JPH1047004A - Rotor blade of rotary fluid machinery - Google Patents
Rotor blade of rotary fluid machineryInfo
- Publication number
- JPH1047004A JPH1047004A JP20026996A JP20026996A JPH1047004A JP H1047004 A JPH1047004 A JP H1047004A JP 20026996 A JP20026996 A JP 20026996A JP 20026996 A JP20026996 A JP 20026996A JP H1047004 A JPH1047004 A JP H1047004A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- hollow
- hollow groove
- vibration
- pin
- 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
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【0001】[0001]
【発明の属する技術分野】本発明は、コンプレッサ、ガ
スタービン、蒸気タービン等の回転流体機械の動翼に関
する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a moving blade of a rotary fluid machine such as a compressor, a gas turbine, and a steam turbine.
【0002】[0002]
【従来の技術】従来のコンプレッサ動翼は、図4に示す
ように、翼部1を立設している翼根2を図示しないロー
タの翼溝に挿入する構造を採用している。このために、
動翼の翼根部でのみ構造減衰(摩擦減衰)をかせぐこと
ができる。しかし、翼が振動した時に生じる翼根と翼溝
の相対すべりは非常に小さいため、大きな構造減衰は期
待できない。2. Description of the Related Art As shown in FIG. 4, a conventional compressor blade adopts a structure in which a blade root 2 on which a blade portion 1 is erected is inserted into a blade groove of a rotor (not shown). For this,
Structural damping (friction damping) can be obtained only at the blade root of the rotor blade. However, since the relative slip between the blade root and the blade groove generated when the blade vibrates is very small, large structural damping cannot be expected.
【0003】[0003]
【発明が解決しようとする課題】従来のコンプレッサ動
翼は、前記のように構造減衰が小さいため、起動昇速中
に通過するサージ領域では流れの乱れによって生じる加
振力によって大きな振動が発生する。この振動は、動翼
の破損の原因になることがある。Since the conventional compressor rotor blade has a small structural damping as described above, a large vibration is generated by the excitation force generated by the turbulence of the flow in the surge region passing during the start-up acceleration. . This vibration may cause the blade to break.
【0004】また定速回転機では、定格回転時に動翼が
共振すると大きな振動が発生し動翼が破損することがあ
る。In a constant-speed rotating machine, when the rotor blades resonate during rated rotation, large vibrations are generated and the rotor blades may be damaged.
【0005】本発明は、以上の問題点を解決することが
できるコンプレッサ等の回転流体機械の動翼を提供しよ
うとするものである。An object of the present invention is to provide a moving blade of a rotary fluid machine such as a compressor which can solve the above problems.
【0006】[0006]
【課題を解決するための手段】本発明の回転流体機械の
動翼は、翼内部に中空溝を設け、同中空溝の内部に同中
空溝と相対的なすべりが可能なダンパを挿入したことを
特徴とする。A rotor blade of a rotary fluid machine according to the present invention has a hollow groove provided inside the blade, and a damper capable of sliding relative to the hollow groove is inserted into the hollow groove. It is characterized by.
【0007】本発明では、動翼に振動が生じると、翼内
部に設けられた中空溝と同中空溝に挿入されたダンパと
の間で相対的なすべりが生じ、両者間の摩擦による減衰
作用によって振動の成長を抑制することができる。In the present invention, when vibration occurs in the rotor blade, relative slip occurs between the hollow groove provided inside the blade and the damper inserted in the hollow groove, and the damping action due to friction between the two. Thereby, the growth of vibration can be suppressed.
【0008】従来の回転流体の動翼では、ロータの回転
数に対する翼の振動振幅が図5中点線で示すようになっ
ているが、本発明では、ロータの回転数に対する翼の振
動振幅が図5中実線で示すようになり、本発明では振動
の成長の抑制が効果的に行なわれることが示されてい
る。In a conventional rotating fluid rotor blade, the vibration amplitude of the blade with respect to the rotation speed of the rotor is shown by a dotted line in FIG. 5, but in the present invention, the vibration amplitude of the blade with respect to the rotation speed of the rotor is plotted. 5, the solid line indicates that the present invention effectively suppresses the growth of vibration.
【0009】[0009]
【発明の実施の形態】コンプレッサの動翼に係る本発明
の実施の第1の形態を、図1によって説明する。翼根2
の下側から翼部1内を翼長(翼高)方向に延び互いに平
行をなす複数個の孔3をあけて翼内部に複数の中空溝を
設け、各中空溝の内部に、同中空溝と相対的なすべりが
可能な孔3とほぼ同一径のピン4(図1(c)参照)や
中空溝に接する複数の小径ピン5を挿入する。このよう
に、ピン4又は複数の小径ピン5を中空溝に挿入した
上、翼根2は図示しないロータの翼溝に挿入される。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A first embodiment of the present invention relating to a moving blade of a compressor will be described with reference to FIG. Wing root 2
A plurality of holes 3 extending in the wing length (wing height) direction from the lower side in the wing portion 1 are provided in the wing, and a plurality of hollow grooves are formed in the wing, and a plurality of hollow grooves are provided inside the wing. A pin 4 (see FIG. 1 (c)) having substantially the same diameter as the hole 3 capable of relative sliding and a plurality of small-diameter pins 5 in contact with the hollow groove are inserted. As described above, after the pin 4 or the plurality of small diameter pins 5 are inserted into the hollow groove, the blade root 2 is inserted into the blade groove of the rotor (not shown).
【0010】本実施の形態では、動翼に振動が生ずる
と、翼内部に設けられた複数の中空溝とピン4又は複数
の小径ピン5との間にすべりが生じてピン4又は複数の
小径ピン5はダンパと作用し、両者間の摩擦による減衰
作用によって動翼の振動の成長を効果的に抑制すること
ができる。In this embodiment, when vibration occurs in the moving blade, a slip occurs between the plurality of hollow grooves provided inside the blade and the pin 4 or the plurality of small-diameter pins 5, causing the pin 4 or the plurality of small-diameter pins to slip. The pin 5 works with a damper, and the growth of vibration of the rotor blade can be effectively suppressed by a damping action due to friction between the two.
【0011】コンプレッサの動翼に係る本発明の実施の
第2の形態を、図2によって説明する。本実施の形態で
は、翼根2の下側から翼部1内を翼長(翼高)方向に延
びる長矩形状の1個の孔6をあけて翼内部に1個の中空
溝を設け、同中空溝内部に、同中空溝と相対的なすべり
が可能な孔6とほぼ断面が同一な薄板状の積層板7を挿
入した。A second embodiment of the present invention relating to a moving blade of a compressor will be described with reference to FIG. In the present embodiment, one hollow groove 6 is provided inside the blade by making one long rectangular hole 6 extending in the blade length (blade height) direction from the lower side of the blade root 2 in the blade portion 1. Inside the hollow groove, a thin laminated plate 7 having substantially the same cross section as the hole 6 capable of sliding relative to the hollow groove was inserted.
【0012】本実施の形態においても、動翼に振動が生
ずると、翼内部に設けられた中空溝と積層板7との間に
すべりが生じて積層板7がダンパとして作用し、両者間
の摩擦による減衰作用によって動翼の振動の成長を効果
的に抑制することができる。Also in the present embodiment, when vibration occurs in the rotor blades, a slip occurs between the hollow groove provided inside the blade and the laminated plate 7, and the laminated plate 7 acts as a damper. The growth of vibration of the rotor blade can be effectively suppressed by the damping action due to friction.
【0013】本発明の実施の第3の形態を、図3によっ
て説明する。本実施の形態は、前記本発明の実施の第1
及び第2の形態におけるピン4又は積層板7の表面に、
それぞれローレット加工8,9を施したもので、ピン4
又は積層板7と翼内部に設けられた中空溝との間の相対
的すべりに当っての摩擦力を更に増加させることがで
き、これによって、動翼の振動の成長を確実に抑制する
ことができる。A third embodiment of the present invention will be described with reference to FIG. This embodiment is a first embodiment of the present invention.
And on the surface of the pin 4 or the laminate 7 in the second embodiment,
Knurled 8 and 9 respectively, pin 4
Alternatively, it is possible to further increase the frictional force applied to the relative slip between the laminated plate 7 and the hollow groove provided inside the blade, whereby it is possible to reliably suppress the growth of the vibration of the blade. it can.
【0014】[0014]
【発明の効果】本発明の回転流体機械の動翼では、翼内
部に中空溝を設け、同中空溝内部に同中空溝と相対的な
すべりが可能なダンパを挿入しているので、動翼の構造
減衰を大きくすることができる。これにより、動翼には
振動が発生しにくくなるため信頼性を向上させることが
できる。In the rotating blade of the rotary fluid machine of the present invention, a hollow groove is provided inside the blade and a damper capable of sliding relative to the hollow groove is inserted into the hollow groove. Can increase the structural damping. This makes it difficult for the rotor blades to generate vibration, thereby improving reliability.
【図1】本発明の実施の第1の形態を示し、図1(a)
はその全体の斜視図、図1(b)はその翼根の部分を示
す斜視図、図1(c)及び図1(d)はそれぞれ同実施
の形態に用いられるピンと複数の小径ピンの斜視図であ
る。FIG. 1 shows a first embodiment of the present invention, and FIG.
FIG. 1B is a perspective view showing the blade root portion, and FIGS. 1C and 1D are perspective views of a pin and a plurality of small diameter pins used in the embodiment. FIG.
【図2】本発明の実施の第2の形態を示し、図2(a)
はその全体の斜視図、図2(b)はその翼根の部分を示
す斜視図、図2(c)は同実施の形態に用いられる積層
板の斜視図である。FIG. 2 shows a second embodiment of the present invention, and FIG.
FIG. 2B is a perspective view showing the blade root portion, and FIG. 2C is a perspective view of a laminate used in the embodiment.
【図3】図3(a)及び図3(b)は、それぞれ本発明
の実施の第3の形態に用いられるピンと積層板の斜視図
である。FIGS. 3 (a) and 3 (b) are perspective views of a pin and a laminate used in a third embodiment of the present invention, respectively.
【図4】従来のコンプレッサ動翼の斜視図である。FIG. 4 is a perspective view of a conventional compressor blade.
【図5】本発明と従来のコンプレッサ動翼におけるロー
タの回転数と翼の振動振幅との関係を示すグラフであ
る。FIG. 5 is a graph showing the relationship between the rotational speed of the rotor and the vibration amplitude of the blade in the compressor rotor blade of the present invention and the conventional compressor rotor blade.
1 翼部 2 翼根 3 孔 4 ピン 5 小径ピン 6 孔 7 積層板 8,9 ローレット加工 DESCRIPTION OF SYMBOLS 1 Wing part 2 Wing root 3 hole 4 pin 5 Small diameter pin 6 hole 7 Laminated plate 8, 9 Knurling
Claims (1)
に同中空溝と相対的なすべりが可能なダンパを挿入した
ことを特徴とする回転流体機械の動翼。1. A rotating blade of a rotary fluid machine, wherein a hollow groove is provided inside a blade, and a damper capable of sliding relative to the hollow groove is inserted into the hollow groove.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP20026996A JPH1047004A (en) | 1996-07-30 | 1996-07-30 | Rotor blade of rotary fluid machinery |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP20026996A JPH1047004A (en) | 1996-07-30 | 1996-07-30 | Rotor blade of rotary fluid machinery |
Publications (1)
Publication Number | Publication Date |
---|---|
JPH1047004A true JPH1047004A (en) | 1998-02-17 |
Family
ID=16421527
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP20026996A Pending JPH1047004A (en) | 1996-07-30 | 1996-07-30 | Rotor blade of rotary fluid machinery |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPH1047004A (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2399866A (en) * | 2003-03-26 | 2004-09-29 | Rolls Royce Plc | A compressor blade |
GB2401407A (en) * | 2003-05-03 | 2004-11-10 | Rolls Royce Plc | a hollow component with internal vibration damping |
EP1538304A2 (en) * | 2003-12-02 | 2005-06-08 | ALSTOM Technology Ltd | Damping arrangement for a blade of an axial turbine |
JP2006052732A (en) * | 2004-08-09 | 2006-02-23 | General Electric Co <Ge> | Mixing synchronization hybrid blade and method related to it |
KR100701545B1 (en) | 2004-02-04 | 2007-03-30 | 유나이티드 테크놀로지스 코포레이션 | Cooled rotor blade with vibration damping device |
WO2010106047A1 (en) * | 2009-03-18 | 2010-09-23 | Technische Universitaet Wien | Support construction having increased structural dampening |
-
1996
- 1996-07-30 JP JP20026996A patent/JPH1047004A/en active Pending
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2399866A (en) * | 2003-03-26 | 2004-09-29 | Rolls Royce Plc | A compressor blade |
GB2399866B (en) * | 2003-03-26 | 2005-06-15 | Rolls Royce Plc | A fan blade |
US7118346B2 (en) | 2003-03-26 | 2006-10-10 | Rolls-Royce Plc | Compressor blade |
GB2401407A (en) * | 2003-05-03 | 2004-11-10 | Rolls Royce Plc | a hollow component with internal vibration damping |
EP1538304A2 (en) * | 2003-12-02 | 2005-06-08 | ALSTOM Technology Ltd | Damping arrangement for a blade of an axial turbine |
JP2005163789A (en) * | 2003-12-02 | 2005-06-23 | Alstom Technology Ltd | Vibration damping device for blade of axial-flow turbine |
EP1538304A3 (en) * | 2003-12-02 | 2012-07-04 | Alstom Technology Ltd | Damping arrangement for a blade of an axial turbine |
KR100701545B1 (en) | 2004-02-04 | 2007-03-30 | 유나이티드 테크놀로지스 코포레이션 | Cooled rotor blade with vibration damping device |
JP2006052732A (en) * | 2004-08-09 | 2006-02-23 | General Electric Co <Ge> | Mixing synchronization hybrid blade and method related to it |
WO2010106047A1 (en) * | 2009-03-18 | 2010-09-23 | Technische Universitaet Wien | Support construction having increased structural dampening |
US9062456B2 (en) | 2009-03-18 | 2015-06-23 | Vsl International Ag | Support construction having increased structural dampening |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
A02 | Decision of refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A02 Effective date: 20010116 |