JP2002054401A - End wall structure between turbine blades - Google Patents
End wall structure between turbine bladesInfo
- Publication number
- JP2002054401A JP2002054401A JP2000242373A JP2000242373A JP2002054401A JP 2002054401 A JP2002054401 A JP 2002054401A JP 2000242373 A JP2000242373 A JP 2000242373A JP 2000242373 A JP2000242373 A JP 2000242373A JP 2002054401 A JP2002054401 A JP 2002054401A
- Authority
- JP
- Japan
- Prior art keywords
- end wall
- blade
- height
- flow
- turbine
- 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.)
- Granted
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明はタービン翼間の端壁
構造に関し、翼端壁の境界層流の流体の流れを加速し流
れを一様化するような形状として効率を向上させる構造
としたものである。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an end wall structure between turbine blades, and more particularly, to a structure for accelerating the flow of fluid in a boundary layer flow of a blade end wall to make the flow uniform, thereby improving efficiency. Things.
【０００２】[0002]
【従来の技術】図５は従来の蒸気タービンやガスタービ
ン、等の翼形状で、静翼を示し、（ａ）は翼の断面形
状、（ｂ）は（ａ）におけるＡ−Ａ断面図である。両図
において、５０はタービン静翼であり、５１は隣接する
翼間のスロート、５２は翼の端壁、５３は翼の負圧面、
５４は翼の圧力面を、それぞれ示している。タービン翼
５０の翼間内で流体は翼の形状に沿って流れる角度を変
えながらスロート５１まで加速される。この時、翼間に
は主流の流線６０の曲率に応じて生ずる遠心力に釣り合
うような圧力勾配が発生する。しかしながら端壁５２上
に発達する境界層内部の速度の遅い流体は、圧力面５４
から負圧面５３へ向かう圧力勾配にバランスするだけの
遠心力がないため主流６０よりも流れの転向が大きくな
り、いわゆる２次流れ６１が発生する。この２次流れ６
１のため、翼列出口での翼高さ方向流れ角分布や軸流速
度分布が非一様となり、静翼だけでなく下流の動翼の効
率も低下する原因となっていた。2. Description of the Related Art FIGS. 5A and 5B show blades of a conventional steam turbine, gas turbine, or the like and show stationary blades. FIG. 5A is a sectional view of the blade, and FIG. is there. In both figures, 50 is a turbine stationary blade, 51 is a throat between adjacent blades, 52 is an end wall of the blade, 53 is a suction surface of the blade,
Numeral 54 indicates a pressure surface of the blade. The fluid is accelerated to the throat 51 while changing the angle of the fluid flowing between the blades 50 along the shape of the blade. At this time, a pressure gradient is generated between the blades so as to balance the centrifugal force generated according to the curvature of the mainstream streamline 60. However, the slow velocity fluid inside the boundary layer developing on the end wall 52 is
Since there is no centrifugal force sufficient to balance the pressure gradient from the pressure to the negative pressure surface 53, the direction of the flow is larger than that of the main flow 60, and a so-called secondary flow 61 is generated. This secondary flow 6
As a result, the flow angle distribution and the axial flow velocity distribution in the blade height direction at the cascade outlet become non-uniform, which causes the efficiency of not only the stationary blades but also the downstream blades to decrease.
【０００３】[0003]
【発明が解決しようとする課題】前述のように、従来の
タービン翼においては、翼間の端壁５２には主流６０と
流れの転向が異なる２次流れ６１が発生し、これが翼列
出口での翼高さ方向の流れ角分布を乱し、速度分布を非
一様にして効率を低下させてしまい、又、静翼出口での
流れの乱れは、下流動翼の性能にも影響を与えており、
流体のタービン翼間での流れの改善による効率の向上策
が強く望まれていた。As described above, in the conventional turbine blade, a secondary flow 61 having a different flow direction from the main flow 60 is generated at the end wall 52 between the blades, and this is generated at the blade row outlet. Disturbing the flow angle distribution in the height direction of the blade, making the velocity distribution non-uniform and lowering the efficiency, and the turbulence of the flow at the exit of the stationary blade also affects the performance of the lower flow blade. And
There has been a strong demand for measures to improve efficiency by improving the flow of fluid between turbine blades.
【０００４】そこで本発明では、タービン翼端壁の形状
に工夫を行い、２次流れの発生を抑えて流れの効率を向
上させるような翼端壁面の形状を採用したタービン翼間
の端壁構造を提供することを課題としてなされたもので
ある。Therefore, in the present invention, the shape of the turbine blade end wall is devised, and the end wall structure between turbine blades adopting a blade end wall shape that suppresses the generation of secondary flow and improves the flow efficiency. The task was to provide
【０００５】[0005]
【課題を解決するための手段】本発明は前述の課題を解
決するために、次の（１）〜（４）の手段を提供する。The present invention provides the following means (1) to (4) in order to solve the above-mentioned problems.
【０００６】（１）タービン静翼の翼間ハブ側端壁面は
前縁、後縁両翼端間に頂部を有する突起形状を備え、同
突起形状の頂部は曲面形状であり、かつ、その曲面の頂
点の軌跡はタービン軸と直交する方向に直線を形成し、
更に同直線の位置は隣接する静翼間で形成されるスロー
トの位置に設定されていることを特徴とするタービン翼
間の端壁構造。(1) The hub-side end wall surface between the blades of the turbine stationary blade has a projection having a top portion between the leading edge and the trailing edge, and the top of the projection shape is a curved surface. The trajectory of the vertex forms a straight line in the direction orthogonal to the turbine axis,
The end wall structure between turbine blades, wherein the position of the straight line is set at a position of a throat formed between adjacent stator blades.
【０００７】（２）先端にシュラウドを有し基部がハブ
側のプラットフォームに固定されている動翼の翼間シュ
ラウド内側端壁面は前縁、後縁両翼端間に頂部を有する
突起形状を備え、同突起形状の頂部は曲面形状であり、
かつその曲面の頂点の軌跡はタービン軸と直交する方向
に直線を形成し、更に同直線の位置は隣接する動翼間で
形成されるスロートの位置に設定されていることを特徴
とするタービン翼間の端壁構造。(2) The inner wall surface of the inner blade between the blades of the blade, which has a shroud at the tip and whose base is fixed to the platform on the hub side, has a protruding shape having a top portion between the leading edge and the trailing edge. The top of the projection is a curved surface,
The trajectory of the apex of the curved surface forms a straight line in a direction orthogonal to the turbine axis, and the position of the straight line is set at the position of a throat formed between adjacent moving blades. End wall structure between.
【０００８】（３）前記シュラウドの突起形状に加え
て、更に、前記プラットフォーム外側端壁面にも前記突
起形状が形成されていることを特徴とする（２）記載の
タービン翼間の端壁構造。(3) The end wall structure between turbine blades according to (2), wherein the protruding shape is further formed on the outer end wall surface of the platform in addition to the protruding shape of the shroud.
【０００９】（４）前記突起形状の高さは翼高さの２．
６％以下とすることを特徴とする（１）から（３）のい
ずれかに記載のタービン翼間の端壁構造。(4) The height of the projection is equal to the height of the blade.
The end wall structure between turbine blades according to any one of (1) to (3), wherein the end wall structure is set to 6% or less.
【００１０】本発明の（１）においては、静翼翼間のハ
ブ側端面の突起形状により流体の流れはこの突起形状に
沿って速度を加速して流れ、これによりハブ側端壁境界
層流体の速度も大きくなり、２次流れを抑制することが
できる。又、本発明の（４）のように、突起形状の高さ
を翼の高さの２．６％以下とし、更に流れ方向の突起形
状の頂点の位置をスロートに一致させて最適化を計って
いる。これにより静翼翼間のハブ側端壁面での２次流れ
の発生が抑えられ、静翼出口で、流れが一様化すること
により効率が向上するものである。In (1) of the present invention, the flow of the fluid flows at an accelerated speed along the shape of the protrusion on the hub-side end face between the stationary blades, whereby the fluid of the hub-side end wall boundary layer fluid flows. The speed is also increased, and the secondary flow can be suppressed. Further, as in (4) of the present invention, the height of the projection is set to 2.6% or less of the height of the blade, and the position of the apex of the projection in the flow direction is matched with the throat for optimization. ing. This suppresses the generation of the secondary flow on the hub-side end wall surface between the stationary blades, and improves the efficiency by making the flow uniform at the stationary blade outlet.
【００１１】本発明の（２）では、突起形状を動翼先端
のシュラウド内側壁面に設けたので、この突起形状によ
り動翼シュラウド壁面の流れが加速され、シュラウド側
端壁境界層流体の速度が大きくなり、シュラウド側壁面
近傍に発生する２次流れを抑制することができる。又、
本発明の（４）のように突起形状の高さを翼の高さの
２．６％以下とし、更に流れ方向の突起形状の頂点の位
置をスロートに一致させ、最適化を計っている。これに
より動翼先端シュラウドの端壁面には２次流れが抑制さ
れ、動翼出口での流れが一様化することにより効率が向
上するものである。In (2) of the present invention, since the protrusion is provided on the shroud inner wall surface at the tip of the blade, the flow of the blade shroud wall surface is accelerated by the protrusion, and the velocity of the boundary layer fluid at the shroud-side end wall is increased. As a result, the secondary flow generated near the shroud side wall surface can be suppressed. or,
As in (4) of the present invention, the height of the protruding shape is set to 2.6% or less of the height of the blade, and the position of the apex of the protruding shape in the flow direction is matched with the throat to optimize. As a result, the secondary flow is suppressed on the end wall surface of the blade tip shroud, and the flow at the blade outlet is made uniform, thereby improving the efficiency.
【００１２】本発明の（３）では、動翼先端のシュラウ
ド内側端壁面に加えて、動翼のプラットフォーム内側端
壁面にも突起形状が形成されており、シュラウド及びプ
ラットフォーム両端壁面の流れは、この突起形状で加速
され、シュラウド及びプラットフォーム両端壁面近傍に
発生する２次流れを抑制することができる。又、本発明
の（４）のように突起形状の高さを翼の高さの２．６％
以下とし、更に流れ方向の突起形状の頂点の位置をスロ
ートに一致させ、最適化を計っている。これにより動翼
先端のシュラウド及びプラットフォームの両端壁面には
２次流れが抑制され、動翼出口での流れが一様化するこ
とにより効率が向上するものである。In (3) of the present invention, in addition to the shroud inner end wall surface at the tip of the rotor blade, a protruding shape is also formed on the platform inner end wall surface of the rotor blade. The secondary flow that is accelerated by the projection shape and occurs near the shroud and the both end wall surfaces of the platform can be suppressed. Also, as in (4) of the present invention, the height of the projection is set to 2.6% of the height of the wing.
In the following, the position of the apex of the protruding shape in the flow direction is matched with the throat for optimization. As a result, the secondary flow is suppressed on the shroud at the tip of the moving blade and on both end wall surfaces of the platform, and the flow at the outlet of the moving blade is made uniform, thereby improving the efficiency.
【００１３】[0013]
【発明の実施の形態】以下、本発明の実施の形態につい
て図面に基づいて具体的に説明する。図１は本発明の実
施の第１形態に係るタービン翼間端壁構造を示し、
（ａ）は全体の側面図、（ｂ）は翼端壁の斜視図であ
り、図１ではタービンの静翼を示し、蒸気タービン、ガ
スタービン、圧縮機、等の回転体を有するタービンに適
用される。両図において、１０は静翼であり、静翼１０
はハブ側端壁１１とケーシング１２との間に固定されて
いる。Embodiments of the present invention will be specifically described below with reference to the drawings. FIG. 1 shows an end wall structure between turbine blades according to a first embodiment of the present invention,
(A) is a side view of the whole, (b) is a perspective view of a blade tip wall, FIG. 1 shows a stationary blade of the turbine, and is applied to a turbine having a rotating body such as a steam turbine, a gas turbine, a compressor, and the like. Is done. In both figures, reference numeral 10 denotes a stationary blade,
Is fixed between the hub side end wall 11 and the casing 12.
【００１４】本実施の第１形態の静翼は、翼高さがＳ、
翼の軸方向コード長がＣであり、ハブ側端壁１１のガス
流れ方向Ｇには、後述するように両端からＸ1 ，Ｘ 2の
寸法となる位置に頂部１４を有すると頂部の高さがＨの
突起壁１３が形成されている。頂部１４は翼端からそれ
ぞれＸ1 ，Ｘ 2の位置で、図１（ｂ）にも示すように軸
と直交方向に頂点の軌跡が直線状に形成され、ハブの底
面から高さＨを保って形成されている。The vane of the first embodiment has a blade height S,
When the axial cord length of the blade is C and the top 14 is located at a position of X 1 and X 2 from both ends in the gas flow direction G of the hub side end wall 11 as described later, the height of the top is Is formed on the projection wall 13. The top 14 is located at X 1 and X 2 from the wing tip, respectively, and the trajectory of the apex is formed linearly in the direction orthogonal to the axis as shown in FIG. 1B, and the height H is maintained from the bottom of the hub. It is formed.
【００１５】図２は上記に説明した突起壁の形状を示す
図で、（ａ）はハブ側端壁の平面図、（ｂ）はその断面
図である。（ａ）に示すように頂部１４はタービンの軸
方向Ｒと直交する方向Ｐに形成され、翼の両端からそれ
ぞれＸ1 ，Ｘ 2の位置に形成され、その頂部１４はなめ
らかな曲面に形成されている。又、Ｘ1 ，Ｘ 2の位置は
頂点１４の軌跡がスロート５１の位置と一致する直線と
なるように決定し、高さＨは翼高さＳの約２．６％以下
としている。FIGS. 2A and 2B are views showing the shape of the above-described projection wall. FIG. 2A is a plan view of the hub-side end wall, and FIG. 2B is a cross-sectional view thereof. As shown in (a), the top portion 14 is formed in a direction P orthogonal to the axial direction R of the turbine, formed at positions X 1 and X 2 from both ends of the blade, and the top portion 14 is formed into a smooth curved surface. ing. The positions of X 1 and X 2 are determined so that the locus of the vertex 14 is a straight line that coincides with the position of the throat 51, and the height H is set to about 2.6% or less of the blade height S.
【００１６】上記構成の実施の第１形態のタービン翼間
の端壁構造においては、高さＨの突起壁１３を翼間のハ
ブ側端壁１１表面に設け、壁面に沿う流体を局所的に突
起壁１３のなめらかな面に沿わせることにより加速さ
せ、ハブ側端壁１１の境界層流体Ｖの速度が大きくな
り、従来の２次流れを抑制することができる。In the end wall structure between the turbine blades according to the first embodiment of the present invention, a projecting wall 13 having a height H is provided on the surface of the hub-side end wall 11 between the blades, and fluid along the wall surface is locally distributed. Acceleration is achieved by following the smooth surface of the projection wall 13, the velocity of the boundary layer fluid V on the hub side end wall 11 increases, and the conventional secondary flow can be suppressed.
【００１７】突起壁１３の高さＨについては、流れが剥
離しない程度の高さとし、突起の流れ方向位置について
もスロート位置との兼ね合いを考慮して、スロート５１
の位置に頂部１４がくるようにＸ1 ，Ｘ 2を決定し、最
適化を計っている。本実施の第１形態では、突起壁１３
の高さＨは、前述のように翼高さの約２．６％を限度と
して設定している。The height H of the projection wall 13 is set to such a level that the flow does not separate, and the position of the projection in the flow direction is also considered in consideration of the throat position.
X 1 and X 2 are determined so that the top 14 comes to the position of, and optimization is performed. In the first embodiment, the projection wall 13
The height H is set to about 2.6% of the blade height as a limit as described above.
【００１８】図３は本発明の実施の第２形態に係るター
ビン翼間の端壁構造の側面図であり、動翼に適用した例
である。図において２０は動翼であり、先端にはチップ
シュラウド２２が取付けられ基部はハブ側のプラットフ
ォーム２１へ固定されている。このシュラウド型動翼２
０は翼高さがＳ、翼の軸方向コード長がＣであり、チッ
プシュラウド２２のガス流れ方向Ｇに寸法Ｙ1 ，Ｙ2 と
なる位置に高さＨの頂部２４を有する突起壁２３が形成
されている。この突起壁２３の寸法Ｙ1 ，Ｙ2、頂部２
３の位置は図２で説明した位置関係と同じであり、その
頂部２４はなめらかな曲面で形成された頂部であり、軸
方向と直交する直線上に形成され、その位置はスロート
５１の位置に一致させている。又、高さＨは翼高さＳの
２．６％を上限として設定している。FIG. 3 is a side view of an end wall structure between turbine blades according to a second embodiment of the present invention, which is an example applied to a moving blade. In the drawing, reference numeral 20 denotes a moving blade, a tip shroud 22 is attached to a tip, and a base is fixed to a platform 21 on the hub side. This shroud-type bucket 2
0 is a blade wall 23 having a top 24 having a height H at a position where the blade height is S, the blade axial code length is C, and the dimensions are Y 1 and Y 2 in the gas flow direction G of the tip shroud 22. Is formed. The dimensions Y 1 and Y 2 of the projection wall 23 and the top 2
The position of 3 is the same as the positional relationship described with reference to FIG. 2, and the top 24 is a top formed by a smooth curved surface and is formed on a straight line perpendicular to the axial direction. Are matched. The height H is set at 2.6% of the blade height S as an upper limit.
【００１９】上記の実施の第２形態においては、動翼２
０において、高さＨの突起壁２３をチップシュラウド２
２に形成し、壁面に沿う流体を局所的に突起壁２３のな
めらかな面に沿わせることにより加速させ、チップシュ
ラウド２２側の端壁境界層流体の速度が大きくなり、チ
ップシュラウド２２側端壁近傍に発生する２次流れを抑
制することができる。In the second embodiment, the moving blade 2
0, the projection wall 23 having the height H is attached to the tip shroud 2.
2, the fluid along the wall surface is locally accelerated by following the smooth surface of the protruding wall 23, and the velocity of the boundary layer fluid on the tip shroud 22 side is increased, whereby the tip shroud 22 side end wall is increased. The secondary flow generated in the vicinity can be suppressed.
【００２０】高さＨについては、流れが剥離しない程度
の高さとし、突起の流れ方向位置についても、スロート
位置との兼ね合いを考慮して両者を最適化する必要があ
る。そこで、本実施の第２形態では、突起の高さを前述
のように翼高さＳの２．６％を限度として、またその流
れ方向の位置については、前述のように突起壁２３の頂
部２４の軌跡がスロート部へ一致する直線形状に設定し
ている。The height H must be such that the flow does not separate, and the position of the projection in the flow direction must be optimized in consideration of the balance with the throat position. Therefore, in the second embodiment, the height of the protrusion is limited to 2.6% of the blade height S as described above, and the position in the flow direction is set at the top of the protrusion wall 23 as described above. 24 trajectories are set in a straight line shape that matches the throat portion.
【００２１】図４は本発明の実施の第３形態に係るター
ビン翼間の端壁構造の側面図であり、チップシュラウド
を有する動翼のシュラウドとプラットフォームの両方に
適用した例である。図において、３０は動翼であり、先
端にはチップシュラウド３２が取付けられ基部はハブ側
のプラットフォーム３１へ固定されている。このシュラ
ウド型動翼３０は翼高さがＳ、翼の軸方向コード長がＣ
であり、チップシュラウド３２の端壁面のガス流れ方向
Ｇに図３の例と同じく寸法Ｙ1 ，Ｙ 2 となる位置に、
更にプラットフォーム３１側の端壁面の流れ方向に
Ｚ1 ，Ｚ 2となる位置に、それぞれ高さＨの突起壁３
３，３５を設けたものである。FIG. 4 is a side view of an end wall structure between turbine blades according to a third embodiment of the present invention, which is an example applied to both a shroud and a platform of a moving blade having a tip shroud. In the drawing, reference numeral 30 denotes a moving blade, a tip shroud 32 is attached to a tip, and a base is fixed to a platform 31 on the hub side. This shroud-type blade 30 has a blade height S and a blade axial code length C.
In the gas flow direction G on the end wall surface of the tip shroud 32, at the position where the dimensions Y 1 and Y 2 are the same as in the example of FIG.
Further, the projection wall 3 having a height H is located at a position Z 1 and Z 2 in the flow direction on the end wall surface on the platform 31 side.
3, 35 are provided.
【００２２】上記の突起壁３３，３５の寸法Ｙ1 ，Ｙ 2
及びＺ1 ，Ｚ 2、頂部３４，３６の位置は図２で説明し
た位置関係と同じであり、その頂部３６，３４はなめら
かな曲面で形成された頂部であり、その軌跡は軸方向に
直交する直線上に形成され、その位置はスロート５１の
位置に一致させている。The dimensions Y 1 and Y 2 of the projection walls 33 and 35 are described.
The positions of Z 1 , Z 2 , and the tops 34, 36 are the same as the positional relationship described with reference to FIG. 2, and the tops 36, 34 are tops formed by a smooth curved surface, and the trajectory thereof is orthogonal to the axial direction. The throat 51 is formed on a straight line.
【００２３】上記構成の実施の第３形態においては、高
さＨの突起壁をチップシュラウド３２及びプラットフォ
ーム３１側の端壁に設け、壁面に沿う流体を局所的に突
起壁のなめらかな面に沿わせることにより加速させ、両
端壁境界層流体の速度が大きくなり、シュラウド３２及
びプラットフォーム３１側端壁付近に発生する２次流れ
を抑制することができる。In the third embodiment of the above construction, a projection wall having a height H is provided on the end wall on the side of the chip shroud 32 and the platform 31, and the fluid along the wall surface is locally distributed along the smooth surface of the projection wall. As a result, the velocity of the boundary layer fluid at both end walls is increased, and the secondary flow generated near the shroud 32 and the end wall on the platform 31 side can be suppressed.
【００２４】突起の高さＨについては、流れが剥離しな
い程度の高さとし、突起の流れ方向位置についても、ス
ロート位置との兼ね合いを考慮して両者を最適化する必
要がある。本実施の第３形態では、突起の高さＨを翼高
さＳの約２．６％を限度として突出させ、またその流れ
方向位置については、前述のように突起の頂部３４，３
６がスロート部に一致する形状としている。The height H of the projections must be such that the flow does not separate, and the position in the flow direction of the projections must be optimized in consideration of the balance with the throat position. In the third embodiment, the height H of the protrusion is projected up to about 2.6% of the blade height S, and the position of the protrusion in the flow direction is determined as described above.
6 has a shape corresponding to the throat portion.
【００２５】[0025]
【発明の効果】本発明のタービン翼間の端壁構造は、
（１）タービン静翼の翼間ハブ側端壁面は前縁、後縁両
翼端間に頂部を有する突起形状を備え、同突起形状の頂
部は曲面形状であり、かつ、その曲面の頂点の軌跡はタ
ービン軸と直交する方向に直線を形成し、更に同直線の
位置は隣接する静翼間で形成されるスロートの位置に設
定されていることを特徴としている。According to the present invention, the end wall structure between turbine blades is as follows.
(1) The inter-blade hub-side end wall surface of the turbine vane has a projection having a top between the leading edge and the trailing edge of the blade, and the top of the projection has a curved surface and the locus of the top of the curved surface. Is characterized in that a straight line is formed in a direction orthogonal to the turbine axis, and the position of the straight line is set to the position of a throat formed between adjacent stator vanes.
【００２６】上記の構成により、静翼翼間のハブ側端面
の突起形状により流体の流れはこの突起形状に沿って速
度を加速して流れ、これによりハブ側端壁境界層流体の
速度も大きくなり、２次流れを抑制することができる。
又、本発明の（４）では、突起形状の高さを翼の高さの
２．６％以下とし、更に流れ方向の突起形状の頂点の位
置をスロートに一致させて最適化を計っている。これに
より静翼翼間のハブ側端壁面には２次流れが発生するこ
とが抑えられ、静翼出口での流れが一様化することによ
り効率が向上するものである。With the above configuration, the flow of the fluid is accelerated along the shape of the protrusion on the hub-side end face between the stationary blades, and the flow of the fluid is accelerated along the shape of the protrusion, thereby increasing the velocity of the fluid on the hub-side end wall boundary layer. The secondary flow can be suppressed.
In (4) of the present invention, the height of the protrusion is set to 2.6% or less of the height of the blade, and the position of the apex of the protrusion in the flow direction is matched with the throat for optimization. . As a result, generation of secondary flow on the hub-side end wall surface between the stator blades is suppressed, and the flow at the outlet of the stator blades is made uniform, thereby improving efficiency.
【００２７】本発明の（２）では、（１）の発明と同じ
構成の突起形状を動翼先端のシュラウド内側壁面に設け
たので、この突起形状により動翼シュラウド壁面の流れ
は流れを加速され、シュラウド側端壁境界層流体の速度
が大きくなり、シュラウド側壁面近傍に発生する２次流
れを抑制することができる。又、本発明の（４）のよう
に、突起形状の高さを翼の高さの２．６％以下とし、更
に流れ方向の突起形状の頂点の位置をスロートに一致さ
せ、最適化を計っている。これにより動翼先端シュラウ
ドの端壁面での２次流れが抑制され、動翼出口での流れ
が一様化することにより効率が向上するものである。In (2) of the present invention, since the protrusion having the same configuration as that of the invention of (1) is provided on the inner wall surface of the shroud at the tip of the blade, the flow on the wall of the blade shroud is accelerated by the protrusion shape. Therefore, the velocity of the shroud-side end wall boundary layer fluid increases, and the secondary flow generated near the shroud side wall surface can be suppressed. Further, as in (4) of the present invention, the height of the projection is set to 2.6% or less of the height of the blade, and the position of the apex of the projection in the flow direction is made to coincide with the throat to optimize. ing. As a result, the secondary flow on the end wall surface of the bucket tip shroud is suppressed, and the flow at the bucket outlet is made uniform to improve the efficiency.
【００２８】本発明の（３）では、動翼先端のシュラウ
ド内側端壁面に加えて、動翼のプラットフォーム内側端
壁面にも突起形状が形成されており、シュラウド及びプ
ラットフォーム両端壁面の流れは、この突起形状で加速
され、シュラウド及びプラットフォーム両端壁面近傍に
発生する２次流れを抑制することができる。又、本発明
の（４）のように突起形状の高さを翼の高さの２．６％
以下とし、更に流れ方向の突起形状の頂点の位置をスロ
ートに一致させ、最適化を計っている。これにより動翼
先端のシュラウド及びプラットフォームの両端壁面では
２次流れが抑制され、動翼出口での流れが一様化するこ
とにより効率が向上するものである。In (3) of the present invention, in addition to the shroud inner end wall surface at the tip of the rotor blade, a protruding shape is also formed on the platform inner end wall surface of the rotor blade. The secondary flow that is accelerated by the projection shape and occurs near the shroud and the both end wall surfaces of the platform can be suppressed. Also, as in (4) of the present invention, the height of the projection is set to 2.6% of the height of the wing.
In the following, the position of the apex of the protruding shape in the flow direction is matched with the throat for optimization. As a result, the secondary flow is suppressed at the shroud at the tip of the moving blade and at both end wall surfaces of the platform, and the flow at the outlet of the moving blade is made uniform, thereby improving the efficiency.
【図１】本発明の実施の第１形態に係るタービン翼間の
端壁構造を示し、（ａ）は側面図、（ｂ）は端壁部の斜
視図である。FIG. 1 shows an end wall structure between turbine blades according to a first embodiment of the present invention, wherein (a) is a side view and (b) is a perspective view of an end wall portion.
【図２】本発明の実施の第１〜第３形態に係るタービン
翼間の端壁構造の位置関係を示し、（ａ）は平面図、
（ｂ）は端壁の断面図である。FIG. 2 shows a positional relationship of an end wall structure between turbine blades according to the first to third embodiments of the present invention, wherein (a) is a plan view,
(B) is sectional drawing of an end wall.
【図３】本発明の実施の第２形態に係るタービン翼間の
端壁構造の側面図である。FIG. 3 is a side view of an end wall structure between turbine blades according to a second embodiment of the present invention.
【図４】本発明の実施の第３形態に係るタービン翼間の
端壁構造の側面図である。FIG. 4 is a side view of an end wall structure between turbine blades according to a third embodiment of the present invention.
【図５】従来のタービン翼間の端壁構造を示し、（ａ）
は翼の断面図、（ｂ）は（ａ）におけるＡ−Ａ断面図で
ある。5A and 5B show a conventional end wall structure between turbine blades, and FIG.
Is a sectional view of the wing, and (b) is an AA sectional view in (a).
１０ 静翼 １１ ハブ側端壁 １２ ケーシング １３，２３，３３，３５ 突起壁 １４，２４，３４，３６ 頂部 ２０，３０ 動翼 ２１，３１ プラットフォーム ２２，３２ チップシュラウド ５１ スロート DESCRIPTION OF SYMBOLS 10 Stator blade 11 Hub side end wall 12 Casing 13,23,33,35 Projection wall 14,24,34,36 Top 20,30 Moving blade 21,31 Platform 22,32 Chip shroud 51 Throat
───────────────────────────────────────────────────── フロントページの続き (72)発明者 松本 慎吾 兵庫県高砂市荒井町新浜２丁目１番１号 三菱重工業株式会社高砂研究所内 (72)発明者 田中 慶三 兵庫県高砂市荒井町新浜２丁目１番１号 三菱重工業株式会社高砂製作所内 (72)発明者 田中 良典 東京都千代田区丸の内二丁目５番１号 三 菱重工業株式会社内 Ｆターム(参考） 3G002 BA04 BB01 GA07 GA17 GB05 ──────────────────────────────────────────────────続 き Continued on the front page (72) Inventor Shingo Matsumoto 2-1-1 Shinhama, Arai-machi, Takasago City, Hyogo Prefecture Inside the Takasago Research Laboratory, Mitsubishi Heavy Industries, Ltd. No. 1 Inside Takasago Works, Mitsubishi Heavy Industries, Ltd. (72) Inventor Yoshinori Tanaka 2-5-1 Marunouchi, Chiyoda-ku, Tokyo F-term in Mitsubishi Heavy Industries, Ltd. 3G002 BA04 BB01 GA07 GA17 GB05
Claims (4)
縁、後縁両翼端間に頂部を有する突起形状を備え、同突
起形状の頂部は曲面形状であり、かつ、その曲面の頂点
の軌跡はタービン軸と直交する方向に直線を形成し、更
に同直線の位置は隣接する静翼間で形成されるスロート
の位置に設定されていることを特徴とするタービン翼間
の端壁構造。1. An inter-blade hub-side end wall surface of a turbine stationary blade has a projection having a top portion between a leading edge and a trailing edge, and the top of the projection shape has a curved surface shape, and a vertex of the curved surface. Wherein the trajectory forms a straight line in a direction orthogonal to the turbine axis, and the position of the straight line is set at the position of a throat formed between adjacent stator vanes. .
プラットフォームに固定されている動翼の翼間シュラウ
ド内側端壁面は前縁、後縁両翼端間に頂部を有する突起
形状を備え、同突起形状の頂部は曲面形状であり、かつ
その曲面の頂点の軌跡はタービン軸と直交する方向に直
線を形成し、更に同直線の位置は隣接する動翼間で形成
されるスロートの位置に設定されていることを特徴とす
るタービン翼間の端壁構造。2. A blade having a shroud at a tip and a base fixed to a platform on a hub side, an inner wall surface between inner blades of a blade is provided with a protruding shape having a top portion between both leading and trailing edges. The top of the protruding shape is a curved surface, and the locus of the apex of the curved surface forms a straight line in a direction orthogonal to the turbine axis, and the position of the straight line is set to the position of the throat formed between adjacent rotor blades An end wall structure between turbine blades.
に、前記プラットフォーム外側端壁面にも前記突起形状
が形成されていることを特徴とする請求項２記載のター
ビン翼間の端壁構造。3. The end wall structure between turbine blades according to claim 2, wherein the protruding shape is further formed on the outer end wall surface of the platform in addition to the protruding shape of the shroud.
以下とすることを特徴とする請求項１から３のいずれか
に記載のタービン翼間の端壁構造。4. The height of the projection is 2.6% of the blade height.
The end wall structure between turbine blades according to any one of claims 1 to 3, wherein:
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|---|---|---|---|
| JP2000242373A JP3626899B2 (en) | 2000-08-10 | 2000-08-10 | End wall structure between turbine blades |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2000242373A JP3626899B2 (en) | 2000-08-10 | 2000-08-10 | End wall structure between turbine blades |
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| Publication Number | Publication Date |
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| JP2002054401A true JP2002054401A (en) | 2002-02-20 |
| JP3626899B2 JP3626899B2 (en) | 2005-03-09 |
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|---|---|---|---|
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2004113685A1 (en) * | 2003-06-21 | 2004-12-29 | Alstom Technology Ltd | Lateral wall embodiment for a diverting flow channel |
| JP2006291949A (en) * | 2005-04-14 | 2006-10-26 | General Electric Co <Ge> | Crescentic ramp turbine stage |
| JP2009531593A (en) * | 2006-03-31 | 2009-09-03 | アルストム テクノロジー リミテッド | Guide blades for fluid machinery, especially steam turbines |
| JP2012092825A (en) * | 2010-09-28 | 2012-05-17 | Hitachi Ltd | Steam turbine stator vane, and steam turbine using the same |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10352180B2 (en) | 2013-10-23 | 2019-07-16 | General Electric Company | Gas turbine nozzle trailing edge fillet |
-
2000
- 2000-08-10 JP JP2000242373A patent/JP3626899B2/en not_active Expired - Lifetime
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2004113685A1 (en) * | 2003-06-21 | 2004-12-29 | Alstom Technology Ltd | Lateral wall embodiment for a diverting flow channel |
| JP2006291949A (en) * | 2005-04-14 | 2006-10-26 | General Electric Co <Ge> | Crescentic ramp turbine stage |
| JP2009531593A (en) * | 2006-03-31 | 2009-09-03 | アルストム テクノロジー リミテッド | Guide blades for fluid machinery, especially steam turbines |
| JP2012092825A (en) * | 2010-09-28 | 2012-05-17 | Hitachi Ltd | Steam turbine stator vane, and steam turbine using the same |
| US9011084B2 (en) | 2010-09-28 | 2015-04-21 | Mitsubishi Hitachi Power Systems, Ltd. | Steam turbine stator vane and steam turbine using the same |
Also Published As
| Publication number | Publication date |
|---|---|
| JP3626899B2 (en) | 2005-03-09 |
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