CN113756883A - Active control device and method for gas turbine blade top clearance - Google Patents
Active control device and method for gas turbine blade top clearance Download PDFInfo
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- CN113756883A CN113756883A CN202111131944.9A CN202111131944A CN113756883A CN 113756883 A CN113756883 A CN 113756883A CN 202111131944 A CN202111131944 A CN 202111131944A CN 113756883 A CN113756883 A CN 113756883A
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- 238000000034 method Methods 0.000 title claims description 12
- 230000009471 action Effects 0.000 claims abstract description 3
- 238000007789 sealing Methods 0.000 claims description 24
- 238000001816 cooling Methods 0.000 claims description 22
- 230000000694 effects Effects 0.000 claims description 11
- 239000000314 lubricant Substances 0.000 claims description 7
- 125000006850 spacer group Chemical group 0.000 claims description 5
- 239000004519 grease Substances 0.000 claims description 4
- CWQXQMHSOZUFJS-UHFFFAOYSA-N molybdenum disulfide Chemical group S=[Mo]=S CWQXQMHSOZUFJS-UHFFFAOYSA-N 0.000 claims description 4
- 229910052982 molybdenum disulfide Inorganic materials 0.000 claims description 4
- 230000007246 mechanism Effects 0.000 description 5
- 230000008569 process Effects 0.000 description 5
- 229910001285 shape-memory alloy Inorganic materials 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000010720 hydraulic oil Substances 0.000 description 2
- 230000001050 lubricating effect Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005065 mining Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a gas turbine blade top gap active control device which comprises a turbine cylinder, a turbine moving blade and a first turbine holding ring, wherein the turbine cylinder, the turbine moving blade and the first turbine holding ring are coaxially arranged, the turbine cylinder is connected with the first turbine holding ring, the first turbine holding ring bears the turbine moving blade, a gap is formed between the first turbine holding ring and the top of the turbine moving blade, the gas turbine blade top gap active control device also comprises a gap adjusting device for adjusting the gap, the first turbine holding ring moves under the action of the gap adjusting device under a first working condition, and the first turbine holding ring and the gap adjusting device return to the original position under a second working condition. According to the invention, the turbine supporting ring is moved to the exhaust side after the gas turbine reaches full load so as to reduce the top clearance of the turbine movable blade, so that the problem that the current heavy gas turbine cannot dynamically control the blade top clearance at the start-stop stage and the full load operation stage is solved.
Description
Technical Field
The invention relates to the field of gas turbines, in particular to a device and a method for actively controlling a blade top clearance of a gas turbine.
Background
The top clearance of the turbine moving blade of the heavy-duty gas turbine varies with different operating conditions, generally speaking, in a hot start or load-raising stage of the gas turbine, the turbine moving blade and the turbine retaining ring are most likely to be worn, and generally, the top clearance value set according to the operating condition requirements of the stage is large. When the gas turbine runs at full load, the smaller the blade top clearance is, the higher the efficiency of the turbine is. Therefore, the large blade tip clearance value set based on the hot start or the load-rise working condition causes low turbine output and low efficiency during full-load movement; if the clearance value of the blade top is directly reduced, the safe operation of the unit at the starting or load-increasing stage cannot be ensured.
In the prior art, two main technical means are used for solving the contradiction, one is that the gap at the top of the turbine movable blade is reduced by moving the rotor to the air inlet side in the full load stage, the technology has the defects that a flow passage of the gas compressor has taper, the gap at the top of the turbine movable blade is reduced while the gap at the top of the turbine movable blade is increased in the process of moving the rotor, and the efficiency of the gas compressor is reduced; another technical means is to control the deformation of the turbine rotor blade by controlling the temperature of the turbine support ring to reduce the tip clearance of the turbine rotor blade, and the temperature control of the turbine support ring is mainly realized by manufacturing a hollow cooling channel on the turbine cylinder, and cooling air is introduced into the turbine cylinder through the cooling channel or the turbine support ring is directly cooled by the cooling air, and the technology has the defect that the requirement for the cooling air quantity is large. For example, chinese patent CN102112703A discloses a gas turbine facility in which an air system used for cooling a second-stage turbine stator vane includes a cooler that forms a cooling air flow path through a cooling blade ring and controls the clearance between the thermal expansion adjustment of the blade ring and the tip of the blade, so that the tip clearance required for the first-stage turbine rotor blade is ensured at the time of starting the facility and the active clearance control for realizing the minimum tip clearance at the time of load operation is possible.
At present, patent CN112160800A discloses an active control device for blade tip clearance of an axial flow gas turbine, which includes a compressor cylinder, a memory alloy mechanism, a compressor moving blade and an active control mechanism, wherein a groove is formed on the surface of the inner wall of the compressor cylinder along the circumferential direction of the inner wall, the memory alloy mechanism is slidably mounted in the groove along the circumferential direction of the inner wall of the compressor cylinder, the active control mechanism includes a cooling fan, a heating resistance wire and a thermocouple sensor, and the active control mechanism controls the blade tip clearance by controlling the deformation temperature of a memory alloy piece. According to the blade top clearance active control scheme, the shape of the memory alloy still needs to be controlled by means of a cooling fan, the cooling air quantity is greatly required, and the energy consumption of blade top clearance control is large. In summary, there is still a need for a technical solution related to active control of the tip clearance, so as to solve the problem that the current heavy-duty gas turbine cannot dynamically control the tip clearance in the start-stop stage and the full-load operation stage, and reduce the control cost and energy consumption.
The present invention has been made in view of the above problems.
Disclosure of Invention
The invention mainly aims to provide a device and a method for actively controlling the blade top clearance of a gas turbine, which are used for solving the problem that a heavy-duty gas turbine in the prior art cannot be dynamically controlled in a start-stop stage and a full-load operation stage.
In order to achieve the above object, according to one aspect of the present invention, there is provided an active control device for a blade tip clearance of a gas turbine, including a turbine cylinder, a turbine moving blade, and a first turbine retaining ring, where the turbine cylinder, the turbine moving blade, and the first turbine retaining ring are coaxially disposed, the turbine cylinder is connected to the first turbine retaining ring, the first turbine retaining ring carries the turbine moving blade, and a clearance is provided between the first turbine retaining ring and the top of the turbine moving blade.
Further, the gap adjusting device can push the first turbine holding ring to move.
Further, the first turbine holder ring may be moved in the axial direction by the gap adjusting means.
Further, the gap adjusting means includes a plurality of power means.
Further, a plurality of power devices are evenly distributed along the circumferential direction.
Further, the power device is fixed on one side of the turbine cylinder close to the axis along the circumferential direction.
Further, the power device is a thrust hydraulic cylinder.
Furthermore, the thrust hydraulic cylinder is a double-piston-rod equal-stroke constant-speed hydraulic cylinder.
Furthermore, the number of the power devices is 6-8.
To achieve the above object, according to one aspect of the present invention, there is provided a turbine cylinder and a first turbine retainer ring that are relatively movable by a power plant.
Further, the turbine cylinder and the first turbine retaining ring can move relatively along the axial direction under the action of the power device.
To achieve the above object, according to one aspect of the present invention, there is provided a blade cooling air chamber between a turbine cylinder and a first turbine retainer ring.
Further, a first sealing assembly is arranged in the blade cooling air cavity and used for preventing cold air leakage when the turbine cylinder and the first turbine holding ring move relatively.
Further, the first seal assembly is a seal ring.
Further, the top of the sealing ring is of a spherical structure.
To achieve the above object, according to one aspect of the present invention, there is provided a turbine cylinder and a first turbine retainer ring both having a horizontally split structure.
Furthermore, a cushion block used for fixing the joint of the turbine cylinder and the first turbine supporting ring is arranged at the connecting position of the turbine cylinder and the first turbine supporting ring.
Further, the cushion block is located at the connection position of the turbine cylinder and the first turbine retaining ring along the circumferential direction.
Furthermore, the connecting position of the turbine cylinder and the first turbine retaining ring is also provided with an adjusting gasket.
Further, the thickness of the spacer can be adjusted.
Furthermore, the connecting positions of the turbine cylinders and the first turbine retaining ring are uniformly distributed along the circumferential direction.
Furthermore, the number of the connecting positions of the turbine cylinder and the first turbine retaining ring is 2-5.
Furthermore, a through hole is formed in the connecting position of the turbine cylinder and the first turbine retaining ring along the radial direction.
Further, the lubricant is injected into the connection gap between the turbine cylinder and the first turbine retainer ring through the through hole.
Further, the lubricant is molybdenum disulfide grease.
In order to achieve the above object, according to one aspect of the present invention, there is provided a turbine cylinder fixed to a first turbine retaining ring by a second turbine retaining ring connected to the turbine cylinder in a radial direction, the second turbine retaining ring being connected to the first turbine retaining ring in an axial direction.
Further, a second sealing assembly is arranged between the second turbine retaining ring and the first turbine retaining ring and used for sealing between the second turbine retaining ring and the first turbine retaining ring.
In order to achieve the above object, according to an aspect of the present invention, there is provided a method for actively controlling a turbine blade tip clearance by using the above active control device for a turbine blade tip clearance, in which when a gas turbine is in a first operating condition, a power device pushes a first turbine flat ring to move axially to reduce the turbine blade tip clearance, and when the gas turbine is in a second operating condition, the power device and the first turbine flat ring are returned to increase the turbine blade tip clearance.
Further, when the gas turbine is in the first working condition, the power device pushes the first turbine supporting ring to move towards the exhaust side along the axial direction, and therefore the top clearance of the turbine movable blades is reduced.
In order to achieve the above object, according to one aspect of the present invention, there is provided a gas turbine including the above gas turbine blade tip clearance active control apparatus.
By applying the technical scheme of the invention, the top clearance of the turbine movable blades is reduced by moving the turbine retaining ring to the exhaust side after the heavy gas turbine reaches full load, so that the heavy gas turbine keeps a smaller clearance as far as possible during full load operation, the output and the efficiency of the unit are improved, and meanwhile, the heavy gas turbine can keep a larger turbine clearance in the processes of cold/hot starting, speed raising and load raising, and the safety of the unit is ensured. The invention also provides a design scheme for sealing through the sealing ring structure, so that when the first turbine retaining ring and the turbine cylinder move relatively, the cooling air chamber of the turbine blade does not leak cold air. The invention also provides a design scheme for fixing the turbine cylinder and the first turbine retaining ring, and the turbine cylinder and the first turbine retaining ring are ensured to be connected safely and reliably by technical means such as the design of the connecting position and the use of an adjusting gasket.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 illustrates a schematic diagram of a turbine bucket tip clearance control architecture according to an embodiment of the present invention; and
FIG. 2 illustrates a schematic cross-sectional view of a turbine cylinder coupled to a first turbine retainer ring in accordance with an embodiment of the present invention; and
FIG. 3 is a schematic diagram of a turbine cylinder and first turbine retaining ring top/bottom position connection according to an embodiment of the present invention; and
FIG. 4 is a schematic illustration of a turbine cylinder horizontal attachment configuration to a first turbine retaining ring in accordance with an embodiment of the present invention; and
FIG. 5 illustrates a schematic diagram of a cooling air plenum seal ring structure in accordance with an embodiment of the present invention; and
fig. 6 shows a schematic view of a structure of a thrust hydraulic cylinder according to an embodiment of the present invention.
Wherein the figures include the following reference numerals:
1. a first turbine support ring; 2. a second seal assembly; 3. a first seal assembly; 4. a turbine cylinder; 5. a second turbine support ring; 6. a thrust hydraulic cylinder; 7. moving blades of a turbine; 8. cushion blocks; 9. adjusting the gasket; 10. a piston rod; 11. a hydraulic oil pipe; 12. a hydraulic oil chamber; 13. a hydraulic cylinder block; 14. a first stage turbine rotor blade; 15. a second stage turbine rotor blade; 16. a third stage turbine rotor blade; 17. a fourth stage turbine rotor blade; 18. a turbine stator vane.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
The present invention is described in further detail below with reference to specific examples, which are not to be construed as limiting the scope of the invention as claimed. The term "comprising" when used indicates the presence of a feature but does not preclude the presence or addition of one or more other features.
As shown in fig. 1, a turbine of a heavy-duty gas turbine generally includes a turbine cylinder 4, turbine moving blades 7 and a first turbine supporting ring 1, the turbine cylinder 4, the turbine moving blades 7 and the first turbine supporting ring 1 are coaxially arranged, the turbine cylinder 4 is connected to the first turbine supporting ring 1, the first turbine supporting ring 1 carries the turbine moving blades 7, and a gap is provided between the first turbine supporting ring 1 and the top of the turbine moving blades 7. Considering that the turbine moving blade 7 and the first turbine shroud 1 are most likely to be subjected to rub-in during the hot start or load-up phase, the tip clearance is required to be set to a large clearance value in accordance with the hot start or load-up phase; during the full-load operation stage of the unit, the top clearance needs to be set to a smaller clearance value so as to ensure the high efficiency of the turbine.
In order to meet the requirements of different top clearances in the hot start or load rise stage and the full load operation stage at the same time, the invention provides the active control device for the blade top clearance of the gas turbine, which also comprises a clearance adjusting device for adjusting the clearance, and the clearance adjusting device adjusts the blade top clearance value under different working conditions, so that the heavy gas turbine keeps a smaller clearance as far as possible when in full load operation, the output and the efficiency of a unit are improved, and meanwhile, the heavy gas turbine can keep a larger turbine clearance in the cold/hot start, speed rise and load rise processes, and the safety of the unit is ensured.
The embodiment provides an active control device for the blade top clearance of a gas turbine, which comprises the turbine cylinder 4, the turbine moving blade 7 and the first turbine retaining ring 1, and a clearance adjusting device for adjusting the clearance. The clearance adjusting device acts on the first turbine retaining ring 1 under a first working condition, namely when the heavy-duty combustion engine runs at full load, and the first turbine retaining ring 1 moves to reduce the clearance value of the blade top; under the second working condition, namely before cold/hot start, speed and load increase and load reduction, the first turbine retaining ring 1 and the clearance adjusting device are reset, and the clearance value of the blade top is increased, so that the operations of starting up, stopping and the like can be safely and smoothly completed. Specifically, by utilizing the characteristic of the taper of the turbine runner, the clearance adjusting device pushes the first turbine retaining ring 1 to move under the first industrial and mining area, so that the blade top clearance of the 1-4 stages of turbine moving blades 7 is reduced, and the output and the efficiency of the unit are improved. Preferably, the first turbine holder ring 1 is moved in the axial direction by the gap adjusting means. Further preferably, the moving direction of the first turbine rotor blade 1 is the axial direction toward the exhaust side (i.e., the axial direction away from the second turbine rotor blade 5) so as to reduce the tip clearance of the turbine rotor blade 7.
In order to ensure the realization effect of the movement, the clearance adjusting device is composed of a plurality of power devices which are uniformly distributed along the circumferential direction. Preferably, the plurality of power units are circumferentially fixed on the side of the turbine cylinder 4 close to the axial center, so as to ensure that the power units can directly contact with the first turbine retaining ring 1 and act on the first turbine retaining ring to move the first turbine retaining ring under the first working condition.
As shown in fig. 6, the plurality of power units in the present embodiment are thrust hydraulic cylinders 6. Preferably, the thrust hydraulic cylinder 6 is a double-piston equal-stroke constant-speed hydraulic cylinder. More preferably, the plurality of power devices are 6 to 8 thrust hydraulic cylinders 6 distributed along the circumferential direction.
In the present embodiment, a blade cooling air chamber is provided between the turbine cylinder 4 and the first turbine retainer ring 1. In the first operating condition, when the plurality of thrust hydraulic cylinders 6 push the first turbine retaining ring 1 to move axially, the turbine cylinder 4 and the first turbine retaining ring 1 may move relatively, and specifically, the turbine cylinder 4 and the first turbine retaining ring 1 may move relatively axially in the first operating condition, which may cause leakage of cold air in the blade cooling air chamber. In order to avoid the cold air leakage situation, the present embodiment is provided with the first seal assembly 3 in the blade cooling air chamber. In order to ensure the sealing effect, the first sealing assembly 3 is preferably a sealing ring, as shown in fig. 5. By sealing with the sealing ring as shown in fig. 5, preferably the top of the sealing ring is a spherical structure, that is, the inner side and the outer side of the sealing ring are in a spherical structure, it can be realized that the good sealing effect can be achieved after the turbine cylinder 4 and the first turbine retaining ring 1 move relatively.
The present exemplary embodiment also provides a fastening between the turbine cylinder 4 and the first turbine retaining ring 1. Specifically, the turbine cylinder 4 and the first turbine retaining ring 1 are both in a horizontal split structure, and the turbine cylinder 4 and the first turbine retaining ring 1 are coaxially arranged. In order to ensure a secure and reliable connection between the turbine cylinder 4 and the first turbine retaining ring 1 and to ensure a concentric coaxial arrangement, the present embodiment achieves the above-mentioned connection effect by providing a spacer 8 at the connection location thereof, as shown in fig. 2. Preferably, the spacer 8 is located at the connection between the turbine cylinder 4 and the first turbine retaining ring 1 along the circumferential direction. Further preferably, the connections are evenly and symmetrically distributed in the circumferential direction. In order to further achieve accurate adjustment, as shown in fig. 4, in this embodiment, an adjusting shim 9 is further provided at the connection between the turbine cylinder 4 and the first turbine retaining ring 1. Preferably, the thickness of the above-mentioned spacer 9 is adjustable. Specifically, the thickness of the shim 9 can be adjusted by grinding to achieve concentricity of the turbine cylinder 4 and the first turbine retainer ring 1 by precise adjustment. In order to improve the fixing effect, it is further preferable that the number of connection positions of the turbine cylinder 4 and the first turbine retaining ring 1 is 2 to 5.
In order to ensure smooth movement of the first turbine retainer ring 1 and reduce wear caused by relative movement, the present embodiment also provides a lubrication scheme between the first turbine retainer ring 1 and the turbine cylinder 4. Specifically, a through hole is provided in the radial direction at the junction of the turbine cylinder 4 and the first turbine retainer ring 1. The lubricant is injected into the connection gap between the turbine cylinder 4 and the first turbine retainer ring 1 through the through hole. In order to enhance the lubricating effect, the lubricant is preferably molybdenum disulfide grease.
As shown in fig. 1, in addition to the above-described fixing scheme, the turbine cylinder 4 and the first turbine retaining ring 1 are fixed by a second turbine retaining ring 5, and the second turbine retaining ring 5 is connected to the turbine cylinder 4 in the radial direction and to the first turbine retaining ring 1 in the axial direction. The above-mentioned junction also has the sealing problem, so there is the second seal assembly 2 between the above-mentioned second turbine holding ring 5 and first turbine holding ring 1, guarantee the sealed effect between first turbine holding ring 1 and the second turbine holding ring 5 through this second seal assembly 2, in order to further guarantee the safe operation of the unit.
From the above description, it can be seen that the above-described embodiments of the present invention achieve the following technical effects:
1. according to the active control device for the blade top clearance of the gas turbine, provided by the invention, the clearance at the top of the turbine movable blade is controlled by utilizing the taper of the turbine runner and pushing the first turbine retaining ring to move by taking the thrust hydraulic cylinder as a power device, so that a small clearance is kept as far as possible when the heavy gas turbine runs at full load, the output and the efficiency of a unit are improved, meanwhile, a large turbine clearance can be kept in the processes of cold/hot starting, speed raising and load raising of the heavy gas turbine, and the safety of the unit is ensured.
2. According to the sealing design scheme provided by the invention, the sealing ring is arranged in the blade cooling air cavity, so that the risk of cold air leakage of the blade cooling air cavity caused by the relative movement of the first turbine supporting ring and the turbine cylinder in the movement process of the first turbine supporting ring can be reduced, and the running safety of a unit is ensured.
3. The invention provides a design scheme for fixing the turbine cylinder and the first turbine retaining ring, and the connection between the turbine cylinder and the first turbine retaining ring is ensured to be safe and reliable by using the connecting positions uniformly distributed in the circumferential direction and the cushion blocks and the adjusting gaskets, the concentric coaxial arrangement of the turbine cylinder and the first turbine retaining ring is continuously maintained, and the operation safety of a unit is improved.
4. In order to increase the fixing effect between the turbine cylinder and the first turbine supporting ring, the invention also provides a design scheme for connecting the turbine cylinder and the first turbine supporting ring through the second turbine supporting ring, and the sealing effect is improved by utilizing the sealing assembly.
5. The invention also provides a design scheme that a through hole for injecting lubricant is arranged at the joint of the turbine cylinder and the first turbine retaining ring, and the first turbine retaining ring is ensured to move smoothly in a high-temperature environment by using molybdenum disulfide lubricating grease, so that the abrasion caused by relative movement of the first turbine retaining ring and the turbine cylinder is reduced, and the overall reliability and safety are improved.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (30)
1. The active control device for the blade top clearance of the gas turbine comprises a turbine cylinder (4), a turbine moving blade (7) and a first turbine supporting ring (1), wherein the turbine cylinder (4), the turbine moving blade (7) and the first turbine supporting ring (1) are coaxially arranged, the turbine cylinder (4) is connected with the first turbine supporting ring (1), the first turbine supporting ring (1) bears the turbine moving blade (7), and a clearance is arranged between the first turbine supporting ring (1) and the top of the turbine moving blade (7).
2. Active control device of the gas turbine blade tip clearance according to claim 1, characterized in that the clearance adjustment device can push the first turbine blade tip ring (1) to move.
3. Active control device of the gas turbine blade tip clearance according to claim 2, characterized in that the first turbine blade tip clearance ring (1) is axially displaceable under the effect of the clearance adjustment device.
4. The active gas turbine tip clearance control device of claim 1, wherein the clearance adjustment device comprises a plurality of power plants.
5. The active gas turbine tip clearance control device of claim 4, wherein the plurality of power plants are evenly distributed circumferentially.
6. The active control device for the blade tip clearance of the gas turbine according to claim 5, wherein the power device is circumferentially fixed on one side of the turbine cylinder (4) close to the shaft center.
7. Active control device of the gas turbine blade tip clearance according to claim 6, characterized in that the power device is a thrust hydraulic cylinder (6).
8. Active control device of the gas turbine blade tip clearance according to claim 7, characterized in that the thrust hydraulic cylinder (6) is a double-piston-rod equal-stroke constant-velocity hydraulic cylinder.
9. The active control device for the tip clearance of a gas turbine according to claim 4, wherein the number of the plurality of power units is 6 to 8.
10. Active control device of the gas turbine blade tip clearance according to any of the claims 1 to 9, characterized in that the turbine cylinder (4) and the first turbine retaining ring (1) are movable relative to each other under the effect of the power plant.
11. The active control device for the blade tip clearance of the gas turbine according to claim 10, wherein the turbine cylinder (4) and the first turbine supporting ring (1) are relatively movable in the axial direction under the action of the power device.
12. Active control device of the gas turbine blade tip clearance according to any of the claims 1 to 9, characterized in that between the turbine cylinder (4) and the first turbine retaining ring (1) there is a blade cooling air chamber.
13. The active control device for the blade tip clearance of a gas turbine according to claim 12, wherein a first sealing assembly (3) is provided in the blade cooling air chamber, and the first sealing assembly (3) is used for preventing cold air leakage when the turbine cylinder (4) and the first turbine supporting ring (1) move relatively.
14. Gas turbine blade tip clearance active control device according to claim 13, characterized in that the first sealing assembly (3) is a sealing ring.
15. The active control device for the tip clearance of a gas turbine blade according to claim 14, wherein the top of the seal ring (3) is of a spherical structure.
16. The active control device for the tip clearance of a gas turbine according to any one of claims 1 to 9, wherein the turbine cylinder (4) and the first turbine retainer ring (1) are both of a horizontally split structure.
17. The active control device for the blade tip clearance of the gas turbine is characterized in that a cushion block (8) used for fixing the joint of the turbine cylinder (4) and the first turbine supporting ring (1) is arranged at the connecting position of the turbine cylinder (4) and the first turbine supporting ring (1).
18. The active control device of the gas turbine blade tip clearance according to claim 17, characterized in that the spacer block (8) is located at the connection of the turbine cylinder (4) and the first turbine shroud ring (1) in the circumferential direction.
19. The active control device for the blade tip clearance of the gas turbine according to claim 17, characterized in that a connecting position of the turbine cylinder (4) and the first turbine supporting ring (1) is further provided with an adjusting gasket (9).
20. Active control device of the gas turbine blade tip clearance according to claim 19, characterized in that the thickness of the shim (9) is adjustable.
21. Active control device of the gas turbine blade tip clearance according to claim 17, characterized in that the connection locations of the turbine cylinders (4) to the first turbine shroud ring (1) are evenly distributed in the circumferential direction.
22. The active control device for the blade tip clearance of the gas turbine as claimed in claim 21, wherein the number of connection positions of the turbine cylinder (4) and the first turbine supporting ring (1) is 2-5.
23. Active control device for the blade tip clearance of a gas turbine according to claim 17, characterized in that the connection of the turbine cylinder (4) and the first turbine retaining ring (1) is provided with a through hole in the radial direction.
24. The active control device for the clearance between the blade tips of a gas turbine as claimed in claim 23, wherein a lubricant is injected into the connection clearance between the turbine cylinder and the first turbine shroud ring through the through hole.
25. The active gas turbine tip clearance control device of claim 24, wherein the lubricant is molybdenum disulfide grease.
26. Active control device of the gas turbine blade tip clearance according to any of the claims 1 to 9, characterized in that the turbine cylinder (4) and the first turbine holding ring (1) are fixed by a second turbine holding ring (5), the second turbine holding ring (5) being connected to the turbine cylinder (4) in radial direction, the second turbine holding ring (5) being connected to the first turbine holding ring (4) in axial direction.
27. The active control device of the gas turbine blade tip clearance according to claim 26, characterized in that a second seal assembly (2) is provided between the second turbine (5) backing ring and the first turbine backing ring (4), the second seal assembly (2) being used for sealing between the second turbine backing ring (5) and the first turbine backing ring (1).
28. A method for actively controlling the tip clearance of a turbine blade by using the active tip clearance control device of a gas turbine as claimed in any one of claims 1 to 27, wherein when the gas turbine is in a first operating condition, the power device pushes the first turbine flat ring to move axially to reduce the tip clearance of the turbine moving blade, and when the gas turbine is in a second operating condition, the power device and the first turbine flat ring are returned to increase the tip clearance of the turbine moving blade.
29. The method of claim 28, wherein the power plant urges the first turbine blade carrier ring to move axially toward the exhaust side to reduce the turbine blade tip clearance when the gas turbine is in the first operating condition.
30. A gas turbine comprising the gas turbine tip clearance active control device of claim 1.
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| CN202111131944.9A CN113756883A (en) | 2021-09-26 | 2021-09-26 | Active control device and method for gas turbine blade top clearance |
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| CN202111131944.9A CN113756883A (en) | 2021-09-26 | 2021-09-26 | Active control device and method for gas turbine blade top clearance |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114412582A (en) * | 2022-01-29 | 2022-04-29 | 中国联合重型燃气轮机技术有限公司 | Gas turbine shroud ring adjusting device and gas turbine |
| CN114427482A (en) * | 2022-01-13 | 2022-05-03 | 上海慕帆动力科技有限公司 | Blade top clearance adjusting system and method of hydrogen fuel gas turbine |
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| CN112160800A (en) * | 2020-10-16 | 2021-01-01 | 杭州汽轮动力集团有限公司 | Active control device for blade top clearance of axial flow gas turbine |
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| JP2003286992A (en) * | 2002-03-28 | 2003-10-10 | Mitsubishi Heavy Ind Ltd | Turbo molecular pump and method of adjusting pump |
| EP2206889A1 (en) * | 2009-01-13 | 2010-07-14 | Siemens Aktiengesellschaft | Method of reducing tip clearance using a rotor displacement device and related gas turbine |
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| CN114427482A (en) * | 2022-01-13 | 2022-05-03 | 上海慕帆动力科技有限公司 | Blade top clearance adjusting system and method of hydrogen fuel gas turbine |
| CN114427482B (en) * | 2022-01-13 | 2023-06-16 | 上海慕帆动力科技有限公司 | Blade tip clearance adjustment system and adjustment method of hydrogen fuel gas turbine |
| CN114412582A (en) * | 2022-01-29 | 2022-04-29 | 中国联合重型燃气轮机技术有限公司 | Gas turbine shroud ring adjusting device and gas turbine |
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