JP2017180380A - Stationary blade ring installed at axial flow rotary machine and axial flow rotary machine - Google Patents

Stationary blade ring installed at axial flow rotary machine and axial flow rotary machine Download PDF

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JP2017180380A
JP2017180380A JP2016071309A JP2016071309A JP2017180380A JP 2017180380 A JP2017180380 A JP 2017180380A JP 2016071309 A JP2016071309 A JP 2016071309A JP 2016071309 A JP2016071309 A JP 2016071309A JP 2017180380 A JP2017180380 A JP 2017180380A
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damper
recess
ring
stationary blade
blade ring
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JP6689117B2 (en
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山下　洋行
Hiroyuki Yamashita
洋行 山下
森　一石
Kazuishi Mori
一石 森
佐藤　英明
Hideaki Sato
英明 佐藤
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Mitsubishi Power Ltd
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Mitsubishi Hitachi Power Systems Ltd
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/184—Two-dimensional patterned sinusoidal

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Abstract

PROBLEM TO BE SOLVED: To provide a stationary blade ring having a dumping function effective for restricting vibration occurred mainly at the stationary blade ring and provide an axial flow rotary machine installed with the stationary blade ring.SOLUTION: Several stationary blade segments 2A, 2B comprised of several stationary blades 3 arranged in a peripheral direction to be spaced apart by a prescribed spacing, an outer peripheral ring 4 for connecting end parts 31 at outer peripheral sides of several stationary blades 3 and an inner peripheral ring 5 connecting end parts 32 at inner peripheral sides of several stationary blades 3 are arranged side by side in an annular manner while being spaced apart from each other by a clearance, there are provided a first recess part 61 formed at one end surface of each of the end parts of the two adjoining inner peripheral rings 5, 5; a second recess part 62 formed at the other end surface; a damper 63 held in the first recess part 61; and a pressing spring 64 held in the second recess part 62 to press the damper 63 against the first recess part 61.SELECTED DRAWING: Figure 1

Description

本発明は、蒸気タービンに用いて好適な、軸流回転機械に装備される静翼環、及びこれを装備した軸流回転機械に関するものである。   The present invention relates to a stationary blade ring equipped in an axial-flow rotating machine suitable for use in a steam turbine, and an axial-flow rotating machine equipped with the same.

例えば蒸気タービン等の軸流回転機械では、高効率化及び低コスト化を目的として、静翼の長大翼化、及び軸受スパンの短縮化による車室のコンパクト化が進められ、静翼の高アスペクト比化が進んでいる。この結果、静翼の振動強度が低下している。   For example, in axial-flow rotating machines such as steam turbines, for the purpose of higher efficiency and lower cost, the use of longer blades and smaller bearing spans have been promoted to achieve a higher aspect ratio of stator blades. The ratio is progressing. As a result, the vibration strength of the stationary blade is reduced.

このような静翼の振動強度の低下は静翼の振動応答性の増大によるので、静翼の振動応答性を低減させればよく、これには静翼の剛性向上や振動の減衰促進が有効である。しかし、静翼の剛性向上には限度があり、振動を減衰させる技術が種々提案されている。   Such a decrease in the vibration strength of the stationary blade is due to an increase in the vibration responsiveness of the stationary blade. Therefore, it is only necessary to reduce the vibration responsiveness of the stationary blade, which is effective by improving the rigidity of the stationary blade and promoting vibration damping. It is. However, there is a limit to improving the rigidity of the stationary blade, and various techniques for damping vibration have been proposed.

例えば特許文献１，２には、静翼の中空部にダンパを設けることにより、構造減衰を付加する構造が開示されている。このダンパ構造は、翼主体の一次モード振動の減衰に有効である。   For example, Patent Documents 1 and 2 disclose structures that add structural damping by providing a damper in the hollow portion of a stationary blade. This damper structure is effective for damping the primary mode vibration mainly of the blade.

特開２００８−１３３８２５号公報JP 2008-133825 A 特開２０１２−１３２３７５号公報JP 2012-132375 A

ところで、蒸気タービンは、周方向に所定間隔で配置された複数の静翼と、これら複数の静翼の外周側の端部同士を接続する外周リングと、複数の静翼の内周側の端部同士を接続する内周リングとからなる静翼環を有している。静翼は静翼環に取り付けられた上で、内車室に組み込まれる。
このような静翼の振動抑制については、翼を主体とした振動の抑制だけでなく、この静翼環（特に、内周リング）を主体とした振動の抑制についても要望されている。 By the way, the steam turbine includes a plurality of stationary blades arranged at predetermined intervals in the circumferential direction, an outer peripheral ring that connects the outer peripheral ends of the plurality of stationary blades, and inner peripheral ends of the plurality of stationary blades. It has a stationary blade ring composed of an inner ring connecting the parts. The stator blade is mounted on the stator blade ring and then incorporated into the inner casing.
As for such vibration suppression of the stationary blade, not only suppression of the vibration mainly of the blade but also suppression of vibration mainly of the stationary blade ring (in particular, the inner peripheral ring) is demanded.

本発明は、このような課題に着目してなされたもので、軸流回転機械に装備される静翼環を主体とした振動の抑制に有効なダンピング機能を有する静翼環、及びこれを装備した軸流回転機械を提供することを目的としている。   The present invention has been made paying attention to such a problem, and a vane ring having a damping function effective for suppressing vibration mainly including a vane ring provided in an axial-flow rotating machine, and the same It is an object to provide an axial flow rotating machine.

（１）上記目的を達成するために、本発明の軸流回転機械に装備される静翼環は、周方向に所定間隔で複数配置された静翼と、前記複数の静翼の外周側の端部同士を接続する外周リングと、前記複数の静翼の内周側の端部同士を接続する内周リングと、からなる複数の静翼セグメントが、互いにクリアランスをあけて環状に並設されてなり、前記複数の静翼セグメントの互いに前記クリアランスをあけて隣接する２つの前記内周リングの各端部の一方の端面に形成された第１凹部と、前記各端部の他方の端面に形成された第２凹部と、前記第１凹部内に保持されたダンパと、前記第２凹部内に保持され前記ダンパを前記第１凹部に押圧する押圧バネと、を備えていることを特徴としている。   (1) In order to achieve the above object, a plurality of stationary blade rings provided in the axial-flow rotating machine of the present invention are arranged on the outer circumferential side of the plurality of stationary blades arranged at predetermined intervals in the circumferential direction. A plurality of stator blade segments each including an outer peripheral ring that connects ends and an inner peripheral ring that connects ends on the inner peripheral side of the plurality of stator blades are arranged in a ring with clearance from each other. A first recess formed in one end face of each end of the two inner circumferential rings adjacent to each other with the clearance between the plurality of stationary blade segments, and the other end face of each end. The second concave portion formed, a damper held in the first concave portion, and a pressing spring held in the second concave portion to press the damper against the first concave portion. Yes.

（２）前記ダンパは、発生する摩擦力に応じて減衰力を発揮する摩擦ダンパであることが好ましい。
（３）前記押圧バネには、板バネが適用されていることが好ましい。
（４）前記第１凹部は、断面形状が矩形に形成され、前記ダンパは、前記第１凹部の形状に合わせて断面形状が矩形の直方体状に形成されていることが好ましい。
（５）前記第１凹部は、断面形状が半円型或いは五角形に形成され、前記ダンパは、前記第１凹部の形状に合わせて断面形状が半円型或いは五角形に形成されていることが好ましい。
（６）前記第２凹部内には、前記前記押圧バネと、前記押圧バネによって前記第２凹部に押圧される第２ダンパとが保持されていることが好ましい。 (2) It is preferable that the damper is a friction damper that exhibits a damping force according to the generated friction force.
(3) It is preferable that a leaf spring is applied to the pressing spring.
(4) Preferably, the first recess is formed in a rectangular cross section, and the damper is formed in a rectangular parallelepiped shape having a rectangular cross section in accordance with the shape of the first recess.
(5) Preferably, the first recess has a semicircular or pentagonal cross-sectional shape, and the damper has a semicircular or pentagonal cross-sectional shape in accordance with the shape of the first recess. .
(6) It is preferable that the pressing spring and a second damper pressed against the second recess by the pressing spring are held in the second recess.

（７）本発明の軸流回転機械は、周方向に所定間隔で複数の動翼が配置されてなる動翼ユニットと、周方向に所定間隔で複数の静翼が配置されてなる静翼ユニットと、を複数段備え、前記複数段のうちの少なくとも何れかの段の前記静翼ユニットに、（１）〜（６）の何れかに記載の静翼環が適用されていることを特徴としている。   (7) The axial-flow rotating machine of the present invention includes a moving blade unit in which a plurality of moving blades are arranged at predetermined intervals in the circumferential direction, and a stationary blade unit in which a plurality of stationary blades are arranged at predetermined intervals in the circumferential direction. And the stator blade ring according to any one of (1) to (6) is applied to the stator blade unit in at least one of the plurality of stages. Yes.

本発明によれば、静翼が流体等から加振力を受けると、内周リングの端部が軸方向に移動するような変形を伴う振動が生じる。これにより、クリアランスをあけて隣接する２つの内周リングの各端部において、端部間に滑りを生じるような相対動が発生する。このように滑りが発生すると、ダンパがこれを抑制するように作用するため、内周リングの振動（静翼環を主体とした振動）がこのダンピング作用によって抑制される。   According to the present invention, when the stationary blade receives an excitation force from a fluid or the like, vibration accompanied by deformation occurs such that the end portion of the inner peripheral ring moves in the axial direction. As a result, a relative movement that causes slippage between the end portions occurs at each end portion of the two inner peripheral rings adjacent to each other with a clearance. When slipping occurs in this way, the damper acts to suppress this, and the vibration of the inner ring (vibration mainly composed of the stationary blade ring) is suppressed by this damping action.

また、押圧バネがダンパを第１凹部に押圧するので、隣接する２つの内周リングのそれぞれの剛性が高まり、この剛性向上によって内周リングの振動応答性を低減でき、内周リングの振動を抑制することができる。   Further, since the pressing spring presses the damper against the first recess, the rigidity of each of the two adjacent inner rings increases, and this rigidity improvement can reduce the vibration responsiveness of the inner ring and reduce the vibration of the inner ring. Can be suppressed.

本発明の第１実施形態に係る静翼環の内周リングの端部間構造を示す図であって、（ａ）はその横断面図、（ｂ）はその一部を破断させて示す斜視図、（ｃ）はその分解斜視図である。It is a figure which shows the structure between the edge parts of the inner peripheral ring of the stator blade ring which concerns on 1st Embodiment of this invention, Comprising: (a) is the cross-sectional view, (b) is the perspective view which fractured | ruptures that one part FIG. 2C is an exploded perspective view thereof. 本発明の各実施形態に係る静翼環を示す図であって、（ａ）はその正面図、（ｂ）はその内周リングの端部間の拡大図〔図２（ａ）のＡ部拡大図〕である。It is a figure which shows the stator blade ring which concerns on each embodiment of this invention, Comprising: (a) is the front view, (b) is an enlarged view between the edge parts of the inner periphery ring [Part A of FIG. 2 (a)] Enlarged view]. 本発明の各実施形態に係る静翼環の静翼環を主体とした振動モードを示す静翼セグメントの斜視図である。It is a perspective view of a stationary blade segment showing a vibration mode mainly using a stationary blade ring of a stationary blade ring according to each embodiment of the present invention. 本発明の第２実施形態に係る静翼環の内周リングの端部間構造を示す図であって、（ａ）はその一部を破断させて示す斜視図、（ｂ）はその構成要素の分解斜視図である。It is a figure which shows the structure between the edge parts of the inner peripheral ring of the stationary blade ring which concerns on 2nd Embodiment of this invention, Comprising: (a) is a perspective view which fractures | ruptures one part, (b) is the component FIG. 本発明の第３実施形態に係る静翼環の内周リングの端部間構造を示す図であって、（ａ）はその一部を破断させて示す斜視図、（ｂ）はその構成要素の分解斜視図である。It is a figure which shows the structure between the edge parts of the inner peripheral ring of the stationary blade ring which concerns on 3rd Embodiment of this invention, Comprising: (a) is a perspective view which fractures | ruptures that one part, (b) is the component FIG. 本発明の第４実施形態に係る静翼環の内周リングの端部間構造を示す横断面図である。It is a cross-sectional view which shows the structure between the edge parts of the inner peripheral ring of the stationary blade ring which concerns on 4th Embodiment of this invention. 本発明の各実施形態に係る押圧バネの変形例を示す斜視図である。It is a perspective view which shows the modification of the press spring which concerns on each embodiment of this invention.

以下、図面を参照して本発明に係る実施の形態を説明する。
なお、以下に示す各実施形態はあくまでも例示に過ぎず、以下の実施形態で明示しない種々の変形や技術の適用を排除する意図はない。以下の実施形態の各構成は、それらの趣旨を逸脱しない範囲で種々変形して実施することができるとともに、必要に応じて取捨選択することができ、あるいは適宜組み合わせることが可能である。 Hereinafter, embodiments of the present invention will be described with reference to the drawings.
Note that each embodiment described below is merely an example, and there is no intention of excluding various modifications and technical applications that are not explicitly described in the following embodiment. Each configuration of the following embodiments can be implemented with various modifications without departing from the spirit thereof, and can be selected as necessary or can be appropriately combined.

また、本実施形態では、軸流回転機械として蒸気タービンを例示するが、軸流回転機械としては、ガスタービン等の他のタービンや圧縮機等にも適用することができる。   In the present embodiment, a steam turbine is exemplified as the axial-flow rotating machine, but the axial-flow rotating machine can be applied to other turbines such as a gas turbine, a compressor, and the like.

〔静翼環〕
まず、各実施形態に係る静翼環について説明する。
図示しないが、軸流回転機械としての蒸気タービンには、複数の動翼が周方向に所定間隔で配置されてなる動翼ユニットと、複数の静翼が周方向に所定間隔で配置されてなる静翼ユニットとが、複数段交互に軸流方向に並んで配置されている。動翼ユニットはタービンロータに結合されタービンロータと一体回転し、静翼ユニットはケーシングに支持されて非回転状態とされる。 [Static blade ring]
First, the stationary blade ring according to each embodiment will be described.
Although not shown, a steam turbine as an axial-flow rotating machine has a moving blade unit in which a plurality of moving blades are arranged at predetermined intervals in the circumferential direction, and a plurality of stationary blades are arranged at predetermined intervals in the circumferential direction. The stationary blade units are arranged in a plurality of stages alternately in the axial direction. The moving blade unit is coupled to the turbine rotor and rotates integrally with the turbine rotor, and the stationary blade unit is supported by the casing and is not rotated.

このうち、静翼ユニットは、図２に示すように、２つの静翼セグメント２Ａ，２Ｂ（両者を区別しない場合は符号２で示す）が、互いにクリアランスをあけて環状に並設されてなる静翼環１として構成されている。   Among these, as shown in FIG. 2, the stationary blade unit includes two stationary blade segments 2A and 2B (indicated by reference numeral 2 when the two are not distinguished from each other) arranged in a ring with a clearance from each other. The blade ring 1 is configured.

各静翼セグメント２Ａ，２Ｂ（両者を区別しない場合は符号２で示す）は、図２，図３に示すように、周方向に所定間隔で配置された複数の静翼３と、これらの複数の静翼３の外周側の端部３１同士を接続する外周リング４Ａ，４Ｂ（両者を区別しない場合は符号４で示す）と、複数の静翼３の内周側の端部３２同士を接続する内周リング５Ａ，５Ｂ（両者を区別しない場合は符号５で示す）とから構成される。
各静翼セグメント２は、外周リング４を図示しないケーシングに図示しないボルトの締結等によって固定される。 Each stationary blade segment 2A, 2B (indicated by reference numeral 2 if they are not distinguished from each other) includes a plurality of stationary blades 3 arranged at a predetermined interval in the circumferential direction, as shown in FIGS. The outer peripheral rings 4A and 4B for connecting the outer peripheral ends 31 of the stationary blades 3 (shown by reference numeral 4 when not distinguished from each other) and the inner peripheral ends 32 of the plurality of stationary blades 3 are connected. The inner rings 5A and 5B (indicated by reference numeral 5 if they are not distinguished from each other).
Each stationary blade segment 2 is fixed to a casing (not shown) by fastening a bolt (not shown) or the like to the outer ring 4.

各静翼セグメント２は、それぞれ半円環状の半リング構造に形成されている。２つの静翼セグメント２Ａ，２Ｂが、互いに対向する端部２１ａ，２１ｂを接近させ且つ直接接触しないようにクリアランスを設けて配置されることにより、円環状（全リング構造）の静翼環１が形成される。したがって、各内周リング５Ａ，５Ｂの互いに対向する端部５１ａ，５１ｂ（両者を区別しない場合は符号５１で示す）も接近し且つ直接接触しないようにクリアランスを設けて配置される。   Each stationary blade segment 2 is formed in a semi-annular half ring structure. The two stator blade segments 2A and 2B are arranged with clearance so that the end portions 21a and 21b facing each other are close to each other and are not in direct contact with each other, whereby an annular (all ring structure) stator blade ring 1 is formed. It is formed. Therefore, the end portions 51a and 51b (indicated by reference numeral 51 in the case where they are not distinguished from each other) of the inner peripheral rings 5A and 5B that are opposed to each other are arranged close to each other and not in direct contact with each other.

このような各静翼セグメント２では、静翼３がケーシング内を流通する流体等から加振力を受け、これにより各静翼３が振動する翼主体振動や内周リング５が振動する翼環主体振動が励起される。   In each stationary blade segment 2 as described above, the stationary blade 3 receives an excitation force from a fluid or the like flowing through the casing, and thereby the blade main vibration in which each stationary blade 3 vibrates or the blade ring in which the inner peripheral ring 5 vibrates. The main vibration is excited.

この結果、内周リング５には、図３に矢印で示すように、その端部５１が軸方向（図３中のＣＬはロータの回転中心線）に移動するような変形を伴うモードの振動（翼環主体振動）が生じる。このような静翼の振動が大きいと、静翼の振動強度の低下を招く。また、タービン性能にも影響する。   As a result, as shown by an arrow in FIG. 3, the inner ring 5 is vibrated in a mode that involves deformation such that its end 51 moves in the axial direction (CL in FIG. 3 is the rotation center line of the rotor). (Blade ring main vibration) occurs. When the vibration of such a stationary blade is large, the vibration strength of the stationary blade is reduced. It also affects turbine performance.

静翼の振動が大きくなるのは、静翼の長大翼化及び軸受スパンの短縮化による、静翼の高アスペクト比化が進められたものにおける１次モード振動（翼主体１次モード振動、翼環主体１次モード振動）であることが解析結果から判明している。比較的低周波の１次モード振動が増幅するのは、静翼の高アスペクト比化による静翼環１の剛性低下と、この剛性低下に伴う固有振動数の低下による共振の誘発とが原因と考えられる。   The vibrations of the stator blades increase because of the primary mode vibrations (blade-dominated primary mode vibration, blades) in which the stator blades have been increased in aspect ratio by increasing the length of the stator blades and shortening the bearing span. It is found from the analysis result that the main mode vibration is a ring-dominated primary mode). The relatively low frequency primary mode vibration is amplified because of the reduction in rigidity of the stator blade ring 1 due to the high aspect ratio of the stator blade and the induction of resonance due to the reduction in the natural frequency associated with this rigidity reduction. Conceivable.

そこで、本静翼環１では、各内周リング５Ａ，５Ｂの互いに対向する端部５１ａ，５１ｂの間に、翼環主体振動を抑制するダンパ装置を付加させて、端部５１ａ，５１ｂの振動を減衰すると共に、静翼環１の剛性を向上させ、この剛性向上により、振動応答を低減させて、振動振幅の軽減を促進するようにしている。各実施形態では、内周リング５Ａ，５Ｂの対向する端部５１ａ，５１ｂは２組あるので、これらの各箇所にダンパ装置を付加させる。
以下、各実施形態の静翼環１に付加されたダンパ装置を説明する。 Therefore, in the stator blade ring 1, a damper device that suppresses blade ring main vibration is added between the end portions 51a and 51b of the inner peripheral rings 5A and 5B facing each other, and the vibrations of the end portions 51a and 51b are added. And the rigidity of the stator blade ring 1 is improved, and by this rigidity improvement, the vibration response is reduced and the reduction of the vibration amplitude is promoted. In each embodiment, since there are two sets of opposing ends 51a and 51b of the inner peripheral rings 5A and 5B, a damper device is added to each of these portions.
Hereinafter, the damper apparatus added to the stationary blade ring 1 of each embodiment is demonstrated.

〔第１実施形態〕
（構成）
本実施形態の静翼環１には、図１に示すように、ダンパ装置６Ａが装備されている。
ダンパ装置６Ａは、内周リング５Ａ，５Ｂの互いに対向する端部５１ａ，５１ｂの一方（端部５１ａ）の端面５２ａに形成された第１凹部６１と、端部５１ａ，５１ｂの他方（端部５１ｂ）の端面５２ｂに形成された第２凹部６２と、第１凹部６１内に保持されたダンパ６３と、第２凹部６２内に保持されダンパ６３を第１凹部６１に押圧する押圧バネ６４とを備えて構成される。 [First Embodiment]
(Constitution)
As shown in FIG. 1, the stator blade ring 1 of the present embodiment is equipped with a damper device 6A.
The damper device 6A includes a first recess 61 formed on one end surface 52a of the end portions 51a and 51b facing each other of the inner peripheral rings 5A and 5B, and the other end portion (end portion) of the end portions 51a and 51b. 51b), a second recess 62 formed in the end surface 52b, a damper 63 held in the first recess 61, a pressing spring 64 held in the second recess 62 and pressing the damper 63 against the first recess 61, It is configured with.

第１凹部６１は断面形状が矩形の平屋根型に形成され、第２凹部６２も断面形状が矩形の平屋根型に形成されている。これらの第１凹部６１，第２凹部６２は、それぞれダンパ６３或いは押圧バネ６４を外部に脱落しないように保持するためのもので、それぞれ脱落防止に有効な４つの側壁面６１ａ，６２ａと、頂壁面６１ｂ或いは底壁面６２ｂと、を有している。   The first recess 61 is formed in a flat roof shape having a rectangular cross section, and the second recess 62 is also formed in a flat roof shape having a rectangular cross section. These first concave portion 61 and second concave portion 62 are for holding the damper 63 or the pressing spring 64 so as not to fall outside, respectively, and are provided with four side wall surfaces 61a and 62a effective for preventing the dropping, and the tops. Wall surface 61b or bottom wall surface 62b.

ダンパ６３は、発生する摩擦力に応じて減衰力を発揮する摩擦ダンパであり、ダンパ６３には、鋼材（ＳＳ４００等の鉄鋼材或いはステンレス鋼等）が用いられている。ダンパ６３は、第１凹部６１の形状に合わせて断面形状が矩形の平屋根型（直方体形状）に形成されている。   The damper 63 is a friction damper that exhibits a damping force in accordance with the generated friction force. The damper 63 is made of a steel material (iron or steel such as SS400 or stainless steel). The damper 63 is formed in a flat roof shape (a rectangular parallelepiped shape) having a rectangular cross section in accordance with the shape of the first recess 61.

ダンパ６３の４つの側面６３ａは、第１凹部６１の対向する側壁面６１ａと隙間を空けて対向し、ダンパ６３の頂面６３ｂは第１凹部６１の頂壁面６１ｂの面に当接する。なお、ダンパ６３の４つの側面６３ａと対向する側壁面６１ａとの隙間のうち、ロータの軸方向（図２中Ｘ方向）の隙間は、端部間の軸方向への滑りを許容するための必須のもので、ロータの径方向（図２中Ｙ方向）の隙間は寸法交差程度のもので必須ではない。   The four side surfaces 63 a of the damper 63 are opposed to the opposing side wall surface 61 a of the first recess 61 with a gap, and the top surface 63 b of the damper 63 is in contact with the surface of the top wall surface 61 b of the first recess 61. Of the gaps between the four side surfaces 63a of the damper 63 and the side wall surfaces 61a facing each other, the gap in the axial direction of the rotor (X direction in FIG. 2) is for allowing slippage between the end portions in the axial direction. The gap in the radial direction (Y direction in FIG. 2) of the rotor is an essential one and is not essential because it is about the dimension crossing.

押圧バネ６４には、断面が波形の板バネが用いられている。押圧バネ６４は、平面視形状をダンパ６３の平面視形状と対応した矩形に形成され、径方向両端の２つの直線状の側端縁６４ａ及び軸方向両端の２つの波形の側端縁６４ａ′と、波形に突出する上下２組の突端部６４ｂ，６４ｃとを有している。   A plate spring having a corrugated cross section is used as the pressing spring 64. The pressing spring 64 is formed in a rectangular shape whose plan view shape corresponds to the plan view shape of the damper 63, and has two linear side end edges 64a at both ends in the radial direction and two wavy side end edges 64a ′ at both ends in the axial direction. And two sets of projecting end portions 64b and 64c projecting in a waveform.

押圧バネ６４は、４つの側端縁６４ａ，６４ａ′を第２凹部６２の対向する側壁面６２ａに当接或いは接近させ、波形に突出する一方の突端部（図１では、下方の複数の端部）６４ｂを第２凹部６２の底壁面６２ｂに当接させ、波形に突出する他方の突端部（図１では、上方の複数の端部）６４ｃをダンパ６３の底面６３ｃに当接させて、ダンパ６３の頂面６３ｂを第１凹部６１の頂壁面６１ｂに弾性的に押し付けている。   The pressing spring 64 has four side edges 64a and 64a 'brought into contact with or approaching the opposing side wall surface 62a of the second recess 62, and has one protruding end protruding in a waveform (in FIG. 1, a plurality of lower ends). Part) 64b is brought into contact with the bottom wall surface 62b of the second recess 62, and the other protruding end part (in FIG. 1, a plurality of upper ends) 64c is brought into contact with the bottom face 63c of the damper 63, The top surface 63 b of the damper 63 is elastically pressed against the top wall surface 61 b of the first recess 61.

（作用及び効果）
本実施形態に係る静翼環１は、このようにダンパ装置６Ａを備えて構成されるので、内周リング５に、図３に矢印で示すように、端部５１が軸方向に移動するような翼環主体振動が生じようとする。このときには、２つの内周リング５Ａ，５Ｂの各端部５１ａ，５１ｂにおいて、互いに滑りを生じるように相対動が発生する。 (Function and effect)
Since the stator blade ring 1 according to the present embodiment is configured to include the damper device 6A as described above, the end portion 51 moves in the axial direction on the inner peripheral ring 5 as indicated by an arrow in FIG. Wing ring main body vibration tends to occur. At this time, relative motion occurs so that the end portions 51a and 51b of the two inner peripheral rings 5A and 5B slip each other.

これにより、ダンパ６３の頂面６３ｂと内周リング５Ａの端部５１ａの第１凹部６１の頂壁面６１ｂとが相対動するため、両者間に摩擦力が発生して、この摩擦力が相対動を減衰させるように作用する。このダンピング作用によって、翼環主体振動が抑制される。   As a result, the top surface 63b of the damper 63 and the top wall surface 61b of the first recess 61 of the end portion 51a of the inner peripheral ring 5A move relative to each other, so that a frictional force is generated between them, and this frictional force is moved relative to each other. Acts to attenuate. By this damping action, the blade ring main vibration is suppressed.

また、押圧バネ６４がダンパ６３を第１凹部６１の頂壁面６１ｂに押圧するので、隣接する２つの内周リング５Ａ，５Ｂのそれぞれの剛性が高まり、この剛性向上によって内周リング５Ａ，５Ｂの振動応答性を低減でき、内周リングの振動を抑制することができる。   Further, since the pressing spring 64 presses the damper 63 against the top wall surface 61b of the first recess 61, the rigidity of each of the two adjacent inner peripheral rings 5A, 5B is increased, and the rigidity of the inner peripheral rings 5A, 5B is increased by this rigidity improvement. Vibration responsiveness can be reduced, and vibration of the inner ring can be suppressed.

特に、静翼３の長大翼化及び軸受スパンの短縮化による、静翼３の高アスペクト比化が進められることにより、静翼３及び静翼環１の振動、特に、１次モード振動（翼主体１次モード振動、翼環主体１次モード振動）が大きくなることが解析結果から判明している。
この比較的低周波の１次モード振動が増幅するのは、静翼３や静翼環１の固有振動数の低下による共振の誘発が一因と考えられる。 In particular, by increasing the aspect ratio of the stationary blade 3 by increasing the length of the stationary blade 3 and shortening the bearing span, vibrations of the stationary blade 3 and the stationary blade ring 1, particularly primary mode vibration (blade) It has been found from the analysis results that the main mode vibration of the main body and the main mode vibration of the blade ring are large.
The reason why the relatively low frequency primary mode vibration is amplified is thought to be due to the induction of resonance due to a decrease in the natural frequency of the stationary blade 3 and the stationary blade ring 1.

特に、静翼３の高アスペクト比化は静翼３や静翼環１の剛性低下を招く。また、静翼３の長大翼化は静翼３の重量増を招くが、静翼３の長大翼化による重量増を抑制するには、中空翼を採用することが有効であるが、中空翼の場合、剛性低下を招き易い。   In particular, increasing the aspect ratio of the stationary blade 3 causes a reduction in rigidity of the stationary blade 3 and the stationary blade ring 1. In addition, the increase in the length of the stationary blade 3 causes an increase in the weight of the stationary blade 3, but in order to suppress the increase in the weight due to the increase in the length of the stationary blade 3, it is effective to employ a hollow blade. In this case, the rigidity is likely to be lowered.

本静翼環１のように、押圧バネ６４がダンパ６３を第１凹部６１に押圧し内周リング５Ａ，５Ｂの剛性を高めることは、内周リング５Ａ，５Ｂの振動応答性を低減して、静翼環１の振動を抑制することに有効であり、静翼３の高アスペクト比化に起因した振動を抑制し、振動強度を確保することができる。   Like the stationary blade ring 1, the pressing spring 64 presses the damper 63 against the first recess 61 to increase the rigidity of the inner peripheral rings 5A and 5B, thereby reducing the vibration responsiveness of the inner peripheral rings 5A and 5B. It is effective in suppressing the vibration of the stationary blade ring 1 and can suppress the vibration caused by the high aspect ratio of the stationary blade 3 to ensure the vibration strength.

また、最下段をはじめとした下流段ほど、低周波の１次モード振動を誘発しやすく、静翼３の高アスペクト比化に伴う共振の発生がより懸念されるため、本ダンパ装置６Ａが有効である。
もちろん、本ダンパ装置６Ａは、下流段に限らず翼環主体振動を抑制したい箇所の静翼環１には広く適用することができる。 In addition, the lower-stage and other downstream stages are more likely to induce low-frequency primary mode vibrations, and there is a greater concern about the occurrence of resonance associated with the increase in the aspect ratio of the stationary blade 3, so this damper device 6A is effective. It is.
Of course, this damper device 6A can be widely applied not only to the downstream stage, but also to the stationary blade ring 1 where it is desired to suppress blade ring main vibration.

〔第２実施形態〕
（構成）
本実施形態の静翼環１には、図４に示すように、ダンパ装置６Ｂが装備されている。
ダンパ装置６Ｂは、第１実施形態にかかるダンパ装置６Ａに対して第１凹部６１Ｂ及びダンパ６３Ｂの形状のみが異なっている。 [Second Embodiment]
(Constitution)
As shown in FIG. 4, the stator blade ring 1 of this embodiment is equipped with a damper device 6B.
The damper device 6B differs from the damper device 6A according to the first embodiment only in the shapes of the first recess 61B and the damper 63B.

つまり、本ダンパ装置６Ｂの第１凹部６１Ｂは、断面形状が半円型（かまぼこ型）に形成されている。つまり、第１凹部６１Ｂは、その径方向両側壁面から連続する頂壁面６１Ｂｂは半円筒面形状に形成され、その軸方向両端の各側壁面（図示略）は半円形状に形成されている。   That is, the first recess 61B of the damper device 6B is formed in a semicircular (kamaboko) cross-sectional shape. That is, as for the 1st recessed part 61B, the top wall surface 61Bb continuing from the radial direction both side wall surface is formed in a semi-cylindrical surface shape, and each side wall surface (not shown) of the axial direction both ends is formed in the semicircle shape.

また、ダンパ６３Ｂは、第１凹部６１Ｂの形状に合わせて断面形状が半円型（かまぼこ型）に形成されている。つまり、ダンパ６３Ｂの径方向両側面から頂面にかけては半円筒面形状６３Ｂｂに形成され、ダンパ６３Ｂの軸方向両側面６３Ｂａは半円形状に形成されている。   Further, the damper 63B has a semicircular (kamaboko) cross-sectional shape in accordance with the shape of the first recess 61B. In other words, the damper 63B is formed in a semi-cylindrical surface shape 63Bb from both the radial side surfaces to the top surface, and the axial side surfaces 63Ba of the damper 63B are formed in a semicircular shape.

ダンパ６３Ｂは、第１実施形態と同様に、発生する摩擦力に応じて減衰力を発揮する摩擦ダンパであり、鋼材（ＳＳ４００等の鉄鋼材或いはステンレス鋼等）が用いられている。ダンパ６３Ｂの軸方向両端の２つの側面６３Ｂａは、第１凹部６１Ｂの対向する側壁面（図示略）と隙間を空けて対向し、ダンパ６３Ｂの頂面６３Ｂｂは第１凹部６１Ｂの頂壁面６１Ｂｂに、押圧バネ６４により押し付けられている。   Similarly to the first embodiment, the damper 63B is a friction damper that exhibits a damping force in accordance with the generated friction force, and a steel material (such as a steel material such as SS400 or stainless steel) is used. The two side surfaces 63Ba at both ends in the axial direction of the damper 63B are opposed to the opposing side wall surface (not shown) of the first recess 61B with a gap, and the top surface 63Bb of the damper 63B is opposed to the top wall surface 61Bb of the first recess 61B. The pressure spring 64 is pressed.

（作用及び効果）
本実施形態に係る静翼環１は、このようにダンパ装置６Ｂを備えて構成されるので、第１実施形態と同様の作用及び効果を得ることができる。
つまり、静翼環１が振動すると、ダンパ６３Ｂの頂面６３Ｂｂと内周リング５Ａの端部５１ａの第１凹部６１Ｂの頂壁面６１Ｂｂとが相対動し両者間に摩擦力が発生して、この摩擦力が相対動を減衰させるように作用するため、翼環主体振動が抑制される。 (Function and effect)
Since the stator blade ring 1 according to the present embodiment is configured to include the damper device 6B as described above, the same operations and effects as those of the first embodiment can be obtained.
That is, when the stationary blade ring 1 vibrates, the top surface 63Bb of the damper 63B and the top wall surface 61Bb of the first recess 61B of the end 51a of the inner peripheral ring 5A move relative to each other, and a frictional force is generated between the two. Since the frictional force acts to attenuate the relative motion, the blade ring main vibration is suppressed.

また、押圧バネ６４がダンパ６３Ｂを第１凹部６１Ｂの頂壁面６１Ｂｂに押圧するので、内周リング５Ａ，５Ｂのそれぞれの剛性が高まり、この剛性向上によって内周リング５Ａ，５Ｂの振動応答性を低減でき、内周リングの振動を抑制することができる。   Further, since the pressing spring 64 presses the damper 63B against the top wall surface 61Bb of the first recess 61B, the rigidity of the inner peripheral rings 5A and 5B is increased, and the vibration responsiveness of the inner peripheral rings 5A and 5B is improved by this rigidity improvement. This can reduce the vibration of the inner ring.

本実施形態の場合、第１凹部６１Ｂの頂壁面６１Ｂｂ及びダンパ６３Ｂの頂面６３Ｂｂが、断面形状が半円型（かまぼこ型）に形成されているので、第１凹部６１Ｂ内へのダンパ６３Ｂの収まりがよく、また、第１凹部６１Ｂの頂壁面６１Ｂｂとダンパ６３Ｂの頂面６３Ｂｂとを広い面積で接触させることができ、摩擦力による振動減衰効果をより確実に得やすいものと考えられる。   In the case of the present embodiment, the top wall surface 61Bb of the first recess 61B and the top surface 63Bb of the damper 63B are formed in a semicircular shape (kamaboko-shaped), so that the damper 63B into the first recess 61B It is considered that the top wall 61Bb of the first recess 61B and the top surface 63Bb of the damper 63B can be brought into contact with each other over a wide area, and the vibration damping effect due to the frictional force can be obtained more reliably.

〔第３実施形態〕
（構成）
本実施形態の静翼環１には、図５に示すように、ダンパ装置６Ｃが装備されている。
ダンパ装置６Ｃは、第１実施形態にかかるダンパ装置６Ａに対して第１凹部６１Ｃ及びダンパ６３Ｃの形状のみが異なっている。 [Third Embodiment]
(Constitution)
As shown in FIG. 5, the stator blade ring 1 of the present embodiment is equipped with a damper device 6C.
The damper device 6C differs from the damper device 6A according to the first embodiment only in the shapes of the first recess 61C and the damper 63C.

つまり、本ダンパ装置６Ｃの第１凹部６１Ｃは、断面形状が五角形（ペントルーフ型）に形成されている。つまり、第１凹部６１Ｃの頂壁面６１Ｃｂは、対向する一対の径方向側壁面６１Ｃａ，６１Ｃａからそれぞれ屈曲して斜め上方へ延びた２つの平面状斜面によって三角屋根形状に形成されている。また、第１凹部６１Ｃの頂壁面６１Ｃｂの径方向側壁面（図示略）は、五角形状に形成されている。   That is, the first recess 61C of the damper device 6C is formed in a pentagonal shape (pent roof type). That is, the top wall surface 61Cb of the first recess 61C is formed in a triangular roof shape by two planar inclined surfaces that are bent from the pair of opposed radial side wall surfaces 61Ca and 61Ca and extend obliquely upward. The radial side wall surface (not shown) of the top wall surface 61Cb of the first recess 61C is formed in a pentagonal shape.

また、ダンパ６３Ｂは、第１凹部６１Ｃの形状に合わせて断面形状が五角形（ペントルーフ型）に形成されている。つまり、ダンパ６３Ｃの頂面６３Ｃｂは、一対の側面６１Ｃａ，６１Ｃａからそれぞれ屈曲して斜め上方へ延びた２つの平面状斜面によって三角屋根形状に形成されている。ダンパ６３Ｃの軸方向両側面６３Ｃａ´は五角形状に形成されている。   Further, the damper 63B is formed in a pentagonal shape (pent roof type) in accordance with the shape of the first recess 61C. That is, the top surface 63Cb of the damper 63C is formed in a triangular roof shape by two planar inclined surfaces that are bent from the pair of side surfaces 61Ca and 61Ca and extend obliquely upward. Both axial side surfaces 63Ca ′ of the damper 63C are formed in a pentagonal shape.

ダンパ６３Ｃも、第１実施形態と同様に、発生する摩擦力に応じて減衰力を発揮する摩擦ダンパであり、鋼材（ＳＳ４００等の鉄鋼材或いはステンレス鋼等）が用いられている。ダンパ６３Ｃの軸方向両側面６３Ｃａ´は、第１凹部６１Ｃの対向する側壁面（図示略）と隙間を空けて対向し、ダンパ６３Ｃの頂面６３Ｃｂは第１凹部６１Ｃの頂壁面６１Ｃｂに、押圧バネ６４により押し付けられている。   Similarly to the first embodiment, the damper 63C is a friction damper that exhibits a damping force according to the generated friction force, and a steel material (steel material such as SS400 or stainless steel or the like) is used. Both side surfaces 63Ca ′ in the axial direction of the damper 63C are opposed to the opposing side wall surface (not shown) of the first recess 61C with a gap, and the top surface 63Cb of the damper 63C is pressed against the top wall surface 61Cb of the first recess 61C. It is pressed by a spring 64.

（作用及び効果）
本実施形態に係る静翼環１は、このようにダンパ装置６Ｃを備えて構成されるので、第１実施形態と同様の作用及び効果を得ることができる。
つまり、静翼環１が振動すると、ダンパ６３Ｃの頂面６３Ｃｂと内周リング５Ａの端部５１ａの第１凹部６１Ｃの頂壁面６１Ｃｂとが相対動し両者間に摩擦力が発生して、この摩擦力が相対動を減衰させるように作用するため、翼環主体振動が抑制される。 (Function and effect)
Since the stator blade ring 1 according to the present embodiment is configured to include the damper device 6C as described above, the same operations and effects as those of the first embodiment can be obtained.
That is, when the stationary blade ring 1 vibrates, the top surface 63Cb of the damper 63C and the top wall surface 61Cb of the first recess 61C of the end 51a of the inner peripheral ring 5A move relative to each other, and a frictional force is generated between them. Since the frictional force acts to attenuate the relative motion, the blade ring main vibration is suppressed.

また、押圧バネ６４がダンパ６３Ｃを第１凹部６１Ｃの頂壁面６１Ｃｂに押圧するので、内周リング５Ａ，５Ｂのそれぞれの剛性が高まり、この剛性向上によって内周リング５Ａ，５Ｂの振動応答性を低減でき、内周リングの振動を抑制することができる。   Further, since the pressing spring 64 presses the damper 63C against the top wall surface 61Cb of the first recess 61C, the rigidity of the inner peripheral rings 5A and 5B is increased, and the vibration responsiveness of the inner peripheral rings 5A and 5B is improved by this rigidity improvement. This can reduce the vibration of the inner ring.

本実施形態の場合、第１凹部６１Ｃの頂壁面６１Ｃｂ及びダンパ６３Ｃの頂面６３Ｃｂが、三角屋根形状に形成されているので、第２実施形態と同様に、第１凹部６１Ｃ内へのダンパ６３Ｃの収まりがよく、また、第１凹部６１Ｃの頂壁面６１Ｃｂとダンパ６３Ｃの頂面６３Ｃｂとを広い面積で接触させることができ、摩擦力による振動減衰効果をより確実に得やすいものと考えられる。   In the case of the present embodiment, since the top wall surface 61Cb of the first recess 61C and the top surface 63Cb of the damper 63C are formed in a triangular roof shape, the damper 63C into the first recess 61C as in the second embodiment. Further, it is considered that the top wall surface 61Cb of the first recess 61C and the top surface 63Cb of the damper 63C can be brought into contact with each other over a wide area, and the vibration damping effect due to the frictional force can be easily obtained.

〔第４実施形態〕
（構成）
本実施形態の静翼環１には、図６に示すように、ダンパ装置６Ｄが装備されている。
ダンパ装置６Ｄは、第１実施形態にかかるダンパ装置６Ａに対して、第２ダンパ６５が追加されている。 [Fourth Embodiment]
(Constitution)
As shown in FIG. 6, the stator blade ring 1 of this embodiment is equipped with a damper device 6D.
In the damper device 6D, a second damper 65 is added to the damper device 6A according to the first embodiment.

つまり、本ダンパ装置６Ｄでは、第１凹部６１内に第１ダンパ６３が装備され、第２凹部６２内に、第２ダンパ６５及び押圧バネ６４が装備されている。
第１ダンパ６３は第１実施形態のダンパ６３と同様のものであり、発生する摩擦力に応じて減衰力を発揮する摩擦ダンパである。第２ダンパ６５も第１ダンパ６３と同様に、発生する摩擦力に応じて減衰力を発揮する摩擦ダンパである。これらのダンパ６３，６４には、鋼材（ＳＳ４００等の鉄鋼材或いはステンレス鋼等）が用いられている。 In other words, in the damper device 6D, the first damper 63 is provided in the first recess 61, and the second damper 65 and the pressing spring 64 are provided in the second recess 62.
The first damper 63 is the same as the damper 63 of the first embodiment, and is a friction damper that exhibits a damping force according to the generated friction force. Similarly to the first damper 63, the second damper 65 is a friction damper that exhibits a damping force according to the generated friction force. These dampers 63 and 64 are made of steel (iron or steel such as SS400 or stainless steel).

第１ダンパ６３は、第１凹部６１の形状に合わせて断面形状が矩形の平屋根型（直方体形状）に形成されている。第１ダンパ６３の４つの側面６３ａは、第１凹部６１の対向する側壁６１ａと隙間を空けて対向し、第１ダンパ６３の頂面６３ｃは第１凹部６１の頂壁面６１ｂに当接する。第１ダンパ６３の４つの側面６３ａと対向する側壁面６１ａとの隙間のうち、ロータの軸方向の隙間は、端部間の軸方向への滑りを許容するための必須のもので、ロータの径方向の隙間は寸法交差程度のもので必須ではない。   The first damper 63 is formed in a flat roof shape (a rectangular parallelepiped shape) having a rectangular cross section in accordance with the shape of the first recess 61. The four side surfaces 63 a of the first damper 63 are opposed to the opposing side wall 61 a of the first recess 61 with a gap, and the top surface 63 c of the first damper 63 is in contact with the top wall surface 61 b of the first recess 61. Of the gaps between the four side surfaces 63a of the first damper 63 and the side wall surfaces 61a facing each other, the gap in the axial direction of the rotor is indispensable for allowing slippage in the axial direction between the end portions. The gap in the radial direction is about a dimension crossing and is not essential.

第２ダンパ６５は、第２凹部６２の形状に合わせて断面形状が矩形の平屋根型（直方体形状）に形成されている。第２ダンパ６５の４つの側面６５ａは、第２凹部６２の対向する側壁面６２ａと隙間を空けて対向し、第２ダンパ６５の底面６５ｃは第２凹部６２のし底壁面６２ｂに当接する。第２ダンパ６５の４つの側面６５ａと対向する側壁面６１ａとの隙間のうち、ロータの軸方向の隙間は、端部間の軸方向への滑りを許容するための必須のもので、ロータの径方向の隙間は寸法交差程度のもので必須ではない。   The second damper 65 is formed in a flat roof shape (a rectangular parallelepiped shape) having a rectangular cross section in accordance with the shape of the second recess 62. The four side surfaces 65 a of the second damper 65 are opposed to the opposing side wall surface 62 a of the second recess 62 with a gap, and the bottom surface 65 c of the second damper 65 is in contact with the bottom wall surface 62 b of the second recess 62. Of the gaps between the four side surfaces 65a of the second damper 65 and the side wall surfaces 61a facing each other, the gap in the axial direction of the rotor is essential for allowing slippage in the axial direction between the end portions. The gap in the radial direction is about a dimension crossing and is not essential.

押圧バネ６４は、４つの側端縁６４ａ，６４ａ′を第２凹部６２の対向する側壁面６２ａに当接或いは接近させて第２凹部６２内に保持され、波形に突出する一方の突端部（図６では、下方の複数の端部）６４ｂを第２ダンパ６５の頂面６５ｂに当接し、波形に突出する他方の突端部（図６では、上方の複数の端部）６４ｃを第１ダンパ６３の底面６３ｃに当接している。これにより、第１ダンパ６３の頂面６３ｂは第１凹部６１の頂壁面６１ｂに、第２ダンパ６５の底面６５ｃは第２凹部６２の底壁面６２ｂに、それぞれ弾性的に押し付けられている。   The pressing spring 64 is held in the second recess 62 with the four side edges 64a and 64a 'abutting or approaching the opposing side wall surface 62a of the second recess 62, and has one protruding end projecting in a waveform ( In FIG. 6, the plurality of lower end portions 64b abut on the top surface 65b of the second damper 65, and the other projecting end portion (in FIG. 6, the plurality of upper end portions in FIG. 6) 64c is the first damper. 63 is in contact with the bottom surface 63c of the plate. Thus, the top surface 63b of the first damper 63 is elastically pressed against the top wall surface 61b of the first recess 61, and the bottom surface 65c of the second damper 65 is elastically pressed against the bottom wall surface 62b of the second recess 62.

（作用及び効果）
本実施形態に係る静翼環１は、このようにダンパ装置６Ｄを備えて構成されるので、静翼環１が振動すると、第１ダンパ６３の頂面６３ｂと第１凹部６１の頂壁面６１ｂとが相対動し、第２ダンパ６５の底面６５ｃと第２凹部６２の底壁面６２ｂとが相対動する。これらの相対動する部材間にそれぞれ摩擦力が発生して、この摩擦力が相対動を減衰させるように作用するため、翼環主体振動が抑制される。 (Function and effect)
Since the stator blade ring 1 according to the present embodiment is configured to include the damper device 6D as described above, when the stator blade ring 1 vibrates, the top surface 63b of the first damper 63 and the top wall surface 61b of the first recess 61 are provided. And the bottom surface 65c of the second damper 65 and the bottom wall surface 62b of the second recess 62 relatively move. A frictional force is generated between the members that move relative to each other, and the frictional force acts so as to attenuate the relative movement, so that the blade ring main vibration is suppressed.

また、押圧バネ６４が、第１ダンパ６３を第１凹部６１の頂壁面６１ｂに、第２ダンパ６５を第２凹部６２の底壁面６２ｂに、それぞれ押圧するので、内周リング５Ａ，５Ｂのそれぞれの剛性が高まり、この剛性向上によって内周リング５Ａ，５Ｂの振動応答性を低減でき、内周リングの振動を抑制することができる。   Further, the pressing spring 64 presses the first damper 63 against the top wall surface 61b of the first recess 61 and the second damper 65 against the bottom wall surface 62b of the second recess 62, so that each of the inner peripheral rings 5A and 5B. The rigidity of the inner ring 5A, 5B can be reduced by this rigidity improvement, and the vibration of the inner ring can be suppressed.

（その他）
以上、本発明の実施形態を説明したが、本発明はかかる実施形態に限定されるものではない。
例えば、各実施形態におけるダンパと押圧バネとの配置を逆に（図１，図４，図５，図６中で上下逆に）配置してもよい。
また、第１凹部や第２凹部やこの内部に収容されるダンパや押圧バネの形状も適宜変更しうるものである。 (Other)
As mentioned above, although embodiment of this invention was described, this invention is not limited to this embodiment.
For example, the arrangement of the damper and the pressing spring in each embodiment may be reversed (upside down in FIGS. 1, 4, 5, and 6).
Further, the shapes of the first recess, the second recess, the damper and the press spring accommodated in the first recess, the second recess, and the like can be appropriately changed.

さらに、上記の各実施形態では、押圧バネ６４を断面が波形の板バネで構成したが、板バネを使う場合もこれに限定されるものではなく、例えば図７に示す押圧バネ６５のように、両縁部が湾曲した脚部６５ａを有し、この脚部の弾性変形でバネ力を発揮するものでもよい。
また、僅かなクリアランス部に押圧バネを介装するために、板バネが好適であるが、適用しうるバネは板バネに限らない。 Further, in each of the above-described embodiments, the pressing spring 64 is configured by a leaf spring having a corrugated cross section, but the case where the leaf spring is used is not limited to this. For example, a pressing spring 65 shown in FIG. The leg portions 65a may be curved at both edges, and the spring force may be exerted by elastic deformation of the leg portions.
Further, a leaf spring is suitable for interposing a pressing spring in a slight clearance, but the applicable spring is not limited to a leaf spring.

また、ダンパの材質も上記実施形態のものに限定されない。
ダンパの種類としては、摩擦ダンパがシンプルで且つ狭隘なスペースに介装するのに適しているが、介装可能であれば、ダンパの種類は問わない。 Further, the material of the damper is not limited to that of the above embodiment.
As the type of the damper, the friction damper is suitable for being interposed in a simple and narrow space, but the type of the damper is not limited as long as it can be interposed.

また、上記の各実施形態のように、各静翼セグメント２は円環状（全リング構造）を２つ割りした半円環状の半リング構造のものが通常であるが、各静翼セグメント２の分割数はこれに限定されない。何れの分割数であっても、複数の静翼セグメントが円環状に並ぶように配置されて円環状（全リング構造）の静翼環が形成されればよい。何れであっても、２つの内周リングの隣接する端部間にダンパ装置を付加させればよい。   In addition, as in each of the above-described embodiments, each stationary blade segment 2 is usually a semi-annular half ring structure in which an annular shape (entire ring structure) is divided into two. The number of divisions is not limited to this. Whatever the number of divisions, a plurality of stator blade segments may be arranged in an annular shape to form an annular (entire ring structure) stator blade ring. In any case, a damper device may be added between adjacent ends of the two inner peripheral rings.

１ 静翼環
２，２Ａ，２Ｂ 静翼セグメント
２１ａ，２１ｂ 静翼セグメント２Ａ，２Ｂの端部
３ 静翼
３１ 静翼３の外周側の端部
３２ 静翼３の内周側の端部
４，４Ａ，４Ｂ 外周リング
５，５Ａ，５Ｂ 内周リング
５１，５１ａ，５１ｂ 内周リング５，５Ａ，５Ｂの端部
５２ａ，５１ｂ 端部５１ａ，５１ｂの端面
６Ａ〜６Ｄ ダンパ装置
６１ 第１凹部
６１ａ 第１凹部６１の側壁面
６１ｂ 第１凹部６１の頂壁面
６２ 第２凹部
６２ａ 第２凹部６２の側壁面
６２ｂ 第２凹部６２の底壁面
６３，６３Ｂ，６３Ｃ，６５ ダンパ
６３ａ，６３Ｂａ，６３Ｃａ，６５ａ ダンパ６３，６３Ｂ，６３Ｃ，６５の側面
６３ｂ，６３Ｂｂ，６３Ｃｂ，６５ｂ ダンパ６３，６３Ｂ，６３Ｃ，６５の頂面
６３ｃ，６３Ｂｃ，６３Ｃｃ，６５ｃ ダンパ６３，６３Ｂ，６３Ｃ，６５の底面
６４，６５ 押圧バネ
６４ａ，６４ａ′ 押圧バネ６４の側端縁
６４ｂ，６４ｃ 押圧バネ６４の突端部 DESCRIPTION OF SYMBOLS 1 Stator blade ring 2, 2A, 2B Stator blade segment 21a, 21b End part of stator blade segment 2A, 2B 3 Stator blade 31 End part of stator blade 3 outer peripheral side 32 End part of stator blade 3 inner peripheral side 4, 4A, 4B Outer ring 5, 5, A, 5B Inner ring 51, 51a, 51b Ends of inner ring 5, 5A, 5B 52a, 51b End surfaces of ends 51a, 51b 6A-6D Damper device 61 First recess 61a First 1 side wall surface 61b of the first recess 61 62 second wall 62a side wall surface 62b of the second recess 62 bottom wall surface 63b of the second recess 62 63, 63B, 63C, 65 damper 63a, 63Ba, 63Ca, 65a damper 63, 63B, 63C, 65 side surfaces 63b, 63Bb, 63Cb, 65b dampers 63, 63B, 63C, 65 top surfaces 63c, 63Bc, 63Cc, 65c dampers 63 63B, 63C, 65 of the bottom surface 64, 65 pressing the spring 64a, 64a 'side edges 64b of the pressing spring 64, the projecting end of 64c pressure spring 64

Claims (7)

周方向に所定間隔で複数配置された静翼と、
前記複数の静翼の外周側の端部同士を接続する外周リングと、
前記複数の静翼の内周側の端部同士を接続する内周リングと、からなる複数の静翼セグメントが、互いにクリアランスをあけて環状に並設されてなり、
前記複数の静翼セグメントの互いに前記クリアランスをあけて隣接する２つの前記内周リングの各端部の一方の端面に形成された第１凹部と、
前記各端部の他方の端面に形成された第２凹部と、
前記第１凹部内に保持されたダンパと、
前記第２凹部内に保持され前記ダンパを前記第１凹部に押圧する押圧バネと、を備えている
ことを特徴とする、軸流回転機械に装備される静翼環。 A plurality of stationary blades arranged at predetermined intervals in the circumferential direction;
An outer ring connecting the outer peripheral ends of the plurality of stationary blades; and
A plurality of stator blade segments composed of inner peripheral rings connecting the inner peripheral ends of the plurality of stator blades, and arranged in a ring with clearance from each other,
A first recess formed on one end surface of each end of the two inner circumferential rings adjacent to each other with the clearance between the plurality of stationary blade segments;
A second recess formed on the other end face of each end,
A damper held in the first recess;
A stationary blade ring equipped in an axial-flow rotating machine, comprising: a pressing spring held in the second recess and pressing the damper against the first recess. 前記ダンパは、発生する摩擦力に応じて減衰力を発揮する摩擦ダンパである
ことを特徴とする、請求項１記載の軸流回転機械に装備される静翼環。 The stator blade ring mounted on the axial-flow rotating machine according to claim 1, wherein the damper is a friction damper that exhibits a damping force according to the generated friction force. 前記押圧バネには、板バネが適用されている
ことを特徴とする、請求項１又は２記載の軸流回転機械に装備される静翼環。 The stationary blade ring equipped in the axial-flow rotating machine according to claim 1, wherein a leaf spring is applied to the pressing spring. 前記第１凹部は、断面形状が矩形に形成され、
前記ダンパは、前記第１凹部の形状に合わせて断面形状が矩形の直方体状に形成されている
ことを特徴とする、請求項１〜３の何れか１項に記載の軸流回転機械に装備される静翼環。 The first recess has a rectangular cross-sectional shape,
4. The axial flow rotating machine according to claim 1, wherein the damper is formed in a rectangular parallelepiped shape in cross section in accordance with the shape of the first recess. 5. Stator blade ring. 前記第１凹部は、断面形状が半円型或いは五角形に形成され、
前記ダンパは、前記第１凹部の形状に合わせて断面形状が半円型或いは五角形に形成されている
ことを特徴とする、請求項１〜３の何れか１項に記載の軸流回転機械に装備される静翼環。 The first recess is formed in a semicircular or pentagonal cross-sectional shape,
The axial flow rotary machine according to any one of claims 1 to 3, wherein the damper has a semicircular or pentagonal cross-sectional shape in accordance with the shape of the first recess. Equipped with vane ring. 前記第２凹部内には、前記前記押圧バネと、前記押圧バネによって前記第２凹部に押圧される第２ダンパとが保持されている
ことを特徴とする、請求項１〜５の何れか１項に記載の軸流回転機械に装備される静翼環。 The said 2nd recessed part hold | maintains the said pressing spring and the 2nd damper pressed by the said 2nd recessed part with the said pressing spring, The any one of Claims 1-5 characterized by the above-mentioned. A stator blade ring mounted on the axial-flow rotating machine described in the paragraph. 周方向に所定間隔で複数の動翼が配置されてなる動翼ユニットと、
周方向に所定間隔で複数の静翼が配置されてなる静翼ユニットと、を複数段備え、
前記複数段のうちの少なくとも何れかの段の前記静翼ユニットに、請求項１〜６の何れか１項に記載の静翼環が適用されている
ことを特徴とする、軸流回転機械。
A moving blade unit in which a plurality of moving blades are arranged at predetermined intervals in the circumferential direction;
A plurality of stator blade units each including a plurality of stator blades arranged at predetermined intervals in the circumferential direction,
An axial-flow rotating machine, wherein the stator blade ring according to any one of claims 1 to 6 is applied to at least one of the plurality of stages of the stator blade units.
JP2016071309A 2016-03-31 2016-03-31 Stator blade ring and axial flow rotary machine equipped in the axial flow rotary machine Active JP6689117B2 (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP7349274B2 (en) 2019-06-27 2023-09-22 三菱重工業株式会社 Stator blade support ring and turbine

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2705001A1 (en) * 1977-02-07 1978-08-10 Kraftwerk Union Ag Vibration damper ring for torsion shaft - has holes in which friction lining is pressed by spring against shaft
JP2006077759A (en) * 2004-09-13 2006-03-23 United Technol Corp <Utc> Damper/seal assembly for turbine blade
JP2007040119A (en) * 2005-08-01 2007-02-15 Mitsubishi Heavy Ind Ltd Fluid machine
JP2009052553A (en) * 2007-08-23 2009-03-12 General Electric Co <Ge> Gas turbine shroud support apparatus
DE102010041808A1 (en) * 2010-09-30 2012-04-05 Siemens Aktiengesellschaft Blade segment, turbomachinery and process for their preparation
US20120099969A1 (en) * 2009-12-29 2012-04-26 Justin Gilman Damper seal and vane assembly for a gas turbine engine
JP2013501181A (en) * 2009-07-31 2013-01-10 スネクマ Outer shell sector for winged rings for aircraft turbomachine stators, including damping shims
CN203584480U (en) * 2013-12-13 2014-05-07 中航商用航空发动机有限责任公司 Turbine blade damping device and turbine thereof
JP2014114734A (en) * 2012-12-07 2014-06-26 Mitsubishi Heavy Ind Ltd Turbine blade and turbine

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2705001A1 (en) * 1977-02-07 1978-08-10 Kraftwerk Union Ag Vibration damper ring for torsion shaft - has holes in which friction lining is pressed by spring against shaft
JP2006077759A (en) * 2004-09-13 2006-03-23 United Technol Corp <Utc> Damper/seal assembly for turbine blade
JP2007040119A (en) * 2005-08-01 2007-02-15 Mitsubishi Heavy Ind Ltd Fluid machine
JP2009052553A (en) * 2007-08-23 2009-03-12 General Electric Co <Ge> Gas turbine shroud support apparatus
JP2013501181A (en) * 2009-07-31 2013-01-10 スネクマ Outer shell sector for winged rings for aircraft turbomachine stators, including damping shims
US20120099969A1 (en) * 2009-12-29 2012-04-26 Justin Gilman Damper seal and vane assembly for a gas turbine engine
DE102010041808A1 (en) * 2010-09-30 2012-04-05 Siemens Aktiengesellschaft Blade segment, turbomachinery and process for their preparation
JP2014114734A (en) * 2012-12-07 2014-06-26 Mitsubishi Heavy Ind Ltd Turbine blade and turbine
CN203584480U (en) * 2013-12-13 2014-05-07 中航商用航空发动机有限责任公司 Turbine blade damping device and turbine thereof

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP7349274B2 (en) 2019-06-27 2023-09-22 三菱重工業株式会社 Stator blade support ring and turbine

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