JPS6217306A - Rotary machine vane - Google Patents

Rotary machine vane

Info

Publication number
JPS6217306A
JPS6217306A JP15376385A JP15376385A JPS6217306A JP S6217306 A JPS6217306 A JP S6217306A JP 15376385 A JP15376385 A JP 15376385A JP 15376385 A JP15376385 A JP 15376385A JP S6217306 A JPS6217306 A JP S6217306A
Authority
JP
Japan
Prior art keywords
vane
blade
movable piece
rotary
groove
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
JP15376385A
Other languages
Japanese (ja)
Inventor
Shigeo Tanaka
重穂 田中
Yukio Suguro
幸男 勝呂
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 JP15376385A priority Critical patent/JPS6217306A/en
Publication of JPS6217306A publication Critical patent/JPS6217306A/en
Pending legal-status Critical Current

Links

Abstract

PURPOSE:To aim at the reduction of vibrational stress by loosely fitting a movable piece between the vane root part of a rotary vane and a rotary disc. CONSTITUTION:The vane root part 3 of a rotary vane 4 is planted on a rotary disc 12. A groove 6a, being directed outward at the radial direction, is formed on the rotary disc 12 between the vane root part 3 and the adjacent vane part 3. A movable piece 6 is loosely fitted to the groove 6a so as to prevent the disconnection thereof by a disconnection suppressing piece 21. Therefore, the movable piece 6a is slightly moved in the groove 6a and thereby the damping energy is generated between the vane root part and the rotary disk 12 so that it is possible to reduce vibrational stress generated on the vane.

Description

【発明の詳細な説明】 〔産業上の利用分野〕 本発明はタービン翼、コンプレッサ翼、プロア翼等の回
転機械翼の翼根部の改良に関する。
DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to improvement of the blade root portion of a rotary machine blade such as a turbine blade, a compressor blade, a prower blade, or the like.

〔従来の技術〕[Conventional technology]

第5図から第7図までは1回転機械翼の在来例を示す図
である。回転機械翼の翼根でサイドエントリタイプのも
のは、従来、第5図、第6図に示す形状をしている。
5 to 7 are diagrams showing conventional examples of single-rotation mechanical blades. Conventionally, side entry type blade roots of rotary machine blades have shapes shown in FIGS. 5 and 6.

第5図中の符号1は回転軸、2は回転軸1と一体もしく
は焼バメなどで結合された回転円板。
In FIG. 5, reference numeral 1 denotes a rotating shaft, and 2 denotes a rotating disk that is integrally connected to the rotating shaft 1 or connected by shrinkage fit.

3は回転機械翼の翼根部、4は回転機械翼の流体通路部
(翼プロフィル部又は翼有効部ともいう)である。
Reference numeral 3 indicates a blade root portion of the rotary machine blade, and 4 indicates a fluid passage portion (also referred to as a blade profile portion or blade effective portion) of the rotary machine blade.

翼根部3と回転円板2は第5図に示す様に。The blade root 3 and rotating disk 2 are as shown in FIG.

互にかみ合う凹凸部を利用して1回転円板2の外周凹部
に翼根部3を嵌挿する事で機械的に結合する。
The blade root portion 3 is inserted into the outer circumferential recess of the one-rotation disk 2 by using the interlocking uneven portions to mechanically connect the blade root portion 3.

この構造は、翼プロフィル部4が高速回転した場合2発
生する遠心力に耐え、かつ翼が流体力もしくは回転軸1
からの外力で振動させられた場合の振動にも耐えるよう
工夫された構造で。
This structure can withstand the centrifugal force that occurs when the blade profile section 4 rotates at high speed, and the blade can also be
The structure is designed to withstand vibrations caused by external force.

従来十分良好な実績を誇っている。It has had a good track record in the past.

但し、近年回転機械の出力増大は著しいものがある。こ
れに対応して1回転機械翼の振動応力が一般に増大して
来ており、特に翼の翼根部での振動応力を低減させる必
要に迫まられている。
However, in recent years, the output of rotating machines has increased significantly. Correspondingly, the vibration stress of single-rotation mechanical blades has generally increased, and there is an urgent need to reduce the vibration stress particularly at the blade root portion of the blade.

〔発明が解決しようとする問題点〕[Problem that the invention seeks to solve]

先に述べた様に1回転機械の出力が増大すると翼に作用
する流体力が増大し、それによる振動応力が増大するが
、その振動モードが例えば。
As mentioned earlier, when the output of a one-rotation machine increases, the fluid force acting on the blade increases, and the resulting vibration stress increases, but the vibration mode is, for example.

円板の円周方向曲げモードである場合は、第7因に図示
する第6図の■−■線矢視断面(点8a。
In the case of the bending mode in the circumferential direction of the disk, the cross section taken along the line ■-■ in FIG. 6 (point 8a) shown in the seventh factor.

3b、  3c、 3dで囲まれる断面)の断面定数z
、=a・b2/6が大きければ大きい程、翼の振動応力
が1成域可能である。
3b, 3c, 3d) section constant z
, =a·b2/6 is larger, the vibration stress of the blade can be in one region.

ところが従来の翼根部構造では断面係数2を大きくとる
ことが困難であった。又翼根部3と回転円板2との結合
部は、遠心力で強く結合するため、振動に際して構造減
衰が十分発生する程の相対すべりも発生しないので構造
減衰により振動応力を十分低減させる事は出来なかった
However, with the conventional blade root structure, it is difficult to increase the section modulus 2. In addition, since the connection between the blade root 3 and the rotating disk 2 is strongly connected by centrifugal force, there is no relative slip that would cause sufficient structural damping during vibration, so it is not possible to sufficiently reduce vibration stress by structural damping. I could not do it.

〔問題点を解決するための手段〕[Means for solving problems]

本発明は回転機械の回転円板に植設される翼の翼根部と
上記回転円板との間に可動片を緩嵌したことを特徴とす
る回転機械翼である。
The present invention is a rotary machine blade characterized in that a movable piece is loosely fitted between a blade root of a blade implanted in a rotary disk of the rotary machine and the rotary disk.

〔作用〕[Effect]

本発明は1回転機械翼の翼根部と上記回転円板との間に
溝を設は同溝内に可動片をゆるやかにはめたことによシ
1翼根部と回転円板及び可動片との接触個所が増え、各
接触面での摩擦と衝撃により構造減衰が従来のものより
大きくなる。
In the present invention, a groove is provided between the blade root of a one-rotation mechanical blade and the above-mentioned rotating disk, and a movable piece is loosely fitted into the groove. The number of contact points increases, and the friction and impact at each contact surface causes structural damping to be greater than in conventional models.

〔実施例〕〔Example〕

第1図から第2図は1本発明に係わる一実施例を示す図
である。
1 to 2 are diagrams showing an embodiment of the present invention.

本実施例が第5図から第7図に図示する従来例と異なる
点は1回転機械の回転円板12に植設される翼の隣り合
う翼根部3と翼根部3間の回転円板12に外半径方向に
溝6aを設けて、間溝6aに可動片6をゆるやかにはめ
たことである。
This embodiment differs from the conventional example shown in FIGS. 5 to 7 in that the rotating disk 12 between adjacent blade roots 3 of the blades installed in the rotating disk 12 of a one-rotation machine is A groove 6a is provided in the outer radial direction, and the movable piece 6 is loosely fitted into the groove 6a.

なお1図中の符号で従来例を示す第5図から第7図中の
符号と同一のものは、はぼ同様な構成であり説明を省略
する。
It should be noted that the same reference numerals in FIG. 1 as those in FIGS. 5 to 7, which indicate the conventional example, have almost the same structure, and the explanation thereof will be omitted.

本実施例では、可動片6が回転機械の運転中回転円板1
2から脱落しない様に、抜は止め21が軸心方向の溝6
a内両端に固定されている。これは可動片6を溝6aに
挿入後9回転円板12をコーキングする等の手段でも十
分である。
In this embodiment, the movable piece 6 is connected to the rotating disk 1 during operation of the rotating machine.
2, the retainer 21 is inserted into the groove 6 in the axial direction to prevent it from falling off.
It is fixed at both ends inside a. This can be accomplished by caulking the nine-turn disc 12 after inserting the movable piece 6 into the groove 6a.

この様な構造とする事で、可動片6は溝6aの中で微か
に動き、翼根部3と回転円板12の間で減衰エネルギを
発生し1回転機械翼の振動応力が低減する。
With this structure, the movable piece 6 moves slightly within the groove 6a, and damping energy is generated between the blade root 3 and the rotating disk 12, thereby reducing the vibration stress of the mechanical blade per rotation.

第3図及び第4図は本発明に係わる他実施例を示す図で
ある。本実施例が前記実施例と異なる点は1回転機械翼
の翼根部13を2つに分岐し、2隣り合う翼根部13と
翼根部13及び回転円板22との間に溝N縁膜けて可動
片16を緩嵌して、接触個所を増したことである。
FIGS. 3 and 4 are diagrams showing other embodiments of the present invention. This embodiment is different from the previous embodiments in that the blade root 13 of a single-rotation mechanical blade is branched into two, and a groove N edge membrane is provided between two adjacent blade roots 13 and the blade root 13 and rotating disk 22. The movable piece 16 is loosely fitted to increase the number of contact points.

なお9本実施例では可動片16が9回転機械の運転中回
転円板22から脱落しない様に、つめ状の抜は止め81
を翼根部18の軸方向側部に設けている。これは可動片
16を溝16a内に緩嵌後、翼根部18をコーキングす
る等の手段で−も十分である。本発明に係わる前記2つ
の実施例を用いた実験結果では、可動片無しの従来例に
較べて振動応力を1/2〜1/10に低減することがで
きた。
In addition, in this embodiment, a claw-shaped stopper 81 is provided to prevent the movable piece 16 from falling off the rotating disk 22 during operation of the rotating machine.
are provided on the axial side of the blade root portion 18. It is sufficient to do this by loosely fitting the movable piece 16 into the groove 16a and then caulking the blade root 18. Experimental results using the above two embodiments of the present invention showed that vibration stress could be reduced to 1/2 to 1/10 compared to the conventional example without a movable piece.

〔発明の効果〕〔Effect of the invention〕

回転機械の回転円板に植設される翼の翼根部と上記回転
円板との間に可動片をゆるやかにはめる事によって、相
隣る翼根部と可動片もしくは同可動片と回転円板との接
触面を増し減衰能増強が実現できる等9本発明は産業の
発達に寄与するところが大きい。
By loosely fitting a movable piece between the blade root of a blade installed on the rotating disk of a rotating machine and the rotating disk, it is possible to connect the adjacent blade root to the movable piece or the same movable piece to the rotating disk. The present invention greatly contributes to the development of industry, such as increasing the contact surface and increasing the damping capacity.

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

第1図から第2図は本発明に係わる一実施例を示す図で
、第1図は回転機械の要部組立状況を示す第2図のIr
I線矢視正面図、第2図は第1図の■−■矢視平面図で
ある。第3図及び第4図は本発明に係わる他実施例を示
す図で。 第3図は要部組立状況を示す第4図のl−11I線矢視
正面図を、第4図は第8図のIT−■矢視千   ′面
図を示している。 第5図から第7図は、2本発明に係わる従来例を示す図
で、第5図は要部組立正面図、第6図は翼の斜視図、第
7図は第6図の■−■線矢視断面図である。 1・・・回転軸、2,12.22・・・回転円板、3゜
13・・・回転機械翼の翼根部、6.16・・・可動片
。 6a、16a・・溝。
1 to 2 are diagrams showing one embodiment of the present invention, and FIG. 1 is a diagram showing an assembly state of main parts of a rotating machine.
FIG. 2 is a front view as viewed from the I-line arrow, and FIG. FIGS. 3 and 4 are diagrams showing other embodiments of the present invention. 3 is a front view taken along the line 1-11I in FIG. 4 showing the state of assembly of the main parts, and FIG. 5 to 7 are views showing conventional examples according to the present invention. FIG. 5 is a front view of main parts assembled, FIG. 6 is a perspective view of the wing, and FIG. ■It is a sectional view taken along the line. 1...Rotating shaft, 2,12.22...Rotating disk, 3°13...Blade root of rotary machine blade, 6.16...Movable piece. 6a, 16a...Groove.

Claims (1)

【特許請求の範囲】[Claims] 回転機械の回転円板に植設される翼の翼根部と上記回転
円板との間に可動片を緩嵌したことを特徴とする回転機
械翼。
1. A rotary machine blade, characterized in that a movable piece is loosely fitted between a blade root of a blade implanted in a rotary disk of the rotary machine and the rotary disk.
JP15376385A 1985-07-12 1985-07-12 Rotary machine vane Pending JPS6217306A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP15376385A JPS6217306A (en) 1985-07-12 1985-07-12 Rotary machine vane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP15376385A JPS6217306A (en) 1985-07-12 1985-07-12 Rotary machine vane

Publications (1)

Publication Number Publication Date
JPS6217306A true JPS6217306A (en) 1987-01-26

Family

ID=15569597

Family Applications (1)

Application Number Title Priority Date Filing Date
JP15376385A Pending JPS6217306A (en) 1985-07-12 1985-07-12 Rotary machine vane

Country Status (1)

Country Link
JP (1) JPS6217306A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5215432A (en) * 1991-07-11 1993-06-01 United Technologies Corporation Stator vane damper
US20100150723A1 (en) * 2006-06-19 2010-06-17 Henrikh Rojanskiy Rotor for a Compressor
JP2014105705A (en) * 2012-11-28 2014-06-09 General Electric Co <Ge> System for damping vibrations in turbine

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS4954704A (en) * 1972-09-27 1974-05-28
JPS5491605A (en) * 1977-12-28 1979-07-20 Gen Electric Moving blade damper with balance weight
JPS5546043A (en) * 1978-09-29 1980-03-31 Hitachi Ltd Vibration attenuator for turbine blade
JPS5736301B2 (en) * 1979-05-28 1982-08-03
JPS57143105A (en) * 1981-03-02 1982-09-04 Hitachi Ltd Vibration damping mechanism of vane in axial-flow rotary machine
JPS58150100A (en) * 1981-12-03 1983-09-06 ソシエテ・ナシオナル・デテユ−ド・エ・ドウ・コンストリユクシオン・ドウ・モト−ル・ダヴイアシオン“エス・エヌ・ウ・セ・エム・ア−” Vibration-proof device for blade of blower of turbine engine
JPS59229002A (en) * 1983-04-14 1984-12-22 ゼネラル・エレクトリツク・カンパニイ Rotary parts

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS4954704A (en) * 1972-09-27 1974-05-28
JPS5491605A (en) * 1977-12-28 1979-07-20 Gen Electric Moving blade damper with balance weight
JPS5546043A (en) * 1978-09-29 1980-03-31 Hitachi Ltd Vibration attenuator for turbine blade
JPS5736301B2 (en) * 1979-05-28 1982-08-03
JPS57143105A (en) * 1981-03-02 1982-09-04 Hitachi Ltd Vibration damping mechanism of vane in axial-flow rotary machine
JPS58150100A (en) * 1981-12-03 1983-09-06 ソシエテ・ナシオナル・デテユ−ド・エ・ドウ・コンストリユクシオン・ドウ・モト−ル・ダヴイアシオン“エス・エヌ・ウ・セ・エム・ア−” Vibration-proof device for blade of blower of turbine engine
JPS59229002A (en) * 1983-04-14 1984-12-22 ゼネラル・エレクトリツク・カンパニイ Rotary parts

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5215432A (en) * 1991-07-11 1993-06-01 United Technologies Corporation Stator vane damper
US20100150723A1 (en) * 2006-06-19 2010-06-17 Henrikh Rojanskiy Rotor for a Compressor
US8206122B2 (en) * 2006-06-19 2012-06-26 Ide Technologies Ltd. Rotor for a compressor
JP2014105705A (en) * 2012-11-28 2014-06-09 General Electric Co <Ge> System for damping vibrations in turbine

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