Gas turbine blade tip radial clearance adjusting device and method and mounting method

Abstract

The invention discloses a gas turbine blade tip radial clearance adjusting device and method and a mounting method.The device comprises a fixing ring (1), an adjusting part (2) and a cylinder jacking device (3), the adjusting part (2) surrounds the fixing ring (1) in the radial direction and is fastened, the cylinder jacking device (3) is detachably connected to the adjusting part (2), and the cylinder jacking device (3) exerts force in the radial direction of the fixing ring (1), so that the gas turbine blade tip radial clearance is adjusted. The device is used for controlling deformation of an air cylinder and adjusting blade tip radial clearances. The invention further comprises a mounting method and a gap adjusting method of the using device, the adjusting method comprises the steps that blade tip gap values are collected in real time after a test is started, if the blade tip gap values are smaller than a safety value, the cylinder deformation quantity needing to be adjusted is calculated according to the blade tip gap values in all directions of a cylinder body, and the cylinder deformation quantity is adjusted. The force application position and the force application value are calculated according to the cylinder deformation quantity, and the cylinder ejector (3) is controlled to adjust the blade tip clearance value according to the force application position and the force application value.

Description

Technical Field

[0001] The present invention relates to the field of tip clearance adjustment of heavy-duty gas turbines, and particularly to a device, method and installation method for adjusting the radial tip clearance of a gas turbine. Background Art

[0002] During the compressor test of a heavy-duty gas turbine, it is necessary to monitor the tip clearance of each stage of moving blades to prevent tip rubbing and ensure the safe progress of the gas turbine test. During the test, as the rotational speed, pressure ratio, and test duration increase, the radial clearance at the tip of the same stage of moving blades varies inconsistently in each direction. For example, the radial clearance at the bottom of the rotor decreases, while the radial clearance at the top increases; there are many possible reasons for this phenomenon. For example, transient thermal deformation of the cylinder rotor, bearing clearance changes, bearing oil film thickness changes, misalignment between the rotor and the cylinder, etc.; if there is no measure to adjust the radial tip clearance, the gas turbine test may not be able to be carried out under working conditions with a relatively high risk due to the tip clearance being less than the safe range. For example, it is impossible to collect test data at high pressure ratio points simultaneously.

[0003] In the patent document CN204783130U, a retaining ring structure and a gas turbine are disclosed, which include several fan-shaped retaining ring segments. Each retaining ring segment is provided with a mounting post, and the mounting post is connected with a fixing structure; the fixing structure includes a support cylinder, a bolt and a nut. The support cylinder is a two-stage stepped cylinder. Among them, the diameter of the first-stage stepped cylinder is larger than that of the second-stage stepped cylinder, and a stop block is provided at the bottom of the second-stage stepped cylinder; the second-stage stepped cylinder is arranged opposite to the mounting post. The bolt passes through the retaining ring segment, the mounting post and the support cylinder in sequence and is fixed by a nut; the nut is fixed inside the first-stage stepped cylinder, and a disc spring is arranged between the nut and the stop block. The disc spring is sleeved on the bolt to solve the problem that the dynamic change of the tip clearance caused by the deformation of the cylinder body needs to be adjusted during the compressor test of the gas turbine.

[0004] In the patent document US10605109B2, a movable air seal for a gas turbine engine is disclosed. The system includes an air seal segment located inside the engine casing, which is connected to the air seal segment through a drive link. The drive link passes through the engine casing; the air seal segment is connected to the drive link through a plurality of connection points, and these connection points can be fasteners, bosses or guide studs to realize the radial movement of the air seal segment; the tip clearance control system for the engine casing of a gas turbine engine includes an air seal segment inside the engine casing. The drive link passes through the engine casing, and the drive link is installed on the air seal segment; it does not solve the problem that the dynamic change of the tip clearance caused by the deformation of the cylinder body needs to be adjusted during the compressor test of the gas turbine.

[0005] In summary, neither of the above two existing patents has solved the problem that the dynamic change of the tip clearance is caused by the deformation of the cylinder block during the gas turbine compressor test, and the deformation of the cylinder block needs to be adjusted. Summary of the Invention

[0006] Based on the above technical problems, the present invention proposes a device, method and installation method for adjusting the radial clearance of the tip of a gas turbine, which solves the problem that the dynamic change of the tip clearance is caused by the deformation of the cylinder block during the gas turbine compressor test, and the deformation of the cylinder block needs to be adjusted.

[0007] To achieve the above object, the present invention proposes a device for adjusting the radial clearance of the tip of a gas turbine.

[0008] A device for adjusting the radial clearance of the tip of a gas turbine includes a fixing ring, an adjusting part and a top cylinder. The adjusting part surrounds the fixing ring radially and is fastened. The top cylinder is detachably connected to the adjusting part, and the top cylinder applies a force along the radial direction of the fixing ring to control the deformation of the cylinder and adjust the radial clearance of the tip.

[0009] Further, a plurality of the adjusting parts are arranged on the fixing ring in a uniformly distributed manner.

[0010] Further, the adjusting part includes a mounting seat, and the two mounting seats are fastened together to form the adjusting part.

[0011] Further, the mounting seat includes a connecting column, a top rod layer and a driving layer. The top rod layer and the driving layer are connected to the connecting column, and the sides of the top rod layer and the driving layer facing the connecting column form an opening of the mounting seat.

[0012] Further, the top rod layer includes a top rod groove, and the top rod groove is arranged at the edge of the top rod layer and penetrates through two surfaces of the top rod layer.

[0013] Further, the driving layer includes a driving groove, and the driving groove is arranged at the edge of the driving layer and communicates with one surface of the driving layer.

[0014] Further, the adjusting part includes a top rod hole and a driving hole, and the top rod hole is arranged at a position corresponding to the driving hole.

[0015] Further, the two top rod grooves form the top rod hole.

[0016] Further, the two driving grooves form the driving hole.

[0017] Further, the top cylinder includes a driving device and a top cylinder rod. The driving device is arranged at the bottom of the top cylinder rod and is used to drive the top cylinder rod to move along the radial direction of the fixing ring.

[0018] Further, the ejector rod hole and the ejector cylinder rod are configured to be fitted together.

[0019] Further, the driving hole and the driving device are configured to be fitted together.

[0020] Further, the fixing ring includes a fixing outer ring, which is arranged at the edge of the fixing ring and extends radially outward along the fixing ring.

[0021] Further, the fixing outer ring includes a locking groove, which is arranged at the edge of the fixing outer ring, and the locking groove and the adjusting part are configured to be fitted together.

[0022] Further, the mounting seat includes a lock block groove and an axial lock block. The lock block groove is arranged inside the ejector rod layer, and the axial lock block and the lock block groove are configured to be fitted together. The axial lock block is used to tighten the mounting seat and the fixing ring.

[0023] Further, it further includes a support seat, which is connected to the outside of the fixing ring and is used to support the fixing ring.

[0024] To achieve the above object, the present invention also proposes a method for adjusting the radial clearance of the tip of a gas turbine blade.

[0025] A method for adjusting the radial clearance of the tip of a gas turbine blade, characterized by comprising:

[0026] After starting the test, the tip clearance value collected in real time is obtained. If the tip clearance value is less than the safety value, the deformation amount of the cylinder to be adjusted is calculated according to the tip clearance values at each azimuth on the cylinder block, the force application position and the force application value are calculated according to the deformation amount of the cylinder, and the tip clearance value is adjusted by controlling the ejector cylinder according to the force application position and the force application value.

[0027] Further, it further includes:

[0028] The cylinder is axially fixed inside the fixing ring along the axis of the fixing ring. The inside of the cylinder includes a rotor and moving blades. The moving blades are arranged radially on the rotor. The tip clearance value is the radial distance from the tip of the moving blade to the inner wall of the cylinder.

[0029] Further, it further includes:

[0030] During the adjustment of the ejector cylinder, the force application value is adjusted according to the tip clearance value collected in real time until the tip clearance value is greater than the safety value, and then the clearance adjustment device is stopped.

[0031] Further, adjusting the force application value according to the tip clearance value collected in real time includes:

[0032] After obtaining the force application position and the force application value, first perform a preliminary adjustment according to the force application position and 60%-85% of the force application value, re-collect the tip clearance value, repeat the above steps to obtain the force application position and the force application value, and perform a final adjustment according to the force application position and 100% of the force application value.

[0033] To achieve the above object, an installation method of a radial clearance adjustment device for a gas turbine blade tip.

[0034] An installation method of a radial clearance adjustment device for a gas turbine blade tip, comprising:

[0035] S1: Fix the adjusting part at the radial position of the fixing ring;

[0036] S2: To embed the jacking cylinder into the adjusting part, repeat the above steps to install a plurality of the adjusting parts and the jacking cylinder, so that the circumferential angle range formed between adjacent adjusting parts is 45°-95°.

[0037] Further, the step S1 further includes:

[0038] Fix the mounting seat in the locking groove, slide the axial locking block along the locking block groove, and tighten the axial locking block and the fixing outer ring with screws.

[0039] Further, before the step S1, it further includes:

[0040] Set the fixing ring on the support seat and fix it.

[0041] Further, it further includes:

[0042] S3: Radially install the moving blade on the rotor, install a cylinder outside the rotor, and axially fix the cylinder inside the fixing ring along the fixing ring.

[0043] Based on the above technical solutions, the present invention has at least the following beneficial effects:

[0044] 1. The present invention proposes a radial clearance adjustment device, method and installation method for a gas turbine blade tip. By arranging a fixing ring, an adjusting part and a jacking cylinder outside the cylinder, an external force is applied at a reasonable position according to the detected tip clearance, and the radial clearance of the blade tip is dynamically adjusted to ensure that the tip clearance is always within the safe range during the gas turbine test process, effectively preventing the occurrence of tip rubbing, and ensuring the safe progress of the gas turbine test; at the same time, the present invention effectively avoids the phenomenon that the radial clearance of the same-stage moving blade tip becomes larger due to inconsistent changes in the radial clearance in each direction during the test process with the increase of the rotational speed, pressure ratio and test duration.

[0045] 2. The present invention provides a device, method and installation method for adjusting the radial tip clearance of a gas turbine. Under high-risk operating conditions such as high pressure ratio or stall boundary, it can monitor the tip clearance in real time, calculate the force applied by the cylinder jack according to the difference between the tip clearance and the safety value, and timely adjust the radial tip clearance to ensure the safe progress of the test under these operating conditions and avoid test interruption or equipment damage caused by too small a clearance. At the same time, the clearance adjustment device has a simple structure, is easy to process, install, disassemble and replace, reducing the maintenance cost and operation difficulty.

[0046] 3. The present invention provides a device, method and installation method for adjusting the radial tip clearance of a gas turbine. By setting a plurality of mounting seats, the cylinder jack is fixed to the fixed ring. At the same time, by setting a locking groove, an axial locking block and a locking block groove, the fixed ring and the adjusting part are firmly fixed. By setting a push rod hole and a driving hole, the cylinder jack is more stable during operation, ensuring the stability and reliability of the device during operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] The accompanying drawings forming a part of the present invention are used to provide a further understanding of the present invention. The schematic embodiments and descriptions thereof of the present invention are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0048] Figure 1 The three-dimensional structure diagram of a device for adjusting the radial tip clearance of a gas turbine according to an embodiment is shown;

[0049] Figure 2 The front view of a device for adjusting the radial tip clearance of a gas turbine according to an embodiment is shown;

[0050] Figure 3 The partial three-dimensional structure diagram of a device for adjusting the radial tip clearance of a gas turbine according to an embodiment is shown;

[0051] Figure 4 The three-dimensional structure diagram of an adjusting part according to an embodiment is shown;

[0052] Figure 5 The sectional view of an adjusting part according to an embodiment is shown;

[0053] Figure 6 The three-dimensional structure diagram of an axial locking block according to an embodiment is shown;

[0054] Figure 7 The three-dimensional structure diagram of a cylinder jack according to an embodiment is shown.

[0055] Among them, the above-mentioned drawings include the following reference numerals:

[0056] 1. Fixed ring; 2. Adjusting part; 3. Cylinder jack; 4. Support seat;

[0057] 11. Fixed outer ring; 111. Locking groove;

[0058] 21. Mounting base; 22. Ejector rod hole; 23. Driving hole; 24. Axial locking block;

[0059] 211. Connecting column; 212. Ejector rod layer; 213. Driving layer; 214. Locking block groove;

[0060] 2121. Ejector rod groove; 2131. Driving groove;

[0061] 31. Driving device; 32. Jacking cylinder rod. Detailed implementation manners

[0062] It should be noted that, without conflict, the embodiments and features in the embodiments of the present invention can be combined with each other. The present invention will be described in detail below with reference to the drawings and in combination with the embodiments.

[0063] The following further describes the present invention in detail with specific embodiments, and these embodiments should not be construed as limiting the scope claimed by the present invention. The term "comprising" indicates the presence of features when used, but does not exclude the presence or addition of one or more other features; the orientation or positional relationship indicated by terms such as "lateral", "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus cannot be construed as a limitation on the present invention; in addition, the terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0064] In the description, it should be noted that unless otherwise clearly specified and defined, the terms "mount", "connected", "connected" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be directly connected, or indirectly connected through an intermediate medium, and can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations. In addition, in the description of the present invention, unless otherwise stated, the meaning of "a plurality of" is two or more.

[0065] Embodiment

[0066] To solve the problem that in the gas turbine compressor test, the deformation of the cylinder body causes the dynamic change of the tip clearance and the deformation of the cylinder body needs to be adjusted, the present invention proposes a device, method and installation method for adjusting the radial clearance of the tip of a gas turbine.

[0067] A device for adjusting the radial clearance of the tip of a gas turbine is as Figure 1As shown in the figure, it includes a fixed ring 1, an adjusting part 2 and a top cylinder 3. The adjusting part 2 radially surrounds the fixed ring 1 and is fastened. The top cylinder 3 is detachably connected to the adjusting part 2. The top cylinder 3 exerts a force along the radial direction of the fixed ring 1 to control the deformation of the cylinder and adjust the tip radial clearance.

[0068] In the present invention, "capable of being fitted and arranged" means that two or more mechanical components can be docked together through a specific interface or joint surface design to form a complete structure or system. This setting requires the shapes, sizes and locking mechanisms of the interfaces or joint surfaces between the components to match.

[0069] In the present invention, "detachably connected" includes common connection forms such as threaded connection, snap connection, release connection, pin connection, elastic deformation connection, hinge connection, etc., which can facilitate the functions of assembling, disassembling and adjusting two or more components.

[0070] Furthermore, as Figure 2 shown in the figure is a front view of a gas turbine tip radial clearance adjusting device. In this embodiment, 4 adjusting parts 2 and 4 corresponding top cylinders 3 are evenly arranged on the fixed ring 1. The fixed ring 1 is installed and fixed on the support seat 4. In other embodiments, 6 or 8 adjusting parts 2 can also be provided.

[0071] Furthermore, as Figure 3 shown in the figure is a partial structure diagram of a gas turbine tip radial clearance adjusting device. Among them, the adjusting part 2 and the locking groove 111 on the fixed ring 1 are capable of being fitted and arranged. One side of the fixed ring is adjacent to the axial locking block 24. The axial locking block 24 and the locking block groove 214 are capable of being fitted and arranged. By adjusting the axial locking block 24 with a screw, the axial locking block 24 exerts a radial force on the fixed ring 1 to fasten the fixed ring 1; the top cylinder is fixed by a regulator so that the top cylinder 3 is arranged along the radial direction of the fixed ring 1 and its top cylinder rod 32 faces the inside of the fixed ring 1.

[0072] Furthermore, as Figure 4 shown in the figure is a three-dimensional structure diagram of the adjusting part 2, which includes 2 mounting seats 21. The mounting seat 21 includes a connecting column 211, a top rod layer 212 and a driving layer 213. The mounting seat 21 is a polygonal structure and includes an opening. The openings of the 2 mounting seats 21 are arranged corresponding to each other and can be fastened by screws and / or glue; the top rod layer 212 and the driving layer 213 are connected to the connecting column 211. The sides of the top rod layer 212 and the driving layer 213 facing the connecting column 211 form the opening of the mounting seat 21; a locking block groove 214 is provided inside the top rod layer 212 and is arranged along the circumferential direction of the fixed ring 1; the top cylinder 3 is arranged and fastened between the 2 mounting seats 21.

[0073] Furthermore, asFigure 5 The sectional view of the adjusting part is shown, in which the ejector rod layer 212 includes ejector rod grooves 2121, and two ejector rod grooves 2121 form an ejector rod hole 22, which penetrates through two surfaces of the ejector rod layer 212; the driving layer 213 includes driving grooves 2131, and two driving grooves 2131 form a driving hole 23. The driving hole 23 communicates with one surface of the driving layer 213, so that the top cylinder device 3 and the adjusting part 2 are detachably connected.

[0074] Further, as Figure 6 The three-dimensional structure diagram of the axial locking block 24 is shown. The axial locking block 24 is in the shape of an annular sector and includes two screw holes for connecting the ejector rod layer 212 and providing a radially outward force to the fixed outer ring 11 to tighten the fixing ring 1.

[0075] Further, as Figure 7 The three-dimensional structure diagram of the top cylinder device 3 is shown, which includes a driving device 31 and an ejector rod 32. The ejector rod 32 can be a multi-segment structure or a single rod. In this embodiment, a two-segment structure is selected. The ejector rod 32 is arranged on the top of the driving device 31, and the driving device 31 is used to drive the ejector rod 32 to apply a radially inward force to the cylinder, so that the cylinder deforms.

[0076] To achieve the above object, the present invention also proposes a method for adjusting the radial clearance of the tip of a gas turbine blade. Using the above-mentioned device for adjusting the radial clearance of the tip of a gas turbine blade, the method includes the following steps:

[0077] After starting the test, the tip clearance value collected in real time is obtained. If the tip clearance value is less than the safety value, the deformation amount of the cylinder to be adjusted is calculated according to the tip clearance values at each position on the cylinder block, the force application position and the force application value are calculated according to the deformation amount of the cylinder, and the top cylinder device 3 is controlled according to the force application position and the force application value to adjust the tip clearance value.

[0078] Further, the cylinder is axially fixed inside the fixing ring 1 along the axis of the fixing ring 1. The inside of the cylinder includes a rotor and moving blades. The moving blades are arranged radially on the rotor, and the tip clearance value is the radial distance from the tip of the moving blade to the inner wall of the cylinder.

[0079] Further, it further includes:

[0080] During the adjustment process of the top cylinder device 3, the force application value is adjusted according to the tip clearance value collected in real time until the tip clearance value is greater than the safety value, and then the clearance adjustment device is stopped.

[0081] Further, adjusting the force application value according to the tip clearance value collected in real time includes:

[0082] After obtaining the force application position and the force application value, first perform a preliminary adjustment according to the force application position and 60%-85% of the force application value, re-collect the tip clearance value, repeat the above steps to obtain the force application position and the force application value, and perform a final adjustment according to the force application position and 100% of the force application value.

[0083] To achieve the above object, the present invention also proposes an installation method for a tip radial clearance adjustment device of a gas turbine, including the following steps:

[0084] S1: Fix the adjusting part 2 at the radial position of the fixing ring 1;

[0085] S2: To embed the jacking cylinder 3 into the adjusting part 2, repeat the above steps to install a plurality of the adjusting parts 2 and the jacking cylinders 3, so that the circumferential angle range formed between adjacent adjusting parts 2 is 45°-95°.

[0086] Further, the step S1 further includes:

[0087] Fix the mounting seat 21 in the locking groove 111, slide the axial locking block 24 along the locking block groove 214, and tighten the axial locking block 24 and the fixed outer ring 11 with screws.

[0088] Further, before the step S1, it further includes:

[0089] Fix the fixing ring 1 on the support seat 4.

[0090] Further, in this embodiment, 4 adjusting parts 2 are evenly arranged on the fixing ring 1, so that the circumferential angle formed between adjacent adjusting parts 2 is 90°. In other embodiments, 6 or 8 adjusting parts 2 can also be arranged on the fixing ring 1, and the circumferential angle formed between adjacent adjusting parts 2 can also be 60° or 45°.

[0091] Further, it further includes:

[0092] S3: Install the moving blade radially on the rotor, install a cylinder outside the rotor, and axially fix the cylinder inside the fixing ring 1 along the fixing ring 1.

[0093] In summary, from the above description, it can be seen that the above embodiments of the present invention achieve the following technical effects:

[0094] 1. The present invention provides a device, method and installation method for adjusting the radial tip clearance of a gas turbine. By arranging a fixing ring, an adjusting part and a cylinder jack outside the cylinder, an external force is applied at a reasonable position according to the detected tip clearance to dynamically adjust the radial tip clearance of the blade, ensuring that the tip clearance is always within the safe range during the gas turbine test, effectively preventing the occurrence of tip rubbing, and ensuring the safe progress of the gas turbine test. At the same time, the present invention effectively avoids the phenomenon that the radial tip clearance of the same stage of moving blade becomes larger due to inconsistent changes in the radial tip clearance in all directions with the increase of rotational speed, pressure ratio and test duration during the test.

[0095] 2. The present invention provides a device, method and installation method for adjusting the radial tip clearance of a gas turbine. Under high-risk working conditions such as high pressure ratio or stall boundary, it can monitor the tip clearance in real time, calculate the force application value of the cylinder jack according to the difference between the tip clearance and the safety value, and timely adjust the radial tip clearance to ensure the safe progress of the test under these working conditions and avoid test interruption or equipment damage caused by too small clearance. At the same time, the clearance adjustment device has a simple structure, is convenient for machining, installation, disassembly and replacement, reducing the maintenance cost and operation difficulty.

[0096] 3. The present invention provides a device, method and installation method for adjusting the radial tip clearance of a gas turbine. The cylinder jack is fixed to the fixing ring by arranging a plurality of mounting seats. At the same time, by arranging a locking groove, an axial locking block and a locking block groove, the fixing ring and the adjusting part are firmly fixed. By arranging a push rod hole and a driving hole, the cylinder jack runs more stably during operation, ensuring the stability and reliability of the device during operation.

[0097] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

[0098] It should be noted that in this article, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variant thereof is intended to cover a non-exclusive inclusion, so that a process, method, article or device comprising a series of elements not only includes those elements, but also includes other elements not expressly listed, or elements inherent to such process, method, article or device. Without further limitation, an element defined by the statement "comprising an..." does not exclude the presence of additional identical elements in the process, method, article or device comprising the element.

[0099] It should be noted that in the description of this specification, the descriptions referring to terms such as "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

Claims

1. A gas turbine blade tip radial clearance adjustment device, characterized in that It includes a fixed ring (1), an adjusting part (2) and a top cylinder device (3). The adjusting part (2) radially surrounds the fixed ring (1) and is fastened. The top cylinder device (3) is detachably connected to the adjusting part (2). The top cylinder device (3) applies a force along the radial direction of the fixed ring (1) to control the deformation of the cylinder and adjust the tip radial clearance.

2. The device according to claim 1, characterized in that A plurality of the adjusting parts (2) are arranged on the fixed ring (1) in a uniformly distributed manner.

3. The device according to claim 2, wherein The adjusting part (2) includes a mounting seat (21), The two mounting seats (21) are fastened together to form the adjusting part (2).

4. The device according to claim 3, characterized in that, The mounting seat (21) includes a connecting column (211), a top rod layer (212) and a driving layer (213), The top rod layer (212) and the driving layer (213) are connected to the connecting column (211). The sides of the top rod layer (212) and the driving layer (213) facing the connecting column (211) make the mounting seat (21) form an opening.

5. The device according to claim 4, wherein The top rod layer (212) includes a top rod groove (2121), The top rod groove (2121) is arranged at the edge of the top rod layer (212) and penetrates through two faces of the top rod layer (212).

6. The device according to claim 5, characterized in that, The driving layer (213) includes a driving groove (2131), The driving groove (2131) is arranged at the edge of the driving layer (213) and communicates with one face of the driving layer (213).

7. The device according to claim 6, characterized in that, The adjusting part (2) includes a top rod hole (22) and a driving hole (23), The top rod hole (22) is arranged at a position corresponding to the driving hole (23).

8. The device according to claim 7, characterized in that The two top rod grooves (2121) form the top rod hole (22).

9. The device according to claim 7, characterized in that The two driving grooves (2131) form the driving hole (23).

10. The device according to claim 7, characterized in that, The top cylinder device (3) includes a driving device (31) and a top cylinder rod (32), The driving device (31) is arranged at the bottom of the top cylinder rod (32) and is used to drive the top cylinder rod (32) to move along the radial direction of the fixed ring (1).

11. The device according to claim 10, characterized in that The top rod hole (22) and the top cylinder rod (32) are arranged to be fitted with each other.

12. The device according to claim 10, characterized in that The driving hole (23) and the driving device (31) are arranged to be fitted with each other.

13. The device according to claim 4, characterized in that, The fixed ring (1) includes a fixed outer ring (11), The fixed outer ring (11) is arranged at the edge of the fixed ring (1) and extends radially outward along the fixed ring (1).

14. The device according to claim 13, characterized in that, The fixed outer ring (11) includes a locking groove (111), The locking groove (111) is arranged at the edge of the fixed outer ring (11). The locking groove (111) and the adjusting part (2) are arranged to be fitted with each other.

15. The device according to claim 14, characterized in that, The mounting seat (21) includes a locking block groove (214) and an axial locking block (24), The lock block groove (214) is arranged inside the ejector rod layer (212), and the axial lock block (24) is arranged to be engaged with the lock block groove (214). The axial lock block (24) is used to tighten the mounting seat (21) and the fixing ring (1).

16. The device according to claim 1, wherein It further includes a support seat (4). The support seat (4) is connected to the outer side of the fixing ring (1) and is used to support the fixing ring (1).

17. A method for adjusting a gas turbine tip radial clearance adjusting device according to any one of claims 1-16, characterized in that, It includes: The tip clearance value collected in real time after the test starts. If the tip clearance value is less than the safety value, calculate the deformation amount of the cylinder to be adjusted according to the tip clearance values at various positions on the cylinder block, calculate the force application position and the force application value according to the deformation amount of the cylinder, and control the jacking cylinder (3) to adjust the tip clearance value according to the force application position and the force application value.

18. The method according to claim 17, wherein It further includes: The cylinder is axially fixed inside the fixing ring (1). The inside of the cylinder includes a rotor and moving blades. The moving blades are arranged radially on the rotor. The tip clearance value is the radial distance from the tip of the moving blade to the inner wall of the cylinder.

19. The method according to claim 17, wherein It further includes: During the adjustment process of the jacking cylinder (3), adjust the force application value according to the tip clearance value collected in real time until the tip clearance value is greater than the safety value, and then stop the clearance adjustment device.

20. The method according to claim 19, wherein Adjusting the force application value according to the tip clearance value collected in real time includes: After obtaining the force application position and the force application value, first perform a preliminary adjustment according to the force application position and 60%-85% of the force application value, re-collect the tip clearance value, repeat the above steps to obtain the force application position and the force application value, and perform a final adjustment according to the force application position and 100% of the force application value.

21. An installation method of a gas turbine tip radial clearance adjusting device described in any one of claims 1-16, characterized in that, It includes: S1: Fix the adjusting part (2) at the radial position of the fixing ring (1). S2: To embed the jacking cylinder (3) into the adjusting part (2), repeat the above steps to install multiple adjusting parts (2) and jacking cylinders (3) so that the circumferential angle range formed between adjacent adjusting parts (2) is 45°-95°.

22. The method according to claim 21, wherein The step S1 further includes: Fix the mounting seat (21) in the locking groove (111), slide the axial lock block (24) along the lock block groove (214), and tighten the axial lock block (24) and the fixing outer ring (11) with screws.

23. The method according to claim 21, wherein Before the step S1, it further includes: Fix the fixing ring (1) on the support seat (4).

24. The method according to claim 21, wherein It further includes: S3: Install the moving blades radially on the rotor, install a cylinder outside the rotor, and axially fix the cylinder inside the fixing ring (1) along the fixing ring (1).

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