JP7356397B2 - High temperature parts and rotating machinery - Google Patents

Description

TECHNICAL FIELD This disclosure relates to high temperature components and rotating machinery.

For example, in a machine such as a gas turbine through which a high-temperature working gas flows, the parts that make up the machine include high-temperature parts that require cooling with a cooling medium. As a cooling structure for such a high-temperature component, it is known that the high-temperature component is cooled by circulating cooling air inside the component (see, for example, Patent Document 1).

Japanese Patent Application Publication No. 2015-92074

In machines such as gas turbines that operate with high-temperature working gas, the loss of heat through cooling generally leads to a decrease in the thermal efficiency of the machine. Therefore, it is desirable to efficiently cool high-temperature components using as little cooling medium as possible. Therefore, it is desirable to increase the flow rate of the cooling medium in the cooling passage by reducing the cross-sectional area of the cooling passage, thereby improving the cooling capacity.
However, as the cross-sectional area of the flow passage becomes smaller, there is a possibility that the risk of the cooling passage being blocked by foreign matter increases.

In view of the above-mentioned circumstances, at least one embodiment of the present disclosure aims to suppress the risk of blockage due to foreign matter in the cooling passage of high-temperature components.

(1) A high-temperature component according to at least one embodiment of the present disclosure,
a plurality of first cooling passages extending linearly;
The extending direction of the first cooling passage is spaced apart from the first cooling passage in a perpendicular direction of a plane including the extending direction of the plurality of first cooling passages, and communicates with any of the first cooling passages. a plurality of second cooling passages extending along;
Equipped with
The maximum value of the cross-sectional area of each of the first cooling passages is larger than the maximum value of the cross-sectional area of the second cooling passage closest to the first cooling passage in a cross section perpendicular to the extending direction.

(2) A rotating machine according to at least one embodiment of the present disclosure includes the high-temperature component configured as described in (1) above.

According to at least one embodiment of the present disclosure, it is possible to suppress the risk of blockage due to foreign matter in the cooling passage of a high-temperature component.

1 is a schematic diagram showing the overall configuration of a gas turbine as an example of a rotating machine. FIG. 2 is a cross-sectional view showing a gas flow path of a gas turbine. It is a perspective view about one of the division bodies which constitute the division ring concerning some embodiments. It is a perspective view about one of the division bodies which constitute the division ring concerning some embodiments. FIG. 4 is a cross-sectional view taken along arrow A in FIG. 3. FIG. FIG. 4 is a sectional view taken in the direction of arrow B in FIG. 3; 4 is an enlarged perspective view of a part of the divided body shown in FIG. 3. FIG. 6 is a sectional view taken along arrow C in FIG. 5. FIG. FIG. 6 is a sectional view taken along arrow D in FIG. 5; 6 is a diagram showing an embodiment of a cross section taken in the direction of arrow E in FIG. 5. FIG. 6 is a diagram showing another embodiment of a cross section taken in the direction of arrow E in FIG. 5. FIG. FIG. 6 is a diagram illustrating a part of a cross section taken along the line CC in FIG. 5 for a divided body according to some embodiments. 6 is a diagram showing a part of an embodiment of a cross section taken along line FF in FIG. 5. FIG. 6 is a diagram illustrating a part of an embodiment of a cross section taken along the line GG in FIG. 5. FIG. 6 is a diagram showing a part of another embodiment of a cross section taken along line FF in FIG. 5. FIG. It is a graph showing how the cross-sectional area of the first cooling passage and the second cooling passage changes depending on the position in the axial direction. FIG. 3 is a diagram that also includes graphs showing the relationship between the axial position and each value in the divided body according to one embodiment. 6 is a diagram illustrating a part of a cross section taken along line FF in FIG. 5 regarding yet another embodiment. FIG. 6 is a diagram illustrating a part of a cross section taken along line FF in FIG. 5 regarding yet another embodiment. FIG. FIG. 2 is a perspective view of a portion of the divided body on the upstream side in the axial direction Da according to some embodiments. FIG. 2 is a perspective view of a portion of the divided body on the upstream side in the axial direction Da according to some embodiments. It is a figure which shows an example of the shape of the flow path cross section of a 1st cooling passage or a 2nd cooling passage. It is a figure which shows an example of the shape of the flow path cross section of a 1st cooling passage or a 2nd cooling passage. 6 is a diagram illustrating a part of a cross section taken along line FF in FIG. 5 regarding yet another embodiment. FIG. 6 is a diagram illustrating a part of a cross section taken along line FF in FIG. 5 regarding yet another embodiment. FIG.

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, and are merely illustrative examples. do not have.
For example, expressions expressing relative or absolute positioning such as "in a certain direction,""along a certain direction,""parallel,""orthogonal,""centered,""concentric," or "coaxial" are strictly In addition to representing such an arrangement, it also represents a state in which they are relatively displaced with a tolerance or an angle or distance that allows the same function to be obtained.
For example, expressions such as "same,""equal," and "homogeneous" that indicate that things are in an equal state do not only mean that things are exactly equal, but also have tolerances or differences in the degree to which the same function can be obtained. It also represents the existing state.
For example, expressions expressing shapes such as squares and cylinders do not only refer to shapes such as squares and cylinders in a strict geometric sense, but also include uneven parts and chamfers to the extent that the same effect can be obtained. Shapes including parts, etc. shall also be expressed.
On the other hand, the expressions "comprising,""comprising,""comprising,""containing," or "having" one component are not exclusive expressions that exclude the presence of other components.

In the following description, high-temperature components according to some embodiments will be described using high-temperature components used in gas turbines as an example.
FIG. 1 is a schematic diagram showing the overall configuration of a gas turbine 10 as an example of a rotating machine. FIG. 2 is a cross-sectional view showing a gas flow path of the gas turbine 10.

In this embodiment, as shown in FIG. 1, the gas turbine 10 includes a compressor 11, a combustor 12, and a turbine 13 arranged coaxially with a rotor 14, and a generator 15 at one end of the rotor 14. connected. In the following description, the direction in which the axis Ax of the rotor 14 extends is referred to as the axial direction Da, the circumferential direction centered on the axis of the rotor 14 is referred to as the circumferential direction Dc, and the direction perpendicular to the axis Ax of the rotor 14 is referred to as the radial direction. Let the direction be Dr.

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

Further, as shown in FIG. 2, in the turbine 13, the turbine stationary blade (stator vane) 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. There is. The turbine rotor blade (rotor blade) 41 is configured such that a base end portion of an airfoil portion 43 is fixed to a platform 45 . The outer shroud 27 and the split ring 50 disposed on the tip side of the rotor blade 41 are supported by the casing (turbine casing) 30 via the heat shield ring 35, and the inner shroud 25 is supported by the support ring 31. has been done. 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 split ring 50.

Note that the inner shroud 25, outer shroud 27, and split ring 50 function as gas path surface forming members. The gas path surface forming member defines the combustion gas flow path 32 and has a gas path surface with which the combustion gas FG comes into contact.

The combustor 12, the rotor blades 41 (for example, the platform 45), the stationary blades 21 (for example, the inner shroud 25 and the outer shroud 27), the split ring 50, etc. are high-temperature components used in a high-temperature environment where the combustion gas FG comes into contact with them. , requiring cooling with a cooling medium. In the following description, as an example of a cooling structure for high-temperature components, a cooling structure for a ring segment 50 of the gas turbine 10 will be described in which a plurality of segment bodies 51 are arranged annularly along the circumferential direction Dc.

FIG. 3 is a perspective view of one of the divided bodies 51 that constitute the divided ring 50 according to some embodiments.
FIG. 4 is a perspective view of one of the divided bodies 51 constituting the divided ring 50 according to some embodiments, and shows a state before attachment of a closing member 517, which will be described later.
FIG. 5 is a sectional view taken in the direction of arrow A in FIG.
FIG. 6 is a cross-sectional view taken in the direction of arrow B in FIG.
FIG. 7 is an enlarged perspective view of a part of the divided body 51 shown in FIG. 3. As shown in FIG.
FIG. 8 is a sectional view taken along arrow C in FIG.
FIG. 9 is a cross-sectional view taken along arrow D in FIG.
FIG. 10 is a diagram showing an embodiment of a cross section taken in the direction of arrow E in FIG.
FIG. 11 is a diagram showing another embodiment of a cross section taken in the direction of arrow E in FIG.

(About the divided body 51)
The divided ring 50 according to some embodiments is composed of a plurality of divided bodies 51 arranged annularly in the circumferential direction Dc. As shown in FIGS. 3 to 7, each divided body 51 includes a plate-shaped main body portion 53 having a cooling passage 6 therein, and a protrusion portion 55 provided to protrude from the main body portion 53. As shown in FIGS. In the divided body 51 according to some embodiments, the protrusion 55 includes a protrusion 55 on the upstream side in the axial direction Da, and a protrusion 55 on the downstream side in the axial direction Da.
In the divided body 51 according to some embodiments, the outer surface 532 on the outside in the radial direction Dr of the main body portion 53 and the side surface 55a facing the upstream side in the axial direction Da of the protruding portion 55 on the downstream side in the axial direction Da are connected to each other. 57.
In the divided body 51 according to some embodiments, the protrusion 55 is separated from the outer surface 532 of the main body 53 by an inlet opening 64a of the cooling passage 6, which will be described later.
In the divided body 51 according to some embodiments, the side surface 55a facing the upstream side in the axial direction Da of the protruding portion 55 on the downstream side in the axial direction Da is an intersecting surface extending in a direction crossing the outer surface 532 of the main body portion 53. It is.
In the divided body 51 according to some embodiments, the connecting portion 57 is connected to one end 571 connected to the surface (outer surface 532) of the main body portion 53 and to the intersecting surface (side surface 55a) of the protruding portion 55. It has the other end 573 and extends from one end 571 to the other end 573 across an inlet opening 64a which will be described later.

As shown in FIG. 2, the divided body 51 is arranged such that the inner surface 531 of the main body portion 53 on the inside in the radial direction Dr faces the combustion gas flow path 32 through which the combustion gas FG flows. A rotor blade 41 that rotates around the rotor 14 is arranged inside the main body portion 53 in the radial direction Dr with a certain gap provided therebetween. In order to prevent thermal damage caused by high-temperature combustion gas FG, a plurality of axial passages (cooling passages) 6 extending in the axial direction Da are formed in the main body portion 53.
A plurality of cooling passages 6 are arranged in parallel in the circumferential direction Dc.

Although not shown, in the gas turbine 10 according to one embodiment, cooling air CA is supplied to each divided body 51 according to some embodiments from the outer surface 532 side of the main body 53 on the outside in the radial direction Dr. It is configured as follows. The cooling air CA supplied to the divided body 51 convectively cools the main body portion 53 of the divided body 51 while flowing through the cooling passage 6 and being discharged into the combustion gas FG.

In the divided body 51 according to some embodiments, the protrusion 55 constitutes a hook 59 for attaching the divided body 51 to the casing 30 side of the gas turbine 10. For example, in the divided body 51 according to some embodiments, as shown in FIG. It is supported by the casing (turbine casing) 30 via 35.

(About cooling passage 6)
Cooling passages 6 according to some embodiments will be described below.
For convenience of explanation regarding the cooling passage 6, it is assumed that positions P1 to P5 in the axial direction Da are the positions shown in FIG. Positions P1 to P5 are located in order from the upstream side to the downstream side in the axial direction Da. For example, the position P1 is assumed to be the position of the upstream side connection end 61a, which will be described later. Further, for example, the position P5 is the position of the downstream connecting end 61b, which will be described later.
The cooling passage 6 according to some embodiments includes a plurality of first cooling passages 61 extending linearly in the axial direction Da, and extending along the extending direction (axial direction Da) of the first cooling passage 61. It includes a plurality of second cooling passages 62 and an introduction passage 64.

(First cooling passage 61)
Each of the plurality of first cooling passages 61 is spaced apart from each other in the circumferential direction Dc. The first cooling passages 61 adjacent to each other in the circumferential direction Dc are separated by a first partition wall 71.
Each of the plurality of first cooling passages 61 includes an upstream connecting end 61a that is connected to the second cooling passage 62 via a first folded passage 66, which will be described later.
Each of the plurality of first cooling passages 61 includes a downstream connection end 61b connected to the introduction passage 64 via a second folded passage 65, which will be described later.
Note that each of the plurality of first cooling passages 61 is also referred to as a downstream passage 61.

(Second cooling passage 62)
Each of the plurality of second cooling passages 62 is spaced apart from the first cooling passage 61 in the perpendicular direction (radial direction Dr) of a plane including the extending direction (axial direction Da) of the plurality of first cooling passages 61. The first cooling passage 61 extends along the extending direction (axial direction Da) of the first cooling passage 61 so as to communicate with any one of the first cooling passages 61, respectively.
Each of the plurality of second cooling passages 62 is spaced apart from each other in the circumferential direction Dc. The second cooling passages 62 adjacent to each other in the circumferential direction Dc are separated by a second partition wall 72.

In the divided body 51 according to some embodiments, as shown in FIGS. 5 and 6, a plurality of second cooling passages 62 are arranged at a radial Dr position close to the inner surface 531 when viewed from the circumferential direction Dc. The plurality of first cooling passages 61 are arranged at radial Dr positions farther from the inner surface 531 than the plurality of second cooling passages 62.

Note that the end surface 71a of the first partition wall 71 on the downstream side in the axial direction Da may be an inclined surface inclined inward in the radial direction Dr, as shown in FIGS. 5, 6, and 9. However, it may extend parallel to the radial direction Dr.

(First return passage 66)
In the divided body 51 according to some embodiments, one second cooling passage 62 is connected to one first cooling passage 61. Each first cooling passage 61 and a second cooling passage 62 communicating with the first cooling passage 61 are connected to each other by each of a plurality of first folded passages 66 .
The plurality of first folding passages 66 are arranged near the end of the main body portion 53 on the upstream side in the axial direction Da, and are connected to the end of the first cooling passage 61 on the upstream side in the axial direction Da and the second cooling passage 62. The end portion on the upstream side in the axial direction Da is connected.
For example, as in one embodiment shown in FIG. 10, each of the plurality of first folding passages 66 may be spaced apart from each other in the circumferential direction Dc. That is, the first folding passages 66 that are adjacent to each other in the circumferential direction Dc are preferably separated by the folding passage partitioning wall 76.
Thereby, the first folding passages 66 adjacent to each other along the circumferential direction Dc can be separated from each other. Furthermore, since the folded passage partition wall 76 functions as a heat transfer member for the cooling air CA flowing through the first folded passage 66, the cooling capacity can be improved.
In the following description, the first folding passage 66 is also referred to as the intermediate folding passage 66.

Note that the first folding passage 66 does not need to be partitioned by the folding passage partition wall 76; for example, as in another embodiment shown in FIG. 11, the first folding passage 66 may be divided into one header space. An intermediate header portion 66A may be provided.

(Introduction passage 64)
The divided body 51 according to some embodiments includes an introduction passage 64, as shown in FIGS. 3 to 8. The introduction passage 64 is spaced apart from the first cooling passage 61 on the opposite side to the plurality of second cooling passages 62 in the radial direction Dr, and is an extension of the first cooling passage 61 so as to communicate with each of the plurality of first cooling passages 61. It extends along the longitudinal direction (axial direction Da) and the plate width direction (circumferential direction Dc) of the main body portion 53.
In the divided body 51 according to some embodiments, as shown in FIG. 8, the passage width along the circumferential direction Dc of the introduction passage 64 is the same as that of the plurality of first cooling passages 61 substantially equal to the placement range. That is, in the divided body 51 according to some embodiments, the introduction passage 64 is a single passage that is not separated in the circumferential direction Dc.
Note that the introduction passage 64 is also referred to as an upstream passage 64.

An inlet opening 64a is formed at the upstream end of the introduction passage 64 in the axial direction Da. The inlet opening 64a is a slit opening extending along the plate width direction (circumferential direction Dc) of the main body portion 53.
In addition, in the divided body 51 according to some embodiments, as described above, the protrusion portion 55 on the downstream side in the axial direction Da is separated from the outer surface 532 of the main body portion 53 by the inlet opening 64a.

(Second return passage 65)
In the divided body 51 according to some embodiments, the introduction passage 64 and the plurality of first cooling passages 61 are connected by a second folded passage 65.
In the divided body 51 according to some embodiments, the second folded passage 65 is disposed near the end of the main body portion 53 on the downstream side in the axial direction Da, and is located near the end of the introduction passage 64 on the downstream side in the axial direction Da. and the downstream end of the first cooling passage 61 in the axial direction Da are connected to each other.
In addition, in the following description, the second folding passage 65 is also referred to as the entrance side folding passage 65.

(Outlet side header section 80)
The divided body 51 according to some embodiments includes a plurality of outlet side header parts 80. In the divided body 51 according to some embodiments, each of the plurality of second cooling passages 62 has an end on the downstream side in the axial direction Da connected to one of the plurality of outlet side header parts 80. In the divided body 51 according to some embodiments, a plurality of second cooling passages 62 are connected to one outlet side header section 80. In the example shown in FIG. 10, the ends of six second cooling passages 62 that are adjacent to each other in the circumferential direction Dc are connected to the upstream side of one outlet header section 80 in the axial direction Da. In some embodiments, a plurality of outlet side header parts 80 are formed in the divided body 51.

An inner wall 82 on the downstream side in the axial direction Da of each outlet header section 80 is provided with a hole for discharging the cooling air CA that has flowed into the outlet header section 80 to the outside of the outlet header section 80, that is, to the outside of the divided body 51. Two outlet passages 83 are formed. The outlet passage 83 opens into the combustion gas FG at the downstream end 511 of the divided body 51 in the axial direction Da.

(Flow of cooling air CA)
In the divided body 51 according to some embodiments, the cooling air CA supplied from the outside of the divided body 51 to the outer surface 532 side of the main body portion 53 on the outside in the radial direction Dr is transferred from the inlet opening 64a of the introduction passage 64 to the introduction passage. 64 and flows in the introduction passage 64 toward the downstream side in the axial direction Da.
The cooling air CA that has passed through the introduction passage 64 flows into each of the first cooling passages 61 via the inlet-side folded passage 65 and flows through each of the first cooling passages 61 toward the upstream side in the axial direction Da.
The cooling air CA that has passed through each of the first cooling passages 61 flows into each of the second cooling passages 62 via the intermediate folded passages 66 and flows through each of the second cooling passages 62 toward the downstream side in the axial direction Da. do.
The cooling air CA flowing through each of the second cooling passages 62 is collected at each outlet side header section 80 and discharged from the outlet passage 83 to the outside of the divided body 51 .

(Regarding the risk of cooling passage blockage)
In machines that operate with high-temperature working gas, such as the gas turbine 10, the loss of heat through cooling generally leads to a decrease in the thermal efficiency of the machine. Therefore, it is desirable to efficiently cool high-temperature components using as little cooling medium as possible. Therefore, by reducing the flow cross-sectional area of the cooling passage, that is, the cross-sectional area of the cooling passage that appears in a cross section perpendicular to the extending direction of the cooling passage, the flow velocity of the cooling medium in the cooling passage is increased and the cooling capacity is improved. This is desirable.
However, as the cross-sectional area of the flow passage becomes smaller, there is a possibility that the risk of the cooling passage being blocked by foreign matter increases.

In the conventional split body, the cooling passages are generally arranged in a single layer at one radial direction Dr position close to the combustion gas flow path 32 through which the combustion gas FG flows.
On the other hand, in the divided body 51 according to some embodiments, the cross-sectional area of the second cooling passage 62 is made larger than that of the cooling passage in the conventional divided body in order to suppress the risk of blocking the cooling passage. There is. In the divided body 51 according to some embodiments, the flow velocity of the cooling air CA is higher than that of the conventional divided body by making the flow passage cross-sectional area of the second cooling passage 62 larger than that of the cooling passage in the conventional divided body. In order to compensate for the cooling capacity that decreases due to the decrease, the first cooling passage 61 is arranged outside the second cooling passage 62 in the radial direction Dr. That is, in the divided bodies 51 according to some embodiments, the cooling passages 6 are arranged doubly in the radial direction Dr.
Thereby, the cross-sectional area of the cooling passage 6 can be increased while ensuring cooling capacity compared to the case where only one of the plurality of first cooling passages 61 or the plurality of second cooling passages 62 is provided. Therefore, compared to the case where only one of the plurality of first cooling passages 61 or the plurality of second cooling passages 62 is provided, that is, the case where the cooling passages are arranged in a single layer as in the conventional split body, the cooling capacity is increased. The risk of blockage in the cooling passage 6 can be suppressed while ensuring the following.
Furthermore, by using the divided bodies 51 according to some embodiments, the reliability of the gas turbine 10 can be improved.

(Regarding the cross-sectional area of the cooling passage 6)
FIG. 12 is a diagram showing a part of a cross section taken along the line CC in FIG. 5 regarding the divided body 51 according to some embodiments.
FIG. 13 is a diagram showing a part of an embodiment of a cross section taken along line FF in FIG.
FIG. 14 is a diagram showing a part of an embodiment of a cross section taken along line GG in FIG.
FIG. 15 is a diagram showing a part of another embodiment of a cross section taken along the line FF in FIG.
FIG. 16 is a graph showing how the cross-sectional areas of the first cooling passage 61 and the second cooling passage 62 change depending on the position in the axial direction Da.
FIG. 17 shows the relationship between the position in the axial direction Da and the temperature Ta of the cooling air CA, the relationship between the position in the axial direction Da and the cross-sectional area S of the cooling passage 6, and the relationship between the axial direction Da and the cross-sectional area S of the cooling passage 6 in the divided body 51 according to one embodiment. FIG. 3 is a diagram that also includes graphs showing the relationship between the position in the axial direction Da and the cooling side heat transfer coefficient hc, and the relationship between the position in the axial direction Da and the combustion gas side heat transfer coefficient hg.

The axial direction Da position of the CC arrow cross section in FIG. is the stacked position.
The axial direction Da position of the FF arrow cross section in FIG. 5 is, for example, a position between positions P3 and P4, and the first cooling passage 61 and the second cooling passage 62 are stacked in the radial direction Dr. It's the location.
The axial direction Da position of the GG arrow cross section in FIG. 5 is, for example, a position between position P1 and position P2, and the first cooling passage 61 and the second cooling passage 62 are stacked in the radial direction Dr. It's the location.

For convenience of illustration, the graph is plotted so that the cross-sectional area S1 of the first cooling passage 61 is larger than the cross-sectional area S2 of the second cooling passage 62 in the section from position P4 to position P5 in the axial direction Da in FIG. However, the cross-sectional area S1 of the first cooling passage 61 and the cross-sectional area S2 of the second cooling passage 62 may be equal.

For example, as shown in FIG. 16, in some embodiments, the first cooling passage 61 is configured such that the cross-sectional area S1 increases from the downstream side to the upstream side in the axial direction Da. Further, as shown in FIG. 16, for example, in some embodiments, the cross-sectional area S1 of the first cooling passage 61 is at least in the section from position P1 to position P4 in the axial direction Da. The area S1 is larger than the cross-sectional area S2 of the second cooling passage 62.
Thereby, the flow velocity of the cooling air CA in the first cooling passage 61 can be suppressed and the static pressure can be increased. Therefore, the static pressure in the first cooling passage 61 located upstream of the second cooling passage 62 with respect to the flow direction of the cooling air CA can be improved, so that the flow velocity of the cooling air CA in the second cooling passage 62 can be increased. , the cooling capacity in the second cooling passage 62 can be improved.
Moreover, compared to the case where the cross-sectional area S1 of the first cooling passage 61 is equal to the cross-sectional area S2 of the second cooling passage 62, the sum of the pressure losses of the first cooling passage and the second cooling passage can be made smaller.
In some embodiments, the cross-sectional dimension of the second cooling passage 62, that is, the dimension in the direction perpendicular to the axial direction Da, is such that if the cross-section of the second cooling passage 62 is circular, the diameter is 0. If the cross section of the second cooling passage 62 is rectangular, the length of one side is 0.1 mm or more and 2.0 mm or less.

For example, as shown in FIG. 16, in some embodiments, the cross-sectional area S1 of the first cooling passage 61 may be constant from position P5 to position P4. The cross-sectional area S1 of the first cooling passage 61 may increase monotonically from the position P4 to the position P3. The cross-sectional area S1 of the first cooling passage 61 may increase monotonically from the position P3 to the position P2. The cross-sectional area S1 of the first cooling passage 61 may be constant from the position P2 to the position P1.
Note that the rate at which the cross-sectional area S1 increases from the position P3 to the position P2 may be greater than the rate at which the cross-sectional area S1 increases from the position P4 to the position P3.

Further, as shown by the broken line a1 in FIG. 16, for example, the cross-sectional area S1 of the first cooling passage 61 may increase monotonically at a constant increasing rate from the position P4 to the position P2.
As shown by a broken line a2 in FIG. 16, for example, the cross-sectional area S2 of the second cooling passage 62 decreases toward the downstream side from the position P1 to an arbitrary position downstream of the position P1 in the axial direction Da. It's okay.

With reference to FIG. 17, the relationship between the temperature Ta of the cooling air CA, the cross-sectional area S of the cooling passage 6, the heat transfer coefficient hb on the main body side, the heat transfer coefficient hg on the combustion gas side, and the position in the axial direction Da will be explained. . Note that the cooling side heat transfer coefficient hc is the heat transfer coefficient between the cooling air CA and the wall forming the cooling passage 6, and the combustion gas side heat transfer coefficient hg is the heat transfer coefficient between the combustion gas FG and the main body 53. is the heat transfer coefficient between
In the graph of FIG. 17, in order to explain the tendency of change of each value, the tendency of change of each value is shown in a simplified manner.

Among the temperatures Ta of the cooling air CA, the temperature Ta1 of the cooling air CA in the first cooling passage 61 increases from the downstream side to the upstream side in the axial direction Da. The temperature Ta2 of the cooling air CA in the second cooling passage 62 increases from the upstream side to the downstream side in the axial direction Da.

Of the cross-sectional area S of the cooling passage 6, the cross-sectional area S1 of the first cooling passage 61 tends to increase from the downstream side to the upstream side in the axial direction Da, as described above. As described above, the cross-sectional area S2 of the second cooling passage 62 is constant regardless of the position Da in the axial direction.

Since the cross-sectional area S1 of the first cooling passage 61 tends to increase from the downstream side to the upstream side in the axial direction Da, the flow velocity of the cooling air CA in the first cooling passage 61 increases from the downstream side to the upstream side in the axial direction Da. It tends to decrease as you go.
Therefore, among the cooling side heat transfer coefficients hc, the heat transfer coefficient hc1 between the cooling air CA and the wall portion forming the first cooling passage 61 tends to decrease from the downstream side to the upstream side in the axial direction Da.
Note that the heat transfer coefficient hc2 between the cooling air CA and the wall portion forming the second cooling passage 62 is constant regardless of the position Da in the axial direction.

The combustion gas side heat transfer coefficient hg has a higher value at a position Da in the axial direction facing the tip of the rotor blade 41 than at other positions.

(Relationship between cross-sectional area S1 and cross-sectional area S2)
In the divided body 51 according to some embodiments, the cross-sectional area (channel area) of the cooling passage 6 is set in consideration of the tendency of change of each value shown in FIG.
For example, in the divided body 51 according to some embodiments, the maximum value S1max of the cross-sectional area S1 of each first cooling passage 61 is within the cross section perpendicular to the extending direction (axial direction Da) of the first cooling passage 61. It is preferable that the cross-sectional area S2 of the second cooling passage 62 closest to the first cooling passage 61 is larger than the maximum value S2max.
This can be expressed as the following equation (1).
S2max<S1max...(1)

As a result, the maximum value S1max of the cross-sectional area S1 of each first cooling passage 61 becomes the maximum value S1max of the cross-sectional area S2 of the second cooling passage 62 closest to the first cooling passage 61 in the cross section perpendicular to the axial direction Da. Compared to the case where S2max is the same or smaller, the flow velocity of the cooling air CA in the first cooling passage 61 can be suppressed and the static pressure can be increased. Therefore, the static pressure in the first cooling passage 61 located upstream of the second cooling passage 62 with respect to the flow direction of the cooling air CA can be improved, so that the flow velocity of the cooling air CA in the second cooling passage 62 can be increased. , the cooling capacity in the second cooling passage 62 can be improved.
Furthermore, by using the divided bodies 51 according to some embodiments, the reliability of the gas turbine 10 can be improved.

In the divided body 51 according to some embodiments, the maximum value S1max of the cross-sectional area S1 of each first cooling passage 61 is the maximum value S1max of the total cross-sectional area AS2 of the second cooling passage 62 communicating with the first cooling passage 61. It is preferable that the value is larger than the value AS2max.
This can be expressed as the following equation (2).
AS2max<S1max...(2)
Note that the total cross-sectional area AS2 is the sum of the cross-sectional areas S2 of all the second cooling passages 62 communicating with the first cooling passage 61.

As a result, the maximum value S1max of the cross-sectional area S1 of each first cooling passage 61 is the same as or smaller than the maximum value AS2max of the total cross-sectional area AS2 of the second cooling passage 62 communicating with the first cooling passage 61. Therefore, it is possible to suppress the flow velocity of the cooling air CA in the first cooling passage 61 and increase the static pressure. Therefore, the static pressure in the first cooling passage 61 located upstream of the second cooling passage 62 with respect to the flow direction of the cooling air CA can be improved, so that the flow velocity of the cooling air CA in the second cooling passage 62 can be increased. , the cooling capacity in the second cooling passage 62 can be improved.

In order to satisfy the above-mentioned formula (1) or formula (2), for example, as shown in FIGS. 13 and 14, the dimension H1 of each first cooling passage 61 in the radial direction Dr is set to The dimension H2 of the cooling passage 62 may be made larger. For example, the maximum value H1max of the dimension H1 of each first cooling passage 61 in the radial direction Dr is made larger than the maximum value H2max of the dimension H2 in the radial direction Dr of the second cooling passage 62 communicating with the first cooling passage 61. You may.
In the divided body 51 according to some embodiments, for example, from the upstream connecting end 61a to a position separated downstream in the axial direction Da by a distance of 0.5 times the length of the first cooling passage 61 in the axial direction Da. At any axial direction Da position within the section, the maximum value H1max of the dimension H1 of each first cooling passage 61 is equal to the dimension H2 in the radial direction Dr of the second cooling passage 62 communicating with the first cooling passage 61. It is preferable that it be larger than the maximum value H2max.
Note that the length of the first cooling passage 61 in the axial direction Da is, for example, the length from the downstream connecting end 61b to the upstream connecting end 61a.

In order to satisfy the above-mentioned formula (1) or formula (2), for example, as shown in FIG. The dimension W1 of the passage 61 may be larger than the dimension W2 of each second cooling passage 62 in the passage width direction. For example, the maximum value W1max of the dimension W1 of each first cooling passage 61 in the passage width direction is made larger than the maximum value W2max of the dimension W2 in the passage width direction of the second cooling passage 62 communicating with the first cooling passage 61. You may.
In the divided body 51 according to some embodiments, for example, from the upstream connecting end 61a to a position separated downstream in the axial direction Da by a distance of 0.5 times the length of the first cooling passage 61 in the axial direction Da. At any axial direction Da position within the section, the maximum value W1max of the dimension W1 of each first cooling passage 61 is equal to the dimension W2 in the passage width direction of the second cooling passage 62 communicating with the first cooling passage 61. It is preferable that it be larger than the maximum value W2max.

In the divided body 51 according to some embodiments, each of the first cooling passages 61 has a cross-sectional area S1 in a region on the side of the connection end (upstream connection end) 61a that is larger than that of the connection end on the upstream side of the region. It is preferable that the cross-sectional area S1 be larger than the cross-sectional area S1 in the region far from 61a.
As a result, in each of the first cooling passages 61, the area closer to the second cooling passage 62 has a larger cross-sectional area S1. Therefore, it is possible to improve the static pressure in a region closer to the second cooling passage 62 of the first cooling passage 61 located upstream of the second cooling passage 62 with respect to the flow direction of the cooling air CA. The flow velocity of the cooling air CA in the cooling passage 62 can be efficiently increased, and the cooling capacity in the second cooling passage 62 can be efficiently improved.
In addition, in the divided body 51 according to some embodiments, there may be a cooling passage 6 that does not satisfy the above-mentioned formula (1) or formula (2).

(Relationship between circumferential direction Dc positions of first cooling passage 61 and second cooling passage 62)
For example, as shown in FIGS. 8, 12 to 15, the circumferential Dc position of each of the second cooling passages 62 is substantially the same as the circumferential direction Dc position of each of the first cooling passages 61. That is, in the divided body 51 according to some embodiments, when viewed from the radial direction Dr, the first partition wall 71 is located at substantially the same position as the second partition wall 72 in the passage width direction (circumferential direction Dc). It would be good if it was placed in
Thereby, the structure of the connecting portion between the first cooling passage 61 and the second cooling passage 62, that is, the intermediate folded passage 66 can be simplified.
Note that the circumferential Dc position of at least one of the plurality of second cooling passages 62 may be substantially the same as the circumferential direction Dc position of any one of the plurality of first cooling passages 61. .

FIG. 18 is a diagram showing a part of still another embodiment of a cross section taken along the line FF in FIG. For example, as shown in FIG. 18, the circumferential Dc position of each of the second cooling passages 62 may be substantially different from the circumferential Dc position of each of the first cooling passages 61. That is, in the divided body 51 according to still another embodiment, the first partition wall 71 is located at a substantially different position from the second partition wall 72 in the passage width direction (circumferential direction Dc) when viewed from the radial direction Dr. It may be placed in
As a result, when viewed from the radial direction Dr, compared to the case where the first partition wall 71 and the second partition wall 72 are arranged at substantially the same position in the circumferential direction Dc, Sometimes, the area where the second partition wall 72 and the first cooling passage 61 overlap increases. Thereby, for example, heat transmitted between two adjacent second cooling passages 62 via the second partition wall 72 is easily transmitted to the cooling air CA flowing through the first cooling passage 61.
Note that the circumferential direction Dc position of at least one or more of the plurality of second cooling passages 62 may be substantially different from the circumferential direction Dc position of any one of the plurality of first cooling passages 61.

(Number of first cooling passages 61 and second cooling passages 62)
FIG. 19 is a diagram showing a part of still another embodiment of a cross section taken along the line FF in FIG. In the embodiment shown in FIG. 19, the dimension W1 in the circumferential direction Dc of one first cooling passage 61 at the axial direction Da position of the FF arrow cross section in FIG. It is more than twice the dimension W2 of Dc.
For example, in the embodiment shown in FIG. 19, two second cooling passages 62 may be connected to one first cooling passage 61.
That is, in the divided body 51 according to some embodiments described above, one second cooling passage 62 was connected to one first cooling passage 61, but one first cooling passage 61 was connected to one second cooling passage 62. Two or more second cooling passages 62 may be connected to the cooling passage 61 .

(About the opening formed at the end on the upstream side of the axial direction Da)
FIG. 20 is a perspective view of a part of the upstream side in the axial direction Da of the divided body 51 according to some embodiments, and shows a state before a closing member 517, which will be described later, is attached.
FIG. 21 is a perspective view of a portion of the divided body 51 on the upstream side in the axial direction Da according to some embodiments, and shows a state after a closing member 517, which will be described later, is attached.
In the divided body 51 according to some embodiments, as shown in FIG. 20, an opening 515 facing the intermediate folding passage 66 is formed at an upstream end 513 on the upstream side in the axial direction Da. In the divided body 51 according to some embodiments, the opening 515 is closed by a closing member 517.

In the divided body 51 according to some embodiments, a pin gauge (not shown) or the like is connected to the first cooling passage 61 or the first cooling passage 61 from the outside of the divided body 51 through the opening 515 and the intermediate folded passage 66 before closing with the closing member 517. 2 cooling passage 62. Thereby, it can be confirmed that there is no blockage in the first cooling passage 61 or the second cooling passage 62. Note that it is necessary to visually confirm that there is no blockage in the first cooling passage 61 or the second cooling passage 62 through the opening 515 and the intermediate folded passage 66 before closing with the closing member 517 from the outside of the divided body 51. You can also do it.
In this way, after it is confirmed that there is no blockage in the first cooling passage 61 or the second cooling passage 62, the closing member 517 is placed in the opening 515 to close it. Note that the closing member 517 can be fixed to the divided body 51 by, for example, welding or the like.

In the divided body 51 according to some embodiments, the closing member 517 abuts at least a portion of the folded passage partition wall 76 . More specifically, in the divided body 51 according to some embodiments, the end face of the closing member 517 facing downstream in the axial direction Da is the end face facing upstream in the axial direction Da of the plurality of folded passage partition walls 76. contact with at least a portion of the
Thereby, leakage of the cooling air CA between the intermediate folding passages 66 that are adjacent to each other in the circumferential direction Dc with the folding passage partition wall 76 in between can be suppressed.
Further, since the closing member 517 comes into contact with at least a portion of the folded passage partition wall 76, positioning of the closing member 517 in the opening 515 becomes easy when attaching the closing member 517 to the opening 515.

The divided body 51 according to some embodiments includes an opening 515 facing the plurality of intermediate folding passages 66 and a closing member 517 that closes the opening 515. Thus, the first cooling passage 61 and the second cooling passage 62 can be accessed. This makes it possible to check whether the first cooling passage 61 and the second cooling passage 62 have a prescribed opening area, for example, at the stage of manufacturing the divided body 51, contributing to quality control of the divided body 51.

(Regarding the position of the intermediate folding passage 66)
For example, as shown in FIG. 5, in the divided body 51 according to some embodiments, at least a part of the plurality of intermediate folded passages 66 is located at the upstream end, which is one end surface in the axial direction Da of the divided body 51. It is preferable to exist at a distance from the upstream end surface 513a of 513 within twice the passage height H6 of the intermediate folded passage 66 in the radial direction Dr. That is, in the divided body 51 according to some embodiments, the thickness Lu of the upstream end portion 513 located upstream of the intermediate folded passage 66 in the axial direction Da is twice the passage height H6 of the intermediate folded passage 66. It is preferable that it is within (Lu≦2×H6).

In the intermediate folding passage 66, since the first cooling passage 61 and the second cooling passage 62 which are located at different positions in the radial direction Dr are connected, the flow direction of the cooling air CA changes. Improves heat transfer coefficient to. Therefore, the cooling capacity of the region of the divided body 51 near the intermediate folded passage 66 is improved.
Generally, the heat load is higher near the upstream end surface 513a of the divided body 51 than in other regions, so it is desirable to arrange the intermediate folded passage 66 near the upstream end surface 513a. By arranging the intermediate folding passage 66 near the upstream end surface 513a, the vicinity of the upstream end surface 513a of the divided body 51 can be efficiently cooled.

(Regarding the position of the entrance side turning passage 65)
For example, as shown in FIG. 5, in the divided body 51 according to some embodiments, at least a part of the inlet side folded passage 65 is located at a downstream end 511 which is the other end surface in the axial direction Da of the divided body 51. It is preferable to exist at a distance within three times the passage height H5 of the inlet-side folded passage 65 in the radial direction Dr from the downstream end surface 511a of the inlet passage 65. That is, in the divided body 51 according to some embodiments, the thickness Ld of the downstream end portion 511 located downstream of the axial direction Da of the inlet side folded passage 65 is equal to the passage height H5 of the inlet side folded passage 65. It is preferable that it is within 3 times (Ld≦3×H5).

In the inlet side folded passage 65, since the introduction passage 64 and the first cooling passage 61, which are located at different positions in the radial direction Dr, are connected, the flow direction of the cooling air CA changes. Improves heat transfer coefficient to. Therefore, the cooling capacity of the area near the inlet side folded passage 65 in the divided body 51 is improved.
Generally, the heat load near the downstream end face 511a of the split body 51 is higher than other areas due to the entrainment of combustion gas FG, so it is desirable to arrange the inlet side folded passage 65 near the downstream end face 511a. By arranging the inlet side folded passage 65 near the downstream end surface 511a, the vicinity of the downstream end surface 511a of the divided body 51 can be efficiently cooled.

(Three-dimensional additively manufactured object)
The divided body 51 according to some embodiments may be a three-dimensional layered product formed by three-dimensional layered manufacturing.
Thereby, even if the divided body 51 includes the long and narrow cooling passage 6, which would be difficult to machine by electrical discharge machining, for example, it can be obtained as a three-dimensional layered product.

(About the connection part 57)
Hereinafter, the role of the connecting portion 57 in the divided body 51 according to some embodiments will be explained.
In the divided body 51 according to some embodiments, the connecting portion 57 is a rib-shaped portion.
In the divided body 51 according to some embodiments, the inlet opening 64a is a slit opening extending along the plate width direction (circumferential direction Dc) of the main body portion 53, as described above. A plurality of connecting portions 57 are provided within the formation range of the slit opening in the plate width direction (circumferential direction Dc).

In the divided body 51 according to some embodiments, since the protrusion 55 is separated from the outer surface 532 of the main body 53 by the inlet opening 64a of the cooling passage 6, the temperature difference between the main body 53 and the protrusion 55 is reduced. However, since the main body part 53 and the protruding part 55 are connected by the connecting part 57, the connecting part 57 functions as a heat transfer path and suppresses the temperature difference between the main body part 53 and the protruding part 55. can. Thereby, thermal stress in the protrusion 55 can be suppressed.
Further, by connecting the protruding portion 55 and the main body portion 53 through the connecting portion 57, deformation of the divided body 51 can be suppressed.
In the divided body 51 according to some embodiments, the portion forming the inlet opening 64a can be reinforced by the plurality of connecting portions 57.

In the divided body 51 according to some embodiments, the radial direction of the protrusion 55 continues from the side surface 55a (hereinafter simply referred to as the side surface 55a) facing the upstream side in the axial direction Da of the protrusion 55 on the downstream side in the axial direction Da. The surface facing toward the Dr inner side is an inclined surface (projection portion inclined surface) 55b which faces toward the radial direction Dr inner side as it goes downstream in the axial direction Da. In the divided body 51 according to some embodiments, the position Pin in the axial direction Da where the intersection 55c of the side surface 55a and the protruding part inclined surface 55b and the outer surface 532 of the main body part 53 face is in the axial direction of the introduction passage 64. Since Da is the upstream end, the axial direction Da position becomes the inlet end 641 of the introduction passage 64.

In the divided body 51 according to some embodiments, as shown in FIG. 5, a part of the connecting portion 57 is located downstream of the inlet end 641 of the introduction passage 64 in the axial direction Da. That is, in the divided body 51 according to some embodiments, the connecting portion 57 is arranged such that the intrusion portion 575, which is a part of the connecting portion 57, intrudes into the inside of the cooling passage 6.
In the divided body 51 according to some embodiments, the intrusion portion 575 is connected to the protrusion inclined surface 55b. That is, in the divided body 51 according to some embodiments, a portion of the connecting portion 57 is connected to the protruding portion inclined surface 55b, which is a wall surface forming the cooling passage 6 that is continuous with the intersecting surface (side surface 55a) of the protruding portion 55. ing.
Thereby, the connection area between the protrusion part 55 and the connection part 57 can be secured in a region other than the intersecting plane (side surface 55a), and the temperature difference between the main body part 53 and the protrusion part 55 can be further suppressed.

In the divided body 51 according to some embodiments, as shown in FIG. (intrusion part inclined surface) 575a. The intrusion portion inclined surface 575a is spaced apart from the outer surface 532. That is, at least a portion of the intrusion portion 575 is spaced apart from the outer surface 532.
Therefore, compared to the case where the intrusion part inclined surface 575a is connected to the outer surface 532, the partial volume in which the intrusion part 575 intrudes into the introduction passage 64 can be suppressed, so that the flow path of the introduction passage 64 in the vicinity of the inlet opening 64a can be suppressed. It is possible to suppress the decrease in area. Therefore, the flow velocity of the cooling air CA flowing through the introduction passage 64 can be suppressed from increasing near the inlet opening 64a, and pressure loss in the introduction passage 64 can be suppressed.
Further, since the flow velocity of the cooling air CA flowing through the introduction passage 64 can be suppressed from increasing near the inlet opening 64a, it is possible to suppress the protrusion 55 from being excessively cooled, and the Temperature differences can be further suppressed.
Furthermore, since the protruding portion 55 can be prevented from being excessively cooled, the temperature rise of the cooling air CA in the introduction passage 64 can be suppressed, and a decrease in the cooling capacity in the first cooling passage 61 and the second cooling passage 62 can be suppressed. .

(About the relationship between the outer surface 532 and the cooling passage 6)
In the divided body 51 according to some embodiments, a portion of the outer surface 532 of the main body portion 53 constitutes a portion of the cooling passage 6. More specifically, in the divided body 51 according to some embodiments, the cooling passage 6 is separated from the upstream passage (introduction passage 64) including the inlet opening 64a and the upstream passage 64 in the above-described cross direction. It includes a downstream passage (first cooling passage 61) arranged at a certain position, and an inlet side folded passage 65 which is a folded passage connecting the upstream passage 64 and the downstream passage 61. As shown in FIG. 5, a portion of the outer surface 532 of the main body portion 53 constitutes a portion of the upstream passage 64 and continues to a wall surface 65a forming the inlet side folded passage 65.

This makes it easier for the cooling air CA to flow into the cooling passage 6 along the outer surface 532 of the main body portion 53.
Further, the inlet opening 64a is located from the end (downstream end 511) of the main body 53 on one side (downstream in the axial direction Da) of the main body 53 in the direction along the outer surface 532 of the main body 53 on the other side (upstream in the axial direction Da). Even if the cooling air CA is provided at a position far away from the inlet opening 64a, it is possible to guide the cooling air CA flowing in from the inlet opening 64a to the downstream side in the axial direction Da by the upstream passage 64, and also direct the cooling air CA to the inlet side turning passage. 65 to the downstream passage 61, the cooling air CA can be guided from the inlet side folded passage 65 toward the upstream side in the axial direction Da.

(Regarding the upstream inclined surface 577 of the connecting portion 57)
In the divided body 51 according to some embodiments, the connecting portion 57 has an upstream inclined surface that is an inclined surface extending obliquely from one end 571 to the other end 573 with respect to the outer surface 532 of the main body 53. It has 577.
The upstream inclined surface 577 is an inclined surface that extends between the end of the one end 571 on the upstream side in the axial direction Da and the claw portion 59a of the hook 59, and faces outward in the radial direction Dr as it goes downstream in the axial direction Da. be.

In the divided body 51 according to some embodiments, the upstream inclined surface 577 extends from the one end 571 connected to the outer surface 532 of the main body 53 to the claw portion 59a of the hook 59 located on the radially outer side of the protrusion 55. Since it extends diagonally with respect to the outer surface 532 of the portion 53, the connecting portion 57 becomes wider as it goes from the distal end side (radial direction Dr outer side) to the proximal end side (radial direction Dr inner side) of the protruding portion 55. It will have a shape. Therefore, the area of the connection between one end 571 of the connecting portion 57 and the outer surface 532 of the main body portion 53 can be increased, and the amount of heat transferred from the main body portion 53 to the protruding portion can be increased. 55 can be further suppressed.

In addition, since the upstream inclined surface 577 is an inclined surface that faces outward in the radial direction Dr as it goes downstream in the axial direction Da, for example, when forming the divided body 51 according to some embodiments by three-dimensional additive manufacturing, If the direction is from the upstream side to the downstream side along the axial direction Da, the connecting portion 57 becomes a portion whose size along the radial direction gradually increases as the modeling progresses. Therefore, the connecting portion 57 can be formed without forming a support, and the connecting portion 57 itself serves as a support for the protruding portion 55. Therefore, the number of supports to be formed can be reduced, the time required for additive manufacturing can be shortened, and the process of removing supports can be simplified.

Furthermore, as described above, the connecting portion 57 is a portion whose size along the radial direction gradually increases as the modeling progresses, so that the protruding portion 55 changes in shape as the modeling progresses in the stacking direction. This can reduce the risk of sudden changes. In general, in metal additive manufacturing, if there is a sudden change in shape when building along the stacking direction, in the vicinity of the sudden change, the outer edge of the model that appears in the cross section perpendicular to the stacking direction There is a possibility that the position may shift in a direction perpendicular to the stacking direction.
As described above, the connecting portion 57 can prevent the protruding portion 55 from becoming a sudden change in shape during modeling in the stacking direction, so that the shape of the divided body 51 is not distorted in the vicinity of the protruding portion 55. You can prevent this from happening.

(Regarding the cross-sectional shapes of the first cooling passage 61 and the second cooling passage 62)
In the several embodiments described above, the cross-sectional shapes of the first cooling passage 61 and the second cooling passage 62 are rectangular, but they may be circular or elliptical. Further, the cross-sectional shape of the first cooling passage 61 and the second cooling passage 62 may be a polygon other than a rectangle, or may be a combination of a polygon, a circle, or an ellipse.
For example, the cross-sectional shape of the first cooling passage 61 and the cross-sectional shape of the second cooling passage 62 may be different. For example, the cross-sectional shape of the first cooling passage 61 may be circular, and the cross-sectional shape of the second cooling passage 62 may be polygonal. Further, for example, the cross-sectional shapes of all the first cooling passages 61 do not need to be the same, and may be different. Similarly, the cross-sectional shapes of all the second cooling passages 62 do not need to be the same and may be different.

FIG. 22A is a diagram showing an example of a polygon that is not a regular polygon as an example of the cross-sectional shape of the first cooling passage 61 or the second cooling passage 62.
FIG. 22B is a diagram showing an example of a cross-sectional shape of the first cooling passage 61 or the second cooling passage 62, which is a combination of a polygon and a circle.
For example, the cross-sectional shape of the flow path shown in FIGS. 22A and 22B has an inclined surface 601 that is inclined with respect to the vertical direction in the drawing on the upper side of the flow path in the drawing.
For example, when forming the divided body 51 by three-dimensional additive manufacturing, if the stacking direction in the cooling passage 6 is from the bottom to the top in the drawing, the cooling passage 6 has an inclined surface 601 as shown in FIGS. 22A and 22B, for example. If it has, it is possible to suppress deformation of the inclined surface 601 which becomes an overhang region during modeling.

FIG. 23A is a diagram illustrating a part of a cross section taken along line FF in FIG. 5 regarding still another embodiment.
For example, as shown in FIG. 23A, the cross-sectional shapes of the first cooling passage 61 and the second cooling passage 62 may be triangular. In this case, in the second cooling passage 62, one side 602 of the flow passage cross section having a triangular shape when viewed along the axial direction Da may face inward in the radial direction Dr of the main body portion 53. As a result, the distance between the second cooling passage 62 and the inner surface 531 can be reduced while increasing the projected area of the flow passage cross section when viewed radially outward from the inner surface 531 of the main body portion 53. The region on the inner surface 531 side of the main body portion 53 can be efficiently cooled by the cooling air CA flowing through the second cooling passage 62.
Note that, as shown in FIG. 23A, in the second cooling passage 62, one side 602 of the flow passage cross section having a triangular shape when viewed along the axial direction Da is directed inward in the radial direction Dr of the main body portion 53. , one vertex 603 of the triangle faces outward in the radial direction Dr. Therefore, as shown in FIG. 23A, in the first cooling passage 61, one vertex 604 of the triangle of the flow passage cross section that has a triangular shape when viewed along the axial direction Da is directed inside the radial direction Dr, and the vertex 604 overlaps with the second cooling passage 62 in the radial direction Dr, the thickness of the main body portion 53 in the radial direction Dr can be suppressed.

FIG. 23B is a diagram showing a part of a cross section taken along the line FF in FIG. 5 regarding yet another embodiment.
For example, as shown in FIG. 23B, the cross-sectional shape of the first cooling passage 61 may be rhombic, and the cross-sectional shape of the second cooling passage 62 may be triangular. In this case, similarly to the example shown in FIG. 23A, in the second cooling passage 62, one side 602 of the flow passage cross section having a triangular shape when viewed along the axial direction Da extends inside the main body part 53 in the radial direction Dr. It is best to face it. As a result, the distance between the second cooling passage 62 and the inner surface 531 can be reduced while increasing the projected area of the flow passage cross section when viewed radially outward from the inner surface 531 of the main body portion 53. The region on the inner surface 531 side of the main body portion 53 can be efficiently cooled by the cooling air CA flowing through the second cooling passage 62.
Note that, as shown in FIG. 23B, in the second cooling passage 62, one side 602 of the flow passage cross section having a triangular shape when viewed along the axial direction Da is oriented toward the inside of the main body portion 53 in the radial direction Dr. , one vertex 603 of the triangle faces outward in the radial direction Dr. Therefore, as shown in FIG. 23B, in the first cooling passage 61, one apex 605 of the rhombus of the flow passage cross section that has a rhombic shape when viewed along the axial direction Da is directed inside the radial direction Dr, and the apex 605 overlaps with the second cooling passage 62 in the radial direction Dr, the thickness of the main body portion 53 in the radial direction Dr can be suppressed.

The present disclosure is not limited to the embodiments described above, and also includes forms in which modifications are added to the embodiments described above, and forms in which these forms are appropriately combined.

The contents described in each of the above embodiments can be understood as follows, for example.
(1) A high-temperature component according to at least one embodiment of the present disclosure includes a plurality of linearly extending first cooling passages 61 and a first cooling passage 61 extending in a perpendicular direction to a plane including the extending direction of the plurality of first cooling passages 61. A plurality of second cooling passages 62 are provided that are spaced apart from the first cooling passage 61 and extend along the extending direction of the first cooling passage 61 so as to communicate with any one of the first cooling passages 61, respectively. The maximum value S1max of the cross-sectional area S1 of each first cooling passage 61 is larger than the maximum value S2max of the cross-sectional area S2 of the second cooling passage 62 closest to the first cooling passage 61 in the cross section orthogonal to the above-mentioned extending direction. It's also big.

As described above, in a machine such as the gas turbine 10 that operates with high-temperature working gas, the loss of heat through cooling generally leads to a decrease in the thermal efficiency of the machine. Therefore, it is desirable to efficiently cool high-temperature components using as little cooling medium as possible. Therefore, it is desirable to increase the flow rate of the cooling medium in the cooling passage 6 by reducing the cross-sectional area S of the cooling passage 6, thereby improving the cooling capacity.
However, as the flow passage cross-sectional area S becomes smaller, there is a possibility that the risk of the cooling passage 6 being blocked by foreign matter increases.

According to the configuration (1) above, since the plurality of first cooling passages 61 and the plurality of second cooling passages 62 spaced apart from the first cooling passage 1 in the perpendicular direction are provided, the plurality of first cooling passages 61 Alternatively, the cooling capacity can be improved compared to the case where only one of the plurality of second cooling passages 62 is provided. Thereby, the cross-sectional area S of the cooling passage 6 can be increased while ensuring cooling capacity compared to the case where only one of the plurality of first cooling passages 61 or the plurality of second cooling passages 62 is provided. . Therefore, compared to the case where only one of the plurality of first cooling passages 61 or the plurality of second cooling passages 62 is provided, the risk of blockage in the cooling passage 6 can be suppressed while ensuring cooling capacity.

Further, according to the configuration (1) above, the maximum value S1max of the cross-sectional area S1 of each first cooling passage 61 is the second cooling passage closest to the first cooling passage 61 in the cross section orthogonal to the extending direction. Compared to the case where the cross-sectional area S2 of the cooling passage 62 is equal to or smaller than the maximum value S2max, the flow velocity of the cooling medium in the first cooling passage 61 can be suppressed to increase the static pressure. Therefore, when the direction of flow of the cooling medium is from the first cooling passage 61 to the second cooling passage 62, the static flow in the first cooling passage 61, which is located upstream of the second cooling passage 62, is Since the pressure can be increased, the flow rate of the cooling medium in the second cooling passage 62 can be increased, and the cooling capacity in the second cooling passage 62 can be improved.

(2) In some embodiments, in the configuration of (1) above, the maximum value S1max of the cross-sectional area S1 of each first cooling passage 61 is the maximum value S1max of the cross-sectional area S1 of each first cooling passage 61. It is larger than the maximum value AS2max of the total cross-sectional area AS2.

According to the configuration (2) above, the maximum value S1max of the cross-sectional area S1 of each first cooling passage 61 is equal to the maximum value AS2max of the total cross-sectional area AS2 of the second cooling passage 62 communicating with the first cooling passage 61. The static pressure can be increased by suppressing the flow velocity of the cooling medium in the first cooling passage 61, compared to the case where the flow rate is the same or smaller. Therefore, when the direction of flow of the cooling medium is from the first cooling passage 61 to the second cooling passage 62, the static flow in the first cooling passage 61, which is located upstream of the second cooling passage 62, is Since the pressure can be increased, the flow rate of the cooling medium in the second cooling passage 62 can be increased, and the cooling capacity in the second cooling passage 62 can be improved.

(3) In some embodiments, in the configuration of (1) or (2) above, the maximum value H1max of the dimension H1 of each first cooling passage 61 in the perpendicular direction is in communication with the first cooling passage 61. is larger than the maximum value H2max of the dimension H2 of the second cooling passage 62 in the perpendicular direction.

According to configuration (3) above, the maximum value H1max of the dimension H1 of each of the first cooling passages 61 in the perpendicular direction is equal to the dimension H2 of the second cooling passage 62 in the perpendicular direction that communicates with the first cooling passage 61. By making the maximum value S1max of the cross-sectional area S1 of each first cooling passage 61 larger than the maximum value H2max of the second cooling passage 61, the maximum value S1max of the cross-sectional area S1 of each first cooling passage 61 is set to The cross-sectional area S2 of the passage 62 can be made larger than the maximum value S2max.

(4) In some embodiments, in any of the configurations (1) to (3) above, the dimension W1 of each first cooling passage 61 in the passage width direction perpendicular to the perpendicular direction and the extension direction. The maximum value W1max of is larger than the maximum value W2max of the dimension W2 in the passage width direction of the second cooling passage 62 communicating with the first cooling passage 61.

According to the configuration (4) above, the maximum value W1max of the dimension W1 of each first cooling passage 61 in the passage width direction is equal to the dimension in the passage width direction of the second cooling passage 62 communicating with the first cooling passage 61. By making the maximum value W2max of W2 larger than the maximum value S1max of the cross-sectional area S1 of each first cooling passage 61, the maximum value S1max of the cross-sectional area S1 of each first cooling passage 61 is set to The cross-sectional area S2 of the cooling passage 62 can be made larger than the maximum value S2max.

(5) In some embodiments, in any of the configurations (1) to (4) above, each first cooling passage 61 is connected to a second cooling passage 62 that communicates with the first cooling passage 61. 61a (upstream side connection end). In each of the first cooling passages 61, a cross-sectional area S1 in a region closer to the upstream connecting end 61a is larger than a cross-sectional area S1 in a region farther from the upstream connecting end 61a.

According to configuration (5) above, in each of the first cooling passages 61, the area closer to the second cooling passage 62 has a larger cross-sectional area S1. Therefore, when the direction of flow of the cooling medium is from the first cooling passage 61 to the second cooling passage 62, among the first cooling passages 61 that are located upstream of the second cooling passage 62, Since the static pressure in a region closer to the second cooling passage 62 can be improved, the flow rate of the cooling medium in the second cooling passage 62 can be efficiently increased, and the cooling capacity in the second cooling passage 62 can be efficiently improved.

(6) In some embodiments, in any of the configurations (1) to (5) above, the high temperature component according to at least one embodiment of the present disclosure is arranged in a passage orthogonal to the perpendicular direction and the extending direction. It further includes a first partition wall 71 that partitions the first cooling passages 61 adjacent to each other along the width direction, and a second partition wall 72 that partitions the second cooling passages 62 adjacent to each other along the passage width direction. When viewed from the perpendicular direction, the first partition wall 71 and the second partition wall 72 are arranged at substantially the same position in the passage width direction.

According to the configuration (6) above, since the first partition wall 71 and the second partition wall 72 are arranged at substantially the same position in the passage width direction when viewed from the perpendicular direction, the first The structure of the connecting portion between the cooling passage 61 and the second cooling passage 62 can be simplified.

(7) In some embodiments, in any of the configurations (1) to (5) above, the high temperature component according to at least one embodiment of the present disclosure is arranged in a passage orthogonal to the perpendicular direction and the extending direction. It further includes a first partition wall 71 that partitions the first cooling passages 61 adjacent to each other along the width direction, and a second partition wall 72 that partitions the second cooling passages 62 adjacent to each other along the passage width direction. When viewed from the perpendicular direction, the first partition wall 71 and the second partition wall 72 are arranged at substantially different positions in the passage width direction.

According to the configuration (7) above, when viewed from the perpendicular direction, compared to the case where the first partition wall 71 and the second partition wall 72 are arranged at substantially the same position in the passage width direction, When viewed from the perpendicular direction, the area where the first partition wall 71 and the second cooling passage 62 overlap increases, and the area where the second partition wall 72 and the first cooling passage 61 overlap increases. Thereby, for example, heat transmitted between two adjacent first cooling passages 61 via the first partition wall 71 is easily transmitted to the cooling medium flowing through the second cooling passage 62. Further, for example, heat transmitted between two adjacent second cooling passages 62 via the second partition wall 72 is easily transmitted to the cooling medium flowing through the first cooling passage 61.

(8) In some embodiments, in any of the configurations (1) to (7) above, the high-temperature component according to at least one embodiment of the present disclosure is connected to each first cooling passage 61 and the first cooling passage 61. It further includes a plurality of first folded passages 66 that connect the second cooling passages 62 communicating with the passages 61 to each other.

According to the configuration (8) above, each first cooling passage 61 and the second cooling passage 62 communicating with the first cooling passage 61 can be connected by the first folded passage 66.

(9) In some embodiments, in the configuration of (8) above, the high temperature component according to at least one embodiment of the present disclosure has an opening 515 facing the plurality of first folded passages 66 and a It further includes a closing member 517 for closing.

According to the configuration (9) above, the first cooling passage 61 and the second cooling passage 62 can be accessed from the opening 515 via the first folded passage 66. This makes it possible to check whether the first cooling passage 61 and the second cooling passage 62 have a specified opening area, for example, at the manufacturing stage of high-temperature parts, contributing to quality control of high-temperature parts.

(10) In some embodiments, in the configuration of (8) or (9) above, the high temperature component according to at least one embodiment of the present disclosure is arranged in the passage width direction perpendicular to the perpendicular direction and the extension direction. It further includes a folding passage partition wall 76 that separates the first folding passages 66 adjacent to each other along the line.

According to the configuration (10) above, the first folded passages 66 adjacent to each other along the passage width direction can be separated from each other. Further, according to the configuration (10) above, the folded passage partition wall 76 functions as a heat transfer member for the cooling medium flowing through the first folded passage 66, so that the cooling capacity can be improved.

(11) In some embodiments, in the configuration of (10) above, the high temperature component according to at least one embodiment of the present disclosure has an opening 515 facing the plurality of first folded passages 66 and a It further includes a closing member 517 for closing. The closing member 517 is in contact with at least a portion of the folded passage partition wall 76 .

According to the configuration (11) above, the first cooling passage 61 and the second cooling passage 62 can be accessed from the opening 515 via the first folded passage 66. This makes it possible to check whether the first cooling passage 61 and the second cooling passage 62 have a specified opening area, for example, at the manufacturing stage of high-temperature parts, contributing to quality control of high-temperature parts.
Further, according to the configuration (11) above, the closing member 517 comes into contact with at least a portion of the folded passage partition wall 76, so that positioning of the closing member 517 in the opening 515 becomes easy.

(12) In some embodiments, in any of the configurations (8) to (11) above, at least a portion of the plurality of first folded passages 66 is formed on one end surface of the high temperature component in the extending direction. It exists at a distance from (the upstream end surface 513a) within twice the passage height H6 of the first folded passage 66 in the perpendicular direction.

In the first folded passage 66, since the first cooling passage 61 and the second cooling passage 62, which are located at different positions in the perpendicular direction, are connected, the flow direction of the cooling medium changes. Improves heat transfer coefficient to. Therefore, the cooling capacity of the region near the first folded passage 66 in the high-temperature component is improved.
For example, if the heat load is higher near one end face of the high-temperature component in the extending direction than in other areas, it is desirable to arrange the first folded passage 66 near the end face. Therefore, according to the configuration (12) above, the high-temperature component can be efficiently cooled when the heat load is higher in the vicinity of one end face in the extending direction of the high-temperature component than in other regions.

(13) In some embodiments, in any of the configurations (8) to (12) above, the high temperature component according to at least one embodiment of the present disclosure includes a plurality of second cooling passages 62 in the perpendicular direction. on the opposite side, an introduction passage 64 that is spaced apart from the first cooling passage 61 and extends along the extending direction of the first cooling passage 61 so as to communicate with any one of the first cooling passages 61; It further includes a second folded passage 65 that connects the first cooling passage 61 and the introduction passage 64 to each other.

In the second folded passage 65, the introduction passage 64 and the first cooling passage 61, which are located at different positions in the perpendicular direction, are connected, so the flow direction of the cooling medium changes. Improves heat transfer coefficient. Therefore, according to the configuration (13) above, the cooling capacity of the region near the second folded passage 65 in the high-temperature component is improved.

(14) In some embodiments, in the configuration of (13) above, at least a portion of the plurality of first folded passages 66 are present on one side in the extending direction of the high-temperature component. At least a portion of the second folded passage 65 exists at a distance within three times the passage height H5 of the second folded passage 65 in the perpendicular direction from the other end surface of the high-temperature component in the extending direction.

As described above, since the heat transfer coefficient to the cooling medium in the second folded passage 65 is improved, the cooling capacity of the area near the second folded passage 65 in the high temperature component is improved.
For example, if the heat load is higher near the other end face in the above-mentioned extending direction of the high-temperature component than in other areas, it is desirable to arrange the second folded passage 65 near the end face. Therefore, according to the configuration (14) above, the high-temperature component can be efficiently cooled when the heat load is higher near the other end surface of the high-temperature component in the extending direction than in other regions.

(15) In some embodiments, in any of the configurations (1) to (14) above, the high-temperature component is a divided ring 50 of the gas turbine 10 formed annularly along the circumferential direction. It is body 51.

According to the configuration (15) above, since the divided body 51 has any of the configurations (1) to (14) above, the cross-sectional area S of the cooling passage 6 can be reduced while ensuring the cooling capacity of the divided body 51. can be increased, so the risk of blockage in the cooling passage 6 can be suppressed.
Further, according to the configuration (15) above, the flow velocity of the cooling medium in the second cooling passage 62 can be increased, and the cooling capacity in the second cooling passage 62 can be improved, so that the second cooling passage is more efficient than the first cooling passage 61. By arranging the second cooling passage 62 so that the second cooling passage 62 is closer to the surface exposed to the high-temperature gas, the divided body 51 can be effectively cooled.

(16) In some embodiments, in any of the configurations (1) to (15) above, the high-temperature component (divided body 51) is a three-dimensional layered product.

According to the configuration (16) above, even a high-temperature component with an elongated cooling passage that is difficult to machine by electrical discharge machining, for example, can be obtained as a three-dimensional layered product.

(17) A rotating machine (gas turbine 10) according to at least one embodiment of the present disclosure includes a high-temperature component having the configuration of any one of (1) to (16) above.

According to the configuration (17) above, the reliability of the rotating machine can be improved by suppressing the risk of blockage of the cooling passage in the high-temperature components of the rotating machine.

6 Cooling passage 10 Gas turbine 50 Divided ring 51 Divided body 53 Main body part 55 Projection part 57 Connection part 59 Hook 61 First cooling passage 62 Second cooling passage 64 Introduction passage 65 Second folded passage (inlet side folded passage)
66 First turning passage (intermediate turning passage)
71 First partition wall 72 Second partition wall 515 Opening 517 Closing member 531 Inner surface 532 Outer surface

Claims (16)

a plurality of first cooling passages extending linearly;
The extending direction of the first cooling passage is spaced apart from the first cooling passage in a perpendicular direction of a plane including the extending direction of the plurality of first cooling passages, and communicates with any of the first cooling passages. a plurality of second cooling passages extending along;
Equipped with
The maximum value of the cross-sectional area of each of the first cooling passages is larger than the maximum value of the cross-sectional area of the second cooling passage closest to the first cooling passage in a cross section perpendicular to the extending direction,
The maximum value of the cross-sectional area of each of the first cooling passages is larger than the maximum value of the total cross-sectional area of the second cooling passages communicating with the first cooling passage.
High temperature parts. a plurality of first cooling passages extending linearly;
The extending direction of the first cooling passage is spaced apart from the first cooling passage in a perpendicular direction of a plane including the extending direction of the plurality of first cooling passages, and communicates with any of the first cooling passages. a plurality of second cooling passages extending along;
Equipped with
The maximum value of the cross-sectional area of each of the first cooling passages is larger than the maximum value of the cross-sectional area of the second cooling passage closest to the first cooling passage in a cross section perpendicular to the extending direction,
Each of the first cooling passages includes a connecting end connected to the second cooling passage that communicates with the first cooling passage;
Each of the first cooling passages has a cross-sectional area in a region closer to the connecting end that is larger than a cross-sectional area in a region farther from the connecting end.
High temperature parts. 3. A maximum dimension of each of the first cooling passages in the perpendicular direction is larger than a maximum dimension of each of the second cooling passages communicating with the first cooling passage in the perpendicular direction. high temperature parts. The maximum value of the dimension of each of the first cooling passages in the passage width direction perpendicular to the perpendicular direction and the extension direction is the maximum value of the dimension of the second cooling passage communicating with the first cooling passage in the passage width direction. A high temperature component according to any one of claims 1 to 3, which is greater than the maximum value. a first partition wall that partitions the first cooling passages adjacent to each other along a passage width direction perpendicular to the perpendicular direction and the extension direction;
a second partition wall that partitions the second cooling passages adjacent to each other along the width direction of the passage;
Furthermore,
5. The first partition wall and the second partition wall are arranged at substantially the same position in the passage width direction when viewed from the perpendicular direction. High temperature parts. a first partition wall that partitions the first cooling passages adjacent to each other along a passage width direction perpendicular to the perpendicular direction and the extension direction;
a second partition wall that partitions the second cooling passages adjacent to each other along the width direction of the passage;
Furthermore,
5. The first partition wall according to claim 1, wherein the first partition wall and the second partition wall are arranged at substantially different positions in the passage width direction when viewed from the perpendicular direction. High temperature parts. The high-temperature cooling system according to any one of claims 1 to 6 , further comprising a plurality of first folded passages interconnecting each of the first cooling passages and the second cooling passages communicating with the first cooling passages. parts. a plurality of first cooling passages extending linearly;
The extending direction of the first cooling passage is spaced apart from the first cooling passage in a perpendicular direction of a plane including the extending direction of the plurality of first cooling passages, and communicates with any of the first cooling passages. a plurality of second cooling passages extending along;
Equipped with
The maximum value of the cross-sectional area of each of the first cooling passages is larger than the maximum value of the cross-sectional area of the second cooling passage closest to the first cooling passage in a cross section perpendicular to the extending direction,
a plurality of first folded passages interconnecting each of the first cooling passages and the second cooling passages communicating with the first cooling passages;
a folded passage partition wall that separates the first folded passages adjacent to each other along a passage width direction perpendicular to the perpendicular direction and the extension direction ;
further equipped with
High temperature parts. an opening facing the plurality of first folding passages;
a closing member that closes the opening;
Furthermore,
The high temperature component according to claim 8 , wherein the closing member is in contact with at least a portion of the folded passage partition wall. High temperature parts,
a plurality of first cooling passages extending linearly;
The extending direction of the first cooling passage is spaced apart from the first cooling passage in a perpendicular direction of a plane including the extending direction of the plurality of first cooling passages, and communicates with any of the first cooling passages. a plurality of second cooling passages extending along;
Equipped with
The maximum value of the cross-sectional area of each of the first cooling passages is larger than the maximum value of the cross-sectional area of the second cooling passage closest to the first cooling passage in a cross section perpendicular to the extending direction,
further comprising a plurality of first folded passages interconnecting each of the first cooling passages and the second cooling passages communicating with the first cooling passages,
At least a portion of the plurality of first folded passages exists at a distance from one end face of the high temperature component in the extending direction to a distance within twice the passage height of the first folded passage in the perpendicular direction. Ru
High temperature parts. spaced apart from the first cooling passage on the opposite side from the plurality of second cooling passages in the perpendicular direction, and extending along the extending direction of the first cooling passage so as to communicate with each of the first cooling passages. an introduction passage extending through the
a second folded passage connecting the plurality of first cooling passages and the introduction passage to each other;
The high temperature component according to any one of claims 8 to 10 , further comprising: High temperature parts,
a plurality of first cooling passages extending linearly;
The extending direction of the first cooling passage is spaced apart from the first cooling passage in a perpendicular direction of a plane including the extending direction of the plurality of first cooling passages, and communicates with any of the first cooling passages. a plurality of second cooling passages extending along;
Equipped with
The maximum value of the cross-sectional area of each of the first cooling passages is larger than the maximum value of the cross-sectional area of the second cooling passage closest to the first cooling passage in a cross section perpendicular to the extending direction,
a plurality of first folded passages interconnecting each of the first cooling passages and the second cooling passages communicating with the first cooling passages;
spaced apart from the first cooling passage on the opposite side from the plurality of second cooling passages in the perpendicular direction, and extending along the extending direction of the first cooling passage so as to communicate with each of the first cooling passages. an introduction passage extending through the
a second folded passage connecting the plurality of first cooling passages and the introduction passage to each other;
Furthermore,
At least a portion of the plurality of first folded passages are present on one side in the extending direction in the high temperature component,
At least a portion of the second folded passage is present at a distance from the other end surface of the high-temperature component in the extending direction within three times the passage height of the second folded passage in the perpendicular direction.
High temperature parts. an opening facing the plurality of first folding passages;
a closing member that closes the opening;
The high temperature component according to any one of claims 7 to 12, further comprising: The high-temperature component according to any one of claims 1 to 13 , wherein the high-temperature component is a segmented body that constitutes a segmented ring of a gas turbine that is annularly formed along the circumferential direction. The high-temperature component according to any one of claims 1 to 14 , wherein the high-temperature component is a three-dimensional layered product. A rotating machine comprising a high temperature component according to any one of claims 1 to 15 .

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