JPH09228801A - Integral shroud blade - Google Patents
Integral shroud bladeInfo
- Publication number
- JPH09228801A JPH09228801A JP3954196A JP3954196A JPH09228801A JP H09228801 A JPH09228801 A JP H09228801A JP 3954196 A JP3954196 A JP 3954196A JP 3954196 A JP3954196 A JP 3954196A JP H09228801 A JPH09228801 A JP H09228801A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- section
- twisting
- tip
- gas flow
- 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
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、タービン動翼の羽
根と一体に形成されたインテグラルシュラウド翼に関す
る。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an integral shroud blade integrally formed with a blade of a turbine rotor blade.
【０００２】[0002]
【従来の技術】インテグラルシュラウド翼の全貌を示す
図６，図７を参照し、図８，図９に基づいて従来の技術
を説明する。2. Description of the Related Art A conventional technique will be described with reference to FIGS. 6 and 7, which show the overall appearance of an integral shroud blade, and based on FIGS.
【０００３】従来の回転機械、例えば、蒸気タービンの
高圧段、及び中圧段の動翼に採用されているインテグラ
ルシュラウド翼の翼断面は、図６，図７及び図８に示す
ように翼根元部（以後ＢＡＳＥという）１ａと翼先端部
（以後ＴＩＰという）１ｂとは、ほぼ同一の断面形状で
ある。つまり図８において、ＢＡＳＥ１ａ断面とＴＩＰ
１ｂ断面とはほぼ同一形状であり、半径方向からみると
重なっている。また、シュラウド２も総て同じ形状で形
成されている。As shown in FIGS. 6, 7 and 8, the blade cross section of an integral shroud blade employed in a conventional rotary machine, for example, a high-pressure stage blade and a medium-pressure stage blade of a steam turbine has a blade cross section as shown in FIGS. The root portion (hereinafter referred to as BASE) 1a and the blade tip portion (hereinafter referred to as TIP) 1b have substantially the same cross-sectional shape. That is, in FIG. 8, the BASE1a cross section and the TIP
The 1b cross section has almost the same shape and overlaps when viewed in the radial direction. The shrouds 2 are also formed in the same shape.
【０００４】なお、図６，図７中、３は翼根部、４はプ
ラットホームである。In FIGS. 6 and 7, 3 is a blade root portion, and 4 is a platform.
【０００５】[0005]
【発明が解決しようとする課題】前記したように、従来
の回転機械、例えば、蒸気タービンの高圧段、及び、中
圧段の動翼に採用されているインテグラルシュラウド翼
１においては、総て同じシュラウド２形状で形成されて
おり、かつ、ＢＡＳＥ１ａ断面とＴＩＰ１ｂ断面はほぼ
同一であり、タービン回転時の遠心力による捩り戻り変
形が生じない。As described above, all of the conventional rotary machines, for example, the integral shroud blades 1 used in the moving blades of the high-pressure stage and the intermediate-pressure stage of the steam turbine are all used. They are formed in the same shroud 2 shape, and the BASE1a cross section and the TIP1b cross section are almost the same, so that torsional deformation due to centrifugal force during turbine rotation does not occur.
【０００６】このため、平行翼では先の捩り戻り変形が
生じないので、回転時の遠心力による半径方向の翼の伸
び、あるいは熱伸びによりシュラウド２隙間が拡がり、
シュラウド２に初期隙間を零としていても、あるタービ
ン回転数以上になると隣接するシュラウド２が互いに離
れ、図９に示す如く単独翼の振動特性を有する事にな
る。For this reason, since the above-mentioned torsional deformation does not occur in the parallel blade, the shroud 2 gap expands due to the radial expansion of the blade due to the centrifugal force during rotation or the thermal expansion,
Even if the initial clearance of the shroud 2 is zero, adjacent shrouds 2 are separated from each other at a certain turbine rotation speed or more, and have the vibration characteristics of a single blade as shown in FIG.
【０００７】単独翼の振動特性は、図９に示す様に、無
限翼、あるいは有限な綴り枚数で構成される有限翼に比
較して振動数が低く、又翼と翼との連結部で発生する構
造減衰も無いので、振動強度は数分の１に低下する。そ
の為に、従来は単独翼１次モードの振動数を回転振動試
験により計測し、共振回避を行っている。この場合に
は、シュラウド２の厚さ等を変更して翼振動数を変え、
再度確認試験が必要であり、膨大な試験費用を必要とす
る。As shown in FIG. 9, the vibration characteristics of a single blade are lower than those of an infinite blade or a finite blade composed of a finite number of sheets, and the vibration characteristics are generated at the connecting portion between the blades. Since there is no structural damping, the vibration intensity is reduced to a fraction. For that reason, conventionally, the frequency of the single-wing primary mode is measured by a rotational vibration test to avoid resonance. In this case, change the thickness of the shroud 2 etc. to change the blade frequency,
Confirmation test is required again, and enormous test cost is required.
【０００８】本発明はこのような不具合を解消した新規
にして有益なインテグラルシュラウド翼を提供すること
を課題とするものである。An object of the present invention is to provide a novel and useful integral shroud blade that solves such a problem.
【０００９】[0009]
【課題を解決するための手段】本発明は前記課題を解決
するべくなされたもので、翼の先端部に一体型のシュラ
ウドを有するタービン動翼において、ガス流の出口側を
翼根元部から翼先端方向に行くに従って背側へ捩ってい
った翼断面形状としたインテグラルシュラウド翼を提供
し、このように翼を捩ることにより、回転時の捩り戻り
変形と相殺させて全周繋がった無限翼振動特性により振
動等を安定させ、信頼性の高い翼を得るようにしたもの
である。SUMMARY OF THE INVENTION The present invention has been made to solve the above problems, and in a turbine moving blade having an integral shroud at the tip of the blade, the outlet side of the gas flow is moved from the blade root to the blade. We provide an integral shroud blade with a blade cross-sectional shape that twists to the back side as it goes to the tip direction, and by twisting the blade in this way, it cancels out the torsional deformation at the time of rotation and infinitely connected all around. It is intended to obtain a highly reliable blade by stabilizing the vibration and the like by the blade vibration characteristic.
【００１０】[0010]
【発明の実施の形態】本発明の実施の形態を、図１ない
し図５により説明する。なお、インテグラルシュラウド
翼の全貌を示す図６及び図７も適宜参照し、また従来の
技術として図８等で説明したものと同一の部位について
は同一の符号及び同一の呼び名を用いて示し、相互の関
連性を明確にして理解し易いようにしている。BEST MODE FOR CARRYING OUT THE INVENTION An embodiment of the present invention will be described with reference to FIGS. 6 and 7 showing the whole view of the integral shroud blade are appropriately referred to, and the same parts as those described in FIG. 8 and the like as a conventional technique are indicated by the same reference numerals and the same names. The mutual relationships are clarified so that they are easy to understand.
【００１１】図６，図７は、インテグラルシュラウド翼
の正面図及び側面図であり、図１は平面図を示す。図１
において、ＢＡＳＥ１ａ断面に対して、ＴＩＰ１ｂ断面
の出口部を背側に偏心させる。図２ないし図４は、作動
に際して遠心力Ｆにより、ＴＩＰ１ｂ断面はＢＡＳＥ１
ａ断面に戻ろうとするモーメントＭが発生し、捩り戻り
変形θが生じる事を示す説明図である。6 and 7 are a front view and a side view of the integral shroud blade, and FIG. 1 shows a plan view. FIG.
In, the outlet of the TIP1b section is eccentric to the back side with respect to the BASE1a section. 2 to 4, the TIP1b cross section is BASE1 due to centrifugal force F during operation.
It is explanatory drawing which shows that the moment M which tries to return to a section a is generated, and the torsion return deformation (theta) arises.
【００１２】ＢＡＳＥ１ａ断面を規準とした時に、ＴＩ
Ｐ１ｂ断面の出口部を背側に偏心させると、前記の如
く、捩り戻り変形θが生じる。この変形を利用して全周
繋がった無限翼振動特性を持たせ、振動強度を向上させ
る事が出来る。When the BASE1a cross section is used as a standard, TI
When the outlet of the P1b cross section is eccentric to the back side, as described above, the twist-back deformation θ occurs. By utilizing this deformation, it is possible to improve the vibration strength by giving the infinite wing vibration characteristics that are connected all around.
【００１３】この点を更に詳しく説明すれば、以下の通
りである。This point will be described in more detail below.
【００１４】図１，図３に示す如く、ＢＡＳＥ１ａ断面
を規準とした時に、ＴＩＰ１ｂ断面の出口部を背側に捩
ると、図２示す様に、タービン回転時に発生する遠心力
Ｆにより、ＴＩＰ１ｂ断面はＢＡＳＥ１ａ断面に戻ろう
とするモーメントＭが発生し、捩り戻り変形θが生じ
る。As shown in FIGS. 1 and 3, when the outlet of the TIP1b section is twisted backward when the BASE1a section is taken as a reference, the TIP1b section is generated by the centrifugal force F generated when the turbine rotates as shown in FIG. Generates a moment M that tries to return to the BASE1a cross section, and causes torsional deformation θ.
【００１５】この変形を利用して全周繋がった無限翼振
動特性を持たせ、振動強度を向上させる事が出来る。By utilizing this deformation, it is possible to improve the vibration strength by providing the infinite blade vibration characteristic that is connected all around.
【００１６】尚、図１において、隣合うシュラウド
Ｂ1 ，Ｂ2 の翼型の捩り中心をＧ、シュラウド出口端の
隣接部をＡ、又、シュラウドの角度をβとし、更に、図
７において、Ｇ−Ａ−Ｇの成す角をα，Ｇ−Ａ間の距離
をＲ（Ｒ1 又はＲ2 ）とすると、点Ａにおける、シュラ
ウド接触面の法線方向の変形量ΔＸ（ΔＸ1 又はΔ
Ｘ2 ）は、式１の如く計算出来る。（シュラウド接触方
向の符号を正とする）In FIG. 1, the center of twist of the airfoils of adjacent shrouds B 1 and B 2 is G, the adjacent portion of the shroud outlet end is A, and the angle of the shroud is β. Further, in FIG. When the angle formed by G-A-G is α and the distance between G-A is R (R 1 or R 2 ), the deformation amount ΔX (ΔX 1 or Δ of the shroud contact surface at the point A is normal.
X 2 ) can be calculated as in Equation 1. (The sign of the shroud contact direction is positive)
【００１７】[0017]
【数１】 [Equation 1]
【００１８】となり、捩り戻り変形θにより、シュラウ
ド隙間は狭く、つまりシュラウド反力を増加させる事が
出来る。Due to the torsional deformation θ, the shroud gap can be narrowed, that is, the shroud reaction force can be increased.
【００１９】なお、ＢＡＳＥ１ａ断面に対してＴＩＰ１
ｂ断面を背側に捩る事が重要であり、逆に腹側に捩る
と、シュラウド隙間が拡がり期待する効果は得られない
ことを注意しなければならない。Note that TIP1 is applied to the cross section of BASE1a.
It should be noted that it is important to twist the b-section to the back side, and conversely, if it is twisted to the abdomen side, the shroud gap widens and the expected effect cannot be obtained.
【００２０】なおまた、図５は本実施の形態において予
想されるタービン回転数に対する翼振動数の変化を示す
キャンベル線図である。Further, FIG. 5 is a Campbell diagram showing a change in the blade frequency with respect to the turbine rotation speed expected in the present embodiment.
【００２１】定格回転数まで無限翼の振動特性を維持し
ており、隣接するシュラウド２部で発生する乾性摩擦に
よる構造減衰で、振動応力を低減でき、タービン翼の信
頼性を大幅に向上させる事が出来る。The vibration characteristics of the infinite blade are maintained up to the rated rotation speed, and the structural stress due to the dry friction generated in the adjacent two parts of the shroud can reduce the vibration stress and greatly improve the reliability of the turbine blade. Can be done.
【００２２】以上、本発明を図示の実施の形態について
説明したが、本発明はかかる実施の形態に限定されず、
本発明の範囲内でその具体的構造に種々の変更を加えて
よいことはいうまでもない。Although the present invention has been described with reference to the illustrated embodiment, the present invention is not limited to such an embodiment.
It goes without saying that various modifications may be made to the specific structure within the scope of the present invention.
【００２３】[0023]
【発明の効果】以上本発明によれば、タービン翼をＢＡ
ＳＥからＴＩＰに行くに従い背側へ捩ることにより定格
回転数まで常に無限翼とした振動特性を維持する事がで
きタービン翼の信頼性を大幅に向上させることができた
ものである。As described above, according to the present invention, the turbine blade is
By twisting backward from SE to TIP, it is possible to maintain the vibration characteristics of an infinite blade up to the rated rotation speed and greatly improve the reliability of the turbine blade.
【図１】本発明の実施の一形態に係るインテグラルシュ
ラウド翼の平面図。FIG. 1 is a plan view of an integral shroud blade according to an embodiment of the present invention.
【図２】図１のインテグラルシュラウド翼の捩り戻り変
形の説明図。FIG. 2 is an explanatory view of twist-back deformation of the integral shroud blade of FIG.
【図３】図２と同様のインテグラルシュラウド翼の捩り
戻り変形の説明図。FIG. 3 is an explanatory view of torsional deformation of the integral shroud blade similar to FIG.
【図４】図２，図３と同様のインテグラルシュラウド翼
の捩り戻り変形の説明図。FIG. 4 is an explanatory view of torsional deformation of an integral shroud blade similar to FIGS. 2 and 3.
【図５】図１のインテグラルシュラウド翼のキャンベル
線図。5 is a Campbell diagram of the integral shroud wing of FIG.
【図６】図１のものを含む一般的なインテグラルシュラ
ウド翼の正面図。6 is a front view of a typical integral shroud wing including that of FIG.
【図７】図６の側面図。FIG. 7 is a side view of FIG. 6;
【図８】従来のインテグラルシュラウド翼の平面図。FIG. 8 is a plan view of a conventional integral shroud blade.
【図９】従来のインテグラルシュラウド翼のキャンベル
線図。FIG. 9 is a Campbell diagram of a conventional integral shroud wing.
１ 翼 １ａ ＢＡＳＥ部 １ｂ ＴＩＰ部 ２ シュラウド ３ 翼根部 ４ プラットホーム 1 Wing 1a BASE part 1b TIP part 2 Shroud 3 Wing root part 4 Platform
Claims (1)
タービン動翼において、ガス流の出口側を翼根元部から
翼先端方向へ行くに従って背側へ捩っていった翼断面形
状としたことを特徴とするインテグラルシュラウド翼。1. In a turbine blade having an integral shroud at the blade tip, the outlet side of the gas flow has a blade cross-sectional shape in which it is twisted to the back side from the blade root toward the blade tip. Integral shroud wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3954196A JPH09228801A (en) | 1996-02-27 | 1996-02-27 | Integral shroud blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3954196A JPH09228801A (en) | 1996-02-27 | 1996-02-27 | Integral shroud blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH09228801A true JPH09228801A (en) | 1997-09-02 |
Family
ID=12555921
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP3954196A Pending JPH09228801A (en) | 1996-02-27 | 1996-02-27 | Integral shroud blade |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH09228801A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2003033880A1 (en) * | 2001-10-10 | 2003-04-24 | Hitachi, Ltd. | Turbine blade |
-
1996
- 1996-02-27 JP JP3954196A patent/JPH09228801A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2003033880A1 (en) * | 2001-10-10 | 2003-04-24 | Hitachi, Ltd. | Turbine blade |
| US7018174B2 (en) | 2001-10-10 | 2006-03-28 | Hitachi, Ltd. | Turbine blade |
| CN1313709C (en) * | 2001-10-10 | 2007-05-02 | 株式会社日立制作所 | Turbine blade |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A02 | Decision of refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A02 Effective date: 20030805 |