JPS62170707A - Static blade for axial flow fluid machine - Google Patents
Static blade for axial flow fluid machineInfo
- Publication number
- JPS62170707A JPS62170707A JP1201586A JP1201586A JPS62170707A JP S62170707 A JPS62170707 A JP S62170707A JP 1201586 A JP1201586 A JP 1201586A JP 1201586 A JP1201586 A JP 1201586A JP S62170707 A JPS62170707 A JP S62170707A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- tip
- stator
- inclination angle
- inclined angle
- 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
- 239000012530 fluid Substances 0.000 title claims abstract description 17
- 230000003068 static effect Effects 0.000 title abstract 11
- 238000009434 installation Methods 0.000 claims description 6
- 230000003247 decreasing effect Effects 0.000 abstract 2
- 238000010586 diagram Methods 0.000 description 10
- 230000000694 effects Effects 0.000 description 7
- 238000000034 method Methods 0.000 description 2
- 210000001217 buttock Anatomy 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明は軸流流体機械の静翼構造に係り、とりわけ蒸気
タービン段落内部の蒸気流動の適正化のための静翼の接
線方向翼取付は傾き角の設定に関する。[Detailed Description of the Invention] [Industrial Application Field] The present invention relates to a stator vane structure for an axial flow fluid machine, and particularly to a tangential blade mounting of a stator vane for optimizing steam flow inside a steam turbine stage. Regarding setting the tilt angle.
例えば大容量の発電用蒸気タービン等においては効率の
向上は経済面、資源面等の面から極めて重要な改善課題
であり、従来から国内外の関係者による改善のための研
究開発努力がなされている。For example, improving the efficiency of large-capacity power generation steam turbines is an extremely important improvement issue from economic and resource perspectives, and research and development efforts have been made by domestic and international parties for improvement. There is.
しかしながら蒸気タービンの低圧段落部における、蒸気
流の３次元流動に関する解明若くはそれに基づく改善は
充分に行われていなかった。However, the three-dimensional flow of steam in the low-pressure stage of a steam turbine has not been sufficiently elucidated or improved based on this understanding.
第１図（、）は、フレア角（静翼ダイヤフラム上壁が下
流側に流路断面積を増大するように拡大する角度）のあ
る場合のタービン段落の子午面形状を示す。静翼１は動
翼２への流れを制御するものであり、下流側から静翼の
後縁形状６を見た場合を第１図（ｂ）に示す。従来の静
翼後縁６は直線状をなし、しかも回転軸中心から放射状
に配置されている。従って、翼面から流れを翼根元方向
へ押しつける翼列は働かずこの場合は第２図に示すよう
に、静翼出口の流れは半径方向の速度成分を持ち、翼先
端に向うような流れ８となる。このため、動翼へ流入す
る流れは半径方向速度成分を有する流れとなるが、動翼
のなす仕事は半径方向速度成分とは無関係であり、半径
方向速度成分の値はそのまま損失となってしまう。この
現象は特に静翼のフレア角が大きい場合に、より顕著に
現られる。従来から対策として、低圧タービンのフレア
角の大きい場合に、第３図に示すように、静翼を動翼回
転方向９に・θだけ傾けて取付けることで、静翼から流
れに対して翼根元方向に押しつける力を発生させること
が行われていた。このθを接線方向翼取付は傾き角と呼
ぶが、実機での値は１０″前後の値であり、第３図に示
すようにθの値は半径方向に一定値を保ち、従って翼後
縁形状６は直線状となっていた。この方法では、静翼根
元の流れは改善されるが、一方静翼先端の流れは逆に壁
から離れる方向になるため、二次流れの増大等の原因と
なる欠点がある。これの改善を意図して、実験室レベル
ではあるが、第４図に示すように、接線方向翼取付は傾
き角を静翼根元では動翼回転方向に、静翼先端では動翼
回転方向とは逆方向につける試みがなされた。そのこと
はソ連の熱工学に関する雑誌 チェプロ エネルギチイ
カＣＴＱＦＶＩ３ＨｅＰｒｅＴＮＫＡ １９６４．５
） ニ掲ｆｉす；Ｍ＝フ＋Ｊイヤニーエ ザクルルトキ
イ ポトーカ ナハラＣ０ｒＴ、／ＴＯＦ３ｂｌＹ ｐ
Ｅ（ＩＪ”；＝ＴＤＫ ） す；６ ｍ文テ紹介サレテ
イる。上記文献においては第１図（ｂ）及び第３図及び
第４図に示すような接線方向翼取付は傾き角１％た静翼
単体について実験を行い、翼長方向の損失分布を算出し
てその結果を第５図の（ａ）。FIG. 1(,) shows the meridional plane shape of a turbine stage when there is a flare angle (the angle at which the upper wall of the stator vane diaphragm expands downstream to increase the cross-sectional area of the flow path). The stator blade 1 controls the flow to the rotor blade 2, and FIG. 1(b) shows the trailing edge shape 6 of the stator blade when viewed from the downstream side. The conventional stator blade trailing edge 6 is linear and is arranged radially from the center of the rotation axis. Therefore, the blade row that pushes the flow from the blade surface toward the blade root does not work, and in this case, as shown in Figure 2, the flow at the stationary blade outlet has a velocity component in the radial direction, and the flow 8 is directed toward the blade tip. becomes. Therefore, the flow flowing into the rotor blades has a radial velocity component, but the work done by the rotor blades is unrelated to the radial velocity component, and the value of the radial velocity component becomes a loss. . This phenomenon is particularly noticeable when the stator blade has a large flare angle. Conventionally, as a countermeasure, when the flare angle of a low-pressure turbine is large, as shown in Fig. 3, by installing the stator blades at an angle of θ in the rotor blade rotation direction 9, the blade roots are removed from the stator blades relative to the flow. It was done to generate a force that pushes in the direction. This θ is called the inclination angle when the blade is installed in the tangential direction, but in actual aircraft, the value is around 10'', and as shown in Figure 3, the value of θ remains constant in the radial direction, so the trailing edge of the blade Shape 6 was straight.This method improves the flow at the root of the stator blade, but on the other hand, the flow at the tip of the stator blade moves away from the wall, which causes an increase in secondary flow. In order to improve this problem, although at a laboratory level, as shown in Fig. 4, tangential blade installation changes the inclination angle at the stator blade root in the direction of rotor blade rotation, and at the stator blade tip in the direction of rotor blade rotation. An attempt was made to attach the rotor blades in the opposite direction to the rotating direction.This was reported in the Soviet thermal engineering magazine Chepro Energitchika CTQFVI3HePreTNKA 1964.5
) Ni post; M=F+J Ianie Zakurultkii Potoka Nahara C0rT, /TOF3blY p
E(IJ"; = TDK) S; 6 m sentence introduction. In the above literature, the tangential wing installation as shown in Fig. 1(b), Fig. 3, and Fig. 4 has an inclination angle of 1%. An experiment was conducted on a single stationary blade, and the loss distribution in the blade span direction was calculated, and the results are shown in Figure 5 (a).
（ｂ）、（ｃ）で表している。上記（ａ）（ｂ）（ｃ）
は各々、第１図（ｂ）、第３図及び第４図に対応してい
る。It is represented by (b) and (c). (a) (b) (c) above
correspond to FIG. 1(b), FIG. 3, and FIG. 4, respectively.
第５図によれば、静翼単体の円環翼列としての性能は、
第４図に示すような接線方向翼取付は傾き角が好ましい
ことになる。しかしながら、静翼と動翼を組合せた段落
流れの場合は、第４図に示す方法では、翼先端近傍での
半径方向速度成分を増加させる作用があり、動翼の仕事
量の観点からは好ましい解決策とはいえない。ここで、
このことを明らかにするために、段落内の３次元流動現
象を第６図に示し、動翼入口で半径方向速度成分の発生
する機構を説明する。第６図（、）は静翼後縁から流出
する流れ１３が、動翼入口まで移動する様子を示し、第
６図（ｂ）は静翼と動翼の位置関係と静翼出口から流出
した流れが動翼入口に到達するまでの幾何学的な関係を
示す。第６図（ｂ）に示すように静翼出口からの流れ１
３は静翼と動翼の距離をＸ、流出角をαとすれば、動翼
入口に流れ１３が到達するまでに、接線方向距離でｎ≒
ｘ／ｃｏｓαだけ移動する。従って第６図（ａ）に示す
ように、静翼出口で半径方向速度成分をもたない接線方
向の流れ１３は、動翼人口１４に達した時には、１３′
に示すように半径方向の速度成分を有することになる。According to Fig. 5, the performance of a single stator blade as a ring cascade is as follows:
A tangential wing attachment as shown in FIG. 4 would favor a tilt angle. However, in the case of a stage flow in which a stationary blade and a rotor blade are combined, the method shown in Fig. 4 has the effect of increasing the radial velocity component near the blade tip, which is preferable from the viewpoint of the amount of work of the rotor blade. It's not a solution. here,
In order to clarify this, the three-dimensional flow phenomenon within the paragraph is shown in FIG. 6, and the mechanism by which the radial velocity component is generated at the rotor blade inlet will be explained. Figure 6 (,) shows how the flow 13 flowing out from the trailing edge of the stator blade moves to the rotor blade inlet, and Figure 6 (b) shows the positional relationship between the stator blade and the rotor blade and the flow 13 flowing out from the stator blade outlet. It shows the geometrical relationship until the flow reaches the rotor blade inlet. As shown in Figure 6(b), flow 1 from the stationary blade outlet
3, if the distance between the stationary blade and the rotor blade is
Move by x/cosα. Therefore, as shown in FIG. 6(a), when the tangential flow 13 having no radial velocity component at the exit of the stationary blade reaches the moving blade population 14, the flow 13'
It has a velocity component in the radial direction as shown in .
勿論、実際にはダイヤプラム上壁４と下Ｍ３によって円
環状の流路を形成しているので、流れ１３は幾分円環流
路に沿って流れるようにはなるが、円環流路の効果は翼
から流体に働く力の効果に比べて小さい。Of course, in reality, the diaphragm upper wall 4 and lower M3 form an annular flow path, so the flow 13 flows somewhat along the annular flow path, but the effect of the annular flow path is It is small compared to the effect of the force acting on the fluid from the wing.
従って、半径方向の速度成分を減少するために。Therefore, to reduce the radial velocity component.
第３図に示すように、静翼を取付ける際に、動翼回転方
向に翼を傾けて設置することが行われていた。この時の
流れの様子を第７図に示すが、接線方向翼取付は傾き角
θをつけることにより、翼から流体を根元方向に押しつ
ける力が発生し、静翼出口においては、第７図（ａ）に
示すような負の半径方向速度成分を有する流れ１３が発
生する。As shown in FIG. 3, when installing stator blades, the blades were installed with the blades tilted in the rotating direction of the rotor blades. The state of the flow at this time is shown in Figure 7. By attaching the blade in the tangential direction at an angle of inclination θ, a force is generated that pushes the fluid from the blade toward the root, and at the exit of the stationary blade, as shown in Figure 7 ( A flow 13 is generated having a negative radial velocity component as shown in a).
この流れが動翼入口１４に達すると、θを適切に選ぶこ
とにより、半径方向速度成分はほとんどない１３′のよ
うな流れとなる。このような流れは。When this flow reaches the rotor blade inlet 14, by appropriately selecting θ, it becomes a flow like 13' with almost no radial velocity component. This is the flow.
第７図（ｂ）に示すように、動翼半径方向断面に対して
、はぼ２次元的に流入することになり、流体のもつエネ
ルギを有効に動翼のなす仕事に変換することができる。As shown in Fig. 7(b), the fluid flows into the rotor blade in a radial direction in a nearly two-dimensional manner, and the energy of the fluid can be effectively converted into work performed by the rotor blade. .
これに対して前記のソ連文献では静翼単体のみについて
の対策である故に、上記のような動翼を含めた段落とし
ての問題点について対策はなされず、従ってこれを実際
のタービンの静翼に適用することは不適当である。又、
同じく前記第３図に示すような接線方向翼取付は傾き角
０を一定にすること即ち翼後縁形状を直線状となすこと
は翼先端部において流体の流れを壁面から離し、二次流
れを増大するなどの欠点を有することは前述の通りであ
る。On the other hand, in the above-mentioned Soviet literature, since the countermeasures are only for a single stator blade, no countermeasures are taken for the problem as a paragraph that includes the rotor blade, and therefore, it is not possible to apply this to the stator blade of an actual turbine. It is inappropriate to apply. or,
Similarly, when installing a tangential blade as shown in Figure 3, keeping the inclination angle 0 constant, that is, making the trailing edge shape of the blade straight, directs the fluid flow away from the wall surface at the blade tip and reduces the secondary flow. As mentioned above, it has disadvantages such as increased size.
本発明の第一は静翼群と動翼群で構成される軸流流体機
械の段落において、静翼の接線方向取付け傾き角を静翼
根元から同先端に向って次第に減少させ、しかも先端に
おいても正なる傾き角を有するようにしたことを特徴と
するものである。The first aspect of the present invention is to gradually reduce the tangential mounting angle of the stator blades from the root to the tip of the stator blade in an axial flow machine consisting of a stator blade group and a rotor blade group. It is also characterized in that it has a positive inclination angle.
本発明の第二は静翼の接線方向取付は傾き角θを動翼回
転方向を正とし、静翼翼長方向の各断面における半径位
置をＲで表した場合、上記傾き角θをＲθ”をＲθ≒ｋ
（ｋは定数）の条件で変化させるようにしたことを特徴
とするものである。The second aspect of the present invention is that when the stator blade is mounted in the tangential direction, the inclination angle θ is set as positive in the rotating direction of the rotor blade, and the radial position in each cross section in the span direction of the stator blade is expressed as R. Rθ≒k
(k is a constant).
傾き角が減少するのでその部分における翼根元方向への
押付は力が過大とならず、従って静翼先端附近で流れが
外周壁面から離されることがなくなる。又傾き角を負と
することにより流れに半径方向の速度成分を発生させる
ことがない。Since the inclination angle is reduced, the force applied toward the root of the blade at that portion will not become excessive, and the flow will not be separated from the outer peripheral wall surface near the tip of the stator blade. Furthermore, by making the inclination angle negative, no radial velocity component is generated in the flow.
又、本発明によれば、上記のようにθをＲＯをＲθ≒ｋ
（ｋは定数）の条件で変化させることによって静翼の半
径方向位置における望ましい傾き角が得※
られその結果して半径方向のすべての位置において動翼
に到達した流れに半径方向に速度成分を生するごとがな
くなる。Further, according to the present invention, as described above, θ and RO are Rθ≒k
By varying the condition (k is a constant), a desired inclination angle at the radial position of the stationary blade can be obtained.* As a result, the velocity component in the radial direction is added to the flow reaching the rotor blade at all positions in the radial direction. There will be no life left.
第８図は本発明を適用した時の静翼後縁６の形状を示す
ものである。接線方向翼取付は傾き角θは翼根光でθｒ
、翼先端でＯｔとなり、動翼回転方向９に傾けた場合を
正とした時に、θ、〉Ｏｔ〉０の関係を保持することを
特徴としている。上記の静翼の接線方向翼取付は傾き角
θは第９図に示すようなＲとθの関係で規定され、半径
方向にθは漸次変化する。前述したように、動翼入口で
半径方向速度成分を除去するためには、第６１ｉ！ｊに
示すように、静翼と動翼の翼間距離Ｘと静翼出口の流出
角αに密接に関係する。ところで第６図（ｂ）に示す接
線方向移動距離Ｑは半径位置をＲとし静翼出口から動翼
入口までの角度Ｏに換算すると幾何学的にｆｉ：Ｒθの
関係で定義することができる。そして一つの静翼につい
てはΩはほぼ一定と見て差支えがないのでこれによって
算出された角度θを接線方向翼取付は傾き角とすれば、
動翼入口で、半径方向速度成分をほぼ除去することがで
きる。FIG. 8 shows the shape of the stator blade trailing edge 6 when the present invention is applied. For tangential blade installation, the inclination angle θ is θr in the blade root light.
, Ot at the tip of the blade, and when tilted in the rotor blade rotation direction 9 is positive, the relationship θ,〉Ot〉0 is maintained. In the above-mentioned tangential blade attachment of the stationary blade, the inclination angle θ is defined by the relationship between R and θ as shown in FIG. 9, and θ gradually changes in the radial direction. As mentioned above, in order to remove the radial velocity component at the rotor blade inlet, the 61i! As shown in j, it is closely related to the distance between the stator blade and the moving blade, X, and the outflow angle α at the exit of the stator blade. By the way, the tangential movement distance Q shown in FIG. 6(b) can be geometrically defined by the relationship fi:Rθ when the radial position is R and it is converted into the angle O from the stationary blade outlet to the rotor blade inlet. For one stationary blade, it can be assumed that Ω is almost constant, so if the angle θ calculated from this is the inclination angle when the blade is installed in the tangential direction, then
At the rotor blade inlet, the radial velocity component can be substantially eliminated.
又、第６図（ｂ）より明らかなようにＱ≒ｘ／ｅＯ８α
の関係があるので静翼と動翼の翼間層１ＩＩｌｘと静翼
出口の流出角αからＱを求めることが出来る。ここでＸ
及びαは設計値であるからこれによって予めρを知り従
ってθを予め算出することができる。このＸやαの値い
は蒸気タービンについ求めて図表化したのが第９図であ
る。即ちＲθ＝２０とＲθ＝６で囲まれる範囲が実機に
適用して好適なものである。第１０図は第８図に示した
本発明の実施例と同等の効果を発生させることのできる
静翼の後縁形状を示す図である。第１０図は第８図に示
すような連続的に接線方向翼取付は傾き角を変化させる
のではなく、半径方向位置を複数個に分割し、断続的に
接線方向翼取付は傾き角を変化させる方法を示す。しか
し、第１０図でも第８図と同様にθ、〉Ｏｔ＞Ｏの関係
は保たれて゛・′いる。第１０図の特徴は、第８図の本
実施例と同（ｌＯ）
程度の半径方向速度成分を除去する効果を発生すること
ができ、しかも、第８図の本実施例よりも製作が容易と
いう効果がある。Also, as is clear from Fig. 6(b), Q≒x/eO8α
Since there is the following relationship, Q can be determined from the interblade layer 1IIlx between the stator blade and rotor blade and the outflow angle α at the exit of the stator blade. Here X
Since and α are design values, it is possible to know ρ in advance and therefore calculate θ in advance. Figure 9 shows the values of X and α determined for a steam turbine and graphed. That is, the range surrounded by Rθ=20 and Rθ=6 is suitable for application to an actual machine. FIG. 10 is a diagram showing the shape of the trailing edge of the stationary blade that can produce the same effect as the embodiment of the present invention shown in FIG. 8. Figure 10 shows that the radial position is divided into multiple parts, instead of changing the inclination angle continuously when the blade is installed tangentially as shown in Figure 8, and the angle is changed intermittently when the blade is installed tangentially. We will show you how to do this. However, in FIG. 10 as well as in FIG. 8, the relationship θ, >Ot>O is maintained. The feature of FIG. 10 is that it can produce the same effect of removing the radial velocity component as (lO) as this embodiment of FIG. 8, and it is easier to manufacture than this embodiment of FIG. 8. There is an effect.
本発明によれば流体のもつエネルギを動翼で有効に仕事
に変換できるので軸流流体機械の効率を向上させること
が出来る。According to the present invention, the energy of the fluid can be effectively converted into work by the rotor blades, so that the efficiency of the axial flow fluid machine can be improved.
第１図（ａ）はタービン段落の子午面形状図、第１図（
ｂ）は静翼の後縁形状図、第２図は静翼出口の流れを示
す図、第３図、第４図は接線方向翼取付は傾き角のある
場合の静翼後縁形状図、第５図は静翼の損失分布図、第
６図は静翼出口から動翼入口に至るまでの流れの図、第
７図は接線方向翼取付は傾き角をつけた時の流れの図、
第８図は本発明の一実施例の静翼後縁形状図、第９図は
本発明の接線方向翼取付は傾き角の半径方向分布図、−
４！５＠、第１０図（ａ）（ｂ）は本発明の他（１１）
（ほか１名）
第１図
第２図
第３０
第４図
生
ｃ’−ｑ
第５図
（α） （ｂ） （Ｃ）１嘴
入 （臀大 榎天第６図
（ａン
牛
（ｔ））
箋７０
（ｃＬ）
（ト）
第８０
Ｃ岬９
゛第７図
θ−Figure 1(a) is a meridional plane shape diagram of the turbine stage;
b) is a diagram of the trailing edge shape of the stator blade, Figure 2 is a diagram showing the flow at the exit of the stator blade, Figures 3 and 4 are diagrams of the trailing edge shape of the stator blade when the tangential blade is installed with an inclination angle, Figure 5 is a loss distribution diagram of the stator blade, Figure 6 is a flow diagram from the stator vane outlet to the rotor blade inlet, Figure 7 is a diagram of the flow when the blade is installed tangentially and at an angle of inclination.
FIG. 8 is a profile diagram of the trailing edge of a stationary blade according to an embodiment of the present invention, and FIG. 9 is a diagram of the radial distribution of the inclination angle of the tangential blade installation of the present invention.
4!5@, Figures 10 (a) and (b) are other than the present invention (11)
(1 other person) Figure 1 Figure 2 Figure 30 Figure 4 Raw c'-q Figure 5 (α) (b) (C) 1 mouth (buttocks large Enokiten Figure 6 (a n cow (t) )) Note 70 (cL) (G) No. 80 C Cape 9 ゛Figure 7 θ-
Claims (1)
おいて、上記静翼後縁の接線方向取付け傾き角θを動翼
回転方向を正とし、静翼根元の傾き角をθ＿ｒ、同先端
の傾き角をθ＿ｔで表した場合、θ＿ｒ＞θ＿ｔ＞０と
なるように静翼後縁の接線方向取付け傾き角θを静翼根
元から同先端に向つて次第に減少させ、しかも先端にお
いても正なる傾き角を有するようにしたことを特徴とす
る軸流流体機械の静翼。 ２、静翼群と動翼群で構成される軸流流体機械の段落に
おいて、上記静翼後縁の接線方向取付け傾き角θを動翼
回転方向を正とし、静翼翼長方向の各断面における半径
位置をＲで表した場合、上記傾き角θをＲθ≒ｋ（ｋは
定数）の条件で変化させるようにしたことを特徴とする
軸流流体機械の静翼。 ３、特許請求の範囲第２項において、静翼流出角をα、
静翼と動翼の軸方向翼間距離をｘで表した場合、ｋ≒ｘ
／ｃｏｓαの関係となるようにしたことを特徴とする軸
流流体機械の静翼。 ４、特許請求の範囲第２項において、ｋ＝６〜２０とす
るようにしたことを特徴とする軸流流体機械の静翼。[Claims] 1. In the paragraph of an axial flow fluid machine composed of a stator blade group and a rotor blade group, the tangential installation inclination angle θ of the stator blade trailing edge is positive with respect to the rotating direction of the rotor blade, and the stator blade If the inclination angle at the root is expressed as θ_r and the inclination angle at the tip is expressed as θ_t, then the mounting inclination angle θ in the tangential direction of the trailing edge of the stator blade is gradually increased from the root of the stator blade toward the tip so that θ_r>θ_t>0. A stationary blade for an axial flow fluid machine, characterized in that the blade has a positive inclination angle even at its tip. 2. In the paragraph of an axial flow fluid machine consisting of a stator blade group and a rotor blade group, the tangential installation inclination angle θ of the stator blade trailing edge is defined as positive in the rotor blade rotation direction, and in each cross section in the stator blade span direction. A stationary blade for an axial flow fluid machine, characterized in that when the radial position is represented by R, the above-mentioned inclination angle θ is changed under the condition that Rθ≈k (k is a constant). 3. In claim 2, the stator blade outflow angle is α,
If the axial distance between the stator blade and rotor blade is expressed as x, then k≒x
A stationary blade for an axial flow fluid machine characterized by having a relationship of /cosα. 4. A stationary blade for an axial fluid machine, characterized in that k=6 to 20 as set forth in claim 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP61012015A JPH0689651B2 (en) | 1986-01-24 | 1986-01-24 | Axial flow fluid machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP61012015A JPH0689651B2 (en) | 1986-01-24 | 1986-01-24 | Axial flow fluid machine |
Related Child Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2067115A Division JPH0692723B2 (en) | 1990-03-19 | 1990-03-19 | Axial flow fluid machine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS62170707A true JPS62170707A (en) | 1987-07-27 |
| JPH0689651B2 JPH0689651B2 (en) | 1994-11-09 |
Family
ID=11793767
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP61012015A Expired - Lifetime JPH0689651B2 (en) | 1986-01-24 | 1986-01-24 | Axial flow fluid machine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0689651B2 (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH01106903A (en) * | 1987-10-21 | 1989-04-24 | Toshiba Corp | Turbine nozzle |
| JPH03189304A (en) * | 1990-03-19 | 1991-08-19 | Hitachi Ltd | Stationary blade for axial-flow fluid machinery |
| JPH04124406A (en) * | 1990-09-17 | 1992-04-24 | Hitachi Ltd | Axial flow turbine stationary blade device and axial flow turbine |
| EP1710397A2 (en) | 2005-03-31 | 2006-10-11 | Kabushiki Kaisha Toshiba | Bowed nozzle vane |
| JP2007127132A (en) * | 2005-03-31 | 2007-05-24 | Hitachi Ltd | Axial turbine |
| EP2362063A3 (en) * | 2005-03-31 | 2012-08-29 | Hitachi Ltd. | Axial turbine |
| WO2020194901A1 (en) * | 2019-03-26 | 2020-10-01 | 株式会社Ihi | Stationary blade segment of axial turbine |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS50111403A (en) * | 1974-02-15 | 1975-09-02 | ||
| JPS5144706A (en) * | 1974-10-14 | 1976-04-16 | Tokyo Shibaura Electric Co | TAABINBANE |
-
1986
- 1986-01-24 JP JP61012015A patent/JPH0689651B2/en not_active Expired - Lifetime
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS50111403A (en) * | 1974-02-15 | 1975-09-02 | ||
| JPS5144706A (en) * | 1974-10-14 | 1976-04-16 | Tokyo Shibaura Electric Co | TAABINBANE |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH01106903A (en) * | 1987-10-21 | 1989-04-24 | Toshiba Corp | Turbine nozzle |
| JPH0478803B2 (en) * | 1987-10-21 | 1992-12-14 | Tokyo Shibaura Electric Co | |
| JPH03189304A (en) * | 1990-03-19 | 1991-08-19 | Hitachi Ltd | Stationary blade for axial-flow fluid machinery |
| JPH04124406A (en) * | 1990-09-17 | 1992-04-24 | Hitachi Ltd | Axial flow turbine stationary blade device and axial flow turbine |
| JP2753382B2 (en) * | 1990-09-17 | 1998-05-20 | 株式会社日立製作所 | Axial flow turbine vane device and axial flow turbine |
| JP2007127132A (en) * | 2005-03-31 | 2007-05-24 | Hitachi Ltd | Axial turbine |
| EP1710397A2 (en) | 2005-03-31 | 2006-10-11 | Kabushiki Kaisha Toshiba | Bowed nozzle vane |
| EP1710397A3 (en) * | 2005-03-31 | 2008-03-12 | Kabushiki Kaisha Toshiba | Bowed nozzle vane |
| EP2362063A3 (en) * | 2005-03-31 | 2012-08-29 | Hitachi Ltd. | Axial turbine |
| US8308421B2 (en) | 2005-03-31 | 2012-11-13 | Hitachi, Ltd. | Axial turbine |
| WO2020194901A1 (en) * | 2019-03-26 | 2020-10-01 | 株式会社Ihi | Stationary blade segment of axial turbine |
| JPWO2020194901A1 (en) * | 2019-03-26 | 2021-10-21 | 株式会社Ihi | Axial turbine vane segment |
| US11661854B2 (en) | 2019-03-26 | 2023-05-30 | Ihi Corporation | Stator vane segment of axial turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| JPH0689651B2 (en) | 1994-11-09 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EXPY | Cancellation because of completion of term |