Manual turning gear and method for rotor of heavy-duty gas turbine

Abstract

The invention relates to the technical field of gas turbine turning, and particularly discloses a manual turning device and method for a rotor of a heavy-duty gas turbine, the manual turning device comprises a supporting mechanism, the supporting mechanism comprises a magnetic attraction seat, and a chain groove is formed in one end of the magnetic attraction seat; the driving mechanism comprises a shell, the shell is suitable for being adjacently arranged with the magnetic attraction seat, a magnetic attraction piece is arranged at one end of the shell, a rotating assembly is arranged in the shell, a transmission piece is further arranged in the shell, a connecting piece is arranged on the transmission piece, and the rotating assembly can drive the transmission piece to move; the transmission part is suitable for moving along the chain groove; through the arrangement of the driving mechanism, manual turning can be carried out by a single inspector, a large amount of manpower and material resources are saved in the heavy duty gas turbine rotor turning process, and the working efficiency is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbine cranking, in particular to a manual cranking device and method for a heavy-duty gas turbine rotor. Background Art

[0002] During routine maintenance and regular overhauls of heavy-duty gas turbines, especially operations such as borehole inspections, component disassembly, clearance measurements, and nondestructive testing, manual cranking of the heavy-duty gas turbine rotor is required, with certain rotation angle intervals. Manual cranking is achieved by installing a manual cranking device at the front end of the compressor shaft or by rotating the last-stage turbine blades in the turbine exhaust chamber.

[0003] Currently, inspectors and cranking personnel typically communicate in real time via intercom. The inspector issues cranking commands, and the cranking personnel perform cranking operations at different angles based on their experience and the inspector's stop commands. This cranking method requires the installation of a manual cranking device and the simultaneous operation of multiple personnel. Furthermore, due to the use of intercoms for remote communication and interference from factors such as rotor inertia, over-cranking or under-cranking is prone to occur, consuming significant manpower and resources. Summary of the Invention

[0004] Therefore, the technical problem to be solved by the present invention is that manual cranking consumes a lot of manpower.

[0005] The above technical problem is solved by the following technical solution: The present invention provides a heavy-duty gas turbine rotor manual turning device, which includes a support mechanism, the support mechanism includes a magnetic seat, and a chain groove is formed at one end of the magnetic seat;

[0006] The driving mechanism includes a shell, the shell is suitable for being arranged adjacent to the magnetic seat, a magnetic part is provided at one end of the shell, a rotating component is provided in the shell, a transmission part is also provided in the shell, a connecting part is provided on the transmission part, the rotating component can drive the transmission part to move, and the transmission part is suitable for moving along the chain groove.

[0007] In a preferred embodiment of the manual turning device for a heavy-duty gas turbine rotor according to the present invention: the rotating assembly includes a first gear, a first rotating shaft is provided on the first gear, the first rotating shaft is rotatably connected to the outer shell, a second gear is meshed with the first gear, a second rotating shaft is provided on the second gear, and the other end of the second rotating shaft extends to the outside of the outer shell.

[0008] In a preferred embodiment of the manual turning device for a heavy-duty gas turbine rotor according to the present invention:

[0009] The outer diameter of the first gear is greater than the outer diameter of the second gear, and the outer diameter ratio is ratio: ratio:.

[0010] In a preferred embodiment of the manual turning device for a heavy-duty gas turbine rotor according to the present invention:

[0011] The rotating assembly also includes a rocker, which is fixedly connected to the other end of the second rotating shaft; the rocker is provided with a first handpiece, which is provided at the end of the rocker away from the second rotating shaft, and a second handpiece, which is provided at the end of the rocker close to the second rotating shaft.

[0012] In a preferred embodiment of the manual turning device for a heavy-duty gas turbine rotor according to the present invention:

[0013] The first gear is adapted to be in overlap connection with the transmission member.

[0014] In a preferred embodiment of the manual turning device for a heavy-duty gas turbine rotor according to the present invention:

[0015] The driving mechanism further comprises a housing tenon, and the housing tenon is symmetrically arranged on both sides of the housing.

[0016] In a preferred embodiment of the manual turning device for a heavy-duty gas turbine rotor according to the present invention:

[0017] The supporting mechanism further includes a cover plate, and the cover plate is used to cover the chain groove.

[0018] In a preferred embodiment of the manual turning device for a heavy-duty gas turbine rotor according to the present invention:

[0019] A first slot is provided on the side wall of one side of the support mechanism, and a magnetic seat tenon is provided on the other side, and the first slot is adapted to the tenon of the housing.

[0020] In a preferred embodiment of the manual turning device for a heavy-duty gas turbine rotor according to the present invention:

[0021] The support mechanism further includes a guide wheel, which is arranged in the chain groove. The guide wheel and the cover plate are used to clamp the transmission member.

[0022] The present invention further proposes a heavy-duty gas turbine rotor manual cranking method, comprising the aforementioned heavy-duty gas turbine rotor manual cranking device, and,

[0023] Step 1: Pass the driving mechanism through the IGV blade gap and install it on the inner wall of the heavy-duty gas turbine cylinder;

[0024] Step 2: Pass the support mechanism through the IGV blade gap and fix the support mechanism and the driving mechanism adjacent to the inner wall of the heavy-duty gas turbine cylinder;

[0025] Step 3: Connect the IGV blades to the drive mechanism;

[0026] Step 4: Manually operate the driving mechanism to perform turning;

[0027] Step 5: After inspecting the blades or measuring the clearance, disconnect the IGV blades from the drive mechanism and repeat steps 1 to 4 until a full rotor turning cycle is completed.

[0028] The beneficial effects of the present invention are: through the setting of the driving mechanism, the present invention enables a single inspector to perform manual cranking. Due to the setting of the first gear and the second gear, manpower for cranking is saved. Due to the setting of the first rotating shaft and the second rotating shaft, the cranking speed is controllable. Due to the setting of the supporting mechanism, the transmission parts are sorted and guided when entering the driving mechanism, avoiding interference with the driving mechanism due to deformation of the transmission parts. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings of the embodiments of the present invention. Obviously, the drawings described below only relate to some embodiments of the present invention and are not intended to limit the present invention. Among them:

[0030] Figure 1 Shows the overall structural diagram of the device;

[0031] Figure 2 shows a schematic structural diagram of the driving mechanism;

[0032] Figure 3 Shows a schematic structural diagram of the drive mechanism without the outer shell;

[0033] Figure 4 shows a three-dimensional schematic diagram of the support mechanism;

[0034] Figure 5 A front view of the support mechanism is shown. DETAILED DESCRIPTION

[0035] In order to enable those skilled in the art to better understand the present invention, the present invention is further described in detail below with reference to specific embodiments and the accompanying drawings.

[0036] The terms used in the present invention are those commonly used in the art in view of the functions of the present invention, but these terms may vary according to the intentions of those skilled in the art, precedents, or new technologies in the art. In addition, specific terms may be selected by the applicant, and in such cases, their detailed meanings will be described in the detailed description of the present invention. Therefore, the terms used in the specification should not be understood as simple names, but rather as the meanings of the terms and the overall description of the present invention.

[0037] The present invention provides a heavy-duty gas turbine rotor manual turning device, comprising a support mechanism 1, referring to Figure 4 The support mechanism 1 is used to increase the connection strength between the driving mechanism 2 and the inner wall of the heavy-duty gas turbine cylinder, and to guide the transmission member 23. In order to enable the support mechanism 1 to better guide the transmission member 23, the support mechanism 1 is preferably set to two, which are respectively installed on both sides of the driving mechanism 2.

[0038] As an optional embodiment, refer to Figure 4 The support mechanism 1 includes a magnetic seat 11, which is set to a flat box shape with a smaller width so that it can pass through the IGV blade gap during installation. A switch 15 is set on the magnetic seat 11, and the switch 15 is used to control the magnetic seat 11 to be magnetically attracted to the inner wall of the heavy-duty gas turbine cylinder or to eliminate the magnetic attraction and remove the magnetic seat 11.

[0039] As an optional embodiment, refer to Figure 4 A chain groove 12 is provided at one end of the magnetic seat 11, and the chain groove 12 is arranged adjacent to the inner wall of the heavy-duty gas turbine cylinder.

[0040] As an optional embodiment, a guide wheel 13 is provided in the chain groove 12. In this embodiment, two guide wheels 13 are provided. The guide wheels 13 and the cover plate 16 clamp the transmission member 23 therebetween. The transmission member 23 is guided by the guide wheels 13 and the cover plate 16 to facilitate movement of the transmission member 23 into the support mechanism 1.

[0041] As an optional embodiment, refer to Figure 4 and Figure 5 A first card slot 14 is provided on the side wall of one side of the support mechanism 1. In this embodiment, the cross section of the first card slot 14 is set to be T-shaped, and a magnetic seat tenon 17 is provided on the side wall of the other side of the support mechanism 1.

[0042] When the number of support mechanisms 1 needs to be increased, the magnetic seat tenon 17 of the added support mechanism 1 can be inserted into the first card slot 14 of the original support mechanism 1 to connect the added support mechanism 1 with the original support mechanism 1.

[0043] The device also includes a driving mechanism 2, referring to Figure 2 and Figure 3 , the driving mechanism 2 is used to drive the transmission member 23 to move.

[0044] As an optional embodiment, refer to Figure 1 and Figure 2The driving mechanism 2 includes a shell 21, which is set to a flat box shape with a smaller width so that it can pass through the IGV blade gap during installation. The shell 21 is installed with shell tenons 26 on the two sides adjacent to the magnetic seat 11. The shell tenons 26 can be inserted into the first card slot 14 to fix the support mechanism 1 and the driving mechanism 2. At the same time, it is convenient to disassemble the support mechanism 1 and the driving mechanism 2.

[0045] As an optional embodiment, refer to Figure 3 A magnetic component 25 is installed in the shell 21. The magnetic component 25 is located at one end of the shell 21 and is adjacent to the inner wall of the heavy-duty gas turbine cylinder. The magnetic component 25 is configured as a magnet, which can magnetically attract the driving mechanism 2 to the inner wall of the heavy-duty gas turbine cylinder.

[0046] Furthermore, in order to improve the stability of the magnetic attraction between the driving mechanism 2 and the inner wall of the heavy-duty gas turbine cylinder, two magnetic parts 25 are provided, which are respectively located in the side walls of the outer shell 21 and the moving direction of the transmission part 23. The gap between the two magnetic parts 25 allows the transmission part 23 to pass through.

[0047] As an optional embodiment, refer to Figure 3 A rotating assembly 22 is further provided in the housing. The rotating assembly 22 is used to drive the transmission member 23 to move along the gap between the magnetic members 25. The transmission member 23 moves along the chain groove 12 at the same time.

[0048] As an optional embodiment, refer to Figure 3 The transmission member 23 is tied with a connecting member 24, which is set as a flexible long strip structure, such as a rope, belt, wire, chain, etc. The transmission member 23 is tied to the IGV blade, so that the transmission member 23 drives the IGV blade to move through the connecting member 24 to realize manual turning.

[0049] As an optional embodiment, refer to Figure 3 The rotating assembly 22 includes a first gear 221, and the first rotating shaft 226 is rotatably connected in the middle of the first gear 221, and the first rotating shaft 226 is fixedly connected to the side wall of the shell 21; the first gear 221 is meshed with a second gear 222, and the second gear 222 is fixedly connected in the middle of the second rotating shaft 227, one end of the second rotating shaft 227 is rotatably connected to the side wall of the shell 21, and the other end extends to the outside of the shell 21 and can rotate relative to the shell 21.

[0050] It should be noted that the above-mentioned fixed connection adopts existing technologies such as riveting, welding, interference fit, etc., and the rotating connection adopts existing technologies such as bearing connection, etc., which will not be described in detail here.

[0051] As an optional embodiment, refer to Figure 3The outer diameter of the first gear 221 is larger than that of the second gear 222, with the outer diameter ratio ranging from 10 to 1 to 15 to 1. Due to the large outer diameter ratio between the first gear 221 and the second gear 222, during manual cranking, the second gear 222 drives the first gear 221, i.e., the small gear drives the large gear, converting the torque of the small gear into the torque of the large gear. This improves the efficiency of the cranking operator and makes the cranking operation more labor-saving.

[0052] As an optional embodiment, refer to Figures 1 to 3 The rotating assembly 22 also includes a rocker 223, which is fixedly connected to the other end of the second rotating shaft 227, and drives the second gear 222 to rotate through the rocker 223; a first handpiece 224 is provided on the rocker 223, and the first handpiece 224 is provided on the side wall of the rocker 223 away from the second rotating shaft 227, and a second handpiece 225 is provided on the side wall of the rocker 223 close to the second rotating shaft 227.

[0053] When starting the cranking, a large rotational force is required. Rotating the rocker 223 by the first handpiece 224 utilizes the principle of leverage to reduce the manpower required to start the cranking. After starting the cranking, rotating the rocker 223 by the second handpiece 225 reduces the rotation radius of the force-generating point, thereby increasing the rotation speed of the rocker 223 and improving the cranking speed.

[0054] A portion of the first gear 221 is arranged between the two magnetic parts 25 so that the transmission part 23 passing through the two magnetic parts 25 can be connected to the first gear 221; specifically, the transmission part 23 is arranged as a chain structure, and the chain part is engaged with the first gear 221, and the transmission part 23 is driven to move by the rotation of the first gear 221.

[0055] The present invention also provides a method for manually cranking a heavy-duty gas turbine rotor, comprising the aforementioned manual cranking device for a heavy-duty gas turbine rotor, and the following steps:

[0056] Step 1: Pass the drive mechanism 2 through the IGV blade gap and install it on the inner wall of the heavy-duty gas turbine cylinder;

[0057] Specifically, the driving mechanism 2 is magnetically fixed to the inner wall of the heavy-duty gas turbine cylinder corresponding to the IGV blade that needs to be turned and tested by the magnetic attraction member 25 installed in the driving mechanism 2;

[0058] Step 2: Pass the support mechanism 1 through the gap between the IGV blades and fix the support mechanism 1 and the driving mechanism 2 adjacent to each other on the inner wall of the heavy-duty gas turbine cylinder;

[0059] Specifically, the support mechanisms 1 are installed on both sides of the drive mechanism 2. The magnetic seat tenon 17 is first snapped into the first slot 14. Then, the magnetic attraction of the magnetic seat 11 is turned on by the switch 15, and the support mechanism 1 is magnetically attracted to the inner wall of the heavy-duty gas turbine cylinder. Since the support mechanisms 1 are installed on both sides of the drive mechanism 2, the support mechanisms 1 are symmetrically arranged in two types, that is, the magnetic seat tenons 17 and the first slots 14 of the two support mechanisms 1 are symmetrically arranged.

[0060] Step 3: Connect the IGV blade to the drive mechanism 2;

[0061] Specifically, by tying the other end of the connector 24 to the IGV blade, the IGV blade and the drive mechanism 2 can be synchronized.

[0062] Step 4: Manually operate the drive mechanism 2 to turn the gear;

[0063] Specifically, by shaking the rocker 223, the rotating assembly 22 drives the blade to move through the connecting piece 24; continuing to shake the rocker 223, manual turning is achieved;

[0064] Furthermore, the cranking is started by shaking the rocker 223 through the first hand piece 224 , and after the cranking is started, the rocker 223 is continued to be shaken using the second hand piece 225 to reduce the cranking speed, thereby achieving controllable cranking speed.

[0065] Step 5: After inspecting the blades or measuring the clearance, disconnect the IGV blades from the drive mechanism 2 and repeat steps 1 to 4 until a full rotor turning cycle is completed.

[0066] Specifically, after inspecting the blades or measuring the clearance, the connector 24 is untied from the IGV blades, and the transmission member 23 is returned to its pre-cranking position within the drive mechanism 2. Steps 1 through 4 are repeated until a full rotor cranking cycle is completed. It should be noted that when using this device for cranking, the cranking distance is 20 to 30 cm per turn, as long as the distance between the two sides of the transmission member 23 exposed from the support mechanism 1 is greater than 30 cm before each cranking cycle.

[0067] Through the setting of the drive mechanism 2, the present invention enables a single inspector to perform manual cranking. Due to the setting of the first gear 221 and the second gear 222, manpower for cranking is saved. Due to the setting of the first rotating shaft 226 and the second rotating shaft 227, the cranking speed is controllable. Due to the setting of the support mechanism 1, the transmission member 23 is sorted and guided when entering the drive mechanism 2, avoiding interference with the drive mechanism 2 due to deformation of the transmission member 23.

[0068] In summary, the arrangement of the present invention saves a lot of manpower and material resources during the turning process of the heavy-duty gas turbine rotor and improves work efficiency.

[0069] Finally, it should be pointed out that the methods and devices described in detail above are merely embodiments, and those skilled in the art can modify these embodiments in different ways without departing from the scope of the present invention.

Claims

1. A manual turning device for a heavy-duty gas turbine rotor, characterized by: include, A support mechanism (1), the support mechanism (1) comprising a magnetic seat (11), one end of the magnetic seat (11) being provided with a chain slot (12); A driving mechanism (2) includes a housing (21), the housing (21) is suitable for being arranged adjacent to a magnetic seat (11), a magnetic member (25) is provided at one end of the housing (21), a rotating assembly (22) is provided in the housing, a transmission member (23) is further provided in the housing (21), a connecting member (24) is provided on the transmission member (23), the rotating assembly (22) can drive the transmission member (23) to move, and the transmission member (23) is suitable for moving along the chain groove (12).

2. The heavy-duty gas turbine rotor manual turning device according to claim 1, characterized in that: The rotating assembly (22) includes a first gear (221), a first rotating shaft (226) is provided on the first gear (221), the first rotating shaft (226) is rotatably connected to the housing (21), a second gear (222) is meshed with the first gear (221), a second rotating shaft (227) is provided on the second gear (222), and the other end of the second rotating shaft (227) is extended and provided outside the housing (21).

3. The heavy-duty gas turbine rotor manual turning device according to claim 2, characterized in that: The outer diameter of the first gear (221) is greater than the outer diameter of the second gear (222), and the outer diameter ratio is 10:1 to 15:

1.

4. The heavy-duty gas turbine rotor manual turning device according to claim 2 or 3, characterized in that: The rotating assembly (22) further comprises a rocking arm (223), wherein the rocking arm (223) is fixedly connected to the other end of the second rotating shaft (227); a first hand piece (224) is provided on the rocking arm (223), wherein the first hand piece (224) is provided at one end of the rocking arm (223) away from the second rotating shaft (227), and a second hand piece (225) is provided at one end of the rocking arm (223) close to the second rotating shaft (227).

5. The heavy-duty gas turbine rotor manual turning device according to claim 4, characterized in that: The first gear (221) is suitable for overlapping with the transmission member (23).

6. The heavy-duty gas turbine rotor manual turning device according to claim 1, characterized in that: The driving mechanism (2) further comprises a housing tenon (26), wherein the housing tenon (26) is symmetrically arranged on both sides of the housing (21).

7. The heavy-duty gas turbine rotor manual turning device according to claim 1, characterized in that: The support mechanism (1) further comprises a cover plate (16), and the cover plate (16) is used to cover the chain slot (12).

8. The heavy-duty gas turbine rotor manual turning device according to claim 7, characterized in that: A first slot (14) is provided on the side wall of one side of the support mechanism (1), and a magnetic seat tenon (17) is provided on the other side. The first slot (14) is adapted to the housing tenon (26).

9. The heavy-duty gas turbine rotor manual turning device according to any one of claims 6 to 8, characterized in that: The support mechanism (1) further comprises a guide wheel (13), wherein the guide wheel (13) is arranged in the chain groove (12), and the guide wheel (13) and the cover plate (16) are used to clamp the transmission member (23).

10. A method for manually turning a heavy-duty gas turbine rotor, characterized in that: The invention comprises the manual turning device for a heavy-duty gas turbine rotor according to any one of claims 1 to 9, and Step 1: The driving mechanism (2) is passed through the IGV blade gap and installed on the inner wall of the heavy-duty gas turbine cylinder; Step 2: Pass the support mechanism (1) through the IGV blade gap, and fix the support mechanism (1) and the driving mechanism (2) adjacent to each other on the inner wall of the heavy-duty gas turbine cylinder; Step 3: Connect the IGV blades to the driving mechanism (2); Step 4: manually operate the driving mechanism (2) to perform turning; Step 5: After the blades are inspected or the clearance is measured, the connection between the IGV blades and the drive mechanism (2) is released, and steps 1 to 4 are repeated until a full turn of the rotor is completed.

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