JPH06248902A - Arranging method for turbine moving blade - Google Patents
Arranging method for turbine moving bladeInfo
- Publication number
- JPH06248902A JPH06248902A JP4003993A JP4003993A JPH06248902A JP H06248902 A JPH06248902 A JP H06248902A JP 4003993 A JP4003993 A JP 4003993A JP 4003993 A JP4003993 A JP 4003993A JP H06248902 A JPH06248902 A JP H06248902A
- Authority
- JP
- Japan
- Prior art keywords
- blades
- wheel
- blade
- mode
- natural frequency
- 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.)
- Granted
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
(57)【要約】
【目的】 ホイールモードの振動形態が現われにくい、
或は現われたとしても励振力に対する応答を比較的低く
抑えるための動翼配列方法を得ること。
【構成】 固有振動数が動翼全数の平均値から離れた特
異な振動数を有する翼２をホイールの全周に不均等間隔
で配置し、かつその他の翼をホイール全体の翼の重量差
による不均等ベクトルが最小かまたは許容範囲内におさ
まるように配置する。
(57) [Summary] [Purpose] The vibration mode in the wheel mode is difficult to appear,
Or, even if it appears, to obtain a rotor blade arrangement method for keeping the response to the excitation force relatively low. [Structure] The blades 2 whose natural frequencies are different from the average value of the total number of moving blades are arranged at unequal intervals over the entire circumference of the wheel, and the other blades are made different depending on the weight difference of the blades of the entire wheel. Arrange so that the unequal vector is at the minimum or within the allowable range.
Description
【０００１】[0001]
【産業上の利用分野】本発明は蒸気タービン、ガスター
ビンなどの動翼に係わり、回転体における不釣合量を極
力小さくすると共に、振動応力をも低レベルに押さえる
ことができるような動翼の配列方法に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a moving blade of a steam turbine, a gas turbine or the like, and has an arrangement of moving blades capable of minimizing an unbalance amount in a rotating body and suppressing vibration stress to a low level. Regarding the method.
【０００２】[0002]
【従来の技術】タービン動翼の加工において、特に作動
流体の通路部（以下翼形と称する）の加工方法を見る
と、従来は主にモデル羽根を機械に取り付けて倣い加工
が行なわれていた。一方最近では加工機械の急速な進歩
と加工精度の向上もあいまって高速３次元ＮＣを用いて
直接図寸形状に仕上げようとする方法が採られている。
このような背景から、加工品質も向上し製品の寸法的な
ばらつきも比較的小さくなっている。しかしながら高速
３次元ＮＣに使用されているエンドミル等のカッターに
は、使用時間の経過に伴い、徐々に摩耗等による変形が
生ずるため、実際には翼の加工本数を目安にして交換さ
れる。したがってこのように加工された翼形は、図面で
指定された公差の範囲内で肉厚等の寸法にばらつきが生
じ、この機械加工時における翼形の肉厚のばらつきによ
り各翼の固有振動数や重量にばらつきが生ずる。2. Description of the Related Art In machining a turbine rotor blade, particularly, looking at a machining method of a passage portion (hereinafter referred to as a blade shape) of a working fluid, conventionally, a model blade is mainly attached to a machine and copying is performed. . On the other hand, recently, due to rapid progress of processing machines and improvement of processing accuracy, a method is adopted in which a high-speed three-dimensional NC is used to directly finish a figure-shaped shape.
From such a background, the processing quality is improved and the dimensional variation of products is relatively small. However, a cutter such as an end mill used in a high-speed three-dimensional NC is gradually deformed due to wear or the like with the lapse of use time. Therefore, in practice, the number of blades to be machined is replaced as a guide. Therefore, the airfoil machined in this way has variations in dimensions such as wall thickness within the tolerance specified in the drawing, and the natural frequency of each airfoil varies due to the variation in the airfoil wall thickness during machining. And weight will vary.
【０００３】そこで、機械加工の完了した翼の管理方法
としては、個々の翼の固有振動数計測とモーメント計測
が一般に行なわれている。固有振動数計測は製品のばら
つきを主に管理するものであり、ばらつきが大きく許容
値を超えるものに対しては修正加工が施される場合もあ
る。またモーメント計測は、個々の翼の重量にロータ中
心・翼重心間距離を掛けた値を計測するものであり、こ
の計測値のばらつきが大きい場合も修正加工が施され
る。Therefore, as a method of controlling the blades that have been machined, the natural frequency measurement and moment measurement of each blade are generally performed. The natural frequency measurement mainly manages the variation of the product, and if the variation is large and exceeds the allowable value, correction processing may be performed. The moment measurement is a value obtained by multiplying the weight of each blade by the distance between the center of the rotor and the center of gravity of the blade, and correction processing is performed even if the measured values vary widely.
【０００４】ところで、タービン動翼には高速回転時に
過大な遠心力が作用するため、個々の動翼のわずかな重
量差でも大きな不釣合として作用する場合がある。この
不釣合を小さくするための方法の一つとして、翼をロー
タに組み立てる前に配列計算を実施し、不釣合が極力小
さくなるような翼の配列順序を設定している。更に組み
立て後にはバランスウェイトによる調整もなされてい
る。By the way, since an excessive centrifugal force acts on the turbine blades at high speed, even a slight weight difference between the individual blades may cause a large imbalance. As one of the methods for reducing this imbalance, array calculation is performed before assembling the blades into the rotor, and the blade arrangement order is set so that the unbalance is minimized. Furthermore, after assembly, the balance weight is used for adjustment.
【０００５】翼の配列を決定する場合、実際には次のよ
うな計算が行なわれる。図４において、ロータホイール
一段落全周の翼枚数をＮ、各翼の取り付け角をΘi 、各
翼のモーメントをＭi とするとWhen determining the arrangement of the blades, the following calculation is actually performed. In FIG. 4, assuming that the number of blades around the entire circumference of the rotor wheel is N, the mounting angle of each blade is Θ i , and the moment of each blade is M i.
【０００６】 で定義される。Ｍi は翼の重量Ｗi と、ロータ中心Ｃと
翼の重視Ｇi との距離Ｄi を用いて次のように定義され
る。[0006] Is defined by M i is defined as follows using the blade weight W i and the distance D i between the rotor center C and the blade emphasis G i .
【０００７】Ｍi ＝Ｗi ・Ｄi ベクトルの大きさは次式で与えられる。The magnitude of M i = W i · D i vector is given by the following equation.
【０００８】 Ｖ＝（Ｘ2 ＋Ｙ2 ）1/2 （２） 翼の配列計算ではこのＶの値が最小となるような配列順
序を求めている。V = (X 2 + Y 2 ) 1/2 (2) In the blade array calculation, the array order that minimizes the value of V is obtained.
【０００９】[0009]
【発明が解決しようとする課題】図５はロータホイール
１の一段落に動翼２を装着した場合の一例であり、図６
および図７は一段落分の翼全数に関する低次代表モード
固有振動数の計測値とモーメント計測値の頻度分布を統
計的に表示したものである。図６と図７の相関関係を見
ると一般的には固有振動数の低い領域Ｆ１とモーメント
計測値の低い領域Ｍ１、また固有振動数の高い領域Ｆ２
とモーメント計測値の高い領域Ｍ２が比較的対応する。
すなわち翼の長さが同じ場合、翼形が厚めに加工される
と重量は大きくなり、固有振動数も高くなる。一方翼形
が薄目に加工されると重量は小さくなり、固有振動数も
低くなる傾向がある。FIG. 5 shows an example in which the rotor blade 1 is attached to the paragraph of the rotor wheel 1, and FIG.
And FIG. 7 shows statistically the frequency distribution of the measured values of the low-order representative mode natural frequency and the measured moment values for the total number of blades for one paragraph. Looking at the correlation between FIG. 6 and FIG. 7, generally, a region F1 having a low natural frequency, a region M1 having a low moment measurement value, and a region F2 having a high natural frequency are shown.
And a region M2 having a high moment measurement value correspond relatively.
That is, when the blade length is the same, the thicker the airfoil is, the heavier the weight becomes and the higher the natural frequency becomes. On the other hand, when the airfoil is processed to be thin, its weight tends to be small and its natural frequency tends to be low.
【００１０】図８はこの様な翼を従来の技術により配列
した一例である。従来の技術による配列では、翼のモー
メント計測値を基に決定されるため、図８に示すように
特異なモーメントを有する翼３が数箇所に固まり、ほぼ
等間隔に配置される場合がある。特異なモーメントを有
する翼３としてはモーメント値の小さい翼が等間隔に配
置される場合もあり、またモーメント値の小さい翼が等
間隔に配置される場合もある。FIG. 8 shows an example in which such blades are arranged by a conventional technique. In the arrangement according to the conventional technique, since it is determined based on the measured value of the moment of the blade, the blade 3 having a unique moment may be solidified in several places and arranged at substantially equal intervals as shown in FIG. As the blades 3 having unique moments, blades having small moment values may be arranged at equal intervals, and blades having small moment values may be arranged at equal intervals.
【００１１】前述したようにモーメントの大小と固有振
動数には比較的相関関係があるため、このような配列で
は次のような問題点がある。As described above, since the magnitude of the moment and the natural frequency are relatively correlated with each other, such an array has the following problems.
【００１２】すなわちロータホイールと動翼全体を振動
特性の面から見た場合、例えば固有振動数の極端に高い
翼だけがホイールの特定の箇所に固まり、それが全周に
等間隔に位置するような場合には、その位置がホイール
モード振動の節直径になりやすい。ホイールモード振動
とは翼とロータホイールが連成して円板状の振動形態を
示すものである。このような振動形態は、翼の長さが短
い高中圧段落部、あるいは翼長が比較的長くてもホイー
ルが薄い場合などに現れるものである。また一般に低次
モードすなわち節直径が少ないほど励振力に対する振動
の応答レベルは大きくなる。図８は振動数の特異な翼が
ホイールの４箇所に等間隔に配置され、２節直径モード
の振動形態が現れた例を示している。図中、ＮＤ１とＮ
Ｄ２はホイールモード振動の節直径線を示している。こ
のような振動形態は回転数の２倍周波数をはじめとし
て、２の整数倍で回転同期した励振力に対して大きな応
答を示し大きな振動応力発生の原因となりやすい。That is, when the rotor wheel and the entire moving blade are viewed from the viewpoint of vibration characteristics, for example, only the blade having an extremely high natural frequency is solidified in a specific portion of the wheel, and it is arranged at equal intervals along the entire circumference. In that case, the position is likely to be the node diameter of the wheel mode vibration. Wheel mode vibration refers to a disk-shaped vibration mode in which a blade and a rotor wheel are coupled. Such a vibration form appears in a high-to-medium pressure stage where the blade length is short, or when the wheel is thin even if the blade length is relatively long. In general, the lower the mode, that is, the smaller the node diameter, the greater the vibration response level to the excitation force. FIG. 8 shows an example in which blades having unique frequencies are arranged at four positions on the wheel at equal intervals, and a vibration mode of a two-node diameter mode appears. In the figure, ND1 and N
D2 indicates the nodal diameter line of the wheel mode vibration. Such a vibration form shows a large response to an exciting force rotationally synchronized with an integral multiple of 2 including a frequency twice the rotation speed, and is likely to cause a large vibration stress.
【００１３】図８はホイールモード振動の一例として２
節直径モードを示しているが、節直径が３、４、…と増
した場合には、その節直径の整数倍で回転同期した励振
力に対して大きな応答を示すことになる。FIG. 8 shows two examples of wheel mode vibration.
Although the nodal diameter mode is shown, when the nodal diameter increases to 3, 4, ..., A large response is shown to the excitation force rotationally synchronized with an integral multiple of the nodal diameter.
【００１４】翼がホイールに組み込まれる時の構造とし
ては、翼同志が互いに連結されないフリースタンディン
グ翼、複数の翼を連結した群翼、或いは全周の翼を連結
した全周一群翼などがあるが、そのいずれにおいてもホ
イールモードの振動形態は発生し得る。As a structure when the blades are incorporated into a wheel, there are free standing blades in which the blades are not connected to each other, a group blade in which a plurality of blades are connected, or a group of blades in a full circumference in which blades all around are connected. In either case, the vibration mode of the wheel mode can occur.
【００１５】本発明はかかるホイールモードの振動形態
が現れにくい、あるいは現れたとしても励振力にロータ
ホイールする応答を比較的低く抑えるための翼配列方法
を提供することを目的とする。An object of the present invention is to provide a blade arranging method for suppressing the response of the rotor wheel to the excitation force relatively low even if such a vibration mode of the wheel mode does not appear easily or even if it appears.
【００１６】[0016]
【課題を解決するための手段】本発明に係わるタービン
動翼の配列方法は、上述した従来技術が有する課題を解
決するために、翼の配列計算の際にモーメント計測値だ
けでなく固有振動数計測値も含めて翼の配列順序を決定
しようとするものであり、固有振動数が動翼全数の平均
値から離れた特異の振動数を有する翼をホイールの全周
に不等間隔で配置し、かつその他の翼をホイール全体の
翼の重量差による不均合ベクトルが最小かまたは許容範
囲内におさまるように配置することを特徴とする。In order to solve the problems of the above-mentioned prior art, the turbine blade arranging method according to the present invention solves not only the moment measurement value but also the natural frequency in the blade arranging calculation. It is intended to determine the arrangement order of the blades including the measured values, and the blades whose natural frequency is a singular frequency that is far from the average value of all the moving blades are arranged at equal intervals on the entire circumference of the wheel. , And the other blades are arranged such that the disproportion vector due to the difference in weight of the blades of the entire wheel is minimized or within an allowable range.
【００１７】[0017]
【作用】本発明に係わるタービン動翼の配列方法は、不
釣合ベクトルを最小にする条件のほかに固有振動数の特
異な翼がホイールの数箇所に固まることがなく、しかも
それが等間隔にならないような翼の配列順序となってい
るために、ホイールモードの振動において節直径が現れ
にくく、したがって回転同期した低次の励振力に対して
ホイールモードの振動応力レベルが低く抑えられる。According to the turbine rotor blade arrangement method of the present invention, in addition to the condition that the unbalance vector is minimized, the blades having singular frequencies are not fixed at several points on the wheel, and they are not evenly spaced. Since the blades are arranged in such a manner, the node diameter is unlikely to appear in the vibration of the wheel mode, so that the vibration stress level of the wheel mode is suppressed to be low with respect to the rotationally synchronized low-order excitation force.
【００１８】[0018]
【実施例】以下、本発明に係わるタービン動翼の配列方
法の一実施例を図１を参照して説明する。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of a method for arranging turbine blades according to the present invention will be described below with reference to FIG.
【００１９】図１はホイールに組立られた一段落分の翼
の配列を示している。ホイール１の外周に特異な固有振
動数を有する翼２が不等間隔で配置され、その翼２の間
に比較的平均的な固有振動数を有する翼３が配置されて
いる。翼３はホイール全体の不釣合ベクトルが極力小さ
くなるように配列が決定されている。この実施例では翼
同志の相互の連結構造がないフリースタンディング翼の
例を示している。FIG. 1 shows an array of blades for one paragraph assembled on a wheel. Blades 2 having a specific natural frequency are arranged on the outer periphery of the wheel 1 at unequal intervals, and blades 3 having a relatively average natural frequency are arranged between the blades 2. The blades 3 are arranged so that the unbalance vector of the entire wheel is as small as possible. In this embodiment, an example of a free-standing blade in which the blades are not connected to each other is shown.
【００２０】一方図２は、それに対応する翼１段落分の
固有振動数の頻度分布を示した投影図である。図２にお
いてＦ１は固有振動数の極端に低い翼を示し、Ｆ２は逆
に固有振動数が高い翼を示している。Ｆ３は固有振動数
が平均値に近い翼である。Ｆ１とＦ３、およびＦ３とＦ
２の閾値としては、たとえばＦ１、Ｆ２がそれぞれ全数
の５％となるような設定も一つの方法である。On the other hand, FIG. 2 is a projection diagram showing the frequency distribution of the natural frequencies of one paragraph of the blade corresponding thereto. In FIG. 2, F1 indicates a blade having an extremely low natural frequency, and F2 indicates a blade having a high natural frequency. F3 is a blade whose natural frequency is close to the average value. F1 and F3, and F3 and F
As a threshold value of 2, for example, setting of F1 and F2 to 5% of the total number is also one method.
【００２１】ここで翼の全数をＮ、Ｆ１およびＦ２に相
当する翼の本数をそれぞれＮ１、Ｎ２とする。翼の配列
決定の手順としては、まず全数Ｎをランダムに配列す
る。ランダムに配列する方法としては、たとえば乱数を
用いて翼を順次選んでいくことにより決定できる。また
特定の節直径のみを回避するような配置も容易に設定可
能である。そしてＦ１とＦ２に相当し特異な振動数を有
する翼２（Ｎ１＋Ｎ２）本をこの配列番号で固定する。
配列番号とはホイールの外周に沿って順番に決められた
翼の取り付け位置を示す番号である。Here, the total number of blades is N, and the number of blades corresponding to F1 and F2 is N1 and N2, respectively. As a procedure for determining the arrangement of the blades, first, all N are randomly arranged. The method of arranging at random can be determined by sequentially selecting the blades by using a random number, for example. Further, it is possible to easily set an arrangement that avoids only a specific node diameter. Then, two blades (N1 + N2) corresponding to F1 and F2 and having a unique frequency are fixed by this array number.
The array number is a number that indicates the attachment position of the blade that is determined in order along the outer circumference of the wheel.
【００２２】次にＦ３に相当し比較的平均的な固有振動
数有する翼３のみの取り付け位置を交換することによ
り、（２）式で定義された不釣合ベクトルが最小になる
ような配列を計算する。このとき既に決定されているＦ
１とＦ２に相当する翼２（Ｎ１＋Ｎ２）本の取り付け位
置は固定されているので、特異な固有振動数を持つ翼の
配列はホイールの全周にロータホイールして不等間隔で
分布したままの状態になっている。Next, by exchanging the mounting positions of only the blades 3 corresponding to F3 and having a relatively average natural frequency, an array in which the unbalance vector defined by the equation (2) is minimized is calculated. . F already determined at this time
Since the mounting positions of the blades 2 (N1 + N2) corresponding to 1 and F2 are fixed, the arrangement of the blades having the unique natural frequency is a rotor wheel on the entire circumference of the wheel and remains distributed at unequal intervals. It is in a state.
【００２３】上述した構成と作用から明らかなように、
本実施例のタービン動翼配列方法出は固有振動数の特異
な翼が数箇所に固まること無く、全周に不等間隔で配置
されているために、低次のホイールモードとして節が現
れにくく、したがって回転数の倍数周波数などの低次の
回転同期励振力に対して応答しにくいため、低い振動応
力レベルが維持される。As is apparent from the above-mentioned structure and operation,
In the method for arranging turbine blades of this embodiment, the blades having unique natural frequencies are not fixed at several places and are arranged at unequal intervals over the entire circumference, so that the nodes are less likely to appear as a low-order wheel mode. Therefore, since it is difficult to respond to a low-order rotation synchronous excitation force such as a frequency that is a multiple of the rotation speed, a low vibration stress level is maintained.
【００２４】図３は本発明のタービン動翼配列方法を適
用した他の実施例である。ホイール１の外周には特異な
固有振動数を有する翼２が不等間隔で配置されており、
その特異な固有振動数を有する翼２間に、平均的な固有
振動数を有する翼３がホイール全体の翼の重量差による
不釣合ベクトルが小さくなるように配置されている。こ
の実施例は全周の翼同志をタイワイヤー４により互いに
連結した全周一群翼構造の例を示している。全周一群構
造としては、タイワイヤーを用いずにスリープやカバー
ピース等の連結片を用いることもある。FIG. 3 shows another embodiment to which the turbine moving blade arrangement method of the present invention is applied. Wings 2 having unique natural frequencies are arranged on the outer periphery of the wheel 1 at unequal intervals,
Between the blades 2 having the unique natural frequency, the blades 3 having the average natural frequency are arranged so that the unbalance vector due to the weight difference of the blades of the entire wheel becomes small. This embodiment shows an example of an all-round one-group blade structure in which blades all around the circumference are connected to each other by a tie wire 4. As the all-round one group structure, a connecting piece such as a sleep or a cover piece may be used without using a tie wire.
【００２５】本実施例においても固有振動数の特異な翼
が数箇所に固まること無く、全周に不等間隔で配置され
ているために、低次のホイールモードとしての節が現れ
にくく、したがって回転数の倍数周波数などの低次の回
転同期励振力に対して応答しにくいため、低い振動応力
レベルが維持される。Also in this embodiment, since the blades having a unique natural frequency are not fixed at several places and are arranged at unequal intervals on the entire circumference, nodes as a low-order wheel mode hardly appear. Since it is difficult to respond to a low-order rotation synchronous excitation force such as a frequency that is a multiple of the rotation speed, a low vibration stress level is maintained.
【００２６】その他の実施例としては複数の翼同志を互
いに連結した群翼構造の場合でも本発明の配列方法は適
用可能であり、十分な効果が期待できる。群翼構造にお
いても固有振動数の特異な翼が特定の翼群に固まること
無く、全周に不等間隔で配置されていれば、低次のホイ
ールモードとしての節が現れにくく、したがって回転数
の倍数周波数などの励振力に対して応答しにくいため、
低い振動応力レベルが維持される。As another embodiment, the arrangement method of the present invention can be applied to a group wing structure in which a plurality of blades are connected to each other, and a sufficient effect can be expected. Even in the group wing structure, if the blades with unique natural frequencies are not fixed in a specific blade group and are arranged at unequal intervals over the entire circumference, nodes as low-order wheel modes are less likely to appear, and therefore the rotation speed It is difficult to respond to excitation force such as multiple frequency of
Low vibration stress levels are maintained.
【００２７】タービン動翼の設計において、低圧段落な
どに使用される比較的翼長の長翼では、翼単体でも回転
倍数周波数成分に対して共振しないような設計が成され
るが、翼の剛性に対してホイールの剛性が小さい場合に
はホイールモードの振動が比較的低い振動数で現れるた
め、かかるモードの振動応力を低いレベルに抑える設計
が必要になる。In the design of turbine blades, long blades having a relatively long blade length used in low-pressure stages are designed so that even a single blade will not resonate with a frequency component of a rotational frequency. On the other hand, when the rigidity of the wheel is small, the vibration of the wheel mode appears at a relatively low frequency, so it is necessary to design the vibration stress of this mode to a low level.
【００２８】また、特に翼長の短い動翼ではむしろホイ
ール連成モードの振動が主体となるため、これに対する
対策は重要である。Further, particularly in the case of a moving blade having a short blade length, the vibration in the wheel coupling mode is the main component, so countermeasures against this are important.
【００２９】[0029]
【発明の効果】以上述べたように本発明のタービン動翼
配列方法は、固有振動数の特異な翼が数箇所に固まるこ
と無く、全周に不等間隔で配置されているために、低次
のホイールモードとしての節が現れにくく、したがって
回転数の倍数周波数などの低次の回転同期励振力に対し
て応答しにくいため、低い振動応力レベルが維持され
る。As described above, according to the turbine rotor blade arrangement method of the present invention, since the blades having unique natural frequencies are not fixed at several places and are arranged at unequal intervals over the entire circumference, A low vibration stress level is maintained because the node as the next wheel mode is unlikely to appear and therefore it is difficult to respond to a low-order rotational synchronous excitation force such as a multiple frequency of the rotational speed.
【図１】本発明のタービン動翼配列方法により決定され
た動翼の配置列を示す配列図。FIG. 1 is an array diagram showing an array of blades determined by a turbine blade array method according to the present invention.
【図２】実際に加工された翼の低次代表モード固有振動
数の頻度分布を示す統計図。FIG. 2 is a statistical diagram showing a frequency distribution of low-order representative mode natural frequencies of an actually processed blade.
【図３】本発明の動翼配列方法を全周一群連結構造翼に
適用した他の実施例を示す配列図。FIG. 3 is an array diagram showing another embodiment in which the rotor blade arraying method of the present invention is applied to an all-round one-group connecting structure blade.
【図４】従来の動翼配列方法による不釣合ベクトルの計
算方法を示す説明図。FIG. 4 is an explanatory view showing a method of calculating an unbalance vector by a conventional moving blade array method.
【図５】動翼の組み立て構造を示す鳥かん図。FIG. 5 is a bird's eye view showing the assembled structure of the moving blade.
【図６】動翼１段階分の低次代表的モード固有振動数の
頻度分布を示す統計図。FIG. 6 is a statistical diagram showing a frequency distribution of low-order representative mode natural frequencies for one stage of a moving blade.
【図７】動翼１段落分のモーメント計測値の頻度分布を
示す統計図。FIG. 7 is a statistical chart showing a frequency distribution of moment measurement values for one stage of a moving blade.
【図８】従来の動翼配列方法による動翼の配置列を示す
図。FIG. 8 is a diagram showing a row of blades arranged by a conventional blade arrangement method.
１ ホイール ２ 特異な固有振動数を有する翼 ３ 動翼 ４ タイワイヤ 1 Wheel 2 Wing with unique natural frequency 3 Moving blade 4 Tie wire
Claims (1)
して形成されるタービンロータにおけるタービン動翼の
配列方法において、固有振動数が動翼全数の平均値から
離れた特異な振動数を有する翼をホイールの全周に不等
間隔で配置し、かつその他の翼をホイール全体の翼の重
量差による不釣合ベクトルが最小かまたは許容範囲内に
おさまるように配置することを特徴とするタービン動翼
の配置方法。1. A method of arranging turbine rotor blades in a turbine rotor, which is formed by mounting a large number of turbine rotor blades on the outer circumference of a rotor, wherein a natural frequency is a specific frequency that deviates from an average value of all rotor blades. Turbine motion characterized by arranging the blades that have it on the entire circumference of the wheel at unequal intervals, and arranging the other blades so that the unbalance vector due to the weight difference of the blades of the entire wheel is minimal or is within the allowable range. How to arrange wings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP04003993A JP3272088B2 (en) | 1993-03-01 | 1993-03-01 | Arrangement method of turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP04003993A JP3272088B2 (en) | 1993-03-01 | 1993-03-01 | Arrangement method of turbine blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH06248902A true JPH06248902A (en) | 1994-09-06 |
| JP3272088B2 JP3272088B2 (en) | 2002-04-08 |
Family
ID=12569774
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP04003993A Expired - Lifetime JP3272088B2 (en) | 1993-03-01 | 1993-03-01 | Arrangement method of turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3272088B2 (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005226649A (en) * | 2004-02-10 | 2005-08-25 | General Electric Co <Ge> | State-of-the-art fur tree and broach slot configurations for turbine first and second stage buckets and rotor wheels |
| EP1574666A1 (en) * | 2004-03-08 | 2005-09-14 | Siemens Aktiengesellschaft | Turbine blade array |
| EP2009241A2 (en) | 2007-06-27 | 2008-12-31 | Kabushiki Kaisha Toshiba | Interconnected blades of a steam turbine |
| JP2009275700A (en) * | 2008-04-23 | 2009-11-26 | Snecma | Thermomechanical component constituting rotation body rotated around longitudinal axis including at least one abradable ring for seal labyrinth |
| WO2012035658A1 (en) * | 2010-09-17 | 2012-03-22 | 株式会社日立製作所 | Wing arrangement method |
| DE102017115853A1 (en) * | 2017-07-14 | 2019-01-17 | Rolls-Royce Deutschland Ltd & Co Kg | Impeller of a turbomachine |
| US10954794B2 (en) | 2018-05-25 | 2021-03-23 | Rolls-Royce Plc | Rotor blade arrangement |
| US10989227B2 (en) | 2018-05-25 | 2021-04-27 | Rolls-Royce Plc | Rotor blade arrangement |
| US11111816B2 (en) | 2018-05-25 | 2021-09-07 | Rolls-Royce Plc | Rotor blade arrangement |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2018204504A (en) | 2017-06-01 | 2018-12-27 | 三菱日立パワーシステムズ株式会社 | Maximum response prediction method for turbine blade, maximum response prediction system for turbine blade, and turbine including maximum response prediction system for turbine blade |
| JP7503461B2 (en) | 2020-09-10 | 2024-06-20 | 三菱重工エンジン＆ターボチャージャ株式会社 | Turbine wheels, turbines and turbochargers |
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1993
- 1993-03-01 JP JP04003993A patent/JP3272088B2/en not_active Expired - Lifetime
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005226649A (en) * | 2004-02-10 | 2005-08-25 | General Electric Co <Ge> | State-of-the-art fur tree and broach slot configurations for turbine first and second stage buckets and rotor wheels |
| US7905709B2 (en) | 2004-02-10 | 2011-03-15 | General Electric Company | Advanced firtree and broach slot forms for turbine stage 1 and 2 buckets and rotor wheels |
| EP1574666A1 (en) * | 2004-03-08 | 2005-09-14 | Siemens Aktiengesellschaft | Turbine blade array |
| EP2009241A2 (en) | 2007-06-27 | 2008-12-31 | Kabushiki Kaisha Toshiba | Interconnected blades of a steam turbine |
| US8105038B2 (en) | 2007-06-27 | 2012-01-31 | Kabushiki Kaisha Toshiba | Steam turbine, and intermediate support structure for holding row of long moving blades therein |
| JP2009275700A (en) * | 2008-04-23 | 2009-11-26 | Snecma | Thermomechanical component constituting rotation body rotated around longitudinal axis including at least one abradable ring for seal labyrinth |
| WO2012035658A1 (en) * | 2010-09-17 | 2012-03-22 | 株式会社日立製作所 | Wing arrangement method |
| DE102017115853A1 (en) * | 2017-07-14 | 2019-01-17 | Rolls-Royce Deutschland Ltd & Co Kg | Impeller of a turbomachine |
| US10584591B2 (en) | 2017-07-14 | 2020-03-10 | Rolls-Royce Deutschland Ltd & Co Kg | Rotor with subset of blades having a cutout leading edge |
| US10954794B2 (en) | 2018-05-25 | 2021-03-23 | Rolls-Royce Plc | Rotor blade arrangement |
| US10989227B2 (en) | 2018-05-25 | 2021-04-27 | Rolls-Royce Plc | Rotor blade arrangement |
| US11111816B2 (en) | 2018-05-25 | 2021-09-07 | Rolls-Royce Plc | Rotor blade arrangement |
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|---|---|
| JP3272088B2 (en) | 2002-04-08 |
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