JP2022011589A - Blade of rotary machine and rotary machine - Google Patents

Abstract

To suppress intrusion of working fluid into a cavity between a stationary blade stage and a rotor blade stage in a rotary machine.SOLUTION: A blade of a rotary machine comprises: a mainstream region 71 including a first position where an exit angle defined by a rear edge of the blade is a first exit angle; and a hub side region 73 located on a hub side of the mainstream region 71. At least a part of the hub side region 73 has the distribution of an exit angle α that includes a second position where the exit angle is a second exit angle different from the first exit angle and in which a difference in the exit angle α with respect to the first exit angle increases as it approaches the hub side from the second position. An absolute value of a rate of change of the exit angle α at the second position with respect to a position in a span direction of the blade is more than twice an absolute value of a rate of change of the exit angle α at the first position with respect to a position in the span direction.SELECTED DRAWING: Figure 10A

Description

The present disclosure relates to blades of rotary machinery and rotary machinery.

For example, in a gas turbine as an example of a rotary machine, for example, by supplying bleed air from a compressor, the blades are cooled and the blades and the stationary blades are sealed (see, for example, Patent Document 1).

Japanese Unexamined Patent Publication No. 2004-003494

For example, in a rotary machine such as a gas turbine described in Patent Document 1, a stationary blade stage having a plurality of stationary blades and a moving blade stage having a plurality of moving blades are alternately arranged along the axial direction of the rotor. .. For example, in the gas turbine or the like described in Patent Document 1, a cavity is provided between the stationary blade stage and the moving blade stage in a region radially inside, for example, from the end on the hub side of the moving blade. It is configured to supply bleed air from a compressor, for example, so that a high-temperature working fluid such as a combustion gas does not flow into the turbine.
However, depending on the operating conditions of the gas turbine and the like, there is a possibility that a high-temperature working fluid may flow into the above-mentioned cavity. Therefore, it is desired to suppress the inflow of high-temperature working fluid into the above-mentioned cavity.

At least one embodiment of the present disclosure is an object of the present invention to suppress the infiltration of working fluid into the cavity between the stationary blade stage and the moving blade stage in the rotary machine in view of the above circumstances.

(1) The blade of the rotary machine according to at least one embodiment of the present disclosure is
The wings of a rotating machine
A mainstream region including a first position where the exit angle defined by the trailing edge of the wing is the first exit angle.
The hub side region located on the hub side of the mainstream region and the hub side region
Equipped with
At least a part of the hub-side region includes a second position where the outlet angle is a second exit angle different from the first exit angle, and the first position as the second position approaches the hub side. It has a distribution of the exit angles in which the difference in the exit angles with respect to the angle is large.
The absolute value of the rate of change of the exit angle at the second position with respect to the position of the blade in the span direction is twice the absolute value of the rate of change of the exit angle at the first position with respect to the position in the span direction. Exceed.

(2) The rotary machine according to at least one embodiment of the present disclosure is
With multiple static wings,
With multiple blades,
Equipped with
At least one of the plurality of stationary blades or the plurality of moving blades is the blade having the configuration of the above (1).

According to at least one embodiment of the present disclosure, it is possible to suppress the intrusion of working fluid into the cavity between the stationary blade stage and the moving blade stage in the rotary machine.

It is a schematic diagram which shows the whole structure of a gas turbine as an example of a rotary machine. It is a schematic cross-sectional view which shows the gas flow path of a turbine. It is a schematic diagram which enlarged the neighborhood of a platform and an inner shroud about a stationary blade stage and a moving blade stage adjacent to each other along the axial direction. It is a schematic cross-sectional view for demonstrating the exit angle of a stationary blade. It is a schematic cross-sectional view for demonstrating the exit angle of a moving blade. It is a figure which shows the example of the distribution of the circumferential velocity of the combustion gas after passing through a conventional stationary blade, and the example of the distribution of the circumferential velocity of a fluid in a seal region and a cavity. It is the figure which showed the example of the distribution of the static pressure of the combustion gas in the circumferential direction after passing through the conventional stationary blade, and the example of the position of the boundary between the combustion gas and barge air. It is a figure which shows the example of the distribution of the circumferential velocity of the combustion gas after passing through a vane of one embodiment, and the example of the distribution of the circumferential velocity of a fluid in a seal region and a cavity. It is the figure which showed the example of the distribution of the static pressure of the combustion gas in the circumferential direction after passing through the stationary blade of one embodiment, and the example of the position of the boundary between the combustion gas and barge air. It is a figure which shows the example of the distribution of the circumferential velocity of the combustion gas after passing through a conventional rotor blade, and the example of the distribution of the circumferential velocity of a fluid in a seal region and a cavity. It is the figure which showed the example of the distribution of the static pressure of the combustion gas in the circumferential direction after passing through the conventional rotor blade, and the example of the position of the boundary between the combustion gas and barge air. It is a figure which shows the example of the distribution of the circumferential velocity of the combustion gas after passing through the rotor blade of one embodiment, and the example of the distribution of the circumferential velocity of a fluid in a seal region and a cavity. It is the figure which showed the example of the distribution of the static pressure of the combustion gas in the circumferential direction after passing through the moving blade of one embodiment, and the example of the position of the boundary between the combustion gas and barge air. It is a figure which shows the example of the distribution of the circumferential velocity of the combustion gas after passing through the rotor blade of another embodiment, and the example of the distribution of the circumferential velocity of a fluid in a seal region and a cavity. It is the figure which showed the example of the distribution of the static pressure of the combustion gas in the circumferential direction after passing through the moving blade of another embodiment, and the example of the position of the boundary between the combustion gas and barge air. It is a figure which shows an example of the relationship between the position in the span direction, and the exit angle of a stationary blade. It is a figure which shows another example of the relationship between the position in the span direction, and the exit angle of a stationary blade. It is a figure which shows still another example of the relationship between the position in the span direction, and the exit angle of a stationary blade. It is a figure which shows still another example of the relationship between the position in the span direction, and the exit angle of a stationary blade. It is a figure which shows still another example of the relationship between the position in the span direction, and the exit angle of a stationary blade. It is a figure which shows still another example of the relationship between the position in the span direction, and the exit angle of a stationary blade. It is a figure which shows an example of the relationship between the position in a span direction, and the exit angle of a moving blade. It is a figure which shows another example of the relationship between the position in the span direction, and the exit angle of a moving blade. It is a figure which shows still another example of the relationship between the position in the span direction and the exit angle of a moving blade. It is a figure which shows still another example of the relationship between the position in the span direction and the exit angle of a moving blade. It is a figure which shows still another example of the relationship between the position in the span direction and the exit angle of a moving blade. It is a figure which shows still another example of the relationship between the position in the span direction and the exit angle of a moving blade. It is a figure for demonstrating the mainstream area and the hub side area.

Hereinafter, some embodiments of the present disclosure will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc. of the components described as embodiments or shown in the drawings are not intended to limit the scope of the present disclosure to this, and are merely explanatory examples. do not have.
For example, expressions that represent relative or absolute arrangements such as "in one direction", "along a certain direction", "parallel", "orthogonal", "center", "concentric" or "coaxial" are exact. Not only does it represent such an arrangement, but it also represents a tolerance or a state of relative displacement at an angle or distance to the extent that the same function can be obtained.
For example, expressions such as "same", "equal", and "homogeneous" that indicate that things are in the same state not only represent exactly the same state, but also have tolerances or differences to the extent that the same function can be obtained. It shall also represent the existing state.
For example, the expression representing a shape such as a quadrangular shape or a cylindrical shape not only represents a shape such as a quadrangular shape or a cylindrical shape in a geometrically strict sense, but also an uneven portion or a chamfer within the range where the same effect can be obtained. It shall also represent the shape including the part and the like.
On the other hand, the expressions "equipped", "equipped", "equipped", "included", or "have" one component are not exclusive expressions excluding the existence of other components.

In the following description, a gas turbine will be taken as an example of a rotary machine, and some embodiments will be described.
FIG. 1 is a schematic view showing an overall configuration of a gas turbine as an example of a rotary machine, and FIG. 2 is a schematic cross-sectional view showing a gas flow path of the turbine.

(Gas turbine 10)
In some embodiments, as shown in FIG. 1, the gas turbine 10 is configured with a compressor 11, a combustor 12, and a turbine 13 arranged coaxially by a rotor 14 and a generator at one end of the rotor 14. 15 are connected. In the following description, the direction in which the axis of the rotor 14 extends is the axial Da, the circumferential direction around the axis of the rotor 14 is the circumferential Dc, and the direction perpendicular to the axis Ax of the rotor 14 is the radial direction. Let it be Dr.
In the following description, of the axial Da, the upstream side in the flow of the combustion gas FG in the combustion gas flow path 32 described below is referred to as the axial upstream side or simply the upstream side, and the combustion gas in the combustion gas flow path 32 is referred to. The downstream side in the flow of FG is referred to as an axial downstream side or simply a downstream side.
Further, among the circumferential directions Dc, the rotation direction of the rotor 14 is represented as the rotation direction R.

The compressor 11 generates high-temperature and high-pressure compressed air AC by passing the air AI taken in from the air intake through a plurality of stationary blades and moving blades and compressing the air AI. The combustor 12 supplies the fuel FL to the compressed air AC and burns the fuel FL to generate a combustion gas FG which is a high-temperature and high-pressure working fluid. The turbine 13 drives and rotates the rotor 14 by passing the high-temperature and high-pressure combustion gas FG generated by the combustor 12 through a plurality of stationary blades and moving blades, and drives the generator 15 connected to the rotor 14. do.

(Turbine 13)
As shown in FIG. 2, in the turbine 13, each of the plurality of turbine stationary blades (static blades) 21 is configured such that the hub side of the airfoil portion 23 is fixed to the inner shroud 25 and the tip side is fixed to the outer shroud 27. Has been done. In the turbine 13 according to some embodiments, the stationary blade stage 20 is formed by a plurality of stationary blades 21, an inner shroud 25, and an outer shroud 27.
In the turbine 13 according to some embodiments, a plurality of turbine blades (moving blades) 41 are attached to the outer peripheral portion of the rotor disk 16 at intervals in the circumferential direction. Each of the plurality of turbine blades (rotor blades) 41 is configured such that the hub side of the airfoil portion 43 is fixed to the platform 45. In the turbine 13 according to some embodiments, the rotor blade stage 40 is formed by the rotor disk 16 and the plurality of rotor blades 41 attached to the rotor blades 16.

In the turbine 13 according to some embodiments, a plurality of stationary blade stages 20 and rotor blade stages 40 are alternately arranged along the axial direction Da.
In the following description, a plurality of stationary blade stages 20 arranged along the axial direction Da will be referred to as a first stationary blade stage 20A, a second stationary blade stage 20B, a third stationary blade stage, and the like in order from the upstream side. In FIG. 2, the description of the stationary blade stage 20 after the third stationary blade stage is omitted.
Similarly, in the following description, with respect to the plurality of rotor blade stages 40 arranged along the axial direction Da, the first rotor blade stage 40A, the second rotor blade stage 40B, the third rotor blade stage ... It is called. In FIG. 2, the description of the rotor blade stages 40 after the third rotor blade stage is omitted.

In the turbine 13 according to some embodiments, the outer shroud 27 and the split ring 50 arranged on the tip end side of the rotor blade 41 are supported by the casing (turbine casing) 30 via the heat shield ring 39. The inner shroud 25 is supported by the support ring 31. Therefore, the combustion gas flow path 32 through which the combustion gas FG passes is formed along the axial direction Da as a space surrounded by the inner shroud 25, the outer shroud 27, the platform 45, and the dividing ring 50.

The inner shroud 25, the outer shroud 27, and the split ring 50 function as gas path surface forming members. The gas path surface forming member has a gas path surface that partitions the combustion gas flow path 32 and is in contact with the combustion gas FG.

FIG. 3 is an enlarged schematic view of the vicinity of the platform 45 and the inner shroud 25 for the stationary blade stage 20 and the blade stage 40 adjacent to each other along the axial direction Da.
In the turbine 13 according to some embodiments, for example, in the region inside the hub side end 43a of the airfoil portion 43 of the rotor blade 41 in the radial direction, the stationary blade stage 20 and the rotor blade adjacent to each other along the axial Da. A cavity 37 is provided between the step 40 and the step 40.
In the turbine 13 according to some embodiments, in order to suppress the high temperature combustion gas FG deviating from the combustion gas flow path 32 which is the main flow path from flowing into the cavity 37, for example, the platform 45 of the rotor blade 41 or the static one is used. By providing a portion (projecting portions 25a, 45a) projecting in the axial direction Da such as the inner shroud 25 in the blade stage 20, the gap between the stationary blade stage 20 and the blade stage 40 is reduced. For convenience of explanation, the region in which the gap between the stationary blade stage 20 and the moving blade stage 40 is reduced in this way is referred to as a seal region 35.
Further, in the turbine 13 according to some embodiments, in order to suppress the inflow of the combustion gas FG into the cavity 37, for example, the bleed air from the compressor 11 is configured to be supplied as the purge air PA.
However, depending on the operating conditions of the gas turbine 10, the high-temperature combustion gas FG may flow into the cavity 37 through the seal region 35 described above. Therefore, it is desired to suppress the inflow of the high-temperature combustion gas FG into the cavity 37.

Therefore, in the turbine 13 according to some embodiments, the high-temperature combustion gas FG is suppressed from flowing into the cavity 37 by the configuration described below.

(About the behavior of combustion gas FG)
Hereinafter, the behavior of the combustion gas FG will be described before the configuration for suppressing the inflow of the high-temperature combustion gas FG into the cavity 37 is described.
FIG. 4A is a schematic cross-sectional view for explaining the exit angle of the stationary blade 21, and shows a cross section of the airfoil portion 23 cut along the circumferential direction.
FIG. 4B is a schematic cross-sectional view for explaining the exit angle of the rotor blade 41, and shows a cross section of the airfoil portion 43 cut along the circumferential direction.
FIG. 5A is a diagram showing an example of the distribution of the circumferential velocity of the combustion gas FG after passing through the conventional stationary blade and an example of the distribution of the circumferential velocity of the fluid in the seal region 35 and the cavity 37.
FIG. 5B is a diagram showing an example of the distribution of the static pressure of the combustion gas FG after passing through the conventional stationary blade in the circumferential direction and an example of the position of the boundary between the combustion gas FG and the purge air PA.
FIG. 6A is a diagram showing an example of the distribution of the circumferential velocity of the combustion gas FG after passing through the stationary blade 21 of one embodiment and an example of the distribution of the circumferential velocity of the fluid in the seal region 35 and the cavity 37. ..
FIG. 6B is a diagram showing an example of the distribution of the static pressure of the combustion gas FG after passing through the stationary blade 21 of one embodiment in the circumferential direction and an example of the position of the boundary between the combustion gas FG and the purge air PA. be.
FIG. 7A is a diagram showing an example of the distribution of the circumferential velocity of the combustion gas FG after passing through the conventional rotor blade and an example of the distribution of the circumferential velocity of the fluid in the seal region 35 and the cavity 37.
FIG. 7B is a diagram showing an example of the distribution of the static pressure of the combustion gas FG after passing through the conventional rotor blade in the circumferential direction and an example of the position of the boundary between the combustion gas FG and the purge air PA.
FIG. 8A is a diagram showing an example of the distribution of the circumferential velocity of the combustion gas FG after passing through the rotor blade 41 of one embodiment and an example of the distribution of the circumferential velocity of the fluid in the seal region 35 and the cavity 37. ..
FIG. 8B is a diagram showing an example of the distribution of the static pressure of the combustion gas FG after passing through the rotor blade 41 in the circumferential direction and an example of the position of the boundary between the combustion gas FG and the purge air PA. be.
FIG. 9A is a diagram showing an example of the distribution of the circumferential velocity of the combustion gas FG after passing through the blade 41 of another embodiment and an example of the distribution of the circumferential velocity of the fluid in the seal region 35 and the cavity 37. be.
FIG. 9B is a diagram showing an example of the distribution of the static pressure of the combustion gas FG in the circumferential direction after passing through the rotor blade 41 of another embodiment and an example of the position of the boundary between the combustion gas FG and the purge air PA. Is.

For example, as shown in FIGS. 5B and 7B, in the region between the stationary blade stage 20 and the blade stage 40 in the combustion gas flow path 32 as the main flow path through which the combustion gas FG passes, along the circumferential direction Dc. It has a pressure distribution in which the pressure (static pressure) p'of the combustion gas FG changes periodically. Therefore, the combustion gas FG is affected by the pressure distribution that changes periodically when flowing in the circumferential direction Dc.
It should be noted that this pressure distribution does not move in the circumferential direction Dc even after a lapse of time in the state where the output of the turbine 13 does not change.
In FIGS. 5B and 7B, the curve C showing the relationship between the position of the circumferential direction Dc and the static pressure p'of the combustion gas FG is drawn so as to be located outside the radial direction Dr as the static pressure p'is increased. , The smaller the static pressure p', the more it is drawn to be located inside the radial Dr. That is, the curve C shown in FIGS. 5B and 7B does not indicate the position of the radial Dr in the combustion gas flow path 32. It should be noted that the curve C does not indicate the radial position in the combustion gas flow path 32, which is the same in FIGS. 6B, 8B and 9B described later.

For example, as shown in FIGS. 5B and 7B, when the static pressure p'of the combustion gas FG is high in the region between the stationary blade stage 20 and the blade stage 40 in the combustion gas flow path 32, the combustion gas FG is described above. Since the combustion gas FG easily flows into the cavity 37, the position of the boundary BL between the combustion gas FG and the purge air PA supplied to the cavity 37 moves inward in the radial direction. On the contrary, when the static pressure p'of the combustion gas FG is low in the region, it becomes difficult for the combustion gas FG to flow into the cavity 37, so that the position of the boundary BL moves to the outside of the radial Dr. In FIGS. 5B and 7B, the positions of the peaks and valleys in the circumferential direction Dc are deviated between the curve C and the boundary BL, but the influence of the height of the static pressure p'of the combustion gas FG is the radial Dr of the boundary BL. This is because there is a time difference until it appears as a difference in the position of.

Further, the position of the boundary BL moves inward in the radial direction as the time during which the high static pressure p'acts acts, and outwards in the radial direction as the time during which the high static pressure p'acts shortens. Tends to move.
Therefore, in order to suppress the inflow of the combustion gas FG into the cavity 37, it is desirable to shorten the time during which the high static pressure p'is acting.

(Regarding the suppression of the inflow of combustion gas FG on the downstream side of the stationary blade)
About the velocity distribution of the circumferential velocity Vθm of the combustion gas FG in the combustion gas flow path 32 on the downstream side of the stationary blade, the circumferential velocity Vθs of the fluid in the seal region 35, and the circumferential velocity Vθc of the purge air PA in the cavity 37. explain.
As shown in FIG. 5A, the combustion gas FG after passing through the conventional stationary blade has a circumferential velocity component that swivels in the same direction as the rotation direction R of the rotor 14.
Since the cavity 37 is affected by the rotation of the rotor disk 16, the purge air PA has a circumferential velocity component that rotates in the same direction as the rotation direction R of the rotor 14 (rotor disk 16).
The circumferential velocity Vθm of the combustion gas FG after passing through the conventional stationary blade is larger than the circumferential velocity Vθc of the purge air PA.

In FIGS. 5A, 6A, 7A, 8A, and 9A, the position of the line representing the circumferential velocity is from the reference line L0 extending in the radial direction Dr at the center of the circumferential direction Dc on the paper surface to the circumferential direction Dc. It shows that the absolute value of the circumferential velocity increases as the distance increases. Further, when the position of the line representing the circumferential velocity is located on the right side of the paper surface from the reference line L0, it means that the fluid is flowing in the same direction as the rotation direction R of the rotor 14 (rotor disk 16). When the position of the line representing the directional velocity is located on the left side of the paper surface with respect to the reference line L0, it means that the fluid is flowing in the direction opposite to the rotation direction R of the rotor 14 (rotor disk 16).

As shown in FIG. 5A, the fluid in the seal region 35 has a circumferential velocity component that swivels in the same direction as the rotation direction R of the rotor 14. The circumferential velocity Vθs of the fluid in the region outside the radial Dr in the seal region 35 is affected by the circumferential velocity Vθm of the combustion gas FG in the combustion gas flow path 32. The circumferential velocity Vθs of the fluid in the region inside the radial Dr in the seal region 35 is affected by the circumferential velocity Vθc of the purge air PA in the cavity 37.
Therefore, the circumferential velocity Vθs of the fluid in the seal region 35 approaches the circumferential velocity Vθm of the combustion gas FG in the combustion gas flow path 32 as it approaches the outside of the radial Dr, and the purge air in the cavity 37 as it approaches the inside of the radial Dr. It approaches the circumferential velocity Vθc of PA.

As described above, in order to suppress the inflow of the combustion gas FG into the cavity 37, it is desirable to shorten the time during which the high static pressure p'is acting.
Therefore, for example, as shown in FIG. 6A, when the circumferential velocity Vθm of the combustion gas FG in the combustion gas flow path 32 is increased, the circumferential velocity Vθm of the combustion gas FG in the region on the hub side, that is, the region close to the seal region 35 is increased. , The average velocity Vθs (ave) of the circumferential velocity Vθs of the fluid in the seal region 35 becomes large. Specifically, as will be described later, the stationary blade 21 according to some embodiments is close to the seal region 35 by setting the exit angle in the region near the hub side to an angle different from that of the conventional stationary blade. Increase the circumferential velocity Vθm of the combustion gas FG in the region.
By increasing the average velocity Vθs (ave), as shown in FIG. 6B, the position of the boundary BL can be moved to the outside of the radial Dr as compared with the case shown in FIG. 5B.
In FIG. 6A, the circumferential velocity Vθ1 shown by the broken line represents the circumferential velocity when the conventional stationary blade shown in FIG. 5A is used. In FIG. 6A, the average velocity Vθs (ave) 1 in the seal region 35 is the average velocity in the seal region 35 when the conventional stationary blade shown in FIG. 5A is used. The average velocity Vθs (ave) 2 in the seal region 35 is the average velocity in the seal region 35 when the circumferential velocity Vθm of the combustion gas FG in the region close to the seal region 35 is increased.

(Regarding the suppression of the inflow of combustion gas FG on the downstream side of the rotor blade)
About the velocity distribution of the circumferential velocity Vθm of the combustion gas FG in the combustion gas flow path 32 on the downstream side of the rotor blade, the circumferential velocity Vθs of the fluid in the seal region 35, and the circumferential velocity Vθc of the purge air PA in the cavity 37. explain.
As shown in FIG. 7A, the combustion gas FG after passing through the conventional rotor blade has a peripheral velocity component that swivels in the direction opposite to the rotation direction R of the rotor 14.
As described above, since the cavity 37 is affected by the rotation of the rotor disk 16, the purge air PA has a circumferential velocity component that rotates in the same direction as the rotation direction R of the rotor 14 (rotor disk 16).

As shown in FIG. 7A, the fluid in the seal region 35 has a circumferential velocity component that swirls in the direction opposite to the rotation direction R of the rotor 14 in the region outside the radial direction Dr in the seal region 35, and seals. The region inside the radial direction Dr of the region 35 has a circumferential velocity component that swivels in the same direction as the rotation direction R of the rotor 14.
When the gas turbine 10 is an industrial gas turbine, the flow velocity of the combustion gas FG is smaller than that of an aircraft gas turbine or the like, so that the moving blade stage 40 and the stationary blade stage adjacent to each other on the downstream side of the moving blade stage 40 are adjacent to each other. Although the combustion gas FG in the combustion gas flow path 32 between 20 and 20 flows in the direction opposite to the rotation direction R of the rotor 14 as described above, the absolute value | Vθm | of its circumferential velocity Vθm is relatively small. Become. Therefore, assuming that the case where the circumferential velocity Vθs of the fluid in the seal region 35 goes in the same direction as the rotation direction R of the rotor 14, the average velocity Vθs (ave) of the circumferential velocity Vθs of the fluid in the seal region 35 is positive. Is the value of.

As described above, in order to suppress the inflow of the combustion gas FG into the cavity 37, it is desirable to shorten the time during which the high static pressure p'is acting.
Therefore, for example, as shown in FIG. 8A, with respect to the circumferential velocity Vθm of the combustion gas FG in the combustion gas flow path 32, the circumferential velocity Vθm of the combustion gas FG in the region on the hub side, that is, the region close to the seal region 35 is increased. (Reducing the absolute value of the circumferential velocity Vθm) increases the average velocity Vθs (ave) of the circumferential velocity Vθs of the fluid in the seal region 35. Specifically, as will be described later, the moving blade 41 according to some embodiments is close to the seal region 35 by setting the exit angle in the region close to the hub side to an angle different from that of the conventional stationary blade. Increase the circumferential velocity Vθm of the combustion gas FG in the region (decrease the absolute value of the circumferential velocity Vθm).
In the following description, the outlet angle of the rotor blade 41 is set so as to increase the circumferential velocity Vθm of the combustion gas FG in the region close to the seal region 35 (decrease the absolute value of the circumferential velocity Vθm). Called Case 1.

As described above, by increasing the average velocity Vθs (ave), as shown in FIG. 8B, the position of the boundary BL can be moved to the outside of the radial Dr as compared with the case shown in FIG. 7B.
In FIG. 8A, the circumferential velocity Vθ1 shown by the broken line represents the circumferential velocity when the conventional rotor blade shown in FIG. 7A is used. In FIG. 8A, the average velocity Vθs (ave) 1 in the seal region 35 is the average velocity in the seal region 35 when the conventional rotor blade shown in FIG. 7A is used. The average velocity Vθs (ave) 2 in the seal region 35 is the average in the seal region 35 when the circumferential velocity Vθm of the combustion gas FG in the region close to the seal region 35 is increased (the absolute value of the circumferential velocity Vθm is decreased). Speed.

Generally, in a gas turbine called a transonic gas turbine such as a gas turbine for an aircraft or a gas turbine called a supersonic gas turbine, the flow velocity of the combustion gas FG is higher than that of the industrial gas turbine 10. Since it is large, the combustion gas FG in the combustion gas flow path 32 between the moving blade stage 40 and the stationary blade stage 20 adjacent to each other on the downstream side of the moving blade stage 40 is in the direction opposite to the rotation direction R of the rotor 14. The absolute value | Vθm | of the flow and its circumferential velocity Vθm becomes relatively large. Therefore, the average velocity Vθs (ave) of the circumferential velocity Vθs of the fluid in the seal region 35 becomes a negative value.

As described above, in order to suppress the inflow of the combustion gas FG into the cavity 37, it is desirable to shorten the time during which the high static pressure p'is acting.
Therefore, for example, as shown in FIG. 9A, with respect to the circumferential velocity Vθm of the combustion gas FG in the combustion gas flow path 32, the circumferential velocity Vθm of the combustion gas FG in the region on the hub side, that is, the region close to the seal region 35 is reduced. (Increasing the absolute value of the circumferential velocity Vθm) reduces the average velocity Vθs (ave) of the circumferential velocity Vθs of the fluid in the seal region 35 (absolute value of the average velocity Vθs (ave) | Vθs (ave) | Will be larger). Specifically, as will be described later, the moving blade 41 according to some embodiments is close to the seal region 35 by setting the exit angle in the region close to the hub side to an angle different from that of the conventional stationary blade. Decrease the circumferential velocity Vθm of the combustion gas FG in the region (increase the absolute value of the circumferential velocity Vθm).
In the following description, the outlet angle of the rotor blade 41 is set so as to reduce the circumferential velocity Vθm of the combustion gas FG in the region close to the seal region 35 (increase the absolute value of the circumferential velocity Vθm). It is referred to as case 2.

By increasing the absolute value | Vθs (ave) | of the average velocity Vθs (ave), as shown in FIG. 9B, the position of the boundary BL is moved to the outside of the radial Dr as compared with the case shown in FIG. 7B. be able to.
In FIG. 9A, the circumferential speed Vθ1 shown by the broken line is the circumferential speed when a conventional moving blade is used in a gas turbine called a transonic gas turbine or a gas turbine called a supersonic gas turbine. Represents. In FIG. 9A, the average velocity Vθs (ave) 1 in the seal region 35 is the average velocity in the seal region 35 when the above-mentioned conventional rotor blades are used. The average velocity Vθs (ave) 2 in the seal region 35 is the average in the seal region 35 when the circumferential velocity Vθm of the combustion gas FG in the region close to the seal region 35 is reduced (the absolute value of the circumferential velocity Vθm is increased). Speed.

(About the exit angle)
As shown in FIG. 4A, the exit angle α of the stationary blade 21 is an angle formed by the trailing edge 23T of the airfoil portion 23 with respect to the axis Ax.
As shown in FIG. 4B, the outlet angle β of the moving blade 41 is an angle formed by the trailing edge 43T of the airfoil portion 43 with respect to the axis Ax.

FIG. 10A is a diagram showing an example of the relationship between the position in the span direction and the outlet angle α of the stationary blade 21.
FIG. 10B is a diagram showing another example of the relationship between the position in the span direction and the exit angle α of the stationary blade 21.
FIG. 10C is a diagram showing still another example of the relationship between the position in the span direction and the exit angle α of the stationary blade 21.
FIG. 10D is a diagram showing still another example of the relationship between the position in the span direction and the exit angle α of the stationary blade 21.
FIG. 10E is a diagram showing still another example of the relationship between the position in the span direction and the exit angle α of the stationary blade 21.
FIG. 10F is a diagram showing still another example of the relationship between the position in the span direction and the exit angle α of the stationary blade 21.

FIG. 11A is a diagram showing an example of the relationship between the position in the span direction and the outlet angle β of the rotor blade 41.
FIG. 11B is a diagram showing another example of the relationship between the position in the span direction and the exit angle β of the rotor blade 41.
FIG. 11C is a diagram showing still another example of the relationship between the position in the span direction and the exit angle β of the rotor blade 41.
FIG. 11D is a diagram showing still another example of the relationship between the position in the span direction and the exit angle β of the rotor blade 41.
FIG. 11E is a diagram showing still another example of the relationship between the position in the span direction and the exit angle β of the rotor blade 41.
FIG. 11F is a diagram showing still another example of the relationship between the position in the span direction and the exit angle β of the rotor blade 41.
FIG. 12 is a diagram for explaining the mainstream region and the hub side region, and shows the distribution of the exit angle shown in FIG. 10A as an example of the distribution of the exit angle.
It should be noted that FIGS. 11A to 11F describe both the case corresponding to the above-mentioned case 1 and the case of rubbing the outer cylinder in the case 2.

In the present specification, the span direction is a direction connecting the hub side ends 23a and 43a of the airfoil portions 23 and 43 and the tip side ends 23b and 43b at each dimensionless meridional surface length position. Further, in the present specification, the positions of the hub side ends 23a and 43a of the airfoil portions 23 and 43 are set to 0%, the positions of the tip side ends 23b and 43b are set to 100%, and the span direction from the hub side ends 23a and 43a. The position in the span direction is defined by the length of (length L in the span direction).
Further, in FIGS. 10A to 10F and FIGS. 11A to 11F, the curve showing the exit angle according to the embodiment described below is represented by a solid line, and the curve showing the exit angle of the conventional stationary blade and the moving blade is represented by a broken line. However, in the mainstream region 71, which will be described later, since the curve indicating the exit angle according to the embodiment and the curve indicating the exit angle of the conventional stationary blade and the moving blade overlap, the curve of the exit angle of the conventional stationary blade and the moving blade is used. The description is omitted. In other words, in the mainstream region 71, which will be described later, the curve indicating the exit angle according to the embodiment coincides with the curve indicating the exit angle of the conventional stationary blade and the moving blade.

The stationary blade 21 according to FIGS. 10A to 10F and the moving blade 41 according to FIGS. 11A to 11F have the following features.
For example, the stationary blade 21 according to FIGS. 10A to 10F and the moving blade 41 according to FIGS. 11A to 11F are defined by the trailing edges 23T and 43T of the blades 21 and 41, for example, as shown in FIG. A mainstream region 71 including a first position P1 in which the outlet angles α and β are the first exit angles α1 and β1 and a hub side region 73 located on the hub side of the mainstream region 71 are provided.
Further, in the stationary blade 21 according to FIGS. 10A to 10F and the moving blade 41 according to FIGS. 11A to 11F, for example, as shown in FIG. 12, at least a part of the hub side region 73 has an outlet angle α. β includes a second position P2 having a second exit angle α2 and β2 different from the first exit angles α1 and β1, and an exit angle with respect to the first exit angle α1 and β1 as the second position P2 approaches the hub side. It has a distribution of exit angles α and β in which the difference between α and β becomes large.
Further, in the stationary wing 21 according to FIGS. 10A to 10F and the moving wing 41 according to FIGS. 11A to 11F, for example, as shown in FIG. 12, the exit angle α with respect to the position of the wing 21 and 41 in the span direction. The absolute values of Δα / ΔL and Δβ / ΔL at the second position P2 of β | Δα / ΔL |, | Δβ / ΔL | are the exit angles α with respect to the position in the span direction. The rate of change of β at the first position P1 is more than twice the absolute value of Δα / ΔL, Δβ / ΔL | Δα / ΔL |, | Δβ / ΔL |.
In other words, in the stationary blade 21 according to FIGS. 10A to 10F and the moving blade 41 according to FIGS. 11A to 11F, the first position P1 and the second position P2 satisfying the above-mentioned characteristics are present. good.

Absolute values of rate of change of outlet angles α and β at the second position P2 of blades 21 and 41 in the span direction | Δα / ΔL |, | Δβ / By setting ΔL | as described above, the circumferential velocity Vθm of the combustion gas FG in the region close to the seal region 35 can be set so that the inflow of the combustion gas FG into the cavity 37 is suppressed. That is, the absolute value | Vθs (ave) | of the average velocity Vθs (ave) of the circumferential velocity Vθs of the fluid in the seal region 35 can be increased. As a result, it is possible to suppress the inflow of the high-temperature combustion gas FG into the cavity 37, so that it is possible to suppress the occurrence of problems such as local damage due to the inflow of the high-temperature combustion gas FG into the cavity 37.

For example, in the stationary blade 21 according to FIGS. 10A to 10F and the moving blade 41 according to FIGS. 11A to 11F, for example, as shown in FIG. 12, the mainstream region 71 is a mean height position in the span direction, that is, It is preferable to include a position where the length L in the span direction from the hub side is 50%. The hub side region 73 may include at least a region of 0% or more and 5% or less of the length L in the span direction from the hub side.
As a result, the outlet angles α and β of the mainstream region 71 including the mean height position and having a great influence on the performance of the blades 21 and 41 can be set from the viewpoint of the performance required for the blades 21 and 41, and the blades 21 and 41 can be set. The outlet angles α and β in the hub side region 73 can be set in a region close to the hub side so that the above absolute value | Vθs (ave) | can be increased while suppressing the influence on the performance of the above.

For example, in the stationary blade 21 according to FIGS. 10A to 10F and the moving blade 41 according to FIGS. 11A to 11F, for example, as shown in FIG. 12, the first position P1 is the length in the span direction from the hub side. It is preferable that the position is such that L is 50%. The second position P2 is preferably a position where the length L in the span direction from the hub side is less than 5%.
As a result, the outlet angles α and β of the mainstream region 71, which greatly affects the performance of the blades 21 and 41, can be set from the viewpoint of the performance required for the blades 21 and 41, and the influence on the performance of the blades 21 and 41 can be affected. The exit angles α and β in the hub side region 73 can be set in a region close to the hub side so that the above absolute value | Vθs (ave) | can be increased while suppressing.

For example, in the stationary blade 21 according to FIGS. 10A to 10F and the moving blade 41 according to FIGS. 11A to 11F, the hub side region 73 has the rate of change of the exit angles α and β with respect to the position in the span direction Δα / Δ. It is preferable to include a region where L, Δβ / ΔL is within ± 50% of the rate of change of the exit angles α and β at the second position P2. The transition point Pt from the mainstream region 71 to the hub side region 73 may be present in a region of more than 5% and 35% or less of the length L in the span direction from the hub side.
In other words, the transition point Pt is a transition point from the mainstream region 71 to a region having a rate of change within ± 50% of the rate of change of the exit angles α and β at the second position P2.
As a result, the span direction of the hub side region 73 for increasing the above absolute value | Vθs (ave) | while ensuring the span direction length L of the mainstream region 71 that greatly affects the performance of the blades 21 and 41. The length L can be secured.

For example, the exit angles α and β at the transition point Pt may be the maximum value or the minimum value of the exit angles α and β with respect to the position in the span direction.
Specifically, in the stationary blade 21 according to FIGS. 10A to 10F, the exit angle α at the transition point Pt is the minimum value of the exit angle α with respect to the position in the span direction.
In the rotor blade 41 according to Case 1 of FIG. 11A, Case 1 of FIG. 11B, and Case 1 of FIG. 11C, the exit angle β at the transition point Pt is the maximum value of the exit angle β with respect to the position in the span direction.
In the rotor blade 41 according to the case 2 of FIG. 11D, the case 2 of FIG. 11E, and the case 2 of FIG. 11F, the exit angle β at the transition point Pt is the minimum value of the exit angle β with respect to the position in the span direction.

As described above, the outlet angles α and β in the mainstream region 71 should be set from the viewpoint of the performance required for the blades 21 and 41. On the other hand, the exit angles α and β in the hub side region 73 are set in order to increase the above absolute value | Vθs (ave) |. Therefore, since the setting purpose is different between the outlet angles α and β in the mainstream region 71 and the outlet angles α and β in the hub side region 73, the rate of change of the exit angles α and β with respect to the position in the span direction Δα / ΔL, The tendency to appear in Δβ / ΔL may also be different.
Therefore, as described above, the exit angles α and β at the transition point Pt may be the maximum value or the minimum value of the exit angles α and β with respect to the position in the span direction.

For example, in the stationary blade 21 according to FIGS. 10A to 10F, the rate of change Δα / ΔL at the second position P2 may be negative.
In the stationary blade 21 according to FIGS. 10A to 10F, the circumferential speed Vθm of the combustion gas FG increases on the downstream side of the stationary blade 21 as the difference in the angle from the outlet angle α, that is, the axial Da is increased.
In the stationary blade 21 according to FIGS. 10A to 10F, since the rate of change Δα / ΔL at the second position P2 is negative, the exit angle α increases as it approaches the hub side. As a result, the circumferential velocity Vθm of the combustion gas FG in the region of the combustion gas flow path 32 near the hub side can be efficiently increased.

For example, in the stationary blade 21 according to FIGS. 10A to 10F, the outlet angle α may be maximized at a position where the length L in the span direction from the hub side is 0%.
As a result, the circumferential velocity Vθm of the combustion gas FG in the region of the combustion gas flow path 32 near the hub side can be efficiently increased.

For example, the stationary blade 21 according to FIGS. 10A to 10F may include the stationary blade 21 of the most upstream stage (first stationary blade stage 20A).
In the gas turbine 10 or the like, the temperature of the combustion gas FG in the uppermost stream stage is higher than the temperature of the combustion gas FG in the stage downstream of the uppermost stream stage.
Therefore, in the uppermost stream stage where the temperature of the combustion gas FG is the highest, the circumferential velocity Vθm of the combustion gas FG in the region of the combustion gas flow path 32 near the hub side can be increased. As a result, it is possible to suppress the occurrence of defects in the most upstream stage where defects such as local damage due to the inflow of high-temperature combustion gas FG are most likely to occur.

For example, in the rotor blade 41 according to Case 1 in FIGS. 11A to 11F, the rate of change Δβ / ΔL at the second position P2 may be positive.
That is, when the gas turbine 10 is an industrial gas turbine, the average velocity Vθs (ave) of the circumferential velocity Vθs of the fluid in the seal region 35 becomes a positive value as described above. If the rate of change Δβ / ΔL at the second position P2 is positive, the exit angle β becomes smaller as it approaches the hub side. Therefore, the circumferential velocity Vθm of the combustion gas FG in the region of the combustion gas flow path 32 near the hub side (the circumferential velocity Vθm toward the direction opposite to the rotation direction R of the rotor 14) becomes absolute as it approaches the hub side. The value | Vθm | becomes smaller.
As a result, the average velocity Vθs (ave) of the circumferential velocity Vθs of the fluid in the seal region 35 can be increased, and the inflow of the high-temperature combustion gas FG into the cavity 37 can be suppressed.

For example, in the rotor blade 41 according to Case 1 in FIGS. 11A to 11F, the outlet angle β may be minimized at a position where the length L in the span direction from the hub side becomes 0%.
As a result, the absolute value | Vθm | of the circumferential velocity Vθm of the combustion gas FG in the region of the combustion gas flow path 32 near the hub side can be efficiently reduced.

For example, in the rotor blade 41 according to the case 2 in FIGS. 11A to 11F, the rate of change Δβ / ΔL at the second position P2 may be negative.
That is, when the gas turbine 10 is a gas turbine for an aircraft or the like, as described above, the average velocity Vθs (ave) of the circumferential velocity Vθs of the fluid in the seal region 35 becomes a negative value. If the rate of change Δβ / ΔL at the second position P2 is negative, the exit angle β increases as it approaches the hub side. Therefore, the circumferential velocity Vθm of the combustion gas FG in the region of the combustion gas flow path 32 near the hub side (the circumferential velocity Vθm toward the direction opposite to the rotation direction R of the rotor 14) becomes absolute as it approaches the hub side. The value | Vθm | becomes large.
As a result, the average velocity Vθs (ave) of the circumferential velocity Vθs of the fluid in the seal region 35 can be reduced (the absolute value | Vθs (ave) | of the average velocity Vθs (ave) can be increased), and the cavity 37 can be formed. It is possible to suppress the inflow of high-temperature combustion gas FG.

For example, in the rotor blade 41 according to the case 2 in FIGS. 11A to 11F, the outlet angle β may be maximized at a position where the length L in the span direction from the hub side is 0%.
As a result, the absolute value | Vθm | of the circumferential velocity Vθm of the combustion gas FG heading in the direction opposite to the rotation direction R of the rotor 14 in the region of the combustion gas flow path 32 near the hub side is efficiently increased. Can be done.

For example, the moving blade 41 according to FIGS. 11A to 11F may include the moving blade 41 of the most upstream stage (first moving blade stage 40A).
Thereby, in the uppermost stream stage where the temperature of the combustion gas FG becomes the highest, the absolute value | Vθs (ave) | of the average velocity Vθs (ave) of the circumferential velocity Vθs of the fluid in the seal region 35 can be increased. As a result, it is possible to suppress the occurrence of defects in the most upstream stage where defects such as local damage due to the inflow of high-temperature combustion gas FG are most likely to occur.

As described above, in the turbine 13 according to some embodiments, it is possible to suppress the occurrence of defects such as local damage due to the inflow of the high-temperature combustion gas FG into the cavity 37.

The present disclosure is not limited to the above-described embodiment, and includes a modification of the above-mentioned embodiment and a combination of these embodiments as appropriate.
For example, the turbine 13 according to some of the above-described embodiments is the turbine 13 in the gas turbine 10, but the turbine 13 is not limited to the turbine 13 in the gas turbine 10, and may be a turbine in a steam turbine or a turbocharger.

The contents described in each of the above embodiments are grasped as follows, for example.
(1) The blades of the rotary machine according to at least one embodiment of the present disclosure are blades 21 and 41 of the rotary machine (turbine 13). The blades 21 and 41 have a mainstream region 71 including a first position P1 in which the outlet angles α and β defined by the trailing edges 23T and 43T of the blades 21 and 41 are the first exit angles α1 and β1 and a mainstream region 71. A hub-side region 73 located closer to the hub-side. At least a part of the hub side region 73 includes a second position P2 in which the exit angles α and β are different from the first exit angles α1 and β1 and the second exit angles α2 and β2, and the hub is from the second position P2. It has a distribution of exit angles α and β in which the difference between the exit angles α and β with respect to the first exit angles α1 and β1 increases as the distance approaches the side. Absolute values of rate of change of outlet angles α and β at the second position P2 of wings 21 and 41 in the span direction | Δα / ΔL |, | Δβ / ΔL | is the absolute value of the rate of change of the exit angles α and β at the first position P1 with respect to the position in the span direction Δα / ΔL, Δβ / ΔL | Δα / ΔL |, | Δβ / It is more than twice as large as ΔL |.

According to the configuration of (1) above, as described above, the absolute value | Vθs (ave) | of the average velocity Vθs (ave) of the circumferential velocity Vθs of the fluid in the seal region 35 can be increased. Therefore, since it is possible to suppress the inflow of the high-temperature combustion gas FG into the cavity 37, it is possible to suppress the occurrence of problems such as local damage due to the inflow of the high-temperature combustion gas FG into the cavity 37.

(2) In some embodiments, in the configuration of (1) above, the mainstream region 71 includes a mean height position in the span direction (a position where the length L in the span direction from the hub side is 50%). The hub side region 73 includes at least a region of 0% or more and 5% or less of the length in the span direction (length L in the span direction) from the hub side.

According to the configuration of (2) above, the outlet angles α and β of the mainstream region 71 including the mean height position and having a great influence on the performance of the blades 21 and 41 are set from the viewpoint of the performance required for the blades 21 and 41. The outlet angles α and β in the hub side region 73 are set in the region close to the hub side so that the above absolute value | Vθs (ave) | can be increased while suppressing the influence on the performance of the blades 21 and 41. can.

(3) In some embodiments, in the configuration of (1) or (2) above, the first position P1 is a position where the length in the span direction from the hub side is 50%. The second position P2 is a position where the length in the span direction from the hub side is less than 5%.

According to the configuration of (3) above, the outlet angles α and β of the mainstream region 71, which greatly affects the performance of the blades 21 and 41, can be set from the viewpoint of the performance required for the blades 21 and 41, and the blade 21 and The exit angles α and β in the hub side region 73 can be set in a region close to the hub side so that the above absolute value | Vθs (ave) | can be increased while suppressing the influence on the performance of 41.

(4) In some embodiments, in any of the configurations (1) to (3) above, the hub-side region 73 has a rate of change of outlet angles α and β with respect to a position in the span direction Δα / ΔL. A region is included in which Δβ / ΔL has a rate of change within ± 50% of the rate of change of the exit angle angles α and β at the second position P2, Δα / ΔL and Δβ / ΔL. The transition point Pt from the mainstream region 71 to the hub side region 73 exists in a region of more than 5% and 35% or less of the length in the span direction from the hub side.

According to the configuration of (4) above, the absolute value | Vθs (ave) | is increased while ensuring the length of the mainstream region 71 in the span direction, which greatly affects the performance of the blades 21 and 41. The length L in the span direction of the hub side region 73 can be secured.

(5) In some embodiments, in the configuration of (4) above, the exit angles α and β at the transition point Pt are maximum values or minimum values of the exit angles α and β with respect to the position in the span direction.

As described above, the outlet angles α and β in the mainstream region 71 should be set from the viewpoint of the performance required for the blades 21 and 41. On the other hand, the exit angles α and β in the hub side region 73 are set in order to increase the above absolute value | Vθs (ave) |. Therefore, since the setting purpose is different between the outlet angles α and β in the mainstream region 71 and the outlet angles α and β in the hub side region 73, the rate of change of the exit angles α and β with respect to the position in the span direction Δα / ΔL, The tendency to appear in Δβ / ΔL may also be different.
Therefore, as in the configuration of (5) above, the exit angles α and β at the transition point Pt may be the maximum value or the minimum value of the exit angles α and β with respect to the position in the span direction.

(6) In some embodiments, in any of the configurations (1) to (5) above, the wing is a stationary wing 21. The rate of change Δα / ΔL at the second position P2 is negative.

In the stationary blade 21, the circumferential velocity Vθm of the combustion gas FG increases on the downstream side of the stationary blade 21 as the difference between the outlet angle α, that is, the angle with the axial Da is increased.
In the configuration of (6) above, since the rate of change Δα / ΔL at the second position P2 is negative, the exit angle α increases as it approaches the hub side.
Therefore, according to the configuration of (6) above, the circumferential velocity Vθm of the combustion gas FG in the region of the combustion gas flow path 32 near the hub side can be efficiently increased.

(7) In some embodiments, in the configuration of (6) above, the outlet angle α is maximized at a position where the length in the span direction from the hub side is 0%.

According to the configuration of (7) above, the circumferential velocity Vθm of the combustion gas FG in the region of the combustion gas flow path 32 near the hub side can be efficiently increased.

(8) In some embodiments, in the configuration of (6) or (7), the blade is the vane 21 of the most upstream stage (first vane stage 20A) in the rotary machine (turbine 13). ..

In the gas turbine 10 or the like, the temperature of the combustion gas FG in the uppermost stream stage is higher than the temperature of the combustion gas FG in the stage downstream of the uppermost stream stage.
According to the configuration of (8) above, in the uppermost stream stage where the temperature of the combustion gas FG is the highest, the circumferential velocity Vθm of the combustion gas FG in the region of the combustion gas flow path 32 near the hub side can be increased. can. As a result, it is possible to suppress the occurrence of defects in the most upstream stage where defects such as local damage due to the inflow of high-temperature combustion gas FG are most likely to occur.

(9) In some embodiments, in any of the configurations (1) to (5), the blade is a moving blade 41. The rate of change Δβ / ΔL at the second position P2 is positive.

In the configuration of (9) above, since the rate of change Δβ / ΔL at the second position P2 is positive, the exit angle β becomes smaller as it approaches the hub side. Therefore, the circumferential velocity Vθm of the combustion gas FG in the region of the combustion gas flow path 32 near the hub side (the circumferential velocity Vθm toward the direction opposite to the rotation direction R of the rotor 14) becomes absolute as it approaches the hub side. The value | Vθm | becomes smaller.
Therefore, according to the configuration of (9) above, the average velocity Vθs (ave) of the circumferential velocity Vθs of the fluid in the seal region 35 can be increased, and the high-temperature combustion gas FG flows into the cavity 37. Can be suppressed.

(10) In some embodiments, in the configuration of (9) above, the outlet angle β is minimized at a position where the length in the span direction from the hub side is 0%.

According to the configuration of (10) above, the absolute value | Vθm | of the circumferential velocity Vθm of the combustion gas FG in the region of the combustion gas flow path 32 near the hub side can be efficiently reduced.

(11) In some embodiments, in any of the configurations (1) to (5), the blade is a moving blade 41. The rate of change Δβ / ΔL at the second position P2 is negative.

As described above, when the gas turbine 10 is a gas turbine for an aircraft or the like, the average velocity Vθs (ave) of the circumferential velocity Vθs of the fluid in the seal region 35 becomes a negative value as described above.
In the configuration of (11), since the rate of change Δβ / ΔL at the second position P2 is negative, the exit angle β becomes larger as it approaches the hub side. Therefore, the circumferential velocity Vθm of the combustion gas FG in the region of the combustion gas flow path 32 near the hub side (the circumferential velocity Vθm toward the direction opposite to the rotation direction R of the rotor 14) becomes absolute as it approaches the hub side. The value | Vθm | becomes large.
Therefore, according to the configuration of (11) above, the average velocity Vθs (ave) of the circumferential velocity Vθs of the fluid in the seal region 35 is made small (the absolute value of the average velocity Vθs (ave) | Vθs (ave) | is made large). It is possible to suppress the inflow of high-temperature combustion gas FG into the cavity 37.

(12) In some embodiments, in the configuration of (11) above, the outlet angle β is maximized at a position where the length in the span direction from the hub side is 0%.

According to the configuration of (12) above, the absolute value of the circumferential velocity Vθm of the combustion gas FG heading in the direction opposite to the rotation direction R of the rotor 14 in the region of the combustion gas flow path 32 near the hub side | Vθm | Can be increased efficiently.

(13) In some embodiments, in any of the configurations (9) to (12), the blade is a blade of the most upstream stage (first blade stage 40A) in the rotary machine (turbine 13). 41.

According to the configuration of (13) above, in the uppermost stream where the temperature of the combustion gas FG is the highest, the absolute value of the average velocity Vθs (ave) of the circumferential velocity Vθs of the fluid in the seal region 35 | Vθs (ave) | Can be increased. As a result, it is possible to suppress the occurrence of defects in the most upstream stage where defects such as local damage due to the inflow of high-temperature combustion gas FG are most likely to occur.

(14) The rotary machine (turbine 13) according to at least one embodiment of the present disclosure includes a plurality of stationary blades 21 and a plurality of moving blades 41. In the rotary machine (turbine 13) according to at least one embodiment of the present disclosure, at least one of the plurality of stationary blades 21 or the plurality of rotor blades 41 is any one of the above configurations (1) to (13). Wings 21 and 41.

According to the configuration of the above (14), it is possible to suppress the occurrence of defects such as local damage due to the inflow of the high-temperature combustion gas FG into the cavity 37.

10 Gas turbine 13 Turbine 14 Rotor 20 Static blade stage 21 Turbine stationary blade (static blade)
32 Combustion gas flow path 35 Sealed area 37 Cavity 40 Blade stage 41 Turbine blade (rotor blade)
71 Mainstream area 73 Hub side area

Claims (14)

The wings of a rotating machine
A mainstream region including a first position where the exit angle defined by the trailing edge of the wing is the first exit angle.
The hub side region located on the hub side of the mainstream region and the hub side region
Equipped with
At least a part of the hub-side region includes a second position where the outlet angle is a second exit angle different from the first exit angle, and the first position as the second position approaches the hub side. It has a distribution of the exit angles in which the difference between the exit angles and the exit angles is large.
The absolute value of the rate of change of the exit angle at the second position with respect to the position in the span direction of the blade is twice the absolute value of the rate of change of the exit angle at the first position with respect to the position in the span direction. Over rotating machine wings. The mainstream region includes a mean height position in the span direction.
The blade of a rotary machine according to claim 1, wherein the hub-side region includes at least a region of 0% or more and 5% or less of the length in the span direction from the hub side. The first position is a position where the length in the span direction from the hub side is 50%.
The blade of the rotary machine according to claim 1 or 2, wherein the second position is a position where the length in the span direction from the hub side is less than 5%. The hub-side region includes a region in which the rate of change of the outlet angle with respect to the position in the span direction is within ± 50% of the rate of change of the exit angle at the second position.
The transition point from the mainstream region to the hub side region is according to any one of claims 1 to 3 existing in a region of more than 5% and 35% or less of the length in the span direction from the hub side. The wing of the rotating machine described. The blade of a rotary machine according to claim 4, wherein the outlet angle at the transition point is a maximum value or a minimum value of the exit angle with respect to a position in the span direction. The wing is a stationary wing and
The blade of a rotary machine according to any one of claims 1 to 5, wherein the rate of change at the second position is negative. The blade of the rotary machine according to claim 6, wherein the outlet angle is maximum at a position where the length in the span direction from the hub side is 0%. The blade of the rotary machine according to claim 6 or 7, wherein the blade is a stationary blade of the most upstream stage in the rotary machine. The wing is a moving blade,
The blade of a rotary machine according to any one of claims 1 to 5, wherein the rate of change at the second position is positive. The blade of a rotary machine according to claim 9, wherein the outlet angle is minimized at a position where the length in the span direction from the hub side is 0%. The wing is a moving blade,
The blade of a rotary machine according to any one of claims 1 to 5, wherein the rate of change at the second position is negative. The blade of a rotary machine according to claim 11, wherein the outlet angle is maximum at a position where the length in the span direction from the hub side is 0%. The blade of the rotary machine according to any one of claims 9 to 12, wherein the blade is a moving blade of the most upstream stage in the rotary machine. With multiple static wings,
With multiple blades,
Equipped with
The rotary machine in which at least one of the plurality of stationary blades or the plurality of moving blades is the blade according to any one of claims 1 to 13.

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