JPH04127804U - Vibration damping device for rotor blades - Google Patents
Vibration damping device for rotor bladesInfo
- Publication number
- JPH04127804U JPH04127804U JP3255091U JP3255091U JPH04127804U JP H04127804 U JPH04127804 U JP H04127804U JP 3255091 U JP3255091 U JP 3255091U JP 3255091 U JP3255091 U JP 3255091U JP H04127804 U JPH04127804 U JP H04127804U
- Authority
- JP
- Japan
- Prior art keywords
- rotor blade
- tip
- vibration
- damping device
- vibration damping
- 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.)
- Withdrawn
Links
- 238000013016 damping Methods 0.000 title claims description 10
- 239000012530 fluid Substances 0.000 claims abstract description 7
- 238000010586 diagram Methods 0.000 description 8
- 230000000694 effects Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 230000036651 mood Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Landscapes
- Control Of Turbines (AREA)
Abstract
(57)【要約】
【目的】 動翼の振動を消滅させることを目的とする。
【構成】 センサが動翼先端近傍のディフューザ壁に取
付けられディフューザ壁圧の変動を計測して信号を出力
しこの信号に基づいてコントローラが動翼先端に向けて
流体を注入するように構成する。
(57) [Summary] [Purpose] The purpose is to eliminate the vibration of moving blades. [Structure] A sensor is attached to the diffuser wall near the tip of the rotor blade, measures fluctuations in diffuser wall pressure and outputs a signal, and based on this signal, the controller injects fluid toward the tip of the rotor blade.
Description
【０００１】0001
本考案は、蒸気タービン、ガスタービン、コンプレッサなどの動翼に適用され る動翼の制振装置に関する。 This invention is applied to moving blades of steam turbines, gas turbines, compressors, etc. This invention relates to a vibration damping device for rotor blades.
【０００２】0002
図４は従来の蒸気タービンにおける動翼の構造説明図、図５はその作用説明図 である。図４において、蒸気タービンにおける最終段の動翼１付近の流れは、定 格負荷時にはきれいな流線形をしているが、蒸気量が定格流量の１／４以下の部 分負荷時には非常に複雑な流れとなり、動翼１の根元や先端付近では逆流を生じ ることがある。 Figure 4 is an explanatory diagram of the structure of rotor blades in a conventional steam turbine, and Figure 5 is an explanatory diagram of its operation. It is. In Fig. 4, the flow near the rotor blade 1 in the final stage of the steam turbine is constant. It has a beautiful streamlined shape at rated load, but when the steam volume is less than 1/4 of the rated flow rate. When loaded, the flow becomes very complicated, and reverse flow occurs near the root and tip of rotor blade 1. Sometimes.
【０００３】0003
上記のように、従来の蒸気タービンにおける最終段の動翼１付近の流れは部分 負荷時には非常に複雑な流れとなり、動翼１の先端に逆流や強い半径流を生じる と図５に示すように動翼１への絶対流入速度Ｃが小さくなって相対流入角度βが 大きくなり、流れが剥離し易くなる。なお、２は静翼、Ｕは周速、Ｗは相対流入 速度である。流れが剥離すると動翼１は所謂失速状態となり、剥離渦が発生する ために大きな振動が発生する。特に、動翼１の全周がリング状のワイヤ７により 連結されている構造では、部分負荷時に失速状態となると動翼１とディスクとの 連成振動モード、即ちディスクの周方向に数本の節直径を持つ円板モードの大振 動が発生することがある。 As mentioned above, in a conventional steam turbine, the flow near rotor blade 1 in the final stage is partially When loaded, the flow becomes very complex, producing reverse flow and strong radial flow at the tip of rotor blade 1. As shown in Fig. 5, the absolute inflow velocity C to the moving blade 1 becomes smaller and the relative inflow angle β becomes It becomes larger and the flow becomes easier to separate. In addition, 2 is the stationary blade, U is the circumferential speed, and W is the relative inflow. It's speed. When the flow separates, the rotor blade 1 enters a so-called stall state, and a separation vortex is generated. This causes large vibrations. In particular, the entire circumference of the rotor blade 1 is made of ring-shaped wire 7. In a connected structure, if a stall condition occurs under partial load, the rotor blade 1 and the disk will be separated. Coupled vibration mode, that is, large vibration of disk mode with several nodal diameters in the circumferential direction of the disk. Movement may occur.
【０００４】0004
本考案に係る動翼の制振装置は上記課題の解決を目的にしており、動翼先端近 傍のディフューザ壁に取付けられディフューザ壁圧の変動を計測して信号を出力 するセンサと、該センサが出力する信号に基づいて上記動翼先端に向けて流体を 注入するコントローラとを備えた構成を特徴とする。 The rotor blade vibration damping device according to the present invention aims to solve the above problems, and Attached to the diffuser wall next to it, it measures changes in diffuser wall pressure and outputs a signal. and a sensor that directs fluid toward the tip of the rotor blade based on the signal output by the sensor. and a controller for injection.
【０００５】[0005]
即ち、本考案に係る動翼の制振装置においては、センサが動翼先端近傍のディ フューザ壁に取付けられディフューザ壁圧の変動を計測して信号を出力しこの信 号に基づいてコントローラが動翼先端に向けて流体を注入するようになっており 、センサにより計測されたディフューザ壁圧の変動レベルと動翼における振動の 振幅とは比例関係にあり、動翼が危険な振幅で振動しているか否かをコントロー ラがディフューザ壁圧の変動レベルから判定し、動翼が危険な振幅で振動してい る場合には動翼先端に向けて流体を注入するので、動翼先端部の流れが動翼にス ムーズに沿うようになる。 That is, in the rotor blade vibration damping device according to the present invention, the sensor detects vibrations near the tip of the rotor blade. It is attached to the diffuser wall and measures fluctuations in diffuser wall pressure and outputs a signal. Based on this issue, the controller injects fluid toward the tip of the rotor blade. , the fluctuation level of the diffuser wall pressure measured by the sensor and the vibration of the rotor blade. There is a proportional relationship with the amplitude, and it controls whether the rotor blade is vibrating at a dangerous amplitude. The controller determines from the level of fluctuations in the diffuser wall pressure that the rotor blades are vibrating at dangerous amplitudes. When the fluid is injected toward the tip of the rotor blade, the flow at the tip of the rotor blade is applied to the rotor blade. Become in line with the mood.
【０００６】[0006]
図１は本考案の一実施例に係る動翼の制振装置の構造説明図、図２および図３ は作用説明図である。図において、本実施例に係る動翼の制振装置は蒸気タービ ンの動翼の制振に使用されており、図１に示すように最終段の動翼１先端近傍の 出口側ディフューザ８に壁圧の変動を計測するセンサ３が取付けられ、また図示 しない回転計によりロータの回転数が計測されるようになっている。コントロー ラ９は蒸気５注入用のバルブ４の操作信号を出力する。壁圧の信号と回転数の信 号とはコントローラ９に送られ、コントローラ９により動翼１に円板モードの振 動が発生しているか、動翼１における振動の振幅が危険なレベルか否かが後述す る図２の関係に基づいて判定される。コントローラ９により円板モードの危険な レベルの振動が発生していると判定された場合にはコントローラ９からバルブ４ に操作信号が送られ、動翼１先端近傍の入口側流路の周方向数か所に設けられて いる配管５から動翼１先端に向けて蒸気５が注入されるようになっている。動翼 １の全周はリング状のワイヤ７により連結されている。 FIG. 1 is a structural explanatory diagram of a rotor blade vibration damping device according to an embodiment of the present invention, FIGS. 2 and 3 is an action explanatory diagram. In the figure, the rotor blade vibration damping device according to this embodiment is installed on a steam turbine. It is used for damping the vibration of rotor blades in the final stage near the tip of rotor blade 1 in the final stage, as shown in Figure 1. A sensor 3 for measuring wall pressure fluctuations is attached to the outlet diffuser 8, and The number of rotations of the rotor is measured by a tachometer. control The controller 9 outputs an operation signal for the valve 4 for injecting the steam 5. Wall pressure signal and rotation speed signal The signal is sent to the controller 9, which causes the rotor blade 1 to vibrate in a disk mode. Whether vibration is occurring and whether the amplitude of vibration in rotor blade 1 is at a dangerous level will be discussed later. The determination is made based on the relationship shown in FIG. Controller 9 controls the dangerous mode of disc mode. If it is determined that the level of vibration is occurring, the controller 9 sends the valve 4 An operation signal is sent to the rotor blade 1, which is installed at several locations in the circumferential direction of the inlet side flow path near the tip of rotor blade 1. Steam 5 is injected toward the tip of the rotor blade 1 from a pipe 5 located therein. moving blade The entire circumference of 1 is connected by a ring-shaped wire 7.
【０００７】 部分負荷時に最終段の動翼１に円板モードの振動が発生すると、図２（ａ）， （ｂ）に示すようにセンサ３により壁圧が変動する２種類の周波数ω1 ，ω2 が 計測される。ここで、ω1 ，ω2 ＝｜ωB ±ｎΩ｜で、ωB は発生した円板モー ドの振動数、ｎは円板モードの節直径数、Ωはロータの回転数である。振動数ω B と節直径数ｎとの関係は既知であり、回転数Ωと壁圧が変動する周波数ω1 ， ω2 とが計測されれば、動翼１に円板モードの振動が発生しているかどうかが判 定される。また、計測される壁圧の変動レベルと動翼１の振幅とは図２（ｃ）に 示すように比例関係にあるから、動翼１が危険な振幅で振動しているかどうかも 壁圧の変動レベルから判定される。危険な円板モードの振動が発生している場合 には動翼１先端近傍の入口側流路に設けられている配管６から動翼１先端に向け て蒸気５が注入される。動翼１の振幅は先端部で最大で流体から最もエネルギを 受け易いので、動翼１先端近傍の失速をなくせば動翼１に発生している円板モー ドの振動を消滅させることができる。即ち、動翼１に危険な円板モードの振動が 発生している場合に配管６から動翼１先端に向けて蒸気５が注入されると、図３ （ｂ）に示すように動翼１先端部で絶対流入速度Ｃが増えるので、相対流入角度 βが小さくなって図３（ａ）に示す定格負荷時と同様に動翼１先端部の流れが動 翼１にスムーズに沿うようになり、円板モードの振動が消滅する。なお、２は静 翼、Ｕは周速、Ｗは相対流入速度である。また、本装置は蒸気タービンの他、ガ スタービン、コンプレッサなどにも適用が可能で、これらの場合には蒸気５に代 えて取扱う気体を動翼先端に向けて注入する。[0007] When disk mode vibration occurs in the final stage rotor blade 1 during partial load, Fig. 2(a), As shown in (b), there are two types of frequencies ω at which the wall pressure varies depending on the sensor 3.1,ω2but be measured. Here, ω1,ω2=｜ωB±nΩ｜and ωBis the generated disk motion. n is the nodal diameter number of the disk mode, and Ω is the rotation speed of the rotor. frequency ω B The relationship between and the nodal diameter number n is known, and the rotation speed Ω and the frequency at which the wall pressure fluctuates ω1， ω2If this is measured, it can be determined whether disc mode vibration is occurring in the rotor blade 1. determined. In addition, the measured wall pressure fluctuation level and the amplitude of the rotor blade 1 are shown in Figure 2(c). Since there is a proportional relationship as shown, it is also possible to determine whether rotor blade 1 is vibrating at a dangerous amplitude. Determined from the level of wall pressure fluctuation. If dangerous disk mode vibration is occurring From the pipe 6 installed in the inlet side flow path near the tip of the rotor blade 1 to the tip of the rotor blade 1. Steam 5 is injected. The amplitude of rotor blade 1 is maximum at the tip, where it absorbs the most energy from the fluid. Therefore, if the stall near the tip of rotor blade 1 is eliminated, the disc motor generated in rotor blade 1 can be eliminated. It is possible to eliminate the vibration of the de. In other words, dangerous disc mode vibrations occur in the rotor blade 1. If steam 5 is injected from piping 6 toward the tip of rotor blade 1 when steam is generated, As shown in (b), the absolute inflow velocity C increases at the tip of rotor blade 1, so the relative inflow angle As β becomes smaller, the flow at the tip of rotor blade 1 becomes dynamic, similar to that at the rated load shown in Fig. 3(a). It now follows the blade 1 smoothly, and the disk mode vibration disappears. In addition, 2 is static In the blade, U is the circumferential speed and W is the relative inflow velocity. In addition to steam turbines, this device also It can also be applied to turbines, compressors, etc., and in these cases, it can be used instead of steam 5. Then, the gas to be handled is injected toward the tip of the rotor blade.
【０００８】[0008]
本考案に係る動翼の制振装置は前記のように構成されており、動翼が危険な振 幅で振動している場合にはコントローラが動翼先端に向けて流体を注入するので 、動翼先端部の流れが動翼にスムーズに沿うようになり動翼の振動が消滅する。 The rotor blade vibration damping device according to the present invention is configured as described above, and the rotor blade is subjected to dangerous vibrations. If the blade is vibrating in width, the controller injects fluid toward the tip of the rotor blade. , the flow at the tip of the rotor blade smoothly follows the rotor blade, and the vibration of the rotor blade disappears.
【図１】図１は本考案の一実施例に係る蒸気タービンに
おける動翼の制振装置の模式図である。FIG. 1 is a schematic diagram of a vibration damping device for rotor blades in a steam turbine according to an embodiment of the present invention.
【図２】図２はその作用説明図である。FIG. 2 is an explanatory diagram of its operation.
【図３】図３もその作用説明図である。FIG. 3 is also an explanatory diagram of its operation.
【図４】図４（ａ）は従来の動翼の正面図、同図（ｂ）
は斜視図である。[Fig. 4] Fig. 4(a) is a front view of a conventional rotor blade, and Fig. 4(b) is a front view of a conventional rotor blade.
is a perspective view.
【図５】図５はその作用説明図である。FIG. 5 is an explanatory diagram of its operation.
１ 動翼 ２ 静翼 ３ 壁圧の変動を計測するセンサ ４ バルブ ５ 蒸気 ６ 蒸気の配管 ７ ワイヤ ８ ディフューザ ９ コントローラ 1 Moving blade 2 static wings 3 Sensor that measures wall pressure fluctuations 4 valve 5 Steam 6 Steam piping 7 wire 8 Diffuser 9 Controller
Claims (1)
られディフューザ壁圧の変動を計測して信号を出力する
センサと、該センサが出力する信号に基づいて上記動翼
先端に向けて流体を注入するコントローラとを備えたこ
とを特徴とする動翼の制振装置。1. A sensor attached to the diffuser wall near the tip of the rotor blade that measures fluctuations in diffuser wall pressure and outputs a signal, and injects fluid toward the tip of the rotor blade based on the signal output by the sensor. What is claimed is: 1. A vibration damping device for rotor blades, comprising a controller for controlling
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3255091U JPH04127804U (en) | 1991-05-10 | 1991-05-10 | Vibration damping device for rotor blades |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3255091U JPH04127804U (en) | 1991-05-10 | 1991-05-10 | Vibration damping device for rotor blades |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH04127804U true JPH04127804U (en) | 1992-11-20 |
Family
ID=31915469
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP3255091U Withdrawn JPH04127804U (en) | 1991-05-10 | 1991-05-10 | Vibration damping device for rotor blades |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH04127804U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2013221522A (en) * | 2012-04-18 | 2013-10-28 | General Electric Co <Ge> | System of reducing vibration of turbine |
-
1991
- 1991-05-10 JP JP3255091U patent/JPH04127804U/en not_active Withdrawn
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2013221522A (en) * | 2012-04-18 | 2013-10-28 | General Electric Co <Ge> | System of reducing vibration of turbine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A300 | Application deemed to be withdrawn because no request for examination was validly filed |
Free format text: JAPANESE INTERMEDIATE CODE: A300 Effective date: 19950810 |