WO2011040241A1 - Turbine stator vane designing method, turbine stator vane, and steam turbine device using turbine stator vane - Google Patents
Turbine stator vane designing method, turbine stator vane, and steam turbine device using turbine stator vane Download PDFInfo
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- WO2011040241A1 WO2011040241A1 PCT/JP2010/065934 JP2010065934W WO2011040241A1 WO 2011040241 A1 WO2011040241 A1 WO 2011040241A1 JP 2010065934 W JP2010065934 W JP 2010065934W WO 2011040241 A1 WO2011040241 A1 WO 2011040241A1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
Definitions
- the present invention relates to a stationary blade of an axial flow turbine, particularly a low-aspect ratio turbine stationary blade.
- the secondary flows developed from the blade tip and blade root interfere with each other, producing a more turbulent flow
- the aspect ratio is approximately 1.0 or less
- the secondary flows at the blade tip and blade root often interfere with each other in the blade height direction.
- Patent Document 1 does not take into consideration the flow peculiar to a low aspect ratio paragraph composed of low aspect ratio blades.
- an object of the present invention is to provide a turbine stator blade that is a low aspect ratio turbine stator blade and can improve the paragraph efficiency.
- an s / t (s: throat length, t: pitch length) value distribution composed of a ratio of a throat ratio and a pitch length in the blade height direction.
- An arcuate curve is distributed from the root to the blade tip, the s / t value is minimized at the blade root, and the s / t value is maximized between the blade center and the blade tip.
- FIG. 1 It is sectional drawing showing the principal part structure of the steam turbine stage part which concerns on one Example of this invention. It is a perspective view of the cascade structure of a general low aspect ratio turbine stationary blade. It is explanatory drawing which represents typically the eddy current which generate
- FIG. 1 is a cross-sectional view showing the main structure of a steam turbine stage section according to the present embodiment.
- FIG. 2 is a perspective view showing a cascade structure of a general low aspect ratio turbine stationary blade.
- FIG. 3 is a diagram schematically showing a vortex generated between the blades of the cascade structure shown in FIG.
- FIG. 4 is a graph showing the s / t value distribution in the blade height direction of the turbine stationary blade according to the present embodiment.
- the turbine stage of the steam turbine includes a stationary blade 3 arranged in a circumferential direction between a diaphragm outer ring 1 and a diaphragm inner ring 2, and a steam flow direction of the stationary blade 3.
- the rotor blades 5 are arranged in the circumferential direction on the turbine rotor 4 so as to face the downstream side (hereinafter simply referred to as the downstream side).
- a shroud 6 is provided at the tip of the rotor blade 5 in the turbine radial direction outer peripheral side (hereinafter simply referred to as the outer peripheral side), and a seal structure (not shown) is provided between the stationary blades.
- the steam main flow 7 which is a working fluid passes between the blades from the front edge 8 of the stationary blade 3 and flows out from the rear edge 9.
- the steam turbine causes the main steam 7 flowing out from the stationary blade 3 to collide with the moving blade 5 on the downstream side, thereby rotating the turbine rotor 4 and using a generator (not shown) connected to the end of the turbine rotor 4. It generates electricity by converting rotational energy into electrical energy.
- FIG. 2 shows a general low-aspect-ratio stationary blade cascade structure as a comparative example with the present embodiment.
- a plurality of stator blades 3 are arranged in the circumferential direction between the diaphragm outer ring 1 and the diaphragm inner ring 2.
- the stationary blade 3 has a blade root 10 side fixed to the diaphragm inner ring 2 and a blade tip 11 side fixed to the diaphragm outer ring 1.
- the stationary blades 3 are installed at equal intervals using the interval length t (pitch length) between adjacent blades in the turbine circumferential direction, which is determined from the number of blades installed in the blade row.
- the shortest length s between the blade trailing edge of the stationary blade 3a and the adjacent stationary blade 3b is referred to as a throat length.
- FIG. 3 schematically shows the vortex of the vapor flow generated between the blades of the cascade structure shown in FIG.
- the diaphragm outer ring 1 and inner ring 2 are not shown.
- the stationary blade 3 has a pressure surface 12 formed on the blade side and a suction surface 13 formed on the blade back side.
- the main steam flow 7 is supplied from the front edge portion 8 of the stationary blade 3, passes through the inter-blade channel 14 formed between the pressure surface 12 and the negative pressure surface 13, and flows out from the rear edge portion 9.
- a pressure gradient is generated between the vanes. For this reason, a secondary flow 15 is generated from the pressure surface 12 toward the suction surface 13. Further, the steam main flow 7 flows into the inter-blade channel 14 from the leading edge 8, and vortices are generated on the pressure surface 12 and the negative pressure surface 13.
- the vortex existing on the pressure surface 12 develops in the inter-blade channel, forms a flow channel vortex 16, and moves to the negative pressure surface 13 under the influence of the secondary flow 15.
- the flow path vortex 16 is generated at the blade root 10 and the blade tip 11, respectively.
- the flow path vortices 16 generated at the blade root 10 and the blade tip 11 interfere with each other. It forms a turbulent flow.
- This flow path vortex 16 causes a reduction in work efficiency that the turbine blades should originally perform, and becomes a major factor of side wall loss.
- FIG. 4 shows the s / t value distribution in the blade height direction of the turbine stationary blade according to the present embodiment by a solid line, and the s / t value distribution by the conventional free vortex design by a dotted line.
- the horizontal axis represents the s / t value, which is the ratio of the throat length s to the pitch length t.
- the vertical axis represents the blade height.
- the s / t value gradually increases at a constant rate from the blade root to the blade tip and is distributed in a straight line.
- the s / t value is distributed in an arc shape from the blade root to the blade tip. More specifically, the s / t value is minimum at the blade root, gradually increases so as to draw an arc toward the blade tip, and is maximized between the span center (blade center) and the blade tip, and the blade tip. It gradually becomes smaller so as to draw an arc again.
- the s / t value at the blade tip is not less than the intermediate value between the maximum s / t value and the minimum s / t value and less than the maximum s / t value.
- the minimum s / t value of the blade root is 65% or more of the maximum s / t value and less than the s / t value of the blade root at the time of free vortex design.
- the blade cross-sectional area composed of the blade tip throat length, blade root throat length, blade suction surface, and trailing edge so as to fall within this range is the value of this example and the free vortex.
- the arc shape, blade tip throat length, and blade root throat length of the distribution curve are determined so as to be equal to the value of the cross-sectional area between blades at the time of design.
- the s / t value distribution curve of the turbine stationary blade gradually increases from the minimum s / t value to the maximum s / t value at the blade root, and the blade tip from the position having the maximum s / t value. It is represented by an arcuate curve that protrudes upward and gradually decreases.
- FIG. 5 shows the cascade structure of the turbine vane and cross section between the blades by free vortex design.
- FIG. 6 shows the blade cascade structure of the turbine stationary blade according to the present embodiment and the cross section between the blades.
- FIG. 7 shows a comparison of the cross-sectional area between the blades of the turbine vane according to one embodiment of the present invention and the cross-sectional area between the blades of the turbine vane according to the free vortex design.
- the inter-blade channel cross-sectional area of the present embodiment is equal to the inter-blade channel cross-sectional area at the time of free vortex design.
- the cross-blade channel cross section of the present example has a larger channel width (throat length) from the blade root toward the center of the span, and the maximum channel width between the center of the span and the blade tip. Then, it is formed so as to narrow again toward the tip.
- FIG. 8 shows the blade height direction distribution of the stationary blade outlet flow rate of the turbine stationary blade according to the present embodiment.
- the outlet flow distribution of the turbine vane at the time of the free vortex design shown in FIG. 4 is indicated by a dotted line, and the outlet flow distribution of the turbine vane according to the present embodiment is indicated by a solid line.
- the flow rate of the steam flowing through the vane outlet is distributed substantially uniformly from the blade root toward the blade tip.
- the turbine stationary blade according to the present embodiment has a distribution in which the s / t value is maximized between the center of the span and the blade tip, the stationary blade outlet flow rate increases between the center of the span and the blade tip. An increase in the flow rate leads to an increase in the axial flow velocity. Therefore, in the turbine stationary blade according to the present embodiment, the axial flow velocity of steam from the center of the span to the blade tip increases.
- FIG. 9 shows the efficiency distribution of the turbine stationary blade according to the present embodiment.
- the graph indicated by the solid line is the efficiency distribution of the turbine vane according to the present embodiment
- the graph indicated by the dotted line is the efficiency distribution of the turbine vane at the time of the free vortex design shown in FIG. According to FIG. 9, it can be seen that the efficiency of the turbine stationary blade according to the present embodiment is improved from the center of the span to the blade tip as compared with the turbine stationary blade of the free vortex design.
- a large amount of flow can be distributed to the tip of the stationary blade, and when flowing into the blade, a large amount of flow is distributed from the center of the blade span to the blade tip. Can do. Therefore, the efficiency can be improved in the region, and the paragraph efficiency can be improved as a result of the flow rate averaging in the blade height direction.
- FIG. 10 shows the efficiency improvement amount with respect to the position of the maximum s / t value in the turbine stationary blade according to the present embodiment.
- the vertical axis shows the amount of improvement in efficiency when the present invention is applied as a relative value from the turbine vane by the free vortex design shown in FIG. 4, and is the maximum value of the amount of improvement in efficiency when the present invention is applied. Indicates the dimensioned value.
- FIG. 10 it can be seen that the present invention works most effectively when the position of the maximum s / t value is in the range from 75% to 95% of the entire blade height, particularly from the blade root. It should be noted that the same effect can be obtained by replacing s / t used so far with the blade exit angle sin ⁇ 1 (s / t) representing the geometric angle of the turbine vane.
- FIG. 11 is a system diagram of a steam turbine to which the turbine blade of the present invention is applied.
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Abstract
Provided is a turbine stator vane having a low aspect ratio, whereby the sidewall loss can be reduced, and the stage efficiency can be improved. The turbine stator vane, which is for an axial flow turbine, is a low-aspect-ratio stator vane, and has a s/t value (s: throat length, t: pitch length) distribution formed in an arciform manner from the root of the vane to the tip of the vane in the height direction of the vane. The s/t value is maximum between the center and the tip of the vane in the height direction of the vane, and is minimum at the root of the vane. The s/t value at the tip of the vane is determined so as to be not less than the intermediate value between the maximum s/t value and the minimum s/t value and less than the maximum s/t value, and the s/t value at the root of the vane is determined so as to be not less than 65 % of the maximum s/t value and less than the s/t value at the root of the vane when designing a free vortex.
Description
本発明は、軸流タービンの静翼、特に低アスペクト比のタービン静翼に係る。
The present invention relates to a stationary blade of an axial flow turbine, particularly a low-aspect ratio turbine stationary blade.
軸流タービンにおいては、性能向上を目的とした種々の技術が採用されており、高い効率を実現している。タービンの性能向上を実現するためには、タービン内部の圧力、段落、排気、機械等の各損失を低減させることが必要不可欠となる。中でも、段落損失のうち、側壁損失はタービンの各段落に共通する損失である。この損失は、二次流れの影響により、翼前縁より発生する渦が翼間にて発達し、流路渦を形成することが主な原因である。
In the axial flow turbine, various technologies for improving performance are adopted, and high efficiency is realized. In order to improve the performance of the turbine, it is indispensable to reduce each loss such as pressure, paragraph, exhaust, and machine inside the turbine. Among them, among the paragraph losses, the sidewall loss is a loss common to each paragraph of the turbine. The main cause of this loss is that a vortex generated from the leading edge of the blade develops between the blades due to the influence of the secondary flow and forms a flow path vortex.
一般的に、軸流タービンのタービン翼では、翼根元から翼先端に向けて、スロート長ｓとピッチ長ｔで構成されるｓ／ｔが徐々に大きくなる直線状のｓ／ｔ分布を用いたフリーボルテックス設計が古くから採用されている。
In general, in a turbine blade of an axial flow turbine, a linear s / t distribution in which s / t composed of a throat length s and a pitch length t gradually increases from the blade root toward the blade tip is used. Free vortex design has been adopted for a long time.
しかし、上記フリーボルテックス設計では、翼列内の翼間に生じる二次流れや渦流等により側壁損失が発生しやすく、段落損失が増大しやすい。
However, in the above free vortex design, side wall loss is likely to occur due to the secondary flow or vortex generated between the blades in the cascade, and the paragraph loss tends to increase.
そこで、例えば特許文献１に記載された技術のように、タービン翼のスタッキングを翼高さ方向に変化させ、ｓ／ｔ分布を変化させることで、二次流れや渦流の影響を低減し、側壁損失を低減する技術が提案されている。
Therefore, for example, as in the technique described in Patent Document 1, the influence of the secondary flow and vortex flow is reduced by changing the stacking of the turbine blades in the blade height direction and changing the s / t distribution. Techniques for reducing the loss have been proposed.
ところで、翼高さと翼弦長の比であるアスペクト比が比較的小さい低アスペクト比のタービン静翼では、翼先端および翼根元より発達する二次流れが互いに干渉し、より乱れの大きい流れが発生する場合がある。特に、アスペクト比が概ね１.０以下の場合に、翼先端及び翼根元の二次流れが互いに翼高さ方向で干渉する場合が多い。
By the way, in a low-aspect-ratio turbine stationary blade with a relatively small aspect ratio, which is the ratio of blade height and chord length, the secondary flows developed from the blade tip and blade root interfere with each other, producing a more turbulent flow There is a case. In particular, when the aspect ratio is approximately 1.0 or less, the secondary flows at the blade tip and blade root often interfere with each other in the blade height direction.
しかしながら、特許文献１に記載された技術は、低アスペクト比翼で構成された低アスペクト比段落特有の流れについて考慮したものではない。
However, the technique described in Patent Document 1 does not take into consideration the flow peculiar to a low aspect ratio paragraph composed of low aspect ratio blades.
そこで、本発明は、低アスペクト比のタービン静翼であって、段落効率を向上させることができるタービン静翼を提供することを目的とする。
Therefore, an object of the present invention is to provide a turbine stator blade that is a low aspect ratio turbine stator blade and can improve the paragraph efficiency.
上記目的を達成するために、低アスペクト比タービン静翼において、翼高さ方向のスロート比とピッチ長の比で構成されるｓ／ｔ（ｓ：スロート長 ｔ：ピッチ長）値分布を、翼根元から翼先端まで弧状の曲線を描くように分布させ、翼根元でｓ／ｔ値を最小とし、翼中央と翼先端との間で前記ｓ／ｔ値を最大とする。
In order to achieve the above object, in a low aspect ratio turbine stationary blade, an s / t (s: throat length, t: pitch length) value distribution composed of a ratio of a throat ratio and a pitch length in the blade height direction is used. An arcuate curve is distributed from the root to the blade tip, the s / t value is minimized at the blade root, and the s / t value is maximized between the blade center and the blade tip.
本発明によれば、低アスペクト比のタービン静翼であって、段落効率を向上させることができるタービン静翼を提供することができる。
According to the present invention, it is possible to provide a turbine stator blade having a low aspect ratio, which can improve the paragraph efficiency.
以下、本発明を実施するための形態について、適宜図を参照して詳細に説明する。なお、各図面を通し、同等の構成要素には同一の符号を付してある。
Hereinafter, embodiments for carrying out the present invention will be described in detail with reference to the drawings as appropriate. In addition, the same code | symbol is attached | subjected to the equivalent component through each drawing.
以下、本発明の一実施例として、本発明のタービン静翼を蒸気タービンの低アスペクト比静翼に適用した例について説明する。
Hereinafter, as an embodiment of the present invention, an example in which the turbine stationary blade of the present invention is applied to a low aspect ratio stationary blade of a steam turbine will be described.
図１は、本実施例に係る蒸気タービン段落部の要部構造を示した断面図である。図２は、一般的な低アスペクト比タービン静翼の翼列構造を示した斜視図である。図３は、図２に示した翼列構造の翼間に発生する渦流を模式的に表した図である。図４は、本実施例に係るタービン静翼の翼高さ方向のｓ／ｔ値分布を示したグラフである。
FIG. 1 is a cross-sectional view showing the main structure of a steam turbine stage section according to the present embodiment. FIG. 2 is a perspective view showing a cascade structure of a general low aspect ratio turbine stationary blade. FIG. 3 is a diagram schematically showing a vortex generated between the blades of the cascade structure shown in FIG. FIG. 4 is a graph showing the s / t value distribution in the blade height direction of the turbine stationary blade according to the present embodiment.
図１に示すように、本実施例に係る蒸気タービンのタービン段落は、ダイヤフラム外輪１とダイヤフラム内輪２との間にタービン周方向に列設された静翼３と、静翼３の蒸気流れ方向下流側（以下、単に下流側と記載する）に対向して、タービンロータ４に周方向に列設された動翼５とから構成される。動翼５のタービン半径方向外周側（以下、単に外周側と記載する）の先端にはシュラウド６が設けられ、対向する静止体との間にシール構造（図示せず）が設けられている。
As shown in FIG. 1, the turbine stage of the steam turbine according to this embodiment includes a stationary blade 3 arranged in a circumferential direction between a diaphragm outer ring 1 and a diaphragm inner ring 2, and a steam flow direction of the stationary blade 3. The rotor blades 5 are arranged in the circumferential direction on the turbine rotor 4 so as to face the downstream side (hereinafter simply referred to as the downstream side). A shroud 6 is provided at the tip of the rotor blade 5 in the turbine radial direction outer peripheral side (hereinafter simply referred to as the outer peripheral side), and a seal structure (not shown) is provided between the stationary blades.
作動流体である蒸気主流７は、静翼３の前縁部８より翼間を通過し、後縁部９から流出する。蒸気タービンは、静翼３から流出した蒸気主流７を下流側の動翼５に衝突させることで、タービンロータ４を回転させ、タービンロータ４の端部に接続する発電機（図示せず）によって回転エネルギーを電気エネルギーに変換して発電を行う。
The steam main flow 7 which is a working fluid passes between the blades from the front edge 8 of the stationary blade 3 and flows out from the rear edge 9. The steam turbine causes the main steam 7 flowing out from the stationary blade 3 to collide with the moving blade 5 on the downstream side, thereby rotating the turbine rotor 4 and using a generator (not shown) connected to the end of the turbine rotor 4. It generates electricity by converting rotational energy into electrical energy.
図２に、本実施例との比較例として一般的な低アスペクト比静翼の翼列構造を示す。静翼３は、ダイヤフラム外輪１とダイヤフラム内輪２との間に、周方向に複数枚列設されている。静翼３は、翼根元１０側をダイヤフラム内輪２に固定され、翼先端１１側をダイヤフラム外輪１に固定される。また、静翼３は、翼列内に設置される翼枚数から決定される、タービン周方向に隣り合う翼の間隔長さｔ（ピッチ長）を用いて、等間隔に設置される。ここで、静翼３ａの翼後縁部と隣り合う静翼３ｂとの最短長さｓをスロート長という。
FIG. 2 shows a general low-aspect-ratio stationary blade cascade structure as a comparative example with the present embodiment. A plurality of stator blades 3 are arranged in the circumferential direction between the diaphragm outer ring 1 and the diaphragm inner ring 2. The stationary blade 3 has a blade root 10 side fixed to the diaphragm inner ring 2 and a blade tip 11 side fixed to the diaphragm outer ring 1. The stationary blades 3 are installed at equal intervals using the interval length t (pitch length) between adjacent blades in the turbine circumferential direction, which is determined from the number of blades installed in the blade row. Here, the shortest length s between the blade trailing edge of the stationary blade 3a and the adjacent stationary blade 3b is referred to as a throat length.
図３に、図２に示した翼列構造の翼間に発生する蒸気流の渦を模式的に示す。なお、ダイヤフラム外輪１および内輪２は図示を省略する。
FIG. 3 schematically shows the vortex of the vapor flow generated between the blades of the cascade structure shown in FIG. The diaphragm outer ring 1 and inner ring 2 are not shown.
静翼３は、翼腹側に形成される圧力面１２、および翼背側に形成される負圧面１３を有する。蒸気主流７は、静翼３の前縁部８より供給され、圧力面１２と負圧面１３との間に形成される翼間流路１４を通過し、後縁部９より流出する。蒸気主流７が翼間流路１４を通過する際、翼間に圧力勾配が生じる。このため、圧力面１２から負圧面１３へ向かう二次流れ１５が生じる。また、前縁部８より蒸気主流７が翼間流路１４に流入し、圧力面１２と負圧面１３に渦が発生する。この内、圧力面１２に存在する渦は、翼間流路内で発達しながら、流路渦１６を形成し、また、二次流れ１５の影響を受け、負圧面１３へ移動する。流路渦１６は、翼根元１０および翼先端１１でそれぞれ発生する。アスペクト比が小さい静翼、特にアスペクト比が１.０以下の低アスペクト比静翼で構成される翼列構造では、翼根元１０および翼先端１１でそれぞれ発生した流路渦１６が、相互に干渉し合い、乱れの大きい流れを形成している。この流路渦１６は、本来タービン翼が行うべき仕事の効率低下を招き、側壁損失の大きな要因となる。
The stationary blade 3 has a pressure surface 12 formed on the blade side and a suction surface 13 formed on the blade back side. The main steam flow 7 is supplied from the front edge portion 8 of the stationary blade 3, passes through the inter-blade channel 14 formed between the pressure surface 12 and the negative pressure surface 13, and flows out from the rear edge portion 9. When the steam main flow 7 passes through the inter-blade channel 14, a pressure gradient is generated between the vanes. For this reason, a secondary flow 15 is generated from the pressure surface 12 toward the suction surface 13. Further, the steam main flow 7 flows into the inter-blade channel 14 from the leading edge 8, and vortices are generated on the pressure surface 12 and the negative pressure surface 13. Of these, the vortex existing on the pressure surface 12 develops in the inter-blade channel, forms a flow channel vortex 16, and moves to the negative pressure surface 13 under the influence of the secondary flow 15. The flow path vortex 16 is generated at the blade root 10 and the blade tip 11, respectively. In a cascade structure composed of a stationary blade having a small aspect ratio, particularly a low aspect ratio stationary blade having an aspect ratio of 1.0 or less, the flow path vortices 16 generated at the blade root 10 and the blade tip 11 interfere with each other. It forms a turbulent flow. This flow path vortex 16 causes a reduction in work efficiency that the turbine blades should originally perform, and becomes a major factor of side wall loss.
図４に、本実施例に係るタービン静翼の翼高さ方向のｓ／ｔ値分布を実線で、従来のフリーボルテックス設計によるｓ／ｔ値分布を点線で示す。図４において、横軸はスロート長ｓとピッチ長ｔの比であるｓ／ｔ値を表す。また、縦軸は翼高さを表す。
FIG. 4 shows the s / t value distribution in the blade height direction of the turbine stationary blade according to the present embodiment by a solid line, and the s / t value distribution by the conventional free vortex design by a dotted line. In FIG. 4, the horizontal axis represents the s / t value, which is the ratio of the throat length s to the pitch length t. The vertical axis represents the blade height.
フリーボルテックス設計では、ｓ／ｔ値は、翼根元から翼先端に向かって一定の割合で徐々に大きくなり、直線状に分布する。
In the free vortex design, the s / t value gradually increases at a constant rate from the blade root to the blade tip and is distributed in a straight line.
一方、本実施例に係るタービン静翼では、ｓ／ｔ値は翼根元から翼先端にむけて弧状に分布する。より詳細には、ｓ／ｔ値は、翼根元で最小となり、翼先端に向けて弧を描くように徐々に大きくなり、スパン中央（翼中央）と翼先端との間で最大となり、翼先端に向けて再び弧を描くように徐々に小さくなる。翼先端のｓ／ｔ値は、最大ｓ／ｔ値と最小ｓ／ｔ値との中間値以上、最大ｓ／ｔ値未満とする。一方、翼根元の最小ｓ／ｔ値は、最大ｓ／ｔ値の６５％以上、フリーボルテックス設計時の翼根元のｓ／ｔ値未満とする。この範囲内に収まるように、かつ、翼先端スロート長、翼根元スロート長、翼負圧面、ならびに、後縁部で構成される翼間流路断面積が、本実施例の値と、フリーボルテックス設計時の翼間流路断面積の値とで等しくなるように、分布曲線の弧の形状、翼先端スロート長、および翼根元スロート長は決定される。
On the other hand, in the turbine stationary blade according to the present embodiment, the s / t value is distributed in an arc shape from the blade root to the blade tip. More specifically, the s / t value is minimum at the blade root, gradually increases so as to draw an arc toward the blade tip, and is maximized between the span center (blade center) and the blade tip, and the blade tip. It gradually becomes smaller so as to draw an arc again. The s / t value at the blade tip is not less than the intermediate value between the maximum s / t value and the minimum s / t value and less than the maximum s / t value. On the other hand, the minimum s / t value of the blade root is 65% or more of the maximum s / t value and less than the s / t value of the blade root at the time of free vortex design. The blade cross-sectional area composed of the blade tip throat length, blade root throat length, blade suction surface, and trailing edge so as to fall within this range is the value of this example and the free vortex. The arc shape, blade tip throat length, and blade root throat length of the distribution curve are determined so as to be equal to the value of the cross-sectional area between blades at the time of design.
よって、本実施例に係るタービン静翼のｓ／ｔ値分布曲線は、翼根元の最小ｓ／ｔ値から最大ｓ／ｔ値まで徐々に大きくなり、最大ｓ／ｔ値を持つ位置から翼先端まで徐々に小さくなる、上側に凸する弧状曲線で表される。
Therefore, the s / t value distribution curve of the turbine stationary blade according to the present embodiment gradually increases from the minimum s / t value to the maximum s / t value at the blade root, and the blade tip from the position having the maximum s / t value. It is represented by an arcuate curve that protrudes upward and gradually decreases.
図５に、フリーボルテックス設計によるタービン静翼の翼列構造および翼間流路断面を表す。図６に、本実施例に係るタービン静翼の翼列構造および翼間流路断面を示す。図７に、本発明の一実施例に係るタービン静翼の翼間流路断面積とフリーボルテックス設計によるタービン静翼の翼間流路断面積とを比較した図を示す。
Fig. 5 shows the cascade structure of the turbine vane and cross section between the blades by free vortex design. FIG. 6 shows the blade cascade structure of the turbine stationary blade according to the present embodiment and the cross section between the blades. FIG. 7 shows a comparison of the cross-sectional area between the blades of the turbine vane according to one embodiment of the present invention and the cross-sectional area between the blades of the turbine vane according to the free vortex design.
前述したように、本実施例の翼間流路断面積は、フリーボルテックス設計時の翼間流路
断面積と等しい。一方で、本実施例の翼間流路断面は、翼根元からスパン中央部に向かっ
て流路幅（スロート長）が大きくなり、スパン中央部と翼先端との間で流路幅は最大とな
り、その後、先端に向かって再度狭くなるように形成される。 As described above, the inter-blade channel cross-sectional area of the present embodiment is equal to the inter-blade channel cross-sectional area at the time of free vortex design. On the other hand, the cross-blade channel cross section of the present example has a larger channel width (throat length) from the blade root toward the center of the span, and the maximum channel width between the center of the span and the blade tip. Then, it is formed so as to narrow again toward the tip.
断面積と等しい。一方で、本実施例の翼間流路断面は、翼根元からスパン中央部に向かっ
て流路幅（スロート長）が大きくなり、スパン中央部と翼先端との間で流路幅は最大とな
り、その後、先端に向かって再度狭くなるように形成される。 As described above, the inter-blade channel cross-sectional area of the present embodiment is equal to the inter-blade channel cross-sectional area at the time of free vortex design. On the other hand, the cross-blade channel cross section of the present example has a larger channel width (throat length) from the blade root toward the center of the span, and the maximum channel width between the center of the span and the blade tip. Then, it is formed so as to narrow again toward the tip.
図８に、本実施例に係るタービン静翼の静翼出口流量の翼高さ方向分布を示す。図４に示したフリーボルテックス設計時のタービン静翼の出口流量分布を点線で示し、本実施例に係るタービン静翼の出口流量分布を実線で示す。図８に示したように、フリーボルテックス設計によるタービン静翼では、静翼出口を流れる蒸気の流量は、翼根元から翼先端に向けて略一定に分布している。一方、本実施例に係るタービン静翼は、ｓ／ｔ値をスパン中央から翼先端の間で最大とする分布としたため、スパン中央から翼先端の間で静翼出口流量が増大する。流量の増大は、軸流速度の増大に繋がる。従って、本実施例に係るタービン静翼では、スパン中央から翼先端までの間の蒸気の軸流速度が増加する。
FIG. 8 shows the blade height direction distribution of the stationary blade outlet flow rate of the turbine stationary blade according to the present embodiment. The outlet flow distribution of the turbine vane at the time of the free vortex design shown in FIG. 4 is indicated by a dotted line, and the outlet flow distribution of the turbine vane according to the present embodiment is indicated by a solid line. As shown in FIG. 8, in the turbine vane by the free vortex design, the flow rate of the steam flowing through the vane outlet is distributed substantially uniformly from the blade root toward the blade tip. On the other hand, since the turbine stationary blade according to the present embodiment has a distribution in which the s / t value is maximized between the center of the span and the blade tip, the stationary blade outlet flow rate increases between the center of the span and the blade tip. An increase in the flow rate leads to an increase in the axial flow velocity. Therefore, in the turbine stationary blade according to the present embodiment, the axial flow velocity of steam from the center of the span to the blade tip increases.
図９に、本実施例に係るタービン静翼の効率分布を示す。実線で示されたグラフが、本実施例に係るタービン静翼の効率分布であり、点線で示されたグラフが、図４に示したフリーボルテックス設計時のタービン静翼の効率分布である。図９によれば、フリーボルテックス設計によるタービン静翼と比較して、本実施例に係るタービン静翼ではスパン中央部から翼先端にかけて効率が改善されていることが分かる。
FIG. 9 shows the efficiency distribution of the turbine stationary blade according to the present embodiment. The graph indicated by the solid line is the efficiency distribution of the turbine vane according to the present embodiment, and the graph indicated by the dotted line is the efficiency distribution of the turbine vane at the time of the free vortex design shown in FIG. According to FIG. 9, it can be seen that the efficiency of the turbine stationary blade according to the present embodiment is improved from the center of the span to the blade tip as compared with the turbine stationary blade of the free vortex design.
本発明によれば、低アスペクト比タービン静翼において、静翼の先端側に流量を多く配分でき、それにより動翼に流入する際、動翼スパン中央部から翼先端にかけて流量を多く配分することができる。よって、当該領域において、効率向上することができ、翼高さ方向に流量平均した結果、段落効率を向上させることができる。
According to the present invention, in a low aspect ratio turbine stationary blade, a large amount of flow can be distributed to the tip of the stationary blade, and when flowing into the blade, a large amount of flow is distributed from the center of the blade span to the blade tip. Can do. Therefore, the efficiency can be improved in the region, and the paragraph efficiency can be improved as a result of the flow rate averaging in the blade height direction.
次に、図１０に、本実施例に係るタービン静翼における、最大ｓ／ｔ値の位置に対する効率改善量を示す。縦軸は、本発明を適用した場合の効率改善量を図４に示したフリーボルテックス設計によるタービン静翼からの相対値で示し、本発明を適用した場合の効率改善量の最大値にて無次元化した値を示す。図１０によれば、本発明は、最大ｓ／ｔ値の位置が、特に翼根元から翼高さ全体の７５％から９５％まで範囲にあるとき、最も効果的に作用することが分かる。なお、これまで説明に用いてきたｓ／ｔを、タービン静翼の幾何学的な角度を表す翼出口角sin-1(ｓ／ｔ)と置き換えても同様な効果を得ることができる。
Next, FIG. 10 shows the efficiency improvement amount with respect to the position of the maximum s / t value in the turbine stationary blade according to the present embodiment. The vertical axis shows the amount of improvement in efficiency when the present invention is applied as a relative value from the turbine vane by the free vortex design shown in FIG. 4, and is the maximum value of the amount of improvement in efficiency when the present invention is applied. Indicates the dimensioned value. According to FIG. 10, it can be seen that the present invention works most effectively when the position of the maximum s / t value is in the range from 75% to 95% of the entire blade height, particularly from the blade root. It should be noted that the same effect can be obtained by replacing s / t used so far with the blade exit angle sin −1 (s / t) representing the geometric angle of the turbine vane.
図１１は、本発明のタービン翼を適用した蒸気タービンのシステム図である。
FIG. 11 is a system diagram of a steam turbine to which the turbine blade of the present invention is applied.
図１１に図示するように、蒸気タービンでは、ボイラー等の蒸気発生器（図示せず）で加圧・加熱された蒸気を主蒸気配管１７に通して高圧タービン１８に送る。高圧タービン１８にて仕事をした蒸気は、再熱器１９で再び加熱された後、中圧タービン２０へと送られ、仕事を行う。中圧タービン２０から排出された蒸気は、クロスオーバ管（連絡管）２１を通り、低圧タービン２２ａおよび２２ｂに送られ、仕事を行う。高圧タービン１８、中圧タービン２０、低圧タービン２２は、回転可能なタービンロータ２３で機械的に連結されており、タービンロータ２３に連結された発電機２４によって、回転仕事を電力に変換する。低圧タービン２２ａおよび２２ｂから排出された蒸気は、さらに下流に設置された復水器（図示せず）に導入され、そこで凝縮されて復水となり、再び蒸気発生器に還流する。
As shown in FIG. 11, in the steam turbine, steam pressurized and heated by a steam generator (not shown) such as a boiler is sent to the high-pressure turbine 18 through the main steam pipe 17. The steam that has worked in the high-pressure turbine 18 is heated again in the reheater 19 and then sent to the intermediate-pressure turbine 20 to perform work. Steam discharged from the intermediate pressure turbine 20 passes through a crossover pipe (communication pipe) 21 and is sent to the low pressure turbines 22a and 22b to perform work. The high-pressure turbine 18, the intermediate-pressure turbine 20, and the low-pressure turbine 22 are mechanically connected by a rotatable turbine rotor 23, and the rotary work is converted into electric power by a generator 24 connected to the turbine rotor 23. The steam discharged from the low- pressure turbines 22a and 22b is introduced into a condenser (not shown) installed further downstream, where it is condensed to condensate and returns to the steam generator again.
３ 静翼
５ 動翼
７ 蒸気主流
１０ 翼根元
１１ 翼先端
１２ 圧力面
１３ 負圧面
１４ 翼間流路
１５ 二次流れ
１６ 流路渦
１７ 主蒸気配管
１８ 高圧タービン
２０ 中圧タービン
２２ 低圧タービン
２４ 発電機 3Stator blade 5 Rotor blade 7 Steam main flow 10 Blade root 11 Blade tip 12 Pressure surface 13 Negative pressure surface 14 Inter-blade channel 15 Secondary flow 16 Channel vortex 17 High pressure turbine 20 Medium pressure turbine 22 Low pressure turbine 24 Power generation Machine
５ 動翼
７ 蒸気主流
１０ 翼根元
１１ 翼先端
１２ 圧力面
１３ 負圧面
１４ 翼間流路
１５ 二次流れ
１６ 流路渦
１７ 主蒸気配管
１８ 高圧タービン
２０ 中圧タービン
２２ 低圧タービン
２４ 発電機 3
Claims (7)
- 軸流タービンに用いられるタービン静翼の設計方法において、
前記タービン静翼は、低アスペクト比のタービン静翼であり、
翼高さ方向のスロート比とピッチ長の比で構成されるｓ／ｔ値（ｓ：スロート長 ｔ：ピッチ長）分布を、翼根元から翼先端まで弧状の曲線を描くように分布させ、翼根元でｓ／ｔ値を最小とし、翼中央と翼先端との間で前記ｓ／ｔ値を最大とすることを特徴とするタービン静翼の設計方法。 In a method for designing a turbine stationary blade used in an axial flow turbine,
The turbine vane is a low aspect ratio turbine vane,
The s / t value (s: throat length t: pitch length) distribution composed of the ratio of throat ratio and pitch length in the blade height direction is distributed so as to draw an arcuate curve from the blade root to the blade tip. A design method for a turbine vane characterized in that the s / t value is minimized at the root and the s / t value is maximized between the blade center and the blade tip. - 前記翼先端の前記ｓ／ｔ値を、前記ｓ／ｔ値の最大値と最小値との中間値以上、かつ前記ｓ／ｔ値の最大値未満とし、
前記翼根元の前記ｓ／ｔ値を、最大ｓ／ｔ値の６５％以上、フリーボルテックス設計時の翼根元のｓ／ｔ値未満としたことを特徴とする請求項1記載のタービン静翼の設計方法。 The s / t value of the blade tip is not less than an intermediate value between the maximum value and the minimum value of the s / t value and less than the maximum value of the s / t value,
2. The turbine stationary blade according to claim 1, wherein the s / t value of the blade root is 65% or more of the maximum s / t value and less than the s / t value of the blade root at the time of free vortex design. Design method. - 前記ｓ／ｔ値を、前記タービン静翼の翼長に対して前記翼根元より７５％以上９５％以下の翼高さ位置で最大とすることを特徴とする請求項２記載のタービン静翼の設計方法。 3. The turbine stationary blade according to claim 2, wherein the s / t value is maximized at a blade height position of 75% or more and 95% or less from the blade root with respect to a blade length of the turbine stationary blade. Design method.
- 軸流タービンのタービン静翼であって、
前記タービン静翼は低アスペクト比静翼であり、
翼高さ方向翼根元から翼先端に向けて弧状に形成されたｓ／ｔ値（ｓ：スロート長 ｔ：ピッチ長）分布を有し、
前記ｓ／ｔ値を、翼高さ方向中央部と翼先端との間で最大とし、かつ前記翼根元で最小としたことを特徴とするタービン静翼。 A turbine vane of an axial turbine,
The turbine vane is a low aspect ratio vane,
S / t value (s: throat length t: pitch length) distribution formed in an arc shape from the blade root in the blade height direction toward the blade tip,
The turbine stationary blade, wherein the s / t value is maximized between a blade height direction center and a blade tip and minimized at the blade root. - 前記翼先端の前記ｓ／ｔ値を、前記ｓ／ｔ値の最大値と最小値との中間値以上、かつ前記ｓ／ｔ値の最大値未満とし、
前記翼根元の前記ｓ／ｔ値を、最大ｓ／ｔ値の６５％以上、フリーボルテックス設計時の翼根元のｓ／ｔ値未満としたことを特徴とする請求項4記載のタービン静翼。 The s / t value of the blade tip is not less than an intermediate value between the maximum value and the minimum value of the s / t value and less than the maximum value of the s / t value,
5. The turbine stationary blade according to claim 4, wherein the s / t value of the blade root is 65% or more of the maximum s / t value and less than the s / t value of the blade root at the time of free vortex design. - 前記ｓ／ｔ値を、前記タービン静翼の翼長に対して前記翼根元より７５％以上９５％以下の翼高さ位置で最大とすることを特徴とする請求項５記載のタービン静翼。 The turbine stator blade according to claim 5, wherein the s / t value is maximized at a blade height position of 75% or more and 95% or less from the blade root with respect to a blade length of the turbine stator blade.
- 水を加熱して蒸気を生成する蒸気発生器と、該蒸気発生器で生成した前記蒸気で駆動するタービンと、該タービンを駆動した前記蒸気を復水する復水器とを備える蒸気タービン装置であって、
翼高さ方向翼根元から翼先端に向けて弧状に形成されたｓ／ｔ値（ｓ：スロート長 ｔ：ピッチ長）分布を有し、
前記ｓ／ｔ値を、翼高さ方向中央部と翼先端との間で最大とし、かつ前記翼根元で最小とし、
前記翼先端の前記ｓ／ｔ値を、前記ｓ／ｔ値の最大値と最小値との中間値以上、かつ前記ｓ／ｔ値の最大値未満とし、
前記翼根元の前記ｓ／ｔ値を、最大ｓ／ｔ値の６５％以上フリーボルテックス設計時の翼根元のｓ／ｔ値未満とした低アスペクト比タービン静翼を有する前記タービンを備えることを特徴とする蒸気タービン装置。 A steam turbine apparatus comprising: a steam generator that heats water to generate steam; a turbine that is driven by the steam generated by the steam generator; and a condenser that condenses the steam that has driven the turbine. There,
S / t value (s: throat length t: pitch length) distribution formed in an arc shape from the blade root in the blade height direction toward the blade tip,
The s / t value is maximized between the blade height direction center and the blade tip, and is minimized at the blade root,
The s / t value of the blade tip is not less than an intermediate value between the maximum value and the minimum value of the s / t value and less than the maximum value of the s / t value,
The turbine having a low aspect ratio turbine stationary blade in which the s / t value of the blade root is 65% or more of the maximum s / t value and less than the s / t value of the blade root at the time of free vortex design. Steam turbine equipment.
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| US9719354B2 (en) | 2011-03-30 | 2017-08-01 | Mitsubishi Hitachi Power Systems, Ltd. | Gas turbine with improved blade and vane and flue gas diffuser |
| US10859094B2 (en) | 2018-11-21 | 2020-12-08 | Honeywell International Inc. | Throat distribution for a rotor and rotor blade having camber and location of local maximum thickness distribution |
| US11280199B2 (en) | 2018-11-21 | 2022-03-22 | Honeywell International Inc. | Throat distribution for a rotor and rotor blade having camber and location of local maximum thickness distribution |
| US11378093B2 (en) | 2018-11-21 | 2022-07-05 | Honeywell International Inc. | Throat distribution for a rotor and rotor blade having camber and location of local maximum thickness distribution |
| CN111664122A (en) * | 2020-06-05 | 2020-09-15 | 中国航发沈阳发动机研究所 | Stator guide blade at outlet of outer duct |
| CN113217226A (en) * | 2021-06-02 | 2021-08-06 | 中国航发湖南动力机械研究所 | Paddle-fan-turbine integrated engine |
| CN113217226B (en) * | 2021-06-02 | 2022-08-02 | 中国航发湖南动力机械研究所 | Paddle-fan-turbine integrated engine |
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