JP2021169801A - High-temperature component and rotary machine - Google Patents

Abstract

To suppress thermal stress in a high-temperature component.SOLUTION: A high-temperature component 50, 51 includes: a plate-like body part 53 including a cooling passage therein; a projection part 55 provided while projecting from the body part and including a crossing surface 55a that is isolated from a surface 532 of the body part by an inlet opening 64a of the cooling passage and extends in a crossing direction relative to the surface; and a connection part 57 including one end 571 connected to a surface of the body part and the other end 573 connected to the crossing surface of the projection part, and extending from the one end to the other end while straddling the inlet opening.SELECTED DRAWING: Figure 7

Description

The present disclosure relates to high temperature parts and rotary machines.

For example, in a machine such as a gas turbine through which a high-temperature working gas flows, the parts constituting the machine include high-temperature parts that require cooling by 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).

JP-A-2017-160905

When the high-temperature component is a split body or the like constituting a split ring of a gas turbine formed in an annular shape along the circumferential direction like the high-temperature component described in the above-mentioned patent document, the high-temperature component is combined with another member. It may be equipped with a hook or the like for the purpose. When a high-temperature component is provided with a protrusion provided so as to project from a plate-shaped main body like a hook in a divided body, thermal stress may act on the protrusion due to the temperature difference between the main body and the protrusion. Conceivable. Therefore, it is conceivable that it is required to suppress the thermal stress acting on the protruding portion.

At least one embodiment of the present disclosure aims to suppress thermal stress in high temperature components in view of the above circumstances.

(1) The high-temperature parts according to at least one embodiment of the present disclosure are
A plate-shaped main body with a cooling passage inside,
A projecting portion that is provided so as to project from the main body portion, is separated from the surface of the main body portion by an inlet opening of the cooling passage, and has an intersecting surface extending in an intersecting direction with respect to the surface portion.
A connecting portion having one end connected to the surface of the main body portion and the other end connected to the intersecting surface of the protruding portion and extending from the one end to the other end across the inlet opening. ,
To be equipped.

(2) The rotary machine according to at least one embodiment of the present disclosure includes high-temperature parts having the configuration of (1) above.

According to at least one embodiment of the present disclosure, thermal stress can be suppressed in high temperature components.

It is the schematic which shows the whole structure of the gas turbine as an example of a rotary machine. It is sectional drawing which shows the gas flow path of a gas turbine. It is a perspective view about one of the division bodies constituting the division ring which concerns on some embodiments. It is a perspective view about one of the division bodies constituting the division ring which concerns on some embodiments. It is sectional drawing in A arrow view of FIG. It is sectional drawing in B arrow view of FIG. It is an enlarged perspective view about a part of the divided body shown in FIG. It is sectional drawing in C arrow view of FIG. It is sectional drawing in D arrow view of FIG. It is a figure which shows one Embodiment of the cross section in E arrow view of FIG. It is a figure which shows the other embodiment of the cross section in E arrow view of FIG. It is a figure which shows a part of the CC arrow cross section of FIG. 5 about the divided body which concerns on some embodiments. It is a figure which shows a part about one Embodiment of the FF arrow cross section of FIG. It is a figure which shows a part about one Embodiment of the GG arrow cross section of FIG. It is a figure which shows a part about another embodiment of the FF arrow cross section of FIG. It is a graph which shows the state of the change of the cross-sectional area of the 1st cooling passage and the 2nd cooling passage by the position in the axial direction. It is a figure which also shows the graph which shows the relationship between the position in the axial direction and each value in the divided body which concerns on one Embodiment. It is a figure which shows a part about still another embodiment of the FF arrow cross section of FIG. It is a figure which shows a part about still another embodiment of the FF arrow cross section of FIG. It is a perspective view of a part of the axial Da upstream side of the divided body which concerns on some embodiments. It is a perspective view of a part of the axial Da upstream side of the divided body which concerns on some embodiments. It is a figure which shows an example of the shape of the flow path cross section of the 1st cooling passage or the 2nd cooling passage. It is a figure which shows an example of the shape of the flow path cross section of the 1st cooling passage or the 2nd cooling passage. It is a figure which shows a part about still another embodiment of the FF arrow cross section of FIG. It is a figure which shows a part about still another embodiment of the FF arrow cross section of 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 to this, and are merely explanatory examples. No.
For example, expressions that represent relative or absolute arrangements such as "in a certain direction", "along a certain direction", "parallel", "orthogonal", "center", "concentric" or "coaxial" are exact. Not only does it represent such an arrangement, but it also represents a state of relative displacement with tolerances or angles and distances to the extent that the same function can be obtained.
For example, expressions such as "same", "equal", and "homogeneous" that indicate that things are in the same state not only represent exactly the same state, but also have tolerances or differences to the extent that the same function can be obtained. It shall also represent the existing state.
For example, an expression representing a shape such as a quadrangular shape or a cylindrical shape not only represents a shape such as a quadrangular shape or a cylindrical shape in a geometrically strict sense, but also an uneven portion or chamfering within a range in which the same effect can be obtained. The shape including the part and the like shall also be represented.
On the other hand, the expressions "equipped", "equipped", "equipped", "included", or "have" one component are not exclusive expressions that exclude the existence of other components.

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

In the present embodiment, as shown in FIG. 1, the gas turbine 10 is configured such that a compressor 11, a combustor 12, and a turbine 13 are coaxially arranged by a rotor 14, and a generator 15 is provided at one end of the rotor 14. It is connected. In the following description, the direction in which the axis Ax of the rotor 14 extends is the axial Da, the circumferential direction around the axis of the rotor 14 is the circumferential Dc, and the direction perpendicular to the axis Ax of the rotor 14 is the diameter. Let the direction Dr.

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

Further, as shown in FIG. 2, in the turbine 13, the turbine stationary blade (static blade) 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 blade (moving blade) 41 is configured such that the base end portion of the airfoil portion 43 is fixed to the platform 45. Then, the outer shroud 27 and the split ring 50 arranged on the tip end side of the rotor blade 41 are supported by the vehicle interior (turbine vehicle interior) 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 dividing ring 50.

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

The combustor 12, the moving blade 41 (for example, the platform 45), the stationary blade 21 (for example, the inner shroud 25 and the outer shroud 27), the split ring 50, and the like are high-temperature components used in a high-temperature environment in which the combustion gas FG comes into contact. , Requires cooling with a cooling medium. In the following description, as an example of the cooling structure of the high temperature component, the cooling structure of the divided ring 50 of the gas turbine 10 in which a plurality of divided bodies 51 are arranged in an annular shape along the circumferential direction Dc will be described.

FIG. 3 is a perspective view of one of the divided bodies 51 constituting 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 the closing member 517, which will be described later.
FIG. 5 is a cross-sectional view taken along the line A of FIG.
FIG. 6 is a cross-sectional view taken along the line B of FIG.
FIG. 7 is an enlarged perspective view of a part of the divided body 51 shown in FIG.
FIG. 8 is a cross-sectional view taken along the line C of FIG.
FIG. 9 is a cross-sectional view taken along the line D of FIG.
FIG. 10 is a diagram showing an embodiment of a cross section in the direction of arrow E in FIG.
FIG. 11 is a diagram showing another embodiment of the cross section in the E arrow view of FIG.

(About the split body 51)
The split ring 50 according to some embodiments is composed of a plurality of split bodies 51 arranged in a ring shape 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 inside, and a protruding portion 55 provided so as to project from the main body portion 53. In the split body 51 according to some embodiments, the protruding portion 55 includes a protruding portion 55 on the upstream side of the axial Da and a protruding portion 55 on the downstream side of the axial Da.
In the divided body 51 according to some embodiments, the outer surface 532 on the outer side of the radial Dr of the main body 53 and the side surface 55a of the protrusion 55 on the downstream side of the axial Da facing the upstream side of the axial Da are connected. It is connected by 57.
In the split body 51 according to some embodiments, the protruding portion 55 is separated from the outer surface 532 of the main body portion 53 by an inlet opening 64a described later in the cooling passage 6.
In the divided body 51 according to some embodiments, the side surface 55a of the protrusion 55 on the downstream side of the axial Da facing the upstream side of the axial Da extends in the intersecting direction with respect to the outer surface 532 of the main body 53. Is.
In the split 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 intersection 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 the inlet opening 64a described later.

As shown in FIG. 2, the divided body 51 is arranged so that the inner surface 531 inside the radial Dr of the main body 53 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 53 in the radial direction with a certain gap. In order to prevent thermal damage due to the high-temperature combustion gas FG, the main body 53 is formed with a plurality of axial passages (cooling passages) 6 extending in the axial direction Da.
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 of the divided bodies 51 according to some embodiments from the outer surface 532 side outside the radial Dr of the main body 53. It is configured as follows. The cooling air CA supplied to the split body 51 convectally cools the main body 53 of the split body 51 in the process of flowing through the cooling passage 6 and discharging it into the combustion gas FG.

In the split body 51 according to some embodiments, the protruding portion 55 constitutes a hook 59 for attaching the split body 51 to the vehicle interior 30 side of the gas turbine 10. For example, in the split body 51 according to some embodiments, as shown in FIG. 2, the claw portion 59a of the hook 59 engages with the heat shield ring 35 and is locked to the heat shield ring 35, thereby engaging the heat shield ring 35. It is supported by the passenger compartment (turbine passenger compartment) 30 via 35.

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

(First cooling passage 61)
Each of the plurality of first cooling passages 61 is arranged so as to be separated from each other in the circumferential direction Dc. The first cooling passages 61 adjacent to each other in the circumferential direction Dc are partitioned by the first partition wall 71.
Each of the plurality of first cooling passages 61 includes an upstream connection end portion 61a connected to the second cooling passage 62 via the first folding passage 66 described later.
Each of the plurality of first cooling passages 61 includes a downstream connection end portion 61b connected to the introduction passage 64 via the second folding passage 65 described later.
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 separated from the first cooling passage 61 in the perpendicular direction (radial direction Dr) of the plane including the extending direction (axial direction Da) of the plurality of first cooling passages 61. It extends along the extending direction (axial direction Da) of the first cooling passage 61 so as to communicate with any of the cooling passages 61.
Each of the plurality of second cooling passages 62 is arranged so as to be separated from each other in the circumferential direction Dc. The second cooling passages 62 adjacent to each other in the circumferential direction Dc are partitioned by the 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 the 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 the radial Dr position farther from the inner surface 531 than the plurality of second cooling passages 62.

As shown in FIGS. 5, 6 and 9, the end surface 71a on the downstream side of the axial direction Da of the first partition wall 71 may be an inclined surface inclined inward in the radial direction Dr, and is not shown. Although not, it may extend parallel to the radial Dr.

(1st turnaround 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 of the first cooling passages 61 and the second cooling passage 62 communicating with the first cooling passage 61 are connected to each other by each of the plurality of first folding passages 66.
The plurality of first folding passages 66 are arranged near the end of the main body 53 on the upstream side of the axial Da, and the end of the first cooling passage 61 on the upstream side of the axial Da and the second cooling passage 62. It is connected to the end on the upstream side of the axial Da.
For example, as in one embodiment shown in FIG. 10, it is preferable that each of the plurality of first turn-back passages 66 is arranged so as to be separated from each other in the circumferential direction Dc. That is, it is preferable that the first folding passages 66 adjacent to each other in the circumferential direction Dc are partitioned by the folding passage partition wall 76.
Thereby, the first turn-back passages 66 adjacent to each other along the circumferential direction Dc can be separated from each other. Further, since the folding passage partition wall 76 functions as a heat transfer member to the cooling air CA flowing through the first folding passage 66, the cooling capacity can be improved.
In the following description, the first turn-back passage 66 is also referred to as an intermediate turn-back passage 66.

The first folding passage 66 does not have to be partitioned by the folding passage partition wall 76, and the first folding passage 66 may be one header space as in another embodiment shown in FIG. 11, for example. An intermediate header portion 66A may be provided.

(Introduction passage 64)
As shown in FIGS. 3 to 8, the split body 51 according to some embodiments includes an introduction passage 64. The introduction passage 64 extends the first cooling passage 61 so as to be separated from the first cooling passage 61 on the side opposite to the plurality of second cooling passages 62 in the radial direction and communicate with the plurality of first cooling passages 61, respectively. It extends along the existing direction (axial direction Da) and the plate width direction (circumferential direction Dc) of the main body 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 along the circumferential direction Dc circumferential direction Dc 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 one passage not separated by the circumferential direction Dc.
The introduction passage 64 is also referred to as an upstream passage 64.

An inlet opening 64a is formed at the end of the introduction passage 64 on the upstream side 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 53.
In the divided body 51 according to some embodiments, as described above, the protruding portion 55 on the downstream side of the axial Da is separated from the outer surface 532 of the main body portion 53 by the inlet opening 64a.

(2nd turnaround passage 65)
In the split body 51 according to some embodiments, the introduction passage 64 and the plurality of first cooling passages 61 are connected by a second folding passage 65.
In the split body 51 according to some embodiments, the second folding passage 65 is arranged near the end of the main body 53 on the downstream side of the axial Da, and the end of the introduction passage 64 on the downstream side of the axial Da. Is connected to the end of the first cooling passage 61 on the downstream side in the axial direction Da.
In the following description, the second turn-back passage 65 is also referred to as an entrance-side turn-back passage 65.

(Header section 80 on the exit side)
The split body 51 according to some embodiments includes a plurality of outlet side header portions 80. In the split body 51 according to some embodiments, each of the plurality of second cooling passages 62 has an end portion on the downstream side of the axial Da connected to any one of the plurality of outlet side header portions 80. In the split body 51 according to some embodiments, a plurality of second cooling passages 62 are connected to one outlet side header portion 80. In the example shown in FIG. 10, the ends of the six second cooling passages 62 adjacent to each other in the circumferential direction Dc are connected to the upstream side of the axial Da of one outlet side header portion 80. In some embodiments, the split 51 is formed with a plurality of outlet side headers 80.

1 for discharging the cooling air CA flowing into the outlet side header 80 to the outside of the outlet side header 80, that is, to the outside of the divided body 51, on the inner wall 82 on the downstream side of the axial Da of each outlet side header 80. Two exit passages 83 are formed. The outlet passage 83 opens into the combustion gas FG at the downstream end portion 511 of the axial direction Da in the split body 51.

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

(About the risk of blockage of the cooling passage)
In a machine operated by a high-temperature working gas such as a gas turbine 10, generally, the removal of heat by cooling leads to a decrease in the thermal efficiency of the machine. Therefore, it is desirable to efficiently cool high-temperature parts with as few cooling media as possible. Therefore, by reducing the cross-sectional area of the flow path in the cooling passage, that is, the cross-sectional area of the cooling passage appearing in the cross section orthogonal to the extending direction of the cooling passage, the flow rate of the cooling medium in the cooling passage is increased and the cooling capacity is improved. Is desirable.
However, the smaller the cross-sectional area of the flow path, the higher the risk of the cooling passage being blocked by foreign matter.

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

(About 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 of FIG. 5 for the divided body 51 according to some embodiments.
FIG. 13 is a diagram showing a part of an embodiment of the FF arrow cross section of FIG.
FIG. 14 is a diagram showing a part of an embodiment of the cross section taken along the line GG of FIG.
FIG. 15 is a diagram showing a part of another embodiment of the FF arrow cross section of 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 of the axial Da.
FIG. 17 shows the relationship between the position of the axial Da and the temperature Ta of the cooling air CA, the relationship between the position of the axial Da and the cross-sectional area S of the cooling passage 6, and the axial Da in the divided body 51 according to the embodiment. It is a figure which also shows the relationship between the position of and the heat transfer coefficient hc on the cooling side, and the relationship between the position of Da in the axial direction and the heat transfer coefficient hg on the combustion gas side, respectively.

The axial Da position of the CC arrow cross section in FIG. 5 is, for example, a position between the position P4 and the position P5, and the introduction passage 64, the first cooling passage 61, and the second cooling passage 62 are arranged in the radial direction Dr. Is the stacked position.
The axial Da position of the FF arrow cross section in FIG. 5 is, for example, a position between the position P3 and the position P4, and the first cooling passage 61 and the second cooling passage 62 are laminated in the radial direction Dr. The position.
The axial Da position of the cross section taken along the line GG in FIG. 5 is, for example, a position between the positions P1 and P2, and the first cooling passage 61 and the second cooling passage 62 are laminated in the radial direction Dr. The position.

For convenience of illustration, the graph shows 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 the position P4 to the 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 a disconnection of the first cooling passage 61 at least in the section from the position P1 to the position P4 in the axial direction Da. The area S1 is larger than the cross-sectional area S2 of the second cooling passage 62.
As a result, 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, since the static pressure in the first cooling passage 61 located on the upstream side of the second cooling passage 62 with respect to the flow direction of the cooling air CA can be improved, 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.
Further, the sum of the pressure losses between the first cooling passage and the second cooling passage can be reduced as compared with 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.
In some embodiments, the flow path cross-sectional dimension of the second cooling passage 62, that is, the dimension in the direction orthogonal to the axial direction Da, has a diameter of 0 if the flow path cross section of the second cooling passage 62 is circular. If the flow path 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 be monotonically increased from the position P4 to the position P3. The cross-sectional area S1 of the first cooling passage 61 may be monotonically increased 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.
The rate at which the cross-sectional area S1 increases from the position P3 to the position P2 may be larger 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 be monotonically increased at a constant rate of increase from the position P4 to the position P2.
As shown by the broken line a2 in FIG. 16, for example, the cross-sectional area S2 of the second cooling passage 62 decreases from the position P1 to an arbitrary position on the axial Da downstream side of the position P1 toward the downstream side. You may.

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 and the heat transfer coefficient hg on the combustion gas side, and the position in the axial direction Da will be described. .. The heat transfer coefficient hc on the cooling side is the heat transfer coefficient between the cooling air CA and the wall portion forming the cooling passage 6, and the heat transfer coefficient hg on the combustion gas side is the heat transfer coefficient between the combustion gas FG and the main body 53. The heat transfer coefficient between them.
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 simplified.

Of the temperature Ta of the cooling air CA, the temperature Ta1 of the cooling air CA in the first cooling passage 61 rises from the downstream side of the axial Da to the upstream side. The temperature Ta2 of the cooling air CA in the second cooling passage 62 rises from the upstream side to the downstream side of the axial 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 in the axial direction Da to the upstream side as described above. As described above, the cross-sectional area S2 of the second cooling passage 62 is constant regardless of the axial Da position.

Since the cross-sectional area S1 of the first cooling passage 61 tends to increase from the downstream side of the axial Da to the upstream side, the flow velocity of the cooling air CA in the first cooling passage 61 tends to increase from the downstream side of the axial Da to the upstream side. It tends to decrease as it goes.
Therefore, of the cooling-side heat transfer coefficient 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.
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 axial Da position.

The heat transfer coefficient hg on the combustion gas side is higher at the axial Da position 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 (flow path area) of the cooling passage 6 is set in consideration of the tendency of the 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 orthogonal 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.
Expressing this by an equation, it becomes 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 is the maximum value 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 axial direction Da. Compared with the case where it is the same as or smaller than S2max, 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, since the static pressure in the first cooling passage 61 located on the upstream side of the second cooling passage 62 with respect to the flow direction of the cooling air CA can be improved, 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.
Further, the reliability of the gas turbine 10 can be improved by using the divided body 51 according to some embodiments.

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 of the total cross-sectional area AS2 of the second cooling passage 62 communicating with the first cooling passage 61. It should be larger than the value AS2max.
Expressing this by an equation, it becomes the following equation (2).
AS2max <S1max ... (2)
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 equal to 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, the flow velocity of the cooling air CA in the first cooling passage 61 can be suppressed to increase the static pressure. Therefore, since the static pressure in the first cooling passage 61 located on the upstream side of the second cooling passage 62 with respect to the flow direction of the cooling air CA can be improved, 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 each second in the radial direction Dr. The dimension H2 of the cooling passage 62 may be made larger than that. For example, the maximum value H1max of the dimension H1 of each first cooling passage 61 in the radial direction Dr is 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 split body 51 according to some embodiments, for example, from the upstream side connection end portion 61a to a position separated to the downstream side of the axial direction Da by a distance of 0.5 times the length of the axial direction Da of the first cooling passage 61. At any axial Da position in the section, the maximum value H1max of the dimension H1 of each first cooling passage 61 is the dimension H2 in the radial direction Dr of the second cooling passage 62 communicating with the first cooling passage 61. It should be larger than the maximum value H2max.
The length of the first cooling passage 61 in the axial direction Da is, for example, the length from the downstream connection end 61b to the upstream connection end 61a.

Further, in order to satisfy the above-mentioned formula (1) or formula (2), for example, as shown in FIG. 15, each first cooling in the passage width direction (circumferential direction Dc) orthogonal to the radial direction Dr and the axial direction Da. The dimension W1 of the passage 61 may be made 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 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 split body 51 according to some embodiments, for example, from the upstream side connection end portion 61a to a position separated to the downstream side of the axial direction Da by a distance of 0.5 times the length of the axial direction Da of the first cooling passage 61. At any axial Da position in the section, the maximum value W1max of the dimension W1 of each first cooling passage 61 is the dimension W2 in the passage width direction of the second cooling passage 62 communicating with the first cooling passage 61. It should be larger than the maximum value W2max.

In the divided body 51 according to some embodiments, each first cooling passage 61 has a cross-sectional area S1 in a region on the connection end portion (upstream side connection end portion) 61a side, which is upstream of the connection end portion. It is preferable that it is 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 cross-sectional area S1 becomes larger in the region closer to the second cooling passage 62. Therefore, of the first cooling passage 61 located on the upstream side of the second cooling passage 62 with respect to the flow direction of the cooling air CA, the static pressure in the region closer to the second cooling passage 62 can be improved, so that the second cooling passage 62 can be improved. 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 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 the circumferential direction Dc positions of the first cooling passage 61 and the second cooling passage 62)
For example, as shown in FIGS. 8, 12 to 15, each circumferential Dc position of the second cooling passage 62 is substantially the same as each circumferential Dc position of the first cooling passage 61. That is, in the divided body 51 according to some embodiments, the first partition wall 71 is substantially the same position as the second partition wall 72 in the passage width direction (circumferential direction Dc) when viewed from the radial direction Dr. It should be 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 folding passage 66 can be simplified.
It should be noted that, not all of the plurality of second cooling passages 62, but at least one or more circumferential Dc positions may be substantially the same as any of the plurality of first cooling passages 61 in the circumferential direction Dc position. ..

FIG. 18 is a diagram showing a part of still another embodiment of the FF arrow cross section of FIG. For example, as shown in FIG. 18, each circumferential Dc position of the second cooling passage 62 may be substantially different from each circumferential Dc position of the first cooling passage 61. That is, in the divided body 51 according to still another embodiment, the first partition wall 71 is substantially different from the second partition wall 72 in the passage width direction (circumferential direction Dc) when viewed from the radial direction Dr. It may be arranged in.
As a result, when viewed from the radial direction Dr, the first partition wall 71 and the second partition wall 72 are viewed from the radial direction Dr as compared with 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. Occasionally, the area where the second partition wall 72 and the first cooling passage 61 overlap increases. As a result, for example, the heat transmitted between the two adjacent second cooling passages 62 through the second partition wall 72 is easily transferred to the cooling air CA flowing through the first cooling passage 61.
It should be noted that, not all of the plurality of second cooling passages 62, but at least one or more circumferential Dc positions may be substantially different from any of the plurality of first cooling passages 61 in the circumferential direction Dc position.

(Number of first cooling passages 61 and second cooling passages 62)
FIG. 19 is a diagram showing a part of still another embodiment of the FF arrow cross section of FIG. In the embodiment shown in FIG. 19, at the axial Da position of the cross section taken along the line FF in FIG. 5, the dimension W1 of the circumferential direction Dc of one first cooling passage 61 is the circumferential direction of one second cooling passage 62. It is more than twice the size 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 of the above-described embodiments, one second cooling passage 62 is connected to one first cooling passage 61, but one first cooling passage 62 is connected. Two or more second cooling passages 62 may be connected to 61.

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

In the split body 51 according to some embodiments, a pin gauge or the like (not shown) is passed through the opening 515 and the intermediate folding passage 66 before being closed by the closing member 517 from the outside of the split body 51 to the first cooling passage 61 or the first cooling passage 61. 2 Can be inserted into the cooling passage 62. Thereby, it can be confirmed that the first cooling passage 61 and the second cooling passage 62 are not blocked. It should be noted that it is visually confirmed that the first cooling passage 61 and the second cooling passage 62 are not blocked from the outside of the divided body 51 through the opening 515 and the intermediate folding passage 66 before being closed by the closing member 517. You can also.
In this way, after it is confirmed that the first cooling passage 61 and the second cooling passage 62 are not blocked, the closing member 517 is arranged in the opening 515 and closed. The closing member 517 can be fixed to the divided body 51 by welding or the like, for example.

In the split 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 split body 51 according to some embodiments, the end face of the closing member 517 facing the axial Da downstream side is the end face of the plurality of folded passage partition walls 76 facing the axial Da upstream side. Contact at least part of.
As a result, leakage of the cooling air CA between the intermediate folding passages 66 adjacent to each other in the circumferential direction Dc across the folding passage partition wall 76 can be suppressed.
Further, when the closing member 517 comes into contact with at least a part of the folded passage partition wall 76, the closing member 517 can be easily positioned in the opening 515 when the closing member 517 is attached to the opening 515.

Since 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, the opening 515 is passed through the intermediate folding passage 66. The first cooling passage 61 and the second cooling passage 62 can be accessed. Thereby, for example, it can be confirmed whether or not the first cooling passage 61 and the second cooling passage 62 have a specified opening area at the manufacturing stage of the divided body 51, which contributes to the quality control of the divided body 51.

(About the position of the intermediate turn-back passage 66)
For example, as shown in FIG. 5, in the split body 51 according to some embodiments, at least a part of the plurality of intermediate folding passages 66 is an upstream end portion which is one end face in the axial direction Da of the split body 51. It is preferable that the distance from the upstream end surface 513a of the 513 is within twice the passage height H6 of the intermediate folding 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 on the axial Da upstream side of the intermediate folding passage 66 is twice the passage height H6 of the intermediate folding passage 66. It is preferable that it is within (Lu ≦ 2 × H6).

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

(About the position of the entrance side turnaround passage 65)
For example, as shown in FIG. 5, in the split body 51 according to some embodiments, at least a part of the inlet side folding passage 65 is the downstream end portion 511 which is the other end face in the axial direction Da in the split body 51. It is preferable that the vehicle exists at a distance within 3 times the passage height H5 of the inlet-side folding passage 65 in the radial direction from the downstream end surface 511a of the above. That is, in the divided body 51 according to some embodiments, the thickness Ld of the downstream end portion 511 located on the downstream side of the axial direction Da of the entrance side folding passage 65 is the passage height H5 of the entrance side folding passage 65. It is preferable that it is within 3 times (Ld ≦ 3 × H5).

In the inlet side return passage 65, since the introduction passage 64 and the first cooling passage 61 having different positions in the radial direction are connected, the direction of the flow of the cooling air CA changes. Therefore, the cooling air CA in the inlet side return passage 65 The heat transfer coefficient to is improved. Therefore, the cooling capacity of the region in the vicinity of the inlet-side folding passage 65 in the divided body 51 is improved.
Generally, in the vicinity of the downstream end surface 511a of the split body 51, the heat load is higher than in other regions due to the entrainment of the combustion gas FG. Therefore, it is desirable to arrange the inlet side folding passage 65 in the vicinity of the downstream end surface 511a. By arranging the inlet side folding passage 65 in the vicinity of the downstream end surface 511a, the vicinity of the downstream end surface 511a in the split body 51 can be efficiently cooled.

(Three-dimensional laminated model)
The divided body 51 according to some embodiments may be a three-dimensional laminated model formed by three-dimensional laminated modeling.
As a result, even a split body 51 provided with an elongated cooling passage 6 that is difficult to process by electric discharge machining can be obtained as a three-dimensional laminated model.

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

In the divided body 51 according to some embodiments, since the protruding portion 55 is separated from the outer surface 532 of the main body portion 53 by the inlet opening 64a of the cooling passage 6, the temperature difference between the main body portion 53 and the protruding portion 55 is large. Where there is a tendency to expand, since the main body 53 and the protruding portion 55 are connected by the connecting portion 57, the connecting portion 57 functions as a heat transfer path and suppresses the temperature difference between the main body 53 and the protruding portion 55. can. As a result, the thermal stress at the protruding portion 55 can be suppressed.
Further, by connecting the protruding portion 55 and the main body portion 53 with the connecting portion 57, the deformation of the divided body 51 can be suppressed.
In the split 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 protruding portion 55 is continuous from the side surface 55a (hereinafter, simply referred to as the side surface 55a) facing the axial direction Da upstream side of the protruding portion 55 on the downstream side of the axial direction Da. The surface facing the inside of Dr is an inclined surface (protruding portion inclined surface) 55b toward the inside of Dr in the radial direction toward the downstream side of Da in the axial direction. 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 inclined surface 55b of the protrusion and the outer surface 532 of the main body 53 face each other is the axial direction of the introduction passage 64. Since it is the end on the upstream side of Da, the axial Da position is the inlet end 641 of the introduction passage 64.

In the split body 51 according to some embodiments, as shown in FIG. 5, a part of the connecting portion 57 is located on the downstream side of Da in the axial direction from the inlet end 641 of the introduction passage 64. That is, in the divided body 51 according to some embodiments, the connecting portion 57 is arranged so that the invading portion 575, which is a part of the connecting portion 57, invades the inside of the cooling passage 6.
In the split body 51 according to some embodiments, the intruding portion 575 is connected to the protruding portion inclined surface 55b. That is, in the divided body 51 according to some embodiments, a part of the connecting portion 57 is connected to the protruding portion inclined surface 55b which is the forming wall surface of the cooling passage 6 connected to the intersecting surface (side surface 55a) of the protruding portion 55. ing.
As a result, the connection region between the protruding portion 55 and the connecting portion 57 can be secured in a region other than the intersection surface (side surface 55a), and the temperature difference between the main body portion 53 and the protruding portion 55 can be further suppressed.

In the split body 51 according to some embodiments, as shown in FIG. 5, the surface of the intrusion portion 575 facing inward in the radial direction is an inclined surface (outward in the radial direction Dr) toward the downstream side of the axial Da. Intrusion portion inclined surface) 575a. The intruding portion inclined surface 575a is separated from the outer surface 532. That is, at least a part of the invading portion 575 is separated from the outer surface 532.
Therefore, as compared with the case where the intrusion portion inclined surface 575a is connected to the outer surface 532, the partial volume in which the intrusion portion 575 invades 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 The decrease in area can be suppressed. Therefore, it is possible to suppress an increase in the flow velocity of the cooling air CA flowing through the introduction passage 64 in the vicinity of the inlet opening 64a, and to suppress a pressure loss in the introduction passage 64.
Further, since it is possible to suppress an increase in the flow velocity of the cooling air CA flowing through the introduction passage 64 in the vicinity of the inlet opening 64a, it is possible to prevent the protruding portion 55 from being excessively cooled, and the main body portion 53 and the protruding portion 55 The temperature difference can be further suppressed.
Further, since the protrusion 55 can be suppressed from being excessively cooled, the temperature rise of the cooling air CA in the introduction passage 64 can be suppressed, and the decrease in the cooling capacity in the first cooling passage 61 and the second cooling passage 62 can be suppressed. ..

(Regarding the relationship between the outer surface 532 and the cooling passage 6)
In the divided body 51 according to some embodiments, a part of the outer surface 532 of the main body 53 constitutes a part of the cooling passage 6. More specifically, in the split 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-mentioned crossing direction. It includes a downstream passage (first cooling passage 61) arranged at a position, and an inlet side folding passage 65 which is a folding passage connecting the upstream passage 64 and the downstream passage 61. As shown in FIG. 5, a part of the outer surface 532 of the main body 53 constitutes a part of the upstream passage 64 and is connected to the forming wall surface 65a of the entrance side folded passage 65.

As a result, the cooling air CA easily flows into the cooling passage 6 along the outer surface 532 of the main body 53.
Further, the inlet opening 64a is on the other side (upstream side of the axial Da) from the end (downstream end 511) of the main body 53 on one side (downstream side of the axial Da) along the outer surface 532 of the main body 53. The cooling air CA flowing in from the inlet opening 64a can be guided to the downstream side of the axial Da by the upstream passage 64, and the cooling air CA can be guided to the inlet side folding passage even if the cooling air CA is provided at a position away from the inlet side. By guiding the cooling air CA to the downstream passage 61 via the 65, the cooling air CA can be guided from the inlet side folded passage 65 toward the upstream side of the axial Da.

(About the upstream inclined surface 577 of the connecting portion 57)
In the split body 51 according to some embodiments, the connecting portion 57 is an upstream inclined surface which is an inclined surface extending obliquely from one end 571 toward the other end 573 side with respect to the outer surface 532 of the main body 53. Has 577.
The upstream-side inclined surface 577 extends from one end 571 on the upstream side in the axial direction Da to the claw portion 59a of the hook 59, and is an inclined surface extending outward in the radial direction Dr toward the downstream side in the axial direction Da. be.

In the split body 51 according to some embodiments, the main body extends from one end 571 where the upstream inclined surface 577 is connected to the outer surface 532 of the main body 53 to the claw portion 59a of the hook 59 located radially outside the protruding portion 55. Since it extends diagonally with respect to the outer surface 532 of the portion 53, the connecting portion 57 becomes wider at the hem from the tip end side (diameter direction Dr outside) to the base end side (diameter direction Dr inside) of the protrusion portion 55. It will have a shape. Therefore, the area of the connecting portion between one end 571 of the connecting portion 57 and the outer surface 532 of the main body portion 53 can be increased, the amount of heat transfer from the main body portion 53 to the protruding portion can be increased, and the main body portion 53 and the protruding portion can be increased. The temperature difference from 55 can be further suppressed.

Further, since the upstream inclined surface 577 is an inclined surface toward the outside of the radial Dr as it goes toward the downstream side of the axial Da, for example, when the divided body 51 according to some embodiments is formed by three-dimensional laminated molding, it is laminated. 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 proceeds. Therefore, the connecting portion 57 can be formed without forming the 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 the laminated molding can be shortened, and the process of removing the supports can be simplified.

Further, as described above, the connecting portion 57 becomes a portion whose size gradually increases along the radial direction as the molding proceeds, so that the protruding portion 55 has a shape when molding along the stacking direction. It is possible to alleviate sudden changes. Generally, in metal lamination molding, if there is a sudden change portion whose shape changes suddenly when molding along the lamination direction, the outer edge of the modeled object appearing in a cross section orthogonal to the lamination direction in the vicinity of the sudden change portion. The position may shift in the direction orthogonal to the stacking direction.
As described above, since the connecting portion 57 can alleviate the sudden change in shape of the protruding portion 55 when molding along the stacking direction, the shape of the divided body 51 is distorted in the vicinity of the protruding portion 55. It can be suppressed that it ends up.

(Regarding the shape of the flow path cross section of the first cooling passage 61 and the second cooling passage 62)
In some of the above-described embodiments, the shape of the flow path cross section of the first cooling passage 61 and the second cooling passage 62 is rectangular, but it may be circular or elliptical. Further, the shape of the flow path cross section 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 and a circle or an ellipse.
For example, the shape of the flow path cross section of the first cooling passage 61 and the shape of the flow path cross section of the second cooling passage 62 may be different. For example, the shape of the flow path cross section of the first cooling passage 61 may be circular, and the shape of the flow path cross section of the second cooling passage 62 may be polygonal. Further, for example, the shapes of the flow path cross sections of all the first cooling passages 61 do not have to be the same, but may be different. Similarly, the shape of the flow path cross section of all the second cooling passages 62 does not have to be the same, but may be different.

FIG. 22A is a diagram showing an example of a polygon other than a regular polygon as an example of the shape of the flow path cross section of the first cooling passage 61 or the second cooling passage 62.
FIG. 22B is a diagram showing an example of a shape in which a polygon and a circle are combined as an example of the shape of the flow path cross section of the first cooling passage 61 or the second cooling passage 62.
For example, the shape of the flow path cross section shown in FIGS. 22A and 22B has an inclined surface 601 inclined in the vertical direction shown on the upper side of the flow path.
For example, when the divided body 51 is formed by three-dimensional laminated molding, if the stacking direction in the cooling passage 6 is from the lower side to the upper side 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 the shape collapse of the inclined surface 601 which becomes an overhang region at the time of modeling.

FIG. 23A is a diagram showing a part of still another embodiment of the FF arrow cross section of FIG.
For example, as shown in FIG. 23A, the shape of the flow path cross section of the first cooling passage 61 and the second cooling passage 62 may be triangular. In this case, in the second cooling passage 62, it is preferable that one side 602 of the cross section of the flow path having a triangular shape when viewed along the axial direction Da faces the inside of the radial Dr of the main body 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 path cross section when viewed from the inner surface 531 of the main body 53 toward the outside in the radial direction. The cooling air CA flowing through the second cooling passage 62 can efficiently cool the area on the inner surface 531 side of the main body 53.
As shown in FIG. 23A, in the second cooling passage 62, when one side 602 of the flow path cross section having a triangular shape when viewed along the axial direction Da is directed toward the inside of the radial direction Dr of the main body 53. , One vertex 603 of the triangle points outward Dr in the radial direction. Therefore, as shown in FIG. 23A, in the first cooling passage 61, one apex 604 of a triangle having a triangular shape when viewed along the axial direction Da is directed to the inside of the radial Dr, and the apex is formed. If the 604 is overlapped with the second cooling passage 62 in the radial direction Dr, the thickness of the main body 53 along the radial direction Dr can be suppressed.

FIG. 23B is a diagram showing a part of still another embodiment of the FF arrow cross section of FIG.
For example, as shown in FIG. 23B, the shape of the flow path cross section of the first cooling passage 61 may be a rhombus, and the shape of the flow path cross section of the second cooling passage 62 may be a triangle. In this case, as in the example shown in FIG. 23A, in the second cooling passage 62, one side 602 of the flow path cross section having a triangular shape when viewed along the axial direction Da is inside the radial Dr of the main body 53. It is good 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 path cross section when viewed from the inner surface 531 of the main body 53 toward the outside in the radial direction. The cooling air CA flowing through the second cooling passage 62 can efficiently cool the area on the inner surface 531 side of the main body 53.
As shown in FIG. 23B, in the second cooling passage 62, when one side 602 of the flow path cross section having a triangular shape when viewed along the axial direction Da is directed toward the inside of the radial direction Dr of the main body 53. , One vertex 603 of the triangle points outward Dr in the radial direction. Therefore, as shown in FIG. 23B, in the first cooling passage 61, one apex 605 of a rhombus having a rhombus shape when viewed along the axial direction Da is directed to the inside of the radial Dr, and the apex is formed. If the 605 is overlapped with the second cooling passage 62 in the radial direction Dr, the thickness of the main body 53 along the radial direction Dr can be suppressed.

The present disclosure is not limited to the above-described embodiment, and includes a modified form of the above-described embodiment and a combination of these embodiments as appropriate.

The contents described in each of the above embodiments are grasped as follows, for example.
(1) The high-temperature parts according to at least one embodiment of the present disclosure are a plate-shaped main body portion 53 having a cooling passage 6 inside and a protruding portion 55 provided so as to project from the main body portion 53. It is separated from the surface (outer surface 532) of the main body 53 by the inlet opening 64a, and is connected to the protruding portion 55 having an intersecting surface (side surface 55a) extending in the intersecting direction with respect to the surface and the outer surface 532 of the main body 53. One end 571 and the other end 573 connected to the intersecting surface (side surface 55a) of the protrusion 55, and the connecting portion 57 extending from one end 571 to the other end 573 across the inlet opening 64a. ..

According to the configuration of (1) above, since the protruding portion 55 is separated from the outer surface 532 of the main body portion 53 by the inlet opening 64a of the cooling passage 6, the temperature difference between the main body portion 53 and the protruding portion 55 increases. As a tendency, since the main body 53 and the protruding portion 55 are connected by the connecting portion 57, the connecting portion 57 functions as a heat transfer path, and the temperature difference between the main body 53 and the protruding portion 55 can be suppressed. As a result, the thermal stress at the protruding portion 55 can be suppressed.

(2) In some embodiments, in the configuration of (1) above, the connecting portion 57 is arranged so that a part of the connecting portion 57 penetrates into the cooling passage 6.

According to the configuration of (2) above, the connection region between the protruding portion 55 and the connecting portion 57 can be secured in a region other than the intersection surface (side surface 55a), and the temperature difference between the main body portion 53 and the protruding portion 55 can be further suppressed. ..

(3) In some embodiments, in the configuration of (2) above, a part of the connecting portion 57 is a protruding portion inclined surface which is a forming wall surface of a cooling passage 6 connected to an intersecting surface (side surface 55a) of the protruding portion 55. Connected to 55b.

According to the configuration of (3) above, the connection region between the protruding portion 55 and the connecting portion 57 can be secured in a region other than the intersection surface (side surface 55a), and the temperature difference between the main body portion 53 and the protruding portion 55 can be further suppressed. ..

(4) In some embodiments, in any of the above configurations (1) to (3), a part of the surface (outer surface 532) of the main body 53 constitutes a part of the cooling passage 6.

According to the configuration of (4) above, the cooling medium easily flows into the cooling passage 6 along the outer surface 532 of the main body 53.

(5) In some embodiments, in the configuration of (4) above, the cooling passage 6 is arranged at a position separated from the upstream passage 64 including the inlet opening 64a and the upstream passage 64 in the above-mentioned crossing direction. The downstream passage 61 and the entrance side turn-back passage 65, which is a turn-back passage connecting the upstream passage 64 and the downstream passage 61, are included. A part of the outer surface 532 of the main body 53 constitutes a part of the upstream passage 64 and is connected to the forming wall surface 65a of the entrance side folded passage 65.

According to the configuration of (5) above, the inlet opening 64a is from the end portion (downstream side end portion 511) of the main body portion 53 on one side (downstream side of the axial Da) in the direction along the outer surface 532 of the main body portion 53. Even when the cooling medium is provided at a position distant from the side (upstream side of Da in the axial direction), the cooling medium flowing in from the inlet opening 64a can be guided to the one side by the upstream passage 64, and the cooling medium can be guided to the one side. By guiding the cooling medium from the inlet-side folding passage 65 to the downstream passage 61 via the inlet-side folding passage 65, the cooling medium can be guided from the inlet-side folding passage 65 toward the other side.

(6) In some embodiments, in any of the configurations (1) to (5) above, the connecting portion 57 is directed from one end or 571 toward the other end 573 side with respect to the outer surface 532 of the main body 53. It has an upstream inclined surface 577 which is an inclined surface extending diagonally.

According to the configuration of (6) above, the main body portion 53 is from one end 571 where the upstream inclined surface 577 is connected to the outer surface 532 of the main body portion 53 to the claw portion 59a of the hook 59 located on the radial outer side of the protruding portion 55. Since the connecting portion 57 extends diagonally with respect to the outer surface 532 of the above, the connecting portion 57 has a shape in which the hem expands from the tip side (diameter direction Dr outside) to the base end side (diameter Dr inside) of the protrusion 55. Will have. Therefore, the area of the connecting portion between one end 571 of the connecting portion 57 and the outer surface 532 of the main body portion 53 can be increased, the amount of heat transfer from the main body portion 53 to the protruding portion 55 can be increased, and the main body portion 53 and the protruding portion 53 can be projected. The temperature difference from the portion 55 can be further suppressed.

(7) In some embodiments, in any of the configurations (1) to (6) above, the inlet opening 64a is a slit opening extending along the plate width direction (circumferential direction Dc) of the main body 53. Is. The connecting portion 57 includes a plurality of connecting portions 57 provided within the formation range of the slit opening in the plate width direction.

According to the configuration of (7) above, a plurality of connecting portions 57 form a slit opening extending along the plate width direction and extending along the plate width direction (a portion forming the inlet opening 64a). Can be reinforced by.

(8) In some embodiments, in any of the configurations (1) to (7) above, the high temperature component constitutes a split ring 50 of the gas turbine 10 formed in an annular shape along the circumferential direction Dc. The divided body 51.

According to the configuration of the above (8), when the divided body has the structure of any one of the above (1) to (7), the thermal stress can be suppressed in the protruding portion 55 of the divided body 51.

(9) In some embodiments, in the configuration of (8) above, the protrusion 55 constitutes a hook 59 for attaching the split body 51 to the vehicle interior 30 side of the gas turbine 10.

According to the configuration (9) above, thermal stress can be suppressed at the protruding portion 55 constituting the hook 59 of the split body 51.

(10) In some embodiments, in any of the configurations (1) to (9) above, the high temperature component is a three-dimensional laminated model.

According to the configuration of (10) above, even when the protruding portion 55 becomes an overhang region when the high temperature component is formed by laminated molding, the connecting portion 57 can be formed by devising the shape of the connecting portion 57 or the like. Can be used as a support member during laminated molding. This makes it possible to simplify the process of removing the support member after the laminated molding.

(11) The rotary machine (gas turbine 10) according to at least one embodiment of the present disclosure includes high-temperature parts having any of the above configurations (1) to (10).

According to the configuration (11) above, the thermal stress at the protruding portion 55 can be suppressed and the reliability of the rotating machine can be improved.

6 Cooling passage 10 Gas turbine 50 Dividing ring 51 Dividing body 53 Main body 55 Protruding portion 55a Side surface 57 Connecting portion 59 Hook 61 First cooling passage (downstream passage)
62 Second cooling passage 64 Introduction passage (upstream passage)
65 Second turnaround passage (entrance side turnaround passage)
65a Formed wall surface 66 1st turn-back passage (intermediate turn-back passage)
71 1st partition wall 72 2nd partition wall 515 Opening 517 Closing member 531 Inner surface 532 Outer surface 571 One end 573 Other end 577 Upstream side inclined surface

Claims (11)

A plate-shaped main body with a cooling passage inside,
A projecting portion that is provided so as to project from the main body portion, is separated from the surface of the main body portion by an inlet opening of the cooling passage, and has an intersecting surface extending in an intersecting direction with respect to the surface portion.
A connecting portion having one end connected to the surface of the main body portion and the other end connected to the intersecting surface of the protruding portion and extending from the one end to the other end across the inlet opening. ,
High temperature parts with. The high-temperature component according to claim 1, wherein the connecting portion is arranged so that a part of the connecting portion penetrates into the inside of the cooling passage. The high-temperature component according to claim 2, wherein the part of the connecting portion is connected to a wall surface forming the cooling passage connected to the intersecting surface of the protruding portion. The high-temperature component according to any one of claims 1 to 3, wherein a part of the surface of the main body portion constitutes a part of the cooling passage. The cooling passage includes an upstream passage including the inlet opening, a downstream passage arranged at a position separated from the upstream passage in the intersecting direction, and a folded passage connecting the upstream passage and the downstream passage. Including
The high-temperature component according to claim 4, wherein the part of the surface constitutes a part of the upstream passage and is connected to the forming wall surface of the folded passage. The high-temperature component according to any one of claims 1 to 5, wherein the connecting portion has an inclined surface extending obliquely from the one end toward the other end side with respect to the surface of the main body portion. The entrance opening is a slit opening extending along the plate width direction of the main body portion.
The high-temperature component according to any one of claims 1 to 6, wherein the connecting portion includes a plurality of connecting portions provided within the formation range of the slit opening in the plate width direction. The high-temperature component according to any one of claims 1 to 7, wherein the high-temperature component is a split body forming a split ring of a gas turbine formed in an annular shape along the circumferential direction. The high-temperature component according to claim 8, wherein the protruding portion constitutes a hook for attaching the divided body to the vehicle interior side of the gas turbine. The high-temperature component according to any one of claims 1 to 9, wherein the high-temperature component is a three-dimensional laminated model. A rotating machine including the high temperature component according to any one of claims 1 to 10.

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