Auxiliary device for disassembling and assembling gas turbine frame

Abstract

The utility model relates to a gas turbine frame disassembly and assembly auxiliary device, and belongs to the technical field of gas turbine assembly. Comprising a connecting shaft, a frame supporting assembly and a rotor supporting assembly, and the frame supporting assembly and the rotor supporting assembly are assembled in an inserted mode through the connecting shaft. According to the utility model, the concentricity of the frame and the rotor is ensured when the frame is mounted on the rotor, and the gas turbine frame can be safely and stably dismounted from the rotor.

Description

Technical Field

[0001] The utility model relates to a gas turbine frame disassembly and assembly auxiliary device, belonging to the technical field of gas turbine assembly. Background Art

[0002] Tooling is a general term for various auxiliary machines used in the assembly and processing of mechanical parts. Appropriate tooling not only improves the efficiency of mechanical component installation, but also ensures the safety of parts and workers, and improves assembly accuracy.

[0003] like Figure 4 As shown, the gas turbine frame has many stationary seals 9 that cooperate with the rotor, as well as the outer ring of the bearing. Usually, the gap between these stator seals and the rotating seal 10 on the rotor is very small, and the gap between the outer ring of the bearing and the inner ring installed on the rotor is also very small. The stationary seals on the frame and the rotating seals on the rotor are collectively referred to as a sealing assembly. If one sealing assembly or one set of bearings (the outer ring mounted on the frame and the inner ring mounted on the rotor) are installed on the frame and rotor, installing the frame onto the rotor is relatively easy. However, if multiple sets of seals and bearings are included, installing the frame onto the rotor becomes more difficult. Generally, the gas turbine frame and rotor are designed with oil seals and air seals for the bearing cavities, as well as the bearings supported by the rotor. In particular, the middle frame, in addition to the oil seals, air seals, and bearings in the bearing cavities, also has an air seal for the unloading chamber. This makes installing the frame onto the rotor more difficult, potentially causing the stationary seals on the frame and the rotating seals on the rotor to become stuck. In severe cases, this can lead to seal failure. Therefore, the frame must be concentric with the rotor to ensure that the seals on the frame, the outer ring of the bearing, and the seals and inner ring of the bearing on the rotor do not collide with each other even in small clearances. Therefore, a gas turbine frame disassembly and assembly assist device is needed to ensure safe and smooth disassembly and assembly of the gas turbine frame from the rotor. Utility Model Content

[0004] The technical problem to be solved by the utility model is to overcome the deficiencies of the prior art and provide a gas turbine frame disassembly and assembly auxiliary device, which ensures that the frame is concentric with the rotor when the frame is installed on the rotor, and ensures that the gas turbine frame can be safely and smoothly disassembled from the rotor.

[0005] The utility model discloses a gas turbine frame disassembly and assembly auxiliary device, comprising a connecting shaft, a frame support assembly and a rotor support assembly, wherein the frame support assembly and the rotor support assembly are assembled by plugging together the connecting shaft;

[0006] The frame support assembly includes a support frame, a propulsion cylinder and a disassembly and assembly rotation shaft. The support frame and the propulsion cylinder are both installed on the gas turbine frame. The support frame and the propulsion cylinder are connected by bolts. A through hole is provided in the middle of the support frame. A bearing is provided on the support frame. The bearing is concentrically arranged with the through hole on the support frame. The disassembly and assembly rotation shaft is plugged and assembled in the bearing.

[0007] The rotor support assembly includes a drive cylinder and a guide cylinder. The drive cylinder is installed on the gas turbine rotor shaft, the guide cylinder is sleeved on the outer periphery of the drive cylinder, the connecting shaft passes through the disassembly and assembly rotating shaft, the connecting shaft and the disassembly and assembly rotating shaft are connected by threads, the bottom of the connecting shaft is connected to the drive cylinder, and the propulsion cylinder, the drive cylinder and the disassembly and assembly rotating shaft are concentrically arranged.

[0008] Install the support frame and propulsion cylinder on the gas turbine frame, install the drive cylinder and guide cylinder on the gas turbine rotor shaft, hoist the support frame assembly and the gas turbine frame above the gas turbine rotor, rotate the connecting shaft downward from the disassembly and assembly rotating shaft until the connecting shaft is connected to the drive cylinder, rotate the disassembly and assembly rotating shaft, at this time the support frame assembly and the gas turbine frame move downward, continue to rotate the disassembly and assembly rotating shaft until the gas turbine frame and the gas turbine rotor are installed in place.

[0009] The upper portion of the driving cylinder is provided with a tightening nut, which is placed above the guide cylinder and is connected to the driving cylinder through a thread. The tightening nut is used to prevent the guide cylinder from moving up and down and plays a role in limiting the guide cylinder.

[0010] The disassembly and assembly rotating shaft is installed in the bearing by cold installation. After the disassembly and assembly rotating shaft is cooled, its diameter becomes smaller, so that the disassembly and assembly rotating shaft can be easily assembled into the bearing. When the disassembly and assembly rotating shaft returns to room temperature, its outer diameter returns to its original size, thereby achieving a good fit.

[0011] The driving cylinder is connected to the gas turbine rotor via threads.

[0012] The bottom of the connecting shaft is inserted into the driving cylinder, and the bottom of the connecting shaft and the driving cylinder are fixed by a quick-release pin.

[0013] A marking line is provided on the connecting shaft. The marking line allows a visual indication of whether the gas turbine frame has been lowered into position. The support frame assembly and the gas turbine frame are moved downward by rotating the disassembly and assembly rotating shaft. The rotation continues until the marking line on the connecting shaft is flush with the upper end of the disassembly and assembly rotating shaft, indicating that the gas turbine frame and the gas turbine rotor are now in place.

[0014] Compared with the prior art, the beneficial effects of the present invention are:

[0015] (1) The present invention ensures that the frame is concentric with the rotor when the frame is installed on the rotor by arranging the propulsion cylinder, the driving cylinder and the disassembly and assembly rotation axis concentrically. By arranging the guide cylinder and the bearing, it ensures that the gas turbine frame can be safely and smoothly disassembled from the rotor.

[0016] (2) A tightening nut is provided on the upper portion of the driving cylinder. The tightening nut is placed above the guide cylinder and is connected to the driving cylinder by a thread. The tightening nut is used to prevent the guide cylinder from moving up and down and serves as a limit for the guide cylinder.

[0017] (3) A marking line is set on the connecting shaft. The marking line can intuitively tell whether the gas turbine frame has been lowered into place. Rotate the disassembly and assembly rotating shaft. At this time, the support frame assembly and the gas turbine frame move downward. Keep rotating until the marking line on the connecting shaft is flush with the upper end of the disassembly and assembly rotating shaft, indicating that the gas turbine frame and the gas turbine rotor are now installed in place. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 This is a schematic diagram of the three-dimensional structure of Example 1 of the present utility model;

[0019] Figure 2 This is a schematic diagram of the main structure of Example 1 of the utility model;

[0020] Figure 3 yes Figure 2 Schematic cross-sectional view along the AA direction;

[0021] Figure 4 It is a schematic diagram of the working structure of Example 1 of the present utility model.

[0022] In the figure: 1. Propulsion cylinder; 2. Support frame; 3. Bearing; 4. Disassembly and assembly of rotating shaft; 5. Connecting shaft; 6. Drive cylinder; 7. Guide cylinder; 8. Gas turbine frame; 9. Stationary seal; 10. Rotating seal; 11. Gas turbine rotor. DETAILED DESCRIPTION

[0023] The present invention will be further described below in conjunction with the embodiments:

[0024] Example 1

[0025] like Figures 1 to 4 As shown, the gas turbine frame disassembly and assembly auxiliary device described in the utility model includes a connecting shaft 5, a frame support assembly and a rotor support assembly, and the frame support assembly and the rotor support assembly are plugged and assembled through the connecting shaft 5;

[0026] The frame support assembly includes a support frame 2, a propulsion cylinder 1, and a disassembly and assembly rotation shaft 4. The support frame 2 and the propulsion cylinder 1 are both mounted on the gas turbine frame 8 and fixed with bolts. The support frame 2 is connected to the propulsion cylinder 1 by bolts. A through hole is provided in the middle of the support frame 2. A bearing 3 is provided on the support frame 2 and fixed with bolts. The bearing 3 is concentrically arranged with the through hole on the support frame 2. The disassembly and assembly rotation shaft 4 is plugged and assembled in the bearing 3.

[0027] The rotor support assembly includes a drive cylinder 6 and a guide cylinder 7. The drive cylinder 6 is installed on the shaft of the gas turbine rotor 11. The guide cylinder 7 is sleeved on the outer periphery of the drive cylinder 6. The connecting shaft 5 passes through the disassembly and assembly rotating shaft 4. The connecting shaft 5 is connected to the disassembly and assembly rotating shaft 4 by a thread. The bottom of the connecting shaft 5 is connected to the drive cylinder 6. The propulsion cylinder 1, the drive cylinder 6 and the disassembly and assembly rotating shaft 4 are concentrically arranged.

[0028] A tightening nut is provided on the upper portion of the driving cylinder 6 , the tightening nut is placed above the guide cylinder 7 , and the tightening nut is connected to the driving cylinder 6 through threads.

[0029] The disassembly and assembly of the rotating shaft 4 is performed by cold installation into the bearing 3 and fixed with pins.

[0030] The driving cylinder 6 is connected to the gas turbine rotor 11 through threads.

[0031] The bottom of the connecting shaft 5 is inserted into the driving cylinder 6, and the bottom of the connecting shaft 5 and the driving cylinder 6 are fixed by a quick-release pin.

[0032] A marking line is set on the connecting shaft 5.

[0033] Working process: Screw the drive cylinder 6 onto the gas turbine rotor 11 shaft, install the guide cylinder 7 onto the gas turbine rotor 11 shaft, screw the tightening nut onto the drive cylinder 6, install the bearing 3 onto the support frame 2, and fix it with bolts, cool the disassembled rotating shaft 4, install it on the bearing 3, and fix it with pins, fix the support frame 2 and the propulsion cylinder 1 with bolts to form a support frame 2 assembly, install the support frame 2 assembly onto the gas turbine frame 8, and fix it with bolts, hoist the support frame 2 assembly and the gas turbine frame 8 above the gas turbine rotor 11, rotate the connecting shaft 5 downward from the disassembled rotating shaft 4 until the connecting shaft 5 is connected to the drive cylinder 6 and fixed with a quick-release pin, rotate the disassembled rotating shaft 4, at this time the support frame 2 assembly and the gas turbine frame 8 move downward, continue to rotate the disassembled rotating shaft 4 until the marking line on the connecting shaft 5 is flush with the upper end of the disassembled rotating shaft 4, indicating that the gas turbine frame 8 and the gas turbine rotor 11 are now installed in place.

[0034] The description of the direction and relative position relationship of the structure in the present invention, such as the description of front, back, left, right, up and down, does not constitute a limitation of the present invention and is only for the convenience of description.

Claims

1. A gas turbine frame disassembly and assembly auxiliary device, characterized in that: It comprises a connecting shaft (5), a frame support assembly and a rotor support assembly, wherein the frame support assembly and the rotor support assembly are plug-connected and assembled via the connecting shaft (5); The frame support assembly comprises a support frame (2), a propulsion cylinder (1) and a disassembly and assembly rotation shaft (4); the support frame (2) and the propulsion cylinder (1) are both mounted on a gas turbine frame (8); the support frame (2) and the propulsion cylinder (1) are connected by bolts; a through hole is arranged in the middle of the support frame (2); a bearing (3) is arranged on the support frame (2); the bearing (3) and the through hole on the support frame (2) are arranged concentrically; and the disassembly and assembly rotation shaft (4) is plugged and assembled in the bearing (3); The rotor support assembly comprises a driving cylinder (6) and a guide cylinder (7), wherein the driving cylinder (6) is mounted on the shaft of the gas turbine rotor (11), the guide cylinder (7) is sleeved on the outer periphery of the driving cylinder (6), the connecting shaft (5) passes through the disassembly and assembly rotating shaft (4), the connecting shaft (5) is connected to the disassembly and assembly rotating shaft (4) by means of threads, the bottom of the connecting shaft (5) is connected to the driving cylinder (6), and the propulsion cylinder (1), the driving cylinder (6) and the disassembly and assembly rotating shaft (4) are concentrically arranged.

2. The gas turbine frame disassembly and assembly auxiliary device according to claim 1, characterized in that: A tightening nut is arranged on the upper part of the driving cylinder (6), the tightening nut is placed above the guide cylinder (7), and the tightening nut is connected to the driving cylinder (6) through threads.

3. The gas turbine frame disassembly and assembly auxiliary device according to claim 2, characterized in that: The disassembly and assembly of the rotating shaft (4) is performed by cold installation into the bearing (3).

4. The gas turbine frame disassembly and assembly auxiliary device according to claim 2, characterized in that: The driving cylinder (6) is connected to the gas turbine rotor (11) via threads.

5. The gas turbine frame disassembly and assembly auxiliary device according to claim 4, characterized in that: The bottom of the connecting shaft (5) is inserted into the driving cylinder (6), and the bottom of the connecting shaft (5) and the driving cylinder (6) are fixed by a quick-release pin.

6. The gas turbine frame disassembly and assembly auxiliary device according to any one of claims 1 to 5, characterized in that: A marking line is provided on the connecting shaft (5).

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