JPH0618601U - Turbine blade damper - Google Patents
Turbine blade damperInfo
- Publication number
- JPH0618601U JPH0618601U JP5608892U JP5608892U JPH0618601U JP H0618601 U JPH0618601 U JP H0618601U JP 5608892 U JP5608892 U JP 5608892U JP 5608892 U JP5608892 U JP 5608892U JP H0618601 U JPH0618601 U JP H0618601U
- Authority
- JP
- Japan
- Prior art keywords
- groove
- damper
- plate
- implanting
- implant
- 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- Withdrawn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
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
張時及び高速回転時の応力緩和を図るとともに、抜け止
め防止を容易にかつ確実に実施する。
【構成】 溝と植込み部とに弾性接触状態に配される板
状の緩衝部と、該緩衝部の両端部に一体に配され屈曲時
に溝の外縁部に接触して抜け止めされる板状の移動抑制
部とを具備する。
(57) [Summary] [Purpose] This relates to a damper for turbine rotor blades, which is intended to relieve stress during thermal expansion and high-speed rotation, and to easily and reliably prevent disengagement. A plate-shaped cushioning portion disposed in elastic contact with the groove and the implant portion, and a plate-shaped cushioning portion integrally disposed at both ends of the cushioning portion and contacting an outer edge portion of the groove during bending to prevent slippage And a movement restraining section.
Description
【０００１】[0001]
本考案は、タービン動翼のダンパーに係り、特に、植込み部の緩衝と抜け止め とを図る技術に関するものである。 The present invention relates to a damper for a turbine rotor blade, and more particularly to a technique for cushioning and preventing the implant portion from coming off.
【０００２】[0002]
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。 Some turbine blades of gas turbines are used at a high temperature of 1300 ° C., for example, and ceramic parts are expected to be used to ensure heat resistance.
【０００３】 図３は、タービン翼の取り付け構造の例を示すものである。 図３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. 3 shows an example of a turbine blade mounting structure. In FIG. 3, reference numeral 1 is a disk, 2 is a groove, 3 is a moving blade, 4 is an implant portion, 5 is a root, 6 is a platform, 7 is a neck portion, and 8 is an overhang portion. The implanting portion 4 of the rotor 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]
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。 この場合、接触部分に何等かの緩衝材を介在させた構造とすることが有力であ るが、植込み部４及び緩衝材が振動等によって抜け出さないようにすることや、 組み立て時の作業性を損わないようにすることも要求される。 However, if the turbine blade, that is, the moving blade 3 is a ceramic component, the thermal expansion of the disk 1, which is a metal component, becomes larger than the implant portion 4 of the moving blade 3 having a small thermal expansion at a high temperature of 1300 ° C. As a result, the clearance between the groove 2 and the implanting portion 4 becomes non-uniform, and the moving blade 3 rotates at a high speed, so that the implanting portion 4 strongly contacts the overhanging portion 8 in an attempt to move radially outward due to centrifugal force. However, stress may be generated at this contact area, leading to destruction. In this case, it is effective to have a structure in which some cushioning material is interposed at the contact portion, but it is necessary to prevent the implanting part 4 and the cushioning material from coming off due to vibrations, etc., and to improve workability during assembly. It is also required to prevent damage.
【０００５】 本考案は、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 応力緩和を図るとともに、抜け止め防止を容易にかつ確実に実施することを目的 としている。The present invention has been made in view of these circumstances, and an object thereof is to alleviate stress during thermal expansion and high-speed rotation, and to easily and surely prevent disengagement.
【０００６】[0006]
上記目的を達成するため、ディスクの溝へのタービン動翼の植込み部の挿入時 に、溝と植込み部との間に介在状態に配されるダンパーであって、溝と植込み部 とに弾性接触状態に配される板状の緩衝部と、該緩衝部の両端部に一体に配され 屈曲時に溝の外縁部に接触して抜け止めされる板状の移動抑制部とを具備する構 成を採用している。 In order to achieve the above-mentioned object, a damper that is disposed between the groove and the implanting portion when the implanting portion of the turbine blade is inserted into the groove of the disk and elastically contacts the groove and the implanting portion. And a plate-shaped movement suppressing portion that is integrally arranged at both end portions of the buffer portion and that is prevented from coming off by coming into contact with the outer edge portion of the groove during bending. It is adopted.
【０００７】[0007]
ダンパーの緩衝部が、溝と植込み部との間に弾性接触状態に介在することによ 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 。 緩衝部の両端部に一体に配される板状の移動抑制部は、屈曲させた形状とする ことによって、溝の外縁部とタービン動翼の植込み部とに接触し、植込み部及び 緩衝部の移動を抑制する。 Since the buffer part of the damper is elastically contacted between the groove and the implant part, the contact pressure of the contact part between the groove and the implant part caused by centrifugal force or the like is relaxed. The plate-shaped movement restraint parts, which are integrally arranged at both ends of the shock-absorbing part, are bent so that they contact the outer edge part of the groove and the implant part of the turbine rotor blade, and Control movement.
【０００８】[0008]
以下、本考案に係るタービン動翼のダンパーの一実施例について、図１及び図 ２に基づいて説明する。 図中、符号１０はダンパー、１１は板状の緩衝部（緩衝部）、１２は板状の移 動抑制部（移動抑制部）、Ｌは折曲げ線である。 An embodiment of a damper for a turbine rotor blade according to the present invention will be described below with reference to FIGS. 1 and 2. In the figure, reference numeral 10 is a damper, 11 is a plate-shaped cushioning portion (buffering portion), 12 is a plate-like movement suppressing portion (movement suppressing portion), and L is a bending line.
【０００９】 該一実施例におけるダンパー１０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を挿入する場合に、溝２と植込み部４との間に介 在状態に配されるものである。As shown in FIG. 1, the damper 10 according to the embodiment includes a groove 2 of a metal disk 1 and a groove 2 and a groove 4 of a blade 3 when the blade 4 is inserted into the groove 2. It is placed in an intervening state.
【００１０】 前記緩衝部１１は、例えばステンレス鋼からなる弾性変形容易な厚さ０．０５ ｍｍないし０．５ｍｍの薄板によって構成される。The buffer portion 11 is made of, for example, a thin plate made of stainless steel and having a thickness of 0.05 mm to 0.5 mm that is easily elastically deformed.
【００１１】 前記移動抑制部１２は、例えばステンレス鋼からなる厚さ１．０ｍｍ程度の薄 板によって構成され、かつ、緩衝部１１の両端部に折曲げ線Ｌの部分から折り曲 げ可能に一体に配されるものである。The movement suppressing portion 12 is made of a thin plate made of, for example, stainless steel and having a thickness of about 1.0 mm, and is integrally formed at both ends of the buffer portion 11 so as to be bendable from a portion of the bending line L. Are to be distributed to.
【００１２】 これら緩衝部１１と移動抑制部１２との一体化は、２種類の金属板を重ねて、 スポット溶接や接着等を施す方法や、緩衝部１１の部分をプレス加工して薄くし て不要部分を削除する方法等によって実施される。The buffering part 11 and the movement suppressing part 12 are integrally formed by stacking two kinds of metal plates and performing spot welding or bonding, or by pressing the part of the buffering part 11 to be thin. It is implemented by a method of deleting unnecessary portions.
【００１３】 ダンパー１０を溝２と植込み部４との間隙に挿入する場合について説明すると 、例えば、動翼３における植込み部４を溝２の中に挿入する作業に先立って、挿 入側の移動抑制部１２と緩衝部１１をＵ字状に折り曲げた状態にして溝２の中に 挿入し、この場合に一対の移動抑制部１２の部分を溝２の両端部から突出させた 状態となるようにダンパー１０を装填する。The case of inserting the damper 10 into the gap between the groove 2 and the implanting portion 4 will be described. For example, prior to the work of inserting the implanting portion 4 in the moving blade 3 into the groove 2, the insertion side movement is performed. The restraining portion 12 and the cushioning portion 11 are bent into a U-shape and inserted into the groove 2, and in this case, a part of the pair of movement restraining portions 12 is projected from both ends of the groove 2. Then, the damper 10 is loaded on the.
【００１４】 次いで、動翼３における植込み部４を、緩衝部１１が溝２と植込み部４との間 に介在させた状態となるように溝２に挿入する。Next, the implanting portion 4 of the moving blade 3 is inserted into the groove 2 so that the cushioning portion 11 is interposed between the groove 2 and the implanting portion 4.
【００１５】 溝２と植込み部４と緩衝部１１との位置合わせを行なった後、Ｕ字状（または Δ状等に）に折り曲げた移動抑制部１２をいったん元の平坦状に広げ、その後移 動抑制部１２の部分を折曲げ線Ｌから折り曲げて、図１に示す屈曲状態とする。 この状態にあっては、移動抑制部１２が溝２の外縁部や植込み部４の両端部に 接触し、溝２の長手方向の相互移動を抑制するため、ディスク１の回転状態及び 非回転状態において、植込み部４及びダンパー１０のずれ発生を防止するものと なる。After aligning the groove 2, the implant portion 4, and the buffer portion 11, the movement suppressing portion 12 bent into a U shape (or Δ shape) is once expanded to its original flat shape, and then transferred. The portion of the motion suppressing portion 12 is bent from the bending line L to be in the bent state shown in FIG. In this state, the movement suppressing portion 12 comes into contact with the outer edge portion of the groove 2 and both end portions of the implanting portion 4 to suppress mutual movement of the groove 2 in the longitudinal direction. In the above, the occurrence of displacement of the implanting portion 4 and the damper 10 is prevented.
【００１６】 また、運転時の遠心力や熱変形によって、溝２と植込み部４との間隙が変化し た場合には、緩衝部１１が、溝２と植込み部４との間に弾性接触状態に介在し続 けることによって、接触部分の接触圧力の変動を小さくし、発生応力を緩和する ことができる。In addition, when the gap between the groove 2 and the implant portion 4 changes due to centrifugal force or thermal deformation during operation, the buffer portion 11 is in an elastic contact state between the groove 2 and the implant portion 4. By continuing to intervene, the fluctuation of the contact pressure at the contact portion can be reduced and the generated stress can be relieved.
【００１７】[0017]
以上説明したように、本考案に係るタービン動翼のダンパーによれば、ダンパ ーが、溝と植込み部とに弾性接触状態に配される板状の緩衝部と、該緩衝部の両 端部に一体に配され屈曲時に溝の外縁部に接触して抜け止めされる板状の移動抑 制部とを具備するものであるから、以下の優れた効果が得られる。 （１） 移動抑制部を屈曲させた形状とすることによって、溝の外縁部とタービ ン動翼の植込み部とに接触させ、植込み部及び緩衝部の移動を抑制することがで きる。 （２） 緩衝部が、溝と植込み部との間に弾性接触状態に介在することによって 、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平均化させて 発生応力を緩和することができる。 （３） 緩衝部と移動抑制部との一体化により、タービン動翼及び緩衝部の抜け 止め作業を容易に実施することができる。 As described above, according to the damper for a turbine rotor blade of the present invention, the damper includes a plate-shaped cushioning portion disposed in elastic contact with the groove and the implant portion, and both end portions of the cushioning portion. Since it has a plate-shaped movement suppressing portion which is integrally arranged on the base plate and which is prevented from coming off by coming into contact with the outer edge portion of the groove when bent, the following excellent effects can be obtained. (1) By making the movement restraining portion into a bent shape, it is possible to restrain the movement of the implantation portion and the cushioning portion by contacting the outer edge portion of the groove and the implantation portion of the turbine blade. (2) Since the buffer section is interposed between the groove and the implant section in an elastic contact state, the contact pressure of the contact section between the groove and the implant section caused by centrifugal force is averaged to alleviate the generated stress. be able to. (3) By integrating the buffer unit and the movement suppressing unit, the work of preventing the turbine rotor blades and the buffer unit from coming off can be easily performed.
【図１】本考案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のダンパー部分の展開図である。FIG. 2 is a development view of a damper portion of FIG.
【図３】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. 3 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 ５ 羽根 ６ プラットホーム ７ ネック部 ８ 張り出し部 １０ ダンパー １１ 板状の緩衝部（緩衝部） １２ 板状の移動抑制部（移動抑制部） Ｌ 折曲げ線 1 Disc 2 Groove 3 Moving Blade 4 Implantation Part 5 Blade 6 Platform 7 Neck Part 8 Overhanging Part 10 Damper 11 Plate-shaped Buffer Part (Buffer Part) 12 Plate-shaped Movement Restriction Part (Movement Restriction Part) L Bending Line
Claims (1)
部の挿入時に、溝と植込み部との間に介在状態に配され
るダンパーであって、溝と植込み部とに弾性接触状態に
配される板状の緩衝部と、該緩衝部の両端部に一体に配
され屈曲時に溝の外縁部に接触して抜け止めされる板状
の移動抑制部とを具備することを特徴とするタービン動
翼のダンパー。1. A damper which is disposed between the groove and the implanting portion when the implanting portion of the turbine rotor blade is inserted into the groove of the disk, the damper being disposed in elastic contact with the groove and the implanting portion. And a plate-shaped movement suppressing portion that is integrally disposed at both ends of the buffer portion and that prevents the slip-out from coming into contact with the outer edge portion of the groove during bending. Moving blade damper.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5608892U JPH0618601U (en) | 1992-08-10 | 1992-08-10 | Turbine blade damper |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5608892U JPH0618601U (en) | 1992-08-10 | 1992-08-10 | Turbine blade damper |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH0618601U true JPH0618601U (en) | 1994-03-11 |
Family
ID=13017345
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP5608892U Withdrawn JPH0618601U (en) | 1992-08-10 | 1992-08-10 | Turbine blade damper |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0618601U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015075970A1 (en) * | 2013-11-20 | 2015-05-28 | 三菱重工業株式会社 | Turbine rotor assembly, blade stop plate for turbine rotor assembly, and method for assembling blade stop plate |
| JP2016205402A (en) * | 2016-08-29 | 2016-12-08 | 三菱重工業株式会社 | Blade stop plate |
-
1992
- 1992-08-10 JP JP5608892U patent/JPH0618601U/en not_active Withdrawn
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2015075970A1 (en) * | 2013-11-20 | 2015-05-28 | 三菱重工業株式会社 | Turbine rotor assembly, blade stop plate for turbine rotor assembly, and method for assembling blade stop plate |
| JP2015098848A (en) * | 2013-11-20 | 2015-05-28 | 三菱重工業株式会社 | Turbine rotor assembly, blade stop plate in turbine rotor assembly, and blade stop plate assembly method |
| JP2016205402A (en) * | 2016-08-29 | 2016-12-08 | 三菱重工業株式会社 | Blade stop plate |
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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: 19961107 |