを、一方の前縁スナッバカバーの
厚みよりも厚く設定したものである。According to a third aspect of the present invention, there is provided a turbine rotor blade according to the present invention, wherein a tip portion of an effective blade portion is arranged in a row along a circumferential direction of a turbine shaft. In a turbine rotor blade having a leading edge snubber cover at the leading edge and a trailing edge snubber cover at the trailing edge, the thickness of the adjacent trailing edge snubber cover is set to be greater than the thickness of one leading edge snubber cover. is there.
【００２６】また、本発明に係るタービン動翼は、上記
目的を達成するために、請求項４に記載したように、隣
の後縁スナッバカバーの厚みを、一方の前縁スナッバカ
バーの厚みよりも、タービン軸の中心を通り半径方向の
内側に向って厚く形成したものである。In order to achieve the above object, in the turbine bucket according to the present invention, the thickness of the adjacent trailing edge snubber cover is made larger than the thickness of one of the leading edge snubber covers. Are formed thicker inward in the radial direction through the center of the turbine shaft.
【００２７】また、本発明に係るタービン動翼は、上記
目的を達成するために、請求項５に記載したように、タ
ービン軸の周方向に沿って列状に配置した翼有効部の先
端部の前縁に前縁スナッバカバーを、その後縁に後縁ス
ナッバカバーを備えたタービン動翼において、隣の後縁
スナッバカバーの端面の厚みと一方の前縁スナッバカバ
ーの端面の厚みを同一にするとともに、上記後縁スナッ
バカバーおよび上記前縁スナッバカバーのそれぞれの中
間部分に切欠溝部を形成したものである。According to a fifth aspect of the present invention, there is provided a turbine rotor blade according to the present invention, wherein the tip portions of the blade effective portions are arranged in a row along the circumferential direction of the turbine shaft. In a turbine rotor blade having a leading edge snubber cover at the leading edge and a trailing edge snubber cover at the trailing edge, the thickness of the end face of the adjacent trailing edge snubber cover is made equal to the thickness of the end face of one leading edge snubber cover. In addition, a cutout groove is formed in each of the intermediate portions of the trailing edge snubber cover and the leading edge snubber cover.
【００２８】また、本発明に係るタービン動翼は、上記
目的を達成するために、請求項６に記載したように、後
縁スナッバカバーおよび前縁スナッバカバーのそれぞれ
の中間部分に形成した切欠溝部を、タービン軸の中心を
通る半径方向の内側に形成したものである。According to a sixth aspect of the present invention, in order to achieve the above object, a notch groove formed in a middle portion between each of a trailing edge snubber cover and a leading edge snubber cover. Is formed radially inward through the center of the turbine shaft.
【００２９】また、本発明に係るタービン動翼は、上記
目的を達成するために、請求項７に記載したように、タ
ービン軸の周方向に沿って列状に配置した翼有効部の先
端部の前縁に前縁スナッバカバーを、その後縁に後縁ス
ナッバカバーを備えたタービン動翼において、上記前縁
スナッバカバーおよび上記後縁スナッバカバーのそれぞ
れの上記翼有効部への結合部の厚みを、上記前縁スナッ
バカバーおよび上記後縁スナッバカバーのそれぞれの端
面の厚みよりも厚く形成したものである。According to a seventh aspect of the present invention, there is provided a turbine rotor blade according to the present invention, wherein a tip portion of an effective blade portion is arranged in a row along a circumferential direction of a turbine shaft. In a turbine rotor blade having a leading edge snubber cover at the leading edge thereof and a trailing edge snubber cover at the trailing edge, the thickness of the connecting portion of the leading edge snubber cover and the trailing edge snubber cover to the respective blade effective portions is reduced. , The leading edge snubber cover and the trailing edge snubber cover are formed to be thicker than the respective end faces.
【００３０】また、本発明に係るタービン動翼は、上記
目的を達成するために、請求項８に記載したように、タ
ービン軸の周方向に沿って列状に配置した翼有効部の先
端部に前縁スナッバカバーを、その後縁に後縁スナッバ
カバーを備えたタービン動翼において、上記後縁スナッ
バカバーを、蒸気の下流側に向って上記後縁よりも長く
突き合せて形成したものである。Further, in order to achieve the above object, a turbine rotor blade according to the present invention has a tip end portion of an effective blade portion arranged in a row along a circumferential direction of a turbine shaft. In a turbine rotor blade provided with a leading edge snubber cover and a trailing edge snubber cover at the trailing edge, the trailing edge snubber cover is formed by abutting longer than the trailing edge toward the downstream side of steam. .
【００３１】また、本発明に係るタービン動翼は、上記
目的を達成するために、請求項９に記載したように、翼
有効部を、４０インチ以上の翼高に形成したものであ
る。In order to achieve the above object, the turbine rotor blade according to the present invention is such that the blade effective portion is formed with a blade height of 40 inches or more.
【００３２】[0032]
【発明の実施の形態】以下、本発明に係るタービン動翼
の実施形態を図面および図中に付した符号を引用して説
明する。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of a turbine rotor blade according to the present invention will be described below with reference to the drawings and reference numerals in the drawings.
【００３３】図１は、本発明に係るタービン動翼の第１
実施形態を示す概略斜視図である。FIG. 1 shows a first embodiment of a turbine rotor blade according to the present invention.
It is a schematic perspective view showing an embodiment.
【００３４】本実施形態に係るタービン動翼は、４０イ
ンチ以上の翼高のものに適用するもので、回転ＲＶの方
向に沿って列状に配置した翼有効部１３をタービン軸
（図示せず）に植設する構成になっている。The turbine blade according to the present embodiment is applied to a blade having a blade height of 40 inches or more. The blade effective portions 13 arranged in a row along the direction of rotation RV are provided with a turbine shaft (not shown). ).
【００３５】翼有効部１３のうち、一方の翼有効部１３
ａの先端部１４ａおよび隣の翼有効部１３ｂの先端部１
４ｂのそれぞれには、一体削り出しのスナッバカバー１
５が設けられている。One of the effective wing portions 13 of the effective wing portion 13
a and the tip 1 of the adjacent wing effective portion 13b
4b, a snubber cover 1 which is integrally cut out
5 are provided.
【００３６】また、スナッバカバー１５のうち、一方の
翼有効部１３ａの先端部１４ａにおける前縁１５ａに
は、外側に向って突き出た前縁スナッバカバー１５ａ1
が設けられ、その後縁１６ａにも、前縁スナッバカバー
１５ａ1 と反対の外側に向って突き出た後縁スナッバカ
バー１５ａ2 が設けられている。In the snubber cover 15, the leading edge 15a of the tip portion 14a of the one wing effective portion 13a has a leading edge snubber cover 15a1 protruding outward.
The trailing edge 16a is also provided with a trailing edge snubber cover 15a2 protruding outwardly opposite the leading edge snubber cover 15a1.
【００３７】また、隣の翼有効部１３ｂｂの先端部１４
ｂにおける前縁１５ｂおよび後縁１６ｂのそれぞれにも
前縁スナッバカバー１５ｂ1 および後縁スナッバカバー
１５ｂ2 が設けられている。The tip 14 of the adjacent wing effective portion 13bb
b, a leading edge snubber cover 15b1 and a trailing edge snubber cover 15b2 are provided on each of the leading edge 15b and the trailing edge 16b.
【００３８】また、一方の翼有効部１３ａの先端部１４
ａにおける前縁スナッバカバー１５ａ1 の端面１７ａと
隣の翼有効部１３ｂの先端部１４ｂにおける後縁スナッ
バカバー１５ｂ2 の端面１７ｂとの間には、図２に示す
ように、一方の翼有効部１３ａにおける前縁スナッバカ
バー１５ａ1 の端面１７ａを、隣の翼有効部１３ｂにお
ける後縁スナッバカバー１５ｂ2 に較べてタービン軸
（図示せず）の中心を通る半径方向に向って偏差高δcv
として予め高く設定する、いわゆるオフセットになって
いる。Further, the tip portion 14 of the one wing effective portion 13a
2, between the end face 17a of the leading edge snubber cover 15a1 and the end face 17b of the trailing edge snubber cover 15b2 at the tip 14b of the adjacent wing effective portion 13b, as shown in FIG. The deviation height δcv of the end face 17a of the leading edge snubber cover 15a1 in the radial direction passing through the center of the turbine shaft (not shown) as compared with the trailing edge snubber cover 15b2 of the adjacent blade effective portion 13b.
This is a so-called offset that is set high in advance.
【００３９】このオフセットとしての偏差高δcvは、以
下に述べる理由により設定される。The deviation height δcv as the offset is set for the following reason.
【００４０】翼有効部１３（１３ａ，１３ｂ）、前縁ス
ナッバカバー１５ａ1 （１５ｂ1 ）および後縁スナッバ
カバー１５ａ2 （１５ｂ2 ）は、図３に示すように、組
立て当初、破線の位置に設定していても、運転中になる
と、実線の位置、すなわち腹側１８から背側１９に向っ
て倒れることが経験的に解っており、前縁スナッバカバ
ー１５ａ1 （１５ｂ1 ）の運転中の半径方向への延びを
Ｌｌｅとし、後縁スナッバカバー１５ａ2 （１５ｂ2 ）
の運転中の半径方向への延びＬｔｅとするとき、Ｌｔｅ
＞Ｌｌｅになっている。このため、後縁スナッバカバー
１５ａ2 （１５ｂ2 ）に対する前縁スナッバカバー１５
ａ1 （１５ｂ1 ）のオフセットとしての偏差高δcvは、
運転中、前縁スナッバカバー１５ａ1 （１５ｂ1 ）およ
び後縁スナッバカバー１５ａ2 （１５ｂ2 ）のそれぞれ
の半径方向への延びＬｌｅ，Ｌｔｅを考慮して、As shown in FIG. 3, the wing effective portions 13 (13a, 13b), the leading edge snubber cover 15a1 (15b1) and the trailing edge snubber cover 15a2 (15b2) are initially set at the positions indicated by broken lines. It is also empirically known that, during operation, the vehicle falls down from the position indicated by the solid line, that is, from the ventral side 18 to the back side 19, and the leading edge snubber cover 15a1 (15b1) extends in the radial direction during operation. Lle, trailing edge snubber cover 15a2 (15b2)
Lte in the radial direction during operation of the vehicle, Lte
> Lle. For this reason, the leading edge snubber cover 15a2 (15b2) and the leading edge snubber cover 15
The deviation height δcv as an offset of a1 (15b1) is
During operation, taking into account the respective radial extensions Lle, Lte of the leading edge snubber cover 15a1 (15b1) and the trailing edge snubber cover 15a2 (15b2),
【数１】δcv＝Ｌｔｅ−Ｌｌｅ に設定しておけば、運転中、ケーシング２０に対する前
縁スナッバカバー１５ａ1 （１５ｂ1 ）および後縁スナ
ッバカバー１５ａ2 （１５ｂ2 ）のそれぞれの隙間ＣＬ
ｌ，ＣＬｔが、If δcv = Lte−Lle, the gap CL between the leading edge snubber cover 15a1 (15b1) and the trailing edge snubber cover 15a2 (15b2) with respect to the casing 20 during operation is set.
l, CLt is
【数２】ＣＬｌ＝ＣＬｔ になることに基づくものである。## EQU2 ## This is based on CL1 = CLt.
【００４１】このように、本実施形態では、後縁スナッ
バカバー１５ａ2 （１５ｂ2 ）に対し、前縁スナッバカ
バー１５ａ1 （１５ｂ1 ）を、組立て当初の偏差高δcv
としてタービン軸の中心を通る半径方向の外側（外径
側）に向って高く設定し、運転中にケーシング２０に対
し、前縁スナッバカバー１５ａ1 （１５ｂ1 ）および後
縁スナッバカバー１５ａ2 （１５ｂ2 ）のそれぞれの隙
間ＣＬｌ，ＣＬｔを、ＣＬｌ＝ＣＬｔにするので、蒸気
漏れを少なくさせることができ、風損を少なくさせて翼
性能を向上させることができ、タービン動翼の長翼化を
実現することができる。As described above, in the present embodiment, the leading edge snubber cover 15a1 (15b1) is attached to the trailing edge snubber cover 15a2 (15b2) with the deviation height δcv at the beginning of assembly.
The height is set higher toward the radially outer side (outer diameter side) passing through the center of the turbine shaft, and the leading edge snubber cover 15a1 (15b1) and the trailing edge snubber cover 15a2 (15b2) are provided to the casing 20 during operation. Since CL1 and CLt are set to CL1 = CLt, steam leakage can be reduced, windage loss can be reduced, blade performance can be improved, and a longer turbine blade can be realized. it can.
【００４２】なお、本実施形態では、組立て当初、後縁
スナッバカバー１５ａ2 （１５ｂ2）に対し、前縁スナ
ッバカバー１５ａ1 （１５ｂ1 ）を、偏差高δcvとして
予め高くオフセットしたことで説明したが、翼有効部１
３（１３ａ，１３ｂ）が例えば蒸気力により腹側１８か
ら背側１９に倒れる変位が大きく高応力になる場合、予
め翼断面の重心位置を調整し、翼有効部１３（１３ａ，
１３ｂ）を積極的に背側１９から腹側１８に変位させる
場合もある。この場合、偏差高δcvを、上述とは逆に、
δcv＝Ｃｌｅ−Ｃｔｅにし、前縁スナッバカバー１５ａ
1 （１５ｂ1 ）は、後縁スナッバカバー１５ａ2 （１５
ｂ2 ）に対し、タービン軸の中心を通る半径方向の内側
（内径側）に向って延びるように設定してもよい。In the present embodiment, the leading edge snubber cover 15a1 (15b1) is offset from the trailing edge snubber cover 15a2 (15b2) as the deviation height δcv in advance at the beginning of assembly. Part 1
3 (13a, 13b), for example, when the displacement falling from the ventral side 18 to the dorsal side 19 due to steam force causes a large stress, the center of gravity of the blade section is adjusted in advance, and the blade effective portion 13 (13a,
13b) may be positively displaced from the dorsal side 19 to the ventral side 18. In this case, the deviation height δcv,
δcv = Cle-Cte, leading edge snubber cover 15a
1 (15b1) is a trailing edge snubber cover 15a2 (15
b2), it may be set so as to extend inward (inner diameter side) in the radial direction passing through the center of the turbine shaft.
【００４３】図４は、本発明に係るタービン動翼の第２
実施形態を示す概略斜視図である。なお、第１実施形態
の構成部分または対応する部分と同一部分には同一符号
を付す。FIG. 4 shows a second embodiment of the turbine rotor blade according to the present invention.
It is a schematic perspective view showing an embodiment. The same reference numerals are given to the same components as those of the first embodiment or corresponding components.
【００４４】本実施形態に係るタービン動翼は、後縁ス
ナッバカバー１５ａ2 （１５ｂ2 ）の端面１７ｂの厚み
Ｔｔを、前縁スナッバカバー１５ａ1 （１５ｂ1 ）の端
面１７ａの厚みＴｌに対し、相対的に厚くしたものであ
る。In the turbine rotor blade according to this embodiment, the thickness Tt of the end face 17b of the trailing snubber cover 15a2 (15b2) is relatively thicker than the thickness Tl of the end face 17a of the leading edge snubber cover 15a1 (15b1). It was done.
【００４５】一般に、タービン動翼は、図５に示すよう
に、隣の翼有効部１３ｂから一方の翼有効部１３ａに向
って流れる蒸気ＳＴに水滴が含まれており、この水滴が
遠心力により吹き飛ばされて図示の軌跡線ＴＲに沿って
流れる。このため、後縁スナッバカバー１５ｂ2 の端面
１７ｂと前縁スナッバカバー１５ａ1 の端面１７ａとの
間に段差部分ができ、前縁スナッバカバー１５ａ1 の端
面１７ａの方が後縁スナッバカバー１５ｂ2 の端面１７
ｂよりもタービン軸の中心を通る半径方向の内側（内径
側）に向って突き出ていると、前縁スナッバカバー１５
ａ1 の端面１７ａが水滴により侵食を受け、フレッティ
ング摩耗を引き起す。Generally, as shown in FIG. 5, in the turbine rotor blade, water droplets are contained in steam ST flowing from the adjacent blade effective portion 13b toward one blade effective portion 13a, and the water droplet is generated by centrifugal force. It is blown off and flows along the illustrated trajectory line TR. Therefore, a step is formed between the end face 17b of the trailing edge snubber cover 15b2 and the end face 17a of the leading edge snubber cover 15a1, and the end face 17a of the leading edge snubber cover 15a1 is closer to the end face 17 of the trailing edge snubber cover 15b2.
b, projecting radially inward (inner diameter side) passing through the center of the turbine shaft, leading edge snubber cover 15
The end face 17a of a1 is eroded by water droplets, causing fretting wear.
【００４６】本実施形態は、この点に着目したもので、
後縁スナッバカバー１５ａ2 （１５ｂ2 ）の端面１７ｂ
の厚みＴｔを、前縁スナッバカバー１５ａ1 （１５ｂ1
）の端面１７ａの厚みＴｌよりもタービン軸の中心を
通る半径方向の内側（内径側）に向って厚く設定し、水
滴による前縁スナッバカバー１５ａ1 （１５ｂ1 ）の侵
食を防止したものである。The present embodiment focuses on this point.
End face 17b of trailing edge snubber cover 15a2 (15b2)
Of the leading edge snubber cover 15a1 (15b1
) Is set to be thicker inward in the radial direction passing through the center of the turbine shaft (inner diameter side) than the thickness Tl of the end face 17a, thereby preventing erosion of the leading edge snubber cover 15a1 (15b1) by water droplets.
【００４７】したがって、本実施形態によれば、後縁ス
ナッバカバー１５ａ2 （１５ｂ2 ）の端面１７ｂの厚み
Ｔｔを、前縁スナッバカバー１５ａ1 （１５ｂ1 ）の端
面１７ａの厚みＴｌよりもタービン軸の中心を通る半径
方向の内側（内径側）に向って厚くし、前縁スナッバカ
バー１５ａ1 （１５ｂ1 ）の水滴により侵食を防止した
ので、タービン動翼に安定した運転を行わせることがで
き、タービン動翼の長翼化を実現することができる。Therefore, according to the present embodiment, the thickness Tt of the end face 17b of the trailing edge snubber cover 15a2 (15b2) passes through the center of the turbine shaft more than the thickness Tl of the end face 17a of the leading edge snubber cover 15a1 (15b1). The thickness is increased toward the inner side (inner diameter side) in the radial direction, and erosion is prevented by water droplets on the leading edge snubber cover 15a1 (15b1). Therefore, the turbine blade can be operated stably, and the length of the turbine blade can be increased. Wing can be realized.
【００４８】図６は、本発明に係るタービン動翼の第３
実施形態を示す概略斜視図である。なお、第１実施形態
の構成部分または対応する部分には同一符号を付す。FIG. 6 shows a third embodiment of the turbine rotor blade according to the present invention.
It is a schematic perspective view showing an embodiment. Note that the same reference numerals are given to constituent parts or corresponding parts of the first embodiment.
【００４９】本実施形態に係るタービン動翼は、前縁ス
ナッバカバー１５ａ1 （１５ｂ1 ）の端面１７ａおよび
後縁スナッバカバー１５ａ2 （１５ｂ2 ）の端面１７ｂ
のそれぞれの厚みＴｄを同一にするとともに、前縁スナ
ッバカバー１５ａ1 （１５ｂ1 ）および後縁スナッバカ
バー１５ａ2 （１５ｂ2 ）のそれぞれの中間部分に、タ
ービン軸（図示せず）の中心を通る半径方向の内側（内
径側）に向って切欠溝部２１ａ（２１ｂ）を形成したも
のである。The turbine blade according to this embodiment has an end face 17a of the leading edge snubber cover 15a1 (15b1) and an end face 17b of the trailing edge snubber cover 15a2 (15b2).
And the middle of the leading edge snubber cover 15a1 (15b1) and the trailing edge snubber cover 15a2 (15b2) at the radially inner side passing through the center of the turbine shaft (not shown). Notched grooves 21a (21b) are formed toward (inner diameter side).
【００５０】従来、タービン動翼は、運転中、一方の前
縁スナッバカバー１５ａ1 の端面１７ａと隣の後縁スナ
ッバカバー１５ｂ2 の端面１７ｂとの面圧を適正値に確
保することが振動を効果的に抑制する上で重要なポイン
トになっている。Conventionally, during operation of a turbine rotor blade, it is effective to secure the surface pressure between the end face 17a of one leading edge snubber cover 15a1 and the end face 17b of the adjacent trailing edge snubber cover 15b2 at an appropriate value to effectively reduce vibration. It has become an important point in suppressing.
【００５１】また、タービン動翼の長翼化に伴ってアン
ツイストも増加するが、上述の面圧を適正値にするに
は、端面１７ａ，１７ｂより広い面積を確保するととも
に、前縁スナッバカバー１５ａ1 および後縁スナッバカ
バー１５ｂ2 の翼有効部１３（１３ａ，１３ｂ）との結
合部分の応力低減化も必要となる。さらに、水滴による
侵食防止を考えると、前縁スナッバカバー１５ａ1 およ
び後縁スナッバカバー１５ｂ2 には、何らかの対策が必
要とされる。Although the untwist increases with the lengthening of the blades of the turbine blade, in order to make the above-mentioned surface pressure an appropriate value, it is necessary to secure a larger area than the end faces 17a and 17b and to provide a leading edge snubber cover. It is also necessary to reduce the stress at the portions of the trailing edge snubber cover 15b2 and the trailing edge snubber cover 15b2 that are connected to the effective blade portions 13 (13a, 13b). Further, in order to prevent erosion by water droplets, some measures are required for the leading edge snubber cover 15a1 and the trailing edge snubber cover 15b2.
【００５２】本実施形態は、このような重要な技術事項
を考慮したもので、図７に示すように、隣の後縁スナッ
バカバー１５ｂ2 の端面１７ｂおよび一方の前縁スナッ
バカバー１５ａ1 の端面１７ａのそれぞれの厚みＴｄを
同一にするとともに、隣の後縁スナッバカバー１５ｂ2
の中間部分および一方の前縁スナッバカバー１５ａ1の
中間部分におけるタービン軸の中心を通る半径方向の内
側（内径側）のそれぞれに切欠溝部２１ａ，２１ｂを形
成し、中間部分における前縁スナッバカバー１５ａ1 お
よび後縁スナッバカバー１５ｂ2 の厚みＴｃを、端面１
７ａ，１７ｂにおける厚みＴｄよりも薄くし、蒸気ＳＴ
に含まれる水滴が図示の軌跡線ＴＲに沿って流れる際、
切欠溝部２１ａ，２１ｂから反転させ、隣の後縁スナッ
バカバー１５ｂ2 および一方の前縁スナッバカバー１５
ａ1 の面圧確保、強度維持、および侵食防止の保護、強
化を図ったものである。This embodiment takes into account such important technical matters. As shown in FIG. 7, the end face 17b of the adjacent rear edge snubber cover 15b2 and the end face 17a of one of the front edge snubber covers 15a1 are provided. The thickness Td of each is made the same, and the trailing edge snubber cover 15b2
Are formed on the radially inner side (inner diameter side) passing through the center of the turbine shaft in the middle portion of the front snubber cover 15a1 and the middle portion of one of the leading edge snubber covers 15a1, respectively. The thickness Tc of the trailing edge snubber cover 15b2 is
7a, 17b, the steam ST
When the water droplets included in the flow along the illustrated trajectory line TR,
The rear snubber cover 15b2 and one leading edge snubber cover 15 are turned over from the notch grooves 21a and 21b.
The purpose is to secure surface pressure, maintain strength, and protect and strengthen erosion prevention.
【００５３】したがって、本実施形態によれば、前縁ス
ナッバカバー１５ａ1 の端面１７ａおよび後縁スナッバ
カバー１５ｂ2 の端面１７ｂのそれぞれの厚みＴｄを厚
くするとともに、前縁スナッバカバー１５ａ1 および後
縁スナッバカバー１５ｂ2 の中間部分におけるタービン
軸の中心を通る半径方向の内側（内径側）に切欠溝部２
１ａ，２１ｂを形成し、中間部分における厚みＴｃを、
上述端面１７ａ，１７ｂの厚みＴｄよりも薄くし、端面
の面圧確保、強度維持、および侵食防止の保護・強化を
図ったので、タービン動翼に安定運転を行わせることが
できる。Therefore, according to the present embodiment, the thickness Td of each of the end face 17a of the leading edge snubber cover 15a1 and the end face 17b of the trailing edge snubber cover 15b2 is increased, and the leading edge snubber cover 15a1 and the trailing edge snubber cover 15b2 are increased. Notch groove 2 in the radially inner side (inner diameter side) passing through the center of the turbine shaft in the middle portion of
1a and 21b, and the thickness Tc at the intermediate portion is
Since the end faces 17a and 17b are made thinner than the thickness Td to secure the surface pressure of the end faces, maintain the strength, and protect / strengthen erosion prevention, the turbine blades can be operated stably.
【００５４】図８は、本発明に係るタービン動翼の第４
実施形態を示す蒸気入口側から見た概略斜視図である。
なお、第１実施形態の構成部分と同一部分または対応す
る部分には同一符号を付す。FIG. 8 shows a fourth embodiment of the turbine rotor blade according to the present invention.
It is the schematic perspective view seen from the steam inlet side which shows embodiment.
The same reference numerals are given to the same or corresponding parts as the constituent parts of the first embodiment.
【００５５】本実施形態に係るタービン動翼は、前縁ス
ナッバカバー１５ａ1 （１５ｂ1 ）および後縁スナッバ
カバー１５ａ2 （１５ｂ2 ）のそれぞれの面圧が充分に
確保されている場合、翼有効部１３（１３ａ，１３ｂ）
のそれぞれの両側から外側に向って突き出た前縁スナッ
バカバー１５ａ1 （１５ｂ1 ）および後縁スナッバカバ
ー１５ａ2 （１５ｂ2 ）の厚みをＴｅとし、翼有効部１
３（１３ａ，１３ｂ）の結合部分までの厚みをＴｂとす
るとき、Ｔｂ＞Ｔｅにして前縁スナッバカバー１５ａ1
（１５ｂ1 ）および後縁スナッバカバー１５ａ2 （１５
ｂ2 ）のそれぞれの端面１７ａ，１７ｂの厚みを薄く
し、スナッバカバー１５の軽量化を図ったものである。In the turbine rotor blade according to this embodiment, when the surface pressures of the leading edge snubber cover 15a1 (15b1) and the trailing edge snubber cover 15a2 (15b2) are sufficiently ensured, the blade effective portion 13 (13a) is provided. , 13b)
The thickness of the leading edge snubber cover 15a1 (15b1) and the trailing edge snubber cover 15a2 (15b2) projecting outward from both sides of the
3 (13a, 13b), when the thickness up to the joint portion is Tb, Tb> Te and the leading edge snubber cover 15a1
(15b1) and trailing edge snubber cover 15a2 (15
The thickness of each of the end faces 17a and 17b of b2) is reduced to reduce the weight of the snubber cover 15.
【００５６】このように、本実施形態では、前縁スナッ
バカバー１５ａ1 （１５ｂ1 ）および後縁スナッバカバ
ー１５ａ2 （１５ｂ2 ）のそれぞれの端面１７ａ，１７
ｂの厚さＴｅを薄くし、翼有効部１３（１３ａ，１３
ｂ）までの結合部分までの厚さＴｂを厚くしてスナッバ
カバー１５の軽量化を図ったので、前縁スナッバカバー
１５ａ1 （１５ｂ1 ）および後縁スナッバカバー１５ａ
2 （１５ｂ2 ）と翼有効部１３（１３ａ，１３ｂ）との
結合部分の強度を高く維持することができる。As described above, in this embodiment, the respective end faces 17a, 17a of the leading edge snubber cover 15a1 (15b1) and the trailing edge snubber cover 15a2 (15b2).
b, and reduce the thickness Te of the wing effective portion 13 (13a, 13a).
The snubber cover 15 is reduced in weight by increasing the thickness Tb up to the connection portion up to b), so that the leading edge snubber cover 15a1 (15b1) and the trailing edge snubber cover 15a are provided.
2 (15b2) and the wing effective portion 13 (13a, 13b) can maintain a high strength at the joint portion.
【００５７】図９は、本発明に係るタービン動翼の第５
実施形態を示す先端部から見た概略平面図である。な
お、第１実施形態の構成部分と同一部分または対応する
部分には同一符号を付す。FIG. 9 shows a fifth embodiment of the turbine blade according to the present invention.
It is the schematic plan view seen from the front-end | tip part which shows embodiment. The same reference numerals are given to the same or corresponding parts as the constituent parts of the first embodiment.
【００５８】本実施形態に係るタービン動翼は、後縁ス
ナッバカバー１５ａ2 （１５ｂ2 ）を、蒸気ＳＴの下流
側に向って翼有効部１３（１３ａ，１３ｂ３）の後縁１
６ａ（１６ｂ）よりも長く突き出させたものである。In the turbine rotor blade according to this embodiment, the trailing edge snubber cover 15a2 (15b2) is moved toward the downstream side of the steam ST so that the trailing edge 1 of the blade effective portion 13 (13a, 13b3).
6a (16b).
【００５９】このように、本実施形態では、後縁スナッ
バカバー１５ａ2 （１５ｂ2 ）を、蒸気ＳＴの下流側に
向って翼有効部１３（１３ａ，１３ｂ）の後縁１６ａ
（１６ｂ）よりも長く突き出させて形成し、パネル振動
モードの節ＶＭの始点Ｓを翼有効部１３（１３ａ，１３
ｂ）の先端部１４ａ（１４ｂ）から離したので、翼有効
部１３（１３ａ，１３ｂ）の先端部１４ａ（１４ｂ）の
振動応力を低く抑えることができ、翼有効部１３（１３
ａ，１３ｂ）と後縁スナッバカバー１５ａ2 （１５ｂ2
）との結合部分の強度を高く維持させることができ
る。As described above, in this embodiment, the trailing edge snubber cover 15a2 (15b2) is moved toward the downstream side of the steam ST so that the trailing edge 16a of the blade effective portion 13 (13a, 13b) is moved.
(16b), the starting point S of the node VM in the panel vibration mode is set to the wing effective portion 13 (13a, 13b).
b), the vibration stress of the tip 14a (14b) of the effective blade portion 13 (13a, 13b) can be reduced, and the effective blade portion 13 (13) can be suppressed.
a, 13b) and the trailing edge snubber cover 15a2 (15b2
) Can be maintained at a high strength.
【００６０】[0060]
【発明の効果】以上の説明のとおり、本発明に係るター
ビン動翼は、隣の後縁スナッバカバーに対し、一方の前
縁スナッバカバーを、組立て当初、タービン軸の中心を
通る半径方向の外側に向って高くオフセットさせ、運転
中、翼有効分のアンツイストによ隣の後縁スナッバカバ
ーおよび一方の前縁スナッバカバーとともにケーシング
に対して隙間を少なくさせたので、蒸気漏れおよび風損
を少なくさせ翼性能を向上させることができる。As described above, in the turbine rotor blade according to the present invention, at the time of assembling, one leading edge snubber cover is attached to the adjacent trailing edge snubber cover in the radial direction passing through the center of the turbine shaft. During operation, the clearance between the casing and the adjacent trailing edge snubber cover and one leading edge snubber cover is reduced by the untwist of the wing effective part during operation, so that steam leakage and windage loss are reduced. And the wing performance can be improved.
【００６１】また、本発明に係るタービン動翼は、隣の
後縁スナッバカバーの厚みを、一方の前縁スナッバカバ
ーの厚みよりも厚くして蒸気に含まれる水滴による前縁
スナッバカバーへの侵食を防止したので、タービン動翼
に安定運転を行わせることができる。Further, in the turbine rotor blade according to the present invention, the leading edge snubber cover is made thicker than one leading edge snubber cover so that the leading edge snubber cover is eroded by water droplets contained in steam. Therefore, the turbine rotor blade can be operated stably.
【００６２】また、本発明に係るタービン動翼は、隣の
後縁スナッバカバーおよび前縁スナッバカバーのそれぞ
れの中間部分に切欠溝部を形成し、各スナッバカバーの
端面を厚く、各スナッバカバーの中間部分を比較的薄く
して各スナッバカバーの端面の面圧確保、強度維持およ
び侵食防止の保護、強化を図ったので、タービン動翼に
安定運転を行わせることができる。Further, in the turbine rotor blade according to the present invention, a notch groove is formed in each of the intermediate portions of the adjacent trailing edge snubber cover and leading edge snubber cover, and the end face of each snubber cover is thickened, so that the middle of each snubber cover is formed. By making the portion relatively thin to secure the surface pressure of the end face of each snubber cover, to maintain the strength and to protect and strengthen the erosion prevention, the turbine blade can be operated stably.
【００６３】また、本発明に係るタービン動翼は、前縁
スナッバカバーおよび後縁スナッバカバーの翼有効部に
対する結合部分を厚く、前縁スナッバカバーおよび後縁
スナッバカバーの厚みを比較的薄くしたので、その結合
部分の強度を高く維持することができる。In the turbine rotor blade according to the present invention, the leading edge snubber cover and the trailing edge snubber cover have thicker connecting portions to the blade effective portion, and the leading edge snubber cover and the trailing edge snubber cover have relatively thinner thicknesses. The strength of the joint can be kept high.
【００６４】また、本発明に係るタービン動翼は、後縁
スナッバカバーを、蒸気の下流側に向って翼有効部の後
縁よりも長く突き出させて形成したので、翼有効部の先
端部の振動応力を低く抑えて翼有効部と後縁スナッバカ
バーとの結合部分の強度を高く維持させることができ
る。In the turbine rotor blade according to the present invention, the trailing edge snubber cover is formed so as to protrude longer than the trailing edge of the blade effective portion toward the downstream side of the steam. Vibration stress can be kept low, and the strength of the joint between the blade effective portion and the trailing edge snubber cover can be maintained high.
【図１】本発明に係るタービン動翼の第１実施形態を示
す概略斜視図。FIG. 1 is a schematic perspective view showing a first embodiment of a turbine blade according to the present invention.
【図２】図１のＡ矢視方向から見た本発明に係るタービ
ン動翼の部分側面図。FIG. 2 is a partial side view of the turbine rotor blade according to the present invention as viewed from the direction of arrow A in FIG. 1;
【図３】本発明に係るタービン動翼の組立て当初の状態
と運転中の状態とを対比させた図。FIG. 3 is a diagram comparing a state in which the turbine blade according to the present invention is initially assembled with a state in operation.
【図４】本発明に係るタービン動翼の第２実施形態を示
す概略斜視図。FIG. 4 is a schematic perspective view showing a second embodiment of a turbine bucket according to the present invention.
【図５】図４のＢ矢視方向から見た本発明に係るタービ
ン動翼の部分側面図。FIG. 5 is a partial side view of the turbine rotor blade according to the present invention as viewed from the direction of arrow B in FIG. 4;
【図６】本発明に係るタービン動翼の第３実施形態を示
す概略斜視図。FIG. 6 is a schematic perspective view showing a third embodiment of a turbine bucket according to the present invention.
【図７】図６のＣ矢視方向から見た本発明に係るタービ
ン動翼の部分側面図。7 is a partial side view of the turbine rotor blade according to the present invention, as viewed from the direction of arrow C in FIG. 6;
【図８】本発明に係るタービン動翼の第４実施形態を示
す蒸気入口側から見た概略正面図。FIG. 8 is a schematic front view showing a turbine blade according to a fourth embodiment of the present invention, as viewed from a steam inlet side.
【図９】本発明に係るタービン動翼の第５実施形態を示
す先端部から見た概略平面図。FIG. 9 is a schematic plan view showing a fifth embodiment of a turbine blade according to the present invention, as viewed from a tip end.
【図１０】従来のタービン動翼の組立て状態を示す概略
斜視図。FIG. 10 is a schematic perspective view showing an assembled state of a conventional turbine blade.
【図１１】従来のタービン動翼における運転前の一方の
スナッバカバーと隣のスナッバカバーとの組立て状態を
示す平面図。FIG. 11 is a plan view showing an assembled state of one snubber cover and an adjacent snubber cover before operation in a conventional turbine rotor blade.
【図１２】従来のタービン動翼における運転中の一方の
スナッバカバーと隣のスナッバカバーとの組立て状態を
示す平面図。FIG. 12 is a plan view showing an assembled state of one snubber cover and an adjacent snubber cover during operation of a conventional turbine blade.
【図１３】従来のタービン動翼におけるスナッバカバー
の運転中の挙動を説明する図。FIG. 13 is a diagram illustrating the behavior of a snubber cover in a conventional turbine blade during operation.
【図１４】従来のタービン動翼の運転中における挙動を
説明する図。FIG. 14 is a diagram illustrating the behavior of a conventional turbine blade during operation.
【図１５】従来のタービン動翼におけるスナッバカバー
のケーシングに対する隙間を説明する図。FIG. 15 is a diagram illustrating a gap between a snubber cover and a casing in a conventional turbine blade.
【図１６】従来のタービン動翼におけるスナッバカバー
の端面と隣のスナッバカバーの端面との接触状態を説明
する図。FIG. 16 is a diagram illustrating a contact state between an end face of a snubber cover and an end face of an adjacent snubber cover in a conventional turbine rotor blade.
１ タービン軸 ２ 植込み部 ３ 翼有効部 ４ 先端部 ５ａ1 ，５ｂ1 前縁スナッバカバー ５ａ2 ，５ｂ2 後縁スナッバカバー ６ａ，６ｂ 前縁 ７ａ，７ｂ 後縁 ８ａ，８ｂ 端面 ９ 腹側 １０ 背側 １１ ケーシング １２ 段差部分 １３ 翼有効部 １４ａ，１４ｂ 先端部 １５ａ，１５ｂ 前縁 １５ａ1 ，１５ｂ1 前縁スナッバカバー １５ａ2 ，１５ｂ2 後縁スナッバカバー １６ａ，１６ｂ 後縁 １７ａ，１７ｂ 端面 １８ 腹側 １９ 背側 ２０ ケーシング ２１ａ，２１ｂ 切欠溝部 DESCRIPTION OF SYMBOLS 1 Turbine shaft 2 Implantation part 3 Blade effective part 4 Tip part 5a1, 5b1 Leading edge snubber cover 5a2, 5b2 Trailing edge snubber cover 6a, 6b Leading edge 7a, 7b Trailing edge 8a, 8b End face 9 Vent side 10 Back side 11 Casing 12 Step portion 13 Effective blade portion 14a, 14b Tip 15a, 15b Leading edge 15a1, 15b1 Leading edge snubber cover 15a2, 15b2 Trailing edge snubber cover 16a, 16b Trailing edge 17a, 17b End face 18 Ventral side 19 Back side 20 Casing 21a21 Notch groove
Claims (9)
した翼有効部の先端部の前縁に前縁スナッバカバーを、
その後縁に後縁スナッバカバーを備えたタービン動翼に
おいて、一方の前縁スナッバカバーを、隣の後縁スナッ
バカバーよりも、上記タービン軸の中心を通る半径方向
の外側に向って高く設定したことを特徴とするタービン
動翼。1. A leading edge snubber cover is provided on a leading edge of a tip end portion of a blade effective portion arranged in a row along a circumferential direction of a turbine shaft.
In the turbine rotor blade having a trailing edge snubber cover on the trailing edge, one leading edge snubber cover is set higher than the adjacent trailing edge snubber cover toward the radial outside passing through the center of the turbine shaft. A turbine blade.
した翼有効部の先端部の前縁に前縁スナッバカバーを、
その後縁に後縁スナッバカバーを備えたタービン動翼に
おいて、一方の前縁スナッバカバーを、隣の後縁スナッ
バカバーよりも、上記タービン軸の中心を通る半径方向
の内側に向って延びるように設定したことを特徴とする
タービン動翼。2. A leading edge snubber cover is provided on a leading edge of a tip end portion of a blade effective portion arranged in a row along a circumferential direction of a turbine shaft.
In a turbine rotor blade provided with a trailing edge snubber cover on the trailing edge, one leading edge snubber cover is set to extend inward in the radial direction passing through the center of the turbine shaft more than the adjacent trailing edge snubber cover. A turbine blade characterized by the following.
した翼有効部の先端部の前縁に前縁スナッバカバーを、
その後縁に後縁スナッバカバーを備えたタービン動翼に
おいて、隣の後縁スナッバカバーの厚みを、一方の前縁
スナッバカバーの厚みよりも厚く設定したことを特徴と
するタービン動翼。3. A leading edge snubber cover is provided on the leading edge of the tip of the blade effective portion arranged in a row along the circumferential direction of the turbine shaft.
A turbine rotor blade having a trailing edge snubber cover on its trailing edge, wherein the thickness of an adjacent trailing edge snubber cover is set to be greater than the thickness of one leading edge snubber cover.
の前縁スナッバカバーの厚みよりも、タービン軸の中心
を通り半径方向の内側に向って厚く形成したことを特徴
とする請求項３記載のタービン動翼。4. The method according to claim 3, wherein the thickness of the adjacent trailing edge snubber cover is greater than the thickness of the one leading edge snubber cover inward in the radial direction through the center of the turbine shaft. The turbine blade as described.
した翼有効部の先端部の前縁に前縁スナッバカバーを、
その後縁に後縁スナッバカバーを備えたタービン動翼に
おいて、隣の後縁スナッバカバーの端面の厚みと一方の
前縁スナッバカバーの端面の厚みを同一にするととも
に、上記後縁スナッバカバーおよび上記前縁スナッバカ
バーのそれぞれの中間部分に切欠溝部を形成したことを
特徴とするタービン動翼。5. A leading edge snubber cover is provided on the leading edge of the tip of the blade effective portion arranged in a row along the circumferential direction of the turbine shaft.
In a turbine rotor blade having a trailing edge snubber cover on the trailing edge, the thickness of the end face of the adjacent trailing edge snubber cover and the thickness of the end face of one leading edge snubber cover are the same, and the trailing edge snubber cover and the front edge A turbine rotor blade having a notch groove formed at an intermediate portion of each of the edge snubber covers.
カバーのそれぞれの中間部分に形成した切欠溝部を、タ
ービン軸の中心を通る半径方向の内側に形成したことを
特徴とする請求項５記載のタービン動翼。6. The turbine according to claim 5, wherein the notch grooves formed in the respective intermediate portions of the trailing edge snubber cover and the leading edge snubber cover are formed in a radially inner side passing through the center of the turbine shaft. Bucket.
した翼有効部の先端部の前縁に前縁スナッバカバーを、
その後縁に後縁スナッバカバーを備えたタービン動翼に
おいて、上記前縁スナッバカバーおよび上記後縁スナッ
バカバーのそれぞれの上記翼有効部への結合部の厚み
を、上記前縁スナッバカバーおよび上記後縁スナッバカ
バーのそれぞれの端面の厚みよりも厚く形成したことを
特徴とするタービン動翼。7. A leading edge snubber cover is provided on the leading edge of the tip of the blade effective portion arranged in a row along the circumferential direction of the turbine shaft.
In a turbine rotor blade provided with a trailing edge snubber cover on a trailing edge, the thickness of the connecting portion of the leading edge snubber cover and the trailing edge snubber cover to the effective blade portion is determined by the leading edge snubber cover and the trailing edge. A turbine rotor blade formed to be thicker than each end face of the snubber cover.
した翼有効部の先端部に前縁スナッバカバーを、その後
縁に後縁スナッバカバーを備えたタービン動翼におい
て、上記後縁スナッバカバーを、蒸気の下流側に向って
上記後縁よりも長く突き合せて形成したことを特徴とす
るタービン動翼。8. A turbine blade having a leading edge snubber cover at a tip end of a blade effective portion arranged in a row along a circumferential direction of a turbine shaft and a trailing edge snubber cover at a trailing edge, wherein the trailing edge snubber is provided. A turbine rotor blade wherein the cover is formed so as to abut against the downstream side of the steam longer than the trailing edge.
成したことを特徴とする請求項１，２，３，５，７また
は８記載のタービン動翼。9. The turbine rotor blade according to claim 1, wherein the blade effective portion has a blade height of 40 inches or more.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14350698A JP4051132B2 (en) | 1998-05-25 | 1998-05-25 | Turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP14350698A JP4051132B2 (en) | 1998-05-25 | 1998-05-25 | Turbine blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH11336501A true JPH11336501A (en) | 1999-12-07 |
| JP4051132B2 JP4051132B2 (en) | 2008-02-20 |
Family
ID=15340322
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP14350698A Expired - Lifetime JP4051132B2 (en) | 1998-05-25 | 1998-05-25 | Turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP4051132B2 (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005214206A (en) * | 2004-01-31 | 2005-08-11 | United Technol Corp <Utc> | Rotor blade for rotary machine |
| JP2007303440A (en) * | 2006-05-15 | 2007-11-22 | Toshiba Corp | Turbine and turbine rotor blade |
| KR100875785B1 (en) | 2006-10-05 | 2008-12-26 | 가부시키가이샤 히타치세이사쿠쇼 | Steam turbine rotary wing |
| JP2009250217A (en) * | 2008-04-11 | 2009-10-29 | Hitachi Ltd | Turbine rotor blade |
| JP2010065689A (en) * | 2008-09-08 | 2010-03-25 | General Electric Co <Ge> | Steam turbine rotating blade for low pressure section of steam turbine engine |
| CN101988392A (en) * | 2009-07-31 | 2011-03-23 | 通用电气公司 | Rotor blades for turbine engines |
| JP2011106449A (en) * | 2009-11-12 | 2011-06-02 | General Electric Co <Ge> | Turbine rotating blade and rotor |
| JP2015175336A (en) * | 2014-03-17 | 2015-10-05 | 株式会社東芝 | Turbine rotor blade and steam turbine |
-
1998
- 1998-05-25 JP JP14350698A patent/JP4051132B2/en not_active Expired - Lifetime
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005214206A (en) * | 2004-01-31 | 2005-08-11 | United Technol Corp <Utc> | Rotor blade for rotary machine |
| JP2007303440A (en) * | 2006-05-15 | 2007-11-22 | Toshiba Corp | Turbine and turbine rotor blade |
| KR100875785B1 (en) | 2006-10-05 | 2008-12-26 | 가부시키가이샤 히타치세이사쿠쇼 | Steam turbine rotary wing |
| JP2009250217A (en) * | 2008-04-11 | 2009-10-29 | Hitachi Ltd | Turbine rotor blade |
| JP2010065689A (en) * | 2008-09-08 | 2010-03-25 | General Electric Co <Ge> | Steam turbine rotating blade for low pressure section of steam turbine engine |
| CN101988392A (en) * | 2009-07-31 | 2011-03-23 | 通用电气公司 | Rotor blades for turbine engines |
| JP2011106449A (en) * | 2009-11-12 | 2011-06-02 | General Electric Co <Ge> | Turbine rotating blade and rotor |
| JP2015175336A (en) * | 2014-03-17 | 2015-10-05 | 株式会社東芝 | Turbine rotor blade and steam turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| JP4051132B2 (en) | 2008-02-20 |
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