Fixed blade, fixed blade segment, axial flow fluid machinery, manufacturing auxiliary device for fixed blade segment, and manufacturing method for fixed blade segment

Abstract

A stationary blade comprises: a blade body extending radially; and a shroud provided at an end portion of the blade body on a first radial side. The shroud comprises: a first circumferential end surface facing the first circumferential side; a second circumferential end surface facing the second circumferential side; an anti-gas path surface facing the first radial side; and an air path surface facing the second radial side. The anti-gas path surface is configured to have a plurality of flat surfaces continuously arranged circumferentially from the first circumferential end surface to the second circumferential end surface.

Description

Technical Field

[0001] The present invention relates to a stationary blade, a stationary blade segment including a plurality of the stationary blades, an axial flow fluid machine including the stationary blade segment, a manufacturing auxiliary device for the stationary blade segment, and a manufacturing method for the stationary blade segment.

[0002] This application claims priority based on Japanese Patent Application No. 2020-087313 filed in Japan on May 19, 2020, the contents of which are incorporated herein by reference. Background Art

[0003] A gas turbine is an axial flow fluid machine. This gas turbine includes a compressor that compresses air; a combustor that uses the air compressed by the compressor to burn fuel to generate combustion gas; and a turbine that is driven by the combustion gas from the combustor. The compressor includes a compressor rotor that rotates about an axis; a compressor casing that covers the compressor rotor; and a plurality of fixed blade rings. The turbine includes a turbine rotor that rotates about an axis; a turbine casing that covers the turbine rotor; and a plurality of fixed blade rings. Therefore, the compressor is also an axial flow fluid machine, and the turbine is also an axial flow fluid machine. The plurality of fixed blade rings of the compressor are arranged in the axial direction in which the axis extends. The plurality of fixed blade rings of the turbine are also arranged in the axial direction in which the axis extends.

[0004] Patent Document 1 below describes a stationary blade ring for a compressor, a type of axial-flow fluid machinery. This stationary blade ring comprises a plurality of arc-shaped stationary blade segments. Each stationary blade segment comprises: a plurality of stationary blades arranged circumferentially relative to an axis; an outer connecting member and an inner connecting member for connecting the plurality of stationary blades. Each of the plurality of stationary blades comprises: a blade body extending radially relative to the axis; an outer shroud disposed at the radially outer end of the blade body; and an inner shroud disposed at the radially inner end of the blade body.

[0005] An outer connecting member is mounted on the outer shrouds of the plurality of stationary blades. Furthermore, an inner connecting member is mounted on the inner shrouds of the plurality of stationary blades. A groove is formed in the outer shroud, recessed from the radially outer side toward the radially inner side and extending circumferentially. The outer connecting member is positioned so as to contact the bottom surface of the groove of the outer shroud of the plurality of stationary blades.

[0006] Previous technical literature

[0007] Patent Literature

[0008] Patent Document 1: Japanese Patent Application Laid-Open No. 2013-209896 Summary of the Invention

[0009] Technical issues to be solved by the invention

[0010] Manufacturers of axial-flow fluid machines are currently developing technologies to improve the performance of the axial-flow fluid machines and reduce their manufacturing costs.

[0011] Therefore, an object of the present invention is to provide a technology that can easily manufacture a stationary blade and suppress its manufacturing cost.

[0012] Means for solving technical problems

[0013] One embodiment of the present invention for achieving the above-mentioned object is a stationary blade arranged in a plurality along a circumferential direction relative to an axis. The stationary blade comprises: a blade body extending radially relative to the axis to form a blade shape; and a shroud provided at an end portion of the blade body on the first radial side, on one side in the radial direction (i.e., a first side) and on the other side (i.e., a second side) in the radial direction in which the axis extends, facing the upstream side; a rear end face facing the downstream side; a first circumferential end face facing the first circumferential side, on one side in the circumferential direction (i.e., a first side) and on the other side (i.e., a second side) along the circumferential direction relative to the axis, facing the second circumferential side; an anti-gas path surface facing the first radial side; and an air path surface facing the second radial side. The anti-gas path surface is configured to have a plurality of flat surfaces arranged continuously along the circumference, from the first circumferential end surface to the second circumferential end surface. A ridge line formed at a boundary between two adjacent planes in the circumferential direction among the plurality of planes is located on an imaginary circle centered on the axis.

[0014] A stationary blade segment according to one embodiment of the present invention for achieving the above-mentioned object includes a plurality of stationary blades of the embodiment described above. The plurality of stationary blades are arranged in the circumferential direction. The plurality of stationary blades are connected to each other in a state where the shrouds of two stationary blades adjacent in the circumferential direction contact each other.

[0015] An axial flow fluid machine according to one embodiment of the present invention, which is used to achieve the above-mentioned object, comprises: a stationary blade segment of the above-mentioned embodiment; a rotor rotating about the axis; and a casing covering the rotor. The stationary blade segment is arranged on the inner circumference of the casing and mounted on the casing.

[0016] As a manufacturing assistance device according to one embodiment of the present invention for achieving the above-mentioned purpose, it is a manufacturing assistance device for the following fixed blade segment. The fixed blade segment includes a plurality of fixed blades arranged in a circumferential direction relative to an axis. Each of the plurality of fixed blades includes: a blade body extending in a radial direction relative to the axis to form a blade shape; and a shroud provided at an end portion of the blade body on the first radial side, on one side in the radial direction, i.e., the first radial side, and on the other side in the radial direction, i.e., the second radial side. The shroud includes: a front end surface facing the upstream side of the axis, on one side in the axial direction in which the axis extends, i.e., the upstream side of the axis, and on the other side in the axial direction in which the axis extends, i.e., the downstream side of the axis; a rear end surface facing the downstream side of the axis; a first circumferential end surface facing the first circumferential side, on one side in the circumferential direction, i.e., the first circumferential side, and on the other side in the circumferential direction relative to the axis, i.e., the second circumferential end surface facing the second circumferential side; an anti-air path surface facing the first radial side; and an air path surface facing the second radial side.

[0017] The manufacturing auxiliary device comprises: a base plate, which is placed in a state where the plurality of fixed blades are arranged in the circumferential direction, and the front end face or the rear end face of the shield of each of the plurality of fixed blades can contact; a radial positioning block, which is fixed to the base plate and has an arc surface extending along the circumferential direction so as to be able to contact the anti-air road surface in the shield of each of the plurality of fixed blades placed on the base plate; a radial pushing device, which is installed on the base plate and pushes the plurality of fixed blades placed on the base plate toward the radial positioning block in the radial direction; a circumferential positioning block, which is fixed to The base plate is capable of contacting the first circumferential end surface of the shroud in the fixed blade, i.e., the first end fixed blade, which is arranged closest to the first circumferential side among the multiple fixed blades carried on the base plate; a circumferential pushing device is installed on the base plate, which pushes the fixed blade, i.e., the second end fixed blade, which is arranged closest to the second circumferential side among the multiple fixed blades carried on the base plate, toward the circumferential positioning block in the circumferential direction; and an axial direction pushing device is installed on the base plate, which pushes the multiple fixed blades carried on the base plate toward the base plate.

[0018] As a manufacturing method for achieving the above-mentioned purpose, one embodiment of the present invention is a manufacturing method for a fixed blade segment. The fixed blade segment includes a plurality of fixed blades arranged in a circumferential direction relative to an axis. Each of the plurality of fixed blades includes: a blade body extending in a radial direction relative to the axis to form a blade shape; and a shroud provided at an end portion of the blade body on the first radial side, on one side in the radial direction, i.e., the first radial side, and on the other side in the radial direction, i.e., the second radial side. The shroud includes: a front end face facing the upstream side of the axis, on one side in the axial direction in which the axis extends, i.e., the upstream side of the axis, and on the other side in the axial direction in which the axis extends, i.e., the downstream side of the axis; a rear end face facing the downstream side of the axis; a first circumferential end face facing the first circumferential side, on one side in the circumferential direction, i.e., the first circumferential side, and on the other side in the circumferential direction relative to the axis, i.e., the second circumferential end face facing the second circumferential side; an anti-gas path face facing the first radial side; and a gas path face facing the second radial side.

[0019] In a method for manufacturing a stationary blade segment, the following steps are performed: a stationary blade manufacturing step of manufacturing a plurality of stationary blades; a stationary blade placement step of arranging the plurality of stationary blades in the circumferential direction and temporarily positioning each of the plurality of stationary blades so that the circumferential position, radial position, and axial position of each of the plurality of stationary blades are at a target position, while the shrouds of two circumferentially adjacent stationary blades contact each other; a coupling step of coupling the plurality of stationary blades while the plurality of stationary blades are temporarily positioned; and a temporary positioning release step of releasing the temporary positioning of the plurality of stationary blades after the coupling step. In the stationary blade manufacturing step, the anti-gas path surface in the shroud of each of the plurality of stationary blades includes a plurality of flat surfaces continuously arranged in the circumferential direction from the first circumferential end surface to the second circumferential end surface, and the stationary blades are manufactured so that a ridge line formed at the intersection of two circumferentially adjacent flat surfaces among the plurality of flat surfaces lies on an imaginary circle centered on the axis.

[0020] Effects of the Invention

[0021] In one aspect of the present invention, the stationary blades can be easily manufactured and their manufacturing costs can be suppressed. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a schematic diagram showing the structure of a gas turbine in one embodiment according to the present invention.

[0023] Figure 2 This is a front view of a stationary blade ring in one embodiment of the present invention.

[0024] Figure 3 This is a perspective view of a stationary blade segment in one embodiment of the present invention.

[0025] Figure 4 It is along Figure 3 Cross-sectional view taken along line IV-IV.

[0026] Figure 5 It is a perspective view of a stationary blade in one embodiment according to the present invention.

[0027] Figure 6 yes Figure 3 VI direction view in .

[0028] Figure 7 It is along Figure 6 Cross-sectional view taken along line VII-VII.

[0029] Figure 8 This is a flowchart showing the steps of manufacturing a stationary blade segment in one embodiment of the present invention.

[0030] Figure 9 It is a side view of the manufacturing support device before temporary positioning in one embodiment of the present invention.

[0031] Figure 10 yes Figure 9 The X-axis view in .

[0032] Figure 11 It is a side view of the manufacturing support device in a temporary positioning state in one embodiment of the present invention.

[0033] Figure 12 yes Figure 11 XII direction view in.

[0034] Figure 13 It is an explanatory diagram showing a method for manufacturing a stationary blade in one embodiment according to the present invention.

[0035] Figure 14 It is an explanatory diagram showing a method of manufacturing a stationary blade in a comparative example.

[0036] Figure 15 It is a plan view of a plurality of stationary blades in a modified example of one embodiment according to the present invention.

[0037] Figure 16 This is a cross-sectional view of a main portion of a stationary blade segment in a modified example of one embodiment according to the present invention. DETAILED DESCRIPTION

[0038] Hereinafter, one embodiment of a stationary blade, a stationary blade segment including a plurality of the stationary blades, an axial flow fluid machine including the stationary blade segment, a stationary blade segment manufacturing assisting device, and a stationary blade segment manufacturing method according to the present invention will be described.

[0039] "Stationary blades, stationary blade segments and axial flow fluid machinery"

[0040] One embodiment of a stationary blade, a stationary blade segment including a plurality of the stationary blades, and an axial flow fluid machine including the stationary blade segment will be described in detail with reference to the drawings.

[0041] like Figure 1 As shown, the gas turbine 10 includes a compressor 40 that compresses external air A to generate compressed air; a plurality of combustors 20 that burn fuel F in the compressed air to generate combustion gas G; and a turbine 30 that is driven by the combustion gas G.

[0042] The compressor 40 includes a compressor rotor 41 that rotates about the rotor axis Ar, a compressor housing 45 that covers the compressor rotor 41, and a plurality of stationary blade rings 46. The turbine 30 includes a turbine rotor 31 that rotates about the axis Ar, a turbine housing 35 that covers the turbine rotor 31, and a plurality of stationary blade rows 36. The axial flow fluid machine of this embodiment is the compressor 40. Hereinafter, the direction in which the axis Ar extends is referred to as the axial direction Da, one of the two sides of the axial direction Da is referred to as the axial upstream side Dau, and the other side is referred to as the axial downstream side Dad.

[0043] The compressor 40 is located on the upstream side Dau of the turbine 30. The compressor rotor 41 and the turbine rotor 31 are located on the same axis Ar and are connected to each other to form the gas turbine rotor 11. For example, the rotor of the generator GEN is connected to the gas turbine rotor 11. The gas turbine 10 further includes an intermediate casing 14 located between the compressor casing 45 and the turbine casing 35. Compressed air from the compressor 40 flows into the intermediate casing 14. A plurality of combustors 20 are arranged along a circumferential direction Dc relative to the axis Ar and are mounted on the intermediate casing 14. The compressor casing 45, the intermediate casing 14, and the turbine casing 35 are connected to each other to form the gas turbine casing 15.

[0044] The compressor rotor 41 includes a rotor shaft 42 extending along an axial direction Da with the axis Ar as its center, and a plurality of rotating blade rows 43 mounted on the rotor shaft 42. The plurality of rotating blade rows 43 are arranged along the axial direction Da. Each rotating blade row 43 is composed of a plurality of rotating blades arranged along a circumferential direction Dc relative to the axis Ar. One of a plurality of stationary blade rings 46 is disposed on the axial downstream side Dad of each of the plurality of rotating blade rows 43. Each stationary blade ring 46 is disposed inside the compressor casing 45. Each stationary blade ring 46 is configured to have a plurality of stationary blades arranged along a circumferential direction Dc relative to the axis Ar.

[0045] The turbine rotor 31 includes a rotor shaft 32 extending in an axial direction Da centered on the axis Ar, and a plurality of rotating blade rows 33 mounted on the rotor shaft 32. The plurality of rotating blade rows 33 are arranged in the axial direction Da. Each rotating blade row 33 is composed of a plurality of rotating blades arranged in a circumferential direction Dc relative to the axis Ar. One of a plurality of stationary blade rows 36 is arranged on the axial upstream side Dau of each of the plurality of rotating blade rows 33. Each stationary blade row 36 is provided inside the turbine casing 35. Each stationary blade row 36 is composed of a plurality of stationary blades arranged in a circumferential direction Dc relative to the axis Ar.

[0046] like Figure 2 As shown, for ease of assembly, the stationary blade ring 46 of the compressor 40 is divided along the circumferential direction Dc. Each segment divided along the circumferential direction Dc constitutes a stationary blade segment 47. The stationary blade segment 47 is formed by interconnecting a plurality of stationary blades 50, some of which constitute the stationary blade ring 46, arranged along the circumferential direction Dc. The plurality of stationary blade segments 47 constituting the stationary blade ring 46 are arranged on the inner circumference of the compressor casing 45 and attached thereto.

[0047] like Figure 3 and Figure 4 As shown, the fixed blade segment 47 has: a plurality of fixed blades 50 arranged along the circumferential direction Dc; a connecting bracket (inner connecting component) 92, which is installed with respect to the radially inner Dri portion of the axis Ar of the plurality of fixed blades 50; and a connecting belt (outer connecting component) 90, which connects the radially outer Dro portion of the axis Ar of the plurality of fixed blades 50 to each other in the circumferential direction Dc.

[0048] like Figure 4 and Figure 5 As shown, the fixed blade 50 includes: a blade body 51 extending in the radial direction Dr to form a blade shape; an inner shroud 52 provided at the radially inner Dri end of the blade body 51; and an outer shroud 72 provided at the radially outer Dro end of the blade body 51.

[0049] The inner shroud 52 includes a shroud body 53, an upstream leg 65f, an upstream lip 66f, a downstream leg 65b, and a downstream lip 66b. The shroud body 53 is a plate-shaped member provided at the radially inner Dri end of the blade body 51 and extending in the circumferential direction Dc and the axial direction Da. The upstream leg 65f extends from the radially inner Dri end of the shroud body 53 along the radially inner Dri. The upstream lip 66f extends from the radially inner Dri end of the upstream leg 65f along the axially upstream Dau. The downstream leg 65b extends from the radially inner Dri end of the shroud body 53 along the axially downstream Dad. The downstream lip 66b extends from the radially inner Dri end of the downstream leg 65b along the axially downstream Dad. An upstream engagement groove 67f is formed between the shroud body 53 and the upstream lip 66f, recessed toward the axially downstream Dad. Furthermore, a downstream engagement groove 67b is formed between the shroud body 53 and the downstream lip 66b, which is recessed toward the axial upstream side Dau. The bottoms of these engagement grooves 67f, 67b are both formed by the legs 65f, 65b.

[0050] The shroud body 53 of the inner shroud 52 has a front end face 54f facing the axial upstream side Dau, a rear end face 54b facing the axial downstream side Dad, a first circumferential end face 55a facing the first circumferential side Dc1, and a second circumferential end face 55b facing the second circumferential side Dc2. The rear end face 54b is substantially parallel to the front end face 54f. The second circumferential end face 55b is substantially parallel to the first circumferential end face 55a. Therefore, when the shroud body 53 is viewed from the radial direction Dr, it has a parallelogram shape.

[0051] The inner shroud 52 further includes an air path surface 56 facing radially outward Dro and an anti-air path surface 57 facing radially inward Dri. The air path surface 56 is a surface facing radially outward Dro of the shroud body 53. The anti-air path surface 57 is configured to include a groove bottom surface 58, which faces radially inward Dri of the shroud body 53; a front anti-air path surface 61f, which faces radially inward Dri of the upstream lip 66f; and a rear anti-air path surface 61b, which faces radially inward Dri of the downstream lip 66b. In the anti-air path surface 57, the groove bottom surface 58 is located radially outward Dro relative to the front anti-air path surface 61f and the rear anti-air path surface 61b.

[0052] The outer shroud 72 includes a shroud body 73, an upstream leg 85f, an upstream lip 86f, a downstream leg 85b, and a downstream lip 86b. The shroud body 73 is a plate-shaped component that is provided at the end of the radially outer side Dro of the blade body 51 and extends in the circumferential direction Dc and the axial direction Da. The upstream leg 85f extends from the portion of the shroud body 73 on the axially upstream side Dau along the radially outer side Dro. The upstream lip 86f extends from the end of the radially outer side Dro of the upstream leg 85f along the axially upstream side Dau. The downstream lip 86b extends from the end of the radially outer side Dro of the downstream leg 85b along the axially downstream side Dad. A band groove 88 is formed between the upstream leg 85f and the downstream leg 85b, recessed from the radially outer side Dro to the radially inward side Dri and extending in the circumferential direction Dc.

[0053] The shroud body 73 of the outer shroud 72 has a front end face 74f facing the axial upstream side Dau, a rear end face 74b facing the axial downstream side Dad, a first circumferential end face 75a facing the circumferential first side Dc1, and a second circumferential end face 75b facing the circumferential second side Dc2. The rear end face 74b is substantially parallel to the front end face 74f. The second circumferential end face 75b is substantially parallel to the first circumferential end face 75a. Therefore, when the shroud body 73 is viewed from the radial direction Dr, it also has a parallelogram shape, similar to the shroud body 53 of the inner shroud 52.

[0054] The outer shroud 72 further includes an air path surface 76 facing radially inward Dri and an anti-air path surface 77 facing radially outward Dro. The air path surface 76 is the surface facing radially inward Dri of the shroud body 73. The anti-air path surface 77 is configured to include a groove bottom surface 78, which faces radially outward Dro of the shroud body 73; a front anti-air path surface 811f, which faces radially outward Dro of the upstream lip 86f; and a rear anti-air path surface 81b, which faces radially outward Dro of the downstream lip 86b. The groove bottom surface 78 is the bottom surface of the groove 88.

[0055] like Figures 5 to 7As shown, the groove bottom surface 78 of the outer shroud 72 is configured to have three flat surfaces 78a, 78b, and 78c arranged continuously along the circumferential direction Dc, extending from the first circumferential end surface 75a to the second circumferential end surface 75b. Of the three flat surfaces 78a, 78b, and 78c, the plane closest to the first circumferential side Dc1 is the first plane 78a, the plane adjacent to the second circumferential side Dc2 of the first plane 78a is the second plane 78b, and the plane adjacent to the second circumferential side Dc2 of the second plane 78b is the third plane 78c. A first ridgeline 79a formed at the intersection of the first and second planes 78a, 78b, extends parallel to the axis Ar and perpendicular to the circumferential direction Dc. A second ridgeline 79b formed at the intersection of the second and third planes 78b, 78c, extends parallel to the axis Ar and perpendicular to the circumferential direction Dc. The first ridgeline 79a and the second ridgeline 79b are both located on an imaginary circle centered on the axis Ar.

[0056] like Figure 4 As shown, the connecting bracket 92 includes a seal holding portion 93, an upstream leg portion 94f, an upstream flange portion 95f, a downstream leg portion 94b, and a downstream flange portion 95b.

[0057] The sealing holding portion 93 extends along the circumferential direction Dc. The upstream leg portion 94f extends from the end portion of the axial upstream side Dau of the sealing holding portion 93 along the radially outer side Dro. The upstream flange portion 95f extends from the end portion of the radially outer side Dro of the upstream leg portion 94f along the axial downstream side Dad. The upstream flange portion 95f is embedded in the upstream side engagement groove 67f of the inner shroud 52. The downstream leg portion 94b extends from the end portion of the axial downstream side Dad of the sealing holding portion 93 along the radially outer side Dro. The downstream flange portion 95b extends from the end portion of the radially outer side Dro of the downstream leg portion 94b along the axial upstream side Dau. The downstream flange portion 95b is embedded in the downstream side engagement groove 67b of the inner shroud 52. A sealing device 96 is provided on the radially inner side Dri of the sealing holding portion 93, and the sealing device 96 connects the rotor shaft 42 (reference Figure 1 ) is sealed between the connecting bracket 92.

[0058] like Figure 3 、 Figure 4 、 Figure 6 and Figure 7As shown, the connecting band 90 has a rectangular plate-like shape when viewed from the radial direction Dr. Furthermore, the connecting band 90 has a rectangular cross-section perpendicular to the circumferential direction Dc. The width of the connecting band 90 in the axial direction Da corresponds to the width of the band groove 88 in the axial direction Da. Furthermore, when the plurality of stationary blades 50 constituting the stationary blade segment 47 are arranged in the circumferential direction Dc, the length of the connecting band 90 in the circumferential direction Dc corresponds to the total length of the groove bottom surfaces 78 of each stationary blade 50 in the circumferential direction Dc.

[0059] "Manufacturing auxiliary device for fixed blade segment, and manufacturing method for fixed blade segment"

[0060] First, refer to Figure 9 and Figure 10 , the manufacturing auxiliary device used in the process of manufacturing the fixed blade segment 47 described above is described. In addition, Figure 10 yes Figure 9 X-axis view.

[0061] The manufacturing support device 100 includes a base plate 101 , a radial positioning block 105 , a radial pressing device 110 , a circumferential positioning block 115 , a circumferential pressing device 120 , an axial pressing device 125 , a circumference measurement reference block 130 , and a measuring instrument 135 .

[0062] A plurality of stationary blades 50 are placed on the base plate 101, arranged along the circumferential direction Dc. The front end surface 74f of the outer shroud 72 and the front end surface 54f of the inner shroud 52 of each of the plurality of stationary blades 50 are in contact with the base plate 101. For the sake of convenience in the following description, among the plurality of stationary blades 50 placed on the base plate 101, the stationary blade 50 positioned closest to the first circumferential side Dc1 is referred to as the first end stationary blade 50a, the stationary blade 50 positioned closest to the second circumferential side Dc2 is referred to as the second end stationary blade 50b, and the plurality of stationary blades 50 positioned between the first end stationary blade 50a and the second end stationary blade 50b is referred to as the intermediate stationary blade 50c.

[0063] Here, the axis Ar that serves as the reference for the circumferential direction Dc, axial direction Da, and radial direction Dr during the manufacturing of the stationary blade segment 47 is not the axis Ar of the compressor rotor 41, but rather a hypothetical axis Ar. However, the relative positional relationship between this hypothetical axis Ar and the plurality of stationary blades 50 temporarily positioned on the base plate 101, and the relative positional relationship between the axis Ar of the compressor rotor 41 and the plurality of stationary blades 50, is identical. Therefore, when the stationary blade segment 47 manufactured by the method of this embodiment is mounted on the compressor housing 45, the hypothetical axis Ar coincides with the axis Ar of the compressor rotor 41. Furthermore, the relationship between the circumferential direction Dc, axial direction Da, and radial direction Dr relative to the hypothetical axis Ar coincides with the relationship between the circumferential direction Dc, axial direction Da, and radial direction Dr relative to the axis Ar of the compressor rotor 41.

[0064] A radial positioning block 105 is fixed to the base plate 101. The radial positioning block 105 has a radially outer facing surface 106 that faces the front air return path 81f in the outer shroud 72 of each of the plurality of stationary blades 50 mounted on the base plate 101. The radially outer facing surface 106 is an arcuate surface centered on the imaginary axis Ar.

[0065] The radial pressing device 110 comprises: a radial pressing block 111 having a radially inner facing surface 112; and a radial pressing mechanism 113 for pressing the radial pressing block 111. Figure 9 In order to facilitate observation of the figure, the radial pushing device 110 is omitted. The radially inner opposing surface 112 is an arc surface centered on the imaginary axis Ar, and is opposed to the radially outer opposing surface 106 of the radial positioning block 105 at a distance in the radial direction Dr. Therefore, the radially inner opposing surface 112 is opposed to the front anti-air path surface 61f in the inner shroud 52 of each of the multiple fixed blades 50 carried on the base plate 101 in the radial direction Dr. The radial pushing mechanism 113 is mounted on the base plate 101. The radial pushing mechanism 113 pushes the radial pushing block 111 toward the radial outer side Dro. In other words, the radial pushing device 110 pushes the multiple fixed blades 50 carried on the base plate 101 toward the radial positioning block 105 side.

[0066] A circumferential positioning block 115 is fixed to the base plate 101. The circumferential positioning block 115 has a first circumferential facing surface 116. The first circumferential facing surface 116 is an inclined surface that is inclined relative to the base plate 101. The first circumferential facing surface 116 is capable of contacting the first circumferential end surface 75a of the outer shroud 72 and the first circumferential end surface 55a of the inner shroud 52 of the first end stationary blade 50a of the plurality of stationary blades 50 mounted on the base plate 101.

[0067] The circumferential pressing device 120 includes a circumferential pressing block 121 having a second circumferentially opposed surface 122, and a circumferentially opposed mechanism 123 for pressing the circumferential pressing block 121. The second circumferentially opposed surface 122 is an inclined surface that is inclined relative to the base plate 101. The second circumferentially opposed surface 122 opposes the first circumferentially opposed surface 116 of the circumferential positioning block 115 with a gap therebetween in the circumferential direction Dc. Therefore, the second circumferentially opposed surface 122 opposes the second circumferential end surface 75b of the outer shroud 72 and the second circumferential end surface 55b of the inner shroud 52 of the second end stationary blades 50b of the plurality of stationary blades 50 mounted on the base plate 101 in the circumferential direction Dc. The circumferential pressing mechanism 123 is mounted on the base plate 101. The circumferential pressing mechanism 123 pushes the circumferential pressing block 121 toward the first circumferential side Dc1. In other words, the circumferential direction pressing device 120 presses the plurality of stationary blades 50 placed on the base plate 101 toward the circumferential direction positioning block 115 .

[0068] The axial pressing device 125 includes an axial pressing block 126 having an axially facing surface 127 and an axially pressing mechanism 128 for pressing the axially pressing block 126. The axially facing surface 127 is formed so as to be able to contact the rear end surface 74b of the outer shroud 72 and the rear end surface 54b of the inner shroud 52 of each of the plurality of stationary blades 50 mounted on the base plate 101. The axially pressing mechanism 128 is mounted on the base plate 101. This axially pressing mechanism 128 presses the axially pressing block 126, which is in contact with the plurality of stationary blades 50 mounted on the base plate 101, toward the axial upstream side Dau. In other words, the axially pressing device 125 presses the plurality of stationary blades 50 mounted on the base plate 101 toward the base plate 101.

[0069] The circumference measurement reference block 130 is fixed to the base plate 101. This circumference measurement reference block 130 has a second circumferentially opposed surface 131. Like the second circumferentially opposed surface 122 of the circumferential pressure block 121, this second circumferentially opposed surface 131 is an inclined surface that is inclined relative to the base plate 101. This second circumferentially opposed surface 131 opposes the first circumferentially opposed surface 116 of the circumferential positioning block 115 with a gap therebetween in the circumferential direction Dc. Therefore, the second circumferentially opposed surface 131 opposes the second circumferential end surface 75b of the outer shroud 72 and the second circumferential end surface 55b of the inner shroud 52 of the second end stationary blades 50b among the plurality of stationary blades 50 mounted on the base plate 101 in the circumferential direction Dc. Therefore, the circumferential distance Dc between the radially outer side Dro portion of the inclined surface in the circumference measurement reference block 130 and the radially outer side Dro portion of the inclined surface in the circumferential positioning block 115, that is, the outer circumference is longer than the designed outer circumference, and the designed outer circumference is the circumferential design length between the first circumferential end surface 75a of the outer shroud 72 in the first end fixed blade 50a constituting a part of the fixed blade segment 47 and the second circumferential end surface 75b of the outer shroud 72 in the second end fixed blade 50b constituting another part of the fixed blade segment 47. Furthermore, the circumferential distance Dc between the radially inner Dri portion of the inclined surface in the circumference measurement reference block 130 and the radially inner Dri portion of the inclined surface in the circumferential positioning block 115, that is, the inner circumference is longer than the designed inner circumference, and the designed inner circumference is the designed length of the circumferential Dc between the first circumferential end surface 55a of the inner shroud 52 in the first end fixed blade 50a constituting a part of the fixed blade segment 47 and the second circumferential end surface 55b of the inner shroud 52 in the second end fixed blade 50b constituting another part of the fixed blade segment 47.

[0070] The circumference measurement reference block 130 is gate-shaped when viewed from the circumferential direction Dc. A portion of the circumferential pressing device 120 is disposed inside the gate-shaped circumference measurement reference block 130. Therefore, a portion of the circumferential pressing device 120 overlaps the circumference measurement reference block 130 when viewed from the axial direction Da.

[0071] The measuring instrument 135 has a longitudinal direction 136 , and a thickness perpendicular to the longitudinal direction varies depending on the position in the longitudinal direction.

[0072] Then, according to Figure 8 The flowchart shown in FIG. 1 illustrates a method for manufacturing the stationary blade segment 47 in this embodiment.

[0073] First, a plurality of stationary blades 50 constituting the stationary blade segment 47 are manufactured (S1: stationary blade manufacturing process). In the stationary blade manufacturing process (S1), first, an intermediate product of each stationary blade 50 is formed by forging or the like. The dimensions of each part of the intermediate product are larger than the dimensions of the finished stationary blade 50. Therefore, the intermediate product is cut using a working machine such as a machining center. Specifically, Figure 13 As shown, a tool 150a, such as a face milling cutter, cuts the front and rear air-repelling surfaces 81fm and 81bm of the outer shroud 72m of the intermediate product 50m. The tool axis 151a is aligned parallel to the front and rear air-repelling surfaces 81f and 81b of the finished outer shroud 72 and is moved relative to the intermediate product 50m in the circumferential direction Dc. As a result, the front and rear air-repelling surfaces 81f and 81b become arcuate surfaces with respect to the axis Ar. Furthermore, a tool 150b, such as a face milling cutter or slot milling cutter, cuts the groove bottom surface 78m of the outer shroud 72m of the intermediate product 50m. The tool axis 151b is aligned perpendicular to the first plane 78a of the multiple planes that constitute the groove bottom surface 78 of the finished outer shroud 72 and is moved in the axial direction Da. As a result, the first plane 78a becomes a plane parallel to the axis Ar. Next, the tool shaft 151b is made perpendicular to the second plane 78b among the multiple planes constituting the groove bottom surface 78 in the outer shield 72 of the finished product, and the tool shaft 151b is moved in the axial direction Da. As a result, the second plane 78b becomes a plane parallel to the axis Ar. And, as Figure 6 and Figure 7 As shown in FIG. 1 , the first ridge line 79a formed at the intersection of the first plane 78a and the second plane 78b is a straight line extending in a direction parallel to the axis Ar and perpendicular to the circumferential direction Dc. Furthermore, the tool axis 151b is made perpendicular to the third plane 78c among the multiple planes constituting the groove bottom surface 78 in the outer shield 72 of the finished product, and the tool axis 151b is moved in the axial direction Da. As a result, the third plane 78c becomes a plane parallel to the axis Ar. Furthermore, as shown in FIG. Figure 6 and Figure 7 As shown, the second ridge line 79b formed at the intersection of the second plane 78b and the third plane 78c is a straight line extending in a direction parallel to the axis Ar and perpendicular to the circumferential direction Dc. As described above, in this embodiment, the groove bottom surface 78m of the intermediate product 50m is processed into the plurality of flat surfaces 78a, 78b, and 78c by face cutting.

[0074] The stator blade manufacturing step ( S1 ) is completed by cutting the intermediate product 50 m described above.

[0075] like Figure 14As shown, if the groove bottom surface 78x in the finished product's outer shroud 72x is formed as an arcuate surface with respect to the axis Ar, machining is impossible, similar to the front and rear anti-airing road surfaces 81fm and 81bm of the intermediate product 50m. Specifically, it is impossible to form the arcuate groove bottom surface 78x by aligning the tool axis 151a of a tool such as a face milling cutter 150a parallel to the groove bottom surface 78x in the finished product's outer shroud 72x and then moving the tool axis 151a relative to the intermediate product 50m in the circumferential direction Dc. This is because if the tool axis 151a of a tool such as a face milling cutter 150a is aligned parallel to the groove bottom surface 78x in the finished product's outer shroud 72x, the tool axis 151a would interfere with the front and rear anti-airing road surfaces 81f and 81b of the finished product. Therefore, to form the groove bottom surface 78x in the finished outer shroud 72x into an arcuate surface with respect to the axis Ar, a tool 150c, such as an end mill, is used. In this case, the tool axis 151c is positioned perpendicular to the arcuate groove bottom surface 78x in the finished outer shroud 72x and moved in the axial direction Da. As a result, only a portion of the arcuate groove bottom surface 78x is formed. Next, the tool axis 151c is slightly offset relative to the intermediate product 50m in the circumferential direction Dc, and then moved in the axial direction Da. As a result, only the remaining portion of the arcuate groove bottom surface 78x is formed. The above steps are repeated to form the arcuate groove bottom surface 78x. In other words, in this case, the groove bottom surface 78m of the intermediate product 50m is machined into an arcuate surface by repeatedly performing wire cutting.

[0076] As described above, when the groove bottom surface 78x in the outer shroud 72x is formed as an arcuate surface with respect to the axis Ar, repeated line cutting is required, which complicates the manufacture of the stator blade 50x and increases its manufacturing cost. On the other hand, in this embodiment, the groove bottom surface 78 in the outer shroud 72 is formed into a plurality of flat surfaces 78a, 78b, and 78c by face cutting, thereby facilitating the manufacture of the stator blade 50x and reducing its manufacturing cost.

[0077] Next, the connecting belt 90 is manufactured ( S2 : belt manufacturing step).

[0078] Next, the connecting bracket 92 is manufactured ( S3 : bracket manufacturing step).

[0079] Next, the plurality of stationary blades 50 manufactured in the stationary blade manufacturing step (S1) are arranged in the circumferential direction Dc. Then, with the outer shrouds 72 of two adjacent stationary blades 50 in the circumferential direction Dc in contact with each other and the inner shrouds 52 of two stationary blades 50 in contact with each other, each of the plurality of stationary blades 50 is temporarily positioned (S4: stationary blade placement step) such that the position of each of the plurality of stationary blades 50 in the circumferential direction Dc, the position in the radial direction Dr, and the position in the axial direction Da are at the target position.

[0080] In the stationary blade arrangement step (S4), first, Figure 9 and Figure 10 As shown, on the base plate 101 of the manufacturing auxiliary device 100, between the radial positioning block 105 and the radial pushing device 110, and between the circumferential positioning block 115 and the circumferential pushing device 120, the plurality of fixed blades 50 manufactured in the fixed blade manufacturing process (S1) are arranged and configured along the circumferential direction Dc. At this time, the front end face 74f of the outer shroud 72 and the front end face 54f of the inner shroud 52 of each of the plurality of fixed blades 50 are brought into contact with the base plate 101. Next, the radial pushing mechanism 113 is operated to push the radial pushing block 111 toward the radial outer side Dro. As a result, as shown in FIG. Figure 11 and Figure 12As shown, the front side anti-air surface 61f of the inner shroud 52 of each of the plurality of stationary blades 50 is in contact with the radially inner facing surface 112 of the radial pressing block 111, and the front side anti-air surface 81f of the outer shroud 72 of each of the plurality of stationary blades 50 is in close contact with the radially outer facing surface 106 of the radial positioning block 105. Furthermore, the circumferential pressing mechanism 123 is operated to press the circumferential pressing block 121 toward the first circumferential side Dc1. As a result, the second circumferential end surface 75b of the outer shroud 72 and the second circumferential end surface 55b of the inner shroud 52 of the second-end stationary blade 50b among the plurality of stationary blades 50 contact the second circumferentially opposed surface 122 of the circumferential pressure block 121. Furthermore, the first circumferential end surface 75a of the outer shroud 72 and the first circumferential end surface 55a of the inner shroud 52 of the first-end stationary blade 50a among the plurality of stationary blades 50 closely contact the first circumferentially opposed surface 116 of the circumferential positioning block 11.5. Furthermore, the outer shrouds 72 of two stationary blades 50 adjacent in the circumferential direction Dc among the plurality of stationary blades 50 contact each other, and the inner shrouds 52 of two stationary blades 50 contact each other. Next, the axial pressure mechanism 128 is operated, and the axial pressure block 126 is pressed toward the axial upstream side Dau. As a result, the entire rear end surface 54b of the inner shroud 52 of each of the plurality of stationary blades 50 and the entire rear end surface 74b of the outer shroud 72 of each of the plurality of stationary blades 50 contact the axially opposed surface 127 of the axially opposed pressing block 126. Furthermore, the entire front end surface 54f of the inner shroud 52 of each of the plurality of stationary blades 50 and the entire front end surface 74f of the outer shroud 72 of each of the plurality of stationary blades 50 are in close contact with the base plate 101. As described above, each of the plurality of stationary blades 50 is temporarily positioned. Furthermore, to temporarily and securely maintain the temporary positioning of each of the plurality of stationary blades 50, the outer shroud 72 of each of the plurality of stationary blades 50 and the axially opposed pressing block 126 can be temporarily fastened using screws.

[0081] After executing the fixed blade configuration step (S4), Figure 11 and Figure 12 As shown, the second circumferential facing surface 131 of the circumference measurement reference block 130 faces the second circumferential end surface 75b of the outer shroud 72 and the second circumferential end surface 55b of the inner shroud 52 of the second end stationary blade 50b among the plurality of stationary blades 50 at intervals in the circumferential direction Dc.

[0082] Next, the length of the entire circumferential direction Dc of the plurality of stationary blades 50 temporarily positioned by the manufacturing support device 100 is measured (S5: circumferential length measuring step). In the circumferential length measuring step (S5), as shown in FIG. Figure 11 and Figure 12As shown, a measuring instrument 135 is inserted between the radially inner portion Dri of the second circumferentially facing surface 131 of the circumference measurement reference block 130 and the second circumferential end surface 55b of the inner shroud 52 of the second end stationary vane 50b. The length Dc between the first circumferential end surface 55a of the inner shroud 52 of the first end stationary vane 50a and the second circumferential end surface 55b of the inner shroud 52 of the second end stationary vane 50b, i.e., the inner circumference, is measured based on the amount of insertion of the measuring instrument 135. Furthermore, the measuring instrument 135 is inserted between the radially outer portion Dro of the second circumferentially facing surface 131 of the circumference measurement reference block 130 and the second circumferential end surface 75b of the outer shroud 72 of the second end stationary vane 50b. Then, the outer circumference (Dc) between the first circumferential end surface 75a of the outer shroud 72 in the first end fixing blade 50a and the second circumferential end surface 75b of the outer shroud 72 in the second end fixing blade 50b is measured based on the insertion amount of the measuring instrument 135.

[0083] Next, the plurality of fixed blades 50 temporarily positioned by the manufacturing support device 100 are connected to each other (S6: connecting step). In the connecting step (S6), as shown in FIG. Figure 3 、 Figure 4 and Figure 7 As shown, the connecting band 90 is placed in the band groove 88 of the plurality of stationary blades 50 temporarily positioned by the manufacturing support device 100, and the connecting band 90 is brought into contact with the ridges 79a and 79b of the plurality of stationary blades 50. Each of the plurality of stationary blades 50 is then connected to the connecting band 90 by welding. Alternatively, each of the plurality of stationary blades 50 may be connected to the connecting band 90 using screws instead of welding.

[0084] When the coupling step ( S6 ) is completed, the temporary positioning of the plurality of stationary blades 50 by the manufacturing support device 100 is released ( S7 : temporary positioning release step). In the temporary positioning release step ( S7 ), the plurality of stationary blades 50 coupled by the coupling band 90 are removed from the manufacturing support device 100 .

[0085] Next, at least one of the first circumferential end faces 55a, 75a of the first end stationary blade 50a and the second circumferential end faces 55b, 75b of the second end stationary blade 50b is cut so that the circumference of the plurality of stationary blades 50 connected by the connecting band 90 reaches the designed circumference (S8: joining surface processing step). Specifically, in this joining surface processing step (S8), at least one of the first circumferential end face 55a of the inner shroud 52 of the first end stationary blade 50a and the second circumferential end face 55b of the inner shroud 52 of the second end stationary blade 50b is cut so that the inner circumference of the plurality of stationary blades 50 connected by the connecting band 90 falls within a predetermined error range relative to the designed inner circumference. Furthermore, at least one of the first circumferential end surface 75a of the outer shroud 72 of the first-end stationary blade 50a and the second circumferential end surface 75b of the outer shroud 72 of the second-end stationary blade 50b is cut so that the outer circumference of the plurality of stationary blades 50 connected by the connecting band 90 falls within a predetermined tolerance range relative to the designed outer circumference. Furthermore, when cutting the shrouds, for example, when cutting the first circumferential end surface 55a of the inner shroud 52 of the first-end stationary blade 50a, the first circumferential end surface 75a of the outer shroud 72 of the first-end stationary blade 50a is cut. While the example herein describes cutting both the first circumferential end surface 55a of the inner shroud 52 and the first circumferential end surface 75a of the outer shroud 72, there are also cases where only one of the first circumferential end surfaces is cut.

[0086] When the joint surface processing step ( S8 ) is completed, coating is applied to the surfaces of the plurality of stationary blades 50 connected by the connecting band 90 ( S9 : coating step). In the coating step ( S9 ), a coating agent is sprayed onto the surfaces of the plurality of stationary blades 50 connected by the connecting band 90 .

[0087] After the coating step ( S9 ) is completed, the connecting bracket 92 is assembled onto the inner shroud 52 of the plurality of stationary blades 50 connected by the connecting band 90 ( S10 : bracket assembly step). During the assembly of the connecting bracket 92 , the upstream flange portion 95 f of the connecting bracket 92 is fitted into the upstream engagement groove 67 f of the inner shroud 52 , and the downstream flange portion 95 b of the connecting bracket 92 is fitted into the downstream engagement groove 67 b of the inner shroud 52 .

[0088] As above, the stationary blade segment 47 is completed.

[0089] As described above, in this embodiment, the plurality of flat surfaces 78 a , 78 b , and 78 c are formed on the groove bottom surface 78 of the outer shroud 72 by plane cutting. This facilitates the manufacture of the stationary blade 50 and the stationary blade segment 47 and reduces their manufacturing costs.

[0090] Furthermore, in this embodiment, the multiple stationary blades 50 are connected to each other after being securely and provisionally positioned using the manufacturing support device 100. Therefore, in this embodiment, each of the multiple stationary blades 50 is positioned at a target position in the circumferential direction Dc, a target position in the radial direction Dr, and a target position in the axial direction Da. "Reaching the target position" here means being very close to the target position; in other words, within a predetermined tolerance range relative to the design position.

[0091] Furthermore, in this embodiment, the circumference of the stationary blade segment 47 is adjusted so that the circumference thereof corresponds to the designed circumference. Therefore, in this embodiment, when arranging a plurality of stationary blade segments 47 along the circumferential direction Dc and assembling the stationary blade ring 46, after arranging one of the plurality of stationary blade segments 47, the other stationary blade segments 47 adjacent in the circumferential direction Dc can be easily assembled. Furthermore, the other stationary blade segments 47 can be arranged at the correct relative positions in the circumferential direction Dc relative to the one stationary blade segment 47.

[0092] "Variation"

[0093] In the above embodiment, the band manufacturing step (S2) is performed after the stationary blade manufacturing step (S1) and before the bracket manufacturing step (S3) and the stationary blade placement step (S4). However, the band manufacturing step (S2) can be performed at any time as long as it is before the connection step (S6) using the connection band 90. Furthermore, in the above embodiment, the bracket manufacturing step (S3) is performed after the stationary blade manufacturing step (S1) and the band manufacturing step (S2) and before the stationary blade placement step (S4). However, the bracket manufacturing step (S3) can be performed at any time as long as it is before the bracket assembly step (S10) using the connection bracket 92.

[0094] In the stator blade placement step ( S4 ) of the above embodiment, the front end surface 74f of the outer shroud 72 and the front end surface 54f of the inner shroud 52 are brought into contact with the base plate 101 . However, the rear end surface 74b of the outer shroud 72 and the rear end surface 54b of the inner shroud 52 may be brought into contact with the base plate 101 .

[0095] The manufacturing support device 100 of this embodiment includes a circumference measurement reference block 130 and a measuring instrument 135. However, the manufacturing support device 100 may also be provided without the circumference measurement reference block 130 and the measuring instrument 135. However, without the circumference measurement reference block 130 and the measuring instrument 135, for example, a flexible, graduated line or the like is passed along the plurality of stationary blades 50 to measure the circumference of the plurality of stationary blades 50. Therefore, in this case, circumference measurement becomes cumbersome, and the error included in the measured circumference value also increases. Therefore, as shown in this embodiment, the manufacturing support device 100 preferably includes the circumference measurement reference block 130 and the measuring instrument 135.

[0096] like Figure 6 As shown, the first ridgeline 79a and the second ridgeline 79b of the outer shroud 72 of this embodiment are both located on an imaginary circle extending in a direction parallel to the axis Ar and perpendicular to the circumferential direction Dc and centered on the axis Ar. Figure 15 As shown in FIG. 1 , the first ridgeline 79a and the second ridgeline 79b of the outer shroud 72 may not extend in a direction perpendicular to the circumferential direction Dc. Figure 15 In the illustrated example, both the first ridgeline 79 a and the second ridgeline 79 b are parallel to the first circumferential end surface 75 a or the second circumferential end surface 75 b of the outer shroud 72 .

[0097] However, as shown in this example, if the first ridgeline 79a and the second ridgeline 79b of the outer shroud 72 do not extend in a direction perpendicular to the circumferential direction Dc, the entire first ridgeline 79a and the entire second ridgeline 79b cannot be positioned on an imaginary circle having the same radius centered on the axis Ar. For example, even if the end portion of the first ridgeline 79a on the upstream side Dau of the axis and the end portion of the first ridgeline 79a on the downstream side Dad of the axis are positioned on an imaginary circle having the same radius centered on the axis Ar, the intermediate portion of the first ridgeline 79a between the end portion of the first ridgeline 79a on the upstream side Dau of the axis and the end portion of the first ridgeline 79a on the downstream side Dad of the axis will not be positioned on the imaginary circle having the same radius centered on the axis Ar. Therefore, as shown in this example, if the first ridgeline 79a and the second ridgeline 79b of the outer shroud 72 do not extend in a direction perpendicular to the circumferential direction Dc, the entire first ridgeline 79a and the entire second ridgeline 79b cannot be brought into contact with the connecting band 90, and the connection between the outer shroud 72 and the connecting band 90 becomes unstable. Therefore, the ridgelines 79a and 79b preferably extend in a direction parallel to the axis Ar and perpendicular to the circumferential direction Dc.

[0098] like Figure 7As shown, of the two stationary blades 50 adjacent to each other in the circumferential direction Dc, the first plane 78a of the stationary blade 50b on the second circumferential side Dc2 is adjacent to the third plane 78c of the stationary blade 50c on the first circumferential side Dc1 in the circumferential direction Dc. The first plane 78a of the stationary blade 50b on the second circumferential side Dc2 is at an angle of 180° relative to the third plane 78c of the stationary blade 50c on the first circumferential side Dc1, and is located on the same imaginary plane as the third plane 78c of the stationary blade 50c on the first circumferential side Dc1. However, the first plane 78a of the stationary blade 50b on the second circumferential side Dc2 may not be located on the same imaginary plane as the third plane 78c of the stationary blade 50c on the first circumferential side Dc1. For example, Figure 16 As shown, the first plane 78a of the stationary blade 50b on the second circumferential side Dc2 is at an angle less than 180° relative to the third plane 78c of the stationary blade 50c on the first circumferential side Dc1, and may not be located on the same imaginary plane as the third plane 78c of the stationary blade 50c on the first circumferential side Dc1.

[0099] The stationary blade segment 47 of the above embodiment is the stationary blade segment 47 in the compressor 40 of the gas turbine 10. However, the stationary blade segment 47 may be a stationary blade segment of another axial flow fluid machine.

[0100] Postscript

[0101] The stationary blade 50 in the above embodiment is explained as follows, for example.

[0102] (1) Regarding the fixed blade 50 in the first embodiment,

[0103] The plurality of stationary blades 50 are arranged along a circumferential direction Dc relative to the axis Ar. The stationary blade 50 includes a blade body 51 extending in a radial direction Dr relative to the axis Ar to form a blade shape; and a shroud 72 provided at an end of the blade body 51 on the radial first side Dro, on one side of the radial direction Dr, and on the other side of the radial second side Dri.

[0104] The shroud 72 includes: a front end surface 74f facing the upstream axial side Dau (on one side, i.e., the upstream axial side Dau) and the downstream axial side Dad (on the other side, i.e., the downstream axial side Dad) in the axial direction Da in which the axis Ar extends; a rear end surface 74b facing the downstream axial side Dad; a first circumferential end surface 75a facing the first circumferential side Dc1 (on one side, i.e., the first circumferential side De1) and the second circumferential side Dc2 (on the other side, i.e., the second circumferential end surface 75b facing the second circumferential side Dc2) along the circumferential direction Dc relative to the axis Ar; an anti-gas path surface 77 facing the first radial side Dro; and an gas path surface 76 facing the second radial side Dri. The anti-gas path surface 77 is configured to include a plurality of flat surfaces 78a, 78b, and 78c arranged continuously along the circumferential direction Dc, extending from the first circumferential end surface 75a to the second circumferential end surface 75b. Ridge lines 79a and 79b formed at the boundary between two adjacent planes in the circumferential direction Dc among the plurality of planes 78a, 78b, and 78c are located on an imaginary circle centered on the axis Ar.

[0105] The anti-gas path surface 77 of the shroud 72 in the stationary blade 50 of this embodiment is configured to include a plurality of flat surfaces 78a, 78b, and 78c arranged continuously along the circumferential direction Dc, extending from the first circumferential end surface 75a to the second circumferential end surface 75b. Therefore, in this embodiment, the plurality of flat surfaces 78a, 78b, and 78c constituting the anti-gas path surface 77 can be formed by face cutting, thereby facilitating the manufacture of the stationary blade 50 and reducing its manufacturing cost.

[0106] (2) Regarding the fixed blade 50 in the second embodiment,

[0107] In the stationary blade 50 of the first embodiment, the plurality of planes 78a, 78b, and 78c include a first plane 78a, a second plane 78b, and a third plane 78c. The first plane 78a and the second plane 78b are adjacent to each other in the circumferential direction Dc, and the second plane 78b and the third plane 78c are adjacent to each other in the circumferential direction Dc. A ridgeline 79a formed at the boundary between the first plane 78a and the second plane 78b, and a ridgeline 79b formed at the boundary between the second plane 78b and the third plane 78c are both located on the imaginary circle centered on the axis Ar.

[0108] In this embodiment, compared with the case where the anti-air path surface 77 is formed by two planes continuously arranged along the circumferential direction Dc from the position of the first circumferential end surface 55a to the position of the second circumferential end surface 75b in the circumferential direction Dc, each plane can be made to lie along an imaginary circle centered on the axis Ar.

[0109] (3) Regarding the fixed blade 50 in the third embodiment,

[0110] In the stationary blade 50 of the first embodiment or the second embodiment, the ridge lines 79 a and 79 b extend in a direction parallel to the axis Ar and perpendicular to the circumferential direction Dc.

[0111] In this embodiment, the entire ridge lines 79a and 79b can be positioned on a virtual circle having the same radius with the axis Ar as the center.

[0112] (4) Regarding the fixed blade 50 in the fourth embodiment,

[0113] In the stationary blade 50 of any one of the first to third aspects, the air return path surface 77 includes the front air return path surface 81 f , the groove bottom surface 78 , and the rear air return path surface 81 b .

[0114] The front air return path surface 81f, the groove bottom surface 78, and the rear air return path surface 81b are arranged in this order from the axial upstream side Dau toward the axial downstream side Dad. The groove bottom surface 78 is located closer to the radial second side Dri than the front air return path surface 81f and the rear air return path surface 81b. The groove bottom surface 78 is configured to have the plurality of flat surfaces 78a, 78b, and 78c.

[0115] (5) Regarding the fixed blade 50 in the fifth embodiment,

[0116] In the stationary blade 50 of any one of the first to fourth aspects, of the radially outer side Dro and the radially inner side Dri in the radial direction Dr, the radially outer side Dro is the radially first side, and the radially inner side Dri is the radially second side. The shroud 72 is an outer shroud provided at an end portion of the radially outer side Dro of the blade body 51.

[0117] The stationary blade segment 47 in the above embodiment can be understood, for example, as follows.

[0118] (6) Regarding the fixed blade segment 47 in the sixth embodiment,

[0119] The plurality of stationary blades 50 are provided in any one of the first to fifth embodiments. The plurality of stationary blades 50 are arranged along the circumferential direction Dc. The plurality of stationary blades 50 are connected to each other in a state where the shrouds of two adjacent stationary blades 50 in the circumferential direction Dc are in contact with each other.

[0120] (7) Regarding the fixed blade segment 47 in the seventh embodiment,

[0121] The invention includes a plurality of stationary blades 50 of any one of the first to fifth embodiments. Furthermore, the invention includes a connecting band 90. The plurality of stationary blades 50 are arranged along the circumferential direction Dc. Each of the plurality of stationary blades 50 is connected to the connecting band 90, with the shrouds of two adjacent stationary blades 50 in the circumferential direction Dc in contact with each other.

[0122] The axial flow fluid machine in the above embodiment can be understood, for example, as follows.

[0123] (8) Regarding the axial flow fluid machinery in the eighth embodiment,

[0124] It includes the sixth or seventh embodiment of the fixed blade segment 47, a rotor 41 that rotates about the axis Ar, and a housing 45 that covers the rotor 41. The fixed blade segment 47 is disposed on the inner circumference of the housing 45 and attached to the housing 45.

[0125] The manufacturing support device 100 for the stationary blade segment 47 in the above embodiment can be understood as follows, for example.

[0126] (9) The manufacturing support device 100 in the ninth embodiment is a manufacturing support device for the fixed blade segment 47 as described below.

[0127] The stationary blade segment 47 includes a plurality of stationary blades 50 arranged along a circumferential direction Dc relative to the axis Ar. Each of the plurality of stationary blades 50 includes a blade body 51 extending in a radial direction Dr relative to the axis Ar to form a blade shape; and a shroud 72 provided at an end portion of the blade body 51 on the radial first side Dro, on one side of the radial direction Dr, and on the radial second side Dri, on the other side of the radial direction Dr. The shield 72 has: a front end face 74f, facing the axial upstream side Dau on one side of the axial direction Da along which the axis Ar extends, i.e., the axial upstream side Dau, and the other side, i.e., the axial downstream side Dad; a rear end face 74b, facing the axial downstream side Dad; a first circumferential end face 75a, facing the circumferential first side Dc1 on one side of the circumferential direction Dc relative to the axis Ar, i.e., the circumferential first side Dc1, and the other side, i.e., the circumferential second side Dc2; a second circumferential end face 75b, facing the circumferential second side Dc2; an anti-air path surface 77, facing the radial first side Dro; and an air path surface 76, facing the radial second side Dri.

[0128] The manufacturing auxiliary device 100 comprises: a base plate 101, which is placed in a state where the plurality of fixed blades 50 are arranged along the circumferential direction Dc, and the front end face 74f or the rear end face 74b of the shield 72 of each of the plurality of fixed blades 50 can contact; a radial positioning block 105, which is fixed on the base plate 101 and has an arc surface 106 extending along the circumferential direction Dc so as to be able to contact the anti-air road surface 77 in the shield 72 of each of the plurality of fixed blades 50 placed on the base plate 101; a radial pushing device 110, which is installed on the base plate 101 and pushes the plurality of fixed blades 50 placed on the base plate 101 toward the radial positioning block 105 side in the radial direction Dr; a circumferential positioning block 11.5, which is fixed on The base plate 101 can contact the first circumferential end face 75a of the shroud 72 in the fixed blade 50, i.e., the first end fixed blade 50a, among the multiple fixed blades 50 carried on the base plate 1.01 and arranged closest to the first circumferential side Dc1; the circumferential pushing device 120 is installed on the base plate 101, and pushes the fixed blade 50, i.e., the second end fixed blade 50b, among the multiple fixed blades 50 carried on the base plate 101 and arranged closest to the second circumferential side Dc2, toward the side of the circumferential positioning block 115 in the circumferential direction Dc; and the axial direction pushing device 125 is installed on the base plate 101, and pushes the multiple fixed blades 50 carried on the base plate 101 toward the side of the base plate 101.

[0129] In this embodiment, the multiple stationary blades 50 constituting the stationary blade segment 47 are arranged along the circumferential direction Dc. With the shrouds of two adjacent stationary blades 50 in the circumferential direction Dc in contact with each other, each of the multiple stationary blades 50 can be easily and accurately provisionally positioned so that its position in the circumferential direction Dc, radial direction Dr, and axial direction Da are at the target position. By using the manufacturing support device 100 of this embodiment, the multiple stationary blades 50 are interconnected while each is provisionally positioned, thereby manufacturing the stationary blade segment 47. Therefore, when the manufacturing support device 100 of this embodiment is used to manufacture the stationary blade segment 47, the position of each of the multiple stationary blades 50 in the circumferential direction Dc, radial direction Dr, and axial direction Da are at the target position. The phrase "at the target position" here means that the position is very close to the target position, in other words, within a predetermined tolerance range relative to the design position.

[0130] (10) Regarding the manufacturing support device 100 in the tenth embodiment,

[0131] In the manufacturing auxiliary device 100 of the ninth mode, there is also provided: a circumference measurement reference block 130, which is fixed on the base plate 101 and is opposite to the second circumferential end face 75b of the second end fixed blade 50b of the multiple fixed blades 50 carried on the base plate 101, separated by a gap in the circumferential direction Dc.

[0132] In this embodiment, the length in the circumferential direction Dc, i.e., the circumference, of the first circumferential end surface 75a of the first end stationary blade 50a and the second circumferential end surface 75b of the second end stationary blade 50b of the plurality of stationary blades 50 constituting the stationary blade segment 47 can be measured using the circumference measurement reference block 130 as a reference.

[0133] (11) Regarding the manufacturing support device 100 in the eleventh embodiment,

[0134] The manufacturing support device 100 of the tenth embodiment further includes a measuring tool 135 having a longitudinal direction 136 , and a thickness perpendicular to the longitudinal direction 136 that changes depending on a position in the longitudinal direction 136 .

[0135] In this embodiment, a measuring instrument 135 is inserted between the second circumferential end surface 75b of the second end stationary blade 50b of the plurality of stationary blades 50 constituting the stationary blade segment 47 and the circumference measurement reference block 130 , thereby making it possible to easily measure the circumference based on the insertion amount of the measuring instrument 135 .

[0136] The method of manufacturing the stationary blade segment 47 in the above embodiment can be understood as follows, for example.

[0137] (12) The manufacturing method in the twelfth embodiment is the following method for manufacturing the stationary blade segment 47 .

[0138] The stationary blade segment 47 includes a plurality of stationary blades 50 arranged along a circumferential direction Dc relative to the axis Ar. Each of the plurality of stationary blades 50 includes a blade body 51 extending in a radial direction Dr relative to the axis Ar to form a blade shape; and a shroud 72 provided at an end portion of the blade body 51 on the radial first side Dro, on one side of the radial direction Dr, and on the radial second side Dri, on the other side of the radial direction Dr. The shield 72 has: a front end face 74f, facing the axial upstream side Dau on one side of the axial direction Da along which the axis Ar extends, i.e., the axial upstream side Dau, and the other side, i.e., the axial downstream side Dad; a rear end face 74b, facing the axial downstream side Dad; a first circumferential end face 75a, facing the circumferential first side Dc1 on one side of the circumferential direction Dc relative to the axis Ar, i.e., the circumferential first side Dc1, and the other side, i.e., the circumferential second side Dc2; a second circumferential end face 75b, facing the circumferential second side Dc2; an anti-air path surface 77, facing the radial first side Dro; and an air path surface 76, facing the radial second side Dri.

[0139] In the manufacturing method of the fixed blade segment 47, the following are performed: a fixed blade manufacturing process S1, manufacturing the plurality of fixed blades 50; a fixed blade configuration process S4, arranging the plurality of fixed blades 50 along the circumferential direction Dc, and temporarily positioning each of the plurality of fixed blades 50 in a manner such that the position of each of the plurality of fixed blades 50 in the circumferential direction Dc becomes a target position, the position of the radial direction Dr becomes a target position, and the position of the axial direction Da becomes a target position, in a state in which the plurality of fixed blades 50 are adjacent to each other in the circumferential direction Dc, while the shrouds 72 of each of the plurality of fixed blades 50 are in contact with each other; a connecting process S6, connecting the plurality of fixed blades 50 to each other in a state in which the plurality of fixed blades 50 are temporarily positioned; and a temporary positioning release process S7, releasing the temporary positioning of the plurality of fixed blades 50 after the connecting process S6. In the fixed blade manufacturing process S1, the anti-air path surface 77 in the shield of each of the multiple fixed blades 50 has a plurality of planes 78a, 78b, 78c continuously arranged along the circumferential direction Dc from the position of the first circumferential end face 75a of the circumferential direction Dc to the position of the second circumferential end face 75b, and the fixed blade 50 is manufactured in such a manner that the ridges 79a, 79b formed at the intersection of two adjacent planes in the multiple planes 78a, 78b, 78c in the circumferential direction Dc are located on an imaginary circle centered on the axis Ar.

[0140] In this embodiment, the plurality of flat surfaces 78 a , 78 b , and 78 c constituting the anti-air path surface 77 can be formed by surface cutting, so that the stator blade 50 can be easily manufactured and its manufacturing cost can be suppressed.

[0141] (13) Regarding the manufacturing method in the thirteenth embodiment,

[0142] The manufacturing method of the twelfth embodiment further includes a band manufacturing step S2 of manufacturing a connecting band 90 for mutually connecting the plurality of stationary blades 50 while the plurality of stationary blades 50 are arranged in the circumferential direction Dc. In the connecting step S6, the ridge lines 79a and 79b of each of the plurality of stationary blades 50 are brought into contact with the connecting band 90 while the plurality of stationary blades 50 are temporarily positioned, thereby connecting each of the plurality of stationary blades 50 to the connecting band 90.

[0143] (14) Regarding the manufacturing method in the fourteenth embodiment,

[0144] In the manufacturing method of the twelfth or thirteenth embodiment, the following are also performed: a circumference measuring process S5, in which, when the multiple fixed blades 50 are temporarily positioned, the length in the circumferential direction Dc, that is, the circumference, from the first circumferential end face 75a of the shroud 72 in the first end fixed blade 50a, which is the fixed blade 50 closest to the first circumferential side Dc1 among the multiple fixed blades 50, to the second circumferential end face 75b of the shroud 72 in the second end fixed blade 50b, which is the fixed blade 50 closest to the second circumferential side Dc2 among the multiple fixed blades 50, is measured; and a joining surface processing process S8, after the temporary positioning release process S7, at least one circumferential end face of the first end fixed blade 50a and the second circumferential end face 75b of the second end fixed blade 50b is cut in such a way that the circumference becomes the target circumference.

[0145] In this embodiment, the circumference of the stationary blade segment 47 can be set to the target circumference. In addition, "reaching the target circumference" here means that the circumference is very close to the target circumference, in other words, the circumference falls within a predetermined error range relative to the design circumference.

[0146] (15) Regarding the manufacturing method in the fifteenth embodiment,

[0147] In the manufacturing method of any one of the twelfth to fourteenth aspects,

[0148] In the fixed blade configuration process S4, the manufacturing auxiliary device 100 of the fixed blade segment 47 of any one of the ninth to eleventh methods is used to temporarily position the multiple fixed blades 50 in such a manner that the circumferential position Dc of each of the multiple fixed blades 50 becomes the target position, the radial position Dr becomes the target position, and the axial position Da becomes the target position.

[0149] In this embodiment, the manufacturing support device 100 is used to temporarily position the plurality of stationary blades 50 that comprise the stationary blade segment 47. Each of the plurality of stationary blades 50 is positioned at a target position in the circumferential direction Dc, a target position in the radial direction Dr, and a target position in the axial direction Da. The phrase "reaching the target position" here means reaching a position very close to the target position; in other words, within a predetermined tolerance range relative to the designed position.

[0150] Industrial applicability

[0151] In one aspect of the present invention, the stationary blades can be easily manufactured and their manufacturing costs can be suppressed.

[0152] Explanation of symbols

[0153] 10-Gas turbine, 11-Gas turbine rotor, 14-Intermediate casing, 15-Gas turbine casing, 20-Combustor, 30-Turbine, 31-Turbine rotor, 32-Rotor shaft, 33-Rotating blade row, 35-Turbine casing, 36-Stationary blade row, 40-Compressor, 41-Compressor rotor, 42-Rotor shaft, 43-Rotating blade row, 45-Compressor casing, 46-Stationary blade ring, 47-Stationary blade segment, 50-Stationary blade, 50a-First end stationary blade, 50b-Second end stationary blade, 50c-Intermediate stationary blade, 50m-Intermediate product, 51-Blade body, 52-Inner shroud, 53-Shroud body, 54f-Front end face, 54b-Rear end face , 55a-first circumferential end face, 55b-second circumferential end face, 56-air pavement surface, 57-anti-air pavement surface, 58-groove bottom surface, 61f-front anti-air pavement surface, 61b-rear anti-air pavement surface, 65f-upstream leg, 66f-upstream lip, 65b-downstream leg, 66b-downstream lip, 67f-upstream engaging groove, 67b-downstream engaging groove, 72, 72m-outer shield, 73-shield body, 74f-front end face, 74b-rear end face, 75a-first circumferential end face, 75b-second circumferential end face, 76-air pavement surface, 77-anti-air pavement surface, 78, 78m-groove bottom surface, 78a-first plane (or simply plane), 78b-second plane (or simply plane), 78c -the third plane (or simply the plane), 79a-the first ridge (or simply the ridge), 79b-the second ridge (or simply the ridge), 81f, 81fm-the front anti-air road surface, 81b, 81bm-the rear anti-air road surface, 85f-the upstream leg, 86f-the upstream lip, 85b-the downstream leg, 86b-the downstream lip, 88-the belt groove, 90-the connecting belt (the outer connecting component), 92-the connecting bracket (the inner connecting component), 93-the sealing holding part, 94f-the upstream leg, 95f-the upstream flange, 94b-the downstream leg, 95b-the downstream flange, 96-the sealing device, 100-the manufacturing auxiliary device, 101-the base plate, 105-the radial positioning block, 106-the radial Outer facing surface (arc surface), 110- radial pushing device, 111- radial pushing block, 112- radial inner facing surface, 113- radial pushing mechanism, 115- circumferential positioning block, 116- first circumferential facing surface, 120- circumferential pushing device, 121- circumferential pushing block, 122- second circumferential facing surface, 123- circumferential pushing mechanism, 125- axial direction pushing device, 126- axial direction pushing block, 127- axial direction facing surface, 128- axial direction pushing mechanism, 130- circumference measurement reference block, 131- second circumferential facing surface, North 5- measuring instrument, 136- length direction, 150a, 150b, 150c- tool, 151a, 151b, 151c- tool axis,A-external air, F-fuel, G-combustion gas, Ar-axis, Da-axis direction, Dau-axis upstream side, Dad-axis downstream side, Dc-circumferential direction, Dc1-circumferential first side, Dc2-circumferential second side, Dr-radial direction, Dro-radial outer side, Dri-radial inner side.

Claims

1. A plurality of stationary blades are arranged in a circumferential direction relative to an axis, wherein the stationary blades have: a blade body extending in a radial direction relative to the axis to form a blade shape; and A shroud is provided at an end portion of the blade body on the first radial side, on one radial side, that is, a first radial side, and on the other radial side, that is, a second radial side. The shield has: The front end face is oriented toward the upstream side of the axis, on one side (i.e., the upstream side) and the other side (i.e., the downstream side) in the axial direction in which the axis extends; a rear end surface facing downstream of the axis; a first circumferential end surface, facing the first circumferential side, between one side, i.e., a first circumferential side, and the other side, i.e., a second circumferential side, along the circumference relative to the axis; a second circumferential end surface facing the second circumferential side; an anti-air road surface, facing the first radial side; and an air path, toward the radial second side, The anti-gas road surface is configured to have a plurality of planes arranged continuously along the circumferential direction from the position of the first circumferential end surface to the position of the second circumferential end surface. The plurality of planes include a first plane, a second plane and a third plane, The first plane is adjacent to the second plane in the circumferential direction, and the second plane is adjacent to the third plane in the circumferential direction. A ridge line formed at the boundary between the first plane and the second plane, and a ridge line formed at the boundary between the second plane and the third plane are both located on an imaginary circle centered on the axis.

2. A plurality of stationary blades arranged in a circumferential direction relative to an axis, the stationary blades comprising: a blade body extending in a radial direction relative to the axis to form a blade shape; and A shroud is provided at an end portion of the blade body on the first radial side, on one radial side, that is, a first radial side, and on the other radial side, that is, a second radial side. The shield has: The front end face is oriented toward the upstream side of the axis, on one side (i.e., the upstream side) and the other side (i.e., the downstream side) in the axial direction in which the axis extends; a rear end surface facing downstream of the axis; a first circumferential end surface, facing the first circumferential side, between one side, i.e., a first circumferential side, and the other side, i.e., a second circumferential side, along the circumference relative to the axis; a second circumferential end surface facing the second circumferential side; an anti-air road surface, facing the first radial side; and an air path, toward the radial second side, The anti-air road surface comprises a front anti-air road surface, a groove bottom surface and a rear anti-air road surface. From the upstream side of the axis toward the downstream side of the axis, the front air-reversing road surface, the groove bottom surface, and the rear air-reversing road surface are arranged in order. The groove bottom surface is located closer to the second side in the radial direction than the front and rear anti-air road surfaces. The groove bottom surface of the anti-gas road surface is configured to have a plurality of flat surfaces continuously arranged along the circumferential direction from the position of the first circumferential end surface to the position of the second circumferential end surface. A ridge line formed at a boundary between two adjacent planes in the circumferential direction among the plurality of planes is located on an imaginary circle centered on the axis.

3. A plurality of stationary blades arranged in a circumferential direction relative to an axis, the stationary blades comprising: a blade body extending in a radial direction relative to the axis to form a blade shape; and A shroud is provided at an end portion of the blade body on the first radial side, on one radial side, that is, a first radial side, and on the other radial side, that is, a second radial side. The shield has: The front end face is oriented toward the upstream side of the axis, on one side (i.e., the upstream side) and the other side (i.e., the downstream side) in the axial direction in which the axis extends; a rear end surface facing downstream of the axis; a first circumferential end surface, facing the first circumferential side, between one side, i.e., a first circumferential side, and the other side, i.e., a second circumferential side, along the circumference relative to the axis; a second circumferential end surface facing the second circumferential side; an anti-air road surface, facing the first radial side; and an air path, toward the radial second side, The anti-gas road surface is configured to have a plurality of planes arranged continuously along the circumferential direction from the position of the first circumferential end surface to the position of the second circumferential end surface. A ridge line formed at the intersection of two circumferentially adjacent planes among the plurality of planes is located on an imaginary circle centered on the axis. Of the radial outer side and the radial inner side in the radial direction, the radial outer side is the radial first side, and the radial inner side is the radial second side. The shroud is an outer shroud provided at the radially outer end of the blade body.

4. The stationary blade according to any one of claims 1 to 3, wherein: The ridge line is parallel to the axis and extends in a direction perpendicular to the circumferential direction.

5. A stationary blade segment comprising a plurality of stationary blades according to any one of claims 1 to 4. The plurality of fixed blades are arranged along the circumferential direction, The plurality of stationary blades are coupled to each other in a state in which the shrouds of two stationary blades adjacent to each other in the circumferential direction among the plurality of stationary blades are in contact with each other.

6. A fixed blade segment comprising a plurality of fixed blades and a connecting belt. The plurality of fixed blades respectively have: a blade body extending in a radial direction relative to the axis to form a blade shape; and A shroud is provided at an end portion of the blade body on the first radial side, on one radial side, that is, a first radial side, and on the other radial side, that is, a second radial side. The shield has: The front end face is oriented toward the upstream side of the axis, on one side (i.e., the upstream side) and the other side (i.e., the downstream side) in the axial direction in which the axis extends; a rear end surface facing downstream of the axis; a first circumferential end surface, facing the first circumferential side, between one side, i.e., a first circumferential side, and the other side, i.e., a second circumferential side, along the circumference relative to the axis; a second circumferential end surface facing the second circumferential side; an anti-air road surface, facing the first radial side; and an air path, toward the radial second side, The anti-gas road surface is configured to have a plurality of planes arranged continuously along the circumferential direction from the position of the first circumferential end surface to the position of the second circumferential end surface. A ridge line formed at the intersection of two circumferentially adjacent planes among the plurality of planes is located on an imaginary circle centered on the axis. The plurality of fixed blades are arranged along the circumferential direction, Each of the plurality of stationary blades is connected to the connecting band in a state where the shrouds of two stationary blades adjacent in the circumferential direction contact each other and the ridge line of each of the plurality of stationary blades contacts the connecting band.

7. A stationary blade segment comprising a plurality of stationary blades according to any one of claims 1 to 4 and a connecting belt. The plurality of fixed blades are arranged along the circumferential direction, Each of the plurality of stationary blades is connected to the connecting band in a state where the shrouds of two stationary blades adjacent in the circumferential direction contact each other and the ridge line of each of the plurality of stationary blades contacts the connecting band.

8. An axial flow fluid machine comprising: The stationary blade segment according to any one of claims 5 to 7; a rotor, rotating about the axis; and a housing covering the rotor, The stationary blade segment is arranged on the inner peripheral side of the casing and mounted on the casing.

9. A manufacturing auxiliary device for fixing blade segments, wherein: The fixed blade segment has: A plurality of fixed blades are arranged in a circumferential direction relative to the axis. The plurality of fixed blades each have: a blade body extending in a radial direction relative to the axis to form a blade shape; and A shroud is provided at an end portion of the blade body on the first radial side, on one radial side, that is, a first radial side, and on the other radial side, that is, a second radial side. The shield has: The front end face is oriented toward the upstream side of the axis, on one side (i.e., the upstream side) and the other side (i.e., the downstream side) in the axial direction in which the axis extends; a rear end surface facing downstream of the axis; a first circumferential end surface, facing the first circumferential side, between one side, i.e., a first circumferential side, and the other side, i.e., a second circumferential side, along the circumference relative to the axis; a second circumferential end surface facing the second circumferential side; an anti-air road surface, facing the first radial side; and an air path, toward the radial second side, The manufacturing auxiliary device for the fixed blade segment includes: a base plate disposed in a state where the plurality of stationary blades are arranged in the circumferential direction and capable of contacting the front end face or the rear end face of the shroud of each of the plurality of stationary blades; a radial positioning block fixed on the base plate and having an arc surface extending along the circumferential direction so as to be able to contact the anti-air road surface in the shroud of each of the plurality of fixed blades placed on the base plate; a radial pressing device mounted on the base plate, for pressing the plurality of fixed blades placed on the base plate toward the radial positioning block in the radial direction; a circumferential positioning block fixed to the base plate and capable of contacting the first circumferential end surface of the shroud of a first end stationary blade, which is a stationary blade disposed closest to the first circumferential side among the plurality of stationary blades mounted on the base plate; a circumferential pushing device mounted on the base plate, for pushing a second end fixed blade, which is located closest to the second circumferential side, among the plurality of fixed blades mounted on the base plate, toward the circumferential positioning block in the circumferential direction; and The axial direction pressing device is mounted on the base plate and presses the plurality of stationary blades placed on the base plate toward the base plate.

10. The manufacturing assisting device for a stationary blade segment according to claim 9, further comprising: The circumference measurement reference block is fixed to the base plate and faces the second circumferential end surface of the second end stationary blade among the plurality of stationary blades placed on the base plate with a gap in the circumferential direction.

11. The manufacturing assisting device for a stationary blade segment according to claim 10, further comprising: The measuring instrument has a longitudinal direction, and a thickness perpendicular to the longitudinal direction changes according to a position in the longitudinal direction.

12. A method for manufacturing a fixed blade segment, wherein: The stationary blade segment comprises: a plurality of stationary blades arranged in a circumferential direction relative to the axis, The plurality of fixed blades each have: a blade body extending in a radial direction relative to the axis to form a blade shape; and A shroud is provided at an end portion of the blade body on the first radial side, on one radial side, that is, a first radial side, and on the other radial side, that is, a second radial side. The shield has: The front end face is oriented toward the upstream side of the axis, on one side (i.e., the upstream side) and the other side (i.e., the downstream side) in the axial direction in which the axis extends; a rear end surface facing downstream of the axis; a first circumferential end surface, facing the first circumferential side, between one side, i.e., a first circumferential side, and the other side, i.e., a second circumferential side, along the circumference relative to the axis; a second circumferential end surface facing the second circumferential side; an anti-air road surface, facing the first radial side; and an air path, toward the radial second side, In the manufacturing method of the stationary blade segment, the following is performed: a stationary blade manufacturing step of manufacturing the plurality of stationary blades; a stationary blade arranging step of arranging the plurality of stationary blades in the circumferential direction and temporarily positioning each of the plurality of stationary blades in a state in which the shrouds of two stationary blades adjacent in the circumferential direction contact each other so that the circumferential position, the radial position, and the axial position of each of the plurality of stationary blades are at a target position; a connecting step of connecting the plurality of stationary blades to each other in a state where the plurality of stationary blades are temporarily positioned; and a temporary positioning releasing step of releasing the temporary positioning of the plurality of fixed blades after the connecting step; In the above-mentioned stationary blade manufacturing process, The anti-air path surface in the shield of each of the multiple fixed blades has a plurality of planes arranged continuously along the circumference from the position of the first circumferential end face to the position of the second circumferential end face, and the fixed blades are manufactured in such a way that the ridge line formed at the intersection of two adjacent planes in the circumferential direction among the multiple planes is located on an imaginary circle centered on the axis.

13. The method for manufacturing a stationary blade segment according to claim 12, further comprising: a belt manufacturing step of manufacturing a connecting belt for connecting the plurality of stationary blades to each other while the plurality of stationary blades are arranged in the circumferential direction; In the connecting step, in a state where the plurality of stationary blades are temporarily positioned, the ridge line of each of the plurality of stationary blades is brought into contact with the connecting band, thereby connecting each of the plurality of stationary blades to the connecting band.

14. The method for manufacturing a stationary blade segment according to claim 12 or 13, further comprising: a circumference measuring step of measuring, with the plurality of stationary blades temporarily positioned, a circumferential length, i.e., a circumferential length, from the first circumferential end surface of the shroud in the first end stationary blade, which is a stationary blade closest to the first circumferential side among the plurality of stationary blades, to the second circumferential end surface of the shroud in the second end stationary blade, which is a stationary blade closest to the second circumferential side among the plurality of stationary blades; and The joining surface processing step is to cut at least one of the first circumferential end surface of the first end fixing blade and the second circumferential end surface of the second end fixing blade so that the circumference becomes a target circumference after the temporary positioning release step.

15. The method for manufacturing a stationary blade segment according to claim 12 or 13, wherein: In the fixed blade configuration process, a manufacturing auxiliary device for the fixed blade segment described in any one of claims 9 to 11 is used to temporarily position the multiple fixed blades in such a manner that the circumferential position of each of the multiple fixed blades becomes a target position, the radial position becomes a target position, and the axial position becomes a target position.

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