JPS59108802A - Moving blade cover installing device - Google Patents

Moving blade cover installing device

Info

Publication number
JPS59108802A
JPS59108802A JP21687082A JP21687082A JPS59108802A JP S59108802 A JPS59108802 A JP S59108802A JP 21687082 A JP21687082 A JP 21687082A JP 21687082 A JP21687082 A JP 21687082A JP S59108802 A JPS59108802 A JP S59108802A
Authority
JP
Japan
Prior art keywords
tenon
blade
moving blade
cover
deformation
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
Application number
JP21687082A
Other languages
Japanese (ja)
Inventor
Hisao Ogata
尾形 久男
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Toshiba Corp
Original Assignee
Toshiba Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Toshiba Corp filed Critical Toshiba Corp
Priority to JP21687082A priority Critical patent/JPS59108802A/en
Publication of JPS59108802A publication Critical patent/JPS59108802A/en
Pending legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12Blades
    • F01D5/22Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225Blade-to-blade connections, e.g. for damping vibrations by shrouding

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

PURPOSE:To heighten both rigidity and vibration damping effect of a group of moving blades by forming a plurality of indents at the crest part of a tenon of a moving blade cover, which is inserted into a hole formed on the moving blade, so that untwisting deformation of each blade under rotation becomes uniform. CONSTITUTION:The tenon of a moving blade cover is inserted into a lateral hole 3b formed at the trailing edge side of the moving blade. A plurality of indents 11 are formed on the crest part of the tenon in such a manner that the indent 11 is shallower as it is closer to the trailing edge 10 of the blade. The tip of the tenon is expanded as shown by the broken lines in the figure in order to fix the moving blade cover. By providing a plurality of indents like this, the sectional rigidity of the caulked part becomes almost equal in both longitudinal and lateral directions, thereby keeping the untwisting deformation not-too-tight and uniform during rotation.

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の連結装置に係わり、特にタービ
ン動翼の先端に装着されるカバー取付は構造を改良した
動翼カバーの取付は装置に関する。
Detailed Description of the Invention [Technical Field of the Invention] The present invention relates to a coupling device for turbine rotor blades, and particularly relates to a device for attaching a rotor blade cover with an improved structure for attaching a cover attached to the tip of a turbine rotor blade. .

〔発明の技術的背景とその問題点〕[Technical background of the invention and its problems]

一般にタービン低圧最終段落に使用される動翼は羽根の
翼長が長くかつ翼の長さ方向に大きな捩れを有しており
、回転中には遠心力による引張り変形だけでなく、捩れ
の戻り変形が生じる。さらに、羽根の翼長が長いことに
より固有振動数が低下し、連転回転数で共振を避けるべ
き固有振動数モードが増加し、必然的に振動問題が発生
する。
In general, the rotor blades used in the low-pressure final stage of turbines have long blades and large torsions in the blade length direction, and during rotation they undergo not only tensile deformation due to centrifugal force, but also return deformation due to torsion. occurs. Furthermore, due to the long blade span, the natural frequency decreases, and the number of natural frequency modes that should avoid resonance at continuous rotation speed increases, inevitably causing vibration problems.

このような変形および振動強度の問題を解決するために
、翼群構造の剛性を増大しかつ振動減衰効果の俊れたタ
ービン動翼の連結装置を用いることが心安である。
In order to solve such problems of deformation and vibration intensity, it is safe to use a turbine rotor blade coupling device that increases the rigidity of the blade group structure and has an excellent vibration damping effect.

従来この柚の連結装置としては、第1図および第2図に
示すように隣接する兵1の翼先端部2の貫通した横穴3
にカバ一本体4の側面より突き出たテノン5 + 6 
’c 挿入し、一方のテノン5の頂部を翼と完全にカシ
メて固定し、他方のテノン6頂部を翼にルーズカシメ固
定することで翼群の剛性と振動減衰効果の向上を図った
ものが使用されている。
Conventionally, as shown in FIGS. 1 and 2, this connection device has been made by using a horizontal hole 3 that passes through the wing tip 2 of an adjacent soldier 1.
Tenon 5 + 6 protrudes from the side of the cover body 4.
'c is inserted, and the top of one Tenon 5 is completely caulked and fixed to the wing, and the top of the other Tenon 6 is loosely caulked to the wing, thereby improving the rigidity of the blade group and the vibration damping effect. has been done.

しかしながら、従来の連結装置で特にカバー取付は部の
ルーズカシメ部については、テノン頂部端面をポンチで
カシメる方法が一般的に採用されているが、この方法で
はクリアランスの管理が困難であり、以下の理由によシ
強度的に問題が生ずることがある。ポンチによるカシメ
量のばらつきは各其とカバーの隙間が一様とならず、上
述の回転中の捩p戻シの変形(アンツイスト)が隙間の
大きな箇所では大きくなり、小さな箇所ではほとんど変
形せず、結果的に容入の変形が異なることで局所的に翼
の変形が重量され、その箇所にあるカバー付根部に過大
応力が発生し、最恕な場合には割れ等の破損が発生する
こともあり、強度全損なう欠点があった。
However, in conventional coupling devices, especially for the loose caulking part of the cover installation part, the method of caulking the top end face of the tenon with a punch is generally adopted, but it is difficult to manage the clearance with this method, and the following For some reason, problems may arise in terms of strength. The variation in the amount of caulking caused by the punch is that the gap between each punch and the cover is not uniform, and the deformation (untwisting) of the untwisted screw during rotation becomes large in areas with large gaps, and hardly deforms in areas with small gaps. As a result, the difference in the deformation of the container causes the deformation of the blade to be localized, causing excessive stress at the base of the cover at that location, and in the worst case, causing damage such as cracking. As a result, there was a drawback that the strength was completely lost.

このような欠点を解決することを意図したものとして特
公昭53−8010号公報に開示された動翼カックー取
付装置が挙げられる。この動翼カバー取付装置は動翼カ
バーの取付は部であるルーズカシメ側のテノン部の頂部
に第3図(A)および(B)に示すような浴′楢型くほ
み7を形成し、最先端部の横穴3に挿入し、翼と間隙人
をもつよう、くほみ頂部8を全周にわたって押し広げ、
翼にゆるく固定することにより、回転中のアンツイスト
iる程度許容し間隙を一定とすることで全周全ての翼の
アンツイスト変形を一様とし、応力を緩和するとともに
ゆるい固定により振動減衰効果をもたらそうというもの
である。
A moving blade cuckoo attachment device disclosed in Japanese Patent Publication No. 53-8010 is intended to solve these drawbacks. This rotor blade cover attachment device forms a bath-shaped recess 7 as shown in FIGS. 3(A) and (B) at the top of the tenon part on the loose caulking side, which is the part for attaching the rotor blade cover. Insert it into the horizontal hole 3 at the leading edge, and spread the top part 8 of the blade all the way around so that it has wings and gaps.
By loosely fixing it to the blade, it allows some degree of untwisting during rotation, and by keeping the gap constant, the untwisting deformation of the blade is uniform throughout the entire circumference, which relieves stress and has a vibration damping effect due to the loose fixation. It is intended to bring about.

即ちルーズカシメ側テノンの端部に設けられた浴槽型α
み部の頂部を全局にわたって押し広げる構造が特公昭5
3−8010号公報に記載された発明の要点であり、こ
の構造はカバーテノン部が円柱状もしくは材質的に柔か
いカバーテノンに関しては強度上問題なく適用できる。
In other words, the bathtub type α provided at the end of the tenon on the loose caulking side.
The structure in which the top of the groove is spread out over the entire station was developed in the 1970s.
This is the gist of the invention described in Publication No. 3-8010, and this structure can be applied to cover tenons whose cover tenon portions are cylindrical or whose material is soft without any problems in terms of strength.

しかしながら一般に動μカバーの取付部であるテノンは
、カッマ一本体の遠心力と翼のアンライストラある程度
拘束するため曲げ力が作用し、従って強度的にib面を
大きくかつテノン部の曲げ剛性を大きくするよう横長の
楕円形状を採用L、かつ耐力の優れた硬度を有する12
Cr鋼が使用される。このような楕円型テノンに上述の
発明を適用すると、その形状から断面の縦方向および横
方向の剛性が異なり、全周を一様に押し広げることは困
難である。つ゛ま9横方向の押し広げに対しては縦方向
で圧縮が、又縦方向の押し広げには横方向で圧縮が作用
し、両方を押し広げた場合、どちらか一方に過大な応力
と歪が生じ、不拘−ガ歪分布と寿り、特に頂部が薄く剛
性が小さいテノン部では割れが生ずることになる。この
ような動翼カバーのルーズ側カシメ部の強度不足、割れ
は回転中の翼のアンツイストによる曲げ変形をルーズ側
のカシメ部で拘束することが難かしく、やはり従来と同
様に過大応力の発生をカバーテノン部にもたらし、損傷
のおそれを引きおこすものである。
However, in general, the tenon, which is the attachment part of the dynamic μ cover, is subject to bending force because it restrains the centrifugal force of the cutter body and the unreinforced blade to some extent, so the ib surface is increased in terms of strength and the bending rigidity of the tenon part is increased. Adopts a horizontally elongated oval shape L, and has hardness with excellent yield strength 12
Cr steel is used. When the above-mentioned invention is applied to such an elliptical tenon, the stiffness of the cross section in the longitudinal and lateral directions differs due to its shape, and it is difficult to uniformly spread the entire circumference. 9. Compression acts in the vertical direction when pushing and spreading in the horizontal direction, and compression acts in the horizontal direction when pushing and spreading in the vertical direction. If both are pushed and spread, excessive stress and strain will be applied to one of them. This results in unrestrained strain distribution and life, and cracks occur particularly in the tenon portion where the top portion is thin and has low rigidity. This lack of strength and cracking in the loose caulking part of the rotor blade cover is due to the fact that it is difficult to restrain the bending deformation caused by the untwisting of the rotating blade at the loose caulking part, and excessive stress occurs as in the past. This may cause damage to the cover tenon.

〔発明の目的〕[Purpose of the invention]

本発明の目的は、前述の従来技術に依る問題点を解決し
、動翼カバーの取付は部であるルーズカシメ側テノン部
の強度を損なうことなく、ゆるく(ルーズに)翼にカシ
メ固定し、回転中の全周容置のアンツイスト変形を一様
にゆるく保持し、翼群の即]性増加および振動減衰効果
を適切に企図することができる動翼カッ々−の取付は装
置を提供することにある。
An object of the present invention is to solve the problems caused by the above-mentioned prior art, and to fix the rotor blade cover loosely (loosely) to the blade without impairing the strength of the tenon part on the loosely caulked side. To provide a device for attaching a rotor blade that can uniformly and loosely maintain untwisted deformation of the entire circumference of the rotor blade, and appropriately plan for increasing the immediacy of the blade group and achieving a vibration damping effect. It is in.

〔発明の植装〕[Invention planting]

本発明に依れば前述した目的を達成するために、動翼カ
バー取付は装置は、カバ一本体の両側面に一体に形成さ
れたテノンの頂部に複数のくほみを形成した構造を有す
るものである。
According to the present invention, in order to achieve the above-mentioned object, a moving blade cover mounting device has a structure in which a plurality of indentations are formed at the top of a tenon integrally formed on both sides of a cover body. It is something.

〔発明の実施例〕[Embodiments of the invention]

以下本発明の好ましい実施例?:第4図乃至第6図を参
照して説明する。第4図乃至第6図において第1図乃至
第3図に示された部分と同一の部分については同一の符
号を符し、詳細な説明を省略する。
What are the preferred embodiments of the present invention? : This will be explained with reference to FIGS. 4 to 6. The same parts in FIGS. 4 to 6 as those shown in FIGS. 1 to 3 are designated by the same reference numerals, and detailed description thereof will be omitted.

第4図は本発明に依る動翼カバー取付は装置を具備した
動翼先端の拡大図である。動翼の先端部2の前縁側に横
穴3aが、後縁側に横穴3bがそれぞれ形成されている
。力、S+4が、隣接する翼先端部の前縁および後縁側
を被覆するように設けられており、カッマー4の側部に
は、横穴3aに完全にカシメ固定されるテノン5と、横
穴3bにルーズカシメ固定されるテノン6がカバ一本体
と一体に形成されている。テノン5の先端部は従来と同
様の方法で機械的にカシメられる。
FIG. 4 is an enlarged view of a rotor blade tip equipped with a rotor blade cover attachment device according to the present invention. A horizontal hole 3a is formed on the leading edge side of the tip portion 2 of the rotor blade, and a horizontal hole 3b is formed on the trailing edge side. A force S+4 is provided to cover the leading edge and trailing edge sides of the adjacent wing tips, and a tenon 5 is provided on the side of the cummer 4 to be completely caulked and fixed in the side hole 3a, and a tenon 5 is attached to the side hole 3b. A tenon 6 that is loosely crimped and fixed is formed integrally with the cover body. The tip of Tenon 5 is mechanically caulked in the same manner as in the past.

このように完全カシメ側を前述の従来例では真前線およ
び後縁のどちらも許容していたのを翼前縁側に固定した
のは、翼先端部のアンツイスト変形は第5図に示すよう
に翼前縁9よりも後縁10の方が変形が大きく、かつ翼
断面の剛性は前縁側が太きいため、完全カシメ側のテノ
ンを翼後縁部にするとカバ一本体は翼後縁部に追従した
変形となり、翼剛性の大きな前縁側の変形をある8度押
さえるルーズカシメ側テノンに過大な曲げ応力が発生し
かつ翼前縁側に隙間が生じ、この隙間に水滴が付着し、
テノンは根部に水滴によるエロージョンを引きおこす等
強度が損なわれるからである。
In this way, the completely caulked side was fixed on the leading edge side of the wing, whereas in the conventional example described above, both the true front line and the trailing edge were allowed. The deformation of the trailing edge 10 is larger than that of the leading edge 9, and the rigidity of the wing cross section is greater on the leading edge side, so if the tenon on the fully caulked side is placed on the trailing edge of the wing, the cover body will be placed on the trailing edge of the wing. As a result, excessive bending stress is generated in the tenon on the loose caulking side, which suppresses the deformation by a certain 8 degrees on the leading edge side where the blade has greater rigidity, and a gap is created on the leading edge side of the blade, and water droplets adhere to this gap.
This is because tenon causes erosion due to water droplets at the root, resulting in loss of strength.

これに対し本願のように翼前縁部を完全にカシメ名よう
にすれば、前述の問題は生ぜず、本発明に依るカバー取
付装置を一層有効に使用できる。
On the other hand, if the leading edge of the blade is completely caulked as in the present invention, the above-mentioned problem does not occur and the cover attachment device according to the present invention can be used more effectively.

本発明は動翼カッ9−の取付部であるルーズカシメ側テ
ノンの構造および真横穴へ挿入した時の配置を改良する
ものであるが、これを第6図に詳細に示す。即ちルーズ
カシメ側テノン6の先端は複数のカシメ用びみ11ヲ有
し、この窪み11は少なくとも2個先端に形成される。
The present invention improves the structure of the tenon on the loosely caulked side, which is the attachment part of the rotor blade cup 9-, and its arrangement when inserted into the hole right next to it, which is shown in detail in FIG. That is, the tip of the loose caulking side tenon 6 has a plurality of caulking recesses 11, and at least two of these depressions 11 are formed at the tip.

窪み11の深さは翼後縁側の方の窪みを浅くなるように
形成し、翼アンツイストによる変形がすべて窪みカシメ
部で均一に当たるよう調整される。第6図に示される通
り窪み底部の傾斜角θは0.5度乃至3度の範囲であり
、この角度θは只の長さ、捩れ角により決定され任意に
選択される。
The depth of the recess 11 is adjusted so that the recess on the trailing edge side of the blade becomes shallower, so that all deformation caused by untwisting the blade is uniformly applied to the recess caulking portion. As shown in FIG. 6, the inclination angle θ of the bottom of the recess is in the range of 0.5 degrees to 3 degrees, and this angle θ is determined by the length and twist angle and is arbitrarily selected.

本発明に依るルーズカシメ側テノンは翼後縁部の横穴3
bの前縁側側面と接触するように配置され、その後テノ
ンの先端は破線で示したように傾斜状に押し広けられる
。ル−ズカシメ側テノンを横穴にこのように配置すれば
、翼のアンツイストが前縁側に寄りながら変形するため
、テノンに対し前縁側の穴側面は離れる方向に、後縁側
の穴側面は近ずく方向に移動し、従ってテノンと横穴3
bの間隙を最小にし、意図するアンツイスト角に押える
ことが可能である。なお当然のことながらルーズカシメ
側テノンを穴の中央に配置し、穴の両側面との間の間隙
を同一にした場合は、意図するアンツイスト角に保持す
るためには間隙を広げる必要があり、翼の大間の強度が
低下し、逆に間隙をそのままにするとアンツイストが押
えられ、テノン部の強度が低下することとなる。
The loose caulking side tenon according to the present invention has a horizontal hole 3 in the trailing edge of the wing.
The tip of the tenon is placed in contact with the side surface of the leading edge of b, and then the tip of the tenon is pushed out in an inclined manner as shown by the broken line. If the tenon on the loose caulking side is placed in the side hole in this way, the untwist of the wing will deform while moving closer to the leading edge, so the side of the hole on the leading edge side will move away from the tenon, and the side of the hole on the trailing edge will move closer. direction, therefore Tenon and Yokoana 3
It is possible to minimize the gap b and maintain the intended untwist angle. Of course, if the tenon on the loose caulking side is placed in the center of the hole and the gap between it and both sides of the hole is the same, it is necessary to widen the gap in order to maintain the intended untwist angle. The strength of the blade's gap will decrease, and if the gap is left as is, the untwist will be suppressed and the strength of the tenon will decrease.

ルーズカシメ側テノンの先端に複数の窪みを有し、テノ
ンの先端ヲ昼に対しゆるくカシメることは従来に比ベカ
シメ部の断面1411性が縦方向および横方向ともほぼ
同等となり、周方向で均一な歪変形となるため応力が緩
和され強度が増す。なお破線12で示したようにカシメ
後のテノン先端部は従来と異な#)直線を呈さない。こ
れはテノンに住じる応力で遠心力は穴の内側面で受けと
め、アンツイスト力はテノン側面で保持されるため、テ
ノン先端部を全周囲均等に押し広ける必要がないためで
あり、又全周囲にわたる押し広げはかえって強度を損な
うからである。
The tip of the tenon on the loose crimping side has multiple depressions, and the tip of the tenon is crimped loosely against the day. Compared to the conventional method, the cross-sectional 1411 property of the crimped part is almost the same in the vertical and horizontal directions, and it is uniform in the circumferential direction. Due to strain deformation, stress is relaxed and strength increases. As shown by the broken line 12, the tip of the tenon after caulking does not have a straight line unlike the conventional one. This is because the centrifugal force, which is the stress that resides in the Tenon, is received by the inner surface of the hole, and the untwisting force is held by the side surface of the Tenon, so there is no need to spread the tip of the Tenon evenly around the entire circumference. This is because spreading the material around the entire circumference will actually reduce the strength.

〔発明の効果〕〔Effect of the invention〕

以上説明した通υ、本発明に依る#翼カバー取付装置は
、ルーズカシメ側テノンの先端部に複数のくほみを有し
、くほみの深さは後縁側のくぼみの方を浅くし、又翼の
横穴の前縁側内側面と接触するようにテノンを配置する
ために、回転中のアンツイストをルーズカシメ側テノン
で均等にゆるく保持し応力を緩和することができ、更に
カシメによる強度低下を防ぎ適切な振動減衰効果と強度
を有するものである。
As explained above, the wing cover mounting device according to the present invention has a plurality of notches at the tip of the tenon on the loose caulking side, and the depth of the notches is shallower on the trailing edge side, In addition, since the tenon is placed so as to be in contact with the inner surface of the leading edge side of the side hole of the wing, untwisting during rotation can be held evenly and loosely with the tenon on the loose caulking side, thereby relieving stress, and further reducing the strength caused by caulking. It has an appropriate vibration damping effect and strength.

【図面の簡単な説明】[Brief explanation of drawings]

第1図は従来の動翼カバー取付は装置を示す斜視図、第
2図は第1図の取付は装置のテノンカシメ部を示しだ図
、第3図体)および(B)は特公昭53−8010号公
報に開示された動翼カバー取付は装置の詳細図、第4図
は本発明に依る動翼カッ々−取付は装置の一実施例を示
すものでテノンカシメ部を示した図、第5図はアンツイ
スト変形を説明するもので翼先端の羽根形状を示す図、
第6図(A)および(B)は本発明に依る動翼力・々−
取付は装置の詳細図である。 1・・・翼、2・・・翼先端部、k、 3b・・・横穴
、4・・・力六−15,6・・・テノン、7.11・・
・<ホミ。 出願人代理人  波 多 野    次第 7 図 第 2 図 第3 図 (B)
Figure 1 is a perspective view showing the equipment with the conventional rotor blade cover installed, Figure 2 is a view showing the tenon caulking part of the equipment with the installation of Figure 1, Figure 3) and (B) are Japanese Patent Publication No. 53-8010. The rotor blade cover attachment disclosed in the publication is a detailed view of the device, FIG. 4 is a diagram showing an embodiment of the rotor blade cover attachment according to the present invention and shows the tenon caulking part, and FIG. This figure explains the untwist deformation and shows the shape of the blade at the tip of the wing.
FIGS. 6(A) and 6(B) show the rotor blade force and the like according to the present invention.
The installation is a detailed view of the device. 1...Wing, 2...Blade tip, k, 3b...Horizontal hole, 4...Rikiroku-15, 6...Tenon, 7.11...
・<Homi. Applicant's agent Shizuo Hatano 7 Figure 2 Figure 3 (B)

Claims (1)

【特許請求の範囲】 1、カバ一本体と、前記カバ一本体の両側面に一体ある
いは一体的に形成され、動翼に形成された穴へ挿入され
る複数のテノンとを有し、前記テノンの?)チの少なく
とも一方の側のテノンの頂部に複数の鵠みを形成したこ
と全特徴とする動翼カバー取付は装置。 2、幽みはルーズカシメ側テノンに形成されることを特
徴とする特許請求の範囲第1項記載の取付は装置。 3、ルーズカシメ側テノンは動翼後縁部に形成された穴
の前縁側内側面と接触するように配置されることを特徴
とする特許請求の範囲第2項記載の取付は装置。
[Scope of Claims] 1. A cover main body, and a plurality of tenons formed integrally or integrally on both sides of the cover main body and inserted into holes formed in the rotor blade, the tenons of? ) The blade cover mounting device is characterized by having multiple grooves formed on the top of the tenon on at least one side of the blade. 2. The mounting device as claimed in claim 1, wherein the recess is formed on the loose caulking side tenon. 3. The attachment device according to claim 2, wherein the tenon on the loose caulking side is arranged so as to be in contact with the inner surface on the leading edge side of the hole formed in the trailing edge of the rotor blade.
JP21687082A 1982-12-13 1982-12-13 Moving blade cover installing device Pending JPS59108802A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP21687082A JPS59108802A (en) 1982-12-13 1982-12-13 Moving blade cover installing device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP21687082A JPS59108802A (en) 1982-12-13 1982-12-13 Moving blade cover installing device

Publications (1)

Publication Number Publication Date
JPS59108802A true JPS59108802A (en) 1984-06-23

Family

ID=16695198

Family Applications (1)

Application Number Title Priority Date Filing Date
JP21687082A Pending JPS59108802A (en) 1982-12-13 1982-12-13 Moving blade cover installing device

Country Status (1)

Country Link
JP (1) JPS59108802A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9016974B2 (en) 2009-07-02 2015-04-28 Vertical Leisure Ltd Coupling device

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9016974B2 (en) 2009-07-02 2015-04-28 Vertical Leisure Ltd Coupling device

Similar Documents

Publication Publication Date Title
US20010024614A1 (en) Blade assembly with damping elements
JP4869616B2 (en) Steam turbine blade, steam turbine rotor, steam turbine using the same, and power plant
RU2375589C2 (en) Turbine rotor, device and method to produce it
US8231352B2 (en) Vibration damper assembly
US6065938A (en) Rotor for a turbomachine having blades to be fitted into slots, and blade for a rotor
US6860722B2 (en) Snap on blade shim
DE69727727T2 (en) Damping element and seal for turbine blades
DE602005001085T2 (en) Rotor blade with rod-shaped damper element
US7024744B2 (en) Frequency-tuned compressor stator blade and related method
EP1041248A2 (en) Self retaining blade damper
US5143517A (en) Turbofan with dynamic vibration damping
CA2034478A1 (en) Gas turbine bladed disk
KR20010062682A (en) Blade attachment configuration
EP0924380A3 (en) Striated turbomachine blade
EP2322761B1 (en) Bladed rotor wheel
CN104919195B (en) Built-up crankshaft and the method for producing built-up crankshaft
EP1698760B1 (en) Torque-tuned, integrally-covered bucket and related method
JPS59108802A (en) Moving blade cover installing device
JPH10184305A (en) Turbine having shroud moving blade
JPH06117201A (en) Assembly method for turbine moving blade
JP2002106302A (en) Turbine rotor
US4807365A (en) Method for making the shaving head of a dry-shaving apparatus
RU2161257C2 (en) Turbine rotating blade of gas-turbine engine
JPH10176501A (en) Integral cover blade
JPS6149103A (en) Turbine rotor blade linking equipment