Combustion cylinder attachment method

Abstract

A combustion cylinder attachment method according to at least one embodiment of the present disclosure is used in a gas turbine, said method comprising a step for attaching, to one end of a combustion cylinder, a lid member that has: a first display in which the combustion cylinder is displayed so as to indicate one side in the radial direction of a rotor of the gas turbine when attached to a casing covering the outer circumference of the rotor; a second display in which the combustion cylinder is displayed so as to indicate the upper side in the vertical direction when attached to the casing; and a third display which indicates where in the casing the combustion cylinder is attached.

Description

How to install the combustion cylinder

[0001] This application claims priority to Japanese Patent Application No. 2024-064329, filed with the Japan Patent Office on April 12, 2024, the contents of which are incorporated herein by reference.

[0002] 2. Description of the Related Art Generally, industrial gas turbines include a plurality of combustors spaced apart in the circumferential direction of a rotor of the gas turbine (see, for example, Patent Document 1).

[0003] Japanese Patent Application Laid-Open No. 2000-107949

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

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

[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 will face vertically upward when attached to a gas turbine casing.

[0007] A method for installing a combustion liner in a gas turbine according to at least one embodiment of the present disclosure comprises the steps 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 to indicate one radial side of the rotor when the combustion liner is attached to a casing that covers an outer periphery of the rotor of the gas turbine, a second marking that is displayed to indicate a vertically upward side when the combustion liner is attached to the casing, and a third marking that indicates a position in the casing where the combustion liner is to be installed; attaching a hoisting tool to the combustion liner to which the cover member is attached; and attaching the combustion liner that has been lifted using the hoisting tool to the casing, wherein 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 the direction that the combustion liner faces toward the one radial side when the combustion liner is attached to the casing coincides with the direction indicated by the first marking, In the step of attaching the hoisting device, when the combustion tube with the attached cover member is lifted using the hoisting device, the hoisting device is attached to the combustion tube so that the direction indicated by the second indication coincides with the vertical upper side.

[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.

[0009] FIG. 1 is a schematic configuration diagram of a gas turbine to which a combustion liner installation method according to some embodiments can be applied. FIG. 2 is an enlarged view of a combustor. FIG. 3 is a schematic diagram for explaining the arrangement of a plurality of transition pieces arranged at intervals in the circumferential direction of a rotor. FIG. 4 is a schematic diagram of a cover member. FIG. 5 is a schematic diagram of a cover member. FIG. 6 is a schematic diagram showing a state in which the cover member is attached to the transition piece. FIG. 7 is a schematic diagram of a sling belt as an example of a hoisting tool used when hoisting the transition piece. FIG. 8 is a schematic diagram showing a state in which the transition piece has been hoisted. FIG. 9 is a flowchart showing the procedure of processing in a combustion liner installation method according to some embodiments.

[0010] Several embodiments of the present disclosure will be described below 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 not intended to limit the scope of the present disclosure and are merely illustrative examples. For example, expressions expressing relative or absolute arrangements, such as "in a certain direction," "along a certain direction," "parallel," "orthogonal," "center," "concentric," or "coaxial," not only strictly express such arrangements, but also express relative displacements with a tolerance or angle or distance to the extent that the same function is achieved. For example, expressions expressing the equality of things, such as "same," "equal," and "homogeneous," not only express strict equality, but also express tolerance or differences to the extent that the same function is achieved. For example, expressions expressing shapes such as a square or cylindrical shape not only express shapes such as a square or cylindrical shape in the strict geometric sense, but also express shapes including concave and convex portions, chamfered portions, etc., to the extent that the same effect is achieved. 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 includes, in order from the upstream side in a 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 coupled to the turbine 13. The gas turbine includes a rotor (turbine shaft) 24 that can rotate about a central rotation axis L. In the following description, within the axial direction Da, which is the extension direction of the central rotation axis L of the rotor 24, the direction from the compressor 11 toward the turbine 13 is referred to as the axial downstream side Dad of the rotor 24, and the direction from the turbine 13 toward the compressor 11 is referred to as the axial upstream side Dau of the rotor 24. In addition, the circumferential direction Dc centered on the central axis L of rotation of the rotor 24 is also referred to as the circumferential direction Dc of the rotor 24, and the radial direction Dr centered on the central axis L of rotation of the rotor 24 is also 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 that is provided with a flow path through which 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 fuel and 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 has a turbine casing 20 that is provided with a flow path into which the fuel gas generated in the combustor 12 flows. The turbine 13 has a plurality of stator vanes 21 and rotor blades 22 arranged alternately in 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 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 in the space through which the combustion gas passes. The stator vane shroud 50 is also connected to the combustor 12.

[0013] The exhaust chamber 14 has an exhaust diffuser 23 into which 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 disk plates are fixed to the rotor 24, and the rotor blades 18, 22 are connected to the disk 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 generated in the combustor 12, passes through a plurality of stator vanes 21 and rotor blades 22 provided in the turbine 13 and rotates a rotor 24. The rotation of the rotor 24 drives a generator connected to the rotor 24, generating electricity. 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 into 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 at 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 piece 33) The tail piece (combustion piece) 33 has a cylindrical base end (end 33I) that is connected to the tip of the inner cylinder 32. The tail piece 33 has a cross-sectional area that decreases and is curved toward the tip (end 33O) and opens toward the first stage stator vanes 21 of the turbine 13. The tip of the tail piece 33, i.e., the end 33O downstream of the flow of combustion gas, is connected to the stator vane shroud 50. In Figure 2, arrow FG indicates the direction in which combustion gas flows inside the tail 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 to the radially inner side Dri of the rotor 24, and also toward the axially downstream side Dad of the rotor 24. In the downstream region including the downstream end 33O of the combustion gas flow, the transition piece 33 extends toward the axially downstream side Dad of the rotor 24 while maintaining the same position in the radial direction Dr of the rotor 24 as it moves downstream of the combustion gas flow. In this way, the transition piece 33 is formed so that the central axis La of the transition piece 33 curves within an imaginary plane PV (see FIG. 5 ) that includes the rotational center 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 curve in the radial direction Dr of the rotor 24.

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

[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 depending on the 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, the transition piece 33 is hoisted. At this time, after the transition piece 33 has been hoisted, it is difficult to rotate the transition piece 33 in the circumferential direction of the transition piece 33 to adjust its circumferential position. Therefore, in the slinging work for hoisting the transition piece 33, it is necessary to attach, for example, a hoisting sling belt 121 (see FIG. 6 ) to the transition piece 33 so that the circumferential position a2 of the transition piece 33, which will face vertically upward when attached to the turbine casing 20, faces vertically upward when the transition piece 33 is hoisted. However, it is difficult for an inexperienced worker to determine 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, illustrating, as an example, the cover member 100 for attachment to the transition piece 33 located at position P1. FIG. 4B is a schematic diagram of the cover member 100, illustrating, as an example, the cover member 100 for attachment to the transition piece 33 located 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 in a direction along the central axis La. 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 so that its outer edge is temporarily fixed by friction with the inner circumferential surface of the transition piece 33. By being attachable 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 is easier to enlarge the first indicator 101, second indicator 102, and third indicator 103 (described later), making them easier for operators to see.

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

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

[0026] The cover member 100 in some embodiments has a first indicator 101 that is 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 that is displayed to indicate the vertically upper side when the transition piece 33 is attached to the turbine casing 20, and a third indicator 103 that indicates the position in the turbine casing 20 at which 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 to 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 to position P5.

[0028] The first display 101 includes, for example, an arrow 101a indicating the direction of the radially outer side Dro of the rotor 24, 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 determine the direction of the radially outer side Dro of the rotor 24. Note that the first display 101 may indicate the direction of the radially inner side Dri of the rotor 24 instead of or together with the arrow 101a.

[0029] The second display 102 includes, for example, an arrow 102a indicating which direction is vertically upward, i.e., which direction should be vertically upward, and a display 102b indicating that the direction indicated by the arrow 102a is vertically upward. 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 is vertically upward.

[0030] Fig. 5 is a diagram schematically showing the state in which the cover member 100 is attached to the transition piece 33, and shows the state in which the cover member 100 is attached to the transition piece 33 attached at position P5 as an example. Fig. 6 is a diagram schematically showing a sling belt 121 as an example of a hoisting tool used to hoist the transition piece 33. Fig. 7 is a diagram schematically showing the state in which the transition piece 33 is hoisted.

[0031] 5 , for example, the cover member 100 is attached to the transition piece 33 with the arrow 101a of the first marking 101 facing in a direction that faces the radially outer side Dro of the rotor 24 when the transition piece 33 is attached to the turbine casing 20. Note that 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] (Combustion liner installation method) Figure 8 is a flowchart showing the processing steps 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 to the turbine casing 20 according to the steps shown in Figure 8. The combustion liner installation method according to some embodiments includes step S1 of installing a cover member, step S3 of installing a lifting tool, step S5 of lifting, and step S7 of installing the transition piece to the casing.

[0033] (Step S1 of Attaching the Cover 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 101, a second marking 102, and a third marking 103, 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 of Attaching the Lifting Tool) Step S3 of attaching the lifting tool is a step of attaching the lifting tool to the combustion tube to which the cover member 100 is attached. In step S3 of attaching the lifting tool, the worker attaches, for example, a lifting sling belt 121 to the transition piece 33 in the slinging work 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 hooks 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 of 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 103 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 combustion liner installation method according to some embodiments includes step S1 of attaching the cover member, step S3 of attaching the hoisting tool, and step S7 of attaching the transition piece to the casing. This makes it easy for an operator to attach the hoisting tool to the transition piece 33 so that the direction indicated by the second indicator 102 and the vertically upward direction coincide when the transition piece 33, to which the cover member 100 is attached, is hoisted using the hoisting tool. In this manner, the operator can relatively easily grasp the circumferential position of the transition piece 33, which will face vertically upward when attached to the turbine casing 20. Therefore, it is not necessary to adjust the circumferential position of the transition piece 33 by rotating it in the circumferential direction of the transition piece 33 after hoisting it. This avoids the need to lower the hoisted transition piece 33 to the ground and then rotate it in the circumferential direction of the transition piece 33 to adjust its circumferential position, which is an unnecessary step. Therefore, the combustion liner installation method according to some embodiments can improve the efficiency of the installation work of the transition piece 33.

[0038] In the combustion liner installation method according to some embodiments, the direction indicated by the first indication 101 may be the radially outer side Dro of the rotor 24. When an operator looks at the curved shape of the transition piece 33, it is easier for the operator to grasp the circumferential position that faces the radially outer side Dro of the rotor 24 than the circumferential position that faces the radially inner side Dri of the rotor 24 when the transition piece 33 is installed in the turbine casing 20. Therefore, according to the combustion liner installation method according to some embodiments, in step S1 of installing the cover member, it is easy to install the cover member 100 on the transition piece 33 so that the direction that faces the radially outer side Dro of the transition piece 33 when the transition piece 33 is installed in 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 combustion liner mounting method according to at least one embodiment of the present disclosure is a method for mounting a combustion liner (transition piece 33) in a gas turbine 1. The combustion liner mounting method 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 the vertically upper side 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 third mark 103 indicating the position of the combustion tube (transition piece 33) to the casing (stator vane shroud 50) to one end (e.g., end 33I) of the combustion tube (transition piece 33), step S3 of attaching a lifting tool to the combustion tube (transition piece 33) to which the cover member 100 is attached, and step S7 of attaching the combustion tube (transition piece 33) hoisted using the lifting tool (e.g., sling belt 121) to the casing (stator vane shroud 50). In step S1, the cover member 100 is attached to one end (e.g., end 33I) of the combustion duct (transition piece 33), so that the direction of the combustion duct (transition piece 33) facing one radial side (e.g., radially outward Dro) when the combustion duct (transition piece 33) is attached to the casing (stator vane shroud 50) coincides with the direction indicated by the first indicator 101. In step S3, a hoisting tool is attached to the combustion duct (transition piece 33), so that the direction indicated by the second indicator 102 coincides with the vertically upward direction when the combustion duct (transition piece 33) to which the cover member 100 is attached is hoisted using the hoisting tool (e.g., sling belt 121).

[0041] When attaching the combustion duct (transition piece 33) to the casing (stator vane shroud 50) of the gas turbine 1, an operation of lifting 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 the combustion duct (transition piece 33) 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 in which the combustion liner (transition piece 33) faces either the radially inner side Dri or the radially outer side Dro 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 duct (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 duct (transition piece 33) so that the direction indicated by the second indicator 102 and the vertically upward direction coincide. In this way, the worker can relatively easily grasp the circumferential position of the combustion duct (transition piece 33), which will face vertically upward when attached to the casing (stationary vane shroud 50) of the gas turbine 1. Therefore, it is no longer necessary 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). This avoids the need to lower the hoisted combustion duct (transition piece 33) to the ground and then rotate the combustion duct (transition piece 33) in the circumferential direction of the combustion duct (transition piece 33) to adjust the circumferential position. Therefore, according to the above method (1), the installation work of the combustion tube (transition tube 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 duct (transition piece 33), it is easier to grasp the circumferential position at which the combustion duct (transition piece 33) faces the radially outer side Dro of the rotor 24 than the circumferential position at which the combustion duct (transition piece 33) faces the radially inner side Dri of the rotor 24 when the combustion duct (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 duct (transition piece 33), it becomes easy to attach the cover member 100 to the combustion duct (transition piece 33) so that the direction in which the combustion duct (transition piece 33) faces the radially outer side Dro when the combustion duct (transition piece 33) is attached to the casing (stator vane shroud 50) matches the direction indicated by the first indication 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 (e.g., end 33I) of the combustion tube (transition tube 33).

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

[0047] REFERENCE SIGNS LIST 1 Gas turbine 12 Combustor 20 Turbine casing (casing) 24 Rotor (turbine shaft) 33 Transition piece (combustion duct) 33I Base end (end) 33O Tip end (end) 50 Stationary vane shroud 100 Cover member 101 First display 102 Second display 103 Third display

Claims

1. A method for installing a combustion liner in a gas turbine, comprising the steps 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 to indicate one radial side of the rotor when the combustion liner is installed in a casing that covers the outer periphery of the rotor of the gas turbine, a second marking that is displayed to indicate the vertically upward side when the combustion liner is installed in the casing, and a third marking that indicates the position of the combustion liner to be installed in the casing; attaching a hoisting tool to the combustion liner to which the cover member is installed; and attaching the combustion liner, which has been lifted using the hoisting tool, to the casing; wherein 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 the direction that the combustion liner faces in the radial direction when the combustion liner is installed in the casing coincides with the direction indicated by the first marking; In the step of attaching the hoisting device, the hoisting device is attached to the combustion tube so that when the combustion tube with the cover member attached is lifted using the hoisting device, the direction indicated by the second indication and the vertical upper side coincide.

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

3. A method for installing a combustion liner as set forth in claim 1 or 2, wherein the cover member is capable of closing the opening at the end of the one side of the combustion liner.

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