JPH0626302A - Turbine blade damper - Google Patents
Turbine blade damperInfo
- Publication number
- JPH0626302A JPH0626302A JP1558692A JP1558692A JPH0626302A JP H0626302 A JPH0626302 A JP H0626302A JP 1558692 A JP1558692 A JP 1558692A JP 1558692 A JP1558692 A JP 1558692A JP H0626302 A JPH0626302 A JP H0626302A
- Authority
- JP
- Japan
- Prior art keywords
- elastic body
- groove
- blade
- moving blade
- contact
- 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.)
- Withdrawn
Links
- 239000007943 implant Substances 0.000 claims description 11
- 238000013016 damping Methods 0.000 abstract description 3
- 230000005489 elastic deformation Effects 0.000 abstract description 2
- 239000000919 ceramic Substances 0.000 description 6
- 125000006850 spacer group Chemical group 0.000 description 5
- 239000002184 metal Substances 0.000 description 4
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 229910001220 stainless steel Inorganic materials 0.000 description 2
- 239000010935 stainless steel Substances 0.000 description 2
- 230000002238 attenuated effect Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000005524 ceramic coating Methods 0.000 description 1
- 238000005229 chemical vapour deposition Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000011888 foil Substances 0.000 description 1
- 238000002513 implantation Methods 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
(57)【要約】
【目的】 タービン動翼のダンパーに係るもので、熱膨
張時や高速回転時における応力緩和と振動減衰とを行な
う。
【構成】 溝と植込み部との間に弾性体が配され、弾性
体が、動翼のプラットホームの下面に対して接触状態
に、かつ、溝の側面と植込み部との間に圧接状態に挿入
される。弾性体の弾性変形によって集中応力を緩和し、
遠心力によって弾性体の一部を、動翼のプラットホーム
の下面に接触させて振動抑制を行なう。
(57) [Abstract] [Purpose] This relates to a damper for turbine blades, and performs stress relaxation and vibration damping during thermal expansion and high-speed rotation. [Structure] An elastic body is arranged between the groove and the implanting portion, and the elastic body is inserted in contact with the lower surface of the platform of the moving blade and in a pressure contact state between the side surface of the groove and the implanting portion. To be done. Concentrated stress is relaxed by elastic deformation of the elastic body,
A part of the elastic body is brought into contact with the lower surface of the platform of the moving blade by centrifugal force to suppress vibration.
Description
【０００１】[0001]
【産業上の利用分野】本発明は、タービン動翼のダンパ
ーに係り、特に、植込み部の緩衝と振動減衰を図る技術
に関するものである。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a damper for a turbine rotor blade, and more particularly to a technique for cushioning and dampening vibrations in an implant portion.
【０００２】[0002]
【従来の技術】ガスタービンのタービン翼にあっては、
例えば１３００℃にも及ぶ高温で使用されるものがあ
り、耐熱性を確保するためにセラミックス部品の採用が
期待されている。2. Description of the Related Art In a turbine blade of a gas turbine,
For example, some of them are used at a high temperature as high as 1300 ° C., and ceramic parts are expected to be used to ensure heat resistance.
【０００３】図９は、タービン翼の取り付け構造の例を
示すものである。図９において、符号１はディスク、２
は溝、３は動翼、４は植込み部、５は羽根、６はプラッ
トホーム、７はネック部、８は張り出し部である。そし
て、動翼３の植込み部４は、ディスク１の溝２に収容さ
れ、ネック部７と係合している張り出し部８で、植込み
部４の抜け止めを行なうようにしている。また、ディス
ク１は例えば金属製とされるが、動翼３の部分はセラミ
ックス化の対象となる。FIG. 9 shows an example of a turbine blade mounting structure. In FIG. 9, reference numeral 1 is a disk, 2
Is a groove, 3 is a moving blade, 4 is an implant part, 5 is a blade, 6 is a platform, 7 is a neck part, and 8 is an overhang part. The implanting portion 4 of the moving blade 3 is housed in the groove 2 of the disk 1 and the projecting portion 8 engaging with the neck portion 7 prevents the implanting portion 4 from coming off. The disk 1 is made of metal, for example, but the portion of the moving blade 3 is to be made ceramic.
【０００４】[0004]
【発明が解決しようとする課題】しかし、タービン翼、
つまり動翼３をセラミックス部品とすると、１３００℃
もの高温状態では、熱膨張が小さい動翼３の植込み部４
に対して、金属部品であるディスク１の熱膨張が大きく
なって、溝２と植込み部４とのクリアランスが不均一に
なり、かつ、動翼３は高速回転するために遠心力によっ
て植込み部４が半径外方に移動しようとして張り出し部
８に強く接触し、この接触部分に応力集中が発生して破
壊に至るおそれがある。However, the turbine blade,
In other words, if the rotor blade 3 is a ceramic component, then 1300 ° C
In the high temperature state, the implanted portion 4 of the rotor blade 3 having a small thermal expansion
On the other hand, the thermal expansion of the disk 1, which is a metal component, becomes large, the clearance between the groove 2 and the implant portion 4 becomes non-uniform, and the rotor blade 3 rotates at a high speed, so that the implant portion 4 is rotated by centrifugal force. Is strongly contacted with the overhanging portion 8 in an attempt to move outward in the radius, and stress concentration may occur at this contact portion, leading to destruction.
【０００５】本発明は、これらの事情に鑑みてなされた
もので、熱膨張時及び高速回転時の応力緩和と振動減衰
とを行なうことを目的としている。The present invention has been made in view of these circumstances, and an object thereof is to perform stress relaxation and vibration damping during thermal expansion and during high speed rotation.
【０００６】[0006]
【課題を解決するための手段】上記目的を達成するた
め、ディスクの溝に、動翼の植込み部を挿入状態に支持
してなるタービン動翼において、溝と植込み部との間に
弾性体が配され、該弾性体が、動翼のプラットホームの
下面に対して接触状態に、かつ、溝の側面と植込み部と
の間に圧接状態に挿入される構成を採用している。In order to achieve the above object, in a turbine rotor blade in which a blade portion of a blade is inserted and supported in a groove of a disk, an elastic body is provided between the groove and the blade portion. The elastic body is arranged so as to be inserted in contact with the lower surface of the platform of the moving blade and in pressure contact between the side surface of the groove and the implant portion.
【０００７】[0007]
【作用】溝と植込み部との間に介在している弾性体が、
弾性変形をともなうことによって、遠心力等によって生
じる溝と植込み部との接触部分の接触圧力を緩和する。
また、遠心力によって弾性体が回転半径外方に弾性変形
して、動翼のプラットホームの下面に強く接触すること
により、回転に伴って生じる振動を減衰させる。[Operation] The elastic body interposed between the groove and the implant part
By being accompanied by elastic deformation, the contact pressure of the contact portion between the groove and the implant portion, which is generated by centrifugal force or the like, is relaxed.
Further, the elastic body is elastically deformed to the outside of the radius of gyration by the centrifugal force and strongly contacts with the lower surface of the platform of the moving blade, thereby damping the vibration generated by the rotation.
【０００８】[0008]
【実施例】以下、本発明に係るタービン動翼のダンパー
の実施例について、図１ないし図８を参照して説明す
る。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT An embodiment of a damper for a turbine rotor blade according to the present invention will be described below with reference to FIGS.
【０００９】該一実施例におけるタービン動翼では、図
１に示すように、金属製のディスク１の溝２に、動翼３
の植込み部４を挿入し、かつ、溝２と植込み部４との間
に、弾性体１０が配される。In the turbine rotor blade in the embodiment, as shown in FIG. 1, the rotor blade 3 is provided in the groove 2 of the metal disk 1.
The elastic body 10 is disposed between the groove 2 and the implanting part 4 while inserting the implanting part 4 of FIG.
【００１０】そして、弾性体１０は、図１ないし図４に
示すように、動翼３におけるプラットホーム６の下面に
対して接触した状態に、かつ、隣り合う二つの溝２の側
面と、溝２に挿入される植込み部４の側面との間に、挟
持されることにより圧接した状態に配される。As shown in FIGS. 1 to 4, the elastic body 10 is in contact with the lower surface of the platform 6 of the moving blade 3, and the side surfaces of two adjacent grooves 2 and the groove 2 are adjacent to each other. It is arranged in a state of being pressed and contacted by being sandwiched between the side surface of the implanting part 4 and the side surface of the implanting part 4.
【００１１】弾性体１０の配設状態について説明する
と、図１例では、動翼３の植込み部４の途中に、ディス
ク１の回転方向に寸法を大きくした膨出部４ａが形成さ
れているものに適用され、弾性体１０の基部（外方部
分）１０ａに、屈曲部分１０ｂが配されるとともに、挿
入部１０ｃが、植込み部４の中央近傍で、同型の弾性体
１０における挿入部１０ｃと分離された状態に配され
る。The arrangement of the elastic body 10 will be described. In the example shown in FIG. 1, a bulging portion 4a having a larger size in the rotational direction of the disk 1 is formed in the middle of the implanting portion 4 of the moving blade 3. The bending portion 10b is arranged on the base portion (outer portion) 10a of the elastic body 10, and the insertion portion 10c is separated from the insertion portion 10c in the elastic body 10 of the same type in the vicinity of the center of the implantation portion 4. It is arranged in the state of being
【００１２】そして、図２例ないし図４例では、セラミ
ックス製の動翼３における植込み部４が、図１例で説明
した膨出部４ａを省略した形状のものとされ、この植込
み部４に適用される弾性体１０は、図２例では図１例に
準じて屈曲部分１０ｂを有するものとされ、図３例では
基部１０ａにおいて２分割状態とされる分割部分１０ｄ
を有するものとされ、図４例では基部１０ａと動翼３の
プラットホーム６との間に、二つのプラットホーム６の
下面に跨がった状態のスペーサ１１が挟持状態に配され
る。In the examples shown in FIGS. 2 to 4, the implanting portion 4 of the ceramic rotor blade 3 has a shape in which the bulging portion 4a described in the example of FIG. 1 is omitted. In the example of FIG. 2, the applied elastic body 10 is assumed to have a bent portion 10b according to the example of FIG. 1, and in the example of FIG. 3, the divided portion 10d is divided into two in the base portion 10a.
In the example of FIG. 4, the spacer 11 is arranged between the base portion 10a and the platform 6 of the moving blade 3 so as to be sandwiched between the lower surfaces of the two platforms 6.
【００１３】図５ないし図８は、弾性体１０の形状例を
示すものである。図５例にあっては、ステンレス鋼等か
らなる弾性変形容易な板状材が適用される。図６例にあ
っては、ステンレス鋼等からなる弾性変形容易な例えば
板厚ｔが０．０５ｍｍないし０．５ｍｍの薄板部１０ｅ
と、該薄板部１０ｅの表裏両面に幅方向に沿うとともに
表裏両面で長手方向に互い違いに配される複数条の突条
１０ｆとを有するものとされる。前記突条１０ｆは、そ
の高さＨが板厚ｔと同程度とされ、幅Ｗは例えば板厚ｔ
の２倍ないし５倍程度とされる。かつ、突条１０ｆのピ
ッチ２Ｌは、厚さ方向の剛性を勘案して設定される。図
７例に示す弾性体１０にあっては、薄板部１０ｅの片面
（下面）に、全幅の寸法を有する突条１０ｆが配され、
他の片面（上面）に、長い突条１０ｆと、これよりも短
く設定される突条１０ｇとが、交互に配設される。図８
例に示す弾性体１０にあっては、薄板部１０ｅの片面
に、前述の突条１０ｆが配され、他の片面に、中央が幅
広く端部が幅狭く設定される突条１０ｈが配される。そ
して、図６ないし図８に示すいわゆるフォイルバネ状の
弾性体１０は、突条１０ｆ，１０ｇ，１０ｈの長手方向
を、溝２の長さ方向に沿わせて、溝２と植込み部４との
間に挟持することにより圧接状態となる。5 to 8 show examples of the shape of the elastic body 10. In the example of FIG. 5, a plate member made of stainless steel or the like that is easily elastically deformed is applied. In the example of FIG. 6, a thin plate portion 10e made of stainless steel or the like that is easily elastically deformed and has a plate thickness t of 0.05 mm to 0.5 mm is used.
And a plurality of ridges 10f arranged on both the front and back surfaces of the thin plate portion 10e along the width direction and alternately arranged in the longitudinal direction on the front and back surfaces. The height H of the ridge 10f is substantially the same as the plate thickness t, and the width W is, for example, the plate thickness t.
It is about 2 to 5 times. In addition, the pitch 2L of the protrusions 10f is set in consideration of the rigidity in the thickness direction. In the elastic body 10 shown in the example of FIG. 7, a ridge 10f having a full width dimension is arranged on one surface (lower surface) of the thin plate portion 10e,
Long ridges 10f and ridges 10g set to be shorter than the ridges 10f are alternately arranged on the other surface (upper surface). Figure 8
In the elastic body 10 shown in the example, the above-described ridge 10f is arranged on one surface of the thin plate portion 10e, and the ridge 10h having a wide center and narrow end portions is arranged on the other surface. . The so-called foil spring-shaped elastic body 10 shown in FIGS. 6 to 8 is arranged between the groove 2 and the implant portion 4 by aligning the longitudinal direction of the ridges 10f, 10g, 10h with the longitudinal direction of the groove 2. It will be in a pressure contact state by being sandwiched between.
【００１４】また、弾性体１０の表面には、ＣＶＤ法、
ＰＶＤ法等によってセラミックスコーティングが施さ
れ、耐食性、耐酸化性、低摩擦性が付与される。On the surface of the elastic body 10, the CVD method,
A ceramic coating is applied by the PVD method or the like to impart corrosion resistance, oxidation resistance and low friction.
【００１５】このように、弾性体１０が、金属製のディ
スク１とセラミックス製の動翼３との間に介在して、弾
性変形をともなうことによって、溝２と植込み部４との
加工誤差を吸収することができるとともに、運転時の遠
心力や熱変形による片当りを吸収して、接触部分の圧力
を平均化させて発生応力を緩和することができる。As described above, the elastic body 10 is interposed between the metal disk 1 and the ceramic rotor blade 3 and is elastically deformed, so that a machining error between the groove 2 and the implanting portion 4 is prevented. In addition to being able to absorb the stress, it is possible to absorb the partial contact due to centrifugal force and thermal deformation during operation, to average the pressure at the contact portion, and to alleviate the generated stress.
【００１６】また、ディスク１が高速回転している場合
には、遠心力によって弾性体１０が回転半径外方に弾性
変形して、動翼３のプラットホーム６の下面に強く接触
する（スペーサ１１が介在させられている場合には、ス
ペーサ１１を介して接触する）ために、回転に伴って生
じる動翼３の振動を減衰させるものとなる。When the disk 1 is rotating at a high speed, the elastic body 10 is elastically deformed outward by the centrifugal force due to the centrifugal force and comes into strong contact with the lower surface of the platform 6 of the moving blade 3 (the spacer 11 When it is interposed, it contacts via the spacer 11), so that the vibration of the rotor blades 3 caused by the rotation is attenuated.
【００１７】[0017]
【発明の効果】以上説明したように、本発明に係るター
ビン動翼のダンパーによれば、溝と植込み部との間に弾
性体が配され、弾性体が、動翼のプラットホームの下面
に対して接触状態に、かつ、溝の側面と植込み部との間
に圧接状態に挿入される構成を採用しているから、以下
の優れた効果が得られる。 （１） 熱膨張時及び高速回転時に、弾性体がディスク
と動翼との間で弾性変形をともなうため、溝と植込み部
との加工誤差の吸収や、運転時の遠心力や熱変形による
片当り時にも、接触部分の圧力を平均化させて発生応力
を緩和することができる。 （２） ディスクが高速回転すると、遠心力によって弾
性体が回転半径外方に弾性変形して、動翼のプラットホ
ームの下面に強く接触した状態となり、動翼の振動を減
衰させることができる。 （３） 溝と植込み部との間に生じる集中応力を緩和
し、動翼をセラミックス製とする場合の障害を低減する
ことができる。As described above, according to the damper for a turbine rotor blade in accordance with the present invention, the elastic body is arranged between the groove and the implant portion, and the elastic body is attached to the lower surface of the platform of the rotor blade. By adopting a configuration in which they are inserted in contact with each other and in a pressure contact state between the side surface of the groove and the implanting portion, the following excellent effects can be obtained. (1) During thermal expansion and high-speed rotation, the elastic body is elastically deformed between the disk and the moving blade, so that machining error between the groove and the implanting part is absorbed, and centrifugal force or thermal deformation during operation Even at the time of hitting, the stress in the contact portion can be averaged to alleviate the generated stress. (2) When the disk rotates at a high speed, the elastic body is elastically deformed outward by the centrifugal force due to the centrifugal force, and is brought into a state of being in strong contact with the lower surface of the platform of the moving blade, so that the vibration of the moving blade can be damped. (3) It is possible to relieve the concentrated stress generated between the groove and the implant portion and reduce obstacles when the moving blade is made of ceramics.
【図１】本発明に係るタービン動翼のダンパーの一実施
例における要部を示す正断面図である。FIG. 1 is a front sectional view showing a main part of an embodiment of a damper for a turbine rotor blade according to the present invention.
【図２】図１における動翼の植込み部の形状が異なる場
合の適用例を示す正断面図である。FIG. 2 is a front cross-sectional view showing an application example in which the shape of the implanting portion of the moving blade in FIG. 1 is different.
【図３】図２における弾性体の他の例を示す正断面図で
ある。FIG. 3 is a front sectional view showing another example of the elastic body in FIG.
【図４】図２における動翼の植込み部と弾性体との間に
スペーサを介在させた実施例を示す正断面図である。FIG. 4 is a front cross-sectional view showing an embodiment in which a spacer is interposed between the implanting portion of the moving blade and the elastic body in FIG.
【図５】本発明に係るタービン動翼のダンパーに使用さ
れる弾性体の実施例を示す斜視図である。FIG. 5 is a perspective view showing an embodiment of an elastic body used for a damper of a turbine rotor blade according to the present invention.
【図６】本発明に係るタービン動翼のダンパーに使用さ
れる弾性体の他の実施例を示す斜視図である。FIG. 6 is a perspective view showing another embodiment of the elastic body used for the damper of the turbine rotor blade according to the present invention.
【図７】図６の弾性体における突条の変形例を示す斜視
図である。7 is a perspective view showing a modified example of the ridges in the elastic body of FIG.
【図８】図６の弾性体における突条の他の変形例を示す
斜視図である。FIG. 8 is a perspective view showing another modified example of the protrusion in the elastic body of FIG.
【図９】タービン翼の取り付け構造の従来例を示す斜視
図である。FIG. 9 is a perspective view showing a conventional example of a turbine blade mounting structure.
１ ディスク ２ 溝 ３ 動翼 ４ 植込み部 ４ａ 膨出部 ５ 羽根 ６ プラットホーム ７ ネック部 ８ 張り出し部 １０ 弾性体 １０ａ 基部 １０ｂ 屈曲部分 １０ｃ 挿入部 １０ｄ 分割部分 １０ｅ 薄板部 １０ｆ 突条 １０ｇ 突条 １０ｈ 突条 １１ スペーサ 1 Disc 2 Groove 3 Moving Blade 4 Implanted Part 4a Bulging Part 5 Blade 6 Platform 7 Neck Part 8 Overhanging Part 10 Elastic Body 10a Base Part 10b Bent Part 10c Inserted Part 10d Divided Part 10e Thin Plate Part 10f Projection 10g Projection 10h 11 Spacer
Claims (1)
入状態に支持してなるタービン動翼であって、溝と植込
み部との間に弾性体が配され、該弾性体が、動翼のプラ
ットホームの下面に対して接触状態に、かつ、溝の側面
と植込み部との間に圧接状態に挿入されることを特徴と
するタービン動翼のダンパー。1. A turbine rotor blade in which an implanting portion of a rotor blade is inserted into a groove of a disk and is supported by an elastic body disposed between the groove and the implanting portion. A damper for a turbine rotor blade, which is inserted in contact with a lower surface of a blade platform and in a pressure contact state between a side surface of a groove and an implant portion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1558692A JPH0626302A (en) | 1992-01-30 | 1992-01-30 | Turbine blade damper |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1558692A JPH0626302A (en) | 1992-01-30 | 1992-01-30 | Turbine blade damper |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH0626302A true JPH0626302A (en) | 1994-02-01 |
Family
ID=11892834
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1558692A Withdrawn JPH0626302A (en) | 1992-01-30 | 1992-01-30 | Turbine blade damper |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0626302A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2019157663A (en) * | 2018-03-08 | 2019-09-19 | 三菱重工業株式会社 | Rotor blade body and rotary machine |
| WO2021013280A1 (en) * | 2019-07-19 | 2021-01-28 | MTU Aero Engines AG | Intermediate element for a blade/rotor disc connection in a rotor of a turbomachine, associated rotor for a turbomachine, and turbomachine |
| CN113898418A (en) * | 2021-11-12 | 2022-01-07 | 西安热工研究院有限公司 | A rotating machinery blade with expandable graphite damping |
-
1992
- 1992-01-30 JP JP1558692A patent/JPH0626302A/en not_active Withdrawn
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2019157663A (en) * | 2018-03-08 | 2019-09-19 | 三菱重工業株式会社 | Rotor blade body and rotary machine |
| WO2021013280A1 (en) * | 2019-07-19 | 2021-01-28 | MTU Aero Engines AG | Intermediate element for a blade/rotor disc connection in a rotor of a turbomachine, associated rotor for a turbomachine, and turbomachine |
| US11905852B2 (en) | 2019-07-19 | 2024-02-20 | MTU Aero Engines AG | Intermediate element for a blade/rotor disc connection in a rotor of a turbomachine, associated rotor for a turbomachine, and turbomachine |
| CN113898418A (en) * | 2021-11-12 | 2022-01-07 | 西安热工研究院有限公司 | A rotating machinery blade with expandable graphite damping |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A300 | Withdrawal of application because of no request for examination |
Free format text: JAPANESE INTERMEDIATE CODE: A300 Effective date: 19990408 |