Method of installing a combustion cylinder

Abstract

The method for installing a combustor according to at least one embodiment of the present invention is a method for installing a combustor in a gas turbine, including the steps of installing a cover member to one side end of the combustor, the cover member having a first display to display the radial one side of a rotor when the combustor is installed in a casing covering the outer periphery of the rotor of the gas turbine, a second display to display the vertically upper side when the combustor is installed in the casing, and a third display indicating which position the combustor is installed in the casing.

Description

Technical Field

[0001] This invention relates to a method for installing a combustion chamber.

[0002] This application claims priority based on 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. Background Technology

[0003] Typically, industrial gas turbines have multiple burners arranged circumferentially spaced apart on the rotor of the gas turbine (e.g., see Patent Document 1).

[0004] Existing technical documents

[0005] Patent documents

[0006] Patent Document 1: Japanese Patent Application Publication No. 2000-107949 Summary of the Invention

[0007] The problem that the invention aims to solve

[0008] Therefore, in the respective combustion chambers of the multiple burners mounted on the gas turbine housing, the difference between the circumferential position of the combustion chamber facing the radially outer side of the gas turbine rotor and the circumferential position of the combustion chamber facing the vertically upward side varies depending on each combustion chamber.

[0009] When installing the combustor onto the gas turbine casing, the combustor is lifted. After lifting, it is difficult to adjust its circumferential position by rotating it circumferentially. Therefore, in the lifting operation, it is necessary, for example, to install lifting slings onto the combustor so that the circumferential position of the combustor, which was vertically upward when installed on the gas turbine casing, is also vertically upward when lifted.

[0010] However, it is difficult for inexperienced workers to determine the circumferential position of the combustion chamber, which is installed on the casing of a gas turbine, facing upwards in the vertical direction.

[0011] In view of the above, at least one embodiment of the present invention aims to make it relatively easy to determine the circumferential position of the combustion chamber facing the vertical direction upward when it is installed in the housing of a gas turbine.

[0012] Methods for solving problems

[0013] At least one embodiment of the present invention relates to a method for installing a combustion chamber in a gas turbine, the method comprising the following steps:

[0014] The cover component is installed on one side end of the combustion cylinder, the cover component being detachable from one side end of the combustion cylinder, and having: a first display showing the radial side of the rotor when the combustion cylinder is installed on a housing covering the outer periphery of the rotor of the gas turbine; a second display showing the vertically upward side when the combustion cylinder is installed on the housing; and a third display indicating the position of the combustion cylinder within the housing;

[0015] Install a lifting device on the combustion cylinder on which the cover component is installed; and

[0016] The combustion cylinder, lifted using the aforementioned lifting device, is then mounted onto the housing.

[0017] In the step of installing the cover component onto one side end of the combustion cylinder, the cover component is installed onto one side end of the combustion cylinder in such a manner that the direction of the combustion cylinder toward the radial side is consistent with the direction shown in the first illustration when the combustion cylinder is installed in the housing.

[0018] In the step of installing the lifting device, the lifting device is installed on the combustion cylinder in such a manner that the direction indicated by the second display is aligned with the vertical upward direction when the combustion cylinder on which the cover component is installed is lifted using the lifting device.

[0019] Invention Effects

[0020] According to at least one embodiment of the present invention, the circumferential position of the combustion chamber facing the vertical direction upward when installed in the housing of a gas turbine can be determined relatively easily. Attached Figure Description

[0021] Figure 1 This is a schematic structural diagram of a gas turbine that can be applied to the combustion chamber installation method involved in some implementation methods.

[0022] Figure 2 This is an enlarged view of the burner.

[0023] Figure 3 This is a schematic diagram used to illustrate a configuration in which multiple tail cylinders are arranged at intervals along the circumference of the rotor.

[0024] Figure 4A This is a schematic diagram of the cover component.

[0025] Figure 4B This is a schematic diagram of the cover component.

[0026] Figure 5 This diagram schematically illustrates the state in which the cover component is installed on the tailstock.

[0027] Figure 6This is a schematic diagram of a lifting strap, which is an example of a lifting device used when lifting the tailstock.

[0028] Figure 7 It is a schematic diagram showing the state of the tailstock being hoisted.

[0029] Figure 8 This is a flowchart illustrating the processing steps in the combustion chamber installation method according to some embodiments. Detailed Implementation

[0030] Hereinafter, some embodiments of the present invention will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc., of the constituent parts described as embodiments or shown in the drawings are not intended to limit the scope of the present invention, but are merely illustrative examples.

[0031] For example, expressions such as "in a certain direction", "along a certain direction", "parallel", "orthogonal", "center", "concentric" or "coaxial" indicate relative or absolute configuration. They not only indicate such configuration in a strict sense, but also indicate a state of relative displacement by angle or distance with tolerance or to the extent that the same function can be obtained.

[0032] For example, expressions such as "same," "identical," and "homogeneous" that indicate things are in the same state not only indicate the same state in a strict sense, but also indicate the state where there are differences in tolerance or degree to which the same function can be obtained.

[0033] For example, descriptions of shapes such as quadrilaterals and cylinders not only refer to quadrilaterals and cylinders in a strict geometric sense, but also include shapes with concave and convex parts, chamfers, etc., within the range where the same effect can be obtained.

[0034] On the other hand, the expression "possessing," "having," "including," "containing," or "having" a constituent element is not an exclusive expression that excludes the existence of other constituent elements.

[0035] (Regarding the structure of gas turbine 1)

[0036] Figure 1 This is a schematic structural diagram of a gas turbine that can be applied to the combustion chamber installation methods involved in some implementation methods. For example... Figure 1 As shown, the gas turbine 1 includes, in sequence from the upstream side in the direction of fluid flow, a compressor 11, a gas turbine burner (hereinafter referred to as burner) 12, a turbine 13, and an exhaust chamber 14. A generator is connected to the turbine 13, for example. The gas turbine has a rotor (turbine shaft) 24 capable of rotating about a central axis L.

[0037] In the following description, the direction extending from the compressor 11 toward the turbine 13 in the axial direction Da of the rotation center axis L of the rotor 24 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. Furthermore, the circumferential direction Dc centered on the rotation center axis L of the rotor 24 is also referred to as the circumferential Dc of the rotor 24, and the radial direction Dr centered on the rotation center axis L of the rotor 24 is also referred to as the radial direction Dr of the rotor 24.

[0038] The compressor 11 has a compressor chamber 16 connected to an air intake 15 for drawing in air and provided with an airflow path. In the compressor 11, a plurality of fixed blades 17 and rotating blades 18 are alternately arranged in the airflow path within the compressor chamber 16.

[0039] The burner 12 supplies fuel to the compressed air (combustion air) compressed by the compressor 11, causing the mixture of fuel and combustion air to burn and generate combustion gas. Multiple burners 12 are spaced apart on the circumferential Dc of the rotor 24.

[0040] The turbine 13 has a turbine housing (shell) 20, which is provided with a flow path for the gaseous fuel generated in the combustor 12 to flow into. In the turbine 13, within the flow path of the combustion gas in the turbine housing 20, a plurality of fixed blades 21 and rotating blades 22 are arranged alternately, with the upstream of the fluid combustion gas flowing downstream, i.e., towards the axial downstream side of the rotor 24.

[0041] Fixed blade 21 is supported on a portion of turbine housing 20, namely fixed blade shroud 50 (reference). Figure 2 The fixed blade shroud 50 has an internal space for the combustion gases to pass through. Fixed blades 21 are fixed within this space. Furthermore, a burner 12 is connected to the fixed blade shroud 50.

[0042] The exhaust chamber 14 has an exhaust diffuser 23 for the combustion gases that have passed through the turbine 13 to flow into.

[0043] Rotor 24 is located at the radial center of the compressor 11, burner 12, turbine 13, and exhaust chamber 14. The compressor 11 side (upstream side, Dau) end of rotor 24 is rotatably supported by bearing 25 about the rotation axis L, and the exhaust chamber 14 side (downstream side, Dad) end is rotatably supported by bearing 26 about the rotation axis L. Multiple disc plates are fixed on rotor 24, and rotating blades 18 and 22 are connected to the disc plates.

[0044] In this gas turbine 1, air drawn in from the air intake 15 of the compressor 11 is compressed by multiple fixed blades 17 and rotating blades 18 to become high-temperature / high-pressure compressed air. This compressed air is then mixed with fuel in the combustor 12 by supplying a specified amount of fuel. This mixture is burned in the combustor 12 to become combustion gas. The working fluid generated in the combustor 12, i.e., the high-temperature / high-pressure combustion gas, rotates the rotor 24 by passing through multiple fixed blades 21 and rotating blades 22 of the turbine 13. The rotation of the rotor 24 drives a generator connected to it to generate electricity. The exhaust gas passing through the rotor 24 is discharged into the atmosphere as exhaust gas.

[0045] Figure 2 This is an enlarged view of the burner. The burner 12 has a burner housing 30. The burner housing 30 has an inner cylinder 32 disposed inside the outer cylinder 31 and a tail cylinder 33 connected to the front end of the inner cylinder 32, and extends along a central axis La inclined relative to the rotational central axis L of the rotor 24. Here, in the gas turbine 1, the space between the housing 27 and the burner housing 30 is called the burner / compressor housing (hereinafter referred to as the gas / compressor housing) 34. Compressed air compressed by the compressor 11 is drawn into the gas / compressor housing 34. The compressed air drawn into the gas / compressor housing 34 flows into the inner cylinder 32 of the burner 12.

[0046] The outer cylinder 31 is fastened to the housing 27. The base end of the inner cylinder 32 is supported by the outer cylinder 31 and is positioned inside the outer cylinder 31 at predetermined intervals. A pilot nozzle 40 is provided at the center of the inner cylinder 32 along the central axis La. Around the pilot nozzle 40, a plurality of main nozzles 42 are arranged at equal intervals and parallel to the pilot nozzle 40 in a manner that surrounds the pilot nozzle 40.

[0047] (Tail tube 33)

[0048] The base end (end 33I) of the tail tube (combustion tube) 33 is formed into a cylindrical shape and connected to the front end of the inner tube 32. The cross-sectional area of ​​the tail tube 33 decreases towards the front end (end 33O) and is formed in a curved shape, opening toward the first stage fixed blade 21 of the turbine 13. The front end 33O of the tail tube 33, that is, the downstream side of the combustion gas flow, is connected to the fixed blade shroud 50.

[0049] exist Figure 2 In the diagram, arrow FG indicates the direction of combustion gas flow within the tail tube 33.

[0050] The tailstock 33 extends in the region upstream of the flow of combustion gas from the radially outer side Dro of the rotor 24 toward the radially inner side Dri and toward the axially downstream side Dad of the rotor 24, as it moves from the end 33I of the upstream side of the flow of combustion gas toward the downstream side of the flow of combustion gas.

[0051] In the region downstream of the end 33O of the tail cylinder 33, which includes the downstream side of the flow of combustion gas, the radial position of rotor 24 remains unchanged as it moves toward the downstream side of the flow of combustion gas, but extends toward the axial downstream side Dad of rotor 24.

[0052] Thus, the tail cylinder 33 is formed as an imaginary plane PV extending radially along the rotor 24, including the rotational center axis L of the rotor 24 (see reference). Figure 5 The central axis La of the inner tail cylinder 33 is bent. That is, the tail cylinder 33 is formed to be bent radially Dr along the rotor 24.

[0053] Figure 3 This is a schematic diagram illustrating the arrangement of multiple tail cylinders 33 spaced apart on the circumferential Dc of the rotor 24, which is equivalent to a view of the tail cylinders 33 when viewed from the axial downstream side Dad of the rotor 24.

[0054] For ease of explanation, Figure 3 In the middle, there are 12 tail tubes 33 spaced apart on the circumferential Dc, but the number of tail tubes 33 is not limited to 12.

[0055] Furthermore, for ease of explanation, regarding Figure 3 The circumferential Dc positions of the rotor 24 of the tail cylinder 33 are sequentially represented as position P1, position P2, ..., position P12, from the position between 12 o'clock and 1 o'clock in a clockwise direction.

[0056] As described above, since the tailstock 33 is formed to bend radially (Dr) along the rotor 24, in some embodiments of the gas turbine 1, the orientation (direction of bending) of the tailstock 33 varies depending on its installation position within the turbine housing 20 of the gas turbine 1. Therefore, in each of the tailstock 33s of the plurality of combustors 12 installed in the turbine housing 20 of the gas turbine 1, the difference between the circumferential position a1 of the tailstock 33 facing radially outward (Dro) of the rotor 24 and the circumferential position a2 of the tailstock 33 facing vertically upward varies for each tailstock 33.

[0057] When installing the tailpipe 33 into the turbine housing 20, the tailpipe 33 is lifted. At this time, after lifting the tailpipe 33, it is difficult to adjust its circumferential position by rotating it circumferentially. Therefore, in the lifting operation for the tailpipe 33, it is necessary to use, for example, lifting slings 121 (see reference...) Figure 6 It is installed on the tail tube 33 so that the circumferential position a2 of the tail tube 33 facing the upper vertical direction when it is installed in the turbine house 20 is facing the upper vertical direction when the tail tube 33 is lifted.

[0058] However, for inexperienced staff, it is difficult to determine the circumferential position a2 of the tailpipe 33, which is installed in the turbine housing 20 and faces the vertical direction upward.

[0059] Therefore, in some embodiments of the combustion tube installation method, by pre-installing the cover component 100 as described below on the tail tube 33, even inexperienced personnel can easily grasp the circumferential position a2 of the tail tube 33.

[0060] Figure 4A This is a schematic diagram of the cover component 100. As an example, it shows the cover component 100 installed on the tail cylinder 33 configured at position P1.

[0061] Figure 4B This is a schematic diagram of the cover component 100. As an example, it shows the cover component 100 installed on the tail cylinder 33 configured at position P5.

[0062] In some embodiments, the cover member 100 is a member that can be installed on one end of the tail cylinder 33 along the direction of the central axis La. For example, the cover member 100 can be a member that can be installed on the base end (end 33I) of the tail cylinder 33, and can be configured to be inserted into the interior of the tail cylinder 33 from the end 33I, with its outer edge temporarily fixed to the inner circumferential surface of the tail cylinder 33 by friction.

[0063] By designing the tail cylinder 33 to be installed at the end 33I of the tail cylinder 33, which has an opening area larger than the front end (end 33O) of the tail cylinder 33, the first display 101, the second display 102 and the third display 103 described later can be easily magnified, so that the staff can easily identify them visually.

[0064] In some embodiments, the cover member 100 is preferably capable of closing the opening at the end 33I of the tail tube 33.

[0065] The combustion tube has openings at ends 33I and 33O. Therefore, from the viewpoint of preventing foreign matter from entering the tail tube 33, it is preferable to close the openings before the tail tube 33 is installed in the turbine housing 20.

[0066] According to some embodiments, the cover component 100 can reduce the possibility of foreign matter getting into the tail tube 33.

[0067] That is, the cover component 100 preferably also functions as a protective cover to prevent foreign objects from entering the tail tube 33. In other words, the cover component 100 can be configured to display the first display 101, the second display 102 and the third display 103 described above on the protective cover.

[0068] The cover component 100 may be a wooden component, for example, which can be easily temporarily fixed by friction with the inner circumferential surface and is not likely to damage the inner circumferential surface of the tail tube 33. However, it may also be a resin component or a paper component that can be attached to the end 33I of the tail tube 33 with tape or the like.

[0069] Alternatively, the cover component 100 can be a component that can be installed at the front end (end 33O) of the tail tube 33.

[0070] Some embodiments of the cover member 100 include: a first display 101 that indicates the radial side (e.g., radially outer Dro) of the rotor 24 when the tailstock 33 is mounted in the turbine housing 20; a second display 102 that indicates the vertical upper side when the tailstock 33 is mounted in the turbine housing 20; and a third display 103 that indicates the position of the tailstock 33 in the turbine housing 20.

[0071] Figure 4A The cover component 100 shown has a first display 101, a second display 102 and a third display 103 indicating that the tail tube 33 is installed in position P1.

[0072] Figure 4B The cover component 100 shown has a first display 101, a second display 102 and a third display 103 indicating that the tail tube 33 is installed in position P5.

[0073] The first display 101 includes, for example, an arrow 101a indicating the direction of the radially outer Dro of the rotor 24, and a display 101b indicating that the direction indicated by the arrow 101a is the radially outer Dro of the rotor 24. However, the display method of the first display 101 is not limited as long as the direction of the radially outer Dro of the rotor 24 can be known. Figure 4A and Figure 4B The display method shown.

[0074] Additionally, the first display 101 can also replace arrow 101a or, together with arrow 101a, indicate the direction of the radial inner side Dri of rotor 24.

[0075] The second display 102 includes, for example, an arrow 102a indicating which direction is vertically upward, i.e., which direction should be set as vertically upward, and a display 102b indicating that the direction indicated by the arrow 102a is vertically upward. However, the first display 101 is not limited in its display method as long as it is possible to know which direction is vertically upward. Figure 4A and Figure 4B The display method shown.

[0076] Figure 5 This diagram schematically shows the state in which the cover component 100 is installed on the tail cylinder 33. For example, it shows the state in which the cover component 100 is installed on the tail cylinder 33 at position P5.

[0077] Figure 6 This is a schematic diagram of a lifting strap 121, which is an example of a lifting device used when lifting the tailstock 33.

[0078] Figure 7 This diagram schematically illustrates the state of the tailstock 33 being suspended.

[0079] For example, such as Figure 5 As shown, when the tailstock 33 is installed in the turbine housing 20, the cover member 100 is installed on the tailstock 33 such that the arrow 101a of the first display 101 points towards the radially outer direction (Dro) of the rotor 24. In addition, when the tailstock 33 is installed in the turbine housing 20, the direction towards the radially outer direction (Dro) of the rotor 24 can be easily determined by the bending direction of the tailstock 33.

[0080] (Installation method of combustion tube)

[0081] Figure 8 This is a flowchart illustrating the processing steps in the combustion chamber installation method according to some embodiments. In the combustion chamber installation method according to some embodiments, when installing the tailpipe 33, the operator follows... Figure 8 The steps shown are to install the tailstock 33 into the turbine housing 20.

[0082] Some embodiments of the combustion tube installation method include: step S1 of installing the cover component, step S3 of installing the lifting device, step S5 of lifting, and step S7 of installing the tail tube onto the housing.

[0083] (Step S1 for installing the cover component)

[0084] Step S1 of installing the cover component is to install the cover component 100, which is detachable from the base end (end 33I) of the tail cylinder 33 and has a first display 101, a second display 102, and a third display 103, onto the base end (end 33I) of the tail cylinder 33. In step S1 of installing the cover component, as follows: Figure 5As shown, when the tailstock 33 is installed in the turbine housing 20, the operator installs the cover member 100 onto the end 33I of the tailstock 33 with the arrow 101a of the first display 101 pointing towards the radially outer Dro of the rotor 24. Furthermore, as described above, the operator can easily determine the direction of the tailstock 33 towards the radially outer Dro of the rotor 24 when it is installed in the turbine housing 20 by the bending direction of the tailstock 33.

[0085] (Step S3 for installing the lifting gear)

[0086] Step S3 of installing the lifting device is the step of installing the lifting device on the combustion chamber on which the cover component 100 is installed. In step S3 of installing the lifting device, the operator, for example, installs the lifting sling 121 on the tail tube 33 during the lifting operation, so that the direction indicated by the second display 102 of the cover component 100 is vertically upward when lifting the tail tube 33.

[0087] (Lifting step S5)

[0088] The lifting step S5 is the step of lifting the tailstock 33, which has been fitted with a lifting device (e.g., sling 121) in the lifting device installation step S3. In the lifting step S5, as... Figure 7 As shown, the worker hangs one end of the lifting strap 121 on the hook 123 of the lifting device (not shown) and operates the lifting device to lift the tail cylinder 33.

[0089] (Step S7: Installing the tailpipe into the housing)

[0090] Step S7, which involves installing the tailstock 33, which is lifted using a lifting device, into the turbine housing 20, is the process of installing the tailstock 33 into the turbine housing 20. In step S7, the operator refers to the first display 101 and the third display 103 on the cover component 100 installed on the tailstock 33 and installs the end 33O of the tailstock 33 into a portion of the turbine housing 20, namely the fixed blade shroud 50, at a predetermined circumferential Dc position.

[0091] As described above, some embodiments of the combustion tube installation method include step S1 of installing the cover component, step S3 of installing the lifting device, and step S7 of installing the tail tube onto the housing.

[0092] Therefore, in step S3 of installing the lifting device, the operator can easily install the lifting device on the tail cylinder 33 so that when the tail cylinder 33 with the cover component 100 is lifted using the lifting device, the direction indicated by the second display 102 is aligned with the upper vertical direction.

[0093] In this way, the operators can relatively easily determine the circumferential position of the tailpipe 33, which is installed in the turbine housing 20 and faces upward in the vertical direction. Therefore, it is not necessary to rotate the tailpipe 33 circumferentially after hoisting it to adjust its circumferential position, thus avoiding unnecessary work that would require temporarily lowering the hoisted tailpipe 33 to the ground and rotating it circumferentially to adjust its circumferential position.

[0094] Therefore, the installation method of the combustion tube according to some embodiments can improve the installation efficiency of the tail tube 33.

[0095] In some embodiments of the combustion chamber mounting method, the direction indicated by the first display 101 may be the radially outer Dro of the rotor 24.

[0096] When observing the curved shape of the tailpipe 33, it is easier for the operator to grasp the circumferential position of the tailpipe 33 towards the rotor 24, rather than the circumferential position of the tailpipe 33 towards the radially inner side Dri when it is installed in the turbine housing 20. Therefore, according to the combustion tube installation method according to some embodiments, in step S1 of installing the cover component, it is easy to install the cover component 100 onto the tailpipe 33 so that the direction of the tailpipe 33 towards the radially outer side Dro when it is installed in the turbine housing 20 is consistent with the direction indicated by the first display 101.

[0097] The present invention is not limited to the above-described embodiments, but also includes modifications to the above-described embodiments or appropriate combinations thereof.

[0098] The contents described in the above embodiments can be understood as follows, for example.

[0099] (1) The combustion chamber installation method according to at least one embodiment of the present invention is a method for installing the combustion chamber (tail tube 33) in the gas turbine 1. The combustion chamber installation method according to at least one embodiment of the present invention includes: step S1, installing a cover member 100 to one side end (e.g., end 33I) of the combustion chamber (tail tube 33), the cover member 100 being detachable from one side end (e.g., end 33I) of the combustion chamber (tail tube 33), and having: a first display 101 to display a radial side (e.g., radially outer side Dro) of the rotor 24 when the combustion chamber (tail tube 33) is installed on a housing (fixed blade shroud 50) covering the outer periphery of the rotor 24 of the gas turbine 1. The display is shown in the following manner: a second display 102, which shows the upper vertical direction when the combustion tube (tail tube 33) is installed in the housing (fixed blade shroud 50); and a third display 103, which indicates the position of the combustion tube (tail tube 33) in the housing (fixed blade shroud 50); step S3, installing a lifting device on the combustion tube (tail tube 33) with the cover component 100 installed; and step S7, installing the combustion tube (tail tube 33) lifted by the lifting device (e.g., sling 121) into the housing (fixed blade shroud 50). In step S1, where the cover component 100 is installed on one side end (e.g., end 33I) of the combustion tube (tail tube 33), the cover component 100 is installed on one side end (e.g., end 33I) of the combustion tube (tail tube 33) such that when the combustion tube (tail tube 33) is installed on the housing (fixed blade shroud 50), the direction toward the radial side (e.g., radially outward Dro) in the combustion tube (tail tube 33) is aligned with the direction indicated by the first display 101. In step S3, where the combustion tube (tail tube 33) with the cover component 100 is lifted using a lifting device (e.g., sling 121), the lifting device (e.g., sling 121) is installed on the combustion tube (tail tube 33) such that the direction indicated by the second display 102 is aligned with the vertical direction upward.

[0100] When installing the combustion tube (tail tube 33) onto the casing (fixed blade shroud 50) of the gas turbine 1, the operation of lifting the combustion tube (tail tube 33) is performed. At this time, after lifting the combustion tube (tail tube 33), it is difficult to adjust the circumferential position by rotating the combustion tube (tail tube 33) circumferentially. Therefore, in the lifting operation for lifting the combustion tube (tail tube 33), it is necessary to install, for example, a lifting sling (e.g., sling 121) onto the combustion tube (tail tube 33) so that the circumferential position of the combustion tube (tail tube 33) facing upward in the vertical direction when installed on the casing (fixed blade shroud 50) of the gas turbine 1 is also facing upward in the vertical direction when the combustion tube (tail tube 33) is lifted.

[0101] However, it is difficult for inexperienced staff to determine the circumferential position of the combustion chamber (tail tube 33) facing the vertical direction upward when it is installed on the casing (fixed blade shroud 50) of the gas turbine 1.

[0102] According to the method described in (1) above, in step S1, when installing the cover member 100 on one side end (e.g., end 33I) of the combustion tube (tail tube 33), the cover member 100 is installed on one side end (e.g., end 33I) of the combustion tube (tail tube 33) in such a way that the direction toward either the radially inward Dri or the radially outward Dro in the combustion tube (tail tube 33) is consistent with the direction indicated by the first display 101 when the combustion tube (tail tube 33) is installed in the housing (fixed blade shroud 50). A second display 102 is displayed on the cover member 100, which is displayed in a vertically upward manner when the combustion tube (tail tube 33) is installed in the housing (fixed blade shroud 50). Therefore, in step S3 of installing the lifting device, when using the lifting device (e.g., sling 121) to lift the combustion cylinder (tail cylinder 33) with the cover component 100 installed, the lifting device (e.g., sling 121) is installed on the combustion cylinder (tail cylinder 33) so that the direction indicated by the second display 102 is aligned with the vertical direction upward, which makes it easier for the worker.

[0103] In this way, the operator can relatively easily determine the circumferential position of the combustion tube (tail tube 33) facing the vertical direction upward when it is installed on the casing (fixed blade shroud 50) of the gas turbine 1. Therefore, it is not necessary to adjust the circumferential position by rotating the combustion tube (tail tube 33) circumferentially after hoisting it, thus avoiding unnecessary work of temporarily lowering the hoisted combustion tube (tail tube 33) to the ground and rotating it circumferentially to adjust its position.

[0104] Therefore, the installation of the combustion tube (tail tube 33) can be made more efficient by using the method described in (1) above.

[0105] (2) In some embodiments, in the method described in (1) above, the radial side may be the radial outer side of the rotor 24.

[0106] When the operator observes the curved shape of the combustion tube (tail tube 33), the circumferential position of the combustion tube (tail tube 33) towards the rotor 24 is easier to grasp than the circumferential position of the combustion tube (tail tube 33) towards the radially inner side Dri when it is installed in the housing (fixed blade shroud 50). Therefore, according to the method described in (2) above, in step S1 of installing the cover member 100 on one side end (e.g., end 33I) of the combustion tube (tail tube 33), it is easier to install the cover member 100 on the combustion tube (tail tube 33) so that the direction of the combustion tube (tail tube 33) towards the radially outer side Dro in the combustion tube (tail tube 33) when it is installed in the housing (fixed blade shroud 50) is consistent with the direction indicated by the first display 101.

[0107] (3) In some embodiments, in the method described in (1) or (2) above, the cover member 100 may close the opening at one end of the combustion tube (tail tube 33) (e.g., end 33I).

[0108] Since there is an opening at one end of the combustion tube (tail tube 33) (e.g., end 33I), from the viewpoint of preventing foreign matter from entering the combustion tube (tail tube 33), it is preferable to close the opening before the fuel tube (tail tube 33) is installed in the housing (fixed blade shroud 50).

[0109] According to the method described in (3) above, the possibility of foreign matter being mixed into the combustion tube (tail tube 33) can be reduced.

[0110] Symbol explanation:

[0111] 1-Gas turbine, 12-Burner, 20-Turbine housing (casing), 24-Rotor (turbine shaft), 33-Tail tube (combustion tube), 33I-Base end (end), 33O-Front end (end), 50-Fixed blade shroud, 100-Cover component, 101-First display, 102-Second display, 103-Third display.

Claims

1. A method for installing a combustion chamber in a gas turbine, the method comprising the following steps: A cover component is installed on one side end of the combustion cylinder, the cover component being detachable from said one side end of the combustion cylinder, and having: a first display showing the radial side of the rotor when the combustion cylinder is installed on a housing covering the outer periphery of the rotor of the gas turbine; a second display showing the vertically upward side when the combustion cylinder is installed on the housing; and a third display indicating the position of the combustion cylinder within the housing; Install a lifting device on the combustion cylinder on which the cover component is installed; and The combustion cylinder, lifted using the aforementioned lifting device, is then mounted onto the housing. In the step of installing the cover component onto one side end of the combustion cylinder, the cover component is installed onto one side end of the combustion cylinder in such a manner that the direction of the combustion cylinder toward the radial side is consistent with the direction shown in the first illustration when the combustion cylinder is installed in the housing. In the step of installing the lifting device, the lifting device is installed on the combustion cylinder in such a manner that the direction indicated by the second display is aligned with the vertical upward direction when the combustion cylinder on which the cover component is installed is lifted using the lifting device.

2. The method for installing the combustion chamber according to claim 1, wherein, The radial side is the radial outer side of the rotor.

3. The method for installing the combustion chamber according to claim 1 or 2, wherein, The cover component is capable of closing the opening at one end of the combustion cylinder.

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