Gas turbine and stator blade mounting method

Abstract

This appropriately suppresses the shortening of component fatigue life caused by the relatively high temperature of the stator vanes during operation. [Solution] A gas turbine is provided comprising: an inner casing 50 formed in a cylindrical shape extending along the axis and positioned on the outer circumference side of the turbine with respect to the axis; a stator vane segment 80 having stator vanes 81 arranged at multiple locations in the circumferential direction around the axis and positioned inside the inner casing 50; and a stator vane holding mechanism 90 formed in an annular shape around the axis and positioned between the inner casing 50 and the stator vane segment 80 in the radial direction RD perpendicular to the axis, and holding the stator vane segment 80 in a position relative to the inner casing 50, wherein the stator vane holding mechanism 90 is divided in the circumferential direction and has a plurality of stator vane holding members 91 formed of a metal material.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to a gas turbine and a stationary blade mounting method.

BACKGROUND ART

[0002] Conventionally, gas turbines used as aircraft engines and the like are known (see, for example, Patent Document 1 and Patent Document 2). Patent Document 1 discloses a structure in which a pair of protrusions protruding radially outward from an outer shroud of a stationary blade are fixed to the inner peripheral surface of a turbine casing. Further, Patent Document 2 discloses that the mounting of a plurality of blades to a ring is facilitated by inserting a blade mounting tab into an opening formed only in a part of the annularly formed ring and then moving the blade in the circumferential direction.

PRIOR ART DOCUMENTS

PATENT DOCUMENTS

[0003]

PATENT DOCUMENT 1

PATENT DOCUMENT 2

SUMMARY OF THE INVENTION

PROBLEMS TO BE SOLVED BY THE INVENTION

[0004] During operation of the gas turbine, the blade surface of the structure including the stationary blade (hereinafter referred to as the stationary blade segment) becomes relatively hot due to combustion gas, while the base end portion of the stationary blade segment fixed to the casing becomes relatively low in temperature. As a result, thermal stress corresponding to the temperature difference is generated in the stationary blade segment, which shortens the fatigue life of the stationary blade segment.

[0005] In the structure disclosed in Patent Document 1, since the stationary blade segment is directly attached to the turbine casing, a large temperature difference occurs in the stationary blade segment, which may shorten the fatigue life of the stationary blade segment.

[0006] The structure disclosed in Patent Document 2 involves inserting stator vane segments into a ring, and since multiple stator vane segments inserted into the ring are attached to the turbine casing, large temperature differences are less likely to occur in the stator vane segments compared to the structure in Patent Document 1. However, since the ring in Patent Document 1 is a single annular member, the thermal stress generated in the ring during gas turbine operation can become large, potentially shortening the fatigue life of the ring.

[0007] This disclosure has been made in view of these circumstances and aims to provide a gas turbine and a method for mounting stationary vanes that can appropriately suppress the shortening of the fatigue life of components caused by the stationary vanes becoming relatively hot during operation. [Means for solving the problem]

[0008] To solve the above problems, a gas turbine according to one aspect of the present disclosure comprises: a compressor having a plurality of compression blades that rotate around an axis and compressing external air to generate compressed air; a combustor that burns the compressed air generated by the compressor together with fuel to generate combustion gas; a turbine having a plurality of blades that rotate around the axis and driven by the combustion gas generated by the combustor; a rotating shaft connecting the compressor and the turbine and extending along the axis and rotating in the rotational direction; a casing formed in a cylindrical shape extending along the axis and positioned on the outer circumference side of the turbine with respect to the axis; stator blade segments having stator blades arranged at a plurality of locations in the circumferential direction around the axis and positioned inside the casing; and a stator blade holding mechanism formed in an annular shape around the axis and positioned between the casing and the stator blade segments in the radial direction perpendicular to the axis, holding the stator blade segments in a positioned state relative to the casing, wherein the stator blade holding mechanism has a plurality of stator blade holding members that are divided in the circumferential direction and formed of a metal material.

[0009] A method for attaching stationary blades according to one aspect of the present disclosure is a method for attaching stationary blades to a casing of a gas turbine, wherein the gas turbine has a plurality of compression blades that rotate around an axis and a compressor that compresses external air to generate compressed air, a combustor that burns the compressed air generated by the compressor together with fuel to generate combustion gas, a turbine that has a plurality of compression blades that rotate around an axis and is driven by the combustion gas generated by the combustor, a rotating shaft that connects the compressor and the turbine and is formed to extend along the axis and rotates in the rotational direction, and a cylindrical shape that extends along the axis The turbine comprises a casing positioned on the outer circumference side of the turbine with respect to the axis, stator vane segments having stator vanes arranged at multiple locations in the circumferential direction around the axis and positioned inside the casing, and a stator vane holding mechanism that holds the stator vane segments in a positioned state relative to the casing, wherein the stator vane holding mechanism has a plurality of stator vane holding members that are divided in the circumferential direction and formed of a metal material, and comprises an attachment step of attaching the stator vane holding members to the stator vane segments, and a fixing step of fixing the stator vane holding members attached to the stator vane segments to the casing. [Effects of the Invention]

[0010] According to this disclosure, it is possible to provide a gas turbine and a method for mounting stator blades that can appropriately suppress the shortening of the fatigue life of components caused by the stator blades becoming relatively hot during operation. [Brief explanation of the drawing]

[0011] [Figure 1] This is a longitudinal cross-sectional view showing a gas turbine according to the first embodiment of this disclosure. [Figure 2] This is a magnified view of section A of the gas turbine shown in Figure 1. [Figure 3] Figure 2 is a perspective view showing the stator vane retaining member removed from the stator vane segment. [Figure 4] This is a flowchart showing the method for attaching the stationary vanes. [Figure 5] This is a partially enlarged view of a gas turbine according to a second embodiment of this disclosure. [Figure 6] Figure 4 is a perspective view showing the stator vane retaining member removed from the stator vane segment. [Modes for carrying out the invention]

[0012] [First Embodiment] Hereinafter, a gas turbine 100 according to the first embodiment of this disclosure will be described with reference to the drawings. Figure 1 is a longitudinal cross-sectional view showing a gas turbine 100 according to one embodiment of this disclosure. Figure 2 is a partially enlarged view of part A of the gas turbine 100 shown in Figure 1. Figure 3 is a perspective view showing the stator blade holding member 91 shown in Figure 2 removed from the stator blade segment 80. The gas turbine 100 of this embodiment is, for example, a turbofan engine used as a thrust generator for an aircraft.

[0013] As shown in Figures 1 and 2, the gas turbine 100 comprises a compressor 10, a combustor 20, a turbine 30, a supercharging fan 40, an inner casing 50, an outer casing 60, a high-pressure rotating shaft 70A, a low-pressure rotating shaft 70B, a stator vane segment 80, and a stator vane holding mechanism 90.

[0014] The compressor 10 is a device that generates compressed air by compressing external air EA flowing in from the front in the direction of the aircraft's movement. The compressor 10 has a plurality of rotor blades (compression rotor blades) 11 that rotate around axis X and are connected to a high-pressure rotating shaft 70A, and generates compressed air by passing the incoming external air EA through the plurality of rotor blades 11.

[0015] The combustor 20 is a device that burns compressed air produced by the compressor 10 together with fuel to generate high-temperature, high-pressure combustion gas CA. The combustor 20 supplies the high-temperature, high-pressure combustion gas CA to the turbine 30, thereby rotating the turbine 30 around axis X. Multiple combustors 20 are installed around axis X.

[0016] The turbine 30 is a device driven by the combustion gas CA generated by the combustor 20. The turbine 30 includes a high-pressure turbine 31, and a low-pressure turbine 32 disposed downstream of the high-pressure turbine 31 in the flow direction of the combustion gas CA. The high-pressure turbine 31 has a plurality of high-pressure turbine rotor blades 31a connected to the high-pressure rotating shaft 70A. The low-pressure turbine 32 has a plurality of low-pressure turbine rotor blades 32a connected to the low-pressure rotating shaft 70B.

[0017] The low-pressure turbine 32 includes a plurality of low-pressure turbine rotor blades 32a that rotate around the axis X, and a turbine disk 32b connected to the low-pressure turbine rotor blades 32a. The low-pressure turbine rotor blade 32a has a blade portion 32a1, and a platform portion 32a2 formed integrally with the blade portion 32a1. The blade portion 32a1 is connected to the turbine disk 32b attached to the low-pressure rotating shaft 70B via the platform portion 32a2.

[0018] By guiding the combustion gas CA to the turbine 30, the plurality of high-pressure turbine rotor blades 31a and the plurality of low-pressure turbine rotor blades 32a are driven to rotate around the axis X. The driving force that causes the high-pressure turbine rotor blades 31a to rotate around the axis X is transmitted to the compressor 10 via the high-pressure rotating shaft 70A. The compressor 10 generates compressed air by rotating the rotor blades 11 with the power obtained from the high-pressure turbine 31.

[0019] The booster fan 40 is a device that rotates around the axis X to supply external air EA to both the internal space of the inner casing 50 and the space between the inner casing 50 and the outer casing 60. The booster fan 40 is connected to the low-pressure turbine 32 via the low-pressure rotating shaft 70B. The booster fan 40 rotates around the axis X as driven by the low-pressure turbine 32, and guides the external air EA to the compressor 10.

[0020] The inner casing 50 is a member that is formed in a cylindrical shape extending along the axis X and is disposed on the outer peripheral side of the turbine 30 with respect to the axis X. The outer casing 60 is formed in a cylindrical shape extending along the axis X and is positioned on the outer circumference side of the inner casing 50 with respect to the axis X.

[0021] The high-pressure rotating shaft 70A is a cylindrical member that connects the compressor 10 and the high-pressure turbine 31 and extends along the axis X, and rotates in the rotational direction. The low-pressure rotating shaft 70B is a shaft-shaped member that connects the supercharging fan 40 and the low-pressure turbine 32 and extends along the axis X, and rotates in the rotational direction. The low-pressure rotating shaft 70B is inserted into the cylindrical high-pressure rotating shaft 70A and rotates independently of the high-pressure rotating shaft 70A.

[0022] The stator vane segment 80 is positioned upstream of the low-pressure turbine rotor blades 32a in the direction of combustion gas CA flow and comprises a stator vane 81, a shroud 82, an upstream flange (first flange) 83, and a downstream flange (first flange) 84, all of which are made of metal. The stator vane segment 80 is a structure in which multiple (four in the example shown in Figure 3) stator vanes 81, shrouds 82, upstream flanges 83, and downstream flanges 84 are assembled as a single unit. As shown in Figure 3, the stator vane segment 80 has a length L1 along the circumferential direction CD around the axis X.

[0023] The stationary vanes 81 are arranged at multiple locations in the circumferential direction around the axis X, and are also positioned inside the inner casing 50. The shroud 82 is a component to which the outer peripheral end of the radial direction RD of the stator vane 81 is attached, and which forms a flow path for the combustion gas CA extending along the axis X. The shrouds 82 of each of the multiple stator vane segments 80 are arranged in an annular shape around the axis X.

[0024] The upstream flange 83 is formed to protrude from the shroud 82 toward the outer circumference in the radial direction RD and toward the upstream side in the flow direction of the combustion gas CA. The downstream flange 84 is formed to protrude from the shroud 82 toward the outer circumference in the radial direction RD and toward the downstream side in the flow direction of the combustion gas CA. The upstream flange 83 and the downstream flange 84 are formed so that their tips protrude toward a direction away from each other in the axial direction AD along the axis X.

[0025] The stator vane holding mechanism 90 is formed in an annular shape around the axis X and is positioned between the inner casing 50 and the stator vane segment 80 in the radial direction RD perpendicular to the axis X. The stator vane holding mechanism 90 holds the stator vane segment 80 in a position relative to the inner casing 50. As shown in Figure 3, the stator vane holding mechanism 90 has a plurality of stator vane holding members 91 that are divided in the circumferential direction CD and are made of a metal material.

[0026] The stator vane retaining member 91 has a length L2 along the circumferential direction CD around the axis X. Preferably, the length L2 is set to 1 / 3 or less of the total length of the circumferential direction CD (the circumference of one turn). Also, the length L2 is set to 0.5 times or more the length L1 of the stator vane segment 80. In Figure 3, the length L2 is the same as the length L1, and one stator vane retaining member 91 holds one stator vane segment 80, but other embodiments are also possible. For example, the length L2 may be set to 2 times or more the length L1, so that one stator vane retaining member 91 holds two or more stator vane segments 80.

[0027] As shown in Figure 2, the stator vane retaining member 91 has an upstream retaining flange (second flange) 92, a downstream retaining flange (second flange) 93, an insertion flange (third flange) 94, and abutment flange (fourth flange) 95.

[0028] The upstream retaining flange 92 is formed to protrude toward the inner circumference in the radial direction RD and toward the downstream side in the flow direction of the combustion gas CA. The downstream retaining flange 93 is formed to protrude toward the inner circumference in the radial direction RD and toward the upstream side in the flow direction of the combustion gas CA. The upstream retaining flange 92 and the downstream retaining flange 93 are formed so that their tips protrude toward each other in the axial direction AD along the axis X.

[0029] As shown in Figure 2, the stator vane segment 80 is held by the stator vane holding member 91 by positioning the upstream flange 83 and downstream flange 84 of the stator vane segment 80 between the upstream holding flange 92 and the downstream holding flange 93 of the stator vane holding member 91 in the axial direction AD and engaging them together.

[0030] As shown in Figure 2, the inner casing 50 has a first groove 50a and a second groove 50b. The first groove 50a is formed so as to extend along the circumferential direction CD and into which the insertion flange 94 of the stator vane retaining member 91 is inserted. The second groove 50b is formed so as to extend along the circumferential direction CD and into which a fixing member 96 for fixing the abutment flange 95 of the stator vane retaining member 91 to the inner casing 50 is inserted. The stator vane retaining member 91 is fixed to the inner casing 50 with the insertion flange 94 inserted into the first groove 50a and the abutment flange 95 in contact with the fixing member 96 inserted into the second groove 50b. The fixing member 96 supports the axial load AD acting on the stator vane retaining member 91 when the combustion gas CA collides with the stator vane 81.

[0031] As shown in Figure 2, when a fluid pressure FPA due to combustion gas CA acts on the stator vane 81, a reaction force FPR1 from the stator vane retaining member 91 acts on the downstream flange 84 of the stator vane segment 80. In addition, a reaction force FPR2 from a fixing member 96 of the same size as the reaction force FPR1 acts on the stator vane retaining member 91.

[0032] When a moment is applied to the stator vane 81 by the fluid pressure FPA in a direction that rotates the stator vane segment 80 counterclockwise in Figure 2, a reaction force FPR6 acts from the inner casing 50 on the insertion flange 94 of the stator vane retaining member 91. Also, a reaction force FPR5 of the same size as the reaction force FPR5 acts on the upstream flange 83 of the stator vane segment 80 from the stator vane retaining member 91. Similarly, a reaction force FPR4 acts from the inner casing 50 on the abutment flange 95 of the stator vane retaining member 91. Also, a reaction force FPR3 of the same size as the reaction force FPR4 acts on the downstream flange 84 of the stator vane segment 80 from the stator vane retaining member 91.

[0033] As shown in Figure 2, the inner casing 50 supports a first moment about a rotation axis RX perpendicular to axis X that acts on the stator vane retaining member 91, which contacts it at a pair of support positions P11 and P12 spaced apart along the axial direction AD. The stator vane retaining member 91 also supports a second moment about a rotation axis RX that acts on the stator vane segment 80, which contacts it at a pair of second support positions P21 and P22 spaced apart along the axial direction AD.

[0034] Next, a method for attaching the stator vane segment 80 of this embodiment to the inner casing 50 will be described. Figure 4 is a flowchart showing the method for attaching the stator vane.

[0035] In step S101, the worker attaches the stator vane retaining member 91 to the stator vane segment 80. Starting from the state in which the stator vane retaining member 91 is removed from the stator vane segment 80 as shown in Figure 3, the worker moves the stator vane retaining member 91 toward the stator vane segment 80 along the circumferential direction CD, and inserts the upstream flange 83 and downstream flange 84 of the stator vane segment 80 between the upstream retaining flange 92 and downstream retaining flange 93 of the stator vane retaining member 91 in the axial direction AD along the axis X.

[0036] In step S102, the worker inserts the insertion flange 94 of the stator vane holding member 91 into the first groove 50a of the inner casing 50. In step S103, the worker inserts the fixing member 96 into the second groove 50b of the inner casing 50 so that the fixing member 96 contacts the abutment flange 95, as shown in Figure 2.

[0037] In steps S102 and S103, the worker fixes the stator vane retaining member 91 attached to the stator vane segment 80 to the inner casing 50. Thus, the stator vane segment 80 is attached to the inner casing 50.

[0038] The functions and effects of the gas turbine 100 of this embodiment, as described above, will now be explained. In the gas turbine 100 of this embodiment, the combustion gas CA generated in the combustor 20 imparts a torque to the rotor blades 11 of the turbine 30, causing the turbine 30 to rotate around the axis X. As the high-pressure turbine 31 rotates, the compressor 10, which is connected via the high-pressure rotating shaft 70A, generates compressed air that is supplied to the combustor 20.

[0039] The stator vane segments 80, each having a stator vane 81 positioned inside the inner casing 50, are arranged at multiple locations in the circumferential direction CD around the axis X. The stator vane segments 80 are held in a position relative to the inner casing 50 by a stator vane holding mechanism 90. Because the stator vane segments 80 are indirectly attached to the inner casing 50 via the stator vane holding mechanism 90, the heat from the combustion gas CA transmitted from the blade surface of the stator vane 81 is transferred from the stator vane segments 80 to the inner casing 50 via the stator vane holding mechanism 90. Therefore, compared to the case where the stator vane segments 80 are directly attached to the inner casing 50, the temperature difference generated in the stator vane segments 80 can be suppressed, and the fatigue life of the stator vane segments 80, which would be shortened due to thermal stress generated in the stator vane segments 80, can be appropriately prevented.

[0040] Furthermore, the stator vane holding mechanism 90, which holds the stator vane segment 80 to the inner casing 50, has a plurality of stator vane holding members 91 that are divided in the circumferential direction CD and are made of metal material. The metal stator vane holding members 91 are subject to deformation due to the heat transmitted from the stator vane segment 80, but are divided in the circumferential direction CD. Therefore, compared to the case where the stator vane holding mechanism 90 is a single annular member extending in the circumferential direction CD, the influence of thermal stress generated inside the member due to the heat transmitted from the stator vane segment 80 can be suppressed, and the fatigue life of the stator vane holding mechanism 90 can be appropriately prevented from being shortened.

[0041] In the gas turbine 100 of this embodiment, the stator blade segment 80 is held by the stator blade holding member 91 by arranging the upstream flange 83 and downstream flange 84 of the stator blade segment 80 between the upstream holding flange 92 and downstream holding flange 93 of the stator blade holding member 91. Since the contact area between the stator blade segment 80 and the stator blade holding member 91 is limited to a minimum, the amount of heat transfer between the stator blade segment 80 and the stator blade holding member 91 is suppressed, and the temperature difference between the stator blade segment 80 and the stator blade holding member 91 can be kept small.

[0042] Furthermore, the upstream flange 83 and downstream flange 84 of the stator vane segment 80 are formed to protrude in directions away from each other, both upstream and downstream in the flow direction of the combustion gas CA. Therefore, compared to the case where they are formed to move closer to each other, the length of the load transmission path from the upstream retaining flange 92 to the insertion flange 94 of the stator vane retaining member 91 can be shortened. This reduces the moment required to apply the reaction force FPR5 from the stator vane retaining member 91 to the stator vane segment 80, and thus the strength required of the stator vane retaining member 91 can be reduced.

[0043] According to the gas turbine 100 of this embodiment, the insertion flange 94 of the stator blade holding member 91 is inserted into the first groove 50a of the inner casing, and the fixing member 96 is inserted into the second groove 50b of the inner casing 50, thereby bringing the fixing member 96 into contact with the abutment flange 95 of the stator blade holding member 91, and thus the stator blade holding member 91 can be fixed to the inner casing 50.

[0044] [Second Embodiment] Next, a gas turbine according to the second embodiment of this disclosure will be described with reference to the drawings. This embodiment is a modification of the first embodiment and is the same as the first embodiment unless otherwise specifically described below, so the following description will be omitted.

[0045] The gas turbine of the second embodiment differs from the gas turbine of the first embodiment in the shape of the upstream flange 83 and downstream flange 84 of the stator blade segment 80, and the shape of the upstream retaining flange 92 and downstream retaining flange 93 of the stator blade retaining member 91. Figure 5 is a partially enlarged view of the gas turbine according to the second embodiment of this disclosure. Figure 6 is a perspective view showing the stator blade retaining member 91 shown in Figure 4 removed from the stator blade segment 80.

[0046] As shown in Figures 5 and 6, the upstream flange 83 and downstream flange 84 of this embodiment are formed so that their tips protrude toward each other in the axial direction AD along axis X. The upstream retaining flange 92 and downstream retaining flange 93 are formed so that their tips protrude toward each other in the axial direction AD along axis X.

[0047] As shown in Figure 5, the stator vane segment 80 is held by the stator vane holding member 91 by positioning the upstream holding flange 92 and downstream holding flange 93 of the stator vane holding member 91 between the upstream flange 83 and downstream flange 84 of the stator vane segment 80 in the axial direction AD and engaging them together.

[0048] As shown in Figure 5, the inner casing 50 has a first groove 50a and a second groove 50b. The first groove 50a is formed so as to extend along the circumferential direction CD and into which the insertion flange 94 of the stator vane retaining member 91 is inserted. The second groove 50b is formed so as to extend along the circumferential direction CD and into which a fixing member 96 for fixing the abutment flange 95 of the stator vane retaining member 91 to the inner casing 50 is inserted. The stator vane retaining member 91 is fixed to the inner casing 50 with the insertion flange 94 inserted into the first groove 50a and the abutment flange 95 in contact with the fixing member 96 inserted into the second groove 50b.

[0049] As shown in Figure 5, when a fluid pressure FPA due to combustion gas CA acts on the stator vane 81, a reaction force FPR1 from the stator vane retaining member 91 acts on the upstream flange 83 of the stator vane segment 80. In addition, a reaction force FPR2 from a fixing member 96 of the same size as the reaction force FPR1 acts on the stator vane retaining member 91.

[0050] When a moment is applied to the stator vane 81 by the fluid pressure FPA in a direction that rotates the stator vane segment 80 counterclockwise in Figure 5, a reaction force FPR6 acts from the inner casing 50 on the insertion flange 94 of the stator vane retaining member 91. Also, a reaction force FPR5 of the same size as the reaction force FPR5 acts on the upstream flange 83 of the stator vane segment 80 from the stator vane retaining member 91. Similarly, a reaction force FPR4 acts from the inner casing 50 on the abutment flange 95 of the stator vane retaining member 91. Also, a reaction force FPR3 of the same size as the reaction force FPR4 acts on the downstream flange 84 of the stator vane segment 80 from the stator vane retaining member 91.

[0051] As shown in Figure 5, the inner casing 50 supports a first moment about a rotation axis RX perpendicular to axis X that acts on the stator vane retaining member 91, which contacts it at a pair of support positions P11 and P12 spaced apart along the axial direction AD. The stator vane retaining member 91 also supports a second moment about a rotation axis RX that acts on the stator vane segment 80, which contacts it at a pair of second support positions P21 and P22 spaced apart along the axial direction AD.

[0052] Next, a method for attaching the stator vane segment 80 of this embodiment to the inner casing 50 will be described.

[0053] In step S101 of Figure 4, the worker attaches the stator vane retaining member 91 to the stator vane segment 80. Starting from the state in which the stator vane retaining member 91 is removed from the stator vane segment 80 as shown in Figure 6, the worker moves the stator vane retaining member 91 toward the stator vane segment 80 along the circumferential direction CD, and inserts the upstream retaining flange 92 and downstream retaining flange 93 of the stator vane retaining member 91 between the upstream flange 83 and the downstream flange 84 of the stator vane segment 80 in the axial direction AD along the axis X.

[0054] In step S102 of Figure 4, the worker inserts the insertion flange 94 of the stator vane holding member 91 into the first groove 50a of the inner casing 50. In step S103, the worker inserts the fixing member 96 into the second groove 50b of the inner casing 50 so that the fixing member 96 contacts the abutment flange 95, as shown in Figure 5.

[0055] In steps S102 and S103, the worker fixes the stator vane retaining member 91 attached to the stator vane segment 80 to the inner casing 50. Thus, the stator vane segment 80 is attached to the inner casing 50.

[0056] In this embodiment of the gas turbine, the stator blade segment 80 is held by the stator blade holding member 91 by arranging the upstream holding flange 92 and downstream holding flange 93 of the stator blade holding member 91 between the upstream flange 83 and downstream flange 84 of the stator blade segment 80. Since the contact area between the stator blade segment 80 and the stator blade holding member 91 is minimized, the amount of heat transfer between the stator blade segment 80 and the stator blade holding member 91 is suppressed, and the temperature difference between the stator blade segment 80 and the stator blade holding member 91 can be kept small.

[0057] Furthermore, the upstream flange 83 and downstream flange 84 of the stator vane segment 80 are formed to protrude toward each other in both the upstream and downstream directions of the combustion gas CA flow. Therefore, compared to the case where they are formed toward each other, the distance between the ends of the upstream flange 83 and downstream flange 84 in the axial direction AD is increased. This makes it possible to reduce the magnitude of the reaction forces FPR3 and FPR5 that the upstream flange 83 and downstream flange 84 receive from the stator vane holding member 91 in response to the moment generated in the stator vane segment 80 by the fluid pressure FPA that the stator vane 81 receives from the combustion gas CA.

[0058] Furthermore, the axial distance AD ​​between the upstream flange 83 and the downstream flange 84 at the connection point where they are connected to the shroud 82 becomes longer. This increases the distance from the central part of the axial distance AD, which is the hottest part of the stator vane segment 80, to the connection point between the upstream flange 83 and the downstream flange 84, thereby reducing the amount of heat transferred from the stator vane 81 to the upstream flange 83 and the downstream flange 84.

[0059] The gas turbines described in each of the embodiments above can be understood, for example, as follows. A gas turbine (100) according to a first aspect of this disclosure includes: a compressor (10) having a plurality of compression blades that rotate around an axis (X) and compressing external air to generate compressed air; a combustor (20) that burns the compressed air generated by the compressor together with fuel to generate combustion gas; a turbine (30) having a plurality of blades (32a) that rotate around the axis and driven by the combustion gas generated by the combustor; a rotating shaft (70A) that connects the compressor and the turbine and is formed to extend along the axis and rotates in the direction of rotation (RD); and a cylindrical shape extending along the axis. The turbine comprises a casing (50) positioned on the outer circumference of the turbine with respect to the axis, a stator vane segment (80) having stator vanes (81) positioned at multiple locations in the circumferential direction (CD) around the axis and positioned inside the casing, and a stator vane holding mechanism (90) formed in an annular shape around the axis and positioned between the casing and the stator vane segment in the radial direction perpendicular to the axis, holding the stator vane segment in a positioned state relative to the casing, wherein the stator vane holding mechanism has a plurality of stator vane holding members that are divided in the circumferential direction and formed of a metal material.

[0060] According to the gas turbine of the first aspect of this disclosure, the combustion gas generated in the combustor imparts a torque to the turbine blades that rotate around their axis, causing the turbine to rotate in the rotational direction. As the turbine rotates, a compressor connected via the rotating shaft generates compressed air that is supplied to the combustor.

[0061] The stator vane segments, each having a stator vane positioned inside the casing, are arranged at multiple locations in the circumferential direction around the axis. The stator vane segments are held in a position relative to the casing by a stator vane holding mechanism. Because the stator vane segments are indirectly attached to the casing via the stator vane holding mechanism, the heat from the combustion gas transmitted from the stator vane surface is transferred from the stator vane segments to the casing via the stator vane holding mechanism. Therefore, compared to the case where the stator vane segments are directly attached to the casing, the temperature difference generated in the stator vane segments can be suppressed, and the fatigue life of the stator vane segments, which would be shortened due to thermal stress generated in the stator vane segments, can be appropriately prevented.

[0062] Furthermore, the stator vane holding mechanism that holds the stator vane segments to the casing has multiple stator vane holding members that are divided in the circumferential direction and are made of metal material. The metal stator vane holding members deform due to the heat transmitted from the stator vane segments, but they are divided in the circumferential direction. Therefore, compared to the case where the stator vane holding mechanism is a single annular member extending in the circumferential direction, the effect of thermal stress generated inside the member due to the heat transmitted from the stator vane segments can be suppressed, and the fatigue life of the stator vane holding mechanism can be appropriately prevented from being shortened.

[0063] A gas turbine according to a second aspect of the present disclosure further comprises the following configurations in the first aspect: the casing supports a first moment about a rotation axis (RX) perpendicular to the axis acting on the stator vane retaining member that contacts it at a pair of first support positions (P11, P12) spaced apart along the axis; the stator vane retaining member supports a second moment about the rotation axis acting on the stator vane segments that contact it at a pair of second support positions (P21, P22) spaced apart along the axis; and a fixing member attached to the casing supports a load acting on the stator vane retaining member in the direction along the axis.

[0064] According to a gas turbine of a second aspect of this disclosure, the casing supports a first moment acting on a stator vane retaining member that contacts a pair of first support positions, and the stator vane retaining member supports a second moment acting on a stator vane segment that contacts a pair of second support positions, thereby maintaining the stator vane segment in a position relative to the casing.

[0065] A gas turbine according to a third aspect of the present disclosure further comprises the following configuration in the first aspect: The stator blade segment has a shroud (82) to which the radial outer end of the stator blade is attached and which forms a flow path for the combustion gas extending along the axis, and a pair of first flange portions (83, 84) formed to project radially outward from the shroud and away from each other on both the upstream and downstream sides in the direction of combustion gas flow, and the stator blade retaining member has a pair of second flange portions (92, 93) formed to project radially inward from each other and away from each other on both the upstream and downstream sides in the direction of combustion gas flow, and the stator blade segment is held by the stator blade retaining member by arranging the pair of first flange portions between the pair of second flange portions in the direction along the axis.

[0066] According to a gas turbine of a third aspect of this disclosure, the stator blade segment is held by the stator blade holding member by arranging a pair of first flange portions of the stator blade segment between a pair of second flange portions of the stator blade holding member. Since the contact area between the stator blade segment and the stator blade holding member is limited to a minimum, the amount of heat transfer between the stator blade segment and the stator blade holding member can be suppressed, and the temperature difference between the stator blade segment and the stator blade holding member can be kept small.

[0067] Furthermore, the pair of first flange portions of the stator vane segment are formed to protrude away from each other on both the upstream and downstream sides in the direction of combustion gas flow. As a result, the distance between the axial ends of the pair of first flange portions is shorter compared to when they are formed to protrude towards each other. This reduces the magnitude of the reaction force that the pair of first flange portions receive from the stator vane retaining member in response to the moment generated in the stator vane segment by the fluid pressure the stator vane receives from the combustion gas.

[0068] A gas turbine according to a fourth aspect of the present disclosure further comprises the following configuration in the first aspect: the stator blade segment has a shroud to which the radial outer end of the stator blade is attached and which forms a flow path for the combustion gas extending along the axis, and a pair of first flange portions formed to project from the shroud toward the radial outer side and toward each other toward both the upstream and downstream sides in the direction of combustion gas flow, and the stator blade retaining member has a pair of second flange portions formed to project toward the radial inner side and toward both the upstream and downstream sides in the direction of combustion gas flow toward each other, and the stator blade segment is held by the stator blade retaining member by arranging the pair of second flange portions between the pair of first flange portions in the axial direction along the axis.

[0069] According to a gas turbine of a fourth aspect of this disclosure, the stator blade segment is held by the stator blade holding member by arranging a pair of second flange portions of the stator blade holding member between a pair of first flange portions of the stator blade segment. Since the contact area between the stator blade segment and the stator blade holding member is limited to a minimum, the amount of heat transfer between the stator blade segment and the stator blade holding member can be suppressed, and the temperature difference between the stator blade segment and the stator blade holding member can be kept small.

[0070] Furthermore, the pair of first flange portions of the stator vane segment are formed to protrude toward each other on both the upstream and downstream sides in the combustion gas flow direction. As a result, the distance between the axial ends of the pair of first flange portions is longer compared to when they are formed toward each other. This increases the distance from the axial central portion of the stator vane segment, which is the hottest, to the first flange portions, thereby reducing the amount of heat transferred from the stator vane to the pair of first flange portions.

[0071] A gas turbine according to a fifth aspect of the present disclosure further comprises the following configuration in the third or fourth aspect: The stator blade retaining member has a third flange portion (94) protruding upstream in the direction of combustion gas flow and a fourth flange portion (95) protruding downstream in the direction of combustion gas flow; the casing has a first groove portion (50a) into which the third flange portion is inserted and which extends along the circumferential direction, and a second groove portion (50b) into which a fixing member (96) for fixing the fourth flange portion to the casing is inserted and which extends along the circumferential direction; the stator blade retaining member is fixed to the casing with the third flange portion inserted into the first groove and the fourth flange portion in contact with the fixing member inserted into the second groove.

[0072] According to the fifth aspect of this disclosure, the stator blade retaining member can be fixed to the casing by inserting the third flange portion of the stator blade retaining member into the first groove portion of the casing and inserting the fixing member into the second groove portion of the casing, thereby bringing the fixing member into contact with the fourth flange portion of the stator blade retaining member.

[0073] In the gas turbine according to the sixth aspect of this disclosure, the second circumferential length (L2) of the stator blade holding member is set to be 0.5 times or more the first circumferential length (L1) of the stator blade segment.

[0074] According to the gas turbine of the sixth aspect of this disclosure, when the second length is set to 0.5 times or more and 1.0 times or less the first length, the circumferential length of the stator blade retaining member relative to the stator blade segment is shortened, which suppresses the widening of the gap between a pair of circumferentially adjacent stator blade retaining members due to deformation of the stator blade retaining member caused by the heat of the combustion gas, thereby reducing the sealing performance of the combustion gas. Furthermore, when the second length is set to 1 time or more the first length, the number of stator blade retaining members required for the gas turbine can be reduced, thereby reducing manufacturing costs and assembly man-hours.

[0075] A seventh aspect of the present disclosure is a method for attaching stationary blades to a casing of a gas turbine, wherein the gas turbine includes a compressor having a plurality of compression blades that rotate around an axis and compressing external air to generate compressed air, a combustor that burns the compressed air generated by the compressor together with fuel to generate combustion gas, a turbine having a plurality of compression blades that rotate around an axis and driven by the combustion gas generated by the combustor, a rotating shaft that connects the compressor and the turbine and is formed to extend along the axis and rotates in the rotational direction, and a cylindrical shape extending along the axis and front The turbine comprises a casing positioned on the outer circumference side of the turbine with respect to its axis, stator vane segments having stator vanes positioned at multiple locations in the circumferential direction around the axis and positioned inside the casing, and a stator vane holding mechanism that holds the stator vane segments in a positioned state relative to the casing, wherein the stator vane holding mechanism has a plurality of stator vane holding members that are divided in the circumferential direction and formed of a metal material, and comprises an attachment step (S101) of attaching the stator vane holding members to the stator vane segments, and a fixing step (S102, S103) of fixing the stator vane holding members attached to the stator vane segments to the casing.

[0076] According to the stator vane mounting method of the seventh aspect of this disclosure, stator vane segments having stator vanes arranged inside the casing are arranged at multiple locations in the circumferential direction around the axis. The stator vane segments are held in a position relative to the casing by a stator vane holding mechanism. Since the stator vane segments are indirectly attached to the casing via the stator vane holding mechanism, the heat of the combustion gas transmitted from the blade surface of the stator vane is transmitted from the stator vane segments to the casing via the stator vane holding mechanism. Therefore, compared to the case where the stator vane segments are directly attached to the casing, it is possible to suppress the temperature difference generated in the stator vane segments and appropriately prevent the fatigue life of the stator vane segments from being shortened due to thermal stress generated in the stator vane segments.

[0077] Furthermore, the stator vane holding mechanism that holds the stator vane segments to the casing has multiple stator vane holding members that are divided in the circumferential direction and are made of metal material. The metal stator vane holding members deform due to the heat transmitted from the stator vane segments, but they are divided in the circumferential direction. Therefore, compared to the case where the stator vane holding mechanism is a single annular member extending in the circumferential direction, the effect of thermal stress generated inside the member due to the heat transmitted from the stator vane segments can be suppressed, and the fatigue life of the stator vane holding mechanism can be appropriately prevented from being shortened.

[0078] A stator vane mounting method according to an eighth aspect of the present disclosure further comprises the following configuration in a seventh aspect: the casing supports a first moment about a rotation axis perpendicular to the axis acting on the stator vane retaining member that contacts it at a pair of first support positions spaced apart along the axis; the stator vane retaining member supports a second moment about the rotation axis acting on the stator vane segment that contacts it at a pair of second support positions spaced apart along the axis; and a fixing member attached to the casing supports a load acting on the stator vane retaining member in a direction along the axis.

[0079] According to the stator vane mounting method of the eighth aspect of this disclosure, the casing supports a first moment acting on stator vane holding members that contact a pair of first support positions, and the stator vane holding members support a second moment acting on stator vane segments that contact a pair of second support positions, thereby maintaining the stator vane segments in a position relative to the casing.

[0080] A stator vane mounting method according to a ninth aspect of the present disclosure further comprises the following configuration in a seventh aspect: The stator vane segment has a shroud to which the radial outer end of the stator vane is attached and which forms a flow path for the combustion gas extending along the axis, and a pair of first flange portions formed to project radially outward from the shroud and toward each other in both the upstream and downstream directions in the flow direction of the combustion gas; the stator vane retaining member has a pair of second flange portions formed to project radially inward from the inner circumference and toward each other in both the upstream and downstream directions in the flow direction of the combustion gas; and the mounting step involves attaching the stator vane retaining member to the stator vane segment by inserting a pair of first flange portions between a pair of second flange portions in a direction along the axis.

[0081] According to the ninth aspect of the present disclosure, the stator vane mounting method is held by the stator vane holding member by arranging a pair of first flange portions of the stator vane segment between a pair of second flange portions of the stator vane holding member. Since the contact area between the stator vane segment and the stator vane holding member is minimized, the amount of heat transfer between the stator vane segment and the stator vane holding member is suppressed, and the temperature difference between the stator vane segment and the stator vane holding member can be kept small.

[0082] Furthermore, the pair of first flange portions of the stator vane segment are formed to protrude away from each other on both the upstream and downstream sides in the direction of combustion gas flow. As a result, the distance between the axial ends of the pair of first flange portions is shorter compared to when they are formed to protrude towards each other. This reduces the magnitude of the reaction force that the pair of first flange portions receive from the stator vane retaining member in response to the moment generated in the stator vane segment by the fluid pressure the stator vane receives from the combustion gas.

[0083] A stator vane mounting method according to a tenth aspect of the present disclosure further comprises the following configuration in a seventh aspect: The stator vane segment has a shroud to which the radial outer end of the stator vane is attached and which forms a flow path for the combustion gas extending along the axis, and a pair of first flange portions formed to project from the shroud toward the radial outer circumferential side and toward each other toward both the upstream and downstream sides in the direction of combustion gas flow, and the stator vane retaining member has a pair of second flange portions formed to project toward the radial inner circumferential side and toward both the upstream and downstream sides in the direction of combustion gas flow toward each other, and the mounting step is to attach the stator vane retaining member to the stator vane segment by inserting the pair of second flange portions between the pair of first flange portions in a direction along the axis.

[0084] According to the 10th aspect of the present disclosure, the stator vane mounting method is held by the stator vane holding member by arranging a pair of second flange portions of the stator vane holding member between a pair of first flange portions of the stator vane segment. Since the contact area between the stator vane segment and the stator vane holding member is minimized, the amount of heat transfer between the stator vane segment and the stator vane holding member is suppressed, and the temperature difference between the stator vane segment and the stator vane holding member can be kept small.

[0085] Furthermore, the pair of first flange portions of the stator vane segment are formed to protrude toward each other on both the upstream and downstream sides in the combustion gas flow direction. As a result, the distance between the axial ends of the pair of first flange portions is longer compared to when they are formed toward each other. This increases the distance from the axial central portion of the stator vane segment, which is the hottest, to the first flange portions, thereby reducing the amount of heat transferred from the stator vane to the pair of first flange portions.

[0086] A stator vane mounting method according to the 11th aspect of this disclosure further comprises the following configuration in the 9th or 10th aspect: The stator vane holding member has a third flange portion projecting toward the upstream side in the flow direction of the combustion gas and a fourth flange portion projecting toward the downstream side in the flow direction of the combustion gas; the casing has a first groove portion into which the third flange portion is inserted and which extends along the circumferential direction and into which a fixing member for fixing the fourth flange portion to the casing is inserted and which extends along the circumferential direction; the fixing step involves inserting the third flange portion into the first groove and inserting the fixing member into the second groove so that the fixing member is in contact with the fourth flange portion.

[0087] According to the 11th aspect of this disclosure, the stator vane mounting method involves inserting the third flange portion of the stator vane holding member into the first groove of the casing and inserting the fixing member into the second groove of the casing, thereby bringing the fixing member into contact with the fourth flange portion of the stator vane holding member, and thus fixing the stator vane holding member to the casing.

[0088] A stator vane mounting method according to a twelfth aspect of the present disclosure further comprises the following configuration in any of the seventh to tenth aspects: the second circumferential length of the stator vane holding member is set to be 0.5 times or more the first circumferential length of the stator vane segment.

[0089] According to the twelfth aspect of this disclosure, when the second length is set to 0.5 times or more and 1.0 times or less the first length, the circumferential length of the stator blade retaining member relative to the stator blade segment is shortened. This suppresses the widening of the gap between adjacent pairs of stator blade retaining members in the circumferential direction due to deformation of the stator blade retaining member caused by the heat of the combustion gas, which can reduce the sealing performance of the combustion gas. Furthermore, when the second length is set to 1 time or more the first length, the number of stator blade retaining members required for the gas turbine can be reduced, thereby reducing manufacturing costs and assembly man-hours. [Explanation of Symbols]

[0090] 10 Compressor 11 Moving blade 20 Combustors 30 Turbine 31 High-pressure turbine 31a High-pressure turbine blades 32 Low-pressure turbine 32a Low-pressure turbine blades 32a1 wing section 32a2 Platform Section 32b Turbine Disc 40 Supercharger Fan 50 Inner casing 50a First groove 50b 2nd groove 60 Outer casing 70A High-Voltage Rotating Shaft 70B Low-pressure rotating shaft 80 stator vane segments 81 Static Wing 82 Shroud 83 Upstream flange (first flange section) 84 Downstream flange (first flange section) 90 Stator blade holding mechanism 91 Stationary vane retaining member 92 Upstream retaining flange (second flange section) 93 Downstream retaining flange (second flange section) 94 Insertion flange (third flange section) 95 Butt flange (fourth flange section) 96 Fixing member 100 Gas Turbine AD Axial direction CA combustion gas CD circumferential direction EA external air FPA Fluid Pressure FPR1, FPR2, FPR3, FPR4, FPR5, FPR6 Reaction force RD (Radial Direction) X axis

Claims

1. A compressor having multiple compression blades that rotate around an axis, which compresses external air to generate compressed air, A combustor that burns the compressed air generated by the compressor together with fuel to produce combustion gas, A turbine having a plurality of rotor blades that rotate around the aforementioned axis and driven by the combustion gas generated by the combustor, A rotating shaft is formed to connect the compressor and the turbine and to extend along the axis, and to rotate in the rotational direction, A casing formed in a cylindrical shape extending along the axis and positioned on the outer circumference side of the turbine with respect to the axis, A stator vane segment having stator vanes arranged at multiple locations in the circumferential direction around the aforementioned axis and positioned inside the casing, The system includes a stator vane holding mechanism that is formed in an annular shape around the axis and positioned between the casing and the stator vane segment in a radial direction perpendicular to the axis, and holds the stator vane segment in a position relative to the casing, The stator vane holding mechanism is a gas turbine having a plurality of stator vane holding members that are divided in the circumferential direction and are made of a metal material.

2. The casing supports a first moment about a rotation axis perpendicular to the axis that acts on the stationary vane holding member, which is in contact with a pair of first support positions arranged spaced apart along the axis. The stator vane holding member supports a second moment about the rotation axis acting on the stator vane segments that contact each other at a pair of second support positions spaced apart along the axis, The gas turbine according to claim 1, wherein the fixing member attached to the casing supports the load acting on the stator blade holding member in the direction along the axis.

3. The aforementioned stator vane segment is A shroud to which the radial outer peripheral end of the stator vane is attached and which forms a flow path for the combustion gas extending along the axis, The shroud has a pair of first flange portions formed to protrude radially from the outer circumference and in directions away from each other on both the upstream and downstream sides in the direction of combustion gas flow, The aforementioned stator vane holding member is It has a pair of second flange portions formed to protrude toward each other on the inner circumference in the radial direction and on both the upstream and downstream sides in the flow direction of the combustion gas, The gas turbine according to claim 1, wherein the stator vane segment is held by the stator vane holding member by arranging a pair of first flange portions between a pair of second flange portions in a direction along the axis.

4. The aforementioned stator vane segment is A shroud to which the radial outer peripheral end of the stator vane is attached and which forms a flow path for the combustion gas extending along the axis, It has a pair of first flange portions formed to protrude from the shroud toward the outer circumference in the radial direction and toward each other toward both the upstream and downstream sides in the direction of combustion gas flow, The aforementioned stator vane holding member is It has a pair of second flange portions formed to protrude toward each other in directions toward the inner circumference in the radial direction and toward both the upstream and downstream sides in the flow direction of the combustion gas, The gas turbine according to claim 1, wherein the stator vane segment is held by the stator vane holding member by arranging a pair of second flange portions between a pair of first flange portions in the axial direction along the axis.

5. The aforementioned stator vane holding member is A third flange portion that protrudes toward the upstream side in the flow direction of the combustion gas, It has a fourth flange portion that protrudes toward the downstream side in the flow direction of the combustion gas, The aforementioned casing is The third flange portion is inserted into the first groove portion which extends along the circumferential direction, The fourth flange portion has a fixing member inserted into it for fixing the fourth flange portion to the casing, and a second groove portion extending along the circumferential direction, The gas turbine according to claim 3 or 4, wherein the stationary vane holding member is fixed to the casing such that the third flange portion is inserted into the first groove and the fourth flange portion is in contact with the fixing member inserted into the second groove.

6. The gas turbine according to any one of claims 1 to 4, wherein the second circumferential length of the stator blade holding member is set to be 0.5 times or more the first circumferential length of the stator blade segment.

7. A method for attaching stator blade segments to the casing of a gas turbine, The aforementioned gas turbine A compressor having multiple compression blades that rotate around an axis, which compresses external air to generate compressed air, A combustor that burns the compressed air generated by the compressor together with fuel to produce combustion gas, A turbine having a plurality of rotor blades that rotate around the aforementioned axis and a turbine disk to which the rotor blades are connected, and driven by the combustion gas generated by the combustor, A rotating shaft is formed to connect the compressor and the turbine disk and to extend along the axis, and to rotate in the rotational direction, The casing is formed in a cylindrical shape extending along the axis and is positioned on the outer circumference side of the turbine with respect to the axis, The stator vane segment has stator vanes arranged at multiple locations in the circumferential direction around the axis and positioned inside the casing, The system includes a stator vane holding mechanism that holds the stator vane segment in a positioned state relative to the casing, The stator vane holding mechanism has a plurality of stator vane holding members that are divided in the circumferential direction and are made of a metal material, A mounting step of attaching the stator vane holding member to the stator vane segment, A method for mounting a stator vane, comprising a fixing step of fixing the stator vane holding member attached to the stator vane segment to the casing.

8. The casing supports a first moment about a rotation axis perpendicular to the axis that acts on the stationary vane holding member, which is in contact with a pair of first support positions arranged spaced apart along the axis. The stator vane holding member supports a second moment about the rotation axis acting on the stator vane segments that contact each other at a pair of second support positions spaced apart along the axis, The method for mounting a stator vane according to claim 7, wherein the fixing member attached to the casing supports the load acting on the stator vane holding member in the direction along the axis.

9. The aforementioned stator vane segment is A shroud to which the radial outer end of the stator vane perpendicular to the axis is attached and which forms a flow path for the combustion gas extending along the axis, The shroud has a pair of first flange portions formed to protrude radially from the outer circumference and in directions away from each other on both the upstream and downstream sides in the direction of combustion gas flow, The aforementioned stator vane holding member is It has a pair of second flange portions formed to protrude toward each other on the inner circumference in the radial direction and on both the upstream and downstream sides in the flow direction of the combustion gas, The method for attaching a stator vane according to claim 7, wherein the attachment step involves attaching the stator vane holding member to the stator vane segment by inserting a pair of first flange portions between a pair of second flange portions in a direction along the axis.

10. The aforementioned stator vane segment is A shroud to which the radial outer end of the stator vane perpendicular to the axis is attached and which forms a flow path for the combustion gas extending along the axis, It has a pair of first flange portions formed to protrude from the shroud toward the outer circumference in the radial direction and toward each other toward both the upstream and downstream sides in the direction of combustion gas flow, The aforementioned stator vane holding member is It has a pair of second flange portions formed to protrude toward each other in directions toward the inner circumference in the radial direction and toward both the upstream and downstream sides in the flow direction of the combustion gas, The method for attaching a stator vane according to claim 7, wherein the attachment step involves attaching the stator vane holding member to the stator vane segment by inserting a pair of second flange portions between a pair of first flange portions in a direction along the axis.

11. The aforementioned stator vane holding member is A third flange portion that protrudes toward the upstream side in the flow direction of the combustion gas, It has a fourth flange portion that protrudes toward the downstream side in the flow direction of the combustion gas, The aforementioned casing is The third flange portion is inserted into the first groove portion which extends along the circumferential direction, The fourth flange portion has a fixing member inserted into it for fixing the fourth flange portion to the casing, and a second groove portion extending along the circumferential direction, The method for mounting a stator vane according to claim 9 or 10, wherein the fixing step involves inserting the third flange portion into the first groove and inserting the fixing member into the second groove so that the fixing member is in contact with the fourth flange portion.

12. A method for mounting a stator vane according to any one of claims 7 to 10, wherein the second circumferential length of the stator vane holding member is set to be 0.5 times or more the first circumferential length of the stator vane segment.

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