JPS6149103A - Turbine rotor blade linking equipment - Google Patents
Turbine rotor blade linking equipmentInfo
- Publication number
- JPS6149103A JPS6149103A JP16992684A JP16992684A JPS6149103A JP S6149103 A JPS6149103 A JP S6149103A JP 16992684 A JP16992684 A JP 16992684A JP 16992684 A JP16992684 A JP 16992684A JP S6149103 A JPS6149103 A JP S6149103A
- Authority
- JP
- Japan
- Prior art keywords
- rotor blade
- faces
- connecting piece
- hole
- turbine rotor
- 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
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【発明の詳細な説明】
〔発明の技術分野〕
本発明はタービン動翼に係り、特に、隣接する動翼相互
間を連結片により全周一群に連結するタービン動翼連結
装置に関する。DETAILED DESCRIPTION OF THE INVENTION [Technical Field of the Invention] The present invention relates to turbine rotor blades, and more particularly to a turbine rotor blade connection device that connects adjacent rotor blades in a group around the entire circumference by connecting pieces.
タービン動翼ｌ翼は通常高速回転で使用されるため、運
転中には大ぎな遠心力が作用する。特に最近のタービン
発電懇の大容但化に伴い、低圧タービンの最終段として
使われるタービン翼には、二極傭として翼長が１ｍを越
すものが出現し、定格回転で翼１本あたりの遠心力が３
００ｔｏｎ以上となるものがある。このような長大な最
終段タービン翼は流体特性から必然的に長手方向に大き
な捩れ形状となるため、前述した過大な遠心力により運
転中には単に引張応力だけでなく、捩り戻りによる捩り
応力が最終段タービン翼に複合して作用し、局部的には
翼材の降伏応力に近い応力が発生する。Since the turbine rotor blades are normally used at high speed rotation, a large centrifugal force acts on them during operation. In particular, with the recent increase in the capacity of turbine power generators, some bipolar turbine blades used as the final stage of low-pressure turbines have a blade length of more than 1 meter, and the number of blades per blade at rated rotation has increased. centrifugal force is 3
There are some that exceed 1,000 tons. Because such a long final stage turbine blade inevitably has a large twist shape in the longitudinal direction due to its fluid characteristics, the excessive centrifugal force mentioned above causes not only tensile stress but also torsional stress due to untwisting during operation. They act in a complex manner on the final stage turbine blade, locally generating stress close to the yield stress of the blade material.
また、一方、振動面においては、タービン翼の長大化に
より翼の固有振動数が低下し、共撮を回避ずべき振動モ
ードが増加する。このにうな背累から長大翼については
、低次から高次までの撮動に対し、振動減衰効果を高め
た連結装置を採用することが疲労強度の面から望まれる
。On the other hand, in terms of vibration, as the turbine blades become longer and larger, the natural frequency of the blades decreases, and the number of vibration modes in which co-photography should be avoided increases. From the viewpoint of fatigue strength, it is desirable to adopt a coupling device with enhanced vibration damping effect for low-order to high-order imaging for this long wing with a long spine.
従来、この種のタービン動翼連結装置どしては第３図（
Ａ）、（Ｂ）、（Ｃ）に示すようなものがめった。Conventionally, this type of turbine rotor blade coupling device was constructed as shown in Fig. 3 (
Things like those shown in A), (B), and (C) were rare.
この第３図（△＞、（Ｂ）、のタービン動翼連結装置は
、隣接する一対の動９２１，１の各長手方向の中間部に
対向する動翼方向く周方向ａ）に突出する突起２を動翼
１と一体に突設し、突起２の先端に球面状底面３ａから
なる穴３を形成し、両切興１．１の穴３．３内に、両端
にほぼ球状突部４ａ、４ａの突設されたバーベル状連結
片４を挿入し、両切’：・：！ １ 、１を相互に緩く
連結するようにしたものである。The turbine rotor blade coupling device shown in FIG. A hole 3 having a spherical bottom surface 3a is formed at the tip of the protrusion 2, and a substantially spherical protrusion 4a is provided at both ends in the hole 3.3 of the both cut-offs 1.1. , insert the protruding barbell-shaped connecting piece 4 of 4a, and cut both sides':・:! 1 and 1 are loosely connected to each other.
このようなタービン＠翼連結装置は、全周の相互の動翼
１を周方向ａに緩く連結するため、動翼１の基本−次モ
ードである周方向振動モードが翼相互の位相により全周
で打消し合い、消滅するという利点をイ１する。また、
高次モードに関しては、連結片４と穴３の接触および高
速により減衰を意図したものである。In such a turbine @ blade coupling device, since the rotor blades 1 on the entire circumference are loosely connected in the circumferential direction a, the circumferential vibration mode, which is the fundamental mode of the rotor blade 1, is caused to change over the entire circumference due to the mutual phase of the blades. It has the advantage of canceling each other out and disappearing. Also,
The higher-order mode is intended to be attenuated by the contact between the connecting piece 4 and the hole 3 and by the high speed.
しかしながら、この連結装置は連結片４と穴３との接触
面が連結片４の両端が球状をなしているため大きく取れ
ず、期待した減衰効果が１写られない欠点がある。ま１
＝、連結片４の中間部がその両端部に比べ剛性が小さく
、前述した動翼１の遠心力による捩れの戻りをある程度
拘束しようとすると、中間部には過大な曲げ応力が作用
し破損するおそれがある。逆に捩れの戻りを完全に許容
する場合には、翼の捩り、曲げ振動に対する制振作用が
失われ、期待した振動減衰効果が得られなくなる。However, this connection device has the disadvantage that the contact surface between the connection piece 4 and the hole 3 cannot be made large because both ends of the connection piece 4 are spherical, and the expected damping effect cannot be obtained. M1
=, the middle part of the connecting piece 4 has lower rigidity than its both ends, and if an attempt is made to restrain the untwisting of the rotor blades 1 to some extent due to the centrifugal force described above, excessive bending stress will act on the middle part, resulting in damage. There is a risk. On the other hand, if the twist is completely allowed to return, the damping effect against twisting and bending vibrations of the blade will be lost, making it impossible to obtain the expected vibration damping effect.
（発明の目的）
本発明は、このような事情を考慮してなされたもので、
強度を損うことなく高い振動減衰効果が得られ、長大岡
の疲労損傷を防ぎ、十分な安全運転をなし得るようにし
たタービン動翼連結装置を提供することを目的とする。(Object of the invention) The present invention was made in consideration of the above circumstances, and
It is an object of the present invention to provide a turbine rotor blade coupling device that can obtain a high vibration damping effect without impairing strength, prevent fatigue damage to the long wall, and enable sufficiently safe operation.
本発明は、各動翼の長手方向中間部に対向する動翼方向
に突出する突起を突設し、突起先端に穴を形成し、隣接
する一対の動翼の穴に両端部が挿入されるように連結片
を配置してなるタービンｆ）Ｊｙ４！連結装置にｄブい
て、前記連結片の上下面をそれぞれ平滑面に形成すると
ともに、連結片の両側面をそれぞれ円弧面、両端部をそ
れぞれ球形面に形成してなり、前記穴を前記連結片とほ
ぼ補形をなす形状に形成したことを特徴どしている。The present invention provides a protrusion that protrudes in the direction of the opposing rotor blade at the longitudinally intermediate portion of each rotor blade, a hole is formed at the tip of the protrusion, and both ends are inserted into the holes of a pair of adjacent rotor blades. A turbine formed by arranging connecting pieces f) Jy4! The connecting device is formed by forming the upper and lower surfaces of the connecting piece into smooth surfaces, and forming both side surfaces of the connecting piece into circular arc surfaces and both end portions into spherical surfaces, and forming the hole into the connecting piece. It is characterized by being formed into a shape that is almost complementary to the above.
以下、本発明の実施例を図面を参照して説明する。なお
、従来のものと同一の構成には同一の符号をイ」ず。Embodiments of the present invention will be described below with reference to the drawings. Note that components that are the same as the conventional one are not designated by the same reference numerals.
第１図（Ａ）、（Ｂ）、（Ｃ）は本発明の実施例を示す
ものであり、各動翼１の長手方向の中間部に突設されて
いる突起２の先端部には穴５が形成されており、この穴
５の底面６は球面状に形成されている。また、この穴５
の内周は、第１図（Ｂ）、（Ｃ）に示すように、上下面
７．８がそれぞれ平滑面に形成されており、両側面９，
１０がそれぞれ円弧面に形成されている。1(A), (B), and (C) show embodiments of the present invention, in which a hole is provided at the tip of a protrusion 2 protruding from the longitudinally intermediate portion of each rotor blade 1. 5 is formed, and the bottom surface 6 of this hole 5 is formed in a spherical shape. Also, this hole 5
As shown in FIGS. 1(B) and 1(C), the inner periphery of the upper and lower surfaces 7.8 are respectively formed as smooth surfaces, and both side surfaces 9,
10 are each formed into a circular arc surface.
一方、隣接する一対の動翼１．１の穴５，５に両端部が
１１１１人される連結片１１は、この穴５の形状とほぼ
補形をなり形状をしている。？ｌ−なわら、連結片１１
の上下面１２．１３はそれぞれ平滑面に形成され、また
両側面１４．１５はそれぞれ円弧面に形成されている。On the other hand, the connecting piece 11 whose both ends are fitted into the holes 5, 5 of the pair of adjacent rotor blades 1.1 has a shape that is almost complementary to the shape of the hole 5. ? l-straw, connecting piece 11
The upper and lower surfaces 12, 13 of each are formed as smooth surfaces, and the both side surfaces 14, 15 are each formed as an arcuate surface.
さらに、連結片１１の両端面１６．１７はそれぞれ球形
面とされ、連結片１１両端部はその側面が前記穴５に対
し０．１〜２．０ｍｍの間隔αをもって挿入されるよう
になっている。Furthermore, both end surfaces 16 and 17 of the connecting piece 11 are each made into a spherical surface, and the side surfaces of both ends of the connecting piece 11 are inserted into the hole 5 with an interval α of 0.1 to 2.0 mm. There is.
つぎに作用について説明する。Next, the effect will be explained.
本タービン動翼連結装置は、動翼１の回転により、まず
、連結片１１の上面１２が、突起２の穴５の上面７に押
付けられ遠心力による面圧を受ける。また、同時に翼１
の捩れの戻りにより、連結片１１の側面１４．１５の穴
５の側面９，１０に接触し、その後の捩れ戻り変形を１
；つ束し、側面１４．１５の円弧部にＪ５いても接触に
よる血圧を受けることになる。特に、連結片１１の端面
１６゜１７と、これに対向する穴５の底面６を球面状に
しているのは動Ｎ１の捩れ戻りの変形を所定の位置まで
、滑かに作動させるためであり、また、側面１４．１５
の曲率形状は、捩れ戻りの拘束による応力集中を緩和す
るものである。このように連結片１１の形状を楕円偏平
球状とし、中間部の剛性を従来に比して大幅に向上させ
たことにより、以下の理由により、強度を損うことなく
、全周において一様なアンツイスト変形を許容し、振動
減衰に必要な所定の面圧を連結片１１ど穴５の当接面で
保持する事がでさ゛る。In this turbine rotor blade coupling device, as the rotor blade 1 rotates, the upper surface 12 of the coupling piece 11 is first pressed against the upper surface 7 of the hole 5 of the protrusion 2 and is subjected to surface pressure due to centrifugal force. Also, at the same time, wing 1
Due to the untwisting, the side faces 14 and 15 of the connecting piece 11 come into contact with the side faces 9 and 10 of the hole 5, and the subsequent untwisting deformation is reduced to 1
; Even if J5 is bundled with the circular arc portion of the side surface 14.15, it will receive blood pressure due to contact. In particular, the end faces 16 and 17 of the connecting piece 11 and the bottom face 6 of the hole 5 facing the end faces 16 and 17 are made spherical in order to smoothly operate the twisting and returning deformation of the dynamic N1 to a predetermined position. , also the side 14.15
The curvature shape of is to relieve stress concentration due to restraint of twisting back. In this way, by making the shape of the connecting piece 11 into an elliptical oblate spherical shape and greatly improving the rigidity of the intermediate part compared to the conventional one, it is possible to achieve uniformity around the entire circumference without sacrificing strength for the following reasons. It is possible to allow untwist deformation and maintain a predetermined surface pressure necessary for vibration damping on the contact surface of the connecting piece 11 and the hole 5.
動翼１のアンツイスト変形を緩く許容し、所定の血圧を
保持するため、連結片１１の中間部と穴５の端部近傍は
周方向ａに平行で間隔Ｃｆ！０．１〜２．０ｍｔｎを有
する構造となっている。この部分はまた連結片１１の両
端部に較べ幅が大きい構造で：ある。動翼１のアンツイ
スト変形は連結片１１との間隔があるため、その間隙ｍ
だけ捩れが戻る。In order to allow loose untwisting deformation of the rotor blade 1 and maintain a predetermined blood pressure, the middle part of the connecting piece 11 and the vicinity of the end of the hole 5 are parallel to the circumferential direction a with an interval Cf! It has a structure having 0.1 to 2.0 mtn. This portion also has a larger width than both ends of the connecting piece 11. Due to the untwist deformation of the moving blade 1, there is a gap m between the moving blade 1 and the connecting piece 11.
Only the twist returns.
そして、穴５と連結片１１との平行部により拘束され所
定の血圧が保持され、全周が一様なアンツイスト変形と
なる。Then, a predetermined blood pressure is maintained by being restrained by the parallel portion of the hole 5 and the connecting piece 11, resulting in a uniform untwist deformation over the entire circumference.
一方、第３図により説明した従来例のような連結片４の
中央部と穴３との接触がない場合、連結片４は穴３内で
端部の曲率範囲内で自由に動き得、全周での拘束が不均
一となり、拘束が強い箇所では過大な応力にＪ二り破損
してしまう。したがって、本発明の実施例のように、連
結片１１の中間部は端部に比べ幅方向の寸法を大きくす
ることが必要である。さらに、アンツイスト変形の拘束
後は連結片１１の中間部には両端部の当面から曲げ応力
が作用する。この曲げ力は翼長ならびに許容アンツイス
トｍにより賃なるが、一般には１〜３ ｔｏｎもの力が
作用する。したがって、連結片中間部の剛性は本発明に
示すように、幅方向で大きくとることにより、曲げ応力
が緩和され強度を損うことなく、振動減衰に必要な所定
の血圧を保持することができる。On the other hand, when there is no contact between the central part of the connecting piece 4 and the hole 3 as in the conventional example explained with reference to FIG. The restraint around the circumference becomes uneven, and in places where the restraint is strong, the excessive stress causes damage. Therefore, as in the embodiment of the present invention, it is necessary that the middle portion of the connecting piece 11 has a larger dimension in the width direction than the end portions. Further, after the untwist deformation is restrained, bending stress acts on the intermediate portion of the connecting piece 11 from both ends. This bending force depends on the blade length and the allowable untwist m, but generally a force of 1 to 3 tons is applied. Therefore, as shown in the present invention, by increasing the rigidity of the intermediate portion of the connecting piece in the width direction, bending stress is alleviated, and a predetermined blood pressure necessary for vibration damping can be maintained without loss of strength. .
前述したような初期の面圧を受けた状態で動翼１の振動
が励起されても、本実施例によれば、連結片１１および
穴５の接触面における摩擦により減衰され、振動応力は
極めて低く押えることができる。特に本実施例の構造は
、周方向ａの振動に対しては従来より連結片１１の穴５
に対する接触面積が増しただＧプでなく、連結片１１の
中間部の剛性が大きく、端部における衝突による減衰が
連結片１１の強度を損うことなく作用できるため、極め
て大きな減衰効果が得られる。さらに軸方向振動、捩り
振動に対しても初期面圧下におけるｆ享擦減衰が高く、
かつ連結片１１と穴５にお【プる間隙によりその振動減
衰効果を最適にすることが可能である。Even if the vibration of the rotor blade 1 is excited under the initial surface pressure as described above, according to this embodiment, it is attenuated by the friction at the contact surface between the connecting piece 11 and the hole 5, and the vibration stress is extremely reduced. Can be held low. In particular, the structure of this embodiment is more effective against vibrations in the circumferential direction a than in the past through the hole 5 of the connecting piece 11.
Although the contact area has increased, the rigidity of the middle part of the connecting piece 11 is large, and the damping due to the collision at the end can act without damaging the strength of the connecting piece 11, so an extremely large damping effect can be obtained. . Furthermore, the f-f friction damping under the initial surface pressure is high for axial vibrations and torsional vibrations,
Furthermore, the vibration damping effect can be optimized by the gap between the connecting piece 11 and the hole 5.
第３図は連結片とザグリ穴の間隙αに対する接合部の応
力σと振動減衰率δを示すものである。FIG. 3 shows the stress σ and vibration damping rate δ of the joint with respect to the gap α between the connecting piece and the counterbore hole.
丈なわら、連結片１１と穴５との間隙０を横軸にそれに
対する接合部の応力（面圧σ）と振動減衰率δを縦軸に
表示したものである。連結片１１の接合部における応力
σは、間隙αのσ吊が増すほど動翼１のアンツイスト変
形を許容するため低下する。この応力σは低いほど強度
的にはよいが、零に近づくと接触拘束がなくなり、振動
減衰（連結による構造減衰）δがなくなって、逆に動翼
１の振動応力が増加する。この振動減衰率δは連結部の
面圧に左右され、本実施例の連結片１１では、第２図に
飯ずように０．１〜２．０ｍｍ間隙で太きくなる。これ
は振動振幅に対し、ある間隙内で摩擦および衝突による
減衰効果が卓越づ“るためであり、連結片１１の構造に
より決まるものである。The horizontal axis represents the gap 0 between the connecting piece 11 and the hole 5, and the vertical axis represents the stress (surface pressure σ) and vibration damping rate δ at the joint. The stress σ at the joint of the connecting piece 11 decreases as the σ of the gap α increases, since the untwisted deformation of the rotor blade 1 is allowed. The lower this stress σ is, the better the strength is, but when it approaches zero, the contact restraint disappears, vibration damping (structural damping due to connection) δ disappears, and the vibration stress of the rotor blade 1 increases. This vibration damping rate δ depends on the surface pressure of the connecting portion, and in the connecting piece 11 of this embodiment, it becomes thicker at a gap of 0.1 to 2.0 mm, as shown in FIG. This is because the damping effect of friction and collision becomes dominant within a certain gap with respect to the vibration amplitude, and is determined by the structure of the connecting piece 11.
したがって、本実施例の連結片１１では、０． １〜２
．０＃の間隙とすることで、強度的にも余裕があり、振
動減衰効果が高い連結装置とすることができる。Therefore, in the connecting piece 11 of this embodiment, 0. 1-2
．． By setting the gap to 0#, it is possible to obtain a coupling device with sufficient strength and a high vibration damping effect.
以上説明したように、本発明に係るタービン動翼連結装
置は各動翼の長手方向中間部に対向する動翼方向に突出
する突起を突設し、突起先端に穴を形成し、隣接する一
対の動翼の穴に両端部が挿入されるように連結片を配置
してなるタービン動Ｒ連結装置において、前記連結片の
上下面をそれぞれ平滑面に形成するとともに、連結片の
両側面゛をそれぞれ円弧面、両端面をそれぞれ球形面に
形成してなり、前記穴を前記連結片とほぼ補形をなす形
状に形成して、連結片仝休をほぼ楕円偏平球状にし、連
結片の中間部も穴の内周面と接触するようにしたので、
連結片の強度をＩＱうことなく高い振動減衰効果が得ら
れ、長大翼の疲労損１烏を防ぎ十分安全な運転を行なう
ことができるという優れた効果を奏する。As explained above, the turbine rotor blade coupling device according to the present invention includes a protrusion protruding from the longitudinally intermediate portion of each rotor blade that protrudes in the direction of the opposing rotor blade, a hole is formed at the tip of the protrusion, and a pair of adjacent rotor blades In a turbine dynamic R coupling device in which a connecting piece is arranged such that both ends thereof are inserted into holes in a rotor blade, the upper and lower surfaces of the connecting piece are respectively formed as smooth surfaces, and both side surfaces of the connecting piece are formed as smooth surfaces. Each of the connecting pieces has a circular arc surface and both end faces are formed as spherical surfaces, and the hole is formed in a shape that is substantially complementary to the connecting piece, so that the connecting piece rests in an approximately elliptical oblate spherical shape, and the intermediate part of the connecting piece Since it also made contact with the inner peripheral surface of the hole,
A high vibration damping effect can be obtained without changing the strength of the connecting pieces, and the excellent effect is that fatigue loss of the long wings can be prevented and sufficiently safe operation can be performed.
第１図（Ａ）は本発明に係るタービン動翼連結装置の実
ＩＪ色例を示ず一部断面正面図、第１図（Ｂ）、（Ｃ）
はそれぞれ第１図（Ａ）のＢ−Ｂ線Ｊ３よびＣＣＦＡに
よる断面図、１２図は第１図の装置による間隙に対ダる
応力および振動減衰率を示すグラフ、？Ａ３図（Ａ）は
従来のタービン動Ｌ”Ｊ連結装置を示す一部断面正面図
、第３図（Ｂ）は第３図（Ａ）の断面図、第３図（Ｃ）
は第３図（Ａ）の連結片の正面図である。
１・・・動ひマ、２・・・突起、３，５・・・穴、４，
１１・・・連結片。
代理人弁理士 則近恵佑（ほか１名）茶 ｌ 図
（Ａ）
第 ２ 図
Ａ”ｌ隙（ｃｔ） −FIG. 1(A) is a partially sectional front view without showing an actual IJ color example of the turbine rotor blade coupling device according to the present invention, and FIGS. 1(B) and (C)
are sectional views taken along line B-B J3 and CCFA in FIG. 1(A), respectively, and FIG. 12 is a graph showing the stress applied to the gap and the vibration damping rate by the device in FIG. 1, and ? Figure A3 (A) is a partially sectional front view showing a conventional turbine dynamic L"J coupling device, Figure 3 (B) is a sectional view of Figure 3 (A), Figure 3 (C)
is a front view of the connecting piece of FIG. 3(A). 1... Moving time, 2... Protrusion, 3, 5... Hole, 4,
11...Connection piece. Representative Patent Attorney Keisuke Norichika (and 1 other person) Figure (A) Figure 2 A"l gap (ct) -
Claims (1)
突起を突設し、突起先端に穴を形成し、隣接する一対の
動翼の穴に両端部が挿入されるように連結片を配置して
なるタービン動翼連結装置において、前記連結片の上下
面をそれぞそれ平滑面に形成するとともに、連結片の両
側面をそれぞれ円弧面、両端面をそれぞれ球形面に形成
してなり、前記穴を前記連結片とほぼ補形をなす形状に
形成したことを特徴とするタービン動翼連結装置。A protrusion protruding in the direction of the opposing rotor blade is provided in the longitudinal middle part of each rotor blade, a hole is formed at the tip of the protrusion, and a connecting piece is inserted so that both ends are inserted into the holes of a pair of adjacent rotor blades. In the turbine rotor blade coupling device, the upper and lower surfaces of the coupling piece are each formed into a smooth surface, and both side surfaces of the coupling piece are each formed into an arcuate surface, and both end surfaces are each formed into a spherical surface. . A turbine rotor blade coupling device, characterized in that the hole is formed in a shape substantially complementary to the coupling piece.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP16992684A JPS6149103A (en) | 1984-08-16 | 1984-08-16 | Turbine rotor blade linking equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP16992684A JPS6149103A (en) | 1984-08-16 | 1984-08-16 | Turbine rotor blade linking equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS6149103A true JPS6149103A (en) | 1986-03-11 |
Family
ID=15895504
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP16992684A Pending JPS6149103A (en) | 1984-08-16 | 1984-08-16 | Turbine rotor blade linking equipment |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS6149103A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4767273A (en) * | 1987-02-24 | 1988-08-30 | Westinghouse Electric Corp. | Apparatus and method for reducing blade flop in steam turbine |
| EP1944466A1 (en) * | 2007-01-10 | 2008-07-16 | Siemens Aktiengesellschaft | Coupling of two rotor blades |
| GB2449493A (en) * | 2007-05-25 | 2008-11-26 | Rolls Royce Plc | A vibration damper assembly |
| US20110274549A1 (en) * | 2010-05-06 | 2011-11-10 | General Electric Company | Blade having asymmetrical mid-span structure portions and related bladed wheel structure |
| EP1515001A3 (en) * | 2003-09-12 | 2012-07-04 | Alstom Technology Ltd | Blade to blade connection in a turbomachine |
-
1984
- 1984-08-16 JP JP16992684A patent/JPS6149103A/en active Pending
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4767273A (en) * | 1987-02-24 | 1988-08-30 | Westinghouse Electric Corp. | Apparatus and method for reducing blade flop in steam turbine |
| EP1515001A3 (en) * | 2003-09-12 | 2012-07-04 | Alstom Technology Ltd | Blade to blade connection in a turbomachine |
| EP1944466A1 (en) * | 2007-01-10 | 2008-07-16 | Siemens Aktiengesellschaft | Coupling of two rotor blades |
| GB2449493A (en) * | 2007-05-25 | 2008-11-26 | Rolls Royce Plc | A vibration damper assembly |
| GB2449493B (en) * | 2007-05-25 | 2009-08-12 | Rolls Royce Plc | Vibration damper assembly |
| US8231352B2 (en) | 2007-05-25 | 2012-07-31 | Rolls-Royce Plc | Vibration damper assembly |
| US20110274549A1 (en) * | 2010-05-06 | 2011-11-10 | General Electric Company | Blade having asymmetrical mid-span structure portions and related bladed wheel structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6341941B1 (en) | Steam turbine | |
| US6568908B2 (en) | Steam turbine | |
| US6375420B1 (en) | High efficiency blade configuration for steam turbine | |
| US4621979A (en) | Fan rotor blades of turbofan engines | |
| US6065938A (en) | Rotor for a turbomachine having blades to be fitted into slots, and blade for a rotor | |
| US2643853A (en) | Turbine apparatus | |
| US5120197A (en) | Tip-shrouded blades and method of manufacture | |
| JPS6149103A (en) | Turbine rotor blade linking equipment | |
| GB2106192A (en) | Turbomachine blade | |
| JPH0475361B2 (en) | ||
| EP0541911B1 (en) | Method for improving the capability of a body to withstand stress in rotation | |
| US3778190A (en) | Bucket cover attachment | |
| JPH045402A (en) | Integral shroud vane | |
| JP3782161B2 (en) | Rotor coupling device for axial flow turbine | |
| JPH06117201A (en) | Assembly method for turbine moving blade | |
| JPH0491302A (en) | Blade of axial turbine | |
| CN112173076B (en) | Blade root structure | |
| JPS6045285B2 (en) | Moving blade coupling device | |
| JPS58110801A (en) | Connecting device for moving blade of turbine | |
| JPS61210855A (en) | Rotary electric machine | |
| JPH0861001A (en) | Turbine step structure | |
| JPS5983548A (en) | Magnetic pole structure for rotary electric machine | |
| JPS59213249A (en) | Rotor for turbine generator | |
| JPH02241903A (en) | Steam turbine blade | |
| JPS5923002A (en) | Tie-wire connecting structure |