JPH0882547A - Wing-vibration measuring apparatus - Google Patents
Wing-vibration measuring apparatusInfo
- Publication number
- JPH0882547A JPH0882547A JP21704594A JP21704594A JPH0882547A JP H0882547 A JPH0882547 A JP H0882547A JP 21704594 A JP21704594 A JP 21704594A JP 21704594 A JP21704594 A JP 21704594A JP H0882547 A JPH0882547 A JP H0882547A
- Authority
- JP
- Japan
- Prior art keywords
- wing
- detected
- blade
- counter
- rotary
- 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
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は蒸気タービンやポンプな
どの回転翼の振動計測に適用される翼振動計測装置に関
するものである。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a blade vibration measuring device applied to the vibration measurement of rotary blades such as steam turbines and pumps.
【０００２】[0002]
【従来の技術】図８乃至図１０は従来の翼振動計測装置
を示し、図８は回転翼の正面図、図９は同側面図、図１
０はシステム図であり、回転翼０１は円周方向に等間隔
にディスク部０２で支持されて回転軸０３に取付けられ
ている。この回転翼０１には歪みゲージ０４が貼り付け
られ、そのリード線０５はディスク部０２を配線され回
転軸０３上に設置された送信トランスミッタ０６へ接続
されている。また回転軸０３上にはバッテリー０７も設
置され、リード線０８により同バッテリー０７は送信ト
ランスミッタ０６へ接続されている。送信トランスミッ
タ０６には図１０の如く送信アンテナ０９が取付けられ
ている。また送信アンテナ０９と相対する静止側には受
信アンテナ０１０が取付けられ、同アンテナ０１０は受
信器０１１に接続されている。受信器０１１の出力は出
力端０１２から図示しない振動処理装置へ入力されるよ
うになされている。しかしこの従来装置によれば、回転
翼０１が振動により変形すると振動応力が発生し、翼表
面には歪みが生じる。この歪みを歪みゲージ０４により
検出し、送信トランスミッタ０６で増幅し、ＦＭ信号に
変換して送信アンテナ０９より送信する。送信されたＦ
Ｍ信号を受信アンテナ０１０で受信し、受信器０１１で
元の歪み信号に比例した電気信号に復調し出力する。8 to 10 show a conventional blade vibration measuring device, FIG. 8 is a front view of a rotary blade, FIG. 9 is a side view of the same, and FIG.
Reference numeral 0 is a system diagram, and the rotor blades 01 are supported by the disk portions 02 at equal intervals in the circumferential direction and attached to the rotating shaft 03. A strain gauge 04 is attached to the rotary blade 01, and a lead wire 05 of the strain gauge 04 is connected to a transmitter transmitter 06 installed on the rotary shaft 03 with the disk portion 02 wired. A battery 07 is also installed on the rotating shaft 03, and the battery 07 is connected to the transmitter transmitter 06 by a lead wire 08. A transmission antenna 09 is attached to the transmission transmitter 06 as shown in FIG. A receiving antenna 010 is attached to the stationary side opposite to the transmitting antenna 09, and the receiving antenna 010 is connected to the receiver 011. The output of the receiver 011 is input to the vibration processing device (not shown) from the output end 012. However, according to this conventional device, when the rotary blade 01 is deformed by vibration, vibration stress is generated, and the blade surface is distorted. This strain is detected by the strain gauge 04, amplified by the transmission transmitter 06, converted into an FM signal, and transmitted from the transmission antenna 09. F sent
The reception antenna 010 receives the M signal, and the receiver 011 demodulates it into an electric signal proportional to the original distortion signal and outputs the electric signal.
【０００３】[0003]
【発明が解決しようとする課題】前記従来装置において
は、歪ゲージ０４により回転翼振動を検出する場合、回
転軸０３上に歪ゲージ０４、ゲージリード線０５、送信
トランスミッタ０６及びバッテリー０７等を取付ける必
要があり、また回転による遠心力に耐えるように取付け
るためには相当の工夫と費用が必要であった。歪ゲージ
０４の１枚では１つの回転翼０１の振動しか検出できな
いので、多数翼を同時計測するためには、回転軸０３上
に取付ける設備が計測する翼数に比例して多くなる。従
って前記従来装置では、多数翼の同時計測は極めて困難
であった。本発明は前記従来の問題を解消しようとする
もので、非接触によりすべての回転翼の振動を容易に把
握できる翼振動計測装置を提供しようとするものであ
る。In the conventional device, when the rotor blade vibration is detected by the strain gauge 04, the strain gauge 04, the gauge lead wire 05, the transmitter transmitter 06, the battery 07, etc. are mounted on the rotary shaft 03. It was necessary, and a considerable amount of ingenuity and cost were required to mount it to withstand the centrifugal force caused by rotation. Since one strain gauge 04 can detect only the vibration of one rotary blade 01, the number of blades installed on the rotary shaft 03 increases in proportion to the number of blades measured in order to simultaneously measure multiple blades. Therefore, it is extremely difficult to simultaneously measure a large number of blades with the conventional device. The present invention is intended to solve the above-mentioned conventional problems, and to provide a blade vibration measuring device capable of easily grasping vibrations of all rotary blades without contact.
【０００４】[0004]
【課題を解決するための手段】このため本発明は、翼先
端部と相対する静止側に等間隔にとりつけられた２のｎ
乗個（ここでｎは正の整数）の電磁ピックアップ出力パ
ルスと、翼基部と相対する静止側に翼のピッチの｛ｋ＋
０．５｝倍（ここでｋは任意の正の整数）の間隔で取付
けられた２個の電磁ピックアップ出力パルスのどちらか
一方との位相差を計数する計数器と、前記翼基部回転パ
ルスの周期を計数する計数器と、前記両計数器の出力の
割り算を行う除算器と、前記両計数器に高周波基準クロ
ック信号を入力する手段とを備えてなるもので、これを
課題解決のための手段とするものである。Therefore, according to the present invention, two n's mounted at equal intervals on the stationary side facing the tip of the blade are provided.
Multiplied (where n is a positive integer) electromagnetic pickup output pulses and the pitch of the blade on the stationary side facing the blade base {k +
A counter for counting the phase difference with one of the two output pulses of the electromagnetic pickup mounted at intervals of 0.5} times (where k is an arbitrary positive integer); A counter for counting the cycle, a divider for dividing the outputs of the both counters, and means for inputting a high-frequency reference clock signal to the both counters are provided. It is a means.
【０００５】[0005]
【作用】本発明によれば、計数器Ｘにより回転翼先端部
と翼基部間の通過時間差を検出し、計数基Ｙで翼ピッチ
分だけ回転する時間を検出し、これらの両検出値の割り
算により回転翼の回転方向の基準点からの変位を翼ピッ
チに対する割合で検出する。また回転翼基部の検出器を
翼ピッチの｛ｋ＋０．５｝倍（ここでｋは任意の正の整
数）の間隔で２個設けているので、これらのどちらかを
適宜選んで処理することにより、回転翼先端部と回転翼
基部間の通過時間差が０又は翼ピッチ分の時間差に近い
場合に生じる不安定な現象（不連続となる）を避け、す
べての計測点について安定な計測をすることができる。
更に回転翼先端部の検出器の数を２のｎ乗個としている
ので、各回転翼毎に検出される信号は等間隔な２のｎ乗
個の時系列波形となり、ＦＦＴ演算が非常に高速に実現
できる。According to the present invention, the counter X detects the passage time difference between the rotor blade tip and the blade base, and the counting base Y detects the time required to rotate by the blade pitch, and divides these two detected values. The displacement of the rotary blade from the reference point is detected by the ratio with respect to the blade pitch. Also, two detectors at the base of the rotary blade are provided at intervals of {k + 0.5} times the blade pitch (where k is an arbitrary positive integer), so either of these can be selected as appropriate for processing. , Avoid unstable phenomena (discontinuity) that occur when the passage time difference between the rotor blade tip and rotor blade base is close to 0 or the blade pitch time difference, and perform stable measurement at all measurement points. You can
Further, since the number of detectors at the tip of the rotor blades is 2 to the n-th power, the signals detected for each rotor are time-series waveforms of the 2n-th power at even intervals, and the FFT calculation is very fast. Can be realized.
【０００６】[0006]
【実施例】以下本発明を図面の実施例について説明する
と、図１は本発明の実施例に係る翼振動計測装置のシス
テム構成を示し、回転翼１の先端部に対向する静止側に
は２のｎ乗個の電磁ピックアップＣが等間隔に取付けら
れている。また回転翼１の基部に対向する静止側には２
個の電磁ピックアップＢが翼ピッチの｛ｋ＋０．５｝倍
（ここでｋは任意の正の整数）の間隔で取付けられてい
る。更にロータ２の軸部に対向する静止側には、１個の
回転パルス検出器Ａ（１回転に１個のパルスを検出）が
取付けられている。またこれらの検出器の信号は、回転
翼の変位を演算するための１次処理装置３に入力され、
その出力信号はＤＭＡ（Direct Memory Access）転送を
行うインターフェースを介して、各種振動解析をオンラ
インで処理するための２次処理装置４に接続されてい
る。図２は各検出器の信号を１次処理装置３で矩形波に
波形成形した後の各パルスのタイミングチャートを示
し、図３は１次処理装置３で実施する演算処理のブロッ
ク線図を示す。図３において、回転翼先端部より検出し
た各パルスと、２個の回転翼基部より検出したパルスの
どちらか一方をゲート信号として基準クロックを計数す
る計数器Ｘと、前記翼基部より検出したパルスの一方を
ゲート信号として基準クロックを計数する計数器Ｙと、
両計数器の出力を割り算（Ｘ／Ｙ）する除算器Ｚを備え
ている。また回転翼基部の電磁ピックアップＢの出力
は、数十から数百メガヘルツの高周波基準クロックを計
数する計数器Ｘのゲート信号となるとともに、ＤＭＡ転
送のタイミングを制御するコントローラ５のゲート信号
となる。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention will be described below with reference to the embodiments of the drawings. FIG. 1 shows a system configuration of a blade vibration measuring device according to an embodiment of the present invention. The n-th power electromagnetic pickups C are mounted at equal intervals. On the stationary side facing the base of the rotor 1,
The electromagnetic pickups B are mounted at intervals of {k + 0.5} times the blade pitch (where k is an arbitrary positive integer). Further, one rotation pulse detector A (one pulse is detected in one rotation) is attached to the stationary side facing the shaft of the rotor 2. The signals of these detectors are input to the primary processing unit 3 for calculating the displacement of the rotor blades,
The output signal is connected to a secondary processing device 4 for online processing of various vibration analyzes via an interface for performing DMA (Direct Memory Access) transfer. FIG. 2 shows a timing chart of each pulse after the signal of each detector is shaped into a rectangular wave by the primary processing device 3, and FIG. 3 shows a block diagram of the arithmetic processing performed by the primary processing device 3. . In FIG. 3, a counter X that counts a reference clock with each pulse detected from the tip of the rotor blade or one of the pulses detected from the two rotor blade bases as a gate signal, and a pulse detected from the blade base A counter Y that counts a reference clock with one of the two as a gate signal,
It has a divider Z that divides (X / Y) the outputs of both counters. The output of the electromagnetic pickup B at the base of the rotary blade serves as the gate signal of the counter X that counts the high-frequency reference clock of several tens to several hundreds of megahertz and the gate signal of the controller 5 that controls the timing of DMA transfer.
【０００７】一方回転翼基部の電磁ピックアップＢ又は
Ｂ’のどちらか一方の出力と、回転翼先端部に対向して
取付けられた電磁ピックアップＣの各出力は、同様に数
十から数百メガヘルツの高周波基準クロックを計数する
計数器Ｙのゲート信号として入力される。計数器Ｘ及び
計数器Ｙの出力は除算器Ｚに入力され、その出力は回転
方向翼振動の変位信号としてバッファー６に入力され、
ＤＭＡコントローラ５の指令に基づいてバッファー６よ
り２次処理装置４に出力される。２次処理装置４では、
入力されたセンサ基準の時系列データを翼基準の時系列
データに並べ変えてＦＦＴ演算を実施し、各種振動解析
を実施する。図４乃至図７に２次処理装置４の出力の例
を示し、図４は翼の振動波形、図５はキャンベル線図、
図６はトラッキング解析結果、図７は全翼の振動モード
図をそれぞれ示す。On the other hand, the output of either the electromagnetic pickup B or B'at the base of the rotary blade and the output of the electromagnetic pickup C mounted so as to face the tip of the rotary blade are similarly tens to hundreds of megahertz. It is inputted as a gate signal of a counter Y which counts a high frequency reference clock. The outputs of the counter X and the counter Y are input to the divider Z, and the outputs thereof are input to the buffer 6 as the displacement signal of the rotational wing vibration,
The data is output from the buffer 6 to the secondary processing device 4 based on a command from the DMA controller 5. In the secondary processing device 4,
The input sensor-based time-series data is rearranged into blade-based time-series data to perform FFT calculation, and various vibration analyzes are performed. 4 to 7 show examples of the output of the secondary treatment device 4, FIG. 4 is a blade vibration waveform, FIG. 5 is a Campbell diagram,
FIG. 6 shows a tracking analysis result, and FIG. 7 shows vibration mode diagrams of all blades.
【０００８】[0008]
【発明の効果】以上詳細に説明した如く本発明の翼振動
計測装置によると、回転体上に全く器材を取付けること
なく非接触により回転方向の翼振動を計測できる。本発
明では等間隔に配置された２のｎ乗個の検出器を用いて
いるので、一定のサンプリング間隔で計測された２のｎ
乗個の時系列データを得ることができ、例えば歪みゲー
ジや加速度計などの接触型の振動計測装置で計測された
場合と同様に、ＦＦＴ分析による詳細な振動解析が可能
であり、また全く同じ条件で回転中のすべての翼の振動
検出ができるので、翼毎のばらつきは全体で構成される
振動モードを評価でき、産業上極めて有益である。As described in detail above, according to the blade vibration measuring apparatus of the present invention, the blade vibration in the rotating direction can be measured in a non-contact manner without mounting any equipment on the rotating body. In the present invention, since 2 n power detectors arranged at equal intervals are used, 2 n measured at constant sampling intervals are used.
It is possible to obtain multiplicity of time-series data, and it is possible to perform detailed vibration analysis by FFT analysis in the same way as when measured with a contact-type vibration measuring device such as a strain gauge or an accelerometer, and it is exactly the same. Since it is possible to detect the vibrations of all the blades that are rotating under the conditions, the variation of each blade can evaluate the vibration mode that is configured as a whole, which is extremely useful in industry.
【図１】本発明の実施例に係る翼振動計測装置のシステ
ム図である。FIG. 1 is a system diagram of a blade vibration measuring device according to an embodiment of the present invention.
【図２】同検出パルスのタイミングチャート図である。FIG. 2 is a timing chart of the same detection pulse.
【図３】同演算処理のブロック線図である。FIG. 3 is a block diagram of the same arithmetic processing.
【図４】同回転翼の振動波形を示す説明図である。FIG. 4 is an explanatory diagram showing a vibration waveform of the rotary blade.
【図５】同キャンベル線図である。FIG. 5 is a Campbell diagram of the same.
【図６】同トラッキング解析結果を示す説明図である。FIG. 6 is an explanatory diagram showing a result of the tracking analysis.
【図７】同全翼の振動モードを示す説明図である。FIG. 7 is an explanatory diagram showing vibration modes of the same blade.
【図８】従来の翼振動計測装置の正面図である。FIG. 8 is a front view of a conventional blade vibration measuring device.
【図９】図８の側面図である。9 is a side view of FIG.
【図１０】図８の装置によるシステム図である。10 is a system diagram of the apparatus of FIG.
１ 回転翼 ２ ロータ ３ １次処理装置 ４ ２次処理装置 ５ ＤＭＡコントローラ ６ バッファー ７ ＤＭＡ転送インターフェース Ａ 回転パルス検出器 Ｂ，Ｂ’ 電磁ピックアップ Ｃ 電磁ピックアップ Ｘ 計数器 Ｙ 計数器 Ｚ 除算器 1 Rotor 2 Rotor 3 Primary Processing Device 4 Secondary Processing Device 5 DMA Controller 6 Buffer 7 DMA Transfer Interface A Rotating Pulse Detector B, B'Electromagnetic Pickup C Electromagnetic Pickup X Counter Y Counter Z Divider
Claims (1)
りつけられた２のｎ乗個（ここでｎは正の整数）の電磁
ピックアップ出力パルスと、翼基部と相対する静止側に
翼のピッチの｛ｋ＋０．５｝倍（ここでｋは任意の正の
整数）の間隔で取付けられた２個の電磁ピックアップ出
力パルスのどちらか一方との位相差を計数する計数器
と、前記翼基部回転パルスの周期を計数する計数器と、
前記両計数器の出力の割り算を行う除算器と、前記両計
数器に高周波基準クロック信号を入力する手段とを備え
てなることを特徴とする翼振動計測装置。1. An electromagnetic pickup output pulse of 2n powers (where n is a positive integer) mounted at equal intervals on the stationary side facing the blade tip, and the blade on the stationary side facing the blade base. A counter for counting the phase difference with either one of the two output pulses of the electromagnetic pickup mounted at intervals of {k + 0.5} times the pitch of (where k is an arbitrary positive integer); A counter for counting the period of the base rotation pulse,
A blade vibration measuring device comprising: a divider that divides the outputs of both counters; and a unit that inputs a high-frequency reference clock signal to both counters.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP21704594A JPH0882547A (en) | 1994-09-12 | 1994-09-12 | Wing-vibration measuring apparatus |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP21704594A JPH0882547A (en) | 1994-09-12 | 1994-09-12 | Wing-vibration measuring apparatus |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH0882547A true JPH0882547A (en) | 1996-03-26 |
Family
ID=16697976
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP21704594A Pending JPH0882547A (en) | 1994-09-12 | 1994-09-12 | Wing-vibration measuring apparatus |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0882547A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007263899A (en) * | 2006-03-30 | 2007-10-11 | Toppan Printing Co Ltd | Device for measuring pattern shape, and pattern shape measuring method |
| JP2013083568A (en) * | 2011-10-11 | 2013-05-09 | Toshiba Corp | Blade vibration measuring device |
| US9057682B2 (en) | 2011-09-13 | 2015-06-16 | Kabushiki Kaisha Toshiba | Blade vibration measuring apparatus |
| EP2672240A3 (en) * | 2012-06-08 | 2017-09-27 | General Electric Company | Campbell diagram displays and methods and systems for implementing same |
| CN114136545A (en) * | 2021-11-08 | 2022-03-04 | 陕西飞机工业有限责任公司 | Airplane outer wing airtight oil seal test equipment and method |
| US11768087B2 (en) | 2019-10-28 | 2023-09-26 | Mitsubishi Heavy Industries, Ltd. | Detection device, rotary machine, and detection method |
-
1994
- 1994-09-12 JP JP21704594A patent/JPH0882547A/en active Pending
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007263899A (en) * | 2006-03-30 | 2007-10-11 | Toppan Printing Co Ltd | Device for measuring pattern shape, and pattern shape measuring method |
| US9057682B2 (en) | 2011-09-13 | 2015-06-16 | Kabushiki Kaisha Toshiba | Blade vibration measuring apparatus |
| JP2013083568A (en) * | 2011-10-11 | 2013-05-09 | Toshiba Corp | Blade vibration measuring device |
| EP2672240A3 (en) * | 2012-06-08 | 2017-09-27 | General Electric Company | Campbell diagram displays and methods and systems for implementing same |
| US11768087B2 (en) | 2019-10-28 | 2023-09-26 | Mitsubishi Heavy Industries, Ltd. | Detection device, rotary machine, and detection method |
| CN114136545A (en) * | 2021-11-08 | 2022-03-04 | 陕西飞机工业有限责任公司 | Airplane outer wing airtight oil seal test equipment and method |
| CN114136545B (en) * | 2021-11-08 | 2023-10-20 | 陕西飞机工业有限责任公司 | Air-tight oil-tight test equipment and method for outer wing of aircraft |
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