JPS61252804A - Device for coupling tip of moving vane of turbine - Google Patents
Device for coupling tip of moving vane of turbineInfo
- Publication number
- JPS61252804A JPS61252804A JP9367285A JP9367285A JPS61252804A JP S61252804 A JPS61252804 A JP S61252804A JP 9367285 A JP9367285 A JP 9367285A JP 9367285 A JP9367285 A JP 9367285A JP S61252804 A JPS61252804 A JP S61252804A
- Authority
- JP
- Japan
- Prior art keywords
- rotor blade
- blade
- rotor
- blades
- 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
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【発明の詳細な説明】
〔発明の利用分野〕
本発明はタービン動翼をその先端部において連結し、動
翼先端部と外周壁間における流体の漏洩を防止する装置
に関する。DETAILED DESCRIPTION OF THE INVENTION [Field of Application of the Invention] The present invention relates to a device for connecting turbine rotor blades at their tips and preventing fluid leakage between the tips of the rotor blades and an outer peripheral wall.
タービン動翼を連結部材によって互いに連結する装置構
造は多種、多岐にわたっているが、そのうち、全周のす
べての翼を円周方向に添って連結 ′の切れ目がないよ
うに連結する装置・構造がある。There are many different types of device structures that connect turbine rotor blades to each other using connecting members, but among them, there is a device and structure that connects all the blades around the entire circumference in a circumferential direction so that there is no break in the blades. .
この構造を総称して、全周一リング構造と呼び、これに
対して、複数本の翼単位で翼の円周方向に連結の切れ目
がある構造を単に群翼構造と呼ぶことにする。これらの
翼構造を振動特性上比較すると、同じ種類の翼を群翼構
造とした場合に比べ、全周一リング構造とした場合、固
有の振動モードの数は、一般に多くなる。しかし、一般
にタービン回転数の整数倍の周波数を持っ励振力を受け
た場合の共振点の数は逆に群真の場合に比べはるかに少
くなり、タービンの運転範囲において共振を回避した翼
設計を行う上で非常に有利なことは良く知られている。This structure is collectively referred to as a full-circumference one-ring structure, whereas a structure in which a plurality of blades are connected in a circumferential direction is simply referred to as a group blade structure. Comparing these blade structures in terms of their vibration characteristics, when the same type of blade has a group structure, the number of unique vibration modes is generally larger when the blade has a one-ring structure all around the circumference. However, in general, when receiving an excitation force with a frequency that is an integral multiple of the turbine rotation speed, the number of resonance points is much smaller than in the case of a group true, so it is important to design blades that avoid resonance within the turbine operating range. It is well known that it is very advantageous to do so.
このような、全周一リング構造を動翼先端部を連結して
達成できるものの例として、例えば、特開昭52−14
107号公報に示されるように。As an example of what can be achieved by connecting the rotor blade tips to achieve such a one-ring structure all around, for example, Japanese Patent Laid-Open No. 52-14
As shown in Publication No. 107.
動翼先端部に設けた溝に連結片を挿入して隣接動翼を連
結するものが知られており、振動特性上は問題のない翼
構造が実現可能である。しかし、一般に、動翼の先端部
とその外周壁間には間隙が存在し、その間隙を作動流体
が上流から下流へ仕事をせずに漏洩して流れる問題があ
るが、全周一リング構造の例では、漏洩防止策は何ら施
されていない。It is known to connect adjacent rotor blades by inserting a connecting piece into a groove provided at the tip of the rotor blade, and it is possible to realize a blade structure with no problems in terms of vibration characteristics. However, there is generally a gap between the tip of the rotor blade and its outer peripheral wall, and there is a problem in which the working fluid leaks and flows from upstream to downstream without doing any work. In this example, no leakage prevention measures are taken.
一方、動翼先端部の漏洩防止に関しては、第3図に示す
ように動翼先端部又は、外周壁部に円周方向に延びるフ
ィンを設け、いわゆる、ラビリンスシールの効果によっ
て漏洩を防止する構造がある。しかし、この構造では、
漏洩防止性能を高めるためフィンギャップをできるだけ
小さくする必要があるが、動翼が回転時の遠心力によっ
て半径方向に大きな伸びの場合、あるいは、動翼、外周
壁の熱変形が大きい場合などは、フィンギャップをあま
り大きくできず、漏洩防止性能の著しい低下をもたらす
。On the other hand, regarding the prevention of leakage at the tip of the rotor blade, as shown in Fig. 3, fins extending in the circumferential direction are provided on the tip of the rotor blade or the outer circumferential wall, and a structure prevents leakage by the effect of a so-called labyrinth seal. There is. However, with this structure,
In order to improve leakage prevention performance, it is necessary to make the fin gap as small as possible, but in cases where the rotor blades have a large elongation in the radial direction due to centrifugal force during rotation, or when there is large thermal deformation of the rotor blades or outer peripheral wall, The fin gap cannot be made too large, resulting in a significant drop in leakage prevention performance.
本発明の目的は、全周のすべての動翼を動翼先端部にお
いて、切れ目なく連結し、動翼先端部と外周壁間の流体
の漏洩を防止する装置を提供することにある。An object of the present invention is to provide a device that seamlessly connects all rotor blades around the entire circumference at the tip of the rotor blade and prevents fluid leakage between the tip of the rotor blade and the outer peripheral wall.
本発明の特徴は、一つの動翼の先端部において、動翼長
手方向(半径方向)に対して、略直角方向に、動翼のそ
れぞれ腹側と背側に延びる突出部を設け、それぞれの突
出部の端部が隣接する動翼の突出部の端部と接する態様
に形成し、かつ、これらの突出部によって形成される外
周部が全周で、動翼の先端部を囲む略円筒面を成するよ
うに形成する。さらに、突出部外周面に一つの動翼の作
動流体入口側から、その動翼の背側に位置する動翼の出
口側に延びるあり溝を設け、このあり溝に係合して、一
つの動翼と隣接動翼を連結する連結片を次々と挿入して
、全周のすべての翼を連結するが、連結片は、動翼の外
周面を形成する円筒面よりも、半径方向外周側に突出し
た、羽根部を備え、この羽根部によって、タービン回転
時に、動翼の下流側から上流側へ流体をポンピングする
作用を持たせるところにある。A feature of the present invention is that at the tip of one rotor blade, protrusions are provided that extend toward the ventral side and the dorsal side of the rotor blade, respectively, in a direction substantially perpendicular to the longitudinal direction (radial direction) of the rotor blade. A substantially cylindrical surface that is formed in such a manner that the end of the protrusion touches the end of the protrusion of an adjacent rotor blade, and that the outer periphery formed by these protrusions is the entire circumference and surrounds the tip of the rotor blade. Form it so that it forms. Further, a dovetail groove extending from the working fluid inlet side of one rotor blade to the outlet side of the rotor blade located on the back side of the rotor blade is provided on the outer circumferential surface of the protrusion, and the dovetail groove is engaged with the rotor blade and the one rotor blade is engaged with the dovetail groove. Connecting pieces that connect the rotor blades and adjacent rotor blades are inserted one after another to connect all the blades around the entire circumference, but the connecting pieces are placed on the radially outer side of the cylindrical surface that forms the outer peripheral surface of the rotor blade. The rotor blade has a protruding blade portion, and the blade portion has the effect of pumping fluid from the downstream side to the upstream side of the rotor blade when the turbine rotates.
以下、本発明の一実施例を図面によって説明する。第1
図は本発明の一実施例を示す動翼先端付近の部分の斜視
図であり、第2図は動翼先端部を半径方向外周側より見
た平面図である。一つの動翼1aの先端部には、動翼の
長手方向(半径方向)に略直角に、それぞれ動翼の背側
へ延びる突出部2aと復側へ延びる突出部3aが設けら
れ、背側突出部2aの端部4aは、動翼1aの背側に位
置する隣接翼1bの腹側突起3bの端部5bと接するよ
うに、また、動翼1aの腹側突出部3aの端部5aは、
動翼1aの腹側に位置する隣接翼ICの背側突起2cの
端部4cと接するように形成される。また、突出部の外
周面6は、全周で略円筒面となるよう形成され、動翼先
端部を囲うリングを形成し、このリングにより動翼先端
部の流体の流れが、動翼先端外周側へ漏洩することを防
止する。さて、次に、一つの突出部2cとこれと端部で
接する突出部3aの外周面には動翼1cの先端部の作動
流体入口側から隣接動翼1aの先端部の作動流体出口側
に延びるあり溝7が設けられ、あり溝7に係合する断面
形状の連結片8が溝方向に ′挿入され、隣接翼
を連結する。一方、連結片7はあり溝に挿入された状態
で、前述の突起2,3の外周面6よりも半径方向外周側
に突出した羽根部9をもつように形成される0次に、第
2図によって説明すると、作動流体による仕事を受けて
タービン動翼が回転すると、連結片8の羽根部9により
、動翼先端の外周側では、作動流体出口側から作動流体
入口側への流れが発生する。この時の羽根部9の形状は
、作動流体出口側から入口側へ流体をポンピングするた
めに、適した翼形形状を選ぶことが望まいく、一般には
第1図、第2図に示すように羽根部9のそりの方向は1
作動流体出口側に凸な形状とするが、そりがなくともポ
ンピング作用は発生する。さて1次に動翼先端の外周側
と外周壁間の流体の漏洩防止について第41!Iによっ
て説明する。第4Imは第2図のA−A矢視断面′図で
ある1羽根部9の外周端10とタービンケーシング等の
外周壁11の間は、タービン回転時における羽根部9と
外周壁のしゆう動を防ぐため間隙12が設けられており
、この部分を通って流体は動翼1の入口側から出口側へ
漏洩して流れる。An embodiment of the present invention will be described below with reference to the drawings. 1st
The figure is a perspective view of a portion near the tip of a rotor blade showing an embodiment of the present invention, and FIG. 2 is a plan view of the tip of the rotor blade viewed from the outer peripheral side in the radial direction. At the tip of one rotor blade 1a, a protrusion 2a extending toward the back side of the rotor blade and a protrusion portion 3a extending toward the return side are provided substantially perpendicularly to the longitudinal direction (radial direction) of the rotor blade. The end 4a of the protrusion 2a is in contact with the end 5b of the ventral protrusion 3b of the adjacent blade 1b located on the dorsal side of the rotor blade 1a, and the end 5a of the ventral protrusion 3a of the rotor blade 1a. teeth,
It is formed so as to be in contact with the end portion 4c of the dorsal projection 2c of the adjacent blade IC located on the ventral side of the rotor blade 1a. The outer circumferential surface 6 of the protrusion is formed to be a substantially cylindrical surface all around, forming a ring surrounding the tip of the rotor blade, and this ring allows the flow of fluid at the tip of the rotor blade to flow around the outer circumference of the tip of the rotor blade. Prevent leakage to the outside. Now, next, the outer circumferential surface of one protrusion 2c and the protrusion 3a that contacts this at the end is connected from the working fluid inlet side of the tip of the rotor blade 1c to the working fluid outlet side of the tip of the adjacent rotor blade 1a. An extending dovetail groove 7 is provided, and a connecting piece 8 having a cross-sectional shape that engages with the dovetail groove 7 is inserted in the direction of the groove to connect adjacent blades. On the other hand, in the state where the connecting piece 7 is inserted into the dovetail groove, the connecting piece 7 is connected to the second 0th order, which is formed to have a blade part 9 that protrudes radially outward from the outer peripheral surface 6 of the projections 2 and 3. To explain with a diagram, when a turbine rotor blade rotates in response to work by the working fluid, a flow is generated from the working fluid outlet side to the working fluid inlet side on the outer peripheral side of the tip of the rotor blade due to the blade portion 9 of the connecting piece 8. do. At this time, it is desirable to select a suitable airfoil shape for the shape of the vane portion 9 in order to pump the fluid from the working fluid outlet side to the inlet side.Generally, it is as shown in Figs. 1 and 2. The direction of warpage of the blade part 9 is 1
Although the shape is convex toward the working fluid outlet side, the pumping action occurs even without warpage. Now, the first step is to prevent fluid leakage between the outer circumferential side of the rotor blade tip and the outer circumferential wall. Explained by I. 4Im is a cross-sectional view taken along the line A-A in FIG. A gap 12 is provided to prevent movement, through which fluid leaks and flows from the inlet side to the outlet side of the moving blade 1.
この漏洩流は仕事をしない流れであり、タービンの効率
の低下の原因となる。しかし、羽根部9の作用により、
動翼出12側から入口側への流れが誘起されるので、第
4図矢印13に示すような循環流が、動翼先端外周部と
外周壁間の全体、または、一部に発生し、動翼先端外周
部部において流体が、動翼入口側から出口側へ漏洩する
ことを防止する効果を持つに至る。この漏洩防止効果に
より、タービン効率の向上がはかれる。なお、本発明で
は羽根部9を設けるので、タービン回転に対してブレー
キ効果を発生させ、軸出力は羽根部9がない場合に比べ
て減少するが、羽根部形状を最適にすることにより、上
述の漏洩防止による効率向上による軸出力の増加より少
ない動力で羽根部9を駆動することができ、タービン効
率を向上させることができる。This leakage flow is a flow that does not perform work and causes a decrease in turbine efficiency. However, due to the action of the blade part 9,
Since a flow is induced from the rotor blade outlet 12 side to the inlet side, a circulating flow as shown by the arrow 13 in FIG. This has the effect of preventing fluid from leaking from the rotor blade inlet side to the outlet side at the outer peripheral portion of the rotor blade tip. This leakage prevention effect improves turbine efficiency. In addition, since the blade part 9 is provided in the present invention, a braking effect is generated on the turbine rotation, and the shaft output is reduced compared to the case without the blade part 9. However, by optimizing the blade part shape, the above-mentioned effect can be achieved. The blade portion 9 can be driven with less power than the increase in shaft output due to efficiency improvement due to leakage prevention, and turbine efficiency can be improved.
なお、連結片8の上部に設ける羽根部は、翼形形状をな
すものとして限定したが、第5図に示すように、連結片
8の長手方向に略平行な突起9′を設けるだけでも、ポ
ンピング効果を発揮することができる。Note that the blades provided on the upper part of the connecting piece 8 are limited to those having an airfoil shape, but as shown in FIG. It can exert a pumping effect.
また、本発明では連結片8はあり溝7に挿入された後、
適当な手段で抜は防止が施されるが、抜は防止の例とし
て第6図に示す構造をとることも可能である。すなわち
、あり溝7の一端13は突出部3によってふさがれてお
り、このあり溝7に、連結片8を挿入した後、図中二点
鎖線で示す翼ldを設置することにより、その突出部2
dにより、連結片8の抜けを防止することができ、この
ようにして次々、連結片の抜は防止を実現できる。Further, in the present invention, after the connecting piece 8 is inserted into the dovetail groove 7,
Although removal is prevented by appropriate means, it is also possible to adopt the structure shown in FIG. 6 as an example of removal prevention. That is, one end 13 of the dovetail groove 7 is closed by the protruding part 3, and after inserting the connecting piece 8 into the dovetail groove 7, the protruding part is closed by installing the wing ld shown by the two-dot chain line in the figure. 2
d can prevent the connecting pieces 8 from coming off, and in this way, it is possible to prevent the connecting pieces from coming off one after another.
この翼構造の組立ては、全周の翼の最後の翼の組立てで
は、連結片8は別の適当な手段によって抜は防止が施さ
れる。During the assembly of this wing structure, the connecting piece 8 is prevented from being pulled out by other suitable means during the assembly of the last wing of the entire circumference.
次に、本発明の実施例では、一つの連結片は隣接する二
つの動翼の先端部のみを連結するものとんで説明したが
、本発明の主旨、効果を損うことなく、第7図に示すよ
うに、一つの連結片8が、連続する三つの動翼先端部を
連結する構造とすることも可能であり、さらには三つ以
上の動翼先端部を連結する構造とすることも可能である
。Next, in the embodiment of the present invention, one connecting piece has been described as connecting only the tips of two adjacent rotor blades. As shown in the figure, it is possible to have a structure in which one connecting piece 8 connects three consecutive rotor blade tips, and furthermore, it is also possible to have a structure in which three or more rotor blade tips are connected. It is possible.
本発明によれば、タービン動翼をその先端部において全
周の翼を切り目なく連結した、いわゆる、全周一リング
翼構造を達成でき、振動特性の優れた翼構造を提供でき
るだけでなく、動翼先端部と外周壁間の流体の漏洩を防
止でき、タービンの効率を向上させることができる。According to the present invention, it is possible to achieve a so-called full-circumference one-ring blade structure in which blades around the entire circumference of a turbine rotor blade are seamlessly connected at the tip thereof, and not only can a blade structure with excellent vibration characteristics be provided, but also Fluid leakage between the tip and the outer peripheral wall can be prevented, and the efficiency of the turbine can be improved.
第1図は1本発明の一実施例の動翼先端部の斜視図、第
2図は本発明の動翼先端部を外周側から見た平面図、第
3図は従来の動翼先端部のラビリンスシールを示す断面
図、第4図は、第2図の■−IV矢視図で本発明の動翼
先端部と外周壁間の流体の流れを示す断面図、第5図は
、本発明の変形例を示す、動翼端部構造の部分の斜視図
、第6図。
第7図は本発明の他の変形例を示す動翼先端部を外周側
より見た平面図である。
7・・・あり溝。FIG. 1 is a perspective view of a tip of a rotor blade according to an embodiment of the present invention, FIG. 2 is a plan view of a tip of a rotor blade of the present invention as viewed from the outer circumferential side, and FIG. 3 is a tip of a conventional rotor blade. FIG. 4 is a cross-sectional view showing the fluid flow between the tip of the rotor blade and the outer peripheral wall of the present invention in the direction of the ■-IV arrow in FIG. 2, and FIG. FIG. 6 is a perspective view of a portion of a rotor blade tip structure showing a modification of the invention. FIG. 7 is a plan view of the rotor blade tip section viewed from the outer peripheral side, showing another modification of the present invention. 7...Dovetail groove.
Claims (1)
それぞれ腹側と背側に延びる突出部を設け、前記突出部
の端部が、隣接する前記動翼の前記突出部の端部と接す
るように形成し、前記突出部によって形成される前記動
翼の外周部が略円筒面を成すように形成し、さらに前記
各動翼の突出部外周面に、前記動翼の流体入口側から、
前記動翼の背側に隣接する前記動翼の流体出口側に延び
るあり溝を設け、前記あり溝に係合して、隣接する前記
動翼を連結する連結片を次々と挿入して、全周のすべて
の翼を切れ目なく、連結すると共に、前記連結片は前記
動翼の突出部外周面よりも、半径方向外周側に突出した
羽根部を備え、これによりタービン回転時に、前記動翼
先端と外周壁間の流体の漏洩を防止するようにしたこと
を特徴とする、タービン動翼の先端部連結装置。[Scope of Claims] 1. A device for connecting the tips of turbine rotor blades, wherein protrusions are provided that extend toward the ventral side and the dorsal side of the rotor blades, respectively, in a direction substantially perpendicular to the longitudinal direction of the rotor blades. , an end of the protruding portion is formed so as to be in contact with an end of the protruding portion of the adjacent rotor blade, and an outer peripheral portion of the rotor blade formed by the protruding portion is formed to form a substantially cylindrical surface. Further, from the fluid inlet side of the rotor blade, on the outer circumferential surface of the protrusion of each of the rotor blades,
A dovetail groove extending to the fluid outlet side of the rotor blade adjacent to the back side of the rotor blade is provided, and connecting pieces that engage with the dovetail groove and connect the adjacent rotor blades are inserted one after another to completely In addition to seamlessly connecting all the blades around the circumference, the connecting piece includes a blade portion that protrudes toward the outer peripheral side in the radial direction than the outer peripheral surface of the protruding portion of the rotor blade, so that when the turbine rotates, the tip of the rotor blade What is claimed is: 1. A turbine rotor blade tip connection device, characterized in that it prevents fluid leakage between the blade and the outer circumferential wall.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP9367285A JPS61252804A (en) | 1985-05-02 | 1985-05-02 | Device for coupling tip of moving vane of turbine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP9367285A JPS61252804A (en) | 1985-05-02 | 1985-05-02 | Device for coupling tip of moving vane of turbine |
Publications (1)
Publication Number | Publication Date |
---|---|
JPS61252804A true JPS61252804A (en) | 1986-11-10 |
Family
ID=14088893
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP9367285A Pending JPS61252804A (en) | 1985-05-02 | 1985-05-02 | Device for coupling tip of moving vane of turbine |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPS61252804A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2427901A (en) * | 2005-06-30 | 2007-01-10 | Rolls Royce Plc | Aerofoil blade with a tip having a groove |
WO2011057613A3 (en) * | 2009-11-13 | 2011-10-27 | Mtu Aero Engines Gmbh | Coupling element for mechanically coupling blades and a rotor |
-
1985
- 1985-05-02 JP JP9367285A patent/JPS61252804A/en active Pending
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2427901A (en) * | 2005-06-30 | 2007-01-10 | Rolls Royce Plc | Aerofoil blade with a tip having a groove |
GB2427901B (en) * | 2005-06-30 | 2007-12-12 | Rolls Royce Plc | A turbofan gas turbine engine fan blade having a tip groove |
WO2011057613A3 (en) * | 2009-11-13 | 2011-10-27 | Mtu Aero Engines Gmbh | Coupling element for mechanically coupling blades and a rotor |
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