JPS62142805A - Moving blade for axial-flow fluid machine - Google Patents

Moving blade for axial-flow fluid machine

Info

Publication number
JPS62142805A
JPS62142805A JP28297485A JP28297485A JPS62142805A JP S62142805 A JPS62142805 A JP S62142805A JP 28297485 A JP28297485 A JP 28297485A JP 28297485 A JP28297485 A JP 28297485A JP S62142805 A JPS62142805 A JP S62142805A
Authority
JP
Japan
Prior art keywords
plate
blade
moving blade
slit
tip
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
JP28297485A
Other languages
Japanese (ja)
Inventor
Yoshiki Niizeki
良樹 新関
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 JP28297485A priority Critical patent/JPS62142805A/en
Publication of JPS62142805A publication Critical patent/JPS62142805A/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
    • F01D5/14Form or construction
    • F01D5/20Specially-shaped blade tips to seal space between tips and stator

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

PURPOSE:To prevent leakage flow due to the presence of a moving-blade tip clearance from taking place by providing a plate-like part which is placed in a slit-shaped groove extending virtually in the direction of the chord of the blade tip so as to be able to move radially, and then providing the plate-like part in such a manner as to move outward freely by the centrifugal force. CONSTITUTION:In a slit-shaped groove 7, which is provided on the blade tip of a moving blade 1 in such a manner as to be curved a little in line with its camber, is fit a plate-like part 6 so that it may be free to travel radially, and then, its movement in the direction of the chord of blade is regulated by means of the leading edge of the groove 7. In addition, on the plate-like part 6 is provided a radial hole 9, and into the hole 9 is inserted a check pin 8, which penetrates the moving blade 1 perpendicularly, so as to guide the radial movement of the plate-like part 6. And further, the centrifugal force resulted from the rotation of the moving blade 1 causes the plate-like part 6 to move outward radially so that it comes onto sliding contact with a casing 2 and thereby, leakage flow from the front side of the moving blade 1 toward the back side thereof, which was caused by the presence heretofore of a clearance between the tip of the moving blade 1 and the casing 2, can now be checked by means of the plate-like part 6 as mentioned above.

Description

【発明の詳細な説明】 〔発明の技術分野〕 本発明は軸流流体機械の動夾の特に興端部の改良した偽
造に関する。
TECHNICAL FIELD OF THE INVENTION The present invention relates to an improved counterfeiting of the motion of an axial fluid machine, particularly at the end.

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

細流型の圧縮機やタービンにおいては、最近の著しい計
算機性能の向上もあって、その空気力学的な性能の改善
は目ざましいものがある。
The aerodynamic performance of trickle-flow compressors and turbines has improved significantly, thanks in part to recent significant improvements in computer performance.

このような軸流型の流体機械における効率向上に対する
問題点としては、2次流れや壁面摩擦など、主として流
体の粘性に起因する損失とともに、各所における漏れに
よる損失が大きい。特に軸流流体機械においては動翼と
ケーシング、あるいは静翼とロータの間には、構造上常
に間隙があるが、この部分からの漏れによる損失は流体
機械の損失全体に対して非常に大きな割合を占めている
ことが明らかとなっている。
Problems with improving efficiency in such axial flow type fluid machines include losses mainly due to fluid viscosity such as secondary flow and wall friction, as well as large losses due to leakage at various locations. Particularly in axial flow fluid machines, there are always gaps between the rotor blades and casing, or between the stator vanes and the rotor due to the structure, but losses due to leakage from these parts account for a very large proportion of the total loss in fluid machines. It is clear that the majority of

この漏れ損失を減小するための最も効果的な方法は、間
隙をできうる限り小とすることであるが、非常に工作上
の精度が要求されること、また、運転中の遠心力による
延び、温度上昇による膨張。
The most effective way to reduce this leakage loss is to make the gap as small as possible, but this requires great precision in the workmanship, and also because of the elongation caused by centrifugal force during operation. , expansion due to temperature increase.

自重によるたわみ等が複雑に影響するため、現実的には
この間隙を小とすることには限度がある。
In reality, there is a limit to how small this gap can be made, since deflection due to its own weight has a complicated effect.

このような理由のため、特に高性能の軸流流体機械に対
しては、次のような手段で翼端の間隙による損失を最小
とする努力がされている。
For these reasons, especially for high-performance axial flow fluid machines, efforts are being made to minimize the loss due to gaps at the blade tips by the following means.

1.翼端部にシュラウドを設ける。1. A shroud is provided at the wing tip.

2 翼端部に対向する部分にハニカム等を用いることに
より、翼が摺動しても影響がないようにする。
2. By using honeycomb etc. on the part facing the wing tip, there will be no effect even if the wing slides.

3、翼端部に対向する部分を機械的あるいは熱制御等を
用いることにより変形可能とする。
3. The portion facing the blade tip can be deformed by using mechanical or thermal control.

したがって、従来技術では翼端間隙による損失を抑制す
るためには、非常に複雑、かつ高価な装置を付与するこ
とが必要となり、このような技術の適用には限界があり
、翼端間隙による損失を抑制する効果的、かつ簡単、安
価な方法の出現が望才れていた。
Therefore, in the conventional technology, in order to suppress the loss due to the blade tip gap, it is necessary to provide a very complicated and expensive device, and there is a limit to the application of such technology. It was hoped that an effective, simple, and inexpensive method would emerge to suppress this.

〔発明の目的〕[Purpose of the invention]

本発明の目的は、上述した従来装置にかわり、軸流流体
機械の翼端間隙からの漏れに起因する損失を最小限に抑
制し、高効率な軸流流体機械を得る方法を簡単、安価に
提供することにある。
An object of the present invention is to provide a simple and inexpensive method for obtaining a highly efficient axial flow machine by minimizing the loss caused by leakage from the blade tip gap of an axial flow machine, in place of the above-mentioned conventional device. It is about providing.

〔発明の概要〕[Summary of the invention]

上記目的を達成するため、第1項の発明は軸流流体機械
の動翼の翼端に、はぼ8弦方向にむかって翼弦長の大部
分にわたる長さをもつスリット状の溝をもち、このスリ
ット状溝にはめこまれ、半径方向に移動可能な板状部分
を備えている。板状部分は、スリット状溝に保持されて
動翼が回転する際に生じる遠心力によって半径方向外側
向きの力を受け、対向するケーシング部分におしつけら
れ、翼端とケーシングの間の間隙を翼の腹側から背側に
向って流れる漏れ流れを封止する。
In order to achieve the above object, the invention of item 1 has a slit-like groove at the tip of a rotor blade of an axial flow fluid machine, the length extending in the direction of the 8th chord and extending over most of the chord length of the blade. , is fitted into this slit-like groove and is provided with a plate-like part that is movable in the radial direction. The plate-shaped part is held in the slit-shaped groove and receives a radially outward force due to the centrifugal force generated when the rotor blade rotates, and is pressed against the opposing casing part, filling the gap between the blade tip and the casing with the blade. This seals the leakage flow from the ventral side to the dorsal side.

板状部分は翼に比べて小さくでき、機械の大きさや回転
数により、適当な力でケーシングと摺動するような重さ
を持つように形状、材料を選択する。条件によってはテ
フロン(商品名)や研磨可能な材料を用いることは本発
明の効果をより大きくする。また板状部材の外周側先端
は、円弧状あるいは巾が漸減するように仕上げて、接触
抵抗が小さくなるようにするとよい。
The plate-like part can be made smaller than the blade, and its shape and material are selected so that it has enough weight to slide against the casing with an appropriate force depending on the size and rotational speed of the machine. Depending on the conditions, using Teflon (trade name) or a polishable material can further enhance the effects of the present invention. Further, it is preferable that the outer peripheral end of the plate-like member is finished in an arcuate shape or in a manner that the width gradually decreases to reduce the contact resistance.

スリット状溝は上記板状部分を保持する目的で設けられ
る。溝は翼弦方向に貫通させてもよいし、前縁部あるい
は後縁部あるいはその両方が封止されていてもよい。た
だし、最後の場合を除き板状部分を翼弦方向に対して拘
束する手段が必要である。本発明では、その手段につい
ては限定しない。
The slit-like groove is provided for the purpose of holding the plate-like portion. The grooves may run chordwise or may be sealed at the leading edge and/or the trailing edge. However, except in the last case, a means for restraining the plate-like portion in the chord direction is required. The present invention does not limit the means.

スリット状溝、板状部分とも直線状である必要はなく、
翼のキャンバ角によってはある程度のそりを持たせるこ
ともよい。
Both the slit-like groove and the plate-like part do not have to be straight,
Depending on the camber angle of the wing, it may be good to have some degree of warpage.

板状部分の前縁側端、後縁側端は、翼の厚さや流体抵抗
の減小のために曲率をもたせて仕上げることや板厚を漸
減することが考えられる。この場合、当然のことながら
、溝部の形状も板状部分の形状に対応するものである必
要がある。
It is conceivable that the leading edge side end and trailing edge side end of the plate-shaped portion be finished with a curvature or that the plate thickness be gradually reduced in order to reduce the thickness of the blade and fluid resistance. In this case, it goes without saying that the shape of the groove also needs to correspond to the shape of the plate-like portion.

板状部分は、半径方向に移動可能であるが、特にその移
動範囲を限定する手段は必要ではない。
Although the plate-shaped portion is movable in the radial direction, there is no need for any means to limit the range of movement.

ただし、翼弦方向の拘束手段によっては両目的を兼用さ
せることで、組立時の作業が簡単化される。
However, depending on the restraint means in the chord direction, the work at the time of assembly can be simplified by serving both purposes.

半径方向の移動は、組立後にケーシング面で限定される
のみで充分であるが、他にヨ℃ノ束手段をもたない場合
は、ロータとケーシングの組立前には板状部分が脱落す
るのを防止する手段を必要とする。
It is sufficient that the radial movement is limited only by the casing surface after assembly, but if no other horizontal bundling means is provided, the plate-like portion may fall off before the rotor and casing are assembled. Requires a means to prevent this.

このためには711立後取りはずす必要があるためクリ
ップ状のもの、あるいは簡単には粘着テープなどを用い
ることが考えられる。
For this purpose, it is necessary to remove it after 711, so it is conceivable to use a clip-like object, or simply an adhesive tape.

第2項の発明は第1項の発明に含まれるが、特に低回転
数運転を行う機械や周速が低い段落等にも適用が可能な
よう番こ補助的に半径方向外向きの力を与える弾性体を
備えるものである。また、この弾性体は、第1項の発明
で述べた板状部品の脱落防止の目的や翼弦方向の拘束の
目的を兼ねさせることが可能である。
The invention of item 2 is included in the invention of item 1, but in order to be especially applicable to machines that operate at low rotational speeds and stages with low circumferential speed, the invention uses a force directed outward in the radial direction as an auxiliary guard. It is equipped with an elastic body that provides Further, this elastic body can serve both of the purposes of preventing the plate-shaped component from falling off and restraining the blade in the chord direction, as described in the first aspect of the invention.

〔発明の効果〕〔Effect of the invention〕

本発明によれば、比較的簡単な構造により、動翼翼端間
隙による漏れ流れを確実に減少できる。
According to the present invention, a relatively simple structure can reliably reduce the leakage flow due to the gap between the rotor blade tips.

本発明によれば各動翼一枚一枚について適確な漏れ防止
が行なえるため、例えば、わずかな偏心等により各翼の
間隙にバラツキがある場合従来技術では対応が難かしい
が本発明では可能である。
According to the present invention, accurate leakage prevention can be performed for each moving blade, so for example, if there is variation in the gap between the blades due to slight eccentricity, etc., it is difficult to deal with this with the conventional technology, but with the present invention, It is possible.

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

本発明について図に基づいて読切する。第1図は本発明
の第1の実施例の斜視図を示している。
The present invention will be read in one piece based on the figures. FIG. 1 shows a perspective view of a first embodiment of the invention.

動翼の回転による遠心力のため板状部分6は動具先端5
から半径方向外側に突出して移動している。
Due to the centrifugal force caused by the rotation of the moving blades, the plate-shaped portion 6 is caused by the moving tool tip 5.
It protrudes and moves radially outward.

板状部分6は、第1図では省略されているが、ケーシン
グ2によってその半径方向の動きを拘束される。このた
め従来wJ翼の翼部と、ケーシングの間に存在する間隙
によって生じていた動翼腹側から背側へ向う漏れ流れは
、板状部分6によって阻止され、この漏れ流れに起因す
る損失は大巾に減少される。第1図に示した例において
は、板状部分6は動翼1のそりに適応させるため若干彎
曲している。また翼弦方向の動きは、スリット状溝2が
前縁部でふさがれていること、およびピン8によって拘
束されており、ピン8は組立作業を容品にする程度に板
状部分6の半径方向の移動をも拘束している。第2図は
、第1図に対する側面図および正面図を示し、第3図は
同様の側面図および正面図を、動翼回転停止時について
示したものである。第3図においては遠心力が働らかな
いため板状部分6がケーシング2から離れている。(動
翼の停止位置によっては、重力の影響により第2図に示
した場合と全く同じ状態になることもあり得る)、スリ
ット状溝7と板状部分6は動翼回転時において板状部分
6が滑らかに移動できるように作られている。また、こ
こに示した例においては板状部分の外側端は直角に作ら
れているが、接触抵抗を減じるために円弧状端面に仕上
げることもよい。次に本発明の第2の実施例を第4図に
よって説明する。これは上で説明した第1の実施例に弾
性体10を付与することによって半径方向外向きの力を
定常的に与えるようにしたものであり、低速回転時等に
も上記第1の実施例と同様の効果が期待できる。第4図
に示した弾性体10の形状は一例であり、この形状を限
定するものではない。
Although the plate-shaped portion 6 is omitted in FIG. 1, its radial movement is restrained by the casing 2. Therefore, the leakage flow from the ventral side to the dorsal side of the rotor blade, which was caused by the gap existing between the blade part of the conventional wJ blade and the casing, is blocked by the plate-shaped part 6, and the loss caused by this leakage flow is reduced. It is reduced to a large extent. In the example shown in FIG. 1, the plate-like portion 6 is slightly curved to accommodate the curvature of the rotor blade 1. Further, movement in the chord direction is restrained by the slit-like groove 2 being closed at the leading edge and by the pin 8, and the pin 8 is fixed at the radius of the plate-like part 6 to the extent that the assembly work is easy. Movement in the direction is also restricted. FIG. 2 shows a side view and a front view with respect to FIG. 1, and FIG. 3 shows a side view and a front view similar to those shown when the rotating blade is stopped. In FIG. 3, the plate-shaped portion 6 is separated from the casing 2 because no centrifugal force is applied. (Depending on the stopping position of the rotor blade, the state may be exactly the same as shown in Fig. 2 due to the influence of gravity.) The slit-like groove 7 and the plate-like portion 6 are the plate-like portion when the rotor blade rotates. 6 is made to move smoothly. Further, in the example shown here, the outer end of the plate-shaped portion is made at a right angle, but it may be finished into an arcuate end face in order to reduce contact resistance. Next, a second embodiment of the present invention will be described with reference to FIG. This is achieved by adding an elastic body 10 to the first embodiment described above to constantly apply outward force in the radial direction, and even during low speed rotation, etc. Similar effects can be expected. The shape of the elastic body 10 shown in FIG. 4 is an example, and is not limited to this shape.

弾性体10を動翼1と板状部分6の間に係合させること
により、板状部分6の軸方向と半径方向の移動範囲を拘
束することも可能である。
By engaging the elastic body 10 between the rotor blade 1 and the plate-like portion 6, it is also possible to restrict the movement range of the plate-like portion 6 in the axial direction and the radial direction.

〔発明の他の実施例〕[Other embodiments of the invention]

上で述べた実施例は、あくまでも本発明を応用した例を
示したにすぎず、本発明を限定するものでないことは百
うまでもない。例えば板状部分6、スリット状溝7の形
状あるいは板状部分6の材質等については、適用される
軸流流体機械の段に要求される性能、あるいはコスト等
によって自由に選択されうるし、板状部分6を軸方向お
よび半径方向に拘束する手段についても限定されない、
例えば第1図に示した例について板状部分62よびスリ
ット状溝を直線形状にすれば、加工費用を大巾に減じ、
かつほぼ同様の効果が期待できる。
The embodiments described above merely show examples of applying the present invention, and needless to say, they do not limit the present invention. For example, the shape of the plate-like portion 6, the slit-like groove 7, the material of the plate-like portion 6, etc. can be freely selected depending on the performance required for the stage of the applied axial flow fluid machine, the cost, etc. The means for restraining the portion 6 in the axial and radial directions are also not limited,
For example, in the example shown in FIG. 1, if the plate-like portion 62 and the slit-like groove are made straight, the processing cost can be greatly reduced.
And almost the same effect can be expected.

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

第1図は本発明の第1の実施例の斜視図、第2図は第1
図に示す本発明の実施例の回転時における状態を示す図
、第3図は第1図に示す本発明の実施例の停止時の状態
を示す図、第4図は本発明の第2の実施例の側面図、第
5図は従来例の斜視図である。 1・・・動翼      2・・・ケーシング3・・・
ロータ     4・・・蒲れ流れ5・・・動翼先端 
   6・・・板状部分7・・・スリット状溝  8・
・・止メビン9・・・止メビン穴  10・・・弾性体
11・・・切り欠き   12・・・興の腹側13・・
・翼の背側   14・・・翼の前縁15・・・翼の後
縁 代理人 弁理士 則 近 憲 佑 同    竹 花 喜久男 第1図 第2図 (a)(b) 第3図 第4図 第5図
FIG. 1 is a perspective view of the first embodiment of the present invention, and FIG. 2 is a perspective view of the first embodiment of the present invention.
FIG. 3 is a diagram showing the state of the embodiment of the present invention shown in FIG. 1 when it is stopped; FIG. 4 is a diagram showing the state of the embodiment of the present invention shown in FIG. A side view of the embodiment, and FIG. 5 is a perspective view of the conventional example. 1... Moving blade 2... Casing 3...
Rotor 4...Flip flow 5...Rotor blade tip
6... Plate-shaped portion 7... Slit-shaped groove 8.
... Stopper pin 9 ... Stopper hole 10 ... Elastic body 11 ... Notch 12 ... Ventral side of the opening 13 ...
・Dorsal side of the wing 14... Leading edge of the wing 15... Trailing edge of the wing Agent Patent attorney Nori Chika Ken Yudo Kikuo Takehana Figure 1 Figure 2 (a) (b) Figure 3 Figure 4 Figure 5

Claims (2)

【特許請求の範囲】[Claims] (1)翼端部のほぼ翼弦方向にむかって翼弦長の大部分
にわたるスリット状溝と、該スリット状溝にはめこまれ
て半径方向に移動可能な板状部分をもち、機械の回転運
動による遠心力によって上記板状部分が、対向するケー
シングに向う方向に移動可能に設けられていることを特
徴とした軸流流体機械の動翼。
(1) It has a slit-like groove extending almost in the chord direction of the blade tip and spanning most of the chord length, and a plate-like part that is fitted into the slit-like groove and movable in the radial direction, and the machine rotates. A rotor blade for an axial flow fluid machine, characterized in that the plate-shaped portion is provided so as to be movable in a direction toward an opposing casing by centrifugal force caused by motion.
(2)スリットと板状部分の間に、板状部分を半径方向
外側にむかって押すような弾性体を備えることを特徴と
する特許請求の範囲第1項記載の軸流流体機械の動翼。
(2) A rotor blade for an axial fluid machine according to claim 1, characterized in that an elastic body is provided between the slit and the plate-shaped part to push the plate-shaped part radially outward. .
JP28297485A 1985-12-18 1985-12-18 Moving blade for axial-flow fluid machine Pending JPS62142805A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP28297485A JPS62142805A (en) 1985-12-18 1985-12-18 Moving blade for axial-flow fluid machine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP28297485A JPS62142805A (en) 1985-12-18 1985-12-18 Moving blade for axial-flow fluid machine

Publications (1)

Publication Number Publication Date
JPS62142805A true JPS62142805A (en) 1987-06-26

Family

ID=17659548

Family Applications (1)

Application Number Title Priority Date Filing Date
JP28297485A Pending JPS62142805A (en) 1985-12-18 1985-12-18 Moving blade for axial-flow fluid machine

Country Status (1)

Country Link
JP (1) JPS62142805A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1469165A1 (en) * 2003-04-16 2004-10-20 Snecma Moteurs Reduction of the blade tip clearance in a gas turbine
JP2008509316A (en) * 2004-08-06 2008-03-27 シーメンス アクチエンゲゼルシヤフト Compressor blade and method and use of compressor blade
JP2009264383A (en) * 2008-04-23 2009-11-12 Rolls Royce Plc Fan blade
WO2013116500A1 (en) 2012-01-31 2013-08-08 United Technologies Corporation Gas turbine rotary blade with tip insert
FR3088954A1 (en) * 2018-11-22 2020-05-29 Safran Aircraft Engines SEALING ASSEMBLY
CN114576202A (en) * 2022-02-28 2022-06-03 北京航空航天大学 Blade structure, compressor and compressor control method

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1469165A1 (en) * 2003-04-16 2004-10-20 Snecma Moteurs Reduction of the blade tip clearance in a gas turbine
FR2853931A1 (en) * 2003-04-16 2004-10-22 Snecma Moteurs REDUCING GAMES IN A GAS TURBINE
US6976824B2 (en) 2003-04-16 2005-12-20 Snecma Moteurs Reducing clearance in a gas turbine
JP2008509316A (en) * 2004-08-06 2008-03-27 シーメンス アクチエンゲゼルシヤフト Compressor blade and method and use of compressor blade
JP4660547B2 (en) * 2004-08-06 2011-03-30 シーメンス アクチエンゲゼルシヤフト Compressor blade, method for manufacturing the same, and axial flow gas turbine provided with the compressor blade
JP2009264383A (en) * 2008-04-23 2009-11-12 Rolls Royce Plc Fan blade
WO2013116500A1 (en) 2012-01-31 2013-08-08 United Technologies Corporation Gas turbine rotary blade with tip insert
EP2809885A4 (en) * 2012-01-31 2015-11-04 United Technologies Corp Gas turbine rotary blade with tip insert
US9752441B2 (en) 2012-01-31 2017-09-05 United Technologies Corporation Gas turbine rotary blade with tip insert
FR3088954A1 (en) * 2018-11-22 2020-05-29 Safran Aircraft Engines SEALING ASSEMBLY
CN114576202A (en) * 2022-02-28 2022-06-03 北京航空航天大学 Blade structure, compressor and compressor control method
CN114576202B (en) * 2022-02-28 2022-12-06 北京航空航天大学 Blade structure, compressor and compressor control method

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