JP2021004584A - Rotor blade for two-phase flow turbine and two-phase flow turbine including the rotor blade - Google Patents

Rotor blade for two-phase flow turbine and two-phase flow turbine including the rotor blade Download PDF

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JP2021004584A
JP2021004584A JP2019119337A JP2019119337A JP2021004584A JP 2021004584 A JP2021004584 A JP 2021004584A JP 2019119337 A JP2019119337 A JP 2019119337A JP 2019119337 A JP2019119337 A JP 2019119337A JP 2021004584 A JP2021004584 A JP 2021004584A
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blade
phase flow
blades
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hub
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東森　弘高
Hirotaka Higashimori
弘高 東森
亮 ▲高▼田
亮 ▲高▼田
Akira Takada
直 谷口
Sunao Taniguchi
直 谷口
小林　直樹
Naoki Kobayashi
小林　　直樹
長谷川　泰士
Hiroshi Hasegawa
泰士 長谷川
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Mitsubishi Heavy Industries Thermal Systems Ltd
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Abstract

To provide a rotor blade for a two-phase flow turbine capable of improving efficiency of the two-phase flow turbine and the two-phase flow turbine including the rotor blade.SOLUTION: A rotor blade for a two-phase flow turbine driven by a gas-liquid two-phase flow of fluid includes: a rotating shaft provided rotatably; and a plurality of blades provided in a circumferential direction around the rotating shaft to be spaced from each other and rotating in the circumferential direction. In a cross section of the blade cut along a surface perpendicular to the rotating shaft, a pressure surface of the blade includes a recessed portion recessed toward the rotating direction of the plurality of blades at least at an intermediate position in the blade height direction, and the recessed portion at least partially extends between a front edge and a rear edge of the blade.SELECTED DRAWING: Figure 4

Description

本開示は、二相流タービンの動翼及びこの動翼を備える二相流タービンに関する。 The present disclosure relates to moving blades of a two-phase flow turbine and a two-phase flow turbine including the moving blades.

特許文献１及び２にはそれぞれ、気液二相流がタービンを駆動することによって動力を回収する二相流タービンが記載されている。一般に、二相流タービンには、軸流衝動タービンの形式が使用される。このような二相流タービンにおいて、１つ又は複数のノズルから流出した気液二相流は、タービンロータの隣り合う翼間に形成された流路を流通する間に、タービンロータの回転方向の力を翼に与える。翼に与えられた力によってタービンロータが回転し、回転動力が発生する。 Patent Documents 1 and 2, respectively, describe a two-phase flow turbine in which a gas-liquid two-phase flow drives a turbine to recover power. Generally, for two-phase flow turbines, the type of axial flow impulse turbine is used. In such a two-phase flow turbine, the gas-liquid two-phase flow flowing out of one or more nozzles is in the direction of rotation of the turbine rotor while flowing through a flow path formed between adjacent blades of the turbine rotor. Give power to the wings. The force applied to the blades causes the turbine rotor to rotate, generating rotational power.

二相流タービンでは、気相と液相とを平均した流速の変化が動翼で動力に変換されるように翼形状が設計される。しかし、液相の体積流量に比べて気相の体積流量が圧倒的に大きいため、従来の二相流タービンの翼形状は、気相に合わせて設計されることになると言える。このため、重量比では逆に圧倒的に大きい液相に適合するように翼形状が設計されないことになるため、二相流タービンの動翼効率が低くなるという課題がある。 In a two-phase flow turbine, the blade shape is designed so that the change in flow velocity, which is the average of the gas phase and the liquid phase, is converted into power by the moving blade. However, since the volumetric flow rate of the gas phase is overwhelmingly larger than the volumetric flow rate of the liquid phase, it can be said that the blade shape of the conventional two-phase flow turbine is designed according to the gas phase. For this reason, on the contrary, the blade shape is not designed so as to be compatible with the overwhelmingly large liquid phase in terms of weight ratio, so that there is a problem that the blade efficiency of the two-phase flow turbine is lowered.

特許第３２２２３５０号公報Japanese Patent No. 3222350 実願昭６０−１８７１０５号公報Judgment No. 60-187105

本発明者らは検討の結果、二相流タービンの動翼効率が低くなる原因を以下のように考えた。二相流タービンでは、ノズルから流出した気液二相流は、液相が表面張力によって微細化されて液滴となることによって、気相と液相とが分離された流れとなる。翼形状が気相に合わせて設計されていると、気相は、翼面に沿って最適に流れることができるが、液相は、液滴が翼面に衝突して再度集積された後、翼面を必ずしも最適に流れることはできない。このため、二相流タービンにおける以下の３つの損失要因Ａ、Ｂ、Ｃが導かれる。 As a result of the study, the present inventors considered the cause of the low blade efficiency of the two-phase flow turbine as follows. In a two-phase flow turbine, the gas-liquid two-phase flow flowing out of the nozzle is a flow in which the gas phase and the liquid phase are separated by the liquid phase being refined by surface tension into droplets. If the blade shape is designed for the gas phase, the gas phase can flow optimally along the blade surface, but the liquid phase will occur after the droplets collide with the blade surface and re-accumulate. It cannot always flow optimally on the wing surface. Therefore, the following three loss factors A, B, and C in the two-phase flow turbine are derived.

（損失要因Ａ）
液相は翼の圧力面に沿って流れるが、液相の粘性は気相に比べて大きいため、液相の流れの翼面に対する摩擦に起因して、気相のみの単相の流れに比べて損失が大きくなる。 (Loss factor A)
The liquid phase flows along the pressure plane of the blade, but since the viscosity of the liquid phase is higher than that of the gas phase, it is compared with the single phase flow of only the gas phase due to the friction of the flow of the liquid phase with respect to the blade surface. And the loss increases.

（損失要因Ｂ）
気相の体積流量が液相の体積流量に比べて圧倒的に大きい気液二相流が翼間の流路を流通すると、液相はほぼ翼の圧力面のみに沿って流れるので、液相が接する圧力面の抵抗はほぼ変化ないが、液相の体積流量が減少すると、液相の単位体積当たりの損失が大きくなる。液相の体積流量が減少すると、液相のみの単相の流れが成す仕事に対する損失の割合に比べて、液相の成す仕事が減少する一方で損失は変わらないので、液相が成す仕事に対する損失の割合が大きくなり、効率が低下する。 (Loss factor B)
The volumetric flow rate of the gas phase is overwhelmingly larger than the volume flow rate of the liquid phase. When the gas-liquid two-phase flow flows through the flow path between the blades, the liquid phase flows almost only along the pressure surface of the blades. Although the resistance of the pressure surface in contact with the liquid phase does not change, the loss per unit volume of the liquid phase increases as the volumetric flow rate of the liquid phase decreases. When the volumetric flow rate of the liquid phase decreases, the work performed by the liquid phase decreases but the loss does not change compared to the ratio of the loss to the work performed by the single-phase flow of the liquid phase only. The rate of loss increases and efficiency decreases.

（損失要因Ｃ）
翼の圧力面に沿って流れる液相の圧力面に対する摩擦により、圧力面上に境界層が形成される。この状態でタービンロータが回転すると、境界層に遠心力が作用し、境界層が翼高さ方向に移動する。境界層が遠心力によって翼高さ方向に移動すると、翼から境界層に動力が与えられる。これは、翼が液体に成す動力のポンプ作用である。 (Loss factor C)
The friction of the liquid phase flowing along the pressure plane of the blade against the pressure plane forms a boundary layer on the pressure plane. When the turbine rotor rotates in this state, centrifugal force acts on the boundary layer, and the boundary layer moves in the blade height direction. When the boundary layer moves in the blade height direction by centrifugal force, power is applied from the blade to the boundary layer. This is the pumping action of the power that the wings make into liquid.

これら３つの損失要因Ａ〜Ｃにより、二相流特有の損失が発生するので、二相流タービンの効率が著しく低下するが、特許文献１及び２のいずれにも、これらの損失要因Ａ〜Ｃに基づく損失低下の抑制は記載されていない。 Since the loss peculiar to the two-phase flow is generated by these three loss factors A to C, the efficiency of the two-phase flow turbine is significantly lowered. However, in both Patent Documents 1 and 2, these loss factors A to C are obtained. There is no mention of suppression of loss reduction based on.

上述の事情に鑑みて、本開示の少なくとも１つの実施形態は、二相流タービンの効率を向上できる二相流タービンの動翼及びこの動翼を備える二相流タービンを提供することを目的とする。 In view of the above circumstances, at least one embodiment of the present disclosure aims to provide a blade of a two-phase flow turbine capable of improving the efficiency of the two-phase flow turbine and a two-phase flow turbine including the blade. To do.

（１）本発明の少なくとも１つの実施形態に係る二相流タービンの動翼は、
流体の気液二相流によって駆動される二相流タービンの動翼であって、
回転可能に設けられた回転軸と、
前記回転軸を中心とした周方向に互いに間隔をあけるようにして設けられるとともに前記周方向に回転する複数の翼と
を備え、前記翼は、前記気液二相流が前記翼に相対的に前記回転軸の軸方向の上流から下流に向かって流れる方向における上流側の前縁と下流側の後縁とを有し、
前記回転軸に垂直な面に沿って切断した前記翼の断面において、前記翼の圧力面は、少なくとも翼高さ方向中間位置において、前記複数の翼の回転方向に向かって凹む凹部を有し、該凹部は、前記前縁及び前記後縁間を少なくとも部分的に延びる。 (1) The moving blade of the two-phase flow turbine according to at least one embodiment of the present invention is
The blades of a two-phase flow turbine driven by a gas-liquid two-phase flow of fluid.
Rotatably provided rotating shaft and
The blades are provided with a plurality of blades that are provided so as to be spaced apart from each other in the circumferential direction about the rotation axis and that rotate in the circumferential direction, and the blades have the gas-liquid two-phase flow relative to the blades. It has an upstream front edge and a downstream trailing edge in the direction of flow from upstream to downstream in the axial direction of the rotation axis.
In a cross section of the blade cut along a plane perpendicular to the axis of rotation, the pressure surface of the blade has recesses recessed in the direction of rotation of the plurality of blades, at least at intermediate positions in the blade height direction. The recess extends at least partially between the front edge and the trailing edge.

上記（１）の構成によると、気液二相流の液相は、凹部に沿って圧力面を前縁近傍から後縁に向かって流れるようになる。凹部に沿って流れる液相の境界層は、遠心力が作用しても、凹部の凹面によって翼高さ方向の移動が抑制されるので、ポンプ作用による損失が抑制される。また、液相の境界層と翼面との翼高さ方向の接触長さが短くなるので、圧力面に対する液相の抵抗が小さくなる。その結果、二相流タービンの効率を向上することができる。尚、翼高さ方向中間位置に設けられた凹部は、翼高さ方向に最も曲率が大きい部分を有し、この部分から翼のハブ端及びチップ端に向かって次第に曲率が小さくなるように構成されても、直線状に構成されてもよい。また、凹部は、翼面に対して窪んだ複数の溝が翼高さ方向に連続して並ぶようにして構成されてもよい。 According to the configuration of (1) above, the liquid phase of the gas-liquid two-phase flow flows along the recess from the vicinity of the front edge toward the rear edge on the pressure surface. Even if centrifugal force acts on the boundary layer of the liquid phase flowing along the recess, the concave surface of the recess suppresses the movement in the blade height direction, so that the loss due to the pumping action is suppressed. Further, since the contact length between the boundary layer of the liquid phase and the blade surface in the blade height direction is shortened, the resistance of the liquid phase to the pressure surface is reduced. As a result, the efficiency of the two-phase flow turbine can be improved. The recess provided at the intermediate position in the blade height direction has a portion having the largest curvature in the blade height direction, and is configured so that the curvature gradually decreases from this portion toward the hub end and the tip end of the blade. It may be formed in a straight line. Further, the recess may be configured such that a plurality of grooves recessed with respect to the blade surface are continuously arranged in the blade height direction.

（２）いくつかの実施形態では、上記（１）の構成において、
隣り合う２つの翼間に前記流体の気液二相流が流通する流路が形成され、
前記２つの翼のうちの一方の翼の前縁と他方の翼の負圧面上の位置である第１位置とによって、前記流路の流路面積が最小となる入口スロートが形成され、
前記回転軸の軸中心から一定半径の円筒面に沿って切断した前記翼の断面において、前記一方の翼の圧力面上には、前記翼の前縁からの軸方向距離が前記負圧面上の前記前縁から前記第１位置までの軸方向距離と同じになる第２位置が存在し、前記凹部は、少なくとも前記第２位置から前記一方の翼の後縁に向かって延びる。 (2) In some embodiments, in the configuration of (1) above,
A flow path through which the gas-liquid two-phase flow of the fluid flows is formed between two adjacent blades.
The front edge of one of the two blades and the first position on the negative pressure surface of the other blade form an inlet throat that minimizes the flow path area of the flow path.
In the cross section of the blade cut along a cylindrical surface having a constant radius from the axis center of the rotation axis, the axial distance from the front edge of the blade is on the negative pressure surface on the pressure surface of the one blade. There is a second position that is the same as the axial distance from the front edge to the first position, and the recess extends from at least the second position towards the trailing edge of the one wing.

隣り合う２つの翼間に形成された流路を流通する気液二相流の液相は、前縁から第２位置までの間で翼の圧力面に達する。上記（２）の構成によると、少なくとも第２位置から翼の後縁に向かって延びるように凹部が形成されていることにより、翼の圧力面に達した液相を確実に凹部に沿って流すことができるようになるので、上記（１）の構成から得られる作用効果を確実に得ることができる。尚、凹部は、第２位置よりも翼の前縁側に延びていてもよいし、翼の後縁まで延びていてもよい。 The liquid phase of the gas-liquid two-phase flow flowing through the flow path formed between two adjacent blades reaches the pressure plane of the blades from the front edge to the second position. According to the configuration of (2) above, since the recess is formed so as to extend from at least the second position toward the trailing edge of the blade, the liquid phase that has reached the pressure surface of the blade is surely flowed along the recess. Therefore, the action and effect obtained from the configuration of the above (1) can be surely obtained. The recess may extend toward the front edge of the wing from the second position, or may extend to the trailing edge of the wing.

（３）いくつかの実施形態では、上記（１）または（２）の構成において、
前記回転軸に垂直な面に沿って切断した前記翼の断面における前記圧力面において、前記凹部は、ハブ端とチップ端との間の一部に前記翼の回転方向に向かって凹み且つ円弧状に湾曲した湾曲部を含み、前記湾曲部は、前記チップ端側の端部であるチップ側端部及び前記ハブ端側の端部であるハブ側端部を有し、
該湾曲部の曲率は、前記ハブ端と前記ハブ側端部との間の前記圧力面の曲率及び前記チップ端と前記チップ側端部との間の前記圧力面の曲率よりも大きい。 (3) In some embodiments, in the configuration of (1) or (2) above,
In the pressure plane in the cross section of the wing cut along a plane perpendicular to the axis of rotation, the recess is recessed and arcuate in a portion between the hub end and the tip end in the direction of rotation of the wing. The curved portion has a chip side end portion which is an end portion on the tip end side and a hub side end portion which is an end portion on the hub end side.
The curvature of the curved portion is larger than the curvature of the pressure surface between the hub end and the hub side end portion and the curvature of the pressure surface between the chip end and the chip side end portion.

上記（３）の構成によると、隣り合う２つの翼間に形成された流路を流通する気液二相流の液相は、曲率の大きい湾曲部に沿って圧力面を後縁に向かって流れるようになる。曲率の大きい湾曲部に沿って液相が流れると、曲率の小さい面に沿って液相が流れる場合に比べて、液相が翼面に接する濡れ縁長さが短くなるので、圧力面に対する液相の抵抗が小さくなり、二相流タービンの効率を向上することができる。 According to the configuration of (3) above, the liquid phase of the gas-liquid two-phase flow flowing through the flow path formed between the two adjacent blades moves the pressure surface toward the trailing edge along the curved portion having a large curvature. It will flow. When the liquid phase flows along a curved portion having a large curvature, the wet edge length at which the liquid phase contacts the blade surface becomes shorter than when the liquid phase flows along a surface having a small curvature, so that the liquid phase with respect to the pressure surface The resistance of the turbine is reduced, and the efficiency of the two-phase flow turbine can be improved.

（４）いくつかの実施形態では、上記（３）の構成において、
前記チップ側端部から前記チップ端までの面は、前記回転軸の軸中心と前記チップ側端部とを通る第１直線に対して前記複数の翼の回転方向と反対側に位置する。 (4) In some embodiments, in the configuration of (3) above,
The surface from the chip side end portion to the chip end portion is located on the side opposite to the rotation direction of the plurality of blades with respect to the first straight line passing through the axial center of the rotation shaft and the chip side end portion.

この構成によると、回転軸に垂直な面に沿って切断した翼の断面において、チップ側端部からチップ端までの面は、湾曲部を後縁に向かって流れる流れの主流及び境界層に作用する翼負荷と遠心力との合成力の方向に対して垂直な方向よりもさらに回転方向とは逆方向に傾斜することになる。このため、チップ側端部からチップ端までの面に沿って、液相の境界層が翼高さの半径方向外向きに移動することを抑制し、さらにチップ端側の主流及び境界層が湾曲部に向かって半径方向内向きに移動しやすくなるので、ポンプ作用による損失が抑制され、二相流タービンの効率を向上することができる。 According to this configuration, in the cross section of the wing cut along the plane perpendicular to the axis of rotation, the plane from the tip end to the tip end acts on the mainstream and boundary layer of the flow flowing through the bend towards the trailing edge. The wing load and the centrifugal force are inclined in the direction opposite to the rotation direction rather than the direction perpendicular to the direction of the combined force. Therefore, the boundary layer of the liquid phase is suppressed from moving outward in the radial direction of the blade height along the surface from the tip side end to the tip end, and the mainstream and the boundary layer on the tip end side are curved. Since it becomes easy to move inward in the radial direction toward the portion, the loss due to the pumping action can be suppressed, and the efficiency of the two-phase flow turbine can be improved.

（５）いくつかの実施形態では、上記（３）または（４）の構成において、
前記ハブ側端部から前記ハブ端までの面は、前記回転軸の軸中心と前記ハブ側端部とを通る第２直線上、又は、該第２直線に対して前記複数の翼の回転方向と反対側に位置する。 (5) In some embodiments, in the configuration of (3) or (4) above,
The surface from the hub-side end to the hub end is on a second straight line passing through the axis center of the rotation shaft and the hub-side end, or in the rotation direction of the plurality of blades with respect to the second straight line. Located on the opposite side of.

この構成によると、ハブ側端部からハブ端までの面において、翼の前縁側から当該面に到達する液相の境界層が湾曲部に向かって半径方向外向きに移動しやすくなり湾曲部に集積するので、液相が翼面に接する濡れ縁長さが短くなり、圧力面に対する液相の抵抗が小さくなって、二相流タービンの効率を向上することができる。 According to this configuration, on the surface from the hub end to the hub end, the boundary layer of the liquid phase reaching the surface from the front edge side of the wing easily moves outward in the radial direction toward the curved portion, and becomes a curved portion. Since they are integrated, the length of the wet edge at which the liquid phase contacts the blade surface is shortened, the resistance of the liquid phase to the pressure surface is reduced, and the efficiency of the two-phase flow turbine can be improved.

（６）いくつかの実施形態では、上記（３）〜（５）のいずれかの構成において、
前記凹部は、前記チップ側端部から前記チップ端まで平坦に延びる第１平坦面、又は、前記ハブ側端部から前記ハブ端まで平坦に延びる第２平坦面の少なくとも一方を含む。 (6) In some embodiments, in any of the configurations (3) to (5) above,
The recess includes at least one of a first flat surface extending flat from the chip side end to the chip end or a second flat surface extending flat from the hub side end to the hub end.

この構成によると、回転軸に垂直な面に沿って切断した翼の断面において、翼高さ方向中間位置における凹部の構成が簡単になるので、凹部の形成作業を簡素化することができる。 According to this configuration, in the cross section of the blade cut along the plane perpendicular to the rotation axis, the configuration of the recess at the intermediate position in the blade height direction is simplified, so that the work of forming the recess can be simplified.

（７）いくつかの実施形態では、上記（３）〜（６）のいずれかの構成において、
前記湾曲部は、前記翼の翼高さ方向に曲率の分布を有し、前記ハブ端から前記チップ端に向かって前記翼の翼高さの３０％の位置から８０％の位置の範囲で前記曲率が最大となる。 (7) In some embodiments, in any of the configurations (3) to (6) above,
The curved portion has a distribution of curvature in the blade height direction of the blade, and the curved portion has a position of 30% to 80% of the blade height of the blade from the hub end to the tip end. The curvature is maximized.

この構成によると、回転軸の軸中心から一定半径の円筒面に沿って切断した翼の断面において、隣り合う２つの翼間に形成された流路を流通する気液二相流中の液相は、回転軸に垂直な面に沿って切断した翼の断面において曲率が最大の部分に沿って圧力面を後縁に向かって流れやすくなり、液相が圧力面に接する濡れ縁長さをより短くできるので、圧力面に対する液相の抵抗が小さくなり、二相流タービンの効率を向上することができる。 According to this configuration, in the cross section of a blade cut along a cylindrical surface having a constant radius from the axis center of the rotation axis, the liquid phase in the gas-liquid two-phase flow flowing through the flow path formed between two adjacent blades. Makes it easier for the liquid phase to flow toward the trailing edge of the pressure plane along the portion of the cross section of the wing cut along the plane perpendicular to the axis of rotation, and shortens the length of the wet edge where the liquid phase contacts the pressure plane. As a result, the resistance of the liquid phase to the pressure surface is reduced, and the efficiency of the two-phase flow turbine can be improved.

（８）いくつかの実施形態では、上記（３）〜（７）のいずれかの構成において、
前記回転軸の軸中心から前記最も凹んだ部分までの距離を、前記翼の入口においてＲ１とし、前記翼の出口においてＲ３としたとき、前記湾曲部のうち前記複数の翼の回転方向に向かって最も凹んだ部分は、前記翼の子午面において前記入口から前記出口の中間における前記距離Ｒ２がＲ１より小さく前記ハブ端に向かって凹状になるように曲線的に変化する（ただし、Ｒ３がＲ２に対してわずかに大きくなる範囲に留める）ように構成される。 (8) In some embodiments, in any of the configurations (3) to (7) above,
When the distance from the axis center of the rotation axis to the most recessed portion is R1 at the inlet of the blade and R3 at the exit of the blade, the curved portion is directed toward the rotation direction of the plurality of blades. The most recessed portion curves in the meridional plane of the wing so that the distance R2 between the inlet and the exit is smaller than R1 and concave toward the hub end (however, R3 becomes R2). On the other hand, it is configured to stay in a slightly larger range).

この構成によると、前縁から第２位置までの間で圧力面に到達した液相が、チップ側端部からチップ端までの面からも、ハブ側端部からハブ端までの面からも、湾曲部に向かって移動して湾曲部において合流して湾曲部を後縁に向かって流れるので、液相の流れを直線状にすることができる。言い換えると、液相の直線状の流れに垂直な力が成す仕事がポンプ作用であり、この構成によって液相の流れを直線状にすることで、遠心力による翼高さ方向の移動に伴うポンプ作用を抑制でき、液相が翼面に接する濡れ縁長さも短くなり、圧力面に対する液相の抵抗が小さくなるので、ポンプ作用による損失が抑制されるとともに圧力面に対する液相の抵抗が小さくり、二相流タービンの効率を向上することができる。 According to this configuration, the liquid phase that has reached the pressure surface between the front edge and the second position can be seen from the surface from the chip side end to the chip end and from the surface from the hub side end to the hub end. Since it moves toward the curved portion, merges at the curved portion, and flows through the curved portion toward the trailing edge, the flow of the liquid phase can be made linear. In other words, the work performed by the force perpendicular to the linear flow of the liquid phase is the pumping action, and by making the flow of the liquid phase linear by this configuration, the pump that accompanies the movement in the blade height direction due to the centrifugal force. The action can be suppressed, the length of the wet edge where the liquid phase contacts the blade surface is shortened, and the resistance of the liquid phase to the pressure surface is reduced, so that the loss due to the pumping action is suppressed and the resistance of the liquid phase to the pressure surface is reduced. The efficiency of the two-phase flow turbine can be improved.

（９）いくつかの実施形態では、上記（３）〜（８）のいずれかの構成において、
前記湾曲部は前記翼の前記後縁まで延びており、
前記湾曲部の下流端は、前記凹部の前記湾曲部以外の部分の下流端よりも前記翼の前記前縁側に位置する。 (9) In some embodiments, in any of the configurations (3) to (8) above,
The curved portion extends to the trailing edge of the wing.
The downstream end of the curved portion is located closer to the front edge of the wing than the downstream end of the portion of the recess other than the curved portion.

液相は主に湾曲部に沿って流れるが、上記（９）の構成によると、湾曲部に沿って流れる液相は、湾曲部以外の部分を流れる液相に比べて圧力面上を流れる距離が短くなる。そのため、圧力面上を流れる距離が短い液相が増加し、圧力面に対する液相の抵抗が小さくなるので、二相流タービンの効率を向上することができる。 The liquid phase mainly flows along the curved portion, but according to the configuration (9) above, the liquid phase flowing along the curved portion is a distance flowing on the pressure surface as compared with the liquid phase flowing in the portion other than the curved portion. Becomes shorter. Therefore, the number of liquid phases flowing on the pressure surface is short, and the resistance of the liquid phase to the pressure surface is reduced, so that the efficiency of the two-phase flow turbine can be improved.

（１０）いくつかの実施形態では、上記（１）〜（９）のいずれかの構成において、
前記入口及び前記出口間の中間部における前記距離をＲ２とすると、Ｒ２＜Ｒ１であり、
前記回転軸に対して垂直な面に沿って切断した前記翼の断面において、前記動翼に流入する前記流体の流れ方向に対して垂直で前記回転軸の軸中心を通る直線を第３直線とし、前記周方向に隣り合う前記翼間に流入した前記流体が前記中間部にあるときの前記流体から前記第３直線までの距離をＹ１とし、前記流体が前記下流端にあるときの前記流体から前記第３直線までの距離をＹ２とすると、Ｙ１＜Ｙ２のときはＲ２＜Ｒ３であり、Ｙ１＞Ｙ２のときはＲ２＞Ｒ３である。 (10) In some embodiments, in any of the configurations (1) to (9) above,
If the distance between the inlet and the outlet is R2, then R2 <R1.
In the cross section of the blade cut along the plane perpendicular to the rotation axis, a straight line passing through the axis center of the rotation axis perpendicular to the flow direction of the fluid flowing into the moving blade is defined as a third straight line. The distance from the fluid to the third straight line when the fluid flowing between the blades adjacent to each other in the circumferential direction is in the intermediate portion is set to Y1, and from the fluid when the fluid is at the downstream end. Assuming that the distance to the third straight line is Y2, R2 <R3 when Y1 <Y2 and R2> R3 when Y1> Y2.

この構成によると、液相が動翼内を直線状に移動することができ、液相が圧力面を流れる際に、液相の流れが描く直線よりも翼高さ方向チップ側縁側への移動を抑制できるので、ポンプ作用を低減でき、二相流タービンの効率を向上することができる。 According to this configuration, the liquid phase can move linearly in the moving blade, and when the liquid phase flows on the pressure surface, it moves toward the tip side edge side in the blade height direction with respect to the straight line drawn by the flow of the liquid phase. It is possible to reduce the pumping action and improve the efficiency of the two-phase flow turbine.

ただし、上記（１０）の構成において、Ｒ２＜Ｒ３とすると、流体が直線状に移動したとしても、中間部から下流端までの間に、回転軸の軸中心から流体までの距離の増加に伴うポンプ作用が生じるので、Ｙ１＞Ｙ２かつＲ２＞Ｒ３とすることが好ましい。 However, in the configuration of (10) above, if R2 <R3, even if the fluid moves linearly, the distance from the center of the rotation axis to the fluid increases between the intermediate portion and the downstream end. Since a pumping action occurs, it is preferable that Y1> Y2 and R2> R3.

（１１）本発明の少なくとも１つの実施形態に係る二相流タービンは、
上記（１）〜（１０）のいずれかの動翼と、
前記動翼に向けて前記流体の気液二相流を流出する少なくとも１つのノズルと
を備える。 (11) The two-phase flow turbine according to at least one embodiment of the present invention is
With any of the above (1) to (10) blades,
It is provided with at least one nozzle that discharges a gas-liquid two-phase flow of the fluid toward the rotor blade.

この構成によると、ポンプ作用による損失が抑制されるとともに圧力面に対する液相の抵抗が小さくなるので、二相流タービンの効率を向上することができる。 According to this configuration, the loss due to the pumping action is suppressed and the resistance of the liquid phase to the pressure surface is reduced, so that the efficiency of the two-phase flow turbine can be improved.

本開示の少なくとも１つの実施形態によれば、気液二相流の液相は、凹部に沿って圧力面を前縁近傍から後縁に向かって流れるようになる。凹部に沿って流れる液相の境界層は、遠心力が作用しても、凹部の凹面によって翼高さ方向の移動が抑制されるので、ポンプ作用による損失が抑制される。また、液相の境界層と翼面との翼高さ方向の接触長さが短くなるので、圧力面に対する液相の抵抗が小さくなる。その結果、二相流タービンの効率を向上することができる。 According to at least one embodiment of the present disclosure, the liquid phase of the gas-liquid two-phase flow flows along the recess along the pressure plane from the vicinity of the front edge toward the trailing edge. Even if centrifugal force acts on the boundary layer of the liquid phase flowing along the recess, the concave surface of the recess suppresses the movement in the blade height direction, so that the loss due to the pumping action is suppressed. Further, since the contact length between the boundary layer of the liquid phase and the blade surface in the blade height direction is shortened, the resistance of the liquid phase to the pressure surface is reduced. As a result, the efficiency of the two-phase flow turbine can be improved.

本開示の実施形態１に係る二相流タービンの構成を示す図である。It is a figure which shows the structure of the two-phase flow turbine which concerns on Embodiment 1 of this disclosure. 図１のＩＩ−ＩＩ線に沿った断面図である。It is sectional drawing along the line II-II of FIG. 本開示の実施形態１に係る二相流タービンにおいて、動翼の隣り合う２つの翼を翼高さ方向中間位置で回転軸の軸中心から一定半径の円筒面に沿って切断した断面図である。In the two-phase flow turbine according to the first embodiment of the present disclosure, it is a cross-sectional view in which two adjacent blades of a moving blade are cut along a cylindrical surface having a constant radius from the axis center of the rotation axis at an intermediate position in the blade height direction. .. 本開示の実施形態１に係る二相流タービンにおいて、冷媒の気液二相流が動翼の隣り合う２つの翼間の流路を流れる動作を説明するための図である。It is a figure for demonstrating the operation which the gas-liquid two-phase flow of a refrigerant flows in the flow path between two adjacent blades of a moving blade in the two-phase flow turbine which concerns on Embodiment 1 of this disclosure. 本開示の実施形態１に係る二相流タービンにおいて、冷媒の気液二相流中の液相が動翼の隣り合う２つの翼間の流路中を翼の圧力面に沿って流れる動作を説明するための図である。In the two-phase flow turbine according to the first embodiment of the present disclosure, an operation in which the liquid phase in the gas-liquid two-phase flow of the refrigerant flows in the flow path between two adjacent blades of the moving blade along the pressure surface of the blade. It is a figure for demonstrating. 本開示の実施形態１に係る二相流タービンの動翼の翼の変形例を示す断面図である。It is sectional drawing which shows the modification of the blade of the moving blade of the two-phase flow turbine which concerns on Embodiment 1 of this disclosure. 本開示の実施形態１に係る二相流タービンの動翼の翼の別の変形例を示す断面図である。It is sectional drawing which shows another modification of the blade of the moving blade of the two-phase flow turbine which concerns on Embodiment 1 of this disclosure. 本開示の実施形態１に係る二相流タービンの動翼の翼のさらに別の変形例を示す断面図である。It is sectional drawing which shows still another modification of the blade of the moving blade of the two-phase flow turbine which concerns on Embodiment 1 of this disclosure. 本開示の実施形態２に係る二相流タービンの動翼を回転軸の軸方向に見た図である。It is a figure which looked at the moving blade of the two-phase flow turbine which concerns on Embodiment 2 of this disclosure in the axial direction of the rotation axis. 本開示の実施形態２に係る二相流タービンの動翼を流通する気液二相流の動作を説明するための図である。It is a figure for demonstrating the operation of the gas-liquid two-phase flow flowing through the moving blade of the two-phase flow turbine which concerns on Embodiment 2 of this disclosure. 本開示の実施形態３に係る二相流タービンにおいて、冷媒の気液二相流が動翼の隣り合う２つの翼間の流路中を翼の圧力面に沿って流れる動作を説明するための図である。In the two-phase flow turbine according to the third embodiment of the present disclosure, an operation for explaining an operation in which a gas-liquid two-phase flow of a refrigerant flows along a pressure plane of a blade in a flow path between two adjacent blades of a moving blade. It is a figure. 本開示の実施形態３に係る二相流タービンにおいて、冷媒の気液二相流が動翼の隣り合う２つの翼間の流路を流れる動作を説明するための図である。It is a figure for demonstrating the operation which the gas-liquid two-phase flow of a refrigerant flows in the flow path between two adjacent blades of a moving blade in the two-phase flow turbine which concerns on Embodiment 3 of this disclosure.

以下、図面を参照して本発明のいくつかの実施形態について説明する。ただし、本発明の範囲は以下の実施形態に限定されるものではない。以下の実施形態に記載されている構成部品の寸法、材質、形状、その相対配置などは、本発明の範囲をそれにのみ限定する趣旨ではなく、単なる説明例に過ぎない。 Hereinafter, some embodiments of the present invention will be described with reference to the drawings. However, the scope of the present invention is not limited to the following embodiments. The dimensions, materials, shapes, relative arrangements, and the like of the components described in the following embodiments are not intended to limit the scope of the present invention to that alone, but are merely explanatory examples.

（実施形態１）
図１に示されるように、本開示の実施形態１に係る二相流タービン１は、例えば冷凍機の冷凍サイクルにおいて膨張弁の代わりとして設けられる衝動式タービンであり、冷凍回路を循環する冷媒によって駆動される。二相流タービン１は、動翼１０とノズル２０とを備えている。動翼１０は、円盤状のディスク１１と、ディスク１１の中心を通るようにしてディスク１１に固定された回転軸１２と、ディスク１１の外周面に等間隔をあけて固定された複数の翼１３とを備えている。すなわち、複数の翼１３は、回転軸１２を中心とした周方向に互いに間隔をあけるようにして設けられている。この構成により、回転軸１２を中心とした周方向（回転方向Ｄ１）に翼１３が回転すると、この回転に伴ってディスク１１が回転する、すなわちディスク１１に固定された回転軸が回転方向Ｄに回転するようになっている。 (Embodiment 1)
As shown in FIG. 1, the two-phase flow turbine 1 according to the first embodiment of the present disclosure is, for example, an impulse turbine provided in place of an expansion valve in the refrigeration cycle of a refrigerator, and is provided by a refrigerant circulating in the refrigeration circuit. Driven. The two-phase flow turbine 1 includes a moving blade 10 and a nozzle 20. The moving blades 10 include a disk-shaped disc 11, a rotating shaft 12 fixed to the disc 11 so as to pass through the center of the disc 11, and a plurality of blades 13 fixed to the outer peripheral surface of the disc 11 at equal intervals. And have. That is, the plurality of blades 13 are provided so as to be spaced apart from each other in the circumferential direction about the rotation shaft 12. With this configuration, when the blade 13 rotates in the circumferential direction (rotation direction D1) about the rotation axis 12, the disk 11 rotates with this rotation, that is, the rotation axis fixed to the disk 11 rotates in the rotation direction D. It is designed to rotate.

ノズル２０は、その内部に流入口２０ｂから噴出口２０ａに延びるように流路２１が形成されるとともに噴出口２０ａが翼１３に面するように設けられている。流路２１は、流入口２０ｂから噴出口２０ａに向かって流路面積が減少し、流入口２０ｂと噴出口２０ａとの間の位置２０ｃにおいて流路面積が最小となり、位置２０ｃから噴出口２０ａに向かって流路面積が増加するように構成されている。 The nozzle 20 is provided so that a flow path 21 is formed inside the nozzle 20 so as to extend from the inflow port 20b to the spout 20a and the spout 20a faces the blade 13. The flow path area of the flow path 21 decreases from the inflow port 20b toward the spout 20a, the flow path area becomes the minimum at the position 20c between the inflow port 20b and the spout 20a, and from the position 20c to the spout 20a. It is configured so that the flow path area increases toward it.

図２には、翼１３の翼高さ方向に沿って切断した翼１３の断面が示されている。この断面において、各翼１３の圧力面１４には、翼１３の回転方向Ｄ１に向かって凹む凹部３０が形成されている。各翼１３の負圧面１５は、翼１３の回転方向Ｄ１に向かって凸状に湾曲している。 FIG. 2 shows a cross section of the blade 13 cut along the blade height direction of the blade 13. In this cross section, the pressure surface 14 of each blade 13 is formed with a recess 30 recessed in the rotation direction D1 of the blade 13. The negative pressure surface 15 of each blade 13 is curved in a convex shape toward the rotation direction D1 of the blade 13.

凹部３０は、翼１３の回転方向Ｄ１に向かって凹み且つ円弧状に湾曲した湾曲部３１と、湾曲部３１のチップ端１６側の端部であるチップ側端部３１ａからチップ端１６まで平坦に延びる第１平坦面３２と、湾曲部３１のハブ端１７側の端部であるハブ側端部３１ｂからハブ端１７まで平坦に延びる第２平坦面３３とを含んでいる。湾曲部３１のうち第１直線Ｌ１に対して最も凹んだ部分３１ｃは、圧力面１４において翼１３の翼高さ方向中間位置Ｐ０に位置している。第１平坦面３２は、チップ側端部３１ａよりもチップ端１６側において、回転軸１２の軸中心１２ａとチップ側端部３１ａとを通る第１直線Ｌ１に対して翼１３の回転方向Ｄ１と反対側に位置している。第２平坦面３３は、ハブ側端部３１ｂよりもハブ端１７側において、回転軸１２の軸中心１２ａとハブ側端部３１ｂとを通る第２直線Ｌ２に対して翼１３の回転方向Ｄ１と反対側に位置している。 The recess 30 is a curved portion 31 that is recessed and curved in an arc shape in the rotation direction D1 of the blade 13, and is flat from the tip side end portion 31a, which is the end portion of the curved portion 31 on the tip end 16 side, to the tip end 16. It includes a first flat surface 32 extending flat and a second flat surface 33 extending flat from the hub side end 31b, which is the end of the curved portion 31 on the hub end 17 side, to the hub end 17. The most recessed portion 31c of the curved portion 31 with respect to the first straight line L1 is located at the intermediate position P0 of the blade 13 in the blade height direction on the pressure surface 14. The first flat surface 32 is located on the chip end 16 side of the chip side end portion 31a, with respect to the rotation direction D1 of the blade 13 with respect to the first straight line L1 passing through the shaft center 12a of the rotating shaft 12 and the chip side end portion 31a. It is located on the other side. The second flat surface 33 is located on the hub end 17 side of the hub side end portion 31b, with respect to the rotation direction D1 of the blade 13 with respect to the second straight line L2 passing through the axis center 12a of the rotating shaft 12 and the hub side end portion 31b. It is located on the other side.

図３に示されるように、隣り合う２つの翼１３，１３間には、冷媒が流通する流路４０が形成されている。一方の翼１３の前縁１８と他方の翼１３の負圧面１５上の位置である第１位置Ｐ１とによって、流路４０の流路面積が最小となる入口スロート４１が形成される。一方の翼１３の圧力面１４上には、前縁１８からの軸方向距離ｄ２が負圧面１５上の前縁１８から第１位置Ｐ１までの軸方向距離ｄ１と同じになる第２位置Ｐ２が存在する。凹部３０（図３では凹部３０の湾曲部３１が図示されている）は、第２位置Ｐ２から翼１３の後縁１９まで延びている。 As shown in FIG. 3, a flow path 40 through which the refrigerant flows is formed between the two adjacent blades 13, 13. The front edge 18 of one blade 13 and the first position P1 located on the negative pressure surface 15 of the other blade 13 form an inlet throat 41 that minimizes the flow path area of the flow path 40. On the pressure surface 14 of one blade 13, there is a second position P2 in which the axial distance d2 from the front edge 18 is the same as the axial distance d1 from the front edge 18 to the first position P1 on the negative pressure surface 15. Exists. The recess 30 (the curved portion 31 of the recess 30 is shown in FIG. 3) extends from the second position P2 to the trailing edge 19 of the wing 13.

次に、本開示の実施形態１に係る二相流タービン１の動作について説明する。 Next, the operation of the two-phase flow turbine 1 according to the first embodiment of the present disclosure will be described.

図１に示されるように、冷凍回路を循環する液体の冷媒は、流入口２０ｂを介してノズル２０に流入し、流路２１を流通する。液体の冷媒が流入口２０ｂから流路２１を流入すると、位置２０ｃまで流路２１の流路面積が減少していくので、位置２０ｃまで流通する間に冷媒が加速される。逆に、位置２０ｃから噴出口２０ａまで流路２１の流路面積が増加していくので、位置２０ｃから噴出口２０ａまで流通する間に冷媒が減圧される。冷媒が減圧されて湿り域に達すると、冷媒の一部が気化し、急速に体積が増加する。冷媒は、位置２０ｃから噴出口２０ａまでの間に膨張し、噴出口２０ａでは圧力差のエネルギーが速度に変換されて、液相と気相とが混在する気液二相流となる。冷媒は、気液二相流としてノズル２０から動翼１０へ噴出される。 As shown in FIG. 1, the liquid refrigerant circulating in the refrigeration circuit flows into the nozzle 20 through the inflow port 20b and flows through the flow path 21. When the liquid refrigerant flows into the flow path 21 from the inflow port 20b, the flow path area of the flow path 21 decreases to the position 20c, so that the refrigerant is accelerated while flowing to the position 20c. On the contrary, since the flow path area of the flow path 21 increases from the position 20c to the spout 20a, the refrigerant is depressurized while flowing from the position 20c to the spout 20a. When the refrigerant is decompressed and reaches a damp area, a part of the refrigerant vaporizes and the volume increases rapidly. The refrigerant expands between the position 20c and the ejection port 20a, and at the ejection port 20a, the energy of the pressure difference is converted into a velocity, resulting in a gas-liquid two-phase flow in which a liquid phase and a gas phase are mixed. The refrigerant is ejected from the nozzle 20 to the rotor blade 10 as a gas-liquid two-phase flow.

ノズル２０から動翼１０へ噴出された冷媒の気液二相流が動翼１０の流路４０を流通する際に、気液二相流の速度エネルギーが翼１３に力を与え、その反力によって翼１３が回転方向Ｄ１に回転する。翼１３の回転とともにディスク１１が回転方向Ｄ１に回転し、これにより回転軸１２が回転方向Ｄに回転して、二相流タービン１から回転動力を得ることができる。 When the gas-liquid two-phase flow of the refrigerant ejected from the nozzle 20 to the moving blade 10 flows through the flow path 40 of the moving blade 10, the velocity energy of the gas-liquid two-phase flow gives a force to the blade 13 and its reaction force. The blade 13 rotates in the rotation direction D1. The disk 11 rotates in the rotation direction D1 with the rotation of the blade 13, whereby the rotation shaft 12 rotates in the rotation direction D, and rotational power can be obtained from the two-phase flow turbine 1.

図４に示されるように、気液二相流１００において、液相は様々な径の液滴となり、気相と分離されている。気相の流れ１０１は、流路４０において翼１３の形状に沿ったものとなる。液滴のうち極小さい径の液滴は、気相の流れ１０１に同伴される。しかし、多くの液滴は、液滴に対する気相の抵抗が小さいために、気相の流れ１０１のように翼１３の形状に沿うような転向をせず、気液二相流１００の方向のまま直線状に流路４０を流通し、前縁１８から第２位置Ｐ２までの間で翼１３の圧力面１４に衝突する。圧力面１４に衝突した液滴の多くは圧力面１４に付着し、表面張力によって相互に合体することで、圧力面１４上に液相の流れ１０２が形成される。液相は、圧力面１４に沿って流れた後、後縁１９を通り越して流路４０から流出する。 As shown in FIG. 4, in the gas-liquid two-phase flow 100, the liquid phase becomes droplets having various diameters and is separated from the gas phase. The gas phase flow 101 follows the shape of the blade 13 in the flow path 40. Of the droplets, the droplets having a very small diameter are accompanied by the gas phase flow 101. However, since many droplets have a small gas-phase resistance to the droplets, they do not rotate along the shape of the blade 13 like the gas-phase flow 101, and are in the direction of the gas-liquid two-phase flow 100. It flows through the flow path 40 in a straight line as it is, and collides with the pressure surface 14 of the blade 13 between the front edge 18 and the second position P2. Most of the droplets that collide with the pressure surface 14 adhere to the pressure surface 14 and coalesce with each other due to surface tension to form a liquid phase flow 102 on the pressure surface 14. The liquid phase flows along the pressure plane 14 and then flows out of the flow path 40 past the trailing edge 19.

圧力面１４に沿った液相の流れ１０２の圧力面１４に対する摩擦により、圧力面１４上に境界層が形成される。この境界層は、圧力面１４の近傍では翼１３の回転速度で回転する。この回転による遠心力が境界層に作用することで、境界層は、ハブ端１７からチップ端１６に向かう方向（翼高さの半径方向外向き）に移動するようになる。 The friction of the liquid phase flow 102 along the pressure surface 14 with respect to the pressure surface 14 forms a boundary layer on the pressure surface 14. This boundary layer rotates at the rotational speed of the blade 13 in the vicinity of the pressure surface 14. The centrifugal force due to this rotation acts on the boundary layer, so that the boundary layer moves in the direction from the hub end 17 to the chip end 16 (outward in the radial direction of the blade height).

ここで、図５に示されるように、翼１３の圧力面１４に、第２位置Ｐ２から後縁１９に向かって順次互いに間隔をあけて第３位置Ｐ３及び第４位置Ｐ４を定義し、圧力面１４に凹部３０が形成されていない場合の圧力面１４に沿った液相の流れを１０２’とする。第２位置Ｐ２における境界層の厚さはまだ薄いため、遠心力によってハブ端１７からチップ端１６に向かう方向の液相の流れは少ない。流路４０に流入する気液二相流１００は、チップ端１６からハブ端１７に向かう方向（翼高さの半径方向内向き）の速度成分を有しているので、第２位置Ｐ２において圧力面１４に沿った液相の流れ１０２’は、チップ端１６からハブ端１７に向かう方向の速度成分を有している。このため、第２位置Ｐ２から第３位置Ｐ３までの液相の流れ１０２’は、翼１３の翼高さ方向では、チップ端１６からハブ端１７に向かう方向の流れとなる。 Here, as shown in FIG. 5, a third position P3 and a fourth position P4 are defined on the pressure surface 14 of the blade 13 at intervals from the second position P2 toward the trailing edge 19, and the pressure is increased. The flow of the liquid phase along the pressure surface 14 when the recess 30 is not formed on the surface 14 is 102'. Since the thickness of the boundary layer at the second position P2 is still thin, the flow of the liquid phase in the direction from the hub end 17 to the chip end 16 is small due to centrifugal force. Since the gas-liquid two-phase flow 100 flowing into the flow path 40 has a velocity component in the direction from the tip end 16 to the hub end 17 (inward in the radial direction of the blade height), the pressure at the second position P2. The liquid phase flow 102'along the surface 14 has a velocity component in the direction from the tip end 16 to the hub end 17. Therefore, the flow of the liquid phase 102'from the second position P2 to the third position P3 is a flow in the direction from the tip end 16 to the hub end 17 in the blade height direction of the blade 13.

液相の流れ１０２’が第２位置Ｐ２、第３位置Ｐ３、第４位置Ｐ４と進むに従い、次第に境界層の厚さが厚くなっていくので、遠心力が作用する液相の量が多くなる。そうすると、例えば第３位置Ｐ３付近で、翼１３の翼高さ方向の液相の流れ１０２’が逆転し、ハブ端１７からチップ端１６に向かう方向の流れとなる。すなわち、圧力面１４に沿った液相の流れ１０２’は、第２位置Ｐ２から後縁１９までの間で、翼１３の翼高さ方向に最初はチップ端１６からハブ端１７に向かう方向の流れであるのに対し、途中で方向が逆転し、ハブ端１７からチップ端１６に向かう方向の流れとなる。 As the flow 102'of the liquid phase progresses to the second position P2, the third position P3, and the fourth position P4, the thickness of the boundary layer gradually increases, so that the amount of the liquid phase on which the centrifugal force acts increases. .. Then, for example, in the vicinity of the third position P3, the flow of the liquid phase 102'in the blade height direction of the blade 13 is reversed, and the flow is in the direction from the hub end 17 to the chip end 16. That is, the flow of the liquid phase 102'along the pressure surface 14 is in the direction from the second position P2 to the trailing edge 19 in the blade height direction of the blade 13 and initially from the tip end 16 to the hub end 17. In contrast to the flow, the direction is reversed in the middle, and the flow is in the direction from the hub end 17 to the chip end 16.

圧力面１４に沿った液相の流れ１０２’にこのような翼高さ方向の流れ成分が含まれ、境界層が翼高さ方向に移動すると、翼１３から境界層に与えられる動力が大きくなる、すなわち、気液二相流１００から翼１３に与えられる動力が減少することになるので、ポンプ作用による損失が発生してしまう。しかしながら、図２に示されるように、この実施形態１に係る翼１３には、その圧力面１４に、第２位置Ｐ２から後縁１９（図３又は４参照）まで延びる凹部３０が形成されている。圧力面１４に凹部３０が形成されていると、液相は主に凹部３０の湾曲部３１に沿って流れるようになる。遠心力の作用によって湾曲部３１からチップ端１６に液相の一部が移動しようとすると、湾曲部３１よりチップ端１６側に位置する第１平坦面３２は、回転軸１２の軸中心１２ａとチップ側端部３１ａとを通る第２直線Ｌ２に対して翼１３の回転方向Ｄ１と反対側に位置するような傾きを有しているので、湾曲部３１からチップ端１６への液相の移動を抑制する。 When the flow component of the liquid phase 102'along the pressure surface 14 contains such a flow component in the blade height direction and the boundary layer moves in the blade height direction, the power given from the blade 13 to the boundary layer increases. That is, since the power given to the blade 13 from the gas-liquid two-phase flow 100 is reduced, a loss due to the pumping action occurs. However, as shown in FIG. 2, the wing 13 according to the first embodiment is formed with a recess 30 extending from the second position P2 to the trailing edge 19 (see FIG. 3 or 4) on the pressure surface 14. There is. When the recess 30 is formed on the pressure surface 14, the liquid phase flows mainly along the curved portion 31 of the recess 30. When a part of the liquid phase tries to move from the curved portion 31 to the tip end 16 by the action of centrifugal force, the first flat surface 32 located on the chip end 16 side of the curved portion 31 becomes the axis center 12a of the rotating shaft 12. Since it has an inclination so as to be located on the side opposite to the rotation direction D1 of the blade 13 with respect to the second straight line L2 passing through the tip side end portion 31a, the liquid phase moves from the curved portion 31 to the tip end 16. Suppress.

そうすると、圧力面１４に凹部３０が形成されている場合の圧力面１４に沿った液相の流れ１０２は、凹部３０に沿った流れとなる。凹部３０に沿って流れる液相の境界層は、遠心力が作用しても、凹部３０の第１平坦面３２によって翼高さ方向にチップ端１６へ向かう移動が抑制されるので、ポンプ作用による損失が抑制されて、二相流タービン１の効率を向上することができる。また、液相は主に、曲率の大きい湾曲部３１に沿って圧力面１４を後縁１９に向かって流れるようになるので、曲率の小さい面に沿って液相が流れる場合に比べて、液相が圧力面１４に接する濡れ縁長さ（液相が圧力面１４に接する部分の翼高さ方向の長さ）が短くなり、圧力面１４に対する液相の抵抗が小さくなる。さらに、図５に示されるように、液相の流れ１０２は、凹部３０が圧力面１４に形成されていない場合の液相の流れ１０２’に比べて、翼高さ方向の移動距離が短い流れとなるので、圧力面１４に対する液相の抵抗が小さくなる。その結果、二相流タービン１（図１参照）の効率を向上することができる。 Then, the flow 102 of the liquid phase along the pressure surface 14 when the recess 30 is formed on the pressure surface 14 becomes a flow along the recess 30. Even if centrifugal force acts on the boundary layer of the liquid phase flowing along the recess 30, the first flat surface 32 of the recess 30 suppresses the movement toward the tip end 16 in the blade height direction, so that the pumping action is used. The loss is suppressed and the efficiency of the two-phase flow turbine 1 can be improved. Further, since the liquid phase mainly flows on the pressure surface 14 toward the trailing edge 19 along the curved portion 31 having a large curvature, the liquid phase flows along the surface having a small curvature as compared with the case where the liquid phase flows. The length of the wet edge at which the phase contacts the pressure surface 14 (the length of the portion where the liquid phase contacts the pressure surface 14 in the blade height direction) becomes short, and the resistance of the liquid phase to the pressure surface 14 decreases. Further, as shown in FIG. 5, the flow of the liquid phase 102 has a shorter movement distance in the blade height direction than the flow of the liquid phase 102'when the recess 30 is not formed on the pressure surface 14. Therefore, the resistance of the liquid phase to the pressure surface 14 becomes small. As a result, the efficiency of the two-phase flow turbine 1 (see FIG. 1) can be improved.

尚、この実施形態１では、図２に示されるように、湾曲部３１よりハブ端１７側に位置する第２平坦面３３も、回転軸１２の軸中心１２ａとハブ側端部３１ｂとを通る第２直線Ｌ２に対して翼１３の回転方向Ｄ１と反対側に位置するような傾きを有している。そうすると、図５に示されるように、第２位置Ｐ２から第３位置Ｐ３までの間では、液相はチップ端１６からハブ端１７に向かう方向の流れとなるが、このような液相の移動を第２平坦面３３が抑制するので、液相がさらに、湾曲部３１に沿って圧力面１４を後縁１９に向かって流れやすくなり、圧力面１４に対する液相の抵抗がさらに小さくなる。その結果、二相流タービン１（図１参照）の効率をさらに向上することができる。 In the first embodiment, as shown in FIG. 2, the second flat surface 33 located on the hub end 17 side of the curved portion 31 also passes through the shaft center 12a and the hub side end portion 31b of the rotating shaft 12. It has an inclination so as to be located on the side opposite to the rotation direction D1 of the blade 13 with respect to the second straight line L2. Then, as shown in FIG. 5, between the second position P2 and the third position P3, the liquid phase flows in the direction from the chip end 16 to the hub end 17, and such movement of the liquid phase Is suppressed by the second flat surface 33, so that the liquid phase is more likely to flow along the curved portion 31 toward the trailing edge 19, and the resistance of the liquid phase to the pressure surface 14 is further reduced. As a result, the efficiency of the two-phase flow turbine 1 (see FIG. 1) can be further improved.

実施形態１では、図３に示されるように、凹部３０は、第２位置Ｐ２から後縁１９まで延びるように圧力面１４に形成されているが、この形態に限定するものではない。凹部３０の上流端３１ｄ（図５参照）が第２位置Ｐ２よりも前縁１８側の位置にあってもよいし、凹部３０の上流端３１ｄが前縁１８にあってもよい。気液二相流中の液滴の多くは前縁１８から第２位置Ｐ２までの間で翼１３の圧力面１４に衝突するので、多くの液滴が凹部３０に沿って流れるように、凹部３０の上流端３１ｄは、第２位置Ｐ２又は第２位置Ｐ２よりも前縁１８側にあることが好ましい。また、凹部３０は必ずしも後縁１９まで延びていることに限定するものではなく、凹部３０の下流端３１ｅ（図５参照）が後縁１９よりも前縁１８側に位置していてもよい。すなわち、凹部３０は、前縁１８及び後縁１９間を少なくとも部分的に延びていればよい。 In the first embodiment, as shown in FIG. 3, the recess 30 is formed on the pressure surface 14 so as to extend from the second position P2 to the trailing edge 19, but is not limited to this embodiment. The upstream end 31d of the recess 30 (see FIG. 5) may be located on the front edge 18 side of the second position P2, or the upstream end 31d of the recess 30 may be located on the front edge 18. Most of the droplets in the gas-liquid two-phase flow collide with the pressure surface 14 of the blade 13 between the front edge 18 and the second position P2, so that many droplets flow along the recess 30. The upstream end 31d of 30 is preferably on the front edge 18 side of the second position P2 or the second position P2. Further, the recess 30 is not necessarily limited to extending to the trailing edge 19, and the downstream end 31e (see FIG. 5) of the recess 30 may be located closer to the front edge 18 than the trailing edge 19. That is, the recess 30 may extend at least partially between the front edge 18 and the trailing edge 19.

実施形態１では、図２に示されるように、湾曲部３１のうち翼１３の回転方向Ｄ１に向かって最も凹んだ部分３１ｃは、圧力面１４において翼１３の翼高さ方向中間位置Ｐ０に位置しているが、この形態に限定するものではない。図６に示されるように、最も凹んだ部分３１ｃが、翼高さ方向中間位置Ｐ０とチップ端１６との間に位置していてもよい。この構成によると、圧力面１４に達して湾曲部３１に入り込む前に遠心力の作用によって翼高さ方向のチップ端１６側に移動してしまった液相も、湾曲部３１に入り込んで湾曲部３１に沿って流れることができるようになるので、ポンプ作用による損失が抑制されるとともに圧力面１４に対する液相の抵抗が小さくり、二相流タービン１の効率を向上することができる。 In the first embodiment, as shown in FIG. 2, the most recessed portion 31c of the curved portion 31 toward the rotation direction D1 of the blade 13 is located at the intermediate position P0 of the blade 13 in the blade height direction on the pressure surface 14. However, it is not limited to this form. As shown in FIG. 6, the most recessed portion 31c may be located between the blade height direction intermediate position P0 and the tip end 16. According to this configuration, the liquid phase that has moved to the tip end 16 side in the blade height direction due to the action of centrifugal force before reaching the pressure surface 14 and entering the curved portion 31 also enters the curved portion 31 and enters the curved portion 31. Since it becomes possible to flow along 31, the loss due to the pumping action is suppressed, the resistance of the liquid phase to the pressure surface 14 is reduced, and the efficiency of the two-phase flow turbine 1 can be improved.

実施形態１では、図２に示されるように、湾曲部３１は同一の曲率を有する円弧状であったが、湾曲部３１が翼の翼高さ方向に曲率の分布を有してもよい。この場合、曲率が最大の部分が翼１３の翼高さ方向中間位置Ｐ０に位置していることが好ましい。この構成によると、流路４０を流通する液相は、湾曲部３１のうち曲率が最大の部分に沿って圧力面１４を後縁１９に向かって流れやすくなり、液相が圧力面１４に接する濡れ縁長さをより短くできるので、圧力面１４に対する液相の抵抗が小さくなり、二相流タービン１の効率を向上することができる。尚、曲率が最大の部分は厳密に翼高さ方向中間位置Ｐ０に位置していなくても、ハブ端１７からチップ端１６に向かって翼高さの３０％の位置から８０％の位置の範囲にあれば、曲率が最大の部分が翼高さ方向中間位置Ｐ０に位置する場合とほぼ同等の効果を得ることができる。 In the first embodiment, as shown in FIG. 2, the curved portion 31 has an arc shape having the same curvature, but the curved portion 31 may have a distribution of curvature in the blade height direction of the blade. In this case, it is preferable that the portion having the maximum curvature is located at the intermediate position P0 in the blade height direction of the blade 13. According to this configuration, the liquid phase flowing through the flow path 40 easily flows along the pressure surface 14 toward the trailing edge 19 along the portion of the curved portion 31 having the maximum curvature, and the liquid phase comes into contact with the pressure surface 14. Since the wet edge length can be made shorter, the resistance of the liquid phase to the pressure surface 14 becomes smaller, and the efficiency of the two-phase flow turbine 1 can be improved. Even if the portion having the maximum curvature is not strictly located at the intermediate position P0 in the blade height direction, the position range from 30% to 80% of the blade height from the hub end 17 to the chip end 16. If this is the case, the same effect as when the portion having the maximum curvature is located at the intermediate position P0 in the blade height direction can be obtained.

実施形態１では、図２に示されるように、チップ側端部３１ａからチップ端１６までの部分は平坦に延びる第１平坦面３２であり、ハブ側端部３１ｂからハブ端１７までの部分は平坦に延びる第２平坦面３３であったが、この形態に限定するものではない。第１平坦面３２及び第２平坦面３３の両方又は一方が平坦ではなく、湾曲していてもよい。これらの部分がどのような形態であっても、第１直線Ｌ１又は第２直線Ｌ２に対して翼１３の回転方向Ｄ１と反対側に位置していれば、液相の翼高さ方向の移動を抑制することができる。ただし、チップ側端部３１ａからチップ端１６までの部分と、ハブ側端部３１ｂからハブ端１７までの部分とを平坦にすることにより、凹部３０の構成が簡単になるので、凹部３０の形成作業を簡素化することができる。また、凹部３０は、圧力面１４に対して窪んだ複数の溝が翼高さ方向に連続して並ぶようにして構成されてもよい。 In the first embodiment, as shown in FIG. 2, the portion from the chip side end portion 31a to the chip end 16 is a first flat surface 32 extending flatly, and the portion from the hub side end portion 31b to the hub end 17 is The second flat surface 33 extends flat, but the present invention is not limited to this form. Both or one of the first flat surface 32 and the second flat surface 33 may not be flat but may be curved. Regardless of the form of these parts, if they are located on the side opposite to the rotation direction D1 of the blade 13 with respect to the first straight line L1 or the second straight line L2, the liquid phase moves in the blade height direction. Can be suppressed. However, by flattening the portion from the chip side end portion 31a to the chip end 16 and the portion from the hub side end portion 31b to the hub end 17, the configuration of the recess 30 is simplified, so that the recess 30 is formed. The work can be simplified. Further, the recess 30 may be configured such that a plurality of grooves recessed with respect to the pressure surface 14 are continuously arranged in the blade height direction.

尚、第２平坦面３３は、上述したように、第２位置Ｐ２から第３位置Ｐ３までの間でチップ端１６からハブ端１７に向かう液相の移動を抑制するものであるが、液相にはハブ端１７からチップ端１６に向かう方向の遠心力が作用し、いずれは遠心力が作用する方向に液相は方向転換するので、必ずしも第２平坦面３３が液相のこのような移動を抑制する必要はない。このため、第２平坦面３３は、第３直線Ｌ３上に位置してもよい。 As described above, the second flat surface 33 suppresses the movement of the liquid phase from the chip end 16 to the hub end 17 between the second position P2 and the third position P3, but the liquid phase A centrifugal force acts in the direction from the hub end 17 to the chip end 16, and the liquid phase eventually changes direction in the direction in which the centrifugal force acts. Therefore, the second flat surface 33 does not necessarily move in this way. There is no need to suppress. Therefore, the second flat surface 33 may be located on the third straight line L3.

翼１３のその他の変形例として、図７に示されるように、凹部３０が湾曲部３１のみから構成されていてもよい。また、負圧面１５は、翼１３の回転方向Ｄ１に向かって凸状に湾曲していなくてもよい。さらに、図８に示されるように、凹部３０の断面形状が放物線形状となっており、翼１３の翼高さ方向における凹部３０の両端３０ａ，３０ｂが、隣の翼１３’の負圧面１５’に近接するようになっていてもよい。 As another modification of the wing 13, as shown in FIG. 7, the recess 30 may be composed of only the curved portion 31. Further, the negative pressure surface 15 does not have to be curved convexly toward the rotation direction D1 of the blade 13. Further, as shown in FIG. 8, the cross-sectional shape of the recess 30 is a parabolic shape, and both ends 30a and 30b of the recess 30 in the blade height direction of the blade 13 are negative pressure surfaces 15'of the adjacent blade 13'. It may be close to.

（実施形態２）
次に、実施形態２に係る二相流タービンの動翼について説明する。実施形態２に係る二相流タービンの動翼は、実施形態１に対して、湾曲部３１のうち翼１３の回転方向Ｄ１に向かって最も凹んだ部分３１ｃを、前縁１８から後縁１９にかけて、回転軸１２の軸中心１２ａから最も凹んだ部分３１ｃまでの距離が変化するように構成したものである。尚、実施形態２において、実施形態１の構成要件と同じものは同じ参照符号を付し、その詳細な説明は省略する。 (Embodiment 2)
Next, the moving blades of the two-phase flow turbine according to the second embodiment will be described. In the moving blade of the two-phase flow turbine according to the second embodiment, with respect to the first embodiment, the most recessed portion 31c of the curved portion 31 toward the rotation direction D1 of the blade 13 is extended from the front edge 18 to the trailing edge 19. , The distance from the axis center 12a of the rotating shaft 12 to the most recessed portion 31c is configured to change. In the second embodiment, the same components as those of the first embodiment are designated by the same reference numerals, and detailed description thereof will be omitted.

図９は、動翼１０を回転軸１２の軸方向に見た図を示している。ただし、図９においてディスク１１の外周面に設けられるように描かれた３つの翼１３は、１つの同じ翼１３が回転方向Ｄ１に回転している最中の異なる３つの位置Ａ〜Ｃを示している。すなわち、１つの同じ翼１３が回転方向Ｄ１に回転する間、位置Ａから位置Ｂに移動し、位置Ｂから位置Ｃに順次移動することを示している。位置Ａにおける翼１３は、翼１３の入口、具体的には、凹部３０の湾曲部３１の上流端３１ｄ（図５参照）すなわち第２位置Ｐ２（図３参照）における断面形状として描かれており、位置Ｃにおける翼１３は、翼１３の出口、具体的には、湾曲部３１の下流端３１ｅ（図５参照）すなわち翼１３の後縁１９（図３参照）に面するように翼１３を見た形状として描かれており、位置Ｂにおける翼１３は、湾曲部３１の上流端３１ｄ及び下流端３１ｅ間の中間部における断面形状として描かれている。 FIG. 9 shows a view of the moving blade 10 in the axial direction of the rotating shaft 12. However, the three blades 13 drawn so as to be provided on the outer peripheral surface of the disk 11 in FIG. 9 indicate three different positions A to C while one same blade 13 is rotating in the rotation direction D1. ing. That is, it is shown that while one and the same blade 13 rotates in the rotation direction D1, it moves from the position A to the position B and sequentially moves from the position B to the position C. The wing 13 at position A is depicted as a cross-sectional shape at the inlet of wing 13, specifically, the upstream end 31d (see FIG. 5) of the curved portion 31 of the recess 30, that is, the second position P2 (see FIG. 3). The wing 13 at position C faces the exit of the wing 13, specifically, the downstream end 31e of the curved portion 31 (see FIG. 5), that is, the trailing edge 19 of the wing 13 (see FIG. 3). The wing 13 at position B is depicted as a cross-sectional shape at the intermediate portion between the upstream end 31d and the downstream end 31e of the curved portion 31.

位置Ａ、Ｂ及びＣそれぞれにおいて、翼１３の圧力面１４に形成された凹部３０の湾曲部３１の最も凹んだ部分３１ｃから回転軸１２の軸中心１２ａまでの距離をそれぞれＲ１、Ｒ２及びＲ３とすると、Ｒ２＜Ｒ３＜Ｒ１となっている。その他の構成は実施形態１と同じである。 At positions A, B, and C, the distances from the most recessed portion 31c of the curved portion 31 of the recess 30 formed on the pressure surface 14 of the blade 13 to the axis center 12a of the rotating shaft 12 are defined as R1, R2, and R3, respectively. Then, R2 <R3 <R1. Other configurations are the same as those in the first embodiment.

次に、本開示の実施形態２に係る二相流タービン１の動作を図１０に基づいて説明する。尚、実施形態１の動作と実施形態２の動作とでは、動翼１０における気液二相流の流れのみが異なるため、以下の説明では、動翼１０における気液二相流の流れについてのみ説明する。 Next, the operation of the two-phase flow turbine 1 according to the second embodiment of the present disclosure will be described with reference to FIG. Since only the flow of the gas-liquid two-phase flow in the moving blade 10 is different between the operation of the first embodiment and the operation of the second embodiment, the following description describes only the flow of the gas-liquid two-phase flow in the moving blade 10. explain.

ノズル２０から動翼１０に流入する気液二相流１００の面の形状は、ノズル２０の断面形状や、ノズル２０の長さ方向と回転軸１２との交差角等に依存するが、回転軸１２の軸中心１２ａを通り気液二相流１００に垂直な直線である第３直線Ｌ３の長さ方向に最大となる長さを直径とする円（代表円２００）として説明する。 The shape of the surface of the gas-liquid two-phase flow 100 flowing from the nozzle 20 into the moving blade 10 depends on the cross-sectional shape of the nozzle 20, the intersection angle between the length direction of the nozzle 20 and the rotating shaft 12, and the like. A circle (representative circle 200) having a diameter that is maximum in the length direction of the third straight line L3, which is a straight line passing through the axis center 12a of 12 and perpendicular to the gas-liquid two-phase flow 100, will be described.

気液二相流１００が動翼１０を流通する間、翼１３の各位置Ａ〜Ｃにおいて代表円２００を描くことができ、各位置Ａ〜Ｃにおける代表円２００を連ねることで、気液二相流１００中の液相の流れを代表する長円２０１（液相の移動軌跡の長円）を描くことができる。この長円２０１の左端の位置は、気液二相流１００が湾曲部３１の上流端３１ｄ（図５参照）に位置していることを表し、長円２０１の右端の位置は、気液二相流１００が湾曲部３１の下流端３１ｅ（図５参照）に位置していることを表している。したがって、この長円２０１は、翼１３のチップ端１６及びハブ端１７間に位置する必要がある。すなわち、翼１３の翼高さは、長円２０１の直径よりも大きい必要がある。 While the gas-liquid two-phase flow 100 flows through the moving blade 10, a representative circle 200 can be drawn at each position A to C of the blade 13, and the representative circle 200 at each position A to C can be connected to form the gas-liquid two. An ellipse 201 (an ellipse of the movement locus of the liquid phase) representing the flow of the liquid phase in the phase flow 100 can be drawn. The position of the left end of the oval 201 indicates that the gas-liquid two-phase flow 100 is located at the upstream end 31d (see FIG. 5) of the curved portion 31, and the position of the right end of the oval 201 is the position of the gas-liquid two. It indicates that the phase flow 100 is located at the downstream end 31e (see FIG. 5) of the curved portion 31. Therefore, the oval 201 needs to be located between the tip end 16 and the hub end 17 of the blade 13. That is, the blade height of the blade 13 needs to be larger than the diameter of the oval 201.

この実施形態２では、気液二相流１００が中間部にあるとき（位置Ｂ）の気液二相流１００（代表円２００の中心）から第３直線Ｌ３までの距離をＹ１とし、気液二相流１００が下流端３１ｅにあるときの気液二相流１００から第３直線Ｌ３までの距離をＹ２とすると、Ｙ１＜Ｙ２となっている。この条件は、ノズル２０を動翼１０に対して適切な位置に配置することで実現可能であり、Ｙ１＞Ｙ２やＹ１＝Ｙ２とすることも可能である。 In the second embodiment, the distance from the gas-liquid two-phase flow 100 (center of the representative circle 200) to the third straight line L3 when the gas-liquid two-phase flow 100 is in the middle portion (position B) is Y1, and the gas-liquid Assuming that the distance from the gas-liquid two-phase flow 100 to the third straight line L3 when the two-phase flow 100 is at the downstream end 31e is Y2, Y1 <Y2. This condition can be realized by arranging the nozzle 20 at an appropriate position with respect to the moving blade 10, and it is also possible to set Y1> Y2 or Y1 = Y2.

このようなノズル２０の配置の下で、この実施形態２では、湾曲部３１が上述のＲ２＜Ｒ３＜Ｒ１の条件を満たすことにより、長円２０１は、ノズル２０から流出した気液二相流１００の方向に沿って代表円２００の中心が移動するような形状となる。すなわち、動翼１０における気液二相流１００中の液相の流れは、代表円２００の中心が描く直線となる。実施形態１において、圧力面１４において液相は翼高さ方向において、最初はハブ端１７に向かう流れとなり、その後に向きを変えてチップ端１６に向かう流れとなることを説明したが、実施形態２における湾曲部３１の上述した条件により、液相のハブ端１７に向かう流れ及びチップ端１６に向かう流れが確実に抑制されるので、動翼１０における気液二相流１００中の液相の流れは、代表円２００が描く軌跡（長円２０１はその一部）となる。 Under such an arrangement of the nozzle 20, in the second embodiment, the curved portion 31 satisfies the above-mentioned condition of R2 <R3 <R1, so that the oval 201 has a gas-liquid two-phase flow flowing out from the nozzle 20. The shape is such that the center of the representative circle 200 moves along the direction of 100. That is, the flow of the liquid phase in the gas-liquid two-phase flow 100 in the moving blade 10 is a straight line drawn by the center of the representative circle 200. In the first embodiment, it has been described that the liquid phase at the pressure surface 14 first flows toward the hub end 17 in the blade height direction, and then changes direction and flows toward the chip end 16. Due to the above-mentioned conditions of the curved portion 31 in No. 2, the flow of the liquid phase toward the hub end 17 and the flow toward the tip end 16 are surely suppressed, so that the liquid phase in the gas-liquid two-phase flow 100 in the rotor blade 10 is suppressed. The flow becomes a locus drawn by the representative circle 200 (the oval 201 is a part thereof).

図１０のように、翼１３の前縁１８（図３参照）から後縁１９（図３参照）にかけて、厳密に言えば、湾曲部３１の上流端３１ｄ（図５参照）から下流端３１ｅ（図５参照）にかけて流れる液相を回転軸１２に垂直な平面に投影した場合に、前縁１８から第２位置Ｐ２（図３参照）までの間で圧力面１４に到達した液相が、チップ側端部３１ａ（図２参照）からチップ端１６までの面（例えば第１平坦面３２（図２参照））からも、ハブ側端部３１ｂ（図２参照）からハブ端１７までの面（例えば第２平坦面３３（図２参照））からも、湾曲部３１（図２参照）に向かって移動して湾曲部３１において合流して湾曲部３１を後縁１９に向かって流れるので、液相の流れが直線状になる。ノズル２０から動翼１０に流入した気液二相流１００が動翼１０内で直線状となることが理想的であり、上記の構成によって液相の流れを直線状にすることができる。その結果、遠心力による翼高さ方向の移動に伴うポンプ作用を抑制でき、液相が圧力面１４に接する濡れ縁長さも短くなり、圧力面１４に対する液相の抵抗が小さくなるので、ポンプ作用による損失が抑制されるとともに圧力面１４に対する液相の抵抗が小さくり、二相流タービン１の効率を向上することができる。 As shown in FIG. 10, from the front edge 18 (see FIG. 3) to the trailing edge 19 (see FIG. 3) of the blade 13, strictly speaking, from the upstream end 31d (see FIG. 5) to the downstream end 31e (see FIG. 5) of the curved portion 31. When the liquid phase flowing over (see FIG. 5) is projected onto a plane perpendicular to the rotation axis 12, the liquid phase that reaches the pressure plane 14 between the front edge 18 and the second position P2 (see FIG. 3) is the chip. From the surface from the side end 31a (see FIG. 2) to the chip end 16 (for example, the first flat surface 32 (see FIG. 2)), the surface from the hub side end 31b (see FIG. 2) to the hub end 17 (see FIG. 2). For example, from the second flat surface 33 (see FIG. 2)), the liquid moves toward the curved portion 31 (see FIG. 2), merges at the curved portion 31, and flows through the curved portion 31 toward the trailing edge 19. The flow of the phase becomes linear. Ideally, the gas-liquid two-phase flow 100 flowing from the nozzle 20 into the rotor blade 10 is linear in the rotor blade 10, and the liquid phase flow can be linearized by the above configuration. As a result, the pumping action due to the movement in the blade height direction due to the centrifugal force can be suppressed, the length of the wet edge in which the liquid phase contacts the pressure surface 14 is shortened, and the resistance of the liquid phase to the pressure surface 14 is reduced. The loss is suppressed and the resistance of the liquid phase to the pressure surface 14 is reduced, so that the efficiency of the two-phase flow turbine 1 can be improved.

実施形態２では、Ｙ１＜Ｙ２かつＲ２＜Ｒ３＜Ｒ１であったが、Ｒ２＜Ｒ３とすると、気液二相流１００が直線状に移動したとしても、中間部から下流端３１ｅまでの間に、回転軸１２の軸中心１２ａから気液二相流１００までの距離の増加に伴うポンプ作用が生じるので、動翼１０に対するノズル２０の位置を調整してＹ１＞Ｙ２とし、湾曲部３１の構成をＲ３＜Ｒ２＜Ｒ１とすることが好ましい。 In the second embodiment, Y1 <Y2 and R2 <R3 <R1. However, when R2 <R3, even if the gas-liquid two-phase flow 100 moves linearly, it is between the intermediate portion and the downstream end 31e. Since a pumping action occurs as the distance from the axis center 12a of the rotating shaft 12 to the gas-liquid two-phase flow 100 increases, the position of the nozzle 20 with respect to the moving blade 10 is adjusted so that Y1> Y2, and the curved portion 31 is configured. Is preferably R3 <R2 <R1.

（実施形態３）
次に、実施形態３に係る二相流タービンの動翼について説明する。実施形態３に係る二相流タービンの動翼は、実施形態１又は２に対して、凹部３０の下流端３１ｅの構成を変更したものである。以下では、実施形態１の構成に対して凹部３０の下流端３１ｅの構成を変更した構成で実施形態３を説明するが、実施形態２の構成に対して凹部３０の下流端３１ｅの構成を変更した構成で実施形態３を構成してもよい。尚、実施形態３において、実施形態１の構成要件と同じものは同じ参照符号を付し、その詳細な説明は省略する。 (Embodiment 3)
Next, the moving blades of the two-phase flow turbine according to the third embodiment will be described. The rotor blade of the two-phase flow turbine according to the third embodiment is a modification of the configuration of the downstream end 31e of the recess 30 with respect to the first or second embodiment. In the following, the third embodiment will be described in which the configuration of the downstream end 31e of the recess 30 is changed from the configuration of the first embodiment, but the configuration of the downstream end 31e of the recess 30 is changed from the configuration of the second embodiment. The third embodiment may be configured with the above configuration. In the third embodiment, the same components as those of the first embodiment are designated by the same reference numerals, and detailed description thereof will be omitted.

図１１に示されるように、湾曲部３１は、下流端３１ｅ近傍で下流端３１ｅに向かって凹みの深さが深くなるように構成されている。これにより、湾曲部３１の下流端３１ｅは、凹部３０の湾曲部３１以外の部分の下流端３０ｅよりも翼１３の前縁１８側に位置している。その他の構成は実施形態１と同じである。 As shown in FIG. 11, the curved portion 31 is configured such that the depth of the recess becomes deeper toward the downstream end 31e in the vicinity of the downstream end 31e. As a result, the downstream end 31e of the curved portion 31 is located closer to the front edge 18 of the blade 13 than the downstream end 30e of the portion of the recess 30 other than the curved portion 31. Other configurations are the same as those in the first embodiment.

次に、本開示の実施形態３に係る二相流タービン１の動作を図１２に基づいて説明する。尚、実施形態１の動作と実施形態３の動作とでは、圧力面１４に沿った液相の流れのみが異なるため、以下の説明では、圧力面１４に沿った液相の流れについてのみ説明する。 Next, the operation of the two-phase flow turbine 1 according to the third embodiment of the present disclosure will be described with reference to FIG. Since only the flow of the liquid phase along the pressure surface 14 differs between the operation of the first embodiment and the operation of the third embodiment, only the flow of the liquid phase along the pressure surface 14 will be described in the following description. ..

実施形態１と同様に、気液二相流１００は気相と液相とに分離して、気相の流れ１０１は翼１３の形状に沿ったものとなる一方、液相の流れ１０２は主に凹部３０の湾曲部３１に沿ったものとなる。実施形態３では、湾曲部３１の下流端３１ｅは、凹部３０の湾曲部３１以外の部分の下流端３０ｅよりも翼１３の前縁１８側に位置しているので、湾曲部３１に沿って流れる液相は、湾曲部３１以外の部分に沿って流れる液相よりも翼１３の前縁１８側で流路４０から流出することになる。すなわち、湾曲部３１を流れる液相の翼１３の長さ方向の流通距離が実施形態１と比べて短くなるので、圧力面１４に対する液相の抵抗が小さくなる。その結果、二相流タービン１（図１参照）の効率をさらに向上することができる。 Similar to the first embodiment, the gas-liquid two-phase flow 100 is separated into a gas phase and a liquid phase, and the gas phase flow 101 follows the shape of the blade 13, while the liquid phase flow 102 is the main. It is along the curved portion 31 of the recess 30. In the third embodiment, the downstream end 31e of the curved portion 31 is located on the front edge 18 side of the blade 13 with respect to the downstream end 30e of the portion other than the curved portion 31 of the concave portion 30, and therefore flows along the curved portion 31. The liquid phase flows out from the flow path 40 on the front edge 18 side of the blade 13 with respect to the liquid phase flowing along the portion other than the curved portion 31. That is, since the flow distance of the liquid phase flowing through the curved portion 31 in the length direction of the blade 13 is shorter than that of the first embodiment, the resistance of the liquid phase to the pressure surface 14 is reduced. As a result, the efficiency of the two-phase flow turbine 1 (see FIG. 1) can be further improved.

実施形態１〜３では、冷凍機の冷凍サイクルにおいて膨張弁の代わりとして設けられる衝動式タービンを例にして二相流タービン１を説明してきたが、これに限定するものではない。二相流タービン１は、有機ランキンサイクル用のタービンや地熱用等の蒸気タービン等であってもよく、各種プラントの高圧液体又は気液二相流体から低圧に流れを膨張させて動力を得るタービンであれば、用途に限定はない。 In the first to third embodiments, the two-phase flow turbine 1 has been described by taking as an example an impulse turbine provided in place of the expansion valve in the refrigeration cycle of the refrigerator, but the present invention is not limited to this. The two-phase flow turbine 1 may be a turbine for an organic Rankine cycle, a steam turbine for geothermal use, or the like, and is a turbine that obtains power by expanding the flow from a high-pressure liquid or a gas-liquid two-phase fluid of various plants to a low pressure. If so, the application is not limited.

実施形態１〜３では、厳密な定義なく「二相流」という用語を使用していたが、本開示における二相流は、１種類の物質が液相及び気相の二相になっているものに限定されるものではなく、例えば水の中に空気中の成分等が溶け込んでいる場合のような複数の液体及び気体から構成される物質であって、ある条件で気相の状態と液相の状態とが平衡している流れを意味する。 In the first to third embodiments, the term "two-phase flow" has been used without a strict definition, but in the two-phase flow in the present disclosure, one kind of substance has two phases, a liquid phase and a gas phase. It is not limited to a substance, but is a substance composed of a plurality of liquids and gases such as when a component in the air is dissolved in water, and the gas phase state and the liquid under certain conditions. It means a flow in which the phase state is in equilibrium.

二相流タービン１は、加工の容易さを優先する場合以外は、一般的に、液相が翼１３のチップ端１６より外部に放出されることを防止するために翼１３のチップ端１６の全体を覆うように固定された円環状のリング構造であるシュラウドが設置されている。実施形態１〜３は、シュラウドが設けられていない構成で本願発明を説明しているが、シュラウドが設けられた構成も実施形態１〜３に含まれているものとする。 The two-phase flow turbine 1 generally has a tip end 16 of the blade 13 in order to prevent the liquid phase from being discharged to the outside from the tip end 16 of the blade 13, except when the ease of processing is prioritized. A shroud, which is an annular ring structure fixed so as to cover the whole, is installed. The first to third embodiments describe the present invention with a configuration in which the shroud is not provided, but it is assumed that the configurations in which the shroud is provided are also included in the first to third embodiments.

１ 二相流タービン
１０ 動翼
１１ ディスク
１２ 回転軸
１２ａ （回転軸の）軸中心
１３ 翼
１４ 圧力面
１５ 負圧面
１６ チップ端
１７ ハブ端
１８ 前縁
１９ 後縁
２０ ノズル
２０ａ 噴出口
２０ｂ 流入口
２０ｃ （ノズルの流入口から噴出口までの間の）位置
２１ 流路
３０ 凹部
３０ａ （翼高さ方向における凹部の）端部
３０ｂ （翼高さ方向における凹部の）端部
３０ｅ （凹部の）下流端
３１ 湾曲部
３１ａ （湾曲部の）チップ側端部
３１ｂ （湾曲部の）ハブ側端部
３１ｃ （湾曲部の）最も凹んだ部分
３１ｄ （湾曲部の）上流端
３１ｅ （湾曲部の）下流端
３２ 第１平坦面
３３ 第２平坦面
４０ 流路
４１ 入口スロート
１００ 気液二相流
１０１ 気相の流れ
１０２ 液相の流れ
２００ 代表円
２０１ 液相の移動軌跡の長円
２０１ａ 長円の長さ方向の中心位置
Ａ （翼の）位置
Ｂ （翼の）位置
Ｃ （翼の）位置
Ｄ 回転軸の回転方向
Ｄ１ 翼の回転方向
Ｌ１ 第１直線
Ｌ２ 第２直線
Ｌ３ 第３直線
Ｐ０ 翼高さ方向中間位置
Ｐ１ 第１位置
Ｐ２ 第２位置
Ｐ３ 第３位置
Ｐ４ 第４位置
ｄ１ 軸方向距離
ｄ２ 軸方向距離 1 Two-phase flow turbine 10 Moving blade 11 Disc 12 Rotating shaft 12a (Rotating shaft) Shaft center 13 Blade 14 Pressure surface 15 Negative pressure surface 16 Chip end 17 Hub end 18 Front edge 19 Rear edge 20 Nozzle 20a Inlet 20b Inflow port 20c Position 21 (between the inlet and outlet of the nozzle) Channel 30 Recess 30a End 30a (recess in the blade height direction) End 30e (recess in the blade height direction) End 30e Downstream end (recess) 31 Curved part 31a (Curved part) Chip side end 31b (Curved part) Hub side end 31c (Curved part) Most recessed part 31d (Curved part) Upstream end 31e (Curved part) Downstream end 32 1st flat surface 33 2nd flat surface 40 Flow path 41 Inlet throat 100 Gas-liquid two-phase flow 101 Gas-phase flow 102 Liquid-phase flow 200 Representative circle 201 Oval of liquid-phase movement locus 201a Long direction of oval Center position A (of the wing) Position B (of the wing) Position C (of the wing) Position D Rotation direction of the rotation axis D1 Rotation direction of the wing L1 First straight line L2 Second straight line L3 Third straight line P0 Middle in the wing height direction Position P1 1st position P2 2nd position P3 3rd position P4 4th position d1 Axial distance d2 Axial distance

Claims (11)

流体の気液二相流によって駆動される二相流タービンの動翼であって、
回転可能に設けられた回転軸と、
前記回転軸を中心とした周方向に互いに間隔をあけるようにして設けられるとともに前記周方向に回転する複数の翼と
を備え、前記翼は、前記気液二相流が前記翼に相対的に前記回転軸の軸方向の上流から下流に向かって流れる方向における上流側の前縁と下流側の後縁とを有し、
前記回転軸に垂直な面に沿って切断した前記翼の断面において、前記翼の圧力面は、少なくとも翼高さ方向中間位置において、前記複数の翼の回転方向に向かって凹む凹部を有し、該凹部は、前記前縁及び前記後縁間を少なくとも部分的に延びる、二相流タービンの動翼。 The blades of a two-phase flow turbine driven by a gas-liquid two-phase flow of fluid.
Rotatably provided rotating shaft and
The blades are provided with a plurality of blades that are provided so as to be spaced apart from each other in the circumferential direction about the rotation axis and that rotate in the circumferential direction, and the blades have the gas-liquid two-phase flow relative to the blades. It has an upstream front edge and a downstream trailing edge in the direction of flow from upstream to downstream in the axial direction of the rotation axis.
In a cross section of the blade cut along a plane perpendicular to the axis of rotation, the pressure surface of the blade has recesses recessed in the direction of rotation of the plurality of blades, at least at intermediate positions in the blade height direction. The recess is a blade of a two-phase flow turbine that extends at least partially between the front edge and the trailing edge. 隣り合う２つの翼間に前記流体の気液二相流が流通する流路が形成され、
前記２つの翼のうちの一方の翼の前縁と他方の翼の負圧面上の位置である第１位置とによって、前記流路の流路面積が最小となる入口スロートが形成され、
前記回転軸の軸中心から一定半径の円筒面に沿って切断した前記翼の断面において、前記一方の翼の圧力面上には、前記翼の前縁からの軸方向距離が前記負圧面上の前記前縁から前記第１位置までの軸方向距離と同じになる第２位置が存在し、前記凹部は、少なくとも前記第２位置から前記一方の翼の後縁に向かって延びる、請求項１に記載の二相流タービンの動翼。 A flow path through which the gas-liquid two-phase flow of the fluid flows is formed between two adjacent blades.
The front edge of one of the two blades and the first position on the negative pressure surface of the other blade form an inlet throat that minimizes the flow path area of the flow path.
In the cross section of the blade cut along a cylindrical surface having a constant radius from the axis center of the rotation axis, the axial distance from the front edge of the blade is on the negative pressure surface on the pressure surface of the one blade. According to claim 1, there is a second position that is the same as the axial distance from the front edge to the first position, and the recess extends from at least the second position toward the trailing edge of the one wing. The vane of the described two-phase flow turbine. 前記回転軸に垂直な面に沿って切断した前記翼の断面における前記圧力面において、前記凹部は、ハブ端とチップ端との間の一部に前記翼の回転方向に向かって凹み且つ円弧状に湾曲した湾曲部を含み、前記湾曲部は、前記チップ端側の端部であるチップ側端部及び前記ハブ端側の端部であるハブ側端部を有し、
該湾曲部の曲率は、前記ハブ端と前記ハブ側端部との間の前記圧力面の曲率及び前記チップ端と前記チップ側端部との間の前記圧力面の曲率よりも大きい、請求項１または２に記載の二相流タービンの動翼。 In the pressure plane in the cross section of the wing cut along the plane perpendicular to the axis of rotation, the recess is recessed and arcuate in a portion between the hub end and the tip end in the direction of rotation of the wing. The curved portion has a chip side end portion which is an end portion on the chip end side and a hub side end portion which is an end portion on the hub end side.
Claim that the curvature of the curved portion is larger than the curvature of the pressure surface between the hub end and the hub side end portion and the curvature of the pressure surface between the chip end and the chip side end portion. The blade of the two-phase flow turbine according to 1 or 2. 前記チップ側端部から前記チップ端までの面は、前記回転軸の軸中心と前記チップ側端部とを通る第１直線に対して前記複数の翼の回転方向と反対側に位置する、請求項３に記載の二相流タービンの動翼。 The surface from the tip side end portion to the tip end portion is located on the side opposite to the rotation direction of the plurality of blades with respect to the first straight line passing through the axis center of the rotation shaft and the tip side end portion. Item 3. The rotor blade of the two-phase flow turbine according to Item 3. 前記ハブ側端部から前記ハブ端までの面は、前記回転軸の軸中心と前記ハブ側端部とを通る第２直線上、又は、該第２直線に対して前記複数の翼の回転方向と反対側に位置する、請求項３または４に記載の二相流タービンの動翼。 The surface from the hub-side end to the hub end is on a second straight line passing through the axial center of the rotation shaft and the hub-side end, or in the rotation direction of the plurality of blades with respect to the second straight line. The rotor blade of the two-phase flow turbine according to claim 3 or 4, which is located on the opposite side of the wheel. 前記凹部は、前記チップ側端部から前記チップ端まで平坦に延びる第１平坦面、又は、前記ハブ側端部から前記ハブ端まで平坦に延びる第２平坦面の少なくとも一方を含む、請求項３〜５のいずれか一項に記載の二相流タービンの動翼。 3. The recess comprises at least one of a first flat surface extending flatly from the chip side end to the chip end or a second flat surface extending flatly from the hub side end to the hub end. The blade of the two-phase flow turbine according to any one of the items to 5. 前記湾曲部は、前記翼の翼高さ方向に曲率の分布を有し、前記ハブ端から前記チップ端に向かって前記翼の翼高さの３０％の位置から８０％の位置の範囲で前記曲率が最大となる、請求項３〜６のいずれか一項に記載の二相流タービンの動翼。 The curved portion has a distribution of curvature in the blade height direction of the blade, and the curved portion has a position of 30% to 80% of the blade height of the blade from the hub end to the tip end. The rotor blade of the two-phase flow turbine according to any one of claims 3 to 6, which has the maximum curvature. 前記回転軸の軸中心から前記最も凹んだ部分までの距離を、前記翼の入口においてＲ１とし、前記翼の出口においてＲ３としたとき、前記湾曲部のうち前記複数の翼の回転方向に向かって最も凹んだ部分は、前記翼の子午面において前記入口から前記出口の中間における前記距離Ｒ２がＲ１より小さく前記ハブ端に向かって凹状になるように曲線的に変化するように構成される、請求項３〜７のいずれか一項に記載の二相流タービンの動翼。 When the distance from the axis center of the rotating shaft to the most recessed portion is R1 at the inlet of the blade and R3 at the outlet of the blade, the curved portion is directed toward the rotation direction of the plurality of blades. The most recessed portion is configured such that the distance R2 between the inlet and the outlet is less than R1 on the meridional surface of the wing and changes curvilinearly towards the hub end. The moving blade of the two-phase flow turbine according to any one of Items 3 to 7. 前記湾曲部は前記翼の前記後縁まで延びており、
前記湾曲部の下流端は、前記凹部の前記湾曲部以外の部分の下流端よりも前記翼の前記前縁側に位置する、請求項３〜８のいずれか一項に記載の二相流タービンの動翼。 The curved portion extends to the trailing edge of the wing.
The two-phase flow turbine according to any one of claims 3 to 8, wherein the downstream end of the curved portion is located on the front edge side of the blade with respect to the downstream end of the portion other than the curved portion of the recess. Moving blades. 前記入口及び前記出口間の中間部における前記距離をＲ２とすると、Ｒ２＜Ｒ１であり、
前記回転軸に対して垂直な面に沿って切断した前記翼の断面において、前記動翼に流入する前記流体の流れ方向に対して垂直で前記回転軸の軸中心を通る直線を第３直線とし、前記周方向に隣り合う前記翼間に流入した前記流体が前記中間部にあるときの前記流体から前記第３直線までの距離をＹ１とし、前記流体が前記下流端にあるときの前記流体から前記第３直線までの距離をＹ２とすると、Ｙ１＜Ｙ２のときはＲ２＜Ｒ３であり、Ｙ１＞Ｙ２のときはＲ２＞Ｒ３である、請求項１〜９のいずれか一項に記載の二相流タービンの動翼。 If the distance between the inlet and the outlet is R2, then R2 <R1.
In the cross section of the blade cut along the plane perpendicular to the rotation axis, a straight line passing through the axis center of the rotation axis perpendicular to the flow direction of the fluid flowing into the moving blade is defined as a third straight line. The distance from the fluid to the third straight line when the fluid flowing between the blades adjacent to each other in the circumferential direction is in the intermediate portion is set to Y1, and from the fluid when the fluid is at the downstream end. 2. According to any one of claims 1 to 9, where Y2 is the distance to the third straight line, R2 <R3 when Y1 <Y2 and R2> R3 when Y1> Y2. Moving blades of a phase fluid turbine. 請求項１〜１０のいずれか一項に記載の動翼と、
前記動翼に向けて前記流体の気液二相流を流出する少なくとも１つのノズルと
を備える二相流タービン。 The moving blade according to any one of claims 1 to 10.
A two-phase flow turbine including at least one nozzle that discharges a gas-liquid two-phase flow of the fluid toward the rotor blade.
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114075997A (en) * 2020-08-20 2022-02-22 曹建礼 Special-shaped worm wheel blade

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114075997A (en) * 2020-08-20 2022-02-22 曹建礼 Special-shaped worm wheel blade
CN114075997B (en) * 2020-08-20 2024-05-31 曹建礼 Special-shaped turbine blade

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