JP7264685B2 - Turbine vanes and turbines - Google Patents

Description

The present invention relates to turbine vanes and turbines.

A gas turbine includes a compressor, a combustor, and a turbine. The compressor compresses outside air to produce high pressure air. The combustor mixes and combusts fuel with this high-pressure air to generate high-temperature, high-pressure combustion gas. A turbine is rotationally driven by the combustion gases. The rotational power of the turbine is taken out from the shaft end and used for various purposes.

A turbine includes a rotating shaft that rotates about its axis, turbine rotor blade stages arranged along the axial direction on the rotating shaft, a casing that covers the rotating shaft and the turbine rotor blade stages from the outside, and an inner peripheral surface of the casing. and has turbine stator blade stages alternately arranged in the axial direction with the above-mentioned turbine rotor blade stages.

The turbine stator vane stage has a plurality of turbine stator vanes arranged in a circumferential direction with respect to the axis. Each turbine stator vane extends radially with respect to the axis. Fluid (combustion gas) flowing from one axial side collides with these turbine stationary blades to change the flow direction and is guided to the following turbine rotor blade stage. Here, in the turbine stator blade, of the extension length in the radial direction, the portion on the tip side (outside in the radial direction) and the portion on the hub side (inside in the radial direction) are the center It is known that a flow component called a secondary flow is more likely to occur than in a part. A secondary flow is a flow that advances while swirling from the leading edge to the trailing edge of a turbine stationary blade. When the secondary flow is dominant, the energy loss of the main stream flowing along the turbine stator blades becomes large. As a result, turbine efficiency may be reduced.

Therefore, for example, a configuration described in Patent Document 1 below has been proposed. In the turbine stator vane (nozzle vane) described in Patent Document 1, the trailing edge of the vane is curved in the circumferential direction, thereby increasing the throat pitch ratio at the central portion in the vane height direction. It is said that this causes the flow to concentrate in the central portion and suppress the secondary flow.

Japanese Patent No. 4724034

However, in the turbine stator vane described in Patent Document 1, since the trailing edge where the flow velocity is relatively high is curved, the friction loss between the fluid and the turbine stator vane increases. As a result, the effect of suppressing the secondary flow is offset by the friction loss, which may limit the efficiency improvement of the turbine.

SUMMARY OF THE INVENTION An object of the present invention is to provide a turbine stator vane and a turbine in which the efficiency is further improved by suppressing the secondary flow.

A turbine blade according to an aspect of the present invention is a turbine stator blade provided in a flow path of a fluid flowing along an axis, the blade extending in the radial direction of the axis and having a ventral surface on the high-pressure side when viewed in the radial direction. , and a blade body having an airfoil-shaped cross-section with a back surface serving as a low-pressure side, wherein the blade body comprises a tip side portion positioned radially outermost, and a tip side portion provided radially inward of the tip side portion. and a hub side portion provided further radially inward of the central portion, wherein at least one of the tip side portion and the hub side portion is the airfoil in the central portion. With respect to a certain reference airfoil, the leading edge, which is the edge on the upstream side, is located on the ventral side in the direction perpendicular to the chord of the reference airfoil, and the trailing edge, which is the edge on the downstream side, is located on the chord. The trailing edge of at least one of the tip side portion and the hub side portion is twisted so as to be located on the back side in the orthogonal direction, and the amount of twisting with respect to the reference airfoil is smaller than that of the leading edge. The amount of edge twist is greater than zero .

According to the above configuration, in at least one of the tip side portion and the hub side portion, the leading edge is on the ventral side in the direction orthogonal to the chord of the reference airfoil, which is the airfoil in the central portion. and twisted so that the trailing edge is located on the dorsal side in the direction perpendicular to the chord. As a result, in the tip side portion and the hub side portion, the portion where the pressure (static pressure) is lowest in the entire area in the axial direction shifts from the trailing edge side to the leading edge side. As a result, a pressure gradient is formed from the center to the tip or hub side from the leading edge to the trailing edge. This pressure gradient can force the secondary flow against the tip side or hub side. That is, it is possible to reduce the loss due to the growth of the secondary flow.
Furthermore, according to the above configuration, the wetted area on the trailing edge side can be reduced by making the amount of twisting of the trailing edge smaller than that of the leading edge. By reducing the wetted area, it is possible to reduce the friction loss of the fluid passing through the trailing edge. Here, since the flow velocity is high on the trailing edge side, friction loss is likely to occur when the wetted area increases. However, according to the above configuration, since the wetted area is suppressed, such friction loss can be effectively reduced.

In the above turbine stator vane, the front edge of the central portion may be formed in a straight line extending in the radial direction when viewed in the circumferential direction with respect to the axis.

According to the above configuration, at the central portion of the turbine stator vane, the leading edge forms a straight line extending in the radial direction. As a result, an increase in the wetted area can be suppressed compared to, for example, the case where the entire front edge is curved instead of straight. As a result, an increase in friction loss can be suppressed.

In the turbine stator vane, when viewed from the axial direction, the leading edge of the tip side portion may extend toward the ventral surface side as it extends radially outward.

According to the above configuration, in the side portion of the tip, the front edge is inclined toward the ventral side as it goes radially outward. As a result, in the tip side portion, the portion where the pressure (static pressure) is lowest in the entire area in the axial direction shifts from the trailing edge side (downstream side) to the leading edge side. As a result, a pressure gradient is formed from the central portion to the side portion of the chip as it moves from the leading edge to the position where the static pressure is the smallest. This pressure gradient can force the secondary flow against the tip side. That is, it is possible to reduce the loss due to the growth of the secondary flow.

In the above turbine stator vane, when viewed from the axial direction, the front edge of the hub side portion may extend inwardly in the radial direction while being inclined toward the ventral surface side.

According to the above configuration, in the hub side portion, the front edge is inclined toward the ventral side as it goes radially inward. As a result, in the hub side portion, the portion where the pressure (static pressure) is lowest in the entire area in the axial direction shifts from the trailing edge side (downstream side) to the leading edge side (upstream side). As a result, a pressure gradient is formed from the central portion to the hub side portion as it moves from the front edge to the position where the static pressure is the lowest. This pressure gradient can force the secondary flow against the hub side. That is, it is possible to reduce the loss due to the growth of the secondary flow.

In the above turbine stator vane, when viewed from the axial direction, the tip side portion may have a trailing edge that extends toward the rear surface side as it extends radially outward.

According to the above configuration, in the side portion of the tip, the trailing edge is inclined toward the rear side as it goes radially outward. As a result, in the tip side portion, the portion where the pressure (static pressure) is lowest in the entire area in the axial direction shifts from the trailing edge side to the leading edge side (upstream side). As a result, a pressure gradient is formed from the central portion to the side portion of the chip as it moves from the leading edge to the position where the static pressure is the smallest. This pressure gradient can force the secondary flow against the tip side. That is, it is possible to reduce the loss due to the growth of the secondary flow.

In the above turbine stator vane, when viewed from the axial direction, the hub side portion may have a trailing edge that extends toward the rear side as it extends radially inward.

According to the above configuration, in the hub side portion, the trailing edge is inclined toward the rear side as it goes radially outward. As a result, in the hub side portion, the portion where the pressure (static pressure) is lowest in the entire area in the axial direction shifts from the trailing edge side to the leading edge side (upstream side). As a result, a pressure gradient is formed from the central portion to the hub side portion as it moves from the front edge to the position where the static pressure is the lowest. This pressure gradient can force the secondary flow against the hub side. That is, it is possible to reduce the loss due to the growth of the secondary flow.

In the above turbine stator vane, the leading edge of the tip side portion may extend upstream in a radially outward direction when viewed in a circumferential direction with respect to the axis.

In the above turbine stator vane, the front edge of the hub side portion may extend toward the upstream side as it extends radially inward when viewed in the circumferential direction with respect to the axis.

In the above turbine stator vane, the trailing edge of the tip side portion may extend downstream in a radially outward direction when viewed in a circumferential direction with respect to the axis.

In the above turbine stator vane, the hub side portion may have a trailing edge extending radially inwardly toward the downstream side when viewed in a circumferential direction with respect to the axis.

A turbine according to one aspect of the present invention includes a rotating shaft extending along an axis, a plurality of turbine rotor blade stages arranged axially on the rotating shaft at intervals, and and a plurality of turbine stator vane stages having a plurality of turbine stator vanes according to any one of the above aspects alternately arranged with.

According to the above configuration, it is possible to provide a turbine that can be operated more efficiently by suppressing the formation of a secondary flow in the turbine stator vane.

According to the present invention, it is possible to provide a turbine stationary blade and a turbine in which the efficiency is further improved by suppressing the secondary flow.

It is a mimetic diagram showing composition of a turbine concerning an embodiment of the present invention. It is the figure which looked at the turbine stator blade which concerns on embodiment of this invention from the circumferential direction with respect to an axis. 1 is a view of a turbine stator blade according to an embodiment of the present invention viewed from a radial direction with respect to an axis; FIG. 1 is a perspective view showing the configuration of a turbine stationary blade according to an embodiment of the present invention; FIG. It is a figure which shows the pressure distribution (isobar) in the back side of the turbine stationary blade which concerns on embodiment of this invention. 4 is a graph showing the static pressure distribution in the chord direction of the turbine stator blade according to the embodiment of the present invention; It is the figure which looked at the turbine stator vane which concerns on the modification of embodiment of this invention from the circumferential direction with respect to an axis. FIG. 5 is a view showing a further modification of the turbine stator blade according to the embodiment of the present invention, and is a view of the turbine stator blade viewed from the circumferential direction with respect to the axis. FIG. 5 is a cross-sectional view showing the configuration of a turbine stationary blade according to a modification of the embodiment of the invention;

A first embodiment of the present invention will be described with reference to FIGS. 1 to 6. FIG. The turbine 100 according to this embodiment is suitably used for a turboshaft engine mounted on a helicopter. Although not shown in detail, the turboshaft engine consists of a compressor that compresses external air to generate high-pressure air, and a combustor that mixes and burns fuel in the high-pressure air to generate high-temperature, high-pressure combustion gas. , a turbine 100 driven in rotation by combustion gases, and a rotor coaxially connecting the compressor and turbine 100 . Rotational force of the rotor is extracted to the outside through a transmission or the like, and is used to rotate the main rotor and tail rotor in the case of a helicopter.

Next, the configuration of turbine 100 will be described. As shown in FIG. 1 , the turbine 100 has a rotating shaft 1 , turbine rotor blade stages 2 , and turbine stator vane stages 3 . The rotating shaft 1 has a cylindrical shape extending along the axis Ac. A plurality (two) of turbine rotor blade stages 2 are provided on the outer peripheral surface of the rotating shaft 1 at intervals in the direction of the axis line Ac. Each turbine rotor blade stage 2 has a plurality of turbine rotor blades 20 arranged in a circumferential direction with respect to the axis Ac. The turbine rotor blade 20 has a rotor blade body 21 having an airfoil cross section and a platform 22 provided radially inside the rotor blade body 21 . Furthermore, the split ring 4 faces the radially outer end of the rotor blade main body 21 .

The turbine stator blade stages 3 are alternately arranged with the turbine rotor blade stages 2 in the direction of the axis Ac. Specifically, each turbine stator blade stage 3 is arranged downstream of each turbine rotor blade stage 2 . The turbine stator vane stage 3 has a plurality of turbine stator vanes 30 arranged in a circumferential direction with respect to the axis Ac. Each turbine stator vane 30 includes a stator vane body 31 (blade body) having an airfoil cross section, a tip shroud 32 provided at the radially outer end of the stator vane body 31, and a radially inner end. and a hub shroud 33 . Although not shown in detail, the tip shroud 32 is fixed to the inner peripheral surface of the casing.

A transition piece 5 of a combustor is connected to the upstream side of the turbine 100 described above. The combustion gas flowing through the transition piece 5 is rectified while passing through the turbine stator blade stage 3 and collides with the turbine rotor blade stage 2 . Thereby, a rotational force is applied to the rotating shaft 1 .

Next, the configuration of the turbine stationary blade 30 will be described with reference to FIGS. 2 to 4. FIG. FIG. 2 is a diagram of the turbine stator blade 30 viewed from the direction of the axis O. As shown in FIG. As shown in FIG. 2, the turbine stator vane 30 has the tip shroud 32, the stator vane main body 31, and the hub shroud 33 from the radially outer side to the inner side. The stationary blade main body 31 has a tip side portion 31A, a central portion 31B, and a hub side portion 31C from the radially outer side to the inner side. A radially outer end of the tip side portion 31A is connected to the tip shroud 32 . The tip-side radially inner shroud is integrally connected to the radially outer end of the central portion 31B. The radially outer end of the hub side portion 31C is integrally connected to the radially inner end of the central portion 31B. A radially inner end of the hub side portion 31</b>C is connected to the hub shroud 33 .

As shown in FIG. 3, the tip side portion 31A, the central portion 31B, and the hub side portion 31C all have an airfoil cross-sectional shape. More specifically, this airfoil has a ventral surface S1 on the high pressure side and a back surface S2 on the low pressure side when viewed in the radial direction. The ventral surface S1 is recessed toward the downstream side. The back surface S2 is swollen toward the downstream side. Of the connecting portion between the ventral surface S1 and the back surface S2, the edge facing the upstream side is the leading edge 6, and the edge facing the downstream side is the trailing edge 7. As shown in FIG. The end portion including the front edge 6 is smoothly curved from the ventral surface S1 side to the back surface S2 side. At the end including the trailing edge 7, the ventral surface S1 and the dorsal surface S2 intersect at an acute angle.

In FIG. 3, the solid line indicates the airfoil cross section of the tip side portion 31A and the hub side portion 31C, and the dashed line indicates the airfoil cross section of the central portion 31B. Here, the airfoil of the central portion 31B is called a reference airfoil Wc. Further, a straight line connecting the leading edge 6c and the trailing edge 7c of the reference airfoil Wc is called a reference chord line Ch, and a direction perpendicular to the reference chord line Ch is called an orthogonal direction Dc. In this case, as shown in FIG. 3, in the tip side portion 31A and the hub side portion 31C, the leading edge 6d is located on the ventral surface S1 side in the orthogonal direction Dc with respect to the reference airfoil Wc. On the other hand, the trailing edge 7d is located on the back surface S2 side in the orthogonal direction Dc with respect to the reference airfoil Wc. That is, the airfoils of the tip side portion 31A and the hub side portion 31C are twisted counterclockwise with respect to the reference airfoil Wc when viewed from the outside in the radial direction. Furthermore, in the tip side portion 31A and the hub side portion 31C, the amount of twist with respect to the reference airfoil Wc is relatively large on the leading edge 6d side and relatively small on the trailing edge 7d side. Note that the tip side portion 31A and the hub side portion 31C have the same amount of twist. In the hub side portion 31C, it is desirable that the leading edge 6d and the trailing edge 7c are twisted in a region of about 5% to 30% or less of the radial height of the stator blade main body 31. In 31A, it is desirable that the twist is formed in an area of about 70 to 95% or more of the radial height.

Accordingly, when viewed in the direction of the axis O, as shown in FIG. 2, the front edge 6d and the rear edge 7d of the tip side portion 31A and the hub side portion 31C obliquely extend toward the downstream side. Specifically, in the tip side portion 31A, the leading edge 6d and the trailing edge 7d are inclined downstream from the radially inner side toward the outer side. In the hub side portion 31C, the front edge 6d and the rear edge 7d are inclined downstream from the radially outer side toward the inner side. On the other hand, the front edge 6c and the rear edge 7c of the central portion 31B extend linearly in the radial direction. With such a configuration, the turbine stator blade 30 has a shape as shown in FIG. 4 when viewed obliquely.

When the turbine stator blade is viewed from the ventral surface side (the ventral surface side in the circumferential direction) (when viewed from the bottom side in FIG. 3), in the tip side portion 31A, the leading edge 6d moves upstream as it goes radially outward. extending towards. Further, in the hub side portion 31C, the front edge 6d extends toward the upstream side as it goes radially inward. Further, in the tip side portion 31A, the trailing edge 7d extends toward the downstream side as it goes radially outward. Further, in the hub side portion 31C, the trailing edge 7d extends toward the downstream side as it goes radially inward.

Next, behavior of the turbine stator blade 30 according to the present embodiment will be described with reference to FIGS. 5 and 6. FIG. FIG. 5 shows the static pressure distribution (isobar) of the fluid on the back surface S2 of the turbine stator blade 30, with the left side of the drawing being the leading edge 6 side and the right side being the trailing edge 7 side. The upper portion in the drawing is the tip side portion 31A, and the lower portion is the hub side portion 31C. As shown in the figure, a pressure gradient is formed on the rear surface S2 such that the static pressure gradually decreases from the front edge 6 side to the rear edge 7 side (chain line arrow in FIG. 5). Further, in the vicinity of the tip side portion 31A and in the vicinity of the hub side portion 31C, the intervals between the isobars are narrowed, and the ends of the isobars are located closer to the front edge 6 than the central portion 31B. That is, as shown in FIG. 6, in the chord direction, the position P1 where the static pressure is the lowest in the tip side portion 31A and the hub side portion 31C is ahead of the position P2 where the static pressure is the lowest in the central portion 31B. It will be positioned on the edge 6 side.

Here, in the turbine stator blade 30, among the radial extension lengths, the tip side portion 31A and the hub side portion 31C are more likely to generate a flow component called a secondary flow than the central portion 31B. It has been known. The secondary flow is a flow that advances while swirling from the leading edge 6 toward the trailing edge 7 of the turbine stationary blade 30 . If the secondary flow becomes dominant, the energy loss of the main stream flowing along the turbine stationary blade 30 will increase. As a result, the efficiency of turbine 100 may decrease.

However, according to the above configuration, in at least one of the tip side portion 31A and the hub side portion 31C, the leading edge 6d has the reference airfoil Wc, which is the airfoil in the central portion 31B. It is positioned on the ventral surface S1 side in the direction orthogonal to the chord, and is twisted so that the trailing edge 7d is positioned on the back surface S2 side in the direction orthogonal to the chord. As a result, in the tip side portion 31A and the hub side portion 31C, the portion where the pressure (static pressure) is lowest in the entire area in the direction of the axis Ac shifts from the trailing edge 7d side to the leading edge 6d side. As a result, a pressure gradient is formed from the central portion 31B toward the tip side portion 31A or the hub side portion 31C from the front edge 6d toward the position P1 where the pressure (static pressure) is the smallest. This pressure gradient can force the secondary flow against tip side 31A or hub side 31C. That is, it is possible to reduce the loss due to the growth of the secondary flow. As a result, the efficiency of turbine 100 can be improved.

Furthermore, according to the above configuration, in the tip side portion 31A and the hub side portion 31B, the amount of twisting of the trailing edge 7d is smaller than that of the leading edge 6d, so that the wetted area of the trailing edge 7d can be reduced. can. By reducing the wetted area, the friction loss of the fluid passing through the trailing edge 7d can be suppressed. Here, since the flow velocity is higher on the trailing edge 7d side than on the leading edge 6d side, friction loss is likely to occur when the wetted area increases. However, according to the above configuration, since the wetted area is suppressed, such friction loss can be effectively reduced.

In addition, according to the above configuration, in the central portion 31B of the turbine stationary blade 30, the front edge 6c is formed in a linear shape extending in the radial direction. As a result, an increase in the wetted area can be suppressed compared to, for example, the case where the entire front edge 6 is curved rather than straight. As a result, an increase in friction loss can be suppressed.

In addition, according to the above configuration, in the tip side portion 31A, the front edge 6d is inclined toward the ventral surface S1 side and the trailing edge 7d is inclined toward the back surface S2 side as it goes radially outward. . As a result, in the tip side portion 31A, the portion where the pressure (static pressure) is the lowest in the entire area in the direction of the axis Ac shifts from the trailing edge 7d side to the leading edge 6d side. As a result, a pressure gradient is formed from the central portion 31B toward the tip side portion 31A from the leading edge 6d toward the position P1 where the static pressure is the smallest. This pressure gradient can force the secondary flow against the tip side 31A. That is, it is possible to reduce the loss due to the growth of the secondary flow.

Further, according to the above configuration, in the hub side portion 31C, the front edge 6d is inclined toward the ventral surface S1 and the rear edge 7d is inclined toward the back surface S2 as it goes radially inward. As a result, in the hub side portion 31C, the portion where the pressure (static pressure) is the lowest in the entire area in the direction of the axis Ac shifts toward the front edge 6d. As a result, a pressure gradient is formed from the central portion 31B to the hub side portion 31C from the front edge 6d toward the position P1 where the static pressure is the smallest. This pressure gradient can force the secondary flow against the hub side 31C. That is, it is possible to reduce the loss due to the growth of the secondary flow.

The embodiments of the present invention have been described above. Various changes and modifications can be made to the above configuration without departing from the gist of the present invention. For example, in the above embodiment, an example in which twist is formed with respect to the reference airfoil Wc in both the tip side portion 31A and the hub side portion 31C has been described. However, as shown in FIG. 7 or 8, it is also possible to employ a configuration in which only one of the tip side portion 31A and the hub side portion 31C is twisted. In this case, as shown in FIG. 9, when adopting a configuration provided with an insert member 90 for forming a cooling flow path inside the turbine stationary blade 30, the insert member 90 is arranged from the end where the twist is not formed. 90 can be easily inserted.

Furthermore, in the above embodiment, an example in which the turbine stator vane 30 is applied to a turboshaft engine mounted on a helicopter has been described. However, the application target of the turbine stator vane 30 is not limited to the turboshaft engine. As another example of application, the above turbine stator vane 30 is applied to any engine that requires a reduction in the number of stages in the blade row and high-load, low-aspect-ratio blades for structural simplification and cost reduction. Is possible. More specifically, the turbine stator vanes 30 can be suitably used for aircraft engines such as vertical take-off and landing aircraft, flying vehicles, and drones. The aspect ratio mentioned above refers to the ratio of the blade height to the chord length of the blade. The chord length is the length of the line segment connecting the leading edge 6 and the trailing edge 7 . For example, when this aspect ratio is 1 or less, it can be said that the aspect ratio is low.

DESCRIPTION OF SYMBOLS 100... Turbine 1... Rotating shaft 2... Turbine moving blade stage 3... Turbine stationary blade stage 4... Split ring 5... Tailpiece 6, 6c, 6d... Leading edge 7, 7c, 7d... Trailing edge 20... Turbine moving blade 21... Moving blade body 22 Platform 30 Turbine stator blade 31 Stator blade body 32 Tip shroud 33 Hub shroud 31A Tip side portion 31B Central portion 31C Hub side portion Ac Axis line Ch Reference chord line Dc Orthogonal Direction S1... Abdominal surface S2... Back surface Wc... Reference airfoil

Claims (11)

A turbine stator vane provided in a flow path of a fluid flowing along an axis,
a blade body extending in the radial direction of the axis and having an airfoil-shaped cross-section formed with a ventral surface on the high-pressure side and a back surface on the low-pressure side when viewed in the radial direction;
The wing body is
a tip side portion positioned radially outermost;
a central portion provided radially inward of the tip side portion;
a hub side portion provided further radially inward of the central portion;
has
At least one of the tip-side portion and the hub-side portion has a leading edge that is an upstream edge with respect to the reference airfoil that is the airfoil in the central portion and that is perpendicular to the chord of the reference airfoil. It is twisted so that the trailing edge, which is the edge on the downstream side, is located on the ventral side in the direction of the blade and is located on the dorsal side in the direction perpendicular to the chord,
The trailing edge on at least one of the tip side and the hub side has a smaller amount of twist with respect to the reference airfoil than the leading edge, and the trailing edge has an amount of twist greater than zero.
turbine vane. 2. The turbine stator vane according to claim 1, wherein the central portion has a straight leading edge extending radially when viewed in a circumferential direction with respect to the axis. 3. The turbine stator vane according to claim 1, wherein, when viewed from the axial direction, in the tip side portion, a leading edge extends obliquely toward the ventral surface side as it goes radially outward. 4. The turbine stator vane according to any one of claims 1 to 3 , wherein, when viewed from the axial direction, in the hub side portion, a leading edge extends toward the ventral surface side as it extends inward in the radial direction. . The turbine stator vane according to any one of claims 1 to 4 , wherein, when viewed from the axial direction, the tip side portion has a trailing edge that extends obliquely toward the rear surface side as it extends radially outward. . The turbine stator vane according to any one of claims 1 to 5 , wherein, when viewed from the axial direction, the hub side portion has a trailing edge that extends toward the rear surface side while being inclined toward the radially inner side. . The turbine stator vane according to any one of claims 1 to 6 , wherein, in the tip side portion, a leading edge extends upstream as it goes radially outward when viewed in a circumferential direction with respect to the axis. The turbine stator vane according to any one of claims 1 to 7 , wherein in the hub side portion, a leading edge extends toward the upstream side as it goes radially inward when viewed in the circumferential direction with respect to the axis. The turbine stator vane according to any one of claims 1 to 8 , wherein in the tip side portion, the trailing edge extends downstream as it goes radially outward when viewed in the circumferential direction with respect to the axis. 10. The turbine stator vane according to any one of claims 1 to 9 , wherein, in the hub side portion, a trailing edge extends downstream as it goes radially inward when viewed in a circumferential direction with respect to the axis. a rotating shaft extending along the axis;
a plurality of turbine blade stages axially spaced on the axis of rotation;
a plurality of turbine stator vane stages comprising a plurality of turbine stator vanes according to any one of claims 1 to 10 alternating with the turbine rotor blade stages in the axial direction;
turbine with

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