JP2014066223A - Turbine stationary blade vibration control structure - Google Patents

Turbine stationary blade vibration control structure Download PDF

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JP2014066223A
JP2014066223A JP2012213464A JP2012213464A JP2014066223A JP 2014066223 A JP2014066223 A JP 2014066223A JP 2012213464 A JP2012213464 A JP 2012213464A JP 2012213464 A JP2012213464 A JP 2012213464A JP 2014066223 A JP2014066223 A JP 2014066223A
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stationary blade
rotor
turbine
stationary
damping structure
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JP6134878B2 (en
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Hiroyuki Yamashita
洋行 山下
Koji Oyama
宏治 大山
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Mitsubishi Heavy Industries Ltd
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Abstract

PROBLEM TO BE SOLVED: To provide a turbine stationary blade vibration control structure capable of restraining vibration generated to a stationary blade.SOLUTION: A turbine stationary blade vibration control structure comprises a casing 11 for rotatably supporting a rotor 12 of a turbine 1, and plural stationary blades 13 supported on an inner periphery of the casing 11 and aligned in a circumferential direction of the rotor 12. The structure is provided with a back side coupling part 31 projecting outward from back faces 13 of the stationary blades 13, and a front side coupling part 41 projecting outward from front faces 13d of the stationary blades 13. The stationary blades 13 adjacent to each other in the circumferential direction of the rotor 12 are coupled with each other by the back side coupling part 31 and the front side coupling part 41.

Description

本発明は、静翼に発生する振動を抑制することができるタービンの静翼制振構造に関する。   The present invention relates to a turbine stationary blade damping structure capable of suppressing vibrations generated in a stationary blade.

近年、蒸気タービンにおいては、高出力化及び高効率化を進めるのに伴って、低圧最終段の翼を通過する蒸気の流量が増加する傾向にある。一方、作動流体である蒸気を効率的に膨張させるためには、特に、低圧最終段における翼の長翼化を図ることにより、当該翼の環状面積を増加させる必要がある。   In recent years, steam turbines have a tendency to increase the flow rate of steam passing through the blades of the low-pressure final stage as the power output and the efficiency increase. On the other hand, in order to efficiently expand the steam that is the working fluid, it is necessary to increase the annular area of the blade, particularly by increasing the length of the blade in the low-pressure final stage.

また、蒸気タービンに用いられる翼においては、翼の外装形状や質量、あるいは、翼を通過する蒸気の流速や質量に応じて、振動が発生することがある。特に、上述したような、長翼化を図った翼においては、振動が更に発生し易くなるおそれがあった。   In the blade used in the steam turbine, vibration may occur depending on the outer shape and mass of the blade or the flow velocity and mass of the steam passing through the blade. In particular, in the wing having a long wing as described above, there is a risk that vibration is more likely to occur.

そこで、従来から、翼に発生する振動を抑制するようにしたタービンの翼制振構造が、種々提供されており、このような、タービンの翼制振構造は、例えば、特許文献１，２に開示されている。   In view of this, various turbine blade damping structures for turbines that suppress vibration generated in the blades have been conventionally provided. For example, Patent Documents 1 and 2 disclose such turbine blade damping structures. It is disclosed.

特開２０１１−１３７４２４号公報JP 2011-137424 A 特開昭６０−１１１００１号公報Japanese Patent Laid-Open No. 60-11101

上記従来のタービンの翼制振構造では、動翼の背面及び腹面から外側に向けて突出する連結部材を設け、ロータ回転時において動翼に作用する遠心力によって発生する当該動翼の捩じり戻りを利用して、隣接する動翼間の連結部材同士を係合させるようにしている。これにより、従来の翼制振構造においては、動翼に振動が発生すると、連結部材同士が接触して、これらの間に摩擦力が生じることになり、その摩擦力によって、その振動を減衰させることが可能となっている。   In the conventional turbine blade damping structure for a turbine, a connecting member that protrudes outward from the back surface and the abdominal surface of the rotor blade is provided, and the torsion of the rotor blade that is generated by centrifugal force acting on the rotor blade when the rotor rotates. By utilizing the return, the connecting members between adjacent rotor blades are engaged with each other. As a result, in the conventional blade damping structure, when vibration occurs in the moving blade, the connecting members come into contact with each other, and a frictional force is generated between them. The frictional force attenuates the vibration. It is possible.

一方、タービンにおける静翼は、その両端部が固定支持されるものであるため、動翼のように、ロータの回転と共に回転することはない。よって、動翼に採用可能な上記従来の翼制振構造を、静翼に適用しても、当該静翼に発生する振動を抑制することは困難となる。   On the other hand, since both ends of the stationary blade in the turbine are fixedly supported, they do not rotate with the rotation of the rotor, unlike the moving blade. Therefore, even if the conventional blade damping structure that can be used for a moving blade is applied to a stationary blade, it is difficult to suppress vibration generated in the stationary blade.

従って、本発明は上記課題を解決するものであって、静翼に発生する振動を抑制することができるタービンの静翼制振構造を提供することを目的とする。   Accordingly, an object of the present invention is to solve the above-described problems, and to provide a stationary blade damping structure for a turbine that can suppress vibration generated in the stationary blade.

上記課題を解決する第１の発明に係るタービンの静翼制振構造は、
タービンのロータを回転可能に支持するケーシングと、
前記ケーシングの内周部に支持され、前記ロータの周方向に配列される複数の静翼とを備えたタービンの静翼制振構造であって、
前記静翼の背面から外側に向けて突出する背側連結部と、
前記静翼の腹面から外側に向けて突出する腹側連結部とを設け、
前記ロータの周方向において隣接した前記静翼同士を、前記背側連結部と前記腹側連結部とによって連結させる
ことを特徴とする。 A stationary vane damping structure for a turbine according to a first invention for solving the above-described problem is
A casing for rotatably supporting the rotor of the turbine;
A stationary vane damping structure for a turbine comprising a plurality of stationary blades supported by an inner circumferential portion of the casing and arranged in a circumferential direction of the rotor,
A dorsal connection portion protruding outward from the back surface of the stationary blade;
Providing a ventral side connecting portion projecting outward from the abdominal surface of the stationary blade,
The stationary blades adjacent to each other in the circumferential direction of the rotor are connected by the back side connection portion and the ventral side connection portion.

上記課題を解決する第２の発明に係るタービンの静翼制振構造は、
前記背側連結部の先端部に、円弧状に凹むように形成される背側凹部と、
前記腹側連結部の先端部に、円弧状に凹むように形成される腹側凹部と、
前記背側凹部と前記腹側凹部との間に挟持されるピンとを備える
ことを特徴とする。 A stationary vane damping structure for a turbine according to a second invention that solves the above-described problem is as follows.
A dorsal recess formed so as to be recessed in an arc shape at the tip of the dorsal connection portion;
An abdominal recess formed to be recessed in an arc shape at the distal end of the ventral connection,
It is provided with the pin pinched between the said back side recessed part and the said abdominal side recessed part.

上記課題を解決する第３の発明に係るタービンの静翼制振構造は、
前記背側連結部または前記腹側連結部の先端部に、凹状に形成される係合凹部と、
前記腹側連結部または前記背側連結部の先端部に、凸状に形成され、前記係合凹部と係合する係合凸部とを備える
ことを特徴とする。 A stationary vane damping structure for a turbine according to a third invention for solving the above-described problem is
An engagement recess formed in a concave shape at the distal end of the back side connection part or the ventral side connection part,
The distal end of the abdomen-side connecting part or the back-side connecting part includes an engaging convex part that is formed in a convex shape and engages with the engaging concave part.

従って、本発明に係るタービンの静翼制振構造によれば、隣接した静翼同士を、背側連結部と腹側連結部とによって連結することにより、静翼の剛性を向上させることができるので、当該静翼に発生する振動を抑制することができる。   Therefore, according to the stationary blade damping structure for a turbine according to the present invention, since the adjacent stationary blades are connected to each other by the back side connecting portion and the ventral side connecting portion, the rigidity of the stationary blade can be improved. The vibration generated in the stationary blade can be suppressed.

本発明に係るタービンの静翼制振構造が適用される蒸気タービンの概略縦断面図である。It is a schematic longitudinal cross-sectional view of the steam turbine to which the stationary blade damping structure of the turbine which concerns on this invention is applied. 各段の静翼列を背面側から見た斜視図である。It is the perspective view which looked at the stationary blade row | line | column of each step from the back side. 隣接した静翼同士を連結したときの様子を内側端部側から見た平面図である。It is the top view which looked at the mode when adjacent stationary blades were connected from the inner side edge part side. 本発明の第１実施例に係るタービンの静翼制振構造を示した斜視図である。It is the perspective view which showed the stationary blade damping structure of the turbine which concerns on 1st Example of this invention. 本発明の第２実施例に係るタービンの静翼制振構造を示した図であって、（ａ）は斜視図、（ｂ）は平面図である。It is the figure which showed the stationary blade damping structure of the turbine which concerns on 2nd Example of this invention, Comprising: (a) is a perspective view, (b) is a top view. 本発明の第３実施例に係るタービンの静翼制振構造を示した図であって、（ａ）は斜視図、（ｂ）は平面図である。It is the figure which showed the stationary blade damping structure of the turbine which concerns on 3rd Example of this invention, Comprising: (a) is a perspective view, (b) is a top view. 本発明の第４実施例に係るタービンの静翼制振構造を示した図であって、（ａ）は斜視図、（ｂ）は平面図である。It is the figure which showed the stationary blade damping structure of the turbine which concerns on 4th Example of this invention, Comprising: (a) is a perspective view, (b) is a top view.

以下、本発明に係るタービンの静翼制振構造について、図面を用いて詳細に説明する。   Hereinafter, a stationary blade damping structure for a turbine according to the present invention will be described in detail with reference to the drawings.

図１に示すように、蒸気タービン１は、その外殻をなすケーシング（車室）１１と、このケーシン１１内に回転可能に支持されるロータ１２と、ケーシング１１の内周部に支持される複数の静翼１３と、この静翼１３に隣接してロータ１２の外周部に支持される複数の動翼１４とを備えている。   As shown in FIG. 1, the steam turbine 1 is supported by a casing (chamber) 11 that forms an outer shell thereof, a rotor 12 that is rotatably supported in the casing 11, and an inner peripheral portion of the casing 11. A plurality of stationary blades 13 and a plurality of moving blades 14 supported on the outer peripheral portion of the rotor 12 adjacent to the stationary blades 13 are provided.

更に、ケーシング１１の前端部には、蒸気を取り込むための蒸気取込口１５が設けられており、この蒸気取込口１５は、ケーシング１１内に形成される蒸気通路１６に連通している。そして、蒸気通路１６は、ロータ１２の軸方向に形成されており、この蒸気通路１６内には、静翼１３と動翼１４とが交互に配置されている。なお、図１に記載した２点鎖線は、蒸気の流れを示している。   Further, a steam inlet 15 for taking in steam is provided at the front end of the casing 11, and this steam inlet 15 communicates with a steam passage 16 formed in the casing 11. The steam passage 16 is formed in the axial direction of the rotor 12, and the stationary blades 13 and the moving blades 14 are alternately arranged in the steam passage 16. The two-dot chain line shown in FIG. 1 indicates the flow of steam.

静翼１３は、蒸気を下流側に隣接する動翼１４に案内するものであって、ロータ１２の周方向に等角度間隔で、且つ、ロータ１２を中心として放射状に配置されている。そして、図２に示すように、静翼１３におけるロータ１２の径方向内側の内側端部１３ａは、内側シュラウド２１に固定される一方、静翼１３におけるロータ１２の径方向外側の外側端部１３ｂは、環状部材２２に固定されている。   The stationary blades 13 guide steam to the moving blades 14 adjacent to the downstream side, and are arranged radially at equal angular intervals in the circumferential direction of the rotor 12 and centered on the rotor 12. As shown in FIG. 2, the radially inner inner end 13 a of the rotor 12 in the stationary blade 13 is fixed to the inner shroud 21, while the radially outer outer end 13 b of the rotor 12 in the stationary blade 13. Is fixed to the annular member 22.

なお、内側シュラウド２１は、円筒状に形成されており、ロータ１２の径方向において、ケーシング１１とロータ１２との間に配置されている。一方、環状部材２２は、ケーシング１１の内周部に固定されている。   The inner shroud 21 is formed in a cylindrical shape, and is disposed between the casing 11 and the rotor 12 in the radial direction of the rotor 12. On the other hand, the annular member 22 is fixed to the inner peripheral portion of the casing 11.

また、動翼１４は、蒸気の主流が有する運動エネルギを回転エネルギに変換するものであって、ロータ１２の周方向に等角度間隔で、且つ、ロータ１２を中心として放射状に配置されている。そして、動翼１４におけるロータ１２の径方向内側の内側端部は、ロータ１２の外周部に固定される一方、動翼１４におけるロータ１２の径方向外側の外側端部は、ケーシング１２の内周面との間で、所定量の隙間を有している。   The moving blades 14 convert the kinetic energy of the main flow of steam into rotational energy, and are arranged radially at equal angular intervals in the circumferential direction of the rotor 12 and centered on the rotor 12. The inner end of the rotor blade 14 on the radially inner side of the rotor 12 is fixed to the outer periphery of the rotor 12, while the outer end of the rotor blade 14 on the radially outer side of the rotor 12 is the inner periphery of the casing 12. There is a predetermined amount of gap between the surface.

ここで、蒸気タービン１では、ロータ１２の同一円周上において円形状に配列された静翼１３及び動翼１４のそれぞれの集合を、静翼１３列及び動翼１４列としている。そして、それら静翼１３列と動翼１４列とを、ロータ１２の軸方向において交互に配置している。   Here, in the steam turbine 1, a set of the stationary blades 13 and the moving blades 14 arranged in a circular shape on the same circumference of the rotor 12 is formed as a stationary blade 13 row and a moving blade 14 row. The stationary blade 13 rows and the moving blade 14 rows are alternately arranged in the axial direction of the rotor 12.

このとき、静翼１３列と、当該静翼１３列の下流側に隣接した動翼１４列とは、前後一対となって、１つの段を構成している。そして、蒸気タービン１は、その前後一対の静翼１３列及び動翼１４列から構成される段を、複数段（図１では５段）備えている。   At this time, the stationary blade 13 row and the moving blade 14 row adjacent to the downstream side of the stationary blade 13 row form a pair of front and rear to constitute one stage. The steam turbine 1 includes a plurality of stages (five stages in FIG. 1) including a pair of front and rear stationary blades 13 rows and rotor blades 14 rows.

また、複数段の静翼１３列及び動翼１４列においては、その翼長（ロータ１２の径方向の長さ、ロータ１２の軸方向と直交する方向の長さ）が、蒸気通路１６を上流側から下流側に向かうに従って、漸次長くなるように構成されている。   Further, in the plurality of stages of the stationary blade 13 row and the moving blade 14 row, the blade length (the length in the radial direction of the rotor 12 and the length in the direction perpendicular to the axial direction of the rotor 12) is upstream of the steam passage 16. It is comprised so that it may become long gradually as it goes to the downstream from the side.

更に、蒸気通路１６内に配置される最下流側の段は、蒸気圧力を最も低圧にさせる段となることから、低圧最終段となっている。そして、その低圧最終段の静翼１３及び動翼１４は、蒸気タービン１の高出力化及び高効率化を図ることを目的として、その上流側に配置される他の段の静翼１３及び動翼１４と比べて、特に、翼長が長くなるように形成されている。   Furthermore, the most downstream stage disposed in the steam passage 16 is a stage that makes the steam pressure the lowest, and thus is the low-pressure final stage. The stationary blades 13 and the moving blades 14 of the low-pressure final stage are used for the purpose of increasing the output and the efficiency of the steam turbine 1, and the stationary blades 13 and the moving blades of the other stages arranged on the upstream side thereof. Compared to the wing 14, the wing length is particularly long.

従って、蒸気タービン１の運転が開始されると、蒸気取込口１５に供給された蒸気は、各段の静翼１３列及び動翼１４列を順次通過しながら、蒸気通路１６内をロータ１２の軸方向に沿って流れる。このとき、蒸気が静翼１３列を通過することにより、蒸気の圧力が低下され、当該蒸気に運動エネルギが発生する。次いで、静翼１３列によって案内された蒸気が動翼１４列を通過することにより、蒸気の運動エネルギが回転エネルギに変換され、ロータ１２が回転される。そして、ロータ１２の回転に伴って発電機が駆動し、その発電機によって、ロータ１２の回転エネルギが電気エネルギに変換され、発電が行われる。   Accordingly, when the operation of the steam turbine 1 is started, the steam supplied to the steam intake port 15 sequentially passes through the stationary blade 13 row and the moving blade 14 row of each stage, while passing through the steam passage 16 and the rotor 12. It flows along the axial direction. At this time, when the steam passes through the 13 rows of stationary blades, the pressure of the steam is reduced, and kinetic energy is generated in the steam. Next, the steam guided by the 13 rows of stationary blades passes through the 14 rows of moving blades, whereby the kinetic energy of the steam is converted into rotational energy, and the rotor 12 is rotated. The generator is driven as the rotor 12 rotates, and the generator converts the rotational energy of the rotor 12 into electric energy to generate power.

即ち、蒸気タービン１においては、取り込んだ蒸気を、静翼１３列及び動翼１４列から構成される各段に順次通過させることにより、その蒸気の圧力を、所定の吐出圧力に達するように徐々に低下させるようにしている。このとき、上述したように、低圧最終段の静翼１３は、その翼長が最も長いため、振動強度上、最も厳しい条件下に配置されている。   That is, in the steam turbine 1, the steam that has been taken in is sequentially passed through the stages including the 13 rows of stationary blades and 14 rows of moving blades, so that the pressure of the steam gradually reaches a predetermined discharge pressure. To lower. At this time, as described above, the stationary blade 13 in the low-pressure final stage has the longest blade length, and is therefore placed under the severest conditions in terms of vibration strength.

そこで、蒸気タービン１においては、複数段の静翼１３列の中でも、少なくとも、蒸気の通過によって振動が発生し易くなる最終段の静翼１３列に対して、本発明に係る静翼制振構造を採用している。   Therefore, in the steam turbine 1, the stationary blade damping structure according to the present invention is applied to at least the last row of stationary blades 13 in which vibration is likely to occur due to the passage of steam among the plurality of rows of stationary blades 13 rows. Is adopted.

次に、本発明に係る静翼制振構造を静翼１３列に適用した場合について、図３乃至図７を用いて具体的に説明する。なお、図３に記載した２点鎖線は、蒸気の流れを示している。   Next, the case where the stationary blade damping structure according to the present invention is applied to the 13 rows of stationary blades will be specifically described with reference to FIGS. The two-dot chain line shown in FIG. 3 indicates the flow of steam.

先ず、第１実施例に係る静翼制振構造として、図３及び図４に示すように、静翼１３の背面１３ｃ及び腹面１３ｄには、背側連結部材３１及び腹側連結部材４１が設けられている。   First, as shown in FIGS. 3 and 4, as the stationary blade damping structure according to the first embodiment, the back side coupling member 31 and the abdominal side coupling member 41 are provided on the back surface 13 c and the abdominal surface 13 d of the stationary blade 13. It has been.

背側連結部材３１は、背面１３ｃからロータ１２の周方向外側に向けて突出するような、先細り形状となっている。一方、腹側連結部材４１は、腹面１３ｄからロータ１２の周方向外側に向けて突出するような、先細り形状となっている。そして、背側連結部材３１の先端面３１ａと、腹側連結部材４１の先端面４１ａとは、溶接によって連結されている。   The back side connection member 31 has a tapered shape that protrudes from the back surface 13 c toward the outer side in the circumferential direction of the rotor 12. On the other hand, the ventral side connecting member 41 has a tapered shape that protrudes from the abdominal surface 13d toward the outer side in the circumferential direction of the rotor 12. And the front end surface 31a of the back side connection member 31 and the front end surface 41a of the abdominal side connection member 41 are connected by welding.

従って、静翼１３列をロータ１２の周方向において一体化させることができるので、静翼１３の剛性を向上させることができる。これにより、静翼１３に発生する振動を抑制することができる。   Therefore, since the rows of the stationary blades 13 can be integrated in the circumferential direction of the rotor 12, the rigidity of the stationary blades 13 can be improved. Thereby, the vibration which generate | occur | produces in the stationary blade 13 can be suppressed.

また、第２実施例に係る静翼制振構造として、図５に示すように、静翼１３の背面１３ｃ及び腹面１３ｄには、背側連結部材３２及び腹側連結部材４２が設けられている。   Further, as shown in FIG. 5, as the stationary blade damping structure according to the second embodiment, a back side coupling member 32 and a ventral side coupling member 42 are provided on the back surface 13 c and the abdominal surface 13 d of the stationary blade 13. .

背側連結部材３２は、背面１３ｃからロータ１２の周方向外側に向けて突出するような、先細り形状となっており、その先端中央部には、半円状（円弧状）に凹んだ背側凹部３２ａが形成されている。一方、腹側連結部材４２は、腹面１３ｄからロータ１２の周方向外側に向けて突出するような、先細り形状となっており、その先端中央部には、半円状（円弧状）に凹んだ腹側凹部４２ａが形成されている。   The back-side connecting member 32 has a tapered shape that protrudes from the back surface 13 c toward the outer side in the circumferential direction of the rotor 12, and the back side that is recessed in a semicircular shape (arc shape) at the center of the tip. A recess 32a is formed. On the other hand, the abdominal side connecting member 42 has a tapered shape protruding from the abdominal surface 13d toward the outer side in the circumferential direction of the rotor 12, and is recessed in a semicircular shape (arc shape) at the center of the tip. A ventral recess 42a is formed.

そして、背側凹部３２ａと腹側凹部４２ａとの間には、円柱状のピン５２が挟持されている。即ち、背側連結部材３２と腹側連結部材４２とは、対向した凹部３２ａ，４２ａ間にピン５２を介在させることにより、連結されることになる。   A cylindrical pin 52 is sandwiched between the back-side recess 32a and the ventral-side recess 42a. That is, the back side connection member 32 and the abdominal side connection member 42 are connected by interposing the pin 52 between the opposed recesses 32a, 42a.

従って、静翼１３列をロータ１２に周方向において一体化させることができるので、静翼１３の剛性を向上させることができる。このとき、静翼１３に振動が発生して、背側凹部３２ａ及び腹側凹部４２ａがピン５２に強く接触すると、これら背側凹部３２ａ及び腹側凹部４２ａに対して、ピン５２からの反力が作用することになる。この結果、そのような、ピン５２のダンパ作用によって、静翼１３の振動を減衰させることができる。これにより、静翼１３に発生する振動を抑制することができる。   Therefore, since the stator blade 13 row can be integrated with the rotor 12 in the circumferential direction, the rigidity of the stator blade 13 can be improved. At this time, when vibration is generated in the stationary blade 13 and the back-side recess 32a and the abdomen-side recess 42a come into strong contact with the pin 52, the reaction force from the pin 52 against the back-side recess 32a and the abdomen-side recess 42a. Will act. As a result, the vibration of the stationary blade 13 can be attenuated by such a damper action of the pin 52. Thereby, the vibration which generate | occur | produces in the stationary blade 13 can be suppressed.

更に、第３実施例に係る静翼制振構造として、図６に示すように、静翼１３の背面１３ｃ及び腹面１３ｄには、背側連結部材３３及び腹側連結部材４３が設けられている。   Furthermore, as shown in FIG. 6, as a stationary blade damping structure according to the third embodiment, a back side coupling member 33 and a ventral side coupling member 43 are provided on the back surface 13 c and the abdominal surface 13 d of the stationary blade 13. .

背側連結部材３３は、背面１３ｃからロータ１２の周方向外側に向けて突出するような、先細り形状となっており、その先端中央部には、円形状に開口した係合凹部３３ａが形成されている。一方、腹側連結部材４３は、腹面１３ｄからロータ１２の周方向外側に向けて突出するような、先細り形状となっており、その先端中央部には、円形状に膨出した係合凸部４３ａが形成されている。   The back-side connecting member 33 has a tapered shape that protrudes from the back surface 13c toward the outer side in the circumferential direction of the rotor 12, and an engagement recess 33a that is opened in a circular shape is formed at the center of the tip. ing. On the other hand, the abdomen-side connecting member 43 has a tapered shape that protrudes from the abdominal surface 13d toward the outer side in the circumferential direction of the rotor 12, and an engagement convex portion that bulges in a circular shape at the center of the tip. 43a is formed.

そして、係合凹部３３ａと係合凸部４３ａとは、係合（嵌合）されている。即ち、背側連結部材３３と腹側連結部材４３とは、係合凹部３３ａと係合凸部４３ａとを係合させることにより、連結されることになる。   And the engagement recessed part 33a and the engagement convex part 43a are engaged (fitted). That is, the back side connecting member 33 and the abdominal side connecting member 43 are connected by engaging the engaging concave portion 33a and the engaging convex portion 43a.

従って、静翼１３列をロータ１２に周方向において一体化させることができるので、静翼１３の剛性を向上させることができる。このとき、静翼１３に振動が発生すると、係合凹部３３ａと係合凸部４３ａとの間に摩擦力が生じることになり、この摩擦力によって、静翼１３の振動を減衰させることができる。これにより、静翼１３に発生した振動を抑制することができる。   Therefore, since the stator blade 13 row can be integrated with the rotor 12 in the circumferential direction, the rigidity of the stator blade 13 can be improved. At this time, if vibration is generated in the stationary blade 13, a frictional force is generated between the engaging concave portion 33a and the engaging convex portion 43a, and the vibration of the stationary blade 13 can be attenuated by this frictional force. . Thereby, the vibration which generate | occur | produced in the stationary blade 13 can be suppressed.

また更に、第４実施例に係る静翼制振構造として、図７に示すように、静翼１３の背面１３ｃ及び腹面１３ｄには、背側連結部材３４及び腹側連結部材４４が設けられている。   Furthermore, as shown in FIG. 7, as the stationary blade damping structure according to the fourth embodiment, a back side coupling member 34 and a ventral side coupling member 44 are provided on the back surface 13 c and the abdominal surface 13 d of the stationary blade 13. Yes.

背側連結部材３４は、背面１３ｃからロータ１２の周方向外側に向けて突出するような、先細り形状となっており、その先端中央部には、楔形状に開口した係合凹部３４ａが形成されている。一方、腹側連結部材４４は、腹面１３ｄからロータ１２の周方向外側に向けて突出するような、先細り形状となっており、その先端中央部には、楔形状に膨出した係合凸部４４ａが形成されている。   The back-side connecting member 34 has a tapered shape that protrudes from the back surface 13c toward the outer side in the circumferential direction of the rotor 12, and an engaging recess 34a that is opened in a wedge shape is formed at the center of the tip. ing. On the other hand, the abdomen-side connecting member 44 has a tapered shape that protrudes from the abdominal surface 13d toward the outer side in the circumferential direction of the rotor 12, and an engagement convex portion that bulges in a wedge shape at the center of the tip. 44a is formed.

そして、係合凹部３４ａと係合凸部４４ａとは、係合（嵌合）されている。即ち、背側連結部材３４と腹側連結部材４４とは、係合凹部３４ａと係合凸部４４ａとを係合させることにより、連結されることになる。   The engagement recess 34a and the engagement projection 44a are engaged (fitted). That is, the back side connection member 34 and the abdominal side connection member 44 are connected by engaging the engagement concave part 34a and the engagement convex part 44a.

従って、静翼１３列をロータ１２に周方向において一体化させることができるので、静翼１３の剛性を向上させることができる。このとき、静翼１３に振動が発生すると、係合凹部３４ａと係合凸部４４ａとの間に摩擦力が生じることになり、この摩擦力によって、静翼１３の振動を減衰させることができる。これにより、静翼１３に発生した振動を抑制することができる。   Therefore, since the stator blade 13 row can be integrated with the rotor 12 in the circumferential direction, the rigidity of the stator blade 13 can be improved. At this time, if vibration is generated in the stationary blade 13, a frictional force is generated between the engaging concave portion 34a and the engaging convex portion 44a, and the vibration of the stationary blade 13 can be attenuated by this frictional force. . Thereby, the vibration which generate | occur | produced in the stationary blade 13 can be suppressed.

本発明は、静翼の組み付け精度を向上させることを目的としたタービンの静翼支持構造に適用可能である。   The present invention can be applied to a turbine vane support structure for the purpose of improving the assembly accuracy of a vane.

１ 蒸気タービン
１１ ケーシング
１２ ロータ
１３ 静翼
１３ｃ 背面
１３ｄ 腹面
１４ 動翼
１５ 蒸気取込口
１６ 蒸気通路
２１ 内側シュラウド
２２ 環状部材
３１〜３４ 背側連結部材
４１〜４４ 腹側連結部材 DESCRIPTION OF SYMBOLS 1 Steam turbine 11 Casing 12 Rotor 13 Stator blade 13c Back surface 13d Abdominal surface 14 Rotor blade 15 Steam intake port 16 Steam passage 21 Inner shroud 22 Annular members 31-34 Back side connection members 41-44 Abdominal side connection members

Claims (3)

タービンのロータを回転可能に支持するケーシングと、
前記ケーシングの内周部に支持され、前記ロータの周方向に配列される複数の静翼とを備えたタービンの静翼制振構造であって、
前記静翼の背面から外側に向けて突出する背側連結部と、
前記静翼の腹面から外側に向けて突出する腹側連結部とを設け、
前記ロータの周方向において隣接した前記静翼同士を、前記背側連結部と前記腹側連結部とによって連結させる
ことを特徴とするタービンの静翼制振構造。 A casing for rotatably supporting the rotor of the turbine;
A stationary vane damping structure for a turbine comprising a plurality of stationary blades supported by an inner circumferential portion of the casing and arranged in a circumferential direction of the rotor,
A dorsal connection portion protruding outward from the back surface of the stationary blade;
Providing a ventral side connecting portion projecting outward from the abdominal surface of the stationary blade,
The turbine stationary blade damping structure, wherein the stationary blades adjacent to each other in the circumferential direction of the rotor are coupled to each other by the back side coupling portion and the ventral side coupling portion. 請求項１に記載のタービンの静翼制振構造において、
前記背側連結部の先端部に、円弧状に凹むように形成される背側凹部と、
前記腹側連結部の先端部に、円弧状に凹むように形成される腹側凹部と、
前記背側凹部と前記腹側凹部との間に挟持されるピンとを備える
ことを特徴とするタービンの静翼制振構造。 In the turbine stationary blade damping structure according to claim 1,
A dorsal recess formed so as to be recessed in an arc shape at the tip of the dorsal connection portion;
An abdominal recess formed to be recessed in an arc shape at the distal end of the ventral connection,
A turbine vane damping structure, comprising: a pin sandwiched between the back-side recess and the ventral-side recess. 請求項１に記載のタービンの静翼制振構造において、
前記背側連結部または前記腹側連結部の先端部に、凹状に形成される係合凹部と、
前記腹側連結部または前記背側連結部の先端部に、凸状に形成され、前記係合凹部と係合する係合凸部とを備える
ことを特徴とするタービンの静翼制振構造。 In the turbine stationary blade damping structure according to claim 1,
An engagement recess formed in a concave shape at the distal end of the back side connection part or the ventral side connection part,
A turbine stationary blade damping structure, comprising: an engaging convex portion that is formed in a convex shape at a distal end portion of the ventral side connecting portion or the back side connecting portion and engages with the engaging concave portion.
JP2012213464A 2012-09-27 2012-09-27 Turbine vane damping structure Expired - Fee Related JP6134878B2 (en)

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Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE393333C (en) * 1924-04-01 Karl Imfeld Dipl Ing Blades for turbines
GB532372A (en) * 1938-08-27 1941-01-22 British Thomson Houston Co Ltd Improvements in and relating to elastic fluid turbines
GB863036A (en) * 1957-12-13 1961-03-15 Parsons & Marine Eng Turbine Improvements in and relating to blading in turbines and like fluid flow machines
JPS5449405U (en) * 1977-09-14 1979-04-05
JPS5450711A (en) * 1977-09-14 1979-04-20 Bbc Brown Boveri & Cie Vibration damper for turbine vane
JPS54125307A (en) * 1978-03-24 1979-09-28 Toshiba Corp Connecting device for turbine movable blades
JPS5683601U (en) * 1979-12-03 1981-07-06
JPH10176501A (en) * 1996-12-16 1998-06-30 Hitachi Ltd Integral cover blade
JP2009085214A (en) * 2007-09-11 2009-04-23 Hitachi Ltd Steam turbine moving blade assembly
JP2011137413A (en) * 2009-12-28 2011-07-14 Hitachi Ltd Steam turbine

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE393333C (en) * 1924-04-01 Karl Imfeld Dipl Ing Blades for turbines
GB532372A (en) * 1938-08-27 1941-01-22 British Thomson Houston Co Ltd Improvements in and relating to elastic fluid turbines
GB863036A (en) * 1957-12-13 1961-03-15 Parsons & Marine Eng Turbine Improvements in and relating to blading in turbines and like fluid flow machines
JPS5449405U (en) * 1977-09-14 1979-04-05
JPS5450711A (en) * 1977-09-14 1979-04-20 Bbc Brown Boveri & Cie Vibration damper for turbine vane
JPS54125307A (en) * 1978-03-24 1979-09-28 Toshiba Corp Connecting device for turbine movable blades
JPS5683601U (en) * 1979-12-03 1981-07-06
JPH10176501A (en) * 1996-12-16 1998-06-30 Hitachi Ltd Integral cover blade
JP2009085214A (en) * 2007-09-11 2009-04-23 Hitachi Ltd Steam turbine moving blade assembly
JP2011137413A (en) * 2009-12-28 2011-07-14 Hitachi Ltd Steam turbine

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