JP2023140430A - Blade segment and rotary machine - Google Patents

Abstract

To facilitate assembly of a rotary machine, while suppressing deterioration in efficiency of the rotary machine.SOLUTION: A blade segment according to at least one embodiment of the present disclosure comprises: a first segment that includes one first airfoil part, a first outside shroud provided on the outside in a blade height direction of the one first airfoil part, and a first inside shroud provided on the inside in the blade height direction of the one first airfoil part; and a second segment that comprises one second airfoil part, a second outside shroud provided on the outside in the blade height direction of the one second airfoil part, and a second inside shroud provided on the inside in the blade height direction of the one second airfoil part. The first outside shroud and the second outside shroud are connected with bolts, the first inside shroud and the second inside shroud are connected with bolts, and a recess part is formed across the first outside shroud and the second outside shroud.SELECTED DRAWING: Figure 3

Description

TECHNICAL FIELD This disclosure relates to airfoil segments and rotating machines.

For example, in a gas turbine as an example of a rotating machine, a turbine stator blade having a continuous blade structure in which two airfoils are arranged for one outer shroud and one inner shroud is known. (For example, see Patent Document 1).

Japanese Patent Application Publication No. 2015-090108

However, in a turbine stator blade having a continuous blade structure such as the turbine stator blade described in Patent Document 1, two airfoil portions are arranged close to each other, so a thermal barrier coating is applied to the airfoil portion by, for example, thermal spraying. During construction, when two airfoils face each other, the airfoil surface of one airfoil will be hidden behind the other airfoil. Therefore, there was a problem in that it was difficult to apply a thermal barrier coating to the facing surfaces of the two airfoils.

Therefore, the above problem can be solved by disposing one airfoil for one outer shroud and one inner shroud. However, because the number of circumferential divisions of the outer shroud and inner shroud increases, cooling air flows into the combustion gas flow path from gaps between circumferentially adjacent outer shrouds and between inner shrouds. There is a risk that the flow rate will increase. The increased flow of cooling air into the combustion gas flow path has a negative impact on the efficiency of the gas turbine.

In order to limit the flow rate of cooling air into the flow path of the combustion gases, two of the segments, in which one airfoil is arranged for one outer shroud and one inner shroud, are connected, for example by bolted connections. By doing so, it is possible to eliminate gaps between the outer shrouds of the two segments and between the inner shrouds of the two segments.

By the way, the turbine stationary blade receives a force from the combustion gas that attempts to rotate the turbine stationary blade in the circumferential direction in order to change the flow direction of the combustion gas. Therefore, in order to prevent the turbine stator blade from rotating in the circumferential direction within the casing and to position the turbine stator blade, a positioning pin attached to the casing is configured to engage with the turbine stator blade. There is.

Since turbine stationary blades undergo thermal elongation in the circumferential direction, it is necessary to take this thermal elongation into account and set a gap between the positioning pin and the positioning pin at the portion that engages with the positioning pin.
For example, if one wing segment is constructed by bolting two segments together as described above, for example, if the positioning pin is engaged at a position between two circumferentially adjacent wing segments, , it is necessary to provide a gap between the blade segment and the positioning bolt that can absorb the thermal elongation of the blade segment over the entire length in the circumferential direction, and the size of the gap becomes relatively large.

If the size of the gap is relatively large, the blade segment can be moved circumferentially by the gap during turbine assembly, making it easier to assemble other parts, such as a seal ring adjacent to the blade segment. This may affect the assembly of the turbine, such as making it difficult to assemble the turbine.

In view of the above-mentioned circumstances, at least one embodiment of the present disclosure aims to facilitate assembly of a rotating machine while suppressing a decrease in efficiency of the rotating machine.

(1) A wing segment according to at least one embodiment of the present disclosure includes:
one first airfoil, a first outer shroud provided on the outer side of the one first airfoil in the blade height direction, and the first outer shroud provided on the inner side of the one first airfoil in the blade height direction. a first segment comprising a first inner shroud provided;
one second airfoil, a second outer shroud provided on the outer side of the one second airfoil in the blade height direction, and the second outer shroud provided on the inner side of the one second airfoil in the blade height direction. a second segment including a second inner shroud provided;
Equipped with
the first outer shroud and the second outer shroud are bolted together;
the first inner shroud and the second inner shroud are bolted together;
A recessed portion is formed across the first outer shroud and the second outer shroud.

(2) A rotating machine according to at least one embodiment of the present disclosure,
A wing segment having the configuration of (1) above,
a casing covering the wing segment;
a positioning pin attached to the casing and whose tip engages with the recess;
Equipped with

According to at least one embodiment of the present disclosure, assembly of the rotating machine can be facilitated while suppressing a decrease in efficiency of the rotating machine.

1 is a schematic diagram showing the overall configuration of a gas turbine as an example of a rotating machine. FIG. 3 is a cross-sectional view showing a gas flow path of the turbine. FIG. 2 is a diagram of a turbine stationary blade according to an embodiment viewed from the outside in the radial direction. 4 is a view taken along the line IV-IV in FIG. 3. 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 by 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 that express shapes such as squares and cylinders do not only refer to shapes such as squares and cylinders in a strictly geometric sense, but also include irregularities 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,""equipping,""containing," or "having" one component are not exclusive expressions that exclude the presence of other components.

FIG. 1 is a schematic diagram showing the overall configuration of a gas turbine as an example of a rotating machine, and FIG. 2 is a sectional view showing a gas flow path of the turbine.

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 of the rotor 14 extends is referred to as an axial direction Da, the circumferential direction centered on the axis of the rotor 14 is referred to as a circumferential direction Dc, and the direction perpendicular to the axis Ax of the rotor 14 is referred to as a radial direction. Dr. Note that the radial direction Dr is referred to as the blade height direction.

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 a split ring 51 disposed on the tip side of the rotor blade 41 are supported by the casing (turbine casing) 30 via a heat shield ring 53, 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 51.

FIG. 3 is a diagram of the turbine stationary blade 21 according to one embodiment viewed from the outside in the radial direction Dr.
FIG. 4 is a view taken along the line IV-IV in FIG. 3.
The turbine stationary blade 21 according to one embodiment is a single blade in which two segments 101 in which one airfoil section 23 is arranged for one outer shroud 27 and one inner shroud 25 are connected by bolt connection. It is configured as a segment 100.
Details of the wing segment 100 according to one embodiment will be described in detail later.

As shown in FIG. 3, the airfoil portion 23 is formed from a ventral wing surface 23c formed of a concave pressure surface and a dorsal wing surface 23d formed of a convex surface that is a suction surface. The ventral wing surface 23c and the dorsal wing surface 23d are connected by an upstream leading edge 23a and a downstream trailing edge 23b, forming an integrated airfoil portion 23.

Note that the inner shroud 25 and the outer shroud 27 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. When there is no need to particularly distinguish between the inner shroud 25 and the outer shroud 27, the inner shroud 25 and the outer shroud 27 may be simply referred to as the shroud 2.

(About wing segment 100)
Wing segment 100 according to one embodiment includes two segments 101 that are bolted together, as described above. In the following description, for convenience of explanation, the segment 101 arranged such that the ventral wing surface 23c faces the dorsal wing surface 23d of the partner segment 101 is referred to as the first segment 101A, and the dorsal wing surface 23d is the partner segment. The segment 101 arranged to face the ventral wing surface 23c of the wing 101 is referred to as a second segment 101B. In FIG. 3, the segment 101 on the left side of the drawing is the first segment 101A, and the segment on the right side of the drawing is the second segment 101B.

The first segment 101A includes one first airfoil section 23A, a first outer shroud 27A provided on the outer side of the one first airfoil section 23A in the blade height direction, and a first outer shroud 27A provided outside the one first airfoil section 23A in the blade height direction. A first inner shroud 25A provided on the inner side in the blade height direction.
Similarly, the second segment 101B includes one second airfoil section 23B, a second outer shroud 27B provided on the outside of the one second airfoil section 23B in the blade height direction, and one second airfoil section 23B. A second inner shroud 25B is provided inside the portion 23B in the blade height direction.

In the first segment 101A of the blade segment 100 according to one embodiment, the first outer shroud 27A is capable of storing cooling air supplied from the outside on the outside of the radial direction Dr, which is the surface opposite to the gas path surface 27a. It includes an outer region 155 which is a space. The outer region 155 of the first segment 101A includes a peripheral edge of the first outer shroud 27A, that is, a first side end 151A on the ventral wing surface 23c side and a dorsal wing that form both circumferential ends of the first outer shroud 27A. This is a region surrounded by the first side end 151A on the side of the surface 23d, the first front edge end 153A on the front edge 23a side in the axial direction, and the first rear edge end 154A on the rear edge 23b side, and the radial direction Dr A space 157 recessed inward is formed. The outer region bottom surface 155a forming the bottom surface of the outer region 155 forms a radially outer surface of the gas path surface 27a. That is, the space portion 157 of the first segment 101A has an outer region bottom surface 155a, a first side end portion 151A that is an outer wall portion extending in the blade height direction (radial direction) from the outer region bottom surface 155a, and a first front end portion 151A. This is a space formed from the edge portion 153A and the first rear edge portion 154A.
The gas turbine 10 according to one embodiment is configured such that cooling air CA is supplied from the outside to the space 157 of the first segment 101A.

In the first segment 101A of the wing segment 100 according to one embodiment, the first inner shroud 25A has a first side end 156A on the ventral wing surface 23c side that forms a circumferential end of the first inner shroud 25A. .

Similarly, in the second segment 101B of the blade segment 100 according to one embodiment, the second outer shroud 27B allows cooling air supplied from the outside to be directed outward in the radial direction Dr, which is the surface opposite to the gas path surface 27a. It includes an outer region 155 that is a storage space. The outer region 155 of the second segment 101B includes a peripheral edge of the second outer shroud 27B, that is, a second side end 151B on the ventral wing surface 23c side forming both ends of the second outer shroud 27B in the circumferential direction, and a dorsal wing. This is a region surrounded by the second side end 151B on the surface 23d side, the second front edge end 153B on the front edge 23a side in the axial direction, and the second rear edge end 154B on the rear edge 23b side, and the radial direction Dr A space 157 recessed inward is formed. The outer region bottom surface 155a forming the bottom surface of the outer region 155 forms a radially outer surface of the gas path surface 27a. That is, the space portion 157 of the second segment 101B has an outer region bottom surface 155a, a second side end portion 151B that is an outer wall portion extending in the blade height direction (radial direction) from the outer region bottom surface 155a, and a second front end portion 151B. This is a space formed from the edge portion 153B and the second rear edge portion 154B.
The gas turbine 10 according to one embodiment is configured such that cooling air CA is supplied from the outside to the space 157 of the second segment 101B.

In the second segment 101B of the wing segment 100 according to one embodiment, the second inner shroud 25B has a second side end 158B on the dorsal wing surface 23d side that forms a circumferential end of the second inner shroud 25B. .

(Regarding the bolt connection between the first segment 101A and the second segment 101B)
In the first segment 101A of the wing segment 100 according to one embodiment, the first side end 151A on the ventral wing surface 23c side of the first outer shroud 27A and the first end portion 151A on the ventral wing surface 23c side of the first inner shroud 25A A bolt hole 161 is formed to penetrate the side end portion 156A in the circumferential direction.
In the first segment 101A of the wing segment 100 according to one embodiment, a plurality of bolt holes 161 may be formed at intervals in the axial direction in the first side end 151A of the first outer shroud 27A. In the example shown in FIG. 3, there are two bolt holes 161, but there may be one, or three or more bolt holes.
Although not shown, one bolt hole 161 is formed in the first side end 156A of the first inner shroud 25A, but a plurality of bolt holes 161 are formed at intervals in the axial direction. It's okay.

In the second segment 101B of the wing segment 100 according to one embodiment, the second side end portion 151B on the dorsal wing surface 23d side of the second outer shroud 27B and the second side end portion 151B on the dorsal wing surface 23d side of the second inner shroud 25B A bolt hole 162 is formed that passes through the side end portion 157B in the circumferential direction.
In the second segment 101b of the wing segment 100 according to one embodiment, a plurality of bolt holes 162 may be formed at intervals in the axial direction in the second side end 151B of the second outer shroud 27B. In the example shown in FIGS. 3 and 4, there are two bolt holes 162, but there may be one, or three or more bolt holes.
In the example shown in FIG. 4, one bolt hole 161 is formed in the second side end 157B of the second inner shroud 25B, but a plurality of bolt holes 161 are formed at intervals in the axial direction. You can leave it there.

The positions of the bolt hole 161 of the first segment 101A and the bolt hole 162 of the second segment 101B are set so that the bolt 171 can be inserted into the bolt hole 161 and the bolt hole 162, respectively.
In the wing segment 100 according to one embodiment, the first segment 101A and the second segment 101B are bolted together by inserting the bolt 171 into the bolt hole 161 and the bolt hole 162 and attaching the nut 172.
In addition, in the turbine 13 of the gas turbine 10 according to one embodiment, a plurality of the blade segments 100 described above are arranged in the circumferential direction. Wing segments 100 adjacent in the circumferential direction are not bolted together. A seal plate (not shown) is arranged between the circumferentially adjacent blade segments 100 to prevent cooling air CA from leaking between the circumferentially adjacent blade segments 100.

(About the recess)
The wing segment 100 according to one embodiment has a recess 181 formed across the first outer shroud 27A and the second outer shroud 27B.
Specifically, the recess 181 is located downstream of the first side end 151A of the first segment 101A on the ventral wing surface 23c side and the second side end 151B of the second segment 101B on the dorsal wing surface 23d side. In the side region, it is formed to straddle the first side end portion 151A and the second side end portion 151B and to be recessed toward the inside in the radial direction.
The recess 181 is configured such that the blade segment 100 according to one embodiment engages with a positioning pin 191 for restricting movement of the blade segment 100 in the circumferential direction within the turbine casing 30 which is a casing that covers the blade segment 100. It is configured.
That is, in the wing segment 100 according to one embodiment, the recess 181 is formed between the first outer shroud 27A and the second outer shroud 27B so as to sandwich the positioning pin 191 from the circumferential direction.

The blade segment 100 receives a force from the combustion gas FG that attempts to rotate the blade segment 100 in the circumferential direction in order to change the flow direction of the combustion gas FG. Therefore, in order to prevent the blade segment 100 from rotating in the circumferential direction within the turbine casing 30 and to position the blade segment 100, a positioning pin 191 attached to the turbine casing 30 engages with the recess 181. is configured to do so.

In the blade segment 100 according to one embodiment, gaps between the outer shrouds 27 of the first segment 101A and the second segment 101B and between the inner shrouds 25 can be eliminated, and cooling air CA leaks from the gaps. Therefore, it is possible to suppress a decrease in efficiency in the gas turbine 10 including the blade segment 100 according to the embodiment.
Further, in the blade segment 100 according to one embodiment, the blade segment 100 in which the first segment 101A and the second segment 101B are bolted together is attached to the turbine casing 30 of the gas turbine 10. By engaging the positioning pin 191 with the recess 181, movement of the blade segment 100 in the circumferential direction can be restricted. Furthermore, even if the blade segment 100 is thermally expanded in the circumferential direction, the first segment 101A on one side in the circumferential direction is mainly thermally expanded from the recess 181 to one side, centering on the recess 181 that the positioning pin 191 engages, and the positioning The second segment 101B on the other side in the circumferential direction about the recess 181 with which the pin 191 engages mainly expands thermally from the recess 181 to the other side. Therefore, when the blade segment 100 is cold, the gap between the positioning pin 191 and the recess 181 can be made relatively small. This makes it relatively easy to assemble other members such as a seal ring adjacent to the blade segment 100, and the gas turbine 10 including the blade segment 100 can be easily assembled.

A gas turbine 10 according to an embodiment includes a blade segment 100 according to an embodiment, a turbine casing 30 that covers the blade segment 100, and a positioning pin that is attached to the turbine casing 30 and whose tip end engages with a recess 181. 191.
As a result, the gaps between the outer shrouds 27 and the inner shrouds 25 of the first segment 101A and the second segment 102A can be eliminated, and leakage of cooling air CA from the gaps can be suppressed, so that the gas turbine 10 efficiency reduction can be suppressed.
Further, according to the gas turbine 10 according to the embodiment, it is relatively easy to assemble other members such as a seal ring adjacent to the blade segment 100, and the assembly of the gas turbine 10 can be facilitated.

(Regarding the cooling structure of the outer shroud 27)
The cooling structure of the outer shroud 27 will be described below.
A collision plate (not shown) having a plurality of through holes is arranged in the outer region 155 of the first segment 101A and the second segment 101B so as to cover the entire outer region bottom surface 155a. Note that the collision plate (not shown) covers the hatched area in FIG. 3 .
The outer region 155 forming the space 157 is divided by a collision plate (not shown) into a space 157 on the outside of the Dr in the radial direction and a space 157 on the inside of the Dr in the radial direction. The space 157 on the outside of the radial direction Dr and the space 157 on the inside of the radial direction Dr communicate with each other via a through hole of a collision plate (not shown).

The cooling air supplied to the space 157 is supplied to the space 157 on the inside of the Dr in the radial direction through a through hole of a collision plate (not shown), and performs impingement cooling (impingement cooling) on the outer region bottom surface 155a. By impingement cooling the outer region bottom surface 155a, overheating of the gas path surface 27a due to combustion gas is suppressed. The cooling air that has impingement-cooled the outer region bottom surface 155a is supplied to a first circumferential passage 121, a second circumferential passage 122, a first side passage 131, and a second side passage 132, which will be described later.
The cooling air after impingement cooling the outer region bottom surface 155a is supplied to a plurality of through holes (not shown) formed along the axial direction in the first leading edge end 153A and the second leading edge end 153B. After the first leading edge end 153A and the second leading edge end 153B are cooled, they may be discharged from the leading edge side end 27c of the outer shroud 27 to the outside of the outer shroud.
Further, the cooling air after impingement cooling the outer region bottom surface 155a is supplied to a plurality of through holes (not shown) formed along the axial direction in the first trailing edge end 154A and the second trailing edge end 154B. After cooling the first trailing edge end portion 154A and the second trailing edge end portion 154B, the cooling fluid may be discharged from the trailing edge end portion 27d of the outer shroud 27 to the outside of the outer shroud.

In the first segment 101A according to one embodiment, the first opening 111 is formed in the surface of the first front edge end 153A facing the rear edge 23b, that is, the wall surface facing the space 157 inside the radial direction Dr. has been done.
In the first segment 101A according to one embodiment, a first circumferential passage 121 extending in the circumferential direction is formed in the first front edge end 153A.
In the first segment 101A according to one embodiment, a first side passage 131 extending in the axial direction is formed in the first side end 151A on the ventral wing surface 23c side.

In the first segment 101A according to one embodiment, the first circumferential passage 121 is a passage that communicates the first opening 111 and the first side passage 131.
In the first segment 101A according to one embodiment, the first side passage 131 is a passage formed in the first side end 151A on the ventral wing surface 23c side from the leading edge 23a side to the trailing edge 23b side. The end on the side is connected to the first circumferential passage 121, and the end on the downstream side opens to the end 27d on the trailing edge side of the first outer shroud 27A.
The first side passage 131 overlaps with the recess 181 when viewed from the axial direction.

In the first segment 101A according to one embodiment, the cooling air that has impingement-cooled the outer region bottom surface 155a flows into the first circumferential passage 121 in the first leading edge end 153A from the first opening 111 and flows into the first circumferential passage 121 in the first leading edge end 153A. By flowing through the circumferential passage 121, the first leading edge end 153A is cooled.
The cooling air that has passed through the first circumferential passage 121 passes through the first side passage 131 and cools the first side end 151A on the ventral wing surface 23c side and the periphery of the recess 181. It is discharged to the outside of the first outer shroud 27A from the rear edge side end 27d of the outer shroud 27A.

In the second segment 101B according to one embodiment, the second opening 112 is formed in the surface of the second front edge end 153B facing the rear edge 23b, that is, the wall surface facing the space 157 inside the radial direction Dr. has been done.
In the second segment 101B according to one embodiment, a second circumferential passage 122 extending in the circumferential direction is formed in the second front edge end 153B.
In the second segment 101B according to one embodiment, a second side passage 132 extending in the axial direction is formed at the second side end 151B on the side of the dorsal wing surface 23d.

In the second segment 101B according to one embodiment, the second circumferential passage 122 is a passage that communicates the second opening 112 and the second side passage 132.
In the second segment 101B according to one embodiment, the second side passage 132 is a passage formed in the second side end 151B on the dorsal wing surface 23d side from the leading edge 23a side to the trailing edge 23b side, and The end on the side is connected to the second circumferential passage 122, and the end on the downstream side opens to the end 27d on the trailing edge side of the second outer shroud 27B.
The second side passage 132 overlaps with the recess 181 when viewed from the axial direction.

In the second segment 101B according to one embodiment, the cooling air that has impingement-cooled the outer region bottom surface 155a flows into the second circumferential passage 122 in the second leading edge end 153B from the second opening 112 and flows into the second circumferential passage 122 in the second leading edge end 153B. By flowing through the two circumferential passages 122, the second leading edge end 153B is cooled.
The cooling air that has passed through the second circumferential passage 122 passes through the second side passage 132 and cools the second side end 151B on the dorsal wing surface 23d side and the periphery of the recess 181. It is discharged to the outside of the second outer shroud 27B from the rear edge side end 27d of the outer shroud 27B.

In this way, in the blade segment 100 according to one embodiment, the vicinity of the recess 181 can be cooled by the cooling air CA flowing through the first side passage 131 and the cooling air CA flowing through the second side passage 132. .
Since the recess 181 is configured to engage with the positioning pin 191 as described above, it is difficult to perform impingement cooling on the recess 181, for example. Therefore, the metal temperature near the recess 181 tends to be relatively high.
According to the wing segment 100 according to one embodiment, the cooling air is circulated through the first side passage 131 and the second side passage 132 by circulating the cooling air through the first side passage 131 and the second side passage 132. The vicinity of the recess 181 is formed by the cooling air CA. This makes it possible to effectively cool areas where the metal temperature tends to be relatively high.

Note that the blade segment 100 according to one embodiment is configured so that the vicinity of the recess 181 can be formed by the cooling air CA flowing through at least one of the first side passage 131 and the second side passage 132. It's okay. That is, only either the first side passage 131 or the second side passage 132 may overlap with the recess 181 when viewed from the axial direction.

In the wing segment 100 according to one embodiment, the first side end portion 151A on the dorsal wing surface 23d side of the first outer shroud 27A is the ventral wing surface of the second outer shroud 27B in another wing segment 100 adjacent in the circumferential direction. It faces the second side end 151B on the side 23c with a gap for absorbing thermal expansion in the circumferential direction. Therefore, cooling can be expected by a small amount of cooling air leaking from the gap.
Similarly, the second side end 151B on the ventral wing surface 23c side of the second outer shroud 27B is the first side end on the dorsal wing surface 23d side of the first outer shroud 27A in another circumferentially adjacent blade segment 100. It faces the portion 151A with a gap for absorbing thermal expansion in the circumferential direction. Therefore, cooling can be expected by a small amount of cooling air leaking from the gap.

In the wing segment 100 according to one embodiment, the first outer shroud 27A has a first side end 151A on the ventral wing surface 23c side that faces the second outer shroud 27B among the two first side ends 151A. The first side passage 131 may not be included in the first side end 151A on the side of the dorsal wing surface 23d located on the opposite side.
Similarly, the second outer shroud 27B has a ventral wing located on the side opposite to the second side end 151B on the side of the dorsal wing surface 23d that faces the first outer shroud 27A. The second side passage 132 may not be included in the second side end 151B on the surface 23c side.
As a result, in the first side end 151A on the dorsal wing surface 23d side of the first outer shroud 27A and the second side end 151B on the ventral wing surface 23c side of the second outer shroud 27B, which are relatively less necessary. Since the processing for providing the first side passage 131 and the second side passage 132 can be omitted, the manufacturing cost of the blade segment 100 can be suppressed.

In the wing segment 100 according to one embodiment, a first opening 111 , a second opening 112 , a first circumferential passage 121 , a second circumferential passage 122 , a first side passage 131 , and a second side passage 132 It is good to include.
According to the blade segment 100 according to one embodiment, the cooling air that has flowed in from the first opening 111 can be made to flow through the first circumferential passage 121 to the first side passage 131 . Moreover, by circulating the fluid flowing in from the first opening 111 into the first circumferential passage 121, the first leading edge end 153A, which tends to have a relatively high metal temperature, can be efficiently cooled.
Similarly, according to the embodiment of the wing segment 100 , fluid flowing from the second opening 112 can be caused to flow through the second circumferential passage 122 to the second side passage 132 . Moreover, by circulating the fluid flowing in from the second opening 112 through the second circumferential passage 122, the second leading edge end 153B, where the metal temperature tends to be relatively high, can be efficiently cooled.

In the wing segment 100 according to one embodiment, the position of the first opening 111 with respect to the first airfoil 23A may be the same as the position of the second opening 112 with respect to the second airfoil 23B.
For example, when manufacturing the first segment 101A and the second segment 101B by casting, when the first segment 101A and the second segment 101B are obtained from castings of the same shape, the first opening 111 and the second opening 112 Corresponding openings can also be formed during the casting step. Thereby, the number of processing steps after casting can be reduced, and the manufacturing cost of the blade segment 100 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) The blade segment 100 according to at least one embodiment of the present disclosure includes one first airfoil portion 23A and a first outer shroud 27A provided outside the one first airfoil portion 23A in the blade height direction. and a first inner shroud 25A provided inside one first airfoil portion 23A in the blade height direction. The blade segment 100 according to at least one embodiment of the present disclosure includes one second airfoil portion 23B, a second outer shroud 27B provided on the outside of the one second airfoil portion 23B in the blade height direction, and one second airfoil portion 23B. and a second inner shroud 25B provided on the inner side in the blade height direction of the second airfoil portions 23B. The first outer shroud 27A and the second outer shroud 27B are bolted together. The first inner shroud 25A and the second inner shroud 25B are bolted together. The wing segment 100 according to at least one embodiment of the present disclosure has a recess 181 formed across the first outer shroud 27A and the second outer shroud 27B.

According to the configuration (1) above, it is possible to eliminate gaps between the outer shrouds 27 of the first segment 101A and the second segment 101B and between the inner shrouds 25, and the fluid (cooling air CA) from the gaps can be eliminated. ), it is possible to suppress a decrease in efficiency in a rotating machine (gas turbine 10) including the blade segment 100.
Further, according to the configuration (1) above, the blade segment 100 in which the first segment 101A and the second segment 101B are bolted together is attached to the casing (turbine casing 30) of the rotating machine (gas turbine 10), and the casing By engaging the positioning pin 191 attached to the turbine casing 30 with the recess 181, movement of the blade segment 100 in the circumferential direction can be restricted. Furthermore, even if the blade segment 100 is thermally expanded in the circumferential direction, the first segment 101A on one side in the circumferential direction is mainly thermally expanded from the recess 181 to one side, centering on the recess 181 that the positioning pin 191 engages, and the positioning The second segment 101B on the other side in the circumferential direction about the recess 181 with which the pin 191 engages mainly expands thermally from the recess 181 to the other side. Therefore, when the blade segment 100 is cold, the gap between the positioning pin 191 and the recess 181 can be made relatively small. This makes it relatively easy to assemble other members such as a seal ring adjacent to the blade segment 100, and the rotating machine (gas turbine 10) including the blade segment 100 can be easily assembled.

(2) In some embodiments, in the configuration of (1) above, the first outer shroud 27A is arranged on the first side of the two first side ends 151A in the circumferential direction, which is opposite to the second outer shroud 27B. It is preferable to include a first side passage 131 formed from the leading edge 23a side to the trailing edge 23b side at the end portion 151A (first side end portion 151A on the ventral wing surface 23c side). Of the two second side ends 151B in the circumferential direction, the second outer shroud 27B has a second side end 151B (second side end 151B on the dorsal wing surface 23d side) that faces the first outer shroud 27A. It is preferable to include a second side passage 132 formed from the front edge 23a side to the rear edge 23b side. At least one of the first side passage 131 and the second side passage 132 preferably overlaps with the recess 181 when viewed from the blade height direction.

According to the configuration (2) above, by circulating the fluid (cooling air CA) through the first side passage 131 and the second side passage 132, the first side passage 131 or the second side passage The vicinity of the recess 181 is formed by the fluid (cooling air CA) flowing through at least one of the recesses 132 . This makes it possible to effectively cool areas where the metal temperature tends to be relatively high.

(3) In some embodiments, in the configuration of (2) above, the first side passage 131 and the second side passage 132 may overlap with the recess 181 when viewed from the blade height direction. .

According to the configuration (3) above, the region where the metal temperature tends to be relatively high can be further effectively cooled.

(4) In some embodiments, in the configuration of (2) or (3) above, the first outer shroud 27A has the first outer shroud 27A facing the second outer shroud 27B of the two first side ends 151A. At the first side end 151A (first side end 151A on the dorsal wing surface 23d side) located on the opposite side to the side end 151A (first side end 151A on the ventral wing surface 23c side), the first side The partial passage 131 may not be included. Of the two second side ends 151B, the second outer shroud 27B is located on the opposite side from the second side end 151B (the second side end 151B on the dorsal wing surface 23d side) that faces the first outer shroud 27A. The second side passage 132 may not be included in the second side end 151B (the second side end 151B on the side of the ventral wing surface 23c).

According to the configuration (4) above, processing for providing the first side passage 131 and the second side passage 132 can be omitted in areas where the necessity is relatively low, so the manufacturing cost of the blade segment 100 can be suppressed. .

(5) In some embodiments, in any of the configurations (2) to (4) above, the first outer shroud 27A has a blade height that is different from the first airfoil portion 23A at the end on the leading edge 23a side. It is preferable to include a first front edge end 153A protruding from the first outer shroud 27A toward the opposite side in the longitudinal direction. The first outer shroud 27A preferably has a first opening 111 formed in a surface of the first leading end 153A facing the rear edge 23b. The first outer shroud 27A may include a first circumferential passage 121 formed at the first leading end 153A and communicating the first opening 111 and the first side passage 131. The second outer shroud 27B includes a second leading edge end 153B that protrudes from the second outer shroud 27B toward the opposite side in the blade height direction from the second airfoil portion 23B at the end on the leading edge 23a side. Good. The second outer shroud 27B preferably has a second opening 112 formed in a surface of the second leading end 153B facing the rear edge 23b. The second outer shroud 27B may include a second circumferential passage 122 formed at the second leading end 153B and communicating between the second opening 112 and the second side passage 132.

According to the configuration (5) above, the fluid (cooling air CA) flowing in from the first opening 111 can be made to flow to the first side passage 131 via the first circumferential passage 121. Furthermore, by circulating the fluid (cooling air CA) flowing in from the first opening 111 through the first circumferential passage 121, the first leading edge end 153A, where the metal temperature tends to be relatively high, can be efficiently heated. Can be cooled.
Further, according to the configuration (5) above, the fluid (cooling air CA) flowing in from the second opening 112 can be caused to flow to the second side passage 132 via the second circumferential passage 122. Furthermore, by circulating the fluid (cooling air CA) flowing in from the second opening 112 through the second circumferential passage 122, the second leading edge end 153B, where the metal temperature tends to be relatively high, can be efficiently heated. Can be cooled.

(6) In some embodiments, in the configuration (5) above, the position of the first opening 111 with respect to the first airfoil 23A is the same as the position of the second opening 112 with respect to the second airfoil 23B. It would be good if it were.

According to configuration (6) above, for example, when the first segment 101A and the second segment 101B are manufactured by casting, when the first segment 101A and the second segment 101B are obtained from a cast product of the same shape, the first segment 101A and the second segment 101B are manufactured by casting. Openings corresponding to the opening 111 and the second opening 112 can also be formed during the casting step. Thereby, the number of processing steps after casting can be reduced, and the manufacturing cost of the blade segment 100 can be suppressed.

(7) A rotating machine (gas turbine 10) according to at least one embodiment of the present disclosure includes a blade segment 100 having the configuration of any one of (1) to (6) above, and a casing (turbine casing) that covers the blade segment 100. 30), and a positioning pin 191 that is attached to the casing (turbine casing 30) and whose tip engages with the recess 181.

According to the configuration (7) above, it is possible to eliminate gaps between the outer shrouds 27 of the first segment 101A and the second segment 101B and between the inner shrouds 25, and the fluid (cooling air CA) from the gaps can be eliminated. ) leakage can be suppressed, so a decrease in efficiency of the rotating machine (gas turbine 10) can be suppressed.
Further, according to the configuration (7) above, it is relatively easy to assemble other members such as a seal ring adjacent to the blade segment 100, and the rotating machine (gas turbine 10) can be easily assembled.

10 Gas turbine 13 Turbine 23, 23A, 23B Airfoil section 25, 25A, 25B Inner shroud 27, 27A, 27B Outer shroud 30 Casing (turbine casing, casing)
23a Leading edge 23b Trailing edge 23c Ventral wing surface 23d Dorsal wing surface 23A First airfoil section 23B Second airfoil section 25 Inner shroud 25A First inner shroud 25B Second inner shroud 27 Outer shroud 27A First outer shroud 27B Second Outer shroud 100 Wing segment 101 Segment 101A First segment 101B Second segment 111 First opening 112 Second opening 131 First side passage 132 Second side passage 181 Recess 191 Locating pin

Claims (7)

one first airfoil, a first outer shroud provided on the outer side of the one first airfoil in the blade height direction, and the first outer shroud provided on the inner side of the one first airfoil in the blade height direction. a first segment comprising a first inner shroud provided;
one second airfoil, a second outer shroud provided on the outer side of the one second airfoil in the blade height direction, and the second outer shroud provided on the inner side of the one second airfoil in the blade height direction. a second segment including a second inner shroud provided;
Equipped with
the first outer shroud and the second outer shroud are bolted together;
the first inner shroud and the second inner shroud are bolted together;
a recess formed across the first outer shroud and the second outer shroud;
wing segment. The first outer shroud has a first side passage formed from a leading edge side to a trailing edge side at the first side end facing the second outer shroud among the two first side ends in the circumferential direction. including,
The second outer shroud has a second side formed from the leading edge side to the trailing edge side at the second side edge facing the first outer shroud among the two second side edges in the circumferential direction. Including departmental aisles,
At least one of the first side passage and the second side passage overlaps the recess when viewed from the blade height direction.
A wing segment according to claim 1. The first side passage and the second side passage overlap the recess when viewed from the blade height direction.
A wing segment according to claim 2. The first outer shroud is arranged such that, of the two first side end portions, the first side end portion is located on the opposite side from the first side end portion facing the second outer shroud. Does not include side passages,
The second outer shroud is arranged such that the second outer shroud has the second outer shroud at the second outer shroud, which is located on the opposite side of the second outer shroud and which faces the first outer shroud. not including side passages,
A wing segment according to claim 2 or 3. The first outer shroud includes:
At the end on the leading edge side, the first airfoil includes a first leading edge end protruding from the first outer shroud toward the opposite side in the blade height direction;
a first opening formed in a surface of the first front edge end facing the rear edge side;
a first circumferential passage formed at the first front edge end and communicating the first opening and the first side passage;
The second outer shroud is
The second airfoil portion includes a second leading edge end portion protruding from the second outer shroud toward the opposite side in the blade height direction at the leading edge side end portion;
a second opening formed in a surface of the second front edge end facing the rear edge side;
a second circumferential passage formed in the second front edge end and communicating the second opening and the second side passage;
A wing segment according to any one of claims 2 to 4. the position of the first opening relative to the first airfoil is the same as the position of the second opening relative to the second airfoil;
A wing segment according to claim 5. A wing segment according to any one of claims 1 to 6,
a casing covering the wing segment;
a positioning pin attached to the casing and whose tip engages with the recess;
Equipped with
rotating machine.

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