Method for mounting combustion cylinder

Abstract

To improve efficiency of work for mounting a combustion cylinder.SOLUTION: A method for mounting a combustion cylinder according to at least one embodiment of the present disclosure is a method for mounting a combustion cylinder in a gas turbine, the method comprising a step of mounting to one end part of the combustion cylinder a cover member having: a first indicator that indicates one radial side of a rotor when the combustion cylinder is mounted in a casing that covers an outer periphery of the rotor of the gas turbine; a second indicator that indicates a vertically upward direction when the combustion cylinder is mounted in the casing; and a third indicator that indicates a position at which the combustion cylinder is to be mounted in the casing.SELECTED DRAWING: Figure 4A

Description

[Technical Field]

[0001] The present disclosure relates to a method for installing a combustion can. [Background technology]

[0002] Generally, an industrial gas turbine includes a plurality of combustors spaced apart in the circumferential direction of the rotor of the gas turbine (see, for example, Patent Document 1). [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Japanese Patent Application Laid-Open No. 2000-107949 Summary of the Invention [Problem to be solved by the invention]

[0004] Therefore, in each combustion liner of a plurality of combustors attached to a casing of a gas turbine, the circumferential position of the combustion liner facing the radially outer side of the rotor of the gas turbine, and The difference between the circumferential position of the combustion tubes facing vertically upward differs for each combustion tube.

[0005] When attaching a combustion tube to a gas turbine casing, the combustion tube is lifted. However, after the combustion tube is lifted, it is difficult to adjust its circumferential position by rotating it in the circumferential direction. Therefore, in the rigging work for lifting the combustion tube, it is necessary to attach, for example, a lifting sling to the combustion tube so that the circumferential position of the combustion tube, which faces vertically upward when attached to the gas turbine casing, faces vertically upward when the combustion tube is lifted. However, it is difficult for an inexperienced worker to grasp the circumferential position of the combustion liner, which will face vertically upward when attached to the casing of the gas turbine.

[0006] In view of the above circumstances, at least one embodiment of the present disclosure aims to make it relatively easy to grasp the circumferential position of a combustion liner that faces vertically upward when attached to a gas turbine casing. [Means for solving the problem]

[0007] A method for installing a combustion can in accordance with at least one embodiment of the present disclosure includes: 1. A method for installing a combustion liner in a gas turbine, comprising: a step of attaching a cover member to one end of the combustion liner, the cover member being detachable from one end of the combustion liner, the cover member having a first marking that is displayed so as to indicate one radial side of the rotor when the combustion liner is attached to a casing that covers the outer periphery of the rotor of the gas turbine, a second marking that is displayed so as to point vertically upward when the combustion liner is attached to the casing, and a third marking that indicates at which position the combustion liner is attached to the casing; Attaching a hanger to the combustion liner with the lid member attached; attaching the combustion liner lifted by the lifting tool to the casing; Equipped with In the step of attaching the cover member to the one end of the combustion liner, the cover member is attached to the one end of the combustion liner so that a direction of the combustion liner facing the one radial direction when the combustion liner is attached to the casing coincides with a direction indicated by the first mark; In the step of attaching the hoisting tool, the hoisting tool is attached to the combustion tube so that when the combustion tube with the attached cover member is lifted using the hoisting tool, the direction indicated by the second indication is aligned with the vertical upward direction. [Effects of the Invention]

[0008] According to at least one embodiment of the present disclosure, it is possible to relatively easily grasp the circumferential position of the combustion liner that will face vertically upward when attached to the casing of a gas turbine. [Brief explanation of the drawings]

[0009] [Figure 1] 1 is a schematic configuration diagram of a gas turbine to which a combustion liner mounting method according to some embodiments can be applied; [Figure 2] FIG. [Figure 3] 4 is a schematic diagram for explaining the arrangement of a plurality of transition pieces arranged at intervals in the circumferential direction of the rotor. FIG. [Figure 4A] FIG. 2 is a schematic diagram of a lid member. [Figure 4B] FIG. 2 is a schematic diagram of a lid member. [Figure 5] FIG. 10 is a diagram schematically illustrating a state in which the cover member is attached to the transition piece. [Figure 6] FIG. 1 is a schematic diagram of a sling belt as an example of a hoisting tool used to hoist a transition piece. [Figure 7] FIG. 10 is a diagram schematically illustrating a state in which the transition piece is lifted. [Figure 8] 1 is a flowchart illustrating a process for installing a combustion liner according to some embodiments. DETAILED DESCRIPTION OF THE INVENTION

[0010] Hereinafter, several embodiments of the present disclosure will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc. of components described as embodiments or shown in the drawings are merely illustrative examples and are not intended to limit the scope of the present disclosure. For example, expressions expressing relative or absolute arrangement such as "in a certain direction," "along a certain direction," "parallel," "orthogonal," "center," "concentric," or "coaxial" not only express such an arrangement exactly, but also express a state in which there is a relative displacement with a tolerance or an angle or distance to the extent that the same function is obtained. For example, expressions such as "identical," "equal," and "homogeneous" that indicate that something is in an equal state not only indicate a state of strict equality, but also indicate a state in which there is a tolerance or a difference to the extent that the same function is obtained. For example, expressions representing shapes such as a square shape or a cylindrical shape not only represent shapes such as a square shape or a cylindrical shape in the strict geometric sense, but also represent shapes including uneven portions, chamfered portions, etc., to the extent that the same effect can be obtained. On the other hand, the expressions "comprise," "include," "have," "includes," or "have" of one element are not exclusive expressions that exclude the presence of other elements.

[0011] (Configuration of gas turbine 1) Fig. 1 is a schematic diagram of a gas turbine to which a combustion liner mounting method according to some embodiments can be applied. As shown in Fig. 1, the gas turbine 1 has, in order from the upstream side in the fluid flow direction, a compressor 11, a gas turbine combustor (hereinafter referred to as the combustor) 12, a turbine 13, and an exhaust chamber 14. A generator, for example, is connected to the turbine 13. The gas turbine has a rotor (turbine shaft) 24 that can rotate around a central rotation axis L. In the following description, within the axial direction Da, which is the direction in which the rotational axis L of the rotor 24 extends, the direction from the compressor 11 toward the turbine 13 will be referred to as the axial downstream side Dad of the rotor 24, and the direction from the turbine 13 toward the compressor 11 will be referred to as the axial upstream side Dau of the rotor 24. In addition, the circumferential direction Dc centered on the rotational axis L of the rotor 24 will also be referred to as the circumferential direction Dc of the rotor 24, and the radial direction Dr centered on the rotational axis L of the rotor 24 will also be referred to as the radial direction Dr of the rotor 24.

[0012] The compressor 11 is connected to an air intake 15 that takes in air and has a compressor casing 16 in which a flow path for the air flows. The compressor 11 has a plurality of stator vanes 17 and rotor blades 18 arranged alternately in the air flow path within the compressor casing 16. The combustor 12 supplies fuel to the compressed air (combustion air) compressed by the compressor 11, and burns the mixture of the fuel and the combustion air to generate combustion gas. A plurality of combustors 12 are provided at intervals in the circumferential direction Dc of the rotor 24. The turbine 13 is formed with a turbine casing 20 having a flow path into which fuel gas generated in the combustor 12 flows. The turbine 13 has a plurality of stator vanes 21 and rotor blades 22 arranged alternately within the combustion gas flow path of the turbine casing 20 from upstream to downstream in the flow direction of the combustion gas as a fluid, i.e., toward the axial downstream side Dad of the rotor 24. The stator vanes 21 are supported by a stator vane shroud 50 (see FIG. 2), which is a part of the turbine casing 20. A space through which combustion gas passes is formed inside the stator vane shroud 50. The stator vane shroud 50 fixes the stator vanes 21 to the space through which the combustion gas passes. In addition, the stator vane shroud 50 is connected to the combustor 12.

[0013] The exhaust chamber 14 has an exhaust diffuser 23 into which the combustion gas that has passed through the turbine 13 flows. The rotor 24 is positioned so as to penetrate through the radial centers of the compressor 11, the combustor 12, the turbine 13, and the exhaust chamber 14. An end of the rotor 24 on the compressor 11 side (axial upstream side Dau) is supported by a bearing 25 so as to be rotatable about the rotation axis L, and an end of the rotor 24 on the exhaust chamber 14 side (axial downstream side Dad) is supported by a bearing 26 so as to be rotatable about the rotation axis L. A plurality of disc plates are fixed to the rotor 24, and the rotor blades 18, 22 are connected to the disc plates.

[0014] In this gas turbine 1, air taken in through an air intake 15 of the compressor 11 passes through a plurality of stator vanes 17 and rotor blades 18 and is compressed to become high-temperature, high-pressure compressed air. This compressed air is mixed with fuel in the combustor 12 by supplying a predetermined fuel to the compressed air. This mixture is combusted in the combustor 12 to become combustion gas. The high-temperature, high-pressure combustion gas, which is a working fluid produced in the combustor 12, passes through a plurality of stator vanes 21 and rotor blades 22 provided in the turbine 13 and rotates the rotor 24. The rotation of the rotor 24 drives a generator connected to the rotor 24, generating electricity. The exhaust gas that passes through the rotor 24 is released into the atmosphere as exhaust gas.

[0015] 2 is an enlarged view of the combustor. The combustor 12 has a combustor casing 30. The combustor casing 30 has an inner cylinder 32 disposed inside an outer cylinder 31 and a transition piece 33 connected to the tip of the inner cylinder 32, and extends along a central axis La inclined with respect to the central axis L of rotation of the rotor 24. Here, in the gas turbine 1, the space between the casing housing 27 and the combustor casing 30 forms a combustor-compressor casing (hereinafter referred to as a combustor-compressor casing) 34. Compressed air compressed by the compressor 11 is bled into the combustor-compressor casing 34. The compressed air bled to the combustor-compressor casing 34 flows into the inner cylinder 32 of the combustor 12.

[0016] The outer cylinder 31 is fastened to the casing housing 27. The inner cylinder 32 has a base end supported by the outer cylinder 31 and is disposed inside the outer cylinder 31 at a predetermined distance from the outer cylinder 31. A pilot nozzle 40 is provided in the center of the inner cylinder 32 along the central axis La. A plurality of main nozzles 42 are disposed around the pilot nozzle 40 at equal intervals and parallel to the pilot nozzle 40 so as to surround the pilot nozzle 40.

[0017] (tail tube 33) The transition piece (combustion duct) 33 has a base end (end 33I) formed in a cylindrical shape and connected to the tip of the inner duct 32. The transition piece 33 is curved and has a smaller cross-sectional area toward the tip (end 33O) side, and opens toward the first stage stator vanes 21 of the turbine 13. The tip of the transition piece 33, i.e., the end 33O on the downstream side of the flow of combustion gas, is connected to the stator vane shroud 50. In FIG. 2, arrow FG indicates the direction in which combustion gas flows within transition piece 33.

[0018] In the upstream region of the combustion gas flow, the transition piece 33 extends from the upstream end 33I of the combustion gas flow toward the downstream side of the combustion gas flow, from the radially outer side Dro of the rotor 24 toward the radially inner side Dri, and also toward the axially downstream side Dad of the rotor 24. In the downstream region including the downstream end 33O of the flow of combustion gas, the transition piece 33 extends toward the axial downstream side Dad of the rotor 24 while the radial position Dr of the rotor 24 does not change as it moves toward the downstream side of the flow of combustion gas. In this way, the transition piece 33 is formed so that the central axis La of the transition piece 33 is curved within an imaginary plane PV (see FIG. 5) that includes the central rotation axis L of the rotor 24 and extends in the radial direction Dr of the rotor 24. In other words, the transition piece 33 is formed so as to be curved in the radial direction Dr of the rotor 24.

[0019] Figure 3 is a schematic diagram for explaining the arrangement of multiple transition pieces 33 arranged at intervals in the circumferential direction Dc of the rotor 24, and corresponds to a view of the transition pieces 33 as viewed toward the axial downstream side Dad of the rotor 24. For convenience of explanation, in FIG. 3, twelve transition pieces 33 are arranged at intervals in the circumferential direction Dc, but the number of arranged transition pieces 33 is not limited to twelve. Also, for ease of explanation, the positions of the transition piece 33 in the circumferential direction Dc of the rotor 24 in Figure 3 will be represented as position P1, position P2, ..., position P12, in that order, starting from a position between 12 o'clock and 1 o'clock and moving clockwise.

[0020] As described above, the transition piece 33 is formed to curve in the radial direction Dr of the rotor 24. Therefore, in the gas turbine 1 according to some embodiments, when the transition piece 33 is attached to the turbine casing 20 of the gas turbine 1, the attitude of the transition piece 33 (the direction in which the transition piece 33 curves) differs for each attachment position to the turbine casing 20. Therefore, in the transition pieces 33 of each of the multiple combustors 12 attached to the turbine casing 20 of the gas turbine 1, the difference in the circumferential position of the transition piece 33 between the circumferential position a1 of the transition piece 33 facing the radially outer side Dro of the rotor 24 and the circumferential position a2 of the transition piece 33 facing vertically upward differs for each transition piece 33.

[0021] When attaching the transition piece 33 to the turbine casing 20, an operation to lift the transition piece 33 is performed. At this time, after the transition piece 33 has been lifted, it is difficult to adjust the circumferential position of the transition piece 33 by rotating the transition piece 33 in the circumferential direction of the transition piece 33. Therefore, in the slinging operation for lifting the transition piece 33, it is necessary to attach, for example, a lifting sling belt 121 (see FIG. 6) to the transition piece 33 so that the circumferential position a2 of the transition piece 33, which faces vertically upward when attached to the turbine casing 20, faces vertically upward when the transition piece 33 is lifted. However, it is difficult for an inexperienced worker to grasp the circumferential position a2 of the transition piece 33, which will face vertically upward when attached to the turbine casing 20.

[0022] Therefore, in some embodiments of the method for installing a combustion tube, a cover member 100 as described below is attached to the transition piece 33 in advance, so that even an inexperienced worker can easily grasp the circumferential position a2 of the transition piece 33.

[0023] FIG. 4A is a schematic diagram of the cover member 100, and shows, as an example, the cover member 100 to be attached to the transition piece 33 disposed at position P1. FIG. 4B is a schematic diagram of the cover member 100, showing, as an example, the cover member 100 to be attached to the transition piece 33 disposed at position P5. The cover member 100 according to some embodiments is a member that can be attached to one end of the transition piece 33. The cover member 100 is a member that can be attached to, for example, the base end (end 33I) of the transition piece 33, and is preferably configured to be fitted into the transition piece 33 from the end 33I, with its outer edge portion temporarily fixed to the inner circumferential surface of the transition piece 33 by friction. By making it possible to attach it to the end 33I of the transition piece 33, which has a larger opening area than the tip (end 33O) of the transition piece 33, it becomes easier to make the first display 101, second display 102, and third display described below larger, making them easier for workers to see.

[0024] The cover member 100 according to some embodiments may be able to close the opening at the end 33I of the transition piece 33. Since the combustion liner has openings at the ends 33I and 33O, it is desirable to close these openings before attaching the transition piece 33 to the turbine casing 20 in order to prevent foreign matter from entering the transition piece 33. According to the cover member 100 according to some embodiments, the possibility of foreign matter entering the transition piece 33 can be reduced. That is, the cover member 100 may also function as a protective cover to prevent foreign matter from entering the transition piece 33. In other words, the cover member 100 may be configured to display the above-described first indicia 101, second indicia 102, and third indicia 103 on the protective cover.

[0025] The cover member 100 is, for example, a wooden member that is easy to temporarily fix with the inner surface by friction and is unlikely to damage the inner surface of the transition piece 33, but it may also be a resin member, or a paper member that can be attached to the end 33I of the transition piece 33 with tape, etc. The cover member 100 may be a member that can be attached to the tip of the transition piece 33 (end portion 33O).

[0026] The cover member 100 in some embodiments has a first indicator 101 displayed to indicate one radial side (e.g., the radially outer side Dro) of the rotor 24 when the transition piece 33 is attached to the turbine casing 20, a second indicator 102 displayed to indicate a vertically upward direction when the transition piece 33 is attached to the turbine casing 20, and a third indicator 103 indicating at which position in the turbine casing 20 the transition piece 33 is attached.

[0027] The cover member 100 shown in FIG. 4A has a first indicator 101, a second indicator 102, and a third indicator 103 that indicates that the transition piece 33 is attached at position P1. The cover member 100 shown in FIG. 4B has a first indicator 101, a second indicator 102, and a third indicator 103 that indicates that the transition piece 33 is attached at position P5.

[0028] The first display 101 includes, for example, an arrow 101a indicating which direction the radially outer side Dro of the rotor 24 is, and a display 101b indicating that the direction indicated by the arrow 101a is the radially outer side Dro of the rotor 24. However, the display form of the first display 101 is not limited to the display form shown in Figures 4A and 4B, as long as it is possible to know which direction the radially outer side Dro of the rotor 24 is. The first indicator 101 may indicate, instead of the arrow 101a, or together with the arrow 101a, which direction the radially inner side Dri of the rotor 24 faces.

[0029] Second display 102 includes, for example, arrow 102a indicating which direction is vertically upward and display 102b indicating that the direction indicated by arrow 102a is vertically upward. However, first display 101 may have any display form other than those shown in FIGS. 4A and 4B, as long as it indicates which direction is vertically upward.

[0030] FIG. 5 is a diagram that shows a schematic view of the state in which the cover member 100 is attached to the transition piece 33, and shows a state in which the cover member 100 is attached to the transition piece 33 that is attached at position P5 as an example. FIG. 6 is a schematic diagram of a sling belt 121 as an example of a sling used to hoist the transition piece 33. As shown in FIG. FIG. 7 is a diagram showing a schematic view of the transition piece 33 in a lifted state.

[0031] 5, the cover member 100 is attached to the transition piece 33 with the arrow 101a of the first marking 101 facing in the direction that faces the radially outer side Dro of the rotor 24 when the transition piece 33 is attached to the turbine casing 20. The direction that faces the radially outer side Dro of the rotor 24 when the transition piece 33 is attached to the turbine casing 20 can be easily determined from the curved direction of the transition piece 33.

[0032] (How to install the combustion tube) 8 is a flowchart showing the procedure of a process in a combustion liner installation method according to some embodiments. In the combustion liner installation method according to some embodiments, when installing the transition piece 33, an operator installs the transition piece 33 in the turbine casing 20 according to the procedure shown in FIG. A method for attaching a combustion liner according to some embodiments includes step S1 of attaching a cover member, step S3 of attaching a hoisting tool, step S5 of lifting, and step S7 of attaching a transition piece to a casing.

[0033] (Step S1: Attaching the lid member) Step S1 of attaching the cover member is a step of attaching a cover member 100, which is detachable from the base end (end 33I) of the transition piece 33 and has a first marking, a second marking, and a third marking, to the base end (end 33I) of the transition piece 33. In step S1 of attaching the cover member, the worker attaches the cover member 100 to the end 33I of the transition piece 33 with the arrow 101a of the first marking 101 facing in the direction that will face the radially outer side Dro of the rotor 24 when the transition piece 33 is attached to the turbine casing 20, as shown in FIG. 5. As described above, the worker can easily determine the direction that will face the radially outer side Dro of the rotor 24 when the transition piece 33 is attached to the turbine casing 20 from the curved direction of the transition piece 33.

[0034] (Step S3: Attaching the sling) Step S3 of attaching the hoisting tool is a step of attaching the hoisting tool to the combustion tube to which the cover member 100 is attached. In step S3 of attaching the hoisting tool, the worker attaches, for example, a sling belt 121 for lifting to the transition piece 33 so that the direction indicated by the second indicator 102 of the cover member 100 faces vertically upward when the transition piece 33 is lifted.

[0035] (Lifting step S5) Lifting step S5 is a step of lifting the transition piece 33 to which the lifting tool (e.g., sling belt 121) has been attached in Attaching the Lifting Tool step S3. In lifting step S5, as shown in FIG. 7, the worker hangs one end of the lifting sling belt 121 on a hook 123 of a lifting device (not shown), and operates the lifting device to lift the transition piece 33.

[0036] (Step S7: attaching the transition piece to the casing) Step S7 of attaching the transition piece to the casing is a step of attaching the transition piece 33, which has been lifted using a lifting tool, to the turbine casing 20. In step S7 of attaching the transition piece to the casing, an operator refers to the first marking 101 and the third marking of the cover member 100 attached to the transition piece 33, and attaches the end 33O of the transition piece 33 to the stator vane shroud 50, which is part of the turbine casing 20, at a specified position in the circumferential direction Dc.

[0037] As described above, the method for attaching a combustion liner according to some embodiments includes step S1 of attaching a cover member, step S3 of attaching a suspender, and step S7 of attaching a transition piece to a casing. This makes it easy for the worker to attach the hoisting tool to the transition piece 33 so that when the transition piece 33 to which the cover member 100 is attached is lifted using the hoisting tool, the direction indicated by the second display 102 matches the vertical upward direction. In this way, workers can relatively easily grasp the circumferential position of the transition piece 33, which will be facing vertically upward when attached to the turbine casing 20. This eliminates the need to adjust the circumferential position by rotating the transition piece 33 in the circumferential direction of the transition piece 33 after lifting it, thereby avoiding the needless work of lowering the lifted transition piece 33 to the ground and then rotating the transition piece 33 in the circumferential direction of the transition piece 33 to adjust the circumferential position. Therefore, according to the combustion liner mounting method according to some embodiments, the mounting work of the transition piece 33 can be made more efficient.

[0038] In the method for attaching a combustion liner according to some embodiments, the direction indicated by the first indicia 101 may be the radially outer side of the rotor. When an operator looks at the curved shape of the transition piece 33, it is easier for the operator to grasp the circumferential position at which the transition piece 33 faces the radially outer side Dro of the rotor 24 than the circumferential position at which the transition piece 33 faces the radially inner side Dri of the rotor 24 when attached to the turbine casing 20. Therefore, according to the combustion liner attachment method according to some embodiments, in step S1 of attaching the cover member, it becomes easy to attach the cover member 100 to the transition piece 33 so that the direction in which the radially outer side Dro of the transition piece 33 faces when attached to the turbine casing 20 matches the direction indicated by the first indication 101.

[0039] The present disclosure is not limited to the above-described embodiments, but also includes modifications to the above-described embodiments and appropriate combinations of these modifications.

[0040] The contents described in each of the above embodiments can be understood, for example, as follows. (1) A method for attaching a combustion liner according to at least one embodiment of the present disclosure is a method for attaching a combustion liner (transition piece 33) to a gas turbine 1. The method for attaching a combustion liner according to at least one embodiment of the present disclosure includes a first indicator 101 that is detachable from one end (e.g., end 33I) of the combustion liner (transition piece 33) and is displayed so as to indicate one radial side (e.g., the radially outer side Dro) of the rotor 24 when the combustion liner (transition piece 33) is attached to a casing (stator vane shroud 50) that covers the outer periphery of the rotor 24 of the gas turbine 1, and a second indicator 102 that is displayed so as to indicate a vertically upward direction when the combustion liner (transition piece 33) is attached to the casing (stator vane shroud 50). The method includes step S1 of attaching a cover member 100 having a first mark 102 and a third mark 103 indicating at which position in the casing (stator vane shroud 50) the combustion duct (transition piece 33) is to be attached to one end (e.g., end 33I) of the combustion duct (transition piece 33), step S3 of attaching a lifting device to the combustion duct (transition piece 33) to which the cover member 100 is attached, and step S7 of attaching the combustion duct (transition piece 33) lifted using the lifting device (e.g., sling belt 121) to the casing (stator vane shroud 50). In step S1 of attaching the cover member 100 to one end (e.g., end 33I) of the combustion liner (transition piece 33), the cover member 100 is attached to one end (e.g., end 33I) of the combustion liner (transition piece 33) so that the direction facing one radial side (e.g., radially outward Dro) of the combustion liner (transition piece 33) when the combustion liner (transition piece 33) is attached to the casing (stator vane shroud 50) coincides with the direction indicated by the first marking 101. In step S3 of attaching a hoisting tool, the hoisting tool (e.g., sling belt 121) is attached to the combustion liner (transition piece 33) so that the direction indicated by the second marking 102 coincides with the vertically upward direction when the combustion liner (transition piece 33) to which the cover member 100 is attached is hoisted using the hoisting tool.

[0041] When attaching the combustion duct (transition piece 33) to the casing (stator vane shroud 50) of the gas turbine 1, an operation to lift the combustion duct (transition piece 33) is performed. At this time, after the combustion duct (transition piece 33) has been lifted, it is difficult to adjust the circumferential position of the combustion duct (transition piece 33) by rotating it in the circumferential direction of the combustion duct (transition piece 33). Therefore, in the slinging operation for lifting the combustion duct (transition piece 33), it is necessary to attach, for example, a lifting sling (e.g., a sling belt 121) to the combustion duct (transition piece 33) so that the circumferential position of the combustion duct (transition piece 33), which faces vertically upward when attached to the casing (stator vane shroud 50) of the gas turbine 1, faces vertically upward when the combustion duct (transition piece 33) is lifted. However, it is difficult for an inexperienced worker to grasp the circumferential position of the combustion duct (transition piece 33), which faces vertically upward when attached to the casing (stationary vane shroud 50) of the gas turbine 1.

[0042] According to the method (1) above, in step S1 of attaching the cover member 100 to one end (e.g., end 33I) of the combustion liner (transition piece 33), the cover member 100 is attached to one end (e.g., end 33I) of the combustion liner (transition piece 33) so that the direction facing either the radially inner side Dri or the radially outer side Dro of the combustion liner (transition piece 33) when the combustion liner (transition piece 33) is attached to the casing (stator vane shroud 50) coincides with the direction indicated by the first indicator 101. This cover member 100 displays a second indicator 102 that is displayed to point vertically upward when the combustion liner (transition piece 33) is attached to the casing (stator vane shroud 50). Therefore, in step S3 of attaching the hoisting tool, when the combustion tube (transition piece 33) to which the cover member 100 is attached is hoisted using the hoisting tool (e.g., sling belt 121), it becomes easy for the worker to attach the hoisting tool (e.g., sling belt 121) to the combustion tube (transition piece 33) so that the direction indicated by the second display 102 is aligned with the vertically upward direction. In this way, an operator can relatively easily grasp the circumferential position of the combustion duct (transition piece 33), which will be oriented vertically upward when attached to the casing (stationary vane shroud 50) of the gas turbine 1. This eliminates the need to adjust the circumferential position by rotating the combustion duct (transition piece 33) in the circumferential direction of the combustion duct (transition piece 33) after lifting it, thereby avoiding the needless work of temporarily lowering the lifted combustion duct (transition piece 33) to the ground and then rotating the combustion duct (transition piece 33) in the circumferential direction of the combustion duct (transition piece 33) to adjust its circumferential position. Therefore, according to the above method (1), the installation work of the combustion tube (transition piece 33) can be made more efficient.

[0043] (2) In some embodiments, in the method (1) above, the one radial side may be the radially outer side Dro of the rotor 24.

[0044] When an operator looks at the curved shape of the combustion liner (transition piece 33), it is easier to grasp the circumferential position at which the combustion liner (transition piece 33) faces the radially outer side Dro of the rotor 24 than the circumferential position at which the combustion liner (transition piece 33) faces the radially inner side Dri of the rotor 24 when the combustion liner (transition piece 33) is attached to the casing (stator vane shroud 50). Therefore, according to the method (2) above, in step S1 of attaching the cover member 100 to one end (e.g., end 33I) of the combustion liner (transition piece 33), it becomes easy to attach the cover member 100 to the combustion liner (transition piece 33) so that the direction in which the combustion liner (transition piece 33) faces the radially outer side Dro when the combustion liner (transition piece 33) is attached to the casing (stator vane shroud 50) matches the direction indicated by the first marking 101.

[0045] (3) In some embodiments, in the method (1) or (2) above, the cover member 100 may be capable of closing an opening at one end (for example, end 33I) of the combustion liner (transition piece 33).

[0046] Since the combustion tube (transition piece 33) has an opening at one end (for example, end 33I), it is desirable to close the opening before attaching the combustion tube (transition piece 33) to the casing (stator vane shroud 50) in order to prevent foreign matter from entering the combustion tube (transition piece 33). According to the above method (3), it is possible to reduce the possibility of foreign matter getting into the combustion tube (transition piece 33). [Explanation of symbols]

[0047] 1. Gas turbine 12 Combustor 20 Turbine casing 24 rotor (turbine shaft) 33 Tail tube (combustion tube) 33I Proximal end (end) 33O Tip (end) 50 Stator blade shroud 100 Lid member 101 1st display 102 2nd display 103 3rd display

Claims

1. 1. A method for installing a combustion liner in a gas turbine, comprising: a step of attaching a cover member to one end of the combustion liner, the cover member being detachable from one end of the combustion liner, the cover member having a first marking that is displayed so as to indicate one radial side of the rotor when the combustion liner is attached to a casing that covers the outer periphery of the rotor of the gas turbine, a second marking that is displayed so as to point vertically upward when the combustion liner is attached to the casing, and a third marking that indicates at which position the combustion liner is attached to the casing; Attaching a hanger to the combustion liner with the lid member attached; attaching the combustion liner lifted by the lifting tool to the casing; Equipped with In the step of attaching the cover member to the one end of the combustion liner, the cover member is attached to the one end of the combustion liner so that a direction of the combustion liner facing the one radial direction when the combustion liner is attached to the casing coincides with a direction indicated by the first mark; In the step of attaching the hoisting tool, the hoisting tool is attached to the combustion tube so that the direction indicated by the second indication coincides with a vertically upward direction when the combustion tube to which the lid member is attached is hoisted using the hoisting tool. How to install the combustion cylinder.

2. The one radial side is the radial outer side of the rotor. A method for mounting a combustion liner according to claim 1.

3. The cover member is capable of closing the opening at the one end of the combustion liner. A method for mounting a combustion liner according to claim 1 or 2.

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