Blade segment body and rotary machine

Abstract

The present invention aims to make the assembly of a rotary machine easier while suppressing a decrease in the efficiency of the rotary machine. A blade segment body of at least one embodiment of the present disclosure includes a first segment body including one first airfoil, a first outer shroud provided on an outer side in a blade height direction of the one first airfoil, and a first inner shroud provided on an inner side in the blade height direction of the one first airfoil, and a second segment body including one second airfoil, a second outer shroud provided on an outer side in a blade height direction of the one second airfoil, and a second inner shroud provided on an inner side in the blade height direction of the one second airfoil. The first outer shroud and the second outer shroud are bolted, the first inner shroud and the second inner shroud are bolted, and the blade segment body has a recess formed across the first outer shroud and the second outer shroud.

Description

Technical Field

[0001] This disclosure relates to blade sections and rotating machinery. Background Technology

[0002] In a gas turbine, which is an example of rotating machinery, turbine stator blades with a connected blade structure having two airfoils arranged relative to an outer shroud and an inner shroud are known (see, for example, Patent Document 1).

[0003] Prior art literature

[0004] Patent documents

[0005] Patent Document 1: Japanese Patent Application Publication No. 2015-090108

[0006] However, in turbine stator blades with a connected blade structure, such as the turbine stator blade described in Patent Document 1, since the two airfoils are arranged close together, when applying a heat-insulating coating to the airfoils, for example by spraying, one airfoil's blade surface is obscured by the shadow of the other airfoil on the blade surfaces facing each other. Therefore, there is a problem that it is difficult to apply a heat-insulating coating to the blade surfaces where the two airfoils face each other.

[0007] Therefore, the aforementioned problem can be solved by configuring an airfoil relative to both an outer shroud and an inner shroud. However, since the number of circumferential divisions of the outer and inner shrouds increases, the flow rate of cooling air into the combustion gas flow path from the gaps between circumferentially adjacent outer shrouds and inner shrouds may increase. If the flow rate of cooling air into the combustion gas flow path increases, it will negatively impact the efficiency of the gas turbine.

[0008] In order to suppress the flow of cooling air into the combustion gas path, if two sections with an airfoil disposed opposite an outer shroud and an inner shroud are connected by means of, for example, bolts, the gaps between the outer shrouds and the inner shrouds of the two sections can be eliminated.

[0009] However, since the turbine stator changes the direction of combustion gas flow, it is subjected to a force from the combustion gas that causes the turbine stator to rotate circumferentially. Therefore, in order to prevent the turbine stator from rotating circumferentially within the housing and for positioning the turbine stator, a locating pin mounted on the housing is configured to engage with the turbine stator.

[0010] Because the turbine stator blades expand thermally in the circumferential direction, this thermal expansion needs to be taken into account, and a gap between the stator blade and the stator pin needs to be set at the part that engages with the stator pin.

[0011] For example, in the case where a blade segment is formed by bolting two segments together as described above, if, for example, the two circumferentially adjacent blade segments are engaged with a locating pin, a gap must be provided between the locating bolt to absorb the thermal expansion of the blade segment over its entire circumferential length, and the size of this gap becomes relatively large.

[0012] If the size of the gap becomes relatively large, the blade section body becomes able to move the gap by a certain amount in the circumferential direction during turbine assembly. Therefore, it may affect the assembly of other components, such as the sealing ring adjacent to the blade section body, as it becomes more difficult. Summary of the Invention

[0013] At least one embodiment of this disclosure was made in view of the above circumstances, and its purpose is to facilitate the assembly of rotating machinery while suppressing the reduction in efficiency of rotating machinery.

[0014] (1) The blade segment body of at least one embodiment of the present disclosure comprises:

[0015] The first segment body includes a first airfoil, a first outer protective cover disposed on the outer side of the first airfoil in the blade height direction, and a first inner protective cover disposed on the inner side of the first airfoil in the blade height direction; and

[0016] The second section body includes a second airfoil, a second outer protective cover disposed on the outer side of the second airfoil in the blade height direction, and a second inner protective cover disposed on the inner side of the second airfoil in the blade height direction.

[0017] The first outer protective cover is bolted to the second outer protective cover.

[0018] The first inner shield is bolted to the second inner shield.

[0019] The blade segment has a recess formed across the first outer shield and the second outer shield.

[0020] (2) The rotating machinery of at least one embodiment of the present disclosure includes:

[0021] The blade segment body of the structure described in (1) above;

[0022] A housing that covers the blade segment body; and

[0023] A locating pin is installed in the housing, and its front end engages with the recess.

[0024] Invention Effects

[0025] According to at least one embodiment of this disclosure, the assembly of rotating machinery can be facilitated while suppressing the reduction in efficiency of rotating machinery. Attached Figure Description

[0026] Figure 1 This is a schematic diagram showing the overall structure of a gas turbine, an example of rotating machinery.

[0027] Figure 2 This is a cross-sectional view showing the gas flow path of the turbine.

[0028] Figure 3 This is a diagram showing a turbine stator blade of one embodiment viewed from the radially outer side.

[0029] Figure 4 yes Figure 3 IV-IV view.

[0030] Explanation of reference numerals in the attached figures:

[0031] 10... Gas turbine;

[0032] 13... Turbine;

[0033] 23, 23A, 23B... airfoil sections;

[0034] 25, 25A, 25B... Inner protective cover;

[0035] 27, 27A, 27B... outer protective cover;

[0036] 30... Engine room (turbine engine room, casing);

[0037] 23a...front edge;

[0038] 23b... trailing edge;

[0039] 23c...ventral blade surface;

[0040] 23d...dorsal blade surface;

[0041] 23A...First airfoil;

[0042] 23B...Second wing section;

[0043] 25...Inner protective cover;

[0044] 25A...First inner protective cover;

[0045] 25B...Second inner shroud;

[0046] 27...Outer protective cover;

[0047] 27A...First outer protective shield;

[0048] 27B...Second outer protective shield;

[0049] 100...blade segment body;

[0050] 101...section body;

[0051] 101A...First Segment Body;

[0052] 101B...Second segment body;

[0053] 111...First opening;

[0054] 112...Second opening;

[0055] 131...First lateral passage;

[0056] 132...Second lateral passage;

[0057] 181...concave;

[0058] 191...locating pin. Detailed Implementation

[0059] Hereinafter, several embodiments of the present disclosure will be described with reference to the accompanying drawings. The dimensions, materials, shapes, and relative arrangements of the constituent components described in the embodiments or shown in the drawings are not intended to limit the scope of the present disclosure, but are merely illustrative examples.

[0060] For example, expressions such as "in a certain direction," "along a certain direction," "parallel," "orthogonal," "center," "concentric," or "coaxial" indicate a relative or absolute configuration, which not only strictly indicate such a configuration, but also indicate a state in which the relative displacement is within tolerance and to the extent that the same function can be obtained.

[0061] For example, expressions such as "same," "equal," and "homogeneous" that indicate the state of equality of things not only indicate a state of strict equality, but also indicate a state of difference where there is a tolerance or a degree of difference in the ability to obtain the same function.

[0062] For example, in this specification, the terms "quadrilateral shape," "cylindrical shape," etc., which describe shapes, not only refer to shapes in a strict geometric sense, but also include shapes such as concave and convex parts and chamfered parts within the range that can achieve the same effect.

[0063] On the other hand, expressions such as “having,” “possessing,” “having,” “including,” or “having” a constituent element are not exclusive expressions that exclude the existence of other constituent elements.

[0064] Figure 1 This is a schematic diagram showing the overall structure of a gas turbine, an example of rotating machinery. Figure 2 This is a cross-sectional view showing the gas flow path of the turbine.

[0065] In this embodiment, such as Figure 1 As shown, the gas turbine 10 is constructed by coaxially arranging the compressor 11, burner 12, and turbine 13 on a rotor 14, and a generator 15 is connected to one end of the rotor 14. It should be noted that in the following description, the direction in which the axis of the rotor 14 extends is defined as the axial direction Da, the circumferential direction centered on the axis of the rotor 14 is defined as the circumferential direction Dc, and the direction perpendicular to the axis Ax of the rotor 14 is defined as the radial direction Dr. It should be noted that the radial direction Dr is referred to as the blade height direction.

[0066] In compressor 11, air AT drawn in from the air inlet is compressed by passing through multiple stationary and moving vanes, thereby generating high-temperature, high-pressure compressed air AC. Combustor 12 supplies a specified amount of fuel FL to the compressed air AC and combusts it, thereby generating high-temperature, high-pressure combustion gas FG. Turbine 13 drives rotor 14 to rotate by passing the high-temperature, high-pressure combustion gas FG generated in combustor 12 through multiple stationary and moving vanes, thereby driving generator 15 connected to rotor 14.

[0067] In addition, such as Figure 2 As shown, in the turbine 13, the turbine stator blade 21 is configured such that the hub side of the airfoil 23 is fixed to the inner shroud 25 and the front end side is fixed to the outer shroud 27. The turbine rotor blade 41 is configured such that the base end of the airfoil 43 is fixed to the platform 45. Furthermore, the outer shroud 27 and the dividing ring 51 disposed on the front end side of the rotor blade 41 are supported in the turbine housing 30 via a heat insulation ring 53, and the inner shroud 25 is supported by a support ring 31. Therefore, the combustion gas flow path 32 through which the combustion gas FG passes is formed along the axial direction Da as a space surrounded by the inner shroud 25, the outer shroud 27, the platform 45, and the dividing ring 51.

[0068] Figure 3 This is a diagram showing the turbine stator 21 of one embodiment viewed from the radial outside of Dr.

[0069] Figure 4 yes Figure 3 IV-IV view.

[0070] In one embodiment, the turbine stator 21 is configured as a blade section 100, which is formed by connecting two sections 101, each having an airfoil 23 disposed relative to an outer shroud 27 and an inner shroud 25, by bolting.

[0071] Details of the blade segment 100 in one embodiment will be described in detail later.

[0072] It should be noted that, as Figure 3 As shown, the airfoil 23 is formed by a ventral blade surface 23c, which is a concave surface as a pressure surface, and a dorsal blade surface 23d, which is a convex surface as a negative pressure surface. The ventral blade surface 23c and the dorsal blade surface 23d are connected by the leading edge 23a on the upstream side and the trailing edge 23b on the downstream side in the axial direction, forming an integrated airfoil 23.

[0073] It should be noted that the inner shield 25 and the outer shield 27 function as gas passage surface forming members. A gas passage surface forming member refers to a member that divides the combustion gas flow path 32 and has a gas passage surface in contact with the combustion gas FG. When there is no need to specifically distinguish between the inner shield 25 and the outer shield 27, they are sometimes simply referred to as shield 2.

[0074] (Regarding blade segment 100)

[0075] One embodiment of the blade segment body 100 includes two bolt-connected segment bodies 101 as described above. In the following description, for ease of explanation, the segment body 101 arranged with its ventral blade surface 23c facing the dorsal blade surface 23d of the target-side segment body 101 will be designated as the first segment body 101A, and the segment body 101 arranged with its dorsal blade surface 23d facing the ventral blade surface 23c of the target-side segment body 101 will be designated as the second segment body 101B. Figure 3 In the diagram, the segment 101 on the left is the first segment 101A, and the segment on the right is the second segment 101B.

[0076] The first section body 101A includes a first airfoil 23A, a first outer shield 27A disposed on the outer side of the first airfoil 23A in the blade height direction, and an inner shield 25 (first inner shield) disposed on the inner side of the first airfoil 23A in the blade height direction.

[0077] Similarly, the second section body 101B includes a second airfoil 23B, a second outer shroud 27B disposed on the outer side of the second airfoil 23B in the blade height direction, and a second inner shroud 25B disposed on the inner side of the second airfoil 23B in the blade height direction.

[0078] In the first section 101A of the blade section body 100 in one embodiment, the first outer shroud 27A has an outer region 155 on the side opposite to the gas passage surface 27a, i.e., radially outside Dr., capable of storing cooling air supplied from the outside. The outer region 155 of the first section body 101A is a region surrounded by the peripheral portion of the first outer shroud 27A, i.e., the first side end 151A on the ventral blade surface 23c side and the first side end 151A on the dorsal blade surface 23d side of the two circumferential ends of the first outer shroud 27A, the first leading edge end 153A on the axial leading edge 23a side, and the first trailing edge end 154A on the trailing edge 23b side, and has a space portion 157 recessed in the radially inward direction of Dr. The bottom surface 155a of the outer region forming the bottom surface of the outer region 155 forms the radially outer side of the gas passage surface 27a. That is, the space portion 157 of the first section body 101A is a space formed by the bottom surface 155a of the outer region, the outer wall portion extending from the bottom surface 155a of the outer region along the blade height direction (radial), namely the first side end portion 151A and the first leading edge end portion 153A, and the first trailing edge end portion 154A.

[0079] In one embodiment of the gas turbine 10, cooling air CA is supplied from the outside to the space portion 157 of the first section body 101A.

[0080] In the first section 101A of the blade section body 100 in one embodiment, the inner shield 25 (first inner shield) has a first side end on the ventral blade surface 23c side that forms the circumferential end of the inner shield 25 (first inner shield).

[0081] Similarly, in the second section 101B of the blade section body 100 in one embodiment, the second outer shield 27B has an outer region 155 on the side opposite to the gas passage surface 27a, i.e., radially outside Dr., capable of storing cooling air supplied from the outside. The outer region 155 of the second section body 101B is a region surrounded by the peripheral portion of the second outer shield 27B, i.e., the second side end 151B on the ventral blade surface 23c side and the second side end 151B on the dorsal blade surface 23d side of the two circumferential ends of the second outer shield 27B, the second leading edge end 153B on the axial leading edge 23a side, and the second trailing edge end 154B on the trailing edge 23b side, and has a space portion 157 recessed in the radially inward direction of Dr. The bottom surface 155a of the outer region forming the bottom surface of the outer region 155 forms the radially outer side of the gas passage surface 27a. That is, the space portion 157 of the second section body 101B is a space formed by the bottom surface 155a of the outer region, the outer wall portion extending from the bottom surface 155a of the outer region along the blade height direction (radial), namely the second side end portion 151B and the second leading edge end portion 153B, and the second trailing edge end portion 154B.

[0082] In one embodiment of the gas turbine 10, cooling air CA is supplied from the outside to the space portion 157 of the second section body 101B.

[0083] In the second section body 101B of the blade section body 100 in one embodiment, the second inner shield 25B has a second side end 158B on the back side blade surface 23d side that forms the circumferential end of the second inner shield 25B.

[0084] (Regarding the bolted connection between the first section body 101A and the second section body 101B)

[0085] In the first section 101A of the blade section body 100 in one embodiment, a first side end 151A is formed that extends circumferentially through the ventral blade surface 23c side of the first outer shield 27A and the first side end 161 through the ventral blade surface 23c side of the inner shield 25 (first inner shield).

[0086] In one embodiment of the blade section body 100, a plurality of bolt holes 161 may be formed axially spaced at the first side end 151A of the first outer protective cover 27A. Figure 3 In the example shown, there are two bolt holes 161, but there could also be one, or even more than three.

[0087] Although not shown in the figure, a bolt hole 161 is formed at the first side end of the inner cover 25 (first inner cover), but multiple bolt holes 161 may also be formed at intervals along the axial direction.

[0088] In the second section 101B of the blade section body 100 in one embodiment, bolt holes 162 are formed that extend circumferentially through the second side end 151B on the back side blade surface 23d side of the second outer shield 27B and the second side end 157B on the back side blade surface 23d side of the second inner shield 25B.

[0089] In the second section 101b of the blade section body 100 in one embodiment, a plurality of bolt holes 162 may be formed axially spaced at the second side end 151B of the second outer protective cover 27B. Figure 3 as well as Figure 4 In the example shown, there are two bolt holes 162, but there could also be one or more.

[0090] exist Figure 4 In the example shown, a bolt hole 162 is formed at the second side end 157B of the second inner cover 25B, but multiple bolt holes 162 may also be formed at axial intervals.

[0091] The positions of the bolt holes 161 in the first section body 101A and the bolt holes 162 in the second section body 101B are respectively set so that the bolt 171 can pass through the bolt holes 161 and 162.

[0092] In one embodiment of the blade section body 100, the first section body 101A and the second section body 101B are bolted together by passing a bolt 171 through bolt holes 161 and 162 and installing a nut 172.

[0093] It should be noted that in the turbine 13 of the gas turbine 10 according to one embodiment, multiple blade section bodies 100 are arranged in the circumferential direction. Adjacent blade section bodies 100 in the circumferential direction are not bolted together. A sealing plate (not shown) is arranged between adjacent blade section bodies 100 in the circumferential direction to prevent cooling air CA from leaking between adjacent blade section bodies 100 in the circumferential direction.

[0094] (Regarding the concave part)

[0095] One embodiment of the blade section body 100 has a recess 181 formed across the first outer outer shield 27A and the second outer outer shield 27B.

[0096] Specifically, the recess 181 is formed in the region axially downstream of the first side end 151A on the ventral blade surface 23c side of the first segment body 101A and the second side end 151B on the dorsal blade surface 23d side of the second segment body 101B, spanning the first side end 151A and the second side end 151B and recessed toward the radially inward side.

[0097] The recess 181 is configured to engage with a positioning pin 191 within the housing of the blade section body 100, i.e., the turbine housing 30, in one embodiment, whereby the positioning pin 191 is used to restrict the circumferential movement of the blade section body 100.

[0098] That is, in the blade section body 100 of one embodiment, a recess 181 is formed by the first outer outer shield 27A and the second outer outer shield 27B clamping the positioning pin 191 in the circumferential direction.

[0099] The blade section 100 changes the flow direction of the combustion gas FG, and therefore receives a force from the combustion gas FG that is intended to cause the blade section 100 to rotate circumferentially. Therefore, in order to prevent the blade section 100 from rotating circumferentially within the turbine housing 30 and to position the blade section 100, the positioning pin 191 mounted in the turbine housing 30 is configured to engage with the recess 181.

[0100] In one embodiment of the blade section body 100, the gaps between the outer shrouds 27 of the first section body 101A and the inner shrouds 25 of the second section body 101B and between each other can be eliminated, and the leakage of cooling air CA from the gaps can be suppressed. Therefore, in the gas turbine 10 equipped with one embodiment of the blade section body 100, the reduction in efficiency can be suppressed.

[0101] Furthermore, in one embodiment of the blade section body 100, the blade section body 100, which bolts together the first section body 101A and the second section body 101B, is mounted to the turbine housing 30 of the gas turbine 10, and the locating pin 191 mounted in the turbine housing 30 engages with the recess 181, thereby restricting the circumferential movement of the blade section body 100. Additionally, even if the blade section body 100 undergoes circumferential thermal elongation, the first section body 101A on one side of the circumference centered on the recess 181 engaged by the locating pin 191 primarily elongates from the recess 181 to one side, while the second section body 101B on the other side of the circumference centered on the recess 181 engaged by the locating pin 191 primarily elongates from the recess 181 to the other side. Therefore, when the blade section body 100 is cooled, the gap between the locating pin 191 and the recess 181 can be relatively small. As a result, the assembly of other components such as the sealing ring adjacent to the blade section body 100 becomes easier, thus facilitating the assembly of the gas turbine 10 equipped with the blade section body 100.

[0102] One embodiment of the gas turbine 10 includes a blade section body 100, a turbine housing 30 covering the blade section body 100, and a positioning pin 191 installed in the turbine housing 30 and whose front end engages with a recess 181.

[0103] This eliminates the gaps between the outer shields 27 of the first section body 101A and the inner shields 25 of the second section body 102A, suppresses the leakage of cooling air CA from these gaps, and thus suppresses the reduction in efficiency of the gas turbine 10.

[0104] In addition, according to one embodiment of the gas turbine 10, the assembly of other components such as the sealing ring adjacent to the blade section body 100 becomes easier, thus simplifying the assembly of the gas turbine 10.

[0105] (Regarding the cooling structure of the outer shield 27)

[0106] The cooling structure of the outer shield 27 will be explained below.

[0107] An impact plate (not shown) with multiple through holes is disposed on the outer regions 155 of the first segment body 101A and the second segment body 101B in such a manner that it covers the entire bottom surface 155a of the outer regions. It should be noted that the impact plate (not shown) covers... Figure 3 The area in the middle that has been shaded.

[0108] The outer region 155 of the space 157 is divided by an impact plate (not shown) into a space 157 on the outer radial side (Dr) and a space 157 on the inner radial side (Dr). The space 157 on the outer radial side (Dr) and the space 157 on the inner radial side (Dr) are connected by a through hole in the impact plate (not shown).

[0109] Cooling air supplied to the space 157 is supplied to the space 157 radially inward via a through hole in an impact plate (not shown), performing impact cooling (collision cooling) on ​​the bottom surface 155a of the outer region. By performing impact cooling on the bottom surface 155a of the outer region, overheating of the gas passage surface 27a due to combustion gases is prevented. The cooling air after impact cooling of the bottom surface 155a of the outer region is supplied to the first circumferential passage 121, the second circumferential passage 122, the first side passage 131, and the second side passage 132, which will be described later.

[0110] The cooling air after impact cooling of the bottom surface 155a of the outer region can also be supplied to a plurality of through holes (not shown) formed along the axial direction of the first leading edge end 153A and the second leading edge end 153B to cool the first leading edge end 153A and the second leading edge end 153B, and then discharged from the end 27c on the leading edge side of the outer shield 27 to the outside of the outer shield.

[0111] In addition, the cooling air after impact cooling of the bottom surface 155a of the outer region can also be supplied to a plurality of through holes (not shown) formed along the axial direction at the first trailing edge end 154A and the second trailing edge end 154B to cool the first trailing edge end 154A and the second trailing edge end 154B, and then discharged from the end 27d on the trailing edge side of the outer shield 27 to the outside of the outer shield.

[0112] In one embodiment of the first segment body 101A, a first opening 111 is formed on the surface of the first leading edge end 153A facing the rear edge 23b side, that is, on the wall surface of the space portion 157 facing the radially inner side of Dr.

[0113] In one embodiment, a first circumferential passage 121 extending in the circumferential direction is formed at the first leading edge end 153A.

[0114] In one embodiment, a first section body 101A is formed at a first side end 151A on the ventral blade surface 23c side, where a first side passage 131 extending axially is formed.

[0115] In a first section body 101A of one embodiment, the first circumferential passage 121 is a passage connecting the first opening 111 and the first side passage 131.

[0116] In one embodiment of the first segment body 101A, the first side passage 131 is a passage formed from the leading edge 23a side to the trailing edge 23b side at the first side end 151A on the ventral blade surface 23c side. The upstream end is connected to the first circumferential passage 121, and the downstream end opens at the end 27d on the trailing edge side of the first outer shield 27A.

[0117] The first side passage 131 overlaps with the recess 181 when viewed from the axial direction.

[0118] In one embodiment, in the first section body 101A, cooling air after impact cooling of the bottom surface 155a of the outer region flows into the first circumferential passage 121 in the first leading edge end 153A from the first opening 111 and flows in the first circumferential passage 121, thereby cooling the first leading edge end 153A.

[0119] Cooling air that has flowed through the first circumferential passage 121 flows through the first side passage 131 to cool the first side end 151A and the periphery of the recess 181 on the ventral blade surface 23c side, and then is discharged from the end 27d on the trailing edge side of the first outer shield 27A to the outside of the first outer shield 27A.

[0120] In the second section body 101B of one embodiment, a second opening 112 is formed on the wall surface of the space portion 157 facing the rear edge 23b side in the second leading edge end 153B, that is, facing the radially inner side of Dr.

[0121] In one embodiment, a second circumferential passage 122 extending in the circumferential direction is formed in the second leading edge end 153B.

[0122] In the second section body 101B of one embodiment, a second side passage 132 extending axially is formed at the second side end 151B on the back blade surface 23d side.

[0123] In the second section body 101B of one embodiment, the second circumferential passage 122 is a passage connecting the second opening 112 and the second side passage 132.

[0124] In the second section body 101B of one embodiment, the second side passage 132 is a passage formed from the leading edge 23a side to the trailing edge 23b side of the second side end 151B on the back blade surface 23d side. The upstream end is connected to the second circumferential passage 122, and the downstream end opens at the end 27d on the trailing edge side of the second outer shield 27B.

[0125] The second side passage 132 overlaps with the recess 181 when viewed from the axial direction.

[0126] In the second section body 101B of one embodiment, cooling air that has been subjected to impact cooling of the bottom surface 155a of the outer region flows into the second circumferential passage 122 in the second leading edge end 153B from the second opening 112 and circulates in the second circumferential passage 122, thereby cooling the second leading edge end 153B.

[0127] The cooling air that flows through the second circumferential passage 122 flows through the second side passage 132 to cool the second side end 151B and the periphery of the recess 181 on the back side blade surface 23d side, and then is discharged from the end 27d on the trailing edge side of the second outer shroud 27B to the outside of the second outer shroud 27B.

[0128] Thus, in the blade section body 100 of one embodiment, the area near the recess 181 can be cooled by the cooling air CA flowing in the first side passage 131 and the cooling air CA flowing in the second side passage 132.

[0129] The recess 181 is configured to engage with the locating pin 191 as described above, making it difficult, for example, to perform impact cooling on the recess 181. Therefore, the metal temperature near the recess 181 tends to become higher.

[0130] According to one embodiment of the blade section body 100, by allowing cooling air to flow through the first side passage 131 and the second side passage 132, the cooling air CA flowing through the first side passage 131 and the second side passage 132 can be utilized near the recess 181. This effectively cools areas where the metal temperature tends to become relatively high.

[0131] It should be noted that, in one embodiment of the blade section body 100, it may also be configured such that cooling air CA flowing in at least one of the first side passage 131 and the second side passage 132 is near the recess 181. That is, it is also possible that only one of the first side passage 131 and the second side passage 132 overlaps with the recess 181 when viewed from the axial direction.

[0132] In one embodiment of the blade section body 100, the first side end 151A of the back blade surface 23d side of the first outer shroud 27A is opposed to the second side end 151B of the ventral blade surface 23c side of the second outer shroud 27B of the adjacent blade section body 100 in the circumferential direction, separated by a gap for absorbing circumferential thermal expansion. Therefore, it is expected that cooling can be achieved by utilizing cooling air that leaks slightly from this gap.

[0133] Similarly, the second side end 151B of the ventral blade surface 23c side of the second outer shroud 27B is opposed to the first side end 151A of the dorsal blade surface 23d side of the first outer shroud 27A in the other circumferentially adjacent blade segment body 100, separated by a gap for absorbing circumferential thermal expansion. Therefore, cooling can be expected using cooling air that leaks slightly from this gap.

[0134] In one embodiment of the blade section body 100, the first outer shield 27A may also exclude the first side passage 131 at the first side end 151A on the side opposite to the first side end 151A on the side opposite to the ventral blade surface 23c side of the second outer shield 27B, on the side opposite to the first side end 151A on the side opposite to the second outer shield 27B on the side opposite to the first side end 151A ...

[0135] Similarly, the second outer shield 27B may also exclude the second side passage 132 at the second side end 151B on the ventral blade surface 23c side, which is located on the side opposite to the second side end 151B on the dorsal blade surface 23d side opposite to the first outer shield 27A.

[0136] Therefore, at the first side end 151A on the back blade surface 23d side of the first outer shield 27A and the second side end 151B on the ventral blade surface 23c side of the second outer shield 27B, where the necessity is relatively low, the processing for setting the first side passage 131 and the second side passage 132 can be omitted, thereby suppressing the manufacturing cost of the blade section body 100.

[0137] In one embodiment, the blade section body 100 may include 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.

[0138] According to one embodiment of the blade section body 100, cooling air flowing in from the first opening 111 can be circulated to the first side passage 131 via the first circumferential passage 121. In addition, by allowing fluid flowing in from the first opening 111 to circulate in the first circumferential passage 121, the first leading edge end 153A, which tends to have a relatively high metal temperature, can be effectively cooled.

[0139] Similarly, according to one embodiment of the blade section body 100, fluid flowing in from the second opening 112 can flow through the second circumferential passage 122 to the second side passage 132. In addition, by allowing fluid flowing in from the second opening 112 to flow in the second circumferential passage 122, the second leading edge end 153B, which tends to have a relatively high metal temperature, can be effectively cooled.

[0140] In one embodiment of the blade section body 100, the position of the first opening 111 relative to the first airfoil 23A can be the same as the position of the second opening 112 relative to the second airfoil 23B.

[0141] For example, when the first segment 101A and the second segment 101B are manufactured by casting, and the first segment 101A and the second segment 101B are obtained from castings of the same shape, the openings corresponding to the first opening 111 and the second opening 112 can also be formed during the casting stage. This reduces the processing time after casting and helps to reduce the manufacturing cost of the blade segment 100.

[0142] This disclosure is not limited to the above-described embodiments, but also includes modifications to the above-described embodiments and appropriate combinations thereof.

[0143] The contents described in the above embodiments are as follows.

[0144] (1) The blade segment 100 of at least one embodiment of the present disclosure includes a first segment 101A, which includes a first airfoil 23A, a first outer shield 27A disposed on the outer side of the first airfoil 23A in the blade height direction, and an inner shield 25 (first inner shield) disposed on the inner side of the first airfoil 23A in the blade height direction. The blade segment 100 of at least one embodiment of the present disclosure includes a second segment 101B, which includes a second airfoil 23B, a second outer shield 27B disposed on the outer side of the second airfoil 23B in the blade height direction, and a second inner shield 25B disposed on the inner side of the second airfoil 23B in the blade height direction. The first outer shield 27A and the second outer shield 27B are bolted together. The inner shroud 25 (first inner shroud) of the first airfoil 23A is bolted to the second inner shroud 25B. The blade section body 100 of 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.

[0145] According to the structure described in (1), the gaps between the outer shields 27 of the first section body 101A and the inner shields 25 of the second section body 101B and between each other can be eliminated, and the leakage of fluid (cooling air CA) from the gaps can be suppressed. Therefore, in a rotating machine (gas turbine 10) equipped with blade section body 100, the reduction in efficiency can be suppressed.

[0146] Furthermore, according to the structure described in (1) above, the blade section 100, which bolts together the first section 101A and the second section 101B, is mounted on the housing (turbine chamber 30) of the rotating machinery (gas turbine 10), and the locating pin 191 mounted on the housing (turbine chamber 30) engages with the recess 181, thereby restricting the circumferential movement of the blade section 100. Additionally, even if the blade section 100 undergoes circumferential thermal elongation, the first section 101A, circumferentially extending from the recess 181 where the locating pin 191 engages, primarily elongates to one side, while the second section 101B, circumferentially extending from the recess 181 where the locating pin 191 engages, primarily elongates to the other side. Therefore, when the blade section 100 is cooled, the gap between the locating pin 191 and the recess 181 can be relatively small. As a result, the assembly of other components such as the sealing ring adjacent to the blade section body 100 becomes easier, which facilitates the assembly of rotating machinery (gas turbine 10) equipped with the blade section body 100.

[0147] (2) In several embodiments, in the structure described in (1) above, it is preferred that the first outer shield 27A includes a first side passage 131 formed from the leading edge 23a side to the trailing edge 23b side at one of the two circumferential first side ends 151A opposite to the second outer shield 27B (the first side end 151A on the ventral blade surface 23c side). Preferably, the second outer shield 27B includes a second side passage 132 formed from the leading edge 23a side to the trailing edge 23b side at one of the two circumferential second side ends 151B opposite to the first outer shield 27A (the second side end 151B on the dorsal blade surface 23d side). Preferably, at least one of the first side passage 131 and the second side passage 132 overlaps with the recess 181 when viewed from the blade height direction.

[0148] According to the structure described in (2) above, by allowing fluid (cooling air CA) to flow in the first side passage 131 and the second side passage 132, the fluid (cooling air CA) flowing in at least one of the first side passage 131 and the second side passage 132 can be used near the recess 181. As a result, the area where the metal temperature tends to become relatively high can be effectively cooled.

[0149] (3) In several embodiments, in the structure described in (2) above, it is preferred that the first side passage 131 and the second side passage 132 overlap with the recess 181 when viewed from the blade height direction.

[0150] Based on the structure described in (3) above, it is possible to cool more effectively the region where the metal temperature tends to become higher.

[0151] (4) In several embodiments, in the structure described in (2) or (3) above, it is preferable that the first outer shield 27A does not include a first side passage 131 at the first side end 151A (the first side end 151A on the dorsal blade surface 23d side) located on the side opposite to the first side end 151A (the first side end 151A on the ventral blade surface 23c side) opposite to the second outer shield 27B. The second outer shield 27B does not include a second side passage 132 at the second side end 151B (the second side end 151B on the ventral blade surface 23c side) located on the side opposite to the second side end 151B (the second side end 151B on the dorsal blade surface 23d side) opposite to the first outer shield 27A.

[0152] According to the structure described in (4) above, the processing for setting the first side passage 131 and the second side passage 132 can be omitted in areas where the necessity is relatively low, thereby reducing the manufacturing cost of the blade section body 100.

[0153] (5) In several embodiments, in any of the structures described in (2) to (4) above, it is preferred that the first outer shield 27A includes a first leading edge end portion 153A protruding from the first outer shield 27A toward the side opposite to the first airfoil portion 23A in the blade height direction at the end on the leading edge 23a side. Preferably, the first outer shield 27A has a first opening 111 formed on the surface of the first leading edge end portion 153A toward the trailing edge 23b side. Preferably, the first outer shield 27A includes a first circumferential passage 121 formed on the first leading edge end portion 153A and communicating the first opening 111 with the first side passage 131. The second outer shield 27B includes a second leading edge end portion 153B protruding from the second outer shield 27B toward the side opposite to the second airfoil portion 23B in the blade height direction at the end on the leading edge 23a side. Preferably, the second outer protective cover 27B has a second opening 112 formed on the surface of the second leading edge end 153B facing the trailing edge 23b. Preferably, the second outer protective cover 27B includes a second circumferential passage 122 formed on the second leading edge end 153B and communicating the second opening 112 with the second side passage 132.

[0154] According to the structure described in (5) above, the fluid (cooling air CA) flowing in from the first opening 111 can be allowed to flow through the first circumferential passage 121 to the first side passage 131. In addition, by allowing the fluid (cooling air CA) flowing in from the first opening 111 to flow in the first circumferential passage 121, the first leading edge end 153A, which tends to have a relatively high metal temperature, can be effectively cooled.

[0155] Furthermore, according to the structure described in (5) above, the fluid (cooling air CA) flowing in from the second opening 112 can circulate in the second side passage 132 via the second circumferential passage 122. In addition, by allowing the fluid (cooling air CA) flowing in from the second opening 112 to circulate in the second circumferential passage 122, the second leading edge end 153B, which tends to have a relatively high metal temperature, can be effectively cooled.

[0156] (6) In several embodiments, in the structure described in (5) above, it is preferable that the position of the first opening 111 relative to the first airfoil 23A is the same as the position of the second opening 112 relative to the second airfoil 23B.

[0157] According to the structure described in (6) above, for example, when the first segment 101A and the second segment 101B are manufactured by casting, and the first segment 101A and the second segment 101B are obtained from castings of the same shape, the openings corresponding to the first opening 111 and the second opening 112 can also be formed during the casting stage. This reduces the processing time after casting and reduces the manufacturing cost of the blade segment 100.

[0158] (7) The rotating machinery (gas turbine 10) of at least one embodiment of the present disclosure includes: a blade section body 100 with any of the structures in (1) to (6) above; a housing (turbine chamber 30) covering the blade section body 100; and a positioning pin 191 installed in the housing (turbine chamber 30) and whose front end engages with the recess 181.

[0159] According to the structure described above (7), the gaps between the outer shields 27 of the first section body 101A and the inner shields 25 of the second section body 101B and between each other can be eliminated, and the leakage of fluid (cooling air CA) from the gaps can be suppressed, thereby suppressing the reduction in efficiency of the rotating machinery (gas turbine 10).

[0160] Furthermore, based on the structure described above (7), the assembly of other components such as the sealing ring adjacent to the blade section body 100 becomes easier, which facilitates the assembly of the rotating machinery (gas turbine 10).

Claims

1. A blade segment body, wherein, The blade section body comprises: The first segment body includes a first airfoil, a first outer protective cover disposed on the outer side of the first airfoil in the blade height direction, and a first inner protective cover disposed on the inner side of the first airfoil in the blade height direction; and The second section body includes a second airfoil, a second outer protective cover disposed on the outer side of the second airfoil in the blade height direction, and a second inner protective cover disposed on the inner side of the second airfoil in the blade height direction. The first outer protective cover is bolted to the second outer protective cover. The first inner shield is bolted to the second inner shield. The blade segment has a recess that spans the first outer shield and the second outer shield. The recess is recessed inward toward the blade height direction compared to the area surrounding the recess in the circumferential direction.

2. The blade segment body according to claim 1, wherein, The first outer shield includes a first side passage extending from the leading edge to the trailing edge at one of the two circumferentially oriented first side ends, opposite to the second outer shield. The second outer shield includes a second side passage extending from the leading edge to the trailing edge at one of the two second side ends in the circumferential direction, opposite to the first outer shield. At least one of the first side passage and the second side passage overlaps with the recess when viewed from the blade height direction.

3. The blade segment body according to claim 2, wherein, The first side passage and the second side passage overlap with the recess when viewed from the height direction of the blade.

4. The blade segment body according to claim 2 or 3, wherein, The first outer shield does not include the first side passage at the first side end located on the side opposite to the first side end of the second outer shield, which is one of the two first side ends. The second outer shield does not include the second side passage at the second side end of the two second side ends, which is located on the side opposite to the second side end of the first outer shield.

5. The blade segment body according to claim 2 or 3, wherein, The first outer shroud includes a first leading-edge end portion that protrudes from the first outer shroud toward the side opposite to the first airfoil portion in the direction of blade height at the end on the leading-edge side. The first outer protective cover has a first opening formed at the first leading edge end facing the trailing edge side. The first outer protective cover includes a first circumferential passage formed at the first leading edge end and communicating the first opening and the first side passage. The second outer shroud includes a second leading edge end portion that protrudes from the second outer shroud toward the side opposite to the second airfoil in the direction of blade height at the end portion on the leading edge side. The second outer shield has a second opening formed at the end of the second leading edge facing the rear edge side. The second outer shield includes a second circumferential passage formed at the second leading edge end and connecting the second opening with the second side passage.

6. The blade segment body according to claim 5, wherein, The position of the first opening relative to the first wing-shaped portion is the same as the position of the second opening relative to the second wing-shaped portion.

7. A rotating machine, wherein, The rotating machinery includes: The blade segment body according to any one of claims 1 to 6; A housing that covers the blade segment body; and A locating pin is installed in the housing, and its front end engages with the recess.

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