JP2000230403A - Turbine stator blade - Google Patents
Turbine stator bladeInfo
- Publication number
- JP2000230403A JP2000230403A JP11029956A JP2995699A JP2000230403A JP 2000230403 A JP2000230403 A JP 2000230403A JP 11029956 A JP11029956 A JP 11029956A JP 2995699 A JP2995699 A JP 2995699A JP 2000230403 A JP2000230403 A JP 2000230403A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- turbine
- flow
- secondary flow
- turbine blade
- 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- Withdrawn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
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明はガスタービン等の軸
流回転機械において作動流体を案内するタービン静翼に
関するものである。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a turbine vane for guiding a working fluid in an axial rotating machine such as a gas turbine.
【０００２】[0002]
【従来の技術】従来のタービン静翼の概要について、図
２に基づいて説明する。タービンの静翼は、その半径方
向外側で図示省略の車室に設けた翼環に支持され、半径
方向内側をシュラウド等で支持された複数の翼を周方向
に配列して構成されるが、代表例して一つのタービン翼
０１を図２（ａ）に示す様に、隣接する他のタービン翼
の腹側より圧力の低いタービン翼０１の背側の表面で、
同タービン翼０１のハブ（Ｈｕｂ）側とチップ（Ｔｉ
ｐ）側の端部に２次流れ０２が発生し、この２次流れ０
２が主流中に混入してタービンの作動効率の低下を招く
一つの原因となっている。2. Description of the Related Art An outline of a conventional turbine vane will be described with reference to FIG. The turbine vane is supported by a blade ring provided in a vehicle compartment (not shown) on the outer side in the radial direction, and a plurality of blades supported on the inner side in the radial direction by a shroud or the like are arranged in a circumferential direction. As a representative example, as shown in FIG. 2A, one turbine blade 01 is located on the back surface of the turbine blade 01 having a pressure lower than the ventral side of another adjacent turbine blade.
The hub (Hub) side of the turbine blade 01 and a tip (Ti
A secondary flow 02 is generated at the end on the p) side, and the secondary flow 0
2 mixes into the mainstream and is one of the causes of lowering the operating efficiency of the turbine.
【０００３】この２次流れ０２の発生を抑制し、２次流
れ損失の低減を図る一つの方法として、昨今では翼０１
の背面でハブ側及びチップ側端部における表面を、例え
ば部分的に膨らませた形状に形成するカーブドスタッキ
ング翼が採用され、翼端側の負荷を低減し、翼中央の負
荷を増加することにより前記２次流れ損失の低減を達成
しようとしている。As one method of suppressing the generation of the secondary flow 02 and reducing the secondary flow loss, recently, the blade 01
Curved stacking wings that form the surface at the hub side and the tip side end at the back side, for example, in a partially expanded shape are adopted, reduce the load at the wing tip side, and increase the load at the center of the wing. Attempts are being made to reduce secondary flow losses.
【０００４】[0004]
【発明が解決しようとする課題】しかしながら、タービ
ンの高負荷化に伴って、段落当たりの膨脹比が増加し、
段落の入り口と出口の半径方向の距離の差が大きくな
り、図２（ｂ）に模式的に示す様に、フレア角０４が大
きくなると、図２（ｃ）のグラフに曲線Ａ１として示す
様に、２次流れ損失が翼０１の中央部まで影響を及ぼす
様になり、フレア角０４が大きい翼で発生する２次流れ
損失の主流０５への影響を抑えきれなくなって来る。However, as the load on the turbine increases, the expansion ratio per stage increases,
When the difference in the radial distance between the entrance and the exit of the paragraph increases, and the flare angle 04 increases, as schematically shown in FIG. 2B, the curve A1 in the graph of FIG. Second, the secondary flow loss affects the central portion of the wing 01, and the influence of the secondary flow loss generated on the wing having a large flare angle 04 on the main flow 05 cannot be completely suppressed.
【０００５】本発明は、このような従来のカーブドスタ
ッキング翼における不具合点を解消し、フレア角を大き
くし、段落当たりの膨脹比を大きくしたものにおいて、
２次流れ損失の低減を図る様にしたタービン静翼を提供
することを課題とするものである。SUMMARY OF THE INVENTION The present invention solves such a problem in the conventional curved stacking blade, increases the flare angle, and increases the expansion ratio per paragraph.
It is an object of the present invention to provide a turbine vane in which a secondary flow loss is reduced.
【０００６】[0006]
【課題を解決するための手段】本発明は前記した課題を
解決すべくなされたもので、翼の背面に、チップ側及び
ハブ側から翼高さ方向に向かって盛り上がった段差部を
形成したタービンの静翼を提供するものである。SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned problems, and has a turbine having a stepped portion formed on a back surface of a blade from a tip side and a hub side toward a blade height direction. To provide a stationary wing.
【０００７】すなわち本発明によれば、翼の背面に、チ
ップ側及びハブ側から翼高さ方向に向かって盛り上がっ
た段差部を形成したことにより、翼の背面端部に発生す
る２次流れは段差部で区画された端部内に止まり、翼中
央部に流れ込まないようにして翼中央部の主流ガスの流
れに影響を与えず、主流の効率低下を防止する様にした
ものである。In other words, according to the present invention, since a stepped portion is formed on the back surface of the blade in the height direction from the tip side and the hub side in the blade height direction, the secondary flow generated at the rear end portion of the blade is It stops at the end defined by the step, does not flow into the center of the blade, does not affect the flow of the mainstream gas in the center of the blade, and prevents a reduction in the efficiency of the main flow.
【０００８】また、本発明は、前記段差部は、チップ側
及びハブ側の端部から翼高さ方向に向かって翼高さの１
０〜１５％の位置に形成したタービンの静翼を提供する
ものである。Further, according to the present invention, the stepped portion has a blade height of 1 from the tip side and the hub side ends in the blade height direction.
The present invention provides a turbine vane formed at a position of 0 to 15%.
【０００９】すなわち本発明によれば、チップ側及びハ
ブ側の端部から翼高さ方向に向かって翼高さの１０〜１
５％の位置に段差部を形成することにより、通常２次流
れの発生する領域に当たるこの１０〜１５％の範囲に、
段差部で区画して２次流れを閉じ込め、同２次流れを翼
中央部の主流領域に流し込まず、主流に影響を与えて効
率低下の生じるのを防止する様にしたものである。That is, according to the present invention, the blade height is 10 to 1 from the tip side and the hub side ends toward the blade height direction.
By forming a step portion at a position of 5%, the range of 10 to 15%, which corresponds to a region where the secondary flow occurs, is usually set.
The secondary flow is confined by being divided by a step, and the secondary flow is not flown into the main flow region in the center of the blade, so that the main flow is prevented from being reduced and efficiency is reduced.
【００１０】また、本発明は、前記段差部は、主流の流
れ方向の起点を翼の背面で２次流れが発生し始める位置
に形成したタービンの静翼を提供するものである。The present invention also provides a turbine vane in which the step portion has a starting point in the flow direction of the main flow formed at a position on the back surface of the blade where secondary flow starts to occur.
【００１１】すなわち本発明によれば、翼の背面で２次
流れが発生し始める位置に主流の流れ方向における段差
部の起点を形成しているので、２次流れが発生し始める
位置に至るまでは翼の全面で主流の流れを案内し、２次
流れが生じる位置から翼端部と中央部を段差部で区画す
ることにより、翼背面を効果的に使用して主流の流れを
案内し、効率低下の発生防止を図る様にしたものであ
る。That is, according to the present invention, since the starting point of the step in the main flow direction is formed at the position where the secondary flow starts to be generated on the back surface of the blade, it is possible to reach the position where the secondary flow starts to be generated. Guides the flow of the main flow over the entire surface of the wing and guides the flow of the main flow by effectively using the back of the wing by dividing the wing tip and the center by a step from the position where the secondary flow occurs, This is to prevent the efficiency from being reduced.
【００１２】また、本発明は、前記段差部は、翼後縁側
から見て翼の中央側が背側に凸となる形状に形成したタ
ービンの静翼を提供するものである。Further, the present invention provides a turbine vane in which the step portion is formed such that the center side of the blade is convex to the rear side when viewed from the blade trailing edge side.
【００１３】すなわち本発明によれば、段差部により翼
の形状は翼の中央側が背側に凸となる様に形成されてい
るので、翼の背側でこの中央部を挟むチップ側、ハブ側
の両端部は一段と低くなることとなり、２次流れはこの
低部に閉じ込められ、主流に影響を与えず、主流の効率
低下を来すことのない様にしたものである。In other words, according to the present invention, the wing is formed so that the center side of the wing is convex to the back side by the stepped portion. Therefore, the tip side and the hub side sandwiching the center part on the back side of the wing. , Both ends are further lowered, and the secondary flow is confined in this lower part, so that the main flow is not affected and the efficiency of the main flow is not reduced.
【００１４】更にまた、本発明は、前記段差部は、主流
の流れ範囲の区画に合致させて主流の流れ方向に延ばし
て形成したタービンの静翼を提供するものである。Still further, the present invention provides a turbine vane in which the step portion is formed so as to extend in the direction of flow of the main flow so as to match the section of the flow range of the main flow.
【００１５】すなわち本発明によれば、主流の流れ範囲
の区画に合致させて主流の流れ方向に延ばして段差部を
形成しているので、段落当たりの膨脹比を大きくしてフ
レア角を大きくした場合においては、主流領域はフレア
角に準じて下流方向に広がることになるが、その広がり
を段差部で的確に区画して主流領域に２次流れの流れ込
みを防止し、主流の効率低下を招くことの無いようにし
たものである。That is, according to the present invention, since the stepped portion is formed by extending in the mainstream flow direction in accordance with the section of the mainstream flow range, the expansion ratio per paragraph is increased to increase the flare angle. In such a case, the main flow region spreads in the downstream direction according to the flare angle. However, the spread is accurately divided by the step portion to prevent the secondary flow from flowing into the main flow region, and the main flow efficiency is reduced. It is something that has never happened.
【００１６】[0016]
【発明の実施の形態】本発明の実施の一形態について図
１に基づいて説明する。図１は本実施の形態におけるタ
ービン翼の全貌を概略的に説明するものであり、（ａ）
は翼背面側から見た概要を示し、（ｂ）は翼後縁側から
見た概要を示し、また、（ｃ）は翼の高さ方向における
２次流れ損失を説明している。DESCRIPTION OF THE PREFERRED EMBODIMENTS One embodiment of the present invention will be described with reference to FIG. FIG. 1 schematically illustrates the entire appearance of a turbine blade according to the present embodiment, and FIG.
Fig. 4 shows the outline viewed from the blade rear side, (b) illustrates the outline viewed from the blade trailing edge side, and (c) illustrates the secondary flow loss in the blade height direction.
【００１７】すなわち、本実施の形態においては、ター
ビン翼１１はその高さ方向において、チップ側及びハブ
側の両端部から、タービン翼１１の高さの１０％から１
５％に相当する位置に、同両端部からタービン翼１１の
高さ方向に向かって盛り上がる段差部１３、１３を設け
ている。That is, in the present embodiment, the turbine blade 11 is located at 10% to 1% of the height of the turbine blade 11 from both ends on the tip side and the hub side in the height direction.
At the position corresponding to 5%, step portions 13, 13 rising from both ends toward the height direction of the turbine blade 11 are provided.
【００１８】この各段差部１３、１３はタービン翼１１
のリーディングエッヂから始まるのではなく、主流の流
れ方向で内方に入った位置で始まり、トレーリングエッ
ヂにまで亘って延びている。Each of the steps 13, 13 is provided with a turbine blade 11
Rather than starting at the leading edge, it starts at an inward position in the mainstream flow direction and extends to the trailing edge.
【００１９】そしてこの段差部１３が始まる位置、換言
すれば段差部１３の主流の流れ方向における起点は、タ
ービン翼１１の背側において、チップ側及びハブ側の両
端部に発生する２次流れ１２のパターンを実験または数
値解析により予測し、同２次流れ１２の発生する位置に
定めている。The position where the step 13 starts, in other words, the starting point of the step 13 in the main flow direction is the secondary flow 12 generated at both ends on the tip side and the hub side on the back side of the turbine blade 11. Is predicted by experiment or numerical analysis, and is determined at the position where the secondary flow 12 occurs.
【００２０】従ってこの段差部１３を形成したタービン
翼１１をその後縁側から見てみると、図１（ｂ）に示す
様に、タービン翼１１の中央側が同タービン翼１１の背
側に凸となる形状に形成されている。Accordingly, when the turbine blade 11 having the stepped portion 13 is viewed from the trailing edge side, as shown in FIG. 1B, the center side of the turbine blade 11 is convex on the back side of the turbine blade 11. It is formed in a shape.
【００２１】そしてこの段差部１３により凸形状に区画
された範囲は、一つのタービン翼１１に相当する範囲で
軸方向に区画される１段落での膨脹比を高めようとし
て、リーディングエッヂに対するトレーリングエッヂの
半径方向の長さを大きくし、その結果いわゆるフレア角
が大きくなると、それに準じて凸形状の区画もトレーリ
ングエッヂ側に進むに従って端部側に向かって広くな
り、主流の流れ範囲の区画に合致してトレーリングエッ
ヂ側まで延びるように形成されている。The area defined in the convex shape by the stepped portion 13 is a region corresponding to one turbine blade 11 in an attempt to increase the expansion ratio in one stage axially defined by the trailing edge to the leading edge. When the edge length in the radial direction is increased, and as a result, the so-called flare angle is increased, the section of the convex shape also becomes larger toward the end side as it goes to the trailing edge side, and the section of the flow range of the main flow is accordingly increased. And is formed to extend to the trailing edge side.
【００２２】前記の様に本実施の形態においては、段差
部１３の位置はタービン翼１１の背側で、チップ側及び
ハブ側から高さ方向にそれぞれ１０〜１５％の位置と
し、全体形状とてトレーリングエッヂ側から見て中央部
が凸となるようにしたので、主流の圧力が高い腹側では
なく、圧力の低い背側において、しかも、図示省略の翼
環やシュラウド等の存在により２次流れ１２が発生する
チップ側及びハブ側の端部区域を的確にとらえて２次流
れ１２を閉じ込め、同２次流れ１２を主流側に送らない
様にして、主流の流れを乱すことを防止しているので、
主流の効率低下を来すことのないものである。As described above, in the present embodiment, the position of the stepped portion 13 is on the back side of the turbine blade 11 and at a position of 10 to 15% in the height direction from the tip side and the hub side, respectively. The central part is convex when viewed from the trailing edge side, so it is not on the ventral side where the mainstream pressure is high, but on the back side where the pressure is low, and because of the presence of wing rings and shrouds (not shown). The secondary flow 12 is confined by accurately capturing the end area on the chip side and the hub side where the next flow 12 occurs, preventing the secondary flow 12 from being sent to the main flow side, and preventing the main flow from being disturbed. So
It does not reduce the mainstream efficiency.
【００２３】すなわち、図１（ｃ）において、タービン
翼１１の高さ方向を縦軸にとり、各高さ位置に於ける２
次流れ損失を横軸にとって示すと、曲線Ａ２で描かれる
様にチップ側及びハブ側の端部では２次流れ損失は大き
くなるが、段差部１３に相当する位置を境として中央部
側では前記２次流れ損失が小さくなっており、同２次流
れ損失が主流の流れに影響を与えないものとなっている
ことがわかる。That is, in FIG. 1 (c), the vertical direction is the vertical direction of the turbine blades 11, and 2 at each height position.
When the secondary flow loss is plotted on the horizontal axis, the secondary flow loss increases at the tip side and the hub side ends as depicted by the curve A2, but at the center side with respect to the position corresponding to the step portion 13 as described above. It can be seen that the secondary flow loss is small and the secondary flow loss does not affect the main flow.
【００２４】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 embodiments, the present invention is not limited to such embodiments.
It goes without saying that various changes may be made to the specific structure within the scope of the present invention.
【００２５】例えば、前記図１（ｂ）からも読み取れる
様に、タービン翼１１の背側が凸になることは、翼の重
量等の設計条件からして同凸部分と裏腹となる腹面側は
凹型に形成されるのが普通であるが、２次流れの影響防
止という観点からみるときは、翼の腹面側は通常の球面
に形成することもできる。For example, as can be seen from FIG. 1 (b), the fact that the back side of the turbine blade 11 is convex means that the ventral side, which is opposite to the convex part, is concave due to design conditions such as the weight of the blade. However, from the viewpoint of preventing the influence of the secondary flow, the abdominal surface of the wing may be formed as a normal spherical surface.
【００２６】[0026]
【発明の効果】以上、本発明によれば、翼の背面に、チ
ップ側及びハブ側から翼高さ方向に向かって盛り上がっ
た段差部を形成してタービンの静翼を構成しているの
で、この様に翼の背面に、チップ側及びハブ側から翼高
さ方向に向かって盛り上がった段差部を形成したことに
より、翼の背面端部に発生する２次流れは段差部で区画
された端部内に止まり、翼中央部に流れ込まないように
して翼中央部の主流ガスの流れに影響を与えず、主流の
効率低下を防止する好適なタービンの静翼を得ることが
出来たものである。As described above, according to the present invention, a stepped portion is formed on the back surface of the blade from the tip side and the hub side toward the blade height direction to form a turbine stationary blade. By forming a stepped portion rising from the tip side and the hub side in the blade height direction on the backside of the blade in this way, the secondary flow generated at the back end of the blade is separated by the stepped end. Thus, it is possible to obtain a suitable turbine vane of a turbine which stops in the central portion of the blade and does not flow into the central portion of the blade without affecting the flow of the mainstream gas in the central portion of the blade, thereby preventing a reduction in the efficiency of the main flow.
【００２７】また、請求項２に記載の発明によれば、前
記段差部は、チップ側及びハブ側の端部から翼高さ方向
に向かって翼高さの１０〜１５％の位置に形成してター
ビンの静翼を構成しているので、この様にチップ側及び
ハブ側の端部から翼高さ方向に向かって翼高さの１０〜
１５％の位置に段差部を形成したことにより、通常２次
流れの発生する領域に当たるこの１０〜１５％の範囲
に、段差部で区画して２次流れを閉じ込め、同２次流れ
を翼中央部の主流領域に流し込まず、２次流れが主流に
影響を与えて効率低下の生じることのない様にした好適
なタービンの静翼を得ることが出来たものである。According to the second aspect of the present invention, the step portion is formed at a position of 10 to 15% of the blade height in the blade height direction from the tip side and the hub side ends. Thus, the blades of the turbine are configured so that the blade height is 10 to 10 from the tip side and the hub side end in the blade height direction.
By forming the step portion at the position of 15%, the secondary flow is confined by dividing by the step portion in the range of 10 to 15%, which is usually the region where the secondary flow occurs, and the secondary flow is centered on the blade. Thus, it is possible to obtain a suitable turbine vane of the turbine in which the secondary flow does not flow into the main flow region of the section and the secondary flow does not affect the main flow and the efficiency does not decrease.
【００２８】また、請求項３に記載の発明によれば、前
記段差部は、主流の流れ方向の起点を翼の背面で２次流
れが発生し始める位置に形成してタービンの静翼を構成
しているので、この様に翼の背面で２次流れが発生し始
める位置に主流の流れ方向における段差部の起点を形成
したことにより、２次流れが発生し始める位置に至るま
では翼の全面で主流の流れを案内し、２次流れが生じる
位置から翼端部と中央部を段差部で区画することによ
り、翼背面を効果的に使用して主流の流れを案内し、２
次流れによる効率低下の発生を防止する様にした好適な
タービンの静翼を得ることが出来たものである。According to the third aspect of the present invention, the step portion forms the starting point of the main flow in the flow direction at a position where the secondary flow starts to be generated on the back surface of the blade to constitute a turbine stationary blade. In this way, the starting point of the step in the main flow direction is formed at the position where the secondary flow starts to be generated on the back surface of the blade in this manner, so that the position of the wing until the position where the secondary flow starts to be generated is reached. By guiding the mainstream flow over the entire surface and dividing the wing tip and center with a step from the position where the secondary flow occurs, the backside of the wing is used effectively to guide the mainstream flow,
It is possible to obtain a suitable turbine vane in which the efficiency is prevented from being reduced by the next flow.
【００２９】また、請求項４に記載の発明によれば、前
記段差部は、翼後縁側から見て翼の中央側が背側に凸と
なる形状に形成してタービンの静翼を構成しているの
で、この様に段差部により翼の形状は翼の中央側が背側
に凸となる様に形成したことにより、翼の背側でこの中
央部を挟むチップ側、ハブ側の両端部は一段と低くなる
こととなり、２次流れはこの低部に閉じ込められ、中央
部の主流に影響を与えず、主流が２次流れの影響で効率
低下を来すことのない様にした好適なタービンの静翼を
得ることが出来たものである。According to the fourth aspect of the present invention, the step portion is formed to have a shape in which the center side of the blade is convex to the rear side when viewed from the blade trailing edge side, thereby forming a turbine stationary blade. Therefore, the shape of the wing is formed such that the center side of the wing is convex to the back side due to the step, so both ends on the tip side and hub side sandwiching this center part on the back side of the wing are one step The secondary flow is confined in this lower part and does not affect the main flow in the central part, so that the static flow of the preferred turbine is such that the main flow does not decrease in efficiency due to the influence of the secondary flow. Wings were obtained.
【００３０】更にまた、請求項５に記載の発明によれ
ば、前記段差部は、主流の流れ範囲の区画に合致させて
主流の流れ方向に延ばして形成してタービンの静翼を構
成しているので、この様に主流の流れ範囲の区画に合致
させて主流の流れ方向に延ばして段差部を形成したこと
により、段落当たりの膨脹比を大きくしてフレア角が大
きくなった場合においては、主流領域はフレア角に準じ
て下流方向に広がることになるが、その広がりを段差部
で的確に区画して主流領域に２次流れの流れ込みを防止
し、２次流れの影響により主流の効率低下を招くことの
無いようにした好適なタービンの静翼を得ることが出来
たものである。Further, according to the fifth aspect of the present invention, the step portion is formed to extend in the main flow direction in conformity with the section of the main flow range to form a turbine vane of the turbine. In this case, when the flare angle is increased by increasing the expansion ratio per paragraph by forming a step by extending in the main flow direction in accordance with the section of the main flow area in this way, The main flow region spreads downstream in accordance with the flare angle, but the spread is accurately divided by the steps to prevent the flow of the secondary flow into the main flow region, and the efficiency of the main flow decreases due to the influence of the secondary flow. Thus, it is possible to obtain a suitable stator vane of the turbine so as not to cause the above problem.
【図１】本発明の実施の一形態に係るタービン翼の概要
を示し、（ａ）は翼背面側から見た概略図、（ｂ）は翼
後縁側から見た概略図、また、（ｃ）は翼の高さ方向に
おける２次流れ損失を示す説明図である。1A and 1B schematically show a turbine blade according to an embodiment of the present invention, wherein FIG. 1A is a schematic diagram viewed from the blade rear side, FIG. 1B is a schematic diagram viewed from the blade trailing edge side, and FIG. () Is an explanatory diagram showing the secondary flow loss in the blade height direction.
【図２】従来のタービン翼の概要を示し、（ａ）は翼背
面側から見た概略図、（ｂ）は翼の形状及び主流の状況
を示す模式図、また、（ｃ）は翼の高さ方向における２
次流れ損失を示す説明図である。2A and 2B schematically show a conventional turbine blade, FIG. 2A is a schematic diagram viewed from the back side of the blade, FIG. 2B is a schematic diagram showing the shape of the blade and the state of main flow, and FIG. 2 in the height direction
It is explanatory drawing which shows a next flow loss.
０１ タービン翼 ０２ ２次流れ ０４ フレア角 ０５ 主流 １１ タービン翼 １２ ２次流れ １３ 段差部 01 Turbine blade 02 Secondary flow 04 Flare angle 05 Main flow 11 Turbine blade 12 Secondary flow 13 Step
Claims (5)
高さ方向に向かって盛り上がった段差部を形成したこと
を特徴とするタービンの静翼。1. A turbine vane according to claim 1, wherein a stepped portion is formed on a back surface of the blade from a tip side and a hub side toward a blade height direction.
部から翼高さ方向に向かって翼高さの１０〜１５％の位
置に形成したことを特徴とする請求項１に記載のタービ
ンの静翼。2. The step according to claim 1, wherein the step portion is formed at a position of 10 to 15% of the blade height in the blade height direction from the tip side and the hub side ends. Turbine vane.
翼の背面で２次流れが発生し始める位置に形成したこと
を特徴とする請求項１または２に記載のタービンの静
翼。3. The turbine vane according to claim 1, wherein the step portion has a starting point in the flow direction of the main flow formed at a position on the back surface of the blade where a secondary flow starts to occur.
央側が背側に凸となる形状に形成したことを特徴とする
請求項１、２または３に記載のタービンの静翼。4. The turbine vane according to claim 1, wherein the stepped portion is formed to have a shape in which a center side of the blade is convex to a back side when viewed from a blade trailing edge side.
合致させて主流の流れ方向に延ばして形成したことを特
徴とする請求項１、２、３または４に記載のタービンの
静翼。5. The turbine vane according to claim 1, wherein the stepped portion is formed so as to match a section of a flow range of the main flow and to extend in a flow direction of the main flow. .
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP11029956A JP2000230403A (en) | 1999-02-08 | 1999-02-08 | Turbine stator blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP11029956A JP2000230403A (en) | 1999-02-08 | 1999-02-08 | Turbine stator blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JP2000230403A true JP2000230403A (en) | 2000-08-22 |
Family
ID=12290444
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP11029956A Withdrawn JP2000230403A (en) | 1999-02-08 | 1999-02-08 | Turbine stator blade |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2000230403A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008084563A1 (en) * | 2007-01-12 | 2008-07-17 | Mitsubishi Heavy Industries, Ltd. | Blade structure for gas turbine |
| US7625181B2 (en) | 2003-10-31 | 2009-12-01 | Kabushiki Kaisha Toshiba | Turbine cascade structure |
-
1999
- 1999-02-08 JP JP11029956A patent/JP2000230403A/en not_active Withdrawn
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7625181B2 (en) | 2003-10-31 | 2009-12-01 | Kabushiki Kaisha Toshiba | Turbine cascade structure |
| WO2008084563A1 (en) * | 2007-01-12 | 2008-07-17 | Mitsubishi Heavy Industries, Ltd. | Blade structure for gas turbine |
| US8317466B2 (en) | 2007-01-12 | 2012-11-27 | Mitsubishi Heavy Industries, Ltd. | Blade structure of gas turbine |
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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: 20060509 |