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JPH09209703A - Integral shroud vane - Google Patents

Integral shroud vane

Info

Publication number
JPH09209703A
JPH09209703A JP1519096A JP1519096A JPH09209703A JP H09209703 A JPH09209703 A JP H09209703A JP 1519096 A JP1519096 A JP 1519096A JP 1519096 A JP1519096 A JP 1519096A JP H09209703 A JPH09209703 A JP H09209703A
Authority
JP
Japan
Prior art keywords
shroud
blade
integral shroud
integral
rotor
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
JP1519096A
Other languages
Japanese (ja)
Inventor
Koji Oyama
宏治 大山
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.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries 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 Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Priority to JP1519096A priority Critical patent/JPH09209703A/en
Publication of JPH09209703A publication Critical patent/JPH09209703A/en
Pending legal-status Critical Current

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  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

PROBLEM TO BE SOLVED: To increase the strength against vibration by increasing the restricting force of contact surface of an adjacent shroud. SOLUTION: The contact surface of a shroud 11 formed integrally with the blade end part of an integral shroud vane 10 with an adjacent shroud 11 is formed with a triangular protruded surface 12 and recessed surface 13. Also the apex angle θ1 of the protruded surface 12 is increased layer than the apex angle θ2 of the recessed surface 13, and the protruded surface 12 or recessed surface 13 is fitted closely to the recessed surface 13 or protruded surface 12 of the adjacent shroud 11 in assembling the integral shroud vane 11 into the outer periphery of a rotor. Then the assembly is raised. Thus the restricting force of the contact surface of the adjacent shroud 11 is increased, and the structure damping of the integral shroud 10 vane is increased so as to increase a strength against vibration.

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、若
しくはガスタービンの動翼に係り、特に、作動中の動翼
の翼端部の変形に伴う振動を抑制するシュラウドを、動
翼と一体に成形したインテグラルシュラウド翼に関す
る。
BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a moving blade of a steam turbine or a gas turbine, and more particularly to a shroud which suppresses vibration associated with deformation of a blade end of the moving blade, which is in operation, integrally with the moving blade. Formed integral shroud blade.

【0002】[0002]

【従来の技術】従来、動翼、特に、翼端部に設けるシュ
ラウドを一体に成形した、インテグラルシュラウド翼の
運転中に翼端部に生じる変位によって、発生する振動を
抑制するための方法、又は、構造について多くの提案が
なされている。
2. Description of the Related Art Conventionally, a method for suppressing vibrations generated by displacement of a blade tip during operation of an integral shroud blade, in which a moving blade, in particular, a shroud provided at the blade tip is integrally formed, Alternatively, many proposals have been made regarding the structure.

【0003】図3は、従来のインテグラルシュラウド翼
の一例を示す図である。図3(b)に示すように、シュ
ラウド2を翼端部に一体成形したインテグラルシュラウ
ド翼1は、同様に、翼根部に一体成形した翼取付部3
を、ロータ4の外周部に設けた取付部に、順次嵌合する
ことによって、図4(a)に示すように、ロータ4の全
周に取付けられる。この取付時において、ロータ4の外
周に隣接して取付けられるインテグラルシュラウド翼1
は、シュラウド2の接触面2aによって、隣接するイン
テグラルシュラウド翼1の翼端部が、互いに接触する様
にして、ロータ4の外周に組立てられる。
FIG. 3 is a diagram showing an example of a conventional integral shroud blade. As shown in FIG. 3 (b), the integral shroud blade 1 in which the shroud 2 is integrally formed on the blade tip portion has the blade mounting portion 3 integrally formed on the blade root portion.
Are sequentially fitted to the mounting portion provided on the outer peripheral portion of the rotor 4, so that they are mounted on the entire circumference of the rotor 4 as shown in FIG. At the time of this attachment, the integral shroud blade 1 attached adjacent to the outer periphery of the rotor 4
Is assembled on the outer circumference of the rotor 4 such that the contact surfaces 2a of the shroud 2 cause the blade tips of the adjacent integral shroud blades 1 to contact each other.

【0004】また、この接触面2aは、平面に形成され
ており、隣接するシュラウド2とは全面で、均等に接触
する様に製作されている。
Further, the contact surface 2a is formed into a flat surface, and is manufactured so as to make uniform contact with the adjacent shroud 2 over the entire surface.

【0005】一方、インテグラルシュラウド翼1では運
転中、すなわち、高速回転する翼端部に、遠心力により
変形が起こり、これに伴い振動が発生することがある
が、上述した、従来の形状のインテグラルシュラウド翼
1では、隣接させて設けたインテグラルシュラウド翼1
間では、平面で接触しているだけで、互いのシュラウド
2を連結しようという力が働かないため、振動抑制効果
が期待通り得られないことがあった。すなわち、運転中
インテグラルシュラウド翼1とロータ4の線膨張係数差
による伸び差、或は、工作上の加工精度を原因としたガ
タ、および高速回転による遠心力により、隣接するシュ
ラウド2の接触面が運転中に離れてしまう可能性があ
り、連結による振動抑制効果が働かず、発生する振動を
抑制できないという恐れがあった。
On the other hand, the integral shroud blade 1 may be deformed by centrifugal force during operation, that is, at the blade end portion rotating at high speed, and vibration may be generated due to the deformation. In the integral shroud blade 1, the integral shroud blades 1 provided adjacent to each other
In the meantime, the vibration suppressing effect may not be obtained as expected because the forces for connecting the shrouds 2 to each other do not work just because they are in contact with each other on a plane. That is, the contact surface between the adjacent shrouds 2 due to the difference in expansion due to the difference in the coefficient of linear expansion between the integral shroud blade 1 and the rotor 4 during operation, or the play due to the machining accuracy in machining and the centrifugal force due to the high speed rotation. There is a possibility that the vehicle may be separated during operation, the vibration suppressing effect due to the connection does not work, and there is a fear that the generated vibration cannot be suppressed.

【0006】[0006]

【発明が解決しようとする課題】本発明は、このよう
な、従来のインテグラルシュラウド翼に生じる不具合を
解消するためになされたもので、運転中に於いても、互
いに拘束力(反力)を有するような接触面にし、運転
中、遠心力によりインテグラルシュラウド翼の翼先端が
径方外側に変移しようとしても、互いの接触面による連
結の効果が喪失しないようにして、振動強度を向上させ
るようにした、インテグラルシュラウド翼を提供するこ
とを課題とする。
SUMMARY OF THE INVENTION The present invention has been made in order to solve such a problem that occurs in the conventional integral shroud blade, and the binding force (reaction force) is exerted on each other even during operation. Even if the tip of the integral shroud blade moves outward in the radial direction due to centrifugal force during operation, the effect of the connection by the mutual contact surfaces is not lost and the vibration strength is improved. It is an object to provide an integral shroud wing adapted to the above.

【0007】[0007]

【課題を解決するための手段】このため、本発明のイン
テグラルシュラウド翼は、次の手段とした。ロータ外周
に隣接して植設される動翼の外周端に、それぞれ固着さ
れるシュラウドの接触面に、三角形状の凹凸面を設ける
とともに、凸面の頂角を凹面の頂角より大きくして、ロ
ータ外周へのインテグラルシュラウド翼の組立時、凸面
を凹面に嵌入して組立て、この接触面で、隣接するシュ
ラウドを連結して、変位に対する拘束力(反力)をもた
せるようにした。なお、接触面に設ける凹凸面は、少く
とも、インテグラルシュラウド翼の径方向から見て三角
形状にする必要があるが、外周方向から見ても三角形状
になるようにしても良いものである。
Therefore, the integral shroud blade of the present invention has the following means. At the outer peripheral end of the rotor blade that is planted adjacent to the rotor outer periphery, the contact surface of the shroud fixed to each is provided with a triangular uneven surface, the apex angle of the convex surface is made larger than the apex angle of the concave surface, At the time of assembling the integral shroud blade on the outer circumference of the rotor, the convex surface was fitted into the concave surface for assembly, and adjacent shrouds were connected at this contact surface so as to have a restraining force (reaction force) against displacement. The uneven surface provided on the contact surface needs to be at least triangular when viewed from the radial direction of the integral shroud blade, but may also be triangular when viewed from the outer peripheral direction. .

【0008】本発明のインテグラルシュラウド翼によれ
ば、上述の手段により、ロータ外周へのインテグラルシ
ュラウド翼の組み立て時に与えられた、隣接するシュラ
ウド接触面における拘束力(或は反力)は、運転中の熱
変形、組み立て時のガタに対しても有効に作用し、この
構造ダンピングの増加により、インテグラルシュラウド
翼の振動強度が向上する。
According to the integral shroud blade of the present invention, the restraining force (or reaction force) at the adjacent shroud contact surfaces, which is given at the time of assembling the integral shroud blade to the outer circumference of the rotor by the above-mentioned means, is It effectively acts against thermal deformation during operation and play during assembly, and the increase in structural damping improves the vibration strength of the integral shroud blade.

【0009】[0009]

【発明の実施の形態】以下、本発明のインテグラルシュ
ラウド翼の実施の一形態を、図面にもとづき説明する。
図1は、本発明のインテグラルシュラウド翼の実施の第
1形態を示す図で、図1(a)は全体斜視図、図1
(b)は図1(a)に示すA部の拡大断面図、図1
(c)は図1(a)に示すB部の拡大断面図、図2は図
1に示すシュラウドの部分断面図である。なお、これら
の図において、図3に示す従来のインテグラルシュラウ
ド翼と同一の部分には、同一の符号を付して、重複する
説明は省略する。
BEST MODE FOR CARRYING OUT THE INVENTION An embodiment of the integral shroud blade of the present invention will be described below with reference to the drawings.
FIG. 1 is a diagram showing a first embodiment of an integral shroud blade of the present invention, FIG. 1 (a) is an overall perspective view, and FIG.
1B is an enlarged cross-sectional view of the portion A shown in FIG.
1C is an enlarged cross-sectional view of the B portion shown in FIG. 1A, and FIG. 2 is a partial cross-sectional view of the shroud shown in FIG. In these figures, the same parts as those of the conventional integral shroud blade shown in FIG. 3 are designated by the same reference numerals, and a duplicate description will be omitted.

【0010】図に示すように、本実施の形態のインテグ
ラルシュラウド翼10によれば、インテグラルシュラウ
ド翼10の翼端部に、インテグラルシュラウド翼10の
径方向に三角形状の凸面12、および凹面13を、それ
ぞれ両端に形成したシュラウド11を一体に成形してい
る。この凸面12の頂角θ1 と、凹面13の頂角θ2
は、後述する嵌合時の拘束力の発生、及び組立て時の作
業性上適当と思われる、1°≦θ1 −θ2 <5°degの
差が設けられている。
As shown in the figure, according to the integral shroud blade 10 of the present embodiment, a triangular convex surface 12 in the radial direction of the integral shroud blade 10 is formed at the blade end portion of the integral shroud blade 10. The concave surface 13 is integrally formed with the shroud 11 formed at both ends. The apex angle theta 1 of the convex surface 12, the apex angle theta 2 of the concave 13, generation of the restraining force at the time of fitting to be described later, and appears to the workability during assembly suitable, 1 ° ≦ θ 1 -θ There is a difference of 2 <5 ° deg.

【0011】また、図3に示すように、シュラウド11
の周方向の長さlは、円弧上の長さP(=2πr/N)
に対して、α(α=0.3〜1.0mm)だけ長くしてい
る。さらに、凹面13に設けられる三角形状の頂点に
は、組立て時の応力集中を軽減するための軽減孔14が
設けられている。
Further, as shown in FIG. 3, the shroud 11
The length l in the circumferential direction is the length P on the arc (= 2πr / N)
On the other hand, the length is increased by α (α = 0.3 to 1.0 mm). Further, a relief hole 14 for reducing stress concentration during assembly is provided at the triangular vertex provided on the concave surface 13.

【0012】このような三角形状の凸面12、および凹
面13を両端に設けた、シュラウド11を翼端部に一体
成形したインテグラルシュラウド翼10を、ロータ4外
周に組み立てる時には、凸面12、又は凹面13を隣接
するインテグラルシュラウド翼10のシュラウド11に
設けた凹面13、又は凸面12に嵌入させて組立てる。
このシュラウド11の接触面に設けた、凸面12と凹面
13の嵌合によって、隣接するシュラウド11間には、
拘束力が働き、ロータ4外周に組立てられたインテグラ
ルシュラウド翼の構造ダンピングを増大させ、振動強度
を向上させることができる。
When the integral shroud blade 10 having the triangular convex surface 12 and the concave surface 13 provided at both ends and the shroud 11 integrally formed at the blade end is assembled on the outer circumference of the rotor 4, the convex surface 12 or the concave surface is formed. 13 is fitted into the concave surface 13 or the convex surface 12 provided on the shroud 11 of the adjacent integral shroud blade 10 to assemble.
By fitting the convex surface 12 and the concave surface 13 provided on the contact surface of the shroud 11, between the adjacent shrouds 11,
The restraint force acts, and the structural damping of the integral shroud blade assembled on the outer periphery of the rotor 4 can be increased, and the vibration strength can be improved.

【0013】このように、本実施の形態のインテグラル
シュラウド翼10では、隣接して配設されるインテグラ
ルシュラウド翼10の、シュラウド11の接触面に凹面
13、凸面12をつけ、組み立て時に、この部分が互に
はまり込むようにして、尚かつ、この部分で拘束力(或
は反力)をもたせるようにしたことにより、この拘束力
(或は反力)は、運転中インテグラルシュラウド翼10
の熱変形、組み立て時のガタに対しても、有効に作用
し、この構造ダンピングの増加により、インテグラルシ
ュラウド翼の振動強度を向上させることができる。
As described above, in the integral shroud blade 10 of the present embodiment, the concave surface 13 and the convex surface 12 are provided on the contact surface of the shroud 11 of the integral shroud blades 10 arranged adjacent to each other, and at the time of assembly, Since these portions are fitted into each other and a restraining force (or reaction force) is exerted at this portion, the restraining force (or reaction force) is reduced by the integral shroud blade 10 during operation.
Also, it effectively acts on the heat deformation and the backlash at the time of assembly, and the vibration strength of the integral shroud blade can be improved by the increase of the structural damping.

【0014】[0014]

【発明の効果】以上述べたように、本発明のインテグラ
ルシュラウド翼によれば、インテグラルシュラウド翼の
組み立て時に、隣接シュラウド接触面に設けた三角形状
の凹凸面で、互いに拘束力(反力)を与えることがで
き、その結果、運転中に熱変形、または、組み立て時に
ガタにより、隣接するシュラウドが互いに離れることが
なく、構造ダンピングを有効に作用させ、インテグラル
シュラウド翼の振動強度を向上させることができる。
As described above, according to the integral shroud blade of the present invention, at the time of assembling the integral shroud blade, the concavo-convex surfaces of the triangular shape provided on the contact surfaces of the adjacent shrouds mutually restrain the forces (reaction force). ) Is provided, and as a result, adjacent shrouds do not separate from each other due to thermal deformation during operation or rattling during assembly, structural damping effectively acts, and vibration strength of integral shroud blades is improved. Can be made.

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

【図1】本発明のインテグラルシュラウド翼の実施の第
1形態を示す図で、図1(a)は斜視図、図1(b)は
図1(a)に示すA部拡大断面図、図1(c)は図1
(a)に示すB部拡大断面図、
FIG. 1 is a view showing a first embodiment of an integral shroud blade of the present invention, FIG. 1 (a) is a perspective view, FIG. 1 (b) is an enlarged sectional view of a portion A shown in FIG. 1 (a), 1 (c) is shown in FIG.
An enlarged cross-sectional view of a B portion shown in (a),

【図2】図1に示すシュラウドの円弧上の長さと、周方
向長さを説明するための部分断面図、
FIG. 2 is a partial cross-sectional view for explaining the arcuate length and the circumferential length of the shroud shown in FIG.

【図3】従来のインテグラルシュラウド翼を示す図で、
図3(a)は全体斜視図、図3(b)は図3(a)に示
すインテグラルシュラウド翼単体を示す斜視図である。
FIG. 3 is a diagram showing a conventional integral shroud blade,
3A is an overall perspective view, and FIG. 3B is a perspective view showing the integral shroud blade alone shown in FIG. 3A.

【符号の説明】[Explanation of symbols]

1,10 インテグラルシュラウド翼 2,11 シュラウド 2a 平滑接触面 3 インテグラルシュラウド翼取付部 4 ロータ 12 シュラウド凸面 13 シュラウド凹面 14 応力軽減穴 l シュラウド周方向長さ θ1 シュラウド凸面頂角 θ2 シュラウド凹面頂角1,10 Integral shroud blade 2,11 Shroud 2a Smooth contact surface 3 Integral shroud blade mounting part 4 Rotor 12 Shroud convex surface 13 Shroud concave surface 14 Stress reduction hole l Shroud circumferential length θ 1 Shroud convex surface angle θ 2 Shroud concave surface Apex angle

Claims (1)

【特許請求の範囲】[Claims] 【請求項1】 ロータの外周に植設された動翼の外周端
に固着され、前記動翼の変位を規制するシュラウドが、
前記動翼と一体に形成されたインテグラルシュラウド翼
において、前記シュラウドに隣接して配設される前記シ
ュラウドとの接触面が、三角形状の凸面と、前記凸面の
頂角より小さい頂角にされ、前記凸面と嵌合する三角形
状の凹面とで形成されていることを特徴とするインテグ
ラルシュラウド翼。
1. A shroud fixed to the outer peripheral end of a rotor blade planted on the outer periphery of a rotor, for controlling displacement of the rotor blade,
In the integral shroud blade integrally formed with the moving blade, a contact surface with the shroud disposed adjacent to the shroud has a triangular convex surface and an apex angle smaller than the apex angle of the convex surface. An integral shroud blade, characterized in that the integral shroud blade is formed by the convex surface and a triangular concave surface that fits.
JP1519096A 1996-01-31 1996-01-31 Integral shroud vane Pending JPH09209703A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP1519096A JPH09209703A (en) 1996-01-31 1996-01-31 Integral shroud vane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP1519096A JPH09209703A (en) 1996-01-31 1996-01-31 Integral shroud vane

Publications (1)

Publication Number Publication Date
JPH09209703A true JPH09209703A (en) 1997-08-12

Family

ID=11881938

Family Applications (1)

Application Number Title Priority Date Filing Date
JP1519096A Pending JPH09209703A (en) 1996-01-31 1996-01-31 Integral shroud vane

Country Status (1)

Country Link
JP (1) JPH09209703A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102330572A (en) * 2010-07-12 2012-01-25 曼柴油机和涡轮机欧洲股份公司 Rotor of a turbomachine
JP2013505385A (en) * 2009-09-18 2013-02-14 マン・ディーゼル・アンド・ターボ・エスイー Turbomachine rotor

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2013505385A (en) * 2009-09-18 2013-02-14 マン・ディーゼル・アンド・ターボ・エスイー Turbomachine rotor
CN102330572A (en) * 2010-07-12 2012-01-25 曼柴油机和涡轮机欧洲股份公司 Rotor of a turbomachine
JP2012021529A (en) * 2010-07-12 2012-02-02 Man Diesel & Turbo Se Rotor of turbomachine
US8974186B2 (en) 2010-07-12 2015-03-10 Man Diesel & Turbo Se Coupling element segments for a rotor of a turbomachine
EP2410131A3 (en) * 2010-07-12 2017-08-02 MAN Diesel & Turbo SE Rotor of a turbomachine

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