JPH11148305A - Moving blade of turbine - Google Patents

Moving blade of turbine

Info

Publication number
JPH11148305A
JPH11148305A JP31483197A JP31483197A JPH11148305A JP H11148305 A JPH11148305 A JP H11148305A JP 31483197 A JP31483197 A JP 31483197A JP 31483197 A JP31483197 A JP 31483197A JP H11148305 A JPH11148305 A JP H11148305A
Authority
JP
Japan
Prior art keywords
shroud
blade
inclination angle
contact surface
contacting surface
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.)
Pending
Application number
JP31483197A
Other languages
Japanese (ja)
Inventor
Ryo Akiyama
陵 秋山
Kazuo Sato
一男 佐藤
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hitachi Ltd
Original Assignee
Hitachi Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Hitachi Ltd filed Critical Hitachi Ltd
Priority to JP31483197A priority Critical patent/JPH11148305A/en
Publication of JPH11148305A publication Critical patent/JPH11148305A/en
Pending legal-status Critical Current

Links

Abstract

PROBLEM TO BE SOLVED: To convert oscillating energy to thermal energy and to damp oscillation by forming a part from the center of the contacting surface to the gas inlet side and the gas outlet side of a contacting surface adjacent to a shroud, on a gradient surface mutually tilting in the leg direction, and providing a groove in a part of the contacting surface, where the tilting angle varies. SOLUTION: A moving blade of a turbine consists of a blade on which gas flows, a dovetail that is a part fixed to a wheel disk, and a shroud formed integrally with them. In the shroud of such moving blade, a contacting surface 6 adjacent to a back side shroud has a part, from the center of the contacting surface to the gas inlet side 9, formed on a gradient surface with an angle at which the upper side of the shroud projects, and has a gas outlet side 10 part formed on a gradient surface with an angle at which the lower side of the shroud projects. A contacting surface 7 adjacent to a front side shroud is formed to have a gradient surface in the opposite direction to the contacting surface 6. A groove 8 is formed in the contacting surface central part where the tilting angle of the contacting surface 7 varies, and can displace oscillatingly relatively.

Description

【発明の詳細な説明】DETAILED DESCRIPTION OF THE INVENTION

【0001】[0001]

【発明の属する技術分野】本発明は蒸気タービン,ガス
タービン等のタービン動翼の先端部にシュラウドを設け
たシュラウド付き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 blade having a shroud provided at the tip of a turbine blade such as a steam turbine or a gas turbine.

【0002】[0002]

【従来の技術】従来のシュラウドは、シュラウドの一方
の対角線を形成する両端部上面を隣り合わせたシュラウ
ド側へせり出して側断面を傾斜せしめ、他方の対角線を
形成する両隅部は、下面側が隣り合わせたシュラウド側
にせり出して側断面を傾斜せしめたことを特徴としてい
る(実開昭58−132103号公報)。このような接触形状と
することで、回転時の遠心力によるシュラウドのめくり
上がりを抑制すると同時に、隣接するシュラウドと接触
させることができるようにしている。
2. Description of the Related Art In a conventional shroud, upper surfaces at both ends forming one diagonal line of the shroud are protruded to the adjacent shroud sides to incline the side cross section, and both corner portions forming the other diagonal line have lower surfaces adjacent to each other. It is characterized by projecting to the shroud side and inclining the side section (Japanese Utility Model Laid-Open No. 58-132103). With such a contact shape, the shroud is prevented from turning up due to centrifugal force during rotation, and can be brought into contact with an adjacent shroud.

【0003】また図10,図11は従来のガスタービン
動翼を部分的に示したものであり、図10は2枚の隣接
するシュラウドが接触した状態の平面図、図11は2枚
の隣接するシュラウドが接触した状態の斜視図である。
運転時には翼は遠心力によりねじり変形する。このねじ
り変形の反力によってシュラウド16,17は図10の
接触面18で接触している。このような接触形状とする
ことで、隣接するシュラウドが互いに異なる位相で振動
すれば接触面に振動的相対変位が生じ、その間の摩擦力
により振動エネルギが熱エネルギに変換されて振動が減
衰される。
FIGS. 10 and 11 partially show a conventional gas turbine blade. FIG. 10 is a plan view showing two adjacent shrouds in contact with each other, and FIG. 11 is a plan view showing two adjacent shrouds. FIG. 3 is a perspective view of a state in which a shroud is in contact.
During operation, the wings are torsionally deformed by centrifugal force. The shrouds 16, 17 are in contact at the contact surface 18 in FIG. 10 due to the reaction force of the torsional deformation. By adopting such a contact shape, if adjacent shrouds vibrate in different phases, an oscillating relative displacement occurs on the contact surface, and vibration energy is converted into thermal energy by frictional force therebetween, thereby attenuating vibration. .

【0004】[0004]

【発明が解決しようとする課題】従来の技術の最初に述
べた従来のタービン動翼は、隣接するシュラウドが互い
に異なる位相で振動して接触面に振動的相対変位を生じ
るということが起こりにくいため、十分な振動の減衰効
果を得にくいという難点があった。
In the conventional turbine blade described at the beginning of the prior art, it is unlikely that adjacent shrouds vibrate at different phases from each other and cause an oscillating relative displacement on the contact surface. However, it is difficult to obtain a sufficient vibration damping effect.

【0005】また、図10,図11で示す従来のガスタ
ービン動翼は、回転時の遠心力によるシュラウドの車盤
半径方向へのめくり上がりを抑制することができなかっ
た。本発明の目的は隣接するシュラウドとの接触面に振
動的相対変位を生じることができる構造として十分な減
衰効果を持たせ、同時に車盤半径方向のめくり上がりも
抑制することができる構造として、このような問題を解
決したタービン動翼を提供することにある。
Further, the conventional gas turbine rotor blades shown in FIGS. 10 and 11 cannot suppress the shroud from turning in the vehicle radial direction due to centrifugal force during rotation. An object of the present invention is to provide a sufficient damping effect as a structure capable of generating an oscillating relative displacement on a contact surface with an adjacent shroud, and at the same time, a structure capable of suppressing turning up in a vehicle radial direction. An object of the present invention is to provide a turbine rotor blade which solves such a problem.

【0006】[0006]

【課題を解決するための手段】本発明は、翼背側のガス
入口側のシュラウド上側がせり出すような傾斜角を有
し、翼背側のガス出口側のシュラウド下側がせり出すよ
うな傾斜角を有し、翼腹側のガス入口側のシュラウド下
側がせり出すような傾斜角を有し、翼腹側のガス出口側
のシュラウド上側がせり出すような傾斜角を有し、翼腹
側のシュラウド接触面の傾斜角が変化する部分に溝を設
けたことを特徴とするシュラウド付きタービン動翼であ
る。
SUMMARY OF THE INVENTION The present invention has an inclination angle such that the upper side of the shroud on the gas inlet side behind the blade protrudes and the lower side of the shroud on the gas outlet side behind the blade. A shroud lower side on the gas inlet side on the blade vent side has an inclination angle protruding, and a shroud upper side on the gas outlet side on the blade vent side has an inclination angle protruding, and a shroud contact surface on the blade vent side. A grooved portion is provided at a portion where the inclination angle of the blade changes.

【0007】本発明におけるシュラウドの傾斜面は、回
転時の遠心力によって隣接するシュラウドの傾斜面と接
触する。ガス入口側のシュラウド接触面の傾斜面がガス
出口側のシュラウド接触面の傾斜面に変化する部分に溝
が設けられているため、シュラウドが互いに異なる位相
で振動すれば接触面に振動的相対変位が生じ、その間の
摩擦力により振動エネルギが熱エネルギに変換されて振
動が減衰される。
[0007] The inclined surface of the shroud in the present invention comes into contact with the inclined surface of the adjacent shroud due to centrifugal force during rotation. A groove is provided in the part where the inclined surface of the gas inlet side shroud contact surface changes to the inclined surface of the gas outlet side shroud contact surface. Is generated, and the vibrational energy is converted into heat energy by the frictional force during the time, so that the vibration is attenuated.

【0008】[0008]

【発明の実施の形態】本発明によるシュラウドは、翼背
側のガス入口側のシュラウド上側がせり出すような傾斜
角を有し、翼背側のガス出口側のシュラウド下側がせり
出すような傾斜角を有し、翼腹側のガス入口側のシュラ
ウド下側がせり出すような傾斜角を有し、翼腹側のガス
出口側のシュラウド上側がせり出すような傾斜角を有
し、翼腹側のシュラウド接触面の傾斜角が変化する部分
に溝を設けたことを特徴とするシュラウド付きタービン
動翼のダンパ構造である。
DESCRIPTION OF THE PREFERRED EMBODIMENTS The shroud according to the present invention has such an inclination angle that the upper side of the shroud on the gas inlet side behind the blade protrudes and the lower side of the shroud on the gas outlet side behind the blade. A shroud lower side on the gas inlet side on the blade vent side has an inclination angle protruding, and a shroud upper side on the gas outlet side on the blade vent side has an inclination angle protruding, and a shroud contact surface on the blade vent side. A groove is provided at a portion where the inclination angle of the turbine blade changes, which is a damper structure of a turbine rotor blade with a shroud.

【0009】以下、図面を用いて本発明の実施例を説明
する。図1はガスタービンの全体図であり、1が圧縮
機、21が燃焼器である。また20は軸であり、軸20
に車盤19が固定されている。車盤19の円周上にはタ
ービン動翼2が多数固定されている。図2はタービン動
翼1枚の傾斜図である。タービン動翼2はガスが流れる
部分であるブレード3と、車盤との固定部分であるダブ
テイル4、またそれらと一体成形されたシュラウド5か
らなる。シュラウド5は図3に示すように隣接するシュ
ラウドと接触している。
An embodiment of the present invention will be described below with reference to the drawings. FIG. 1 is an overall view of a gas turbine, where 1 is a compressor and 21 is a combustor. Reference numeral 20 denotes a shaft.
Is fixed to the vehicle body 19. A large number of turbine blades 2 are fixed on the circumference of the vehicle board 19. FIG. 2 is a perspective view of one turbine blade. The turbine blade 2 includes a blade 3 as a portion through which gas flows, a dovetail 4 as a fixed portion to a vehicle body, and a shroud 5 integrally formed therewith. The shroud 5 is in contact with an adjacent shroud as shown in FIG.

【0010】図4は本発明のシュラウド付きタービン動
翼全体の斜視図、図5は本発明のシュラウド付きタービ
ン動翼の平面図、図6は図5をガス入口側9からシュラ
ウドを見た接触面6の平面図、図7は図5はガス出口側
10からシュラウドを見た接触面7の平面図、図8は接
触面7の斜視図である。
FIG. 4 is a perspective view of the entire turbine blade with a shroud of the present invention, FIG. 5 is a plan view of the turbine blade with a shroud of the present invention, and FIG. 6 is a contact view of FIG. FIG. 7 is a plan view of the contact surface 7 when the shroud is viewed from the gas outlet side 10, and FIG. 7 is a perspective view of the contact surface 7.

【0011】図5において、背側のシュラウドと隣接す
る接触面6は接触面中心からガス入口側の部分がシュラ
ウド上側がせり出すようなある一定の傾斜角を有してお
り、接触面中心からガス出口側の部分はシュラウド下側
がせり出すようなある一定の傾斜角を有している。
In FIG. 5, the contact surface 6 adjacent to the back side shroud has a certain inclination angle such that the portion on the gas inlet side protrudes from the center of the contact surface to the upper side of the shroud. The outlet portion has a certain angle of inclination such that the underside of the shroud protrudes.

【0012】また、腹側のシュラウドと隣接する接触面
7は、接触面中心からガス入口側の部分がシュラウド下
側がせり出すようなある一定の傾斜角を有しており、接
触面中心よりガス出口側の部分はシュラウド上側がせり
出すようなある一定の傾斜角を有している。そして、接
触面7では傾斜角が変化する接触面中心部分に図6の長
さaと同じ深さの溝8を有している。
Further, the contact surface 7 adjacent to the shroud on the ventral side has a certain inclination angle such that the lower part of the shroud projects from the center of the contact surface toward the gas inlet, and the gas outlet from the center of the contact surface. The side portion has a certain angle of inclination such that the upper shroud protrudes. The contact surface 7 has a groove 8 having the same depth as the length a in FIG. 6 at the center of the contact surface where the inclination angle changes.

【0013】図9は本発明のシュラウド付きタービン動
翼2枚が接触している状態の接触面部分の平面図であ
る。運転時には遠心力のためシュラウドは車盤半径方向
にめくり上がるように変形する。この時、図9において
ガス入口側14のシュラウドのA部分,B部分を比べる
と、A部分の方が翼との固着部分からの距離が大きいた
め変形量は大きくなる。このときB部分がシュラウド上
側がせり出すような傾斜をしているため、A部分はB部
分に接触し、遠心力によるめくり上がりを抑制できる。
FIG. 9 is a plan view of a contact surface portion where two shrouded turbine blades of the present invention are in contact with each other. During operation, the shroud is deformed so as to turn up in the radial direction of the vehicle due to centrifugal force. At this time, comparing the portions A and B of the shroud on the gas inlet side 14 in FIG. 9, the amount of deformation is larger in the portion A because the distance from the portion fixed to the blade is larger. At this time, since the portion B is inclined so that the upper side of the shroud protrudes, the portion A comes into contact with the portion B, so that turning over due to centrifugal force can be suppressed.

【0014】同様にガス出口15側のシュラウドのA′
部分とB′部分を比べるとB′部分の方が翼との固着部
分方の距離が大きいため、変形量は大きくなる。このと
きA′部分のシュラウド上側がせり出すような傾斜角を
持っているためB′部分はA′部分と接触し、遠心力に
よるめくり上がりを抑制できる。
Similarly, A 'of the shroud on the gas outlet 15 side
When the portion is compared with the B 'portion, the B' portion has a larger distance between the portion fixed to the wing and the deformation amount is larger. At this time, since the upper part of the shroud of the portion A 'has such an inclination angle as to protrude, the portion B' comes into contact with the portion A ', and it is possible to suppress the turning over due to the centrifugal force.

【0015】更にシュラウド13の接触面に溝が設けら
れているため、シュラウド12,13が互いに異なる位
相で振動すれば接触面に振動的相対変位を生じることが
できる。このため振動エネルギが摩擦による熱エネルギ
に変換されて振動が減衰する。
Further, since a groove is provided on the contact surface of the shroud 13, if the shrouds 12, 13 vibrate in different phases, an oscillating relative displacement can be generated on the contact surface. For this reason, the vibration energy is converted into heat energy due to friction, and the vibration is attenuated.

【0016】[0016]

【発明の効果】本発明によるシュラウド付きタービンに
よれば、隣接するシュラウドとの確実な接触力及びめく
り上がりの抑制、また十分な振動減衰効果が期待でき
る。
According to the shroud-equipped turbine of the present invention, it is possible to expect a reliable contact force with the adjacent shroud, suppression of turning over, and a sufficient vibration damping effect.

【図面の簡単な説明】[Brief description of the drawings]

【図1】本発明の実施例であるガスタービンの全体を示
す図。
FIG. 1 is a diagram showing an entire gas turbine according to an embodiment of the present invention.

【図2】図1のタービン動翼の斜視図。FIG. 2 is a perspective view of the turbine blade shown in FIG. 1;

【図3】本発明の隣接する3枚のタービン動翼を示す斜
視図。
FIG. 3 is a perspective view showing three adjacent turbine blades of the present invention.

【図4】本発明のシュラウド付きタービン動翼の斜視
図。
FIG. 4 is a perspective view of a shrouded turbine blade of the present invention.

【図5】本発明のシュラウド付きタービン動翼の平面
図。
FIG. 5 is a plan view of a turbine blade with a shroud of the present invention.

【図6】図5をガス入口側9からシュラウドを見た接触
面6の平面図。
FIG. 6 is a plan view of the contact surface 6 when the shroud is viewed from the gas inlet side 9 in FIG.

【図7】図5をガス出口側10からシュラウドを見た接
触面7の平面図。
FIG. 7 is a plan view of the contact surface 7 when the shroud is viewed from the gas outlet side 10 in FIG.

【図8】接触面7の斜視図。FIG. 8 is a perspective view of a contact surface 7;

【図9】本発明のシュラウド付きタービン動翼2枚が接
触している状態の接触面部分の平面図。
FIG. 9 is a plan view of a contact surface portion where two shrouded turbine blades of the present invention are in contact with each other.

【図10】従来のシュラウド付きタービン動翼2枚の隣
接するシュラウドが接触した状態の平面図。
FIG. 10 is a plan view showing a state in which two adjacent shrouds of a conventional turbine blade with a shroud are in contact with each other.

【図11】従来のシュラウド付きタービン動翼2枚の隣
接するシュラウドが接触した状態の斜視図。
FIG. 11 is a perspective view showing a state in which two adjacent shrouds of a conventional turbine blade with a shroud are in contact with each other.

【符号の説明】[Explanation of symbols]

1…圧縮機、2…タービン動翼、3…ブレード、4…ダ
ブテイル、5,12,13,16,17…シュラウド、
6,7,18…接触面、8…溝、9,15…ガス入口
側、10,14…ガス出口側、19…車盤、20…軸、
21…燃焼器。
DESCRIPTION OF SYMBOLS 1 ... Compressor, 2 ... Turbine rotor blade, 3 ... Blade, 4 ... Dovetail, 5, 12, 13, 16, 17 ... Shroud,
6, 7, 18 ... contact surface, 8 ... groove, 9, 15 ... gas inlet side, 10, 14 ... gas outlet side, 19 ... car board, 20 ... shaft,
21: Combustor.

Claims (5)

【特許請求の範囲】[Claims] 【請求項1】ロータの車盤の周方向に配置されるシュラ
ウド付きタービン動翼において、隣接するシュラウドと
の接触面が、車盤の軸方向のガス入口側の部分ではある
一定の傾斜角を有し、車盤の軸方向のガス出口側の部分
では上の傾斜角とは異なる一定の傾斜角を有するシュラ
ウドであって、傾斜角が変化する接触面部分に溝を設け
たことを特徴とするタービン動翼。
In a turbine blade with a shroud arranged in a circumferential direction of a vehicle body of a rotor, a contact surface with an adjacent shroud has a certain inclination angle at a portion on a gas inlet side in an axial direction of the vehicle body. A shroud having a constant inclination angle different from the upper inclination angle at a portion on the gas outlet side in the axial direction of the vehicle body, wherein a groove is provided at a contact surface portion where the inclination angle changes. Turbine blade.
【請求項2】翼背側のガス入口側のシュラウド上側がせ
り出すような傾斜角を有し、翼背側のガス出口側のシュ
ラウド下側がせり出すような傾斜角を有し、翼腹側のガ
ス入口側のシュラウド下側がせり出すような傾斜角を有
し、翼腹側のガス出口側のシュラウド上側がせり出すよ
うな傾斜角を有し、シュラウド接触面の傾斜角が変化す
る部分に溝を設けたことを特徴とする請求項1記載のタ
ービン動翼。
The gas shroud on the gas inlet side on the back side of the blade has an inclination angle such that the lower side of the shroud on the gas outlet side on the back side of the blade protrudes. The inlet shroud lower side has an inclination angle that protrudes, the gas outlet side shroud upper side of the blade vent side has an inclination angle that protrudes, and a groove is provided in a portion where the inclination angle of the shroud contact surface changes. The turbine rotor blade according to claim 1, wherein:
【請求項3】翼腹側のシュラウド接触面の傾斜角が変化
する部分のみに溝を設けたことを特徴とする請求項2記
載のタービン動翼。
3. A turbine rotor blade according to claim 2, wherein a groove is provided only in a portion where the inclination angle of the shroud contact surface on the blade vent side changes.
【請求項4】翼背側のシュラウド接触面の傾斜角が変化
する部分のみに溝を設けたことを特徴とする請求項2記
載のタービン動翼。
4. A turbine blade according to claim 2, wherein a groove is provided only in a portion where the inclination angle of the shroud contact surface on the back side of the blade changes.
【請求項5】翼背側のシュラウド接触面の傾斜角が変化
する部分と、翼腹側のシュラウド接触面の傾斜角が変化
する部分に溝を設けたことを特徴とする請求項2記載の
タービン動翼。
5. A groove according to claim 2, wherein a groove is provided at a portion where the inclination angle of the shroud contact surface on the blade back side changes and at a portion where the inclination angle of the shroud contact surface on the blade vent side changes. Turbine blades.
JP31483197A 1997-11-17 1997-11-17 Moving blade of turbine Pending JPH11148305A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP31483197A JPH11148305A (en) 1997-11-17 1997-11-17 Moving blade of turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP31483197A JPH11148305A (en) 1997-11-17 1997-11-17 Moving blade of turbine

Publications (1)

Publication Number Publication Date
JPH11148305A true JPH11148305A (en) 1999-06-02

Family

ID=18058130

Family Applications (1)

Application Number Title Priority Date Filing Date
JP31483197A Pending JPH11148305A (en) 1997-11-17 1997-11-17 Moving blade of turbine

Country Status (1)

Country Link
JP (1) JPH11148305A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101120578B1 (en) * 2007-09-11 2012-03-09 가부시키가이샤 히타치세이사쿠쇼 Steam turbine moving blade assembly
CN102877892A (en) * 2012-10-23 2013-01-16 湖南航翔燃气轮机有限公司 Turbine rotor blade and gas turbine with same

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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US8591194B2 (en) 2007-09-11 2013-11-26 Hitachi, Ltd. Steam turbine rotor blade assembly
CN102877892A (en) * 2012-10-23 2013-01-16 湖南航翔燃气轮机有限公司 Turbine rotor blade and gas turbine with same
CN102877892B (en) * 2012-10-23 2015-02-11 湖南航翔燃气轮机有限公司 Turbine rotor blade and gas turbine with same

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