JP2000130102A - Rotary machine blade tip structure - Google Patents
Rotary machine blade tip structureInfo
- Publication number
- JP2000130102A JP2000130102A JP10308347A JP30834798A JP2000130102A JP 2000130102 A JP2000130102 A JP 2000130102A JP 10308347 A JP10308347 A JP 10308347A JP 30834798 A JP30834798 A JP 30834798A JP 2000130102 A JP2000130102 A JP 2000130102A
- Authority
- JP
- Japan
- Prior art keywords
- vibration
- blades
- blade
- areas
- 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.)
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Links
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- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、圧縮機，タービン
等の回転流体機械において翼に発生するパネルモード振
動を減衰させる回転機械翼端構造に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a rotary machine blade tip structure for attenuating panel mode vibration generated in a blade in a rotary fluid machine such as a compressor or a turbine.
【０００２】[0002]
【従来の技術】軸流圧縮機，タービン等の回転流体機械
の動翼には、隣接する静翼の後縁で発生するウェーク等
の影響で、回転数に比例する起振力が作用し、曲げモー
ド，捩じりモード，パネルモードの３種の振動が発生す
る。2. Description of the Related Art Vibration force proportional to the number of revolutions acts on the moving blades of a rotating fluid machine such as an axial compressor and a turbine due to wakes generated at the trailing edge of an adjacent stationary blade. Three kinds of vibrations of a bending mode, a torsion mode, and a panel mode are generated.
【０００３】曲げモードの振動は、図３（Ａ）に示すよ
うに、翼の末端部を固定端とする曲げ振動であり、等高
線（ａに破線で示す）が固定端にほぼ平行となる変形を
示す。かかる変形では、特に固定端（末端部）に高い曲
げ応力が発生し、図４（Ａ）に斜線部分で示す翼全体が
破損して飛散するような大きな損傷が生じる。そのた
め、かかる曲げモードの振動を本質的に回避するため
に、例えば、曲げモード振動が運転領域で生じないよう
にする、等の基本設計が行われている。As shown in FIG. 3A, the bending mode vibration is a bending vibration in which the end of the blade is a fixed end, and a contour line (shown by a broken line in a) is substantially parallel to the fixed end. Is shown. In such deformation, a high bending stress is generated particularly at the fixed end (end portion), and large damage is caused such that the entire blade shown by the hatched portion in FIG. Therefore, in order to essentially avoid such bending mode vibration, for example, a basic design such as preventing bending mode vibration from occurring in an operation region has been performed.
【０００４】捩じりモードの振動は、図３（Ｂ）に示す
ように、翼の先端部が末端部に対して捩じられる振動で
あり、等高線が固定端にほぼ垂直となる変形を示す。か
かる変形では、翼の中央部に高い剪断応力が発生し、図
４（Ａ）に斜線部分で示すように、かかる損傷は曲げモ
ードによる損傷と同程度になるため、大幅な修理が必要
となるため、曲げモード振動と同様に、運転領域で生じ
ないように設計が行われている。As shown in FIG. 3B, the torsional mode vibration is a vibration in which the tip of the wing is twisted with respect to the end, and shows a deformation in which the contour lines are almost perpendicular to the fixed end. . In such deformation, high shear stress is generated at the center of the wing, and as shown by the hatched portion in FIG. 4A, such damage is almost the same as that in the bending mode, so that a large repair is required. Therefore, similarly to the bending mode vibration, the design is performed so as not to occur in the operation region.
【０００５】[0005]
【発明が解決しようとする課題】パネルモードの振動
は、図３（Ｃ）に示すように、翼の背面と腹面が互いに
バックリングを起こす振動であり、等高線が固定端では
広く、先端部で狭い変形を示す。かかるパネル振動は、
翼の先端部のみが特に大きく変形するため、翼先端部に
軸方向に延びる亀裂が生じ、その一部が飛散することが
ある。かかる損傷は、図４（Ｃ）に示すように、翼の先
端部に生じる比較的軽度の損傷であるが、部品交換等を
早期に行う必要が生じる。また、曲げモード及び捩じり
モードよりも高次の振動であり、回転流体機械の運転領
域（例えば３千Ｈｚ〜２万Ｈｚ）で生じるため、運転上
避けがたい場合が多い。そのため、翼設計上、高次振動
モードであるパネル振動を通常回避できず、長期の使用
により翼先端部にクラックが発生しやすく、翼寿命が短
命化する問題点があった。As shown in FIG. 3 (C), the vibration in the panel mode is a vibration in which the back surface and the abdominal surface of the wing cause buckling with each other. Shows narrow deformation. Such panel vibrations
Since only the tip of the wing is particularly greatly deformed, a crack extending in the axial direction is generated at the tip of the wing, and a part of the crack may be scattered. Such damage is relatively slight damage at the tip of the wing as shown in FIG. 4C, but it is necessary to replace parts at an early stage. Further, the vibration is higher than the bending mode and the torsional mode and occurs in the operation range (for example, 3,000 Hz to 20,000 Hz) of the rotary fluid machine, and therefore, it is often difficult to avoid the operation. Therefore, there is a problem that the panel vibration, which is a high-order vibration mode, cannot be normally avoided in the blade design, and cracks are likely to occur at the blade tip portion due to long-term use, and the blade life is shortened.
【０００６】本発明は、かかる問題点を解決するために
創案されたものである。すなわち、本発明の目的は、回
転流体機械において翼に発生するパネルモード振動を減
衰させることができ、これにより翼先端部のクラック発
生を抑制し、翼寿命を延ばすことができる回転機械翼端
構造を提供することにある。The present invention has been made to solve such a problem. That is, an object of the present invention is to provide a rotary machine blade tip structure capable of attenuating panel mode vibration generated on a blade in a rotating fluid machine, thereby suppressing crack generation at the blade tip and extending blade life. Is to provide.
【０００７】[0007]
【課題を解決するための手段】本発明によれば、回転流
体機械の翼先端部に中空領域又は減肉領域を設け、該中
空領域又は減肉領域に粘弾性材を取り付けた、ことを特
徴とする回転機械翼端構造が提供される。According to the present invention, a hollow region or a thinned region is provided at the tip of a blade of a rotary fluid machine, and a viscoelastic material is attached to the hollow region or the thinned region. The rotary machine wing tip structure is provided.
【０００８】本発明の好ましい実施形態によれば、前記
中空領域は、グルーブであり、前記減肉領域は、スキー
ラである。また、前記粘弾性材は、塑性変形可能な金
属、プラスチック、又はゴムであるのがよい。According to a preferred embodiment of the present invention, the hollow area is a groove, and the thinned area is a squealer. The viscoelastic material is preferably a plastically deformable metal, plastic, or rubber.
【０００９】上記本発明の構成によれば、翼先端部がグ
ルーブ構造又はスキーラ構造と粘弾性材からなるので、
熱膨張や遠心力により翼先端部が静止部分に接触した場
合でも、変形しやすい粘弾性材と翼先端部の薄肉部分が
接触するので、翼先端接触時の損傷を軽減することがで
きる。According to the configuration of the present invention, the tip of the wing is formed of a groove structure or a squealer structure and a viscoelastic material.
Even when the tip of the blade contacts the stationary part due to thermal expansion or centrifugal force, the viscoelastic material that is easily deformed contacts the thin part of the tip of the blade, so that damage at the time of contact with the tip of the blade can be reduced.
【００１０】また、翼先端部の中空領域（例えばグルー
ブ）又は減肉領域（例えばスキーラ）に、粘弾性材（例
えば塑性変形可能な金属、プラスチック、又はゴム）が
取り付けられているので、図３（Ｃ）に示したパネルモ
ードの振動が生じ、翼の先端部のみが特に大きく変形し
た場合でも、先端部の中空領域（グルーブ）又は減肉領
域（スキーラ）に取り付けた粘弾性材もこの変形を受
け、その粘弾性特性により振動エネルギーの一部を吸収
するので、パネルモードの振動を減衰させ、その振動レ
ベルを低減し、クラック発生を抑制することができる。Since a viscoelastic material (for example, metal, plastic, or rubber capable of plastic deformation) is attached to a hollow region (for example, a groove) or a thinning region (for example, a squealer) at the tip of the blade, FIG. Even when the vibration of the panel mode shown in (C) occurs and only the tip of the blade is particularly greatly deformed, the viscoelastic material attached to the hollow area (groove) or the thinned area (squealer) at the tip also deforms. Then, a part of the vibration energy is absorbed by the viscoelastic characteristic, so that the vibration in the panel mode is attenuated, the vibration level is reduced, and the occurrence of cracks can be suppressed.
【００１１】[0011]
【発明の実施の形態】以下本発明の実施形態について、
図面を参照して説明する。図１は、本発明の回転機械翼
端構造を示す構造図である。この図において、（Ａ）は
軸流圧縮機の模式的側面図である。DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiments of the present invention will be described below.
This will be described with reference to the drawings. FIG. 1 is a structural diagram showing a rotary machine blade tip structure of the present invention. In this figure, (A) is a schematic side view of the axial compressor.
【００１２】図１（Ａ）において、１は回転機械のロー
タ、２はケーシング、３は動翼、４は静翼である。回転
機械は、この例ではジェットエンジンの軸流圧縮機であ
るが、本発明はこれに限定されず、例えば軸流タービン
であってもよい。ロータ１は、回転軸Ｚ−Ｚを中心に回
転し、その周囲に複数の動翼３が周方向に間隔を隔てて
配列されている。また、静翼４は、ケーシング２の内側
に周方向に間隔を隔てて複数配列されている。なお、動
翼３を囲むリング状のシュラウド（図示せず）を別個に
設けてもよい。In FIG. 1A, 1 is a rotor of a rotary machine, 2 is a casing, 3 is a moving blade, and 4 is a stationary blade. The rotary machine is an axial compressor of a jet engine in this example, but the present invention is not limited to this, and may be, for example, an axial turbine. The rotor 1 rotates about a rotation axis Z-Z, and a plurality of rotor blades 3 are arranged around the rotor 1 at intervals in the circumferential direction. A plurality of stationary blades 4 are arranged inside the casing 2 at intervals in the circumferential direction. Note that a ring-shaped shroud (not shown) surrounding the rotor blade 3 may be separately provided.
【００１３】図１（Ｂ）は、図１（Ａ）のＡ−Ａ断面図
とＢ−Ｂ断面図の一例であり、ａは動翼３の先端部、ｂ
は静翼４の先端部を示している。また、この図におい
て、ＳＳは翼のサクション面（背面）、ＰＳは翼の圧力
面（腹面）を示している。この図に示すように、回転流
体機械の翼３，４の先端部に中空領域３ａ，４ａが設け
られ、この中空領域３ａ，４ａに粘弾性材５が取り付け
られている。中空領域３ａ，４ａは、翼先端部の外周端
面に設けられたグルーブであり、外縁部のみがケーシン
グ２の内面に近接する位置まで延び、中央部がケーシン
グ２の内面から所定の深さまで凹んで凹部を形成してい
る。この凹部の形状は、好ましくは、半径方向に同一の
翼断面形状であるのがよい。また、半径方向内方の断面
形状を外周部より若干大きくし、内部に取り付ける粘弾
性材５の遠心力等による抜け出しを防止してもよい。FIG. 1B is an example of a sectional view taken along the line AA and a sectional view taken along the line BB of FIG. 1A.
Indicates the tip of the stationary blade 4. In this figure, SS indicates the suction surface (back surface) of the blade, and PS indicates the pressure surface (belly surface) of the blade. As shown in this figure, hollow regions 3a, 4a are provided at the tips of blades 3, 4 of the rotary fluid machine, and viscoelastic material 5 is attached to these hollow regions 3a, 4a. The hollow regions 3a and 4a are grooves provided on the outer peripheral end surface of the blade tip portion, and only the outer edge portion extends to a position close to the inner surface of the casing 2, and the central portion is recessed from the inner surface of the casing 2 to a predetermined depth. A recess is formed. The shape of the concave portion is preferably the same blade cross-sectional shape in the radial direction. Alternatively, the cross-sectional shape of the inner portion in the radial direction may be made slightly larger than the outer peripheral portion to prevent the viscoelastic material 5 attached inside from coming off due to centrifugal force or the like.
【００１４】粘弾性材５は、少なくとも塑性変形可能な
材料、例えば金属、プラスチック、又はゴムであり、上
記中空領域３ａ，４ａ（グルーブ又は凹部）に充填等に
より取り付けられ、中空領域３ａ，４ａの変形に追従し
て変形できるようになっている。なお、粘弾性材５の取
り付け手段は、中空領域３ａ，４ａに追従して変形でき
る限りで、充填、接着、嵌込み、その他の手段であって
もよい。The viscoelastic material 5 is at least a plastically deformable material, for example, metal, plastic, or rubber. The viscoelastic material 5 is attached to the hollow regions 3a and 4a (grooves or concave portions) by filling or the like, and It can be deformed following the deformation. The means for attaching the viscoelastic material 5 may be filling, bonding, fitting, or other means as long as it can be deformed following the hollow regions 3a, 4a.
【００１５】図１（Ｃ）は、図１（Ａ）のＡ−Ａ断面図
とＢ−Ｂ断面図の別の例であり、ａは動翼３の先端部、
ｂは静翼４の先端部を示している。この図において、回
転流体機械の翼３，４の先端部に減肉領域３ｂ，４ｂが
設けられ、この減肉領域３ｂ，４ｂに粘弾性材５が取り
付けられている。減肉領域３ｂ，４ｂは、好ましくはス
キーラであり、半径方向に同一の薄肉部分を残すのがが
よい。また、半径方向内方の減肉面積を外周部より若干
大きくし、この部分に取り付ける粘弾性材５の遠心力等
による飛散を防止してもよい。その他の構成は、図１
（Ｂ）の場合と同様である。FIG. 1C is another example of a cross-sectional view taken along the line AA and a line BB of FIG. 1A.
b indicates the tip of the stationary blade 4. In this figure, the thinning regions 3b, 4b are provided at the tips of the blades 3, 4 of the rotary fluid machine, and the viscoelastic material 5 is attached to the thinning regions 3b, 4b. The thinned areas 3b, 4b are preferably squealers, and preferably leave the same thin part in the radial direction. Further, the radially inward wall thinning area may be slightly larger than the outer peripheral portion to prevent scattering of the viscoelastic material 5 attached to this portion due to centrifugal force or the like. Other configurations are shown in FIG.
This is the same as the case (B).
【００１６】図２は、本発明の回転機械翼端構造の作動
説明図であり、（Ａ）はパネルモードの変形状態、
（Ｂ）は周波数特性を示している。図２（Ａ）におい
て、ａは図１（Ｂ）に示した中空領域（グルーブ）を有
する本発明による翼端構造図、ｂはその端面図、ｃは端
面のパネルモード変形図である。また、図２（Ｂ）にお
いて、横軸は周波数、縦軸は振幅、図中の実線は従来の
特性、破線は本発明による特性を示している。FIGS. 2A and 2B are explanatory views of the operation of the rotary machine blade tip structure of the present invention, wherein FIG.
(B) shows frequency characteristics. 2A, a is a wing tip structural view according to the present invention having the hollow region (groove) shown in FIG. 1B, b is an end view thereof, and c is a panel mode deformation view of the end face. In FIG. 2B, the horizontal axis represents frequency, the vertical axis represents amplitude, the solid line in the figure represents the conventional characteristics, and the broken line represents the characteristics according to the present invention.
【００１７】上述した本発明の構成によれば、翼先端部
がグルーブ構造３ａ，４ａ又はスキーラ構造３ｂ，４ｂ
と粘弾性材５からなるので、熱膨張や遠心力により翼先
端部が静止部分（例えばケーシング２又はロータ１）に
接触した場合でも、変形しやすい粘弾性材５と翼先端部
の薄肉部分が接触するので、翼先端接触時の損傷を軽減
することができる。According to the configuration of the present invention described above, the tip of the blade has a groove structure 3a, 4a or a squealer structure 3b, 4b.
And the viscoelastic material 5, the viscoelastic material 5 which is easily deformed and the thin portion of the wing tip are easily deformed even when the blade tip comes into contact with a stationary portion (for example, the casing 2 or the rotor 1) due to thermal expansion or centrifugal force. Because of the contact, damage at the time of contact with the blade tip can be reduced.
【００１８】また、翼先端部の中空領域３ａ，４ａ（グ
ルーブ）又は減肉領域３ｂ，４ｂ（スキーラ）に、粘弾
性材５（塑性変形可能な金属、プラスチック、ゴム等）
が取り付けられているので、図３（Ｃ）に示したパネル
モードの振動が生じ、翼の先端部のみが特に大きく変形
した場合でも、先端部の中空領域（グルーブ）又は減肉
領域（スキーラ）に取り付けた粘弾性材５がこの変形を
受け、その粘弾性特性により振動エネルギーの一部を吸
収するので、図２（Ｂ）に示すように、パネルモードの
振動を減衰させ、その振動レベルを低減し、クラック発
生を抑制することができる。A viscoelastic material 5 (plastically deformable metal, plastic, rubber, etc.) is provided in the hollow regions 3a, 4a (groove) or the thinned regions 3b, 4b (squealer) at the blade tip.
Is installed, the panel mode vibration shown in FIG. 3 (C) is generated, and even when only the tip of the wing is particularly greatly deformed, a hollow area (groove) or a thinned area (squealer) at the tip is obtained. The viscoelastic material 5 attached to the panel receives this deformation and absorbs a part of the vibration energy due to its viscoelastic characteristics. Therefore, as shown in FIG. 2B, the panel mode vibration is attenuated and the vibration level is reduced. And the occurrence of cracks can be suppressed.
【００１９】なお、本発明は、上述した実施形態に限定
されず、本発明の要旨を逸脱しない範囲で種々に変更で
きることは勿論である。It should be noted that the present invention is not limited to the above-described embodiment, but can be variously modified without departing from the gist of the present invention.
【００２０】[0020]
【発明の効果】上述したように本発明によれば、スキー
ラ等による翼先端接触時の損傷軽減効果を生かしなが
ら、高次モード振動低減によるクラック発生を抑える効
果があり、特に高次モード振動は構造ダンピングが少し
でも増えると振動減衰効果は大きいので、比較的小さい
ダンピング構造でも大きな効果を得ることができる。従
って、本発明の回転機械翼端構造は、回転流体機械にお
いて翼に発生するパネルモード振動を減衰させることが
でき、これにより翼先端部のクラック発生を抑制し、翼
寿命を延ばすことができる、等の優れた効果を有する。As described above, according to the present invention, there is an effect of suppressing the occurrence of cracks by reducing higher-order mode vibrations while utilizing the effect of reducing damage at the time of blade tip contact by a squealer or the like. If the structural damping increases even a little, the vibration damping effect is large, so that a large effect can be obtained even with a relatively small damping structure. Therefore, the rotating machine blade tip structure of the present invention can attenuate panel mode vibration generated in the blade in the rotating fluid machine, thereby suppressing the occurrence of cracks at the blade tip and extending the blade life. And so on.
【図１】本発明の回転機械翼端構造を示す構造図であ
る。FIG. 1 is a structural diagram showing a rotary machine blade tip structure of the present invention.
【図２】本発明の回転機械翼端構造の作動説明図であ
る。FIG. 2 is an operation explanatory view of the rotary machine blade tip structure of the present invention.
【図３】翼に生じる振動モードの説明図である。FIG. 3 is an explanatory diagram of a vibration mode generated in a wing.
【図４】各振動モードによる翼の破損領域を示す図であ
る。FIG. 4 is a diagram showing damaged areas of a blade in each vibration mode.
１ 回転機械のロータ ２ ケーシング ３ 動翼 ４ 静翼 ３ａ，４ａ 中空領域 ３ｂ，４ｂ 減肉領域 ５ 粘弾性材 DESCRIPTION OF SYMBOLS 1 Rotor of rotary machine 2 Casing 3 Moving blade 4 Stator blade 3a, 4a Hollow area 3b, 4b Thinning area 5 Viscoelastic material
Claims (4)
減肉領域を設け、該中空領域又は減肉領域に粘弾性材を
取り付けた、ことを特徴とする回転機械翼端構造。1. A rotary machine blade tip structure, wherein a hollow region or a thinned region is provided at a blade tip of a rotary fluid machine, and a viscoelastic material is attached to the hollow region or the thinned region.
を特徴とする請求項１に記載の回転機械翼端構造。2. The rotary machine blade tip structure according to claim 1, wherein the hollow region is a groove.
を特徴とする請求項１に記載の回転機械翼端構造。3. The rotary machine blade tip structure according to claim 1, wherein said thinning region is a squealer.
プラスチック、又はゴムである、ことを特徴とする請求
項１に記載の回転機械翼端構造。4. The viscoelastic material is a plastically deformable metal,
The rotating machine blade tip structure according to claim 1, wherein the rotating machine blade tip structure is plastic or rubber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP10308347A JP2000130102A (en) | 1998-10-29 | 1998-10-29 | Rotary machine blade tip structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP10308347A JP2000130102A (en) | 1998-10-29 | 1998-10-29 | Rotary machine blade tip structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JP2000130102A true JP2000130102A (en) | 2000-05-09 |
Family
ID=17979977
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP10308347A Pending JP2000130102A (en) | 1998-10-29 | 1998-10-29 | Rotary machine blade tip structure |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2000130102A (en) |
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|---|---|---|---|---|
| US6471484B1 (en) * | 2001-04-27 | 2002-10-29 | General Electric Company | Methods and apparatus for damping rotor assembly vibrations |
| JP2002364592A (en) * | 2001-06-01 | 2002-12-18 | Kubota Corp | Fan for agricultural machine |
| WO2006015899A1 (en) | 2004-08-06 | 2006-02-16 | Siemens Aktiengesellschaft | Compressor blade and production and use of a compressor blade |
| EP1985803A1 (en) * | 2007-04-23 | 2008-10-29 | Siemens Aktiengesellschaft | Process for manufacturing coated turbine blades |
| CN102758792A (en) * | 2011-04-20 | 2012-10-31 | 通用电气公司 | Compressor with blade tip geometry for reducing tip stresses |
| CN105705734A (en) * | 2013-11-07 | 2016-06-22 | 西门子公司 | Turbomachine with a coating, use of a plastic for coating and method for coating the turbomachine |
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-
1998
- 1998-10-29 JP JP10308347A patent/JP2000130102A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6471484B1 (en) * | 2001-04-27 | 2002-10-29 | General Electric Company | Methods and apparatus for damping rotor assembly vibrations |
| JP2002364592A (en) * | 2001-06-01 | 2002-12-18 | Kubota Corp | Fan for agricultural machine |
| US8951008B2 (en) | 2004-08-06 | 2015-02-10 | Siemens Aktiengesellschaft | Compressor blade and production and use of a compressor blade |
| WO2006015899A1 (en) | 2004-08-06 | 2006-02-16 | Siemens Aktiengesellschaft | Compressor blade and production and use of a compressor blade |
| EP1985803A1 (en) * | 2007-04-23 | 2008-10-29 | Siemens Aktiengesellschaft | Process for manufacturing coated turbine blades |
| WO2008128902A1 (en) * | 2007-04-23 | 2008-10-30 | Siemens Aktiengesellschaft | Method for producing coated turbine blades and blade ring for a rotor of a turbine with axial flow |
| JP2010525229A (en) * | 2007-04-23 | 2010-07-22 | シーメンス アクチエンゲゼルシヤフト | Method for manufacturing a coated turbine blade |
| US8607455B2 (en) | 2007-04-23 | 2013-12-17 | Siemens Aktiengesellschaft | Method for the production of coated turbine moving blades and moving-blade ring for a rotor of an axial-throughflow turbine |
| CN102758792A (en) * | 2011-04-20 | 2012-10-31 | 通用电气公司 | Compressor with blade tip geometry for reducing tip stresses |
| CN105705734A (en) * | 2013-11-07 | 2016-06-22 | 西门子公司 | Turbomachine with a coating, use of a plastic for coating and method for coating the turbomachine |
| RU2640864C2 (en) * | 2013-11-07 | 2018-01-12 | Сименс Акциенгезелльшафт | Blade machine |
| KR20190036858A (en) * | 2017-09-28 | 2019-04-05 | 두산중공업 주식회사 | Blade, damper for blade, compressor and gas turbine comprising it |
| KR102000350B1 (en) * | 2017-09-28 | 2019-07-15 | 두산중공업 주식회사 | Blade, damper for blade, compressor and gas turbine comprising it |
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