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CN-117321289-B - Stator vane segment, gas turbine, and method for manufacturing stator vane segment

CN117321289BCN 117321289 BCN117321289 BCN 117321289BCN-117321289-B

Abstract

The vane segment includes a 1 st vane, a 2 nd vane, and a bonding tool for bonding the 1 st vane and the 2 nd vane. The 1 st shroud of the 1 st stator vane has a 1 st gas passage surface and a 1 st projection projecting to the opposite side of the flow passage at the 1 st end of the 1 st shroud. The 2 nd shroud of the 2 nd stator blade has a 2 nd gas passage surface, a 2 nd protrusion protruding to the opposite side of the flow path at the 1 st end of the 2 nd shroud, and a 3 rd protrusion protruding to the opposite side of the flow path at the 2 nd end of the 2 nd shroud and coupled to the 1 st protrusion by a coupling tool. In the region where the 1 st stationary blade and the 2 nd stationary blade are juxtaposed with the 1 st projection in the side direction, the distance between the surface farthest from the 1 st gas path surface and the 1 st gas path surface among the surfaces of the 2 nd end portion of the 1 st shroud is shorter than the distance between the surface farthest from the 2 nd gas path surface and the 2 nd gas path surface among the surfaces of the 2 nd projection.

Inventors

  • MAEDA KENGO
  • OTOMO HIROYUKI
  • Shi Liangshi

Assignees

  • 三菱重工业株式会社

Dates

Publication Date
20260508
Application Date
20220511
Priority Date
20210531

Claims (10)

  1. 1. A stator vane segment is provided with: 1 st stationary blade; A2 nd stationary blade arranged in parallel with the 1 st stationary blade, and A bonding tool for bonding the 1 st stationary blade and the 2 nd stationary blade, The 2 nd stationary blade is located on the 1 st side of the 1 st and 2 nd sides in a side direction in which the 1 st stationary blade and the 2 nd stationary blade are arranged side by side with respect to the 1 st stationary blade, The 1 st stationary blade and the 2 nd stationary blade each have: A vane body disposed in the combustion gas flow path and having a vane shape, and A shroud provided at an end of the blade body in a blade height direction, The 1 st shroud, which is a shroud of the 1 st stator blade, includes: A1 st gas passage surface facing the combustion gas flow path, and A1 st projection which is located at the 1 st end of the 1 st shroud and projects toward the opposite side of the combustion gas flow path, i.e., the opposite side of the flow path, The shroud of the 2 nd stator blade, namely, the 2 nd shroud has: A2 nd gas passage surface facing the combustion gas passage; a2 nd protrusion part located at the 1 st end part of the 2 nd shield, i.e. the 1 st end part, and protruding to the opposite side of the flow path, and A 3 rd protruding portion which is located at the 2 nd end portion of the 2 nd shield, i.e., the 2 nd end portion, protrudes to the opposite side of the flow path, and is coupled to the 1 st protruding portion by the coupling tool, In a region juxtaposed in the side direction with the 1 st projection, a distance between a surface farthest from the 1 st gas path surface among surfaces of 2 nd end portions, i.e., 2 nd end portions, of the 1 st shroud and the 1 st gas path surface is shorter than a distance between a surface farthest from the 2 nd gas path surface among surfaces of the 2 nd projection and the 2 nd gas path surface.
  2. 2. The vane segment of claim 1, wherein, The 1 st shroud includes a 1 st shroud body having the 1 st gas passage surface, and a 1 st peripheral wall provided along a peripheral edge of the 1 st shroud body and protruding to a side opposite to the flow passage to form a cavity into which cooling air flows, The 2 nd shield has a 2 nd shield body having the 2 nd gas passage surface, and a 2 nd peripheral wall provided along a peripheral edge of the 2 nd shield body and protruding to a side opposite to the flow passage to form a cavity into which cooling air flows, The 1 st peripheral wall and the 2 nd peripheral wall each have: A front wall facing an upstream side, which is a side where the combustion gas flows in the combustion gas flow path; a rear wall facing a downstream side, which is a side through which the combustion gas flows in the combustion gas flow path; A1 st side wall connecting the front wall and the rear wall at the 1 st side relative to the blade body, and A2 nd side wall connecting the front wall and the rear wall at the 2 nd side with respect to the blade body, The 1 st projection projects from the 1 st side wall of the 1 st peripheral wall toward the opposite side of the flow path, The 2 nd protruding portion protrudes from the 1 st side wall of the 2 nd peripheral wall to the opposite side of the flow path, The 3 rd protruding portion protrudes from the 2 nd side wall of the 2 nd peripheral wall toward the flow path opposite side.
  3. 3. The stationary blade segment according to claim 1 or 2, wherein, The 1 st projection and the 2 nd projection have the same outer shape.
  4. 4. The stationary blade segment according to claim 1 or 2, wherein, The 1 st projection has a hole through which the bonding tool passes, In a region juxtaposed in the side direction with the 1 st projection, the surface farthest from the 1 st gas passage surface among surfaces of the 2 nd end portion of the 1 st shroud is closer to the 1 st gas passage surface than the surface closest to the 1 st gas passage surface among inner peripheral surfaces of the holes.
  5. 5. The stationary blade segment according to claim 1 or 2, wherein, The 1 st shroud and the 2 nd shroud are outer shrouds located on the outer peripheral side of the stator blade segment in the blade height direction, and the 1 st projection, the 2 nd projection, and the 3 rd projection project toward the outer peripheral side.
  6. 6. The stationary blade segment according to claim 1 or 2, wherein, The 1 st shroud and the 2 nd shroud are inner shrouds located on the inner peripheral side of the stator blade segment in the blade height direction, and the 1 st projection, the 2 nd projection, and the 3 rd projection project toward the inner peripheral side.
  7. 7. The stationary blade segment according to claim 1 or 2, wherein, The 1 st shroud has: A 1 st cooling passage including a portion extending along the 1 st end of the 1 st shroud and through which cooling air flows, and A2 nd cooling passage including a portion extending along the 2 nd end of the 1 st shroud and through which cooling air flows, The 2 nd shield has: A3 rd cooling passage including a portion extending along the 1 st end of the 2 nd shroud and through which cooling air flows, and A 4 th cooling passage including a portion extending along the 2 nd end portion of the 2 nd shroud and through which cooling air flows, The flow rate of the cooling air flowing through the 2 nd cooling passage is greater than the flow rate of the cooling air flowing through the 1 st cooling passage, The flow rate of the cooling air flowing through the 3 rd cooling passage is greater than the flow rate of the cooling air flowing through the 4 th cooling passage.
  8. 8. The vane segment of claim 7, wherein, The 1 st shroud has: a1 st exhaust port for exhausting the cooling air flowing through the 1 st cooling passage to the outside of the 1 st shield, and A 2 nd exhaust port for exhausting the cooling air flowing through the 2 nd cooling passage to the outside of the 1 st shroud, The 2 nd shield has: a3 rd exhaust port for exhausting the cooling air flowing through the 3 rd cooling passage to the outside of the 2 nd shield, and A4 th exhaust port for exhausting the cooling air flowing through the 4 th cooling passage to the outside of the 2 nd shroud, The opening area of the 2 nd exhaust port is larger than the opening area of the 1 st exhaust port, The opening area of the 3 rd exhaust port is larger than the opening area of the 4 th exhaust port.
  9. 9. A gas turbine, comprising: the vane segment of claim 1 or 2; a rotor rotatable about an axis; A housing covering the outer peripheral side of the rotor, and A burner for generating combustion gas by combustion of fuel and delivering the combustion gas into the housing, The stationary blade segments are provided on the inner peripheral side of the casing.
  10. 10. In a method for manufacturing a stator blade segment in which a 1 st stator blade and a2 nd stator blade are joined by a joining tool, the 2 nd stator blade is located on the 1 st side of a 1 st side and a2 nd side in a side direction in which the 1 st stator blade and the 2 nd stator blade are arranged side by side with respect to the 1 st stator blade, in the method, A1 st stator blade member and a2 nd stator blade member are prepared, each of the 1 st stator blade member and the 2 nd stator blade member having a blade body arranged in a combustion gas flow path and having a blade shape, and a shroud provided at an end of the blade body in a blade height direction, the shroud including a gas flow path surface facing the combustion gas flow path, a protrusion protruding toward a flow path opposite side, which is an end 1 of the shroud on the 1 st side, and protruding toward a side opposite to the combustion gas flow path, which is an end 2 of the shroud on the 2 nd side, Removing at least a part of the protruding portion of the 2 nd end portion of the 1 st stationary blade member to form the 1 st stationary blade from the 1 st stationary blade member, The 2 nd stationary blade is formed by the 2 nd stationary blade member while leaving the protruding portion of the 1 st end portion of the 2 nd stationary blade member, The protruding portion of the 1 st end portion of the 1 st stationary blade and the protruding portion of the 2 nd end portion of the 2 nd stationary blade are joined by a joining tool.

Description

Stator vane segment, gas turbine, and method for manufacturing stator vane segment Technical Field The invention relates to a stator blade segment, a gas turbine, and a method for manufacturing the stator blade segment. The present application claims priority from 2021, 5 and 31 in japanese patent application No. 2021-091137, invented in japan, and applies the content thereof. Background There is known a vane segment in which two vanes arranged in a circumferential direction are integrated in a gas turbine. For example, patent documents 1 and 2 disclose vane segments in which a flange provided at a rear end portion of a 1 st vane and a flange provided at a front end portion of a2 nd vane are coupled by bolts so as to integrate the 1 st vane (the belly side vane) and the 2 nd vane (the back side vane) which are arranged in parallel in the circumferential direction. Prior art literature Patent literature Patent document 1 Japanese patent laid-open No. 11-125102 Patent document 2 Japanese patent application laid-open No. 2001-254605 Disclosure of Invention Problems to be solved by the invention However, in the vane segments, depending on the use environment or operating conditions of the gas turbine, large thermal stresses may act. In this case, the life of the gas turbine may be shortened. The present invention has been made to solve the above-described problems, and an object thereof is to provide a stator vane segment, a gas turbine, and a method for manufacturing a stator vane segment, which can reduce thermal stress. Means for solving the problems In order to solve the above problems, a stator vane segment according to the present invention includes a1 st stator vane, a 2 nd stator vane arranged in parallel with the 1 st stator vane, and a bonding tool for bonding the 1 st stator vane and the 2 nd stator vane. The 2 nd stator blade is located on the 1 st side out of the 1 st side and the 2 nd side in a side direction in which the 1 st stator blade and the 2 nd stator blade are arranged side by side with respect to the 1 st stator blade. The 1 st stationary blade and the 2 nd stationary blade each have a blade body disposed in the combustion gas flow path and having a blade shape, and a shroud provided at an end of the blade body in a blade height direction. The 1 st shroud, which is a shroud of the 1 st stator vane, has a1 st gas passage surface facing the combustion gas passage, and a1 st protrusion portion which is located at a1 st end portion, which is an end portion on the 1 st side of the 1 st shroud, and protrudes to a side opposite to the combustion gas passage, which is a side opposite to the passage. The shroud of the 2 nd stationary blade, namely, the 2 nd shroud, has a 2 nd gas passage surface facing the combustion gas flow path, a 2 nd protrusion portion located at the 1 st end portion of the 2 nd shroud, namely, the 1 st end portion, and protruding toward the opposite side of the flow path, and a 3 rd protrusion portion located at the 2 nd end portion of the 2 nd shroud, namely, the 2 nd end portion, and protruding toward the opposite side of the flow path, and is coupled to the 1 st protrusion portion by the coupling tool. In a region juxtaposed in the side direction with the 1 st projection, a distance between a surface farthest from the 1 st gas path surface among surfaces of 2 nd end portions, i.e., 2 nd end portions, of the 1 st shroud and the 1 st gas path surface is shorter than a distance between a surface farthest from the 2 nd gas path surface among surfaces of the 2 nd projection and the 2 nd gas path surface. In order to solve the above problems, a gas turbine according to the present invention includes a stator vane segment, a rotor rotatable about an axis, a casing covering an outer peripheral side of the rotor, and a combustor for generating combustion gas by combustion of fuel and feeding the combustion gas into the casing. The stationary blade segments are provided on the inner peripheral side of the casing. The stator blade segment includes a1 st stator blade, a 2 nd stator blade arranged in parallel with the 1 st stator blade, and a bonding tool for bonding the 1 st stator blade and the 2 nd stator blade. The 2 nd stator blade is located on the 1 st side out of the 1 st side and the 2 nd side in a side direction in which the 1 st stator blade and the 2 nd stator blade are arranged side by side with respect to the 1 st stator blade. The 1 st stationary blade and the 2 nd stationary blade each have a blade body disposed in the combustion gas flow path and having a blade shape, and a shroud provided at an end of the blade body in a blade height direction. The 1 st shroud, which is a shroud of the 1 st stator vane, has a1 st gas passage surface facing the combustion gas passage, and a1 st protrusion portion which is located at a1 st end portion, which is an end portion on the 1 st side of the 1 st shroud, and protrudes to a side opposite to the combustion gas passage, which is