Mechanical adjustment mechanism for shroud turbine tip clearance and gas turbine having the same

Abstract

The application discloses a kind of crown turbine blade tip clearance mechanical adjusting mechanism and gas turbine with it, crown turbine blade tip clearance mechanical adjusting mechanism includes: casing, adjusting cavity and impeller cavity are formed in casing, opening is equipped between adjusting cavity and impeller cavity, both sides of opening are equipped with arc sealing platform, the outer wall of casing is equipped with multiple mounting holes;Deformation plate, deformation plate covers opening, both sides of deformation plate are equipped with the arc lap edge of the shape of the shape adaptation of arc sealing platform;Honeycomb core;Multiple adjusting rods, multiple adjusting rods are respectively movably matched in multiple mounting holes and with the outer surface of deformation plate abut;Driving device, driving device is respectively connected with multiple adjusting rods transmission;Impeller;Crown.According to the crown turbine blade tip clearance mechanical adjusting mechanism of embodiment of the application can reduce the influence of main flow gas temperature, pressure change on gap size, with the advantages of gap size control accurate, small leakage.

Description

Technical Field

[0001] This invention relates to the field of gas turbine manufacturing technology, and more specifically, to a crowned turbine blade tip clearance mechanical adjustment mechanism and a gas turbine having the crowned turbine blade tip clearance mechanical adjustment mechanism. Background Technology

[0002] Gas turbines are mainly used in power generation and marine applications. In power grid systems dominated by renewable energy, power generation gas turbines need to have the ability to start up quickly and change loads rapidly. In the marine sector, the operating conditions of marine gas turbines often change to meet different speed requirements.

[0003] Crowned turbines are a common type of gas turbine, and their blade tip shroud structure significantly enhances overall structural strength. The crowned turbine blades have a serrated structure that, together with the honeycomb lattice on the casing, forms a serrated seal. During gas turbine startup, the clearance needs to be appropriately increased to prevent the serrations from rubbing against the casing lattice and causing structural damage. During stable operation, the radial distance between the serrations and the casing lattice needs to be appropriately reduced to decrease leakage in the sealing gap. To improve gas turbine efficiency, the turbine inlet temperature increases. Under the combined effects of high temperature and centrifugal force, the deformation of the crowned turbine increases significantly, increasing the difficulty of controlling the clearance between the blade tip and the honeycomb lattice.

[0004] The control method for the gap between the blade crown and the honeycomb lattice in related technologies involves installing thin-walled components inside the casing to form a static seal with the grates. When it is necessary to reduce the gap between the grates and the casing, cold air is blown onto the thin-walled components, causing them to cool and contract, thus reducing the gap. During startup and load changes, hot air is blown onto the thin-walled components, increasing their temperature and causing them to expand, thus increasing the gap and preventing scuffing. However, two problems exist: first, due to the dynamic changes in the gaps at various points, the distribution of cold air becomes complex, and the expected convective heat transfer often differs significantly from reality, resulting in gap control not meeting expectations; second, a large amount of cold air needs to be drawn from the compressor to cool the walls, leading to a decrease in volumetric efficiency. In some turbine structures, the cold air mixes with the high-temperature mainstream downstream, lowering the temperature of the mixed airflow and thus reducing the work capacity of the downstream turbine. Summary of the Invention

[0005] This invention aims to at least solve one of the technical problems existing in the prior art. To this end, this invention proposes a crowned turbine blade tip clearance mechanical adjustment mechanism, which can reduce the impact of mainstream gas temperature and pressure changes on the clearance size, and has the advantages of accurate clearance size control and low leakage.

[0006] The present invention also proposes a gas turbine having the aforementioned crowned turbine blade tip clearance mechanical adjustment mechanism.

[0007] To achieve the above objectives, according to an embodiment of the first aspect of the present invention, a crowned turbine blade tip clearance mechanical adjustment mechanism is provided, the crowned turbine blade tip clearance mechanical adjustment mechanism comprising: a casing, wherein an annular adjustment cavity and an impeller cavity located radially within the casing and inside the adjustment cavity are formed therein, an opening is provided between the adjustment cavity and the impeller cavity, and arc-shaped sealing platforms are provided on both sides of the opening along the axial direction of the casing, and a plurality of mounting holes are provided on the outer wall of the casing at intervals along the circumference of the casing; a deformation plate, the deformation plate covering the opening, the deformation plate being located radially within the casing and being positioned at intervals along the axial direction of the casing. Both sides of the upper part are provided with arc-shaped overlapping edges adapted to the shape of the arc-shaped sealing platform, and the two arc-shaped overlapping edges are respectively engaged with the two arc-shaped sealing platforms; honeycomb core, the honeycomb core is provided on the inner surface of the deformable plate; multiple adjusting rods, the multiple adjusting rods are respectively movable along the radial direction of the casing and are engaged in multiple mounting holes and abut against the outer surface of the deformable plate; driving device, the driving device is respectively connected to the multiple adjusting rods; impeller, the impeller is rotatably provided in the impeller cavity; blade crown, the blade crown is provided on the blade tip of the impeller, and the blade crown is provided with serrations.

[0008] The crowned turbine blade tip clearance mechanical adjustment mechanism according to an embodiment of the present invention can reduce the influence of mainstream gas temperature and pressure changes on the clearance size, and has the advantages of accurate clearance size control and low leakage.

[0009] In addition, the crowned turbine blade tip clearance mechanical adjustment mechanism according to the above embodiments of the present invention may also have the following additional technical features:

[0010] According to one embodiment of the present invention, the casing is provided with a nozzle and an exhaust port, both of which are in communication with the adjustment cavity, and the nozzle and the exhaust port are respectively located on two opposite surfaces of the adjustment cavity in the axial direction of the casing.

[0011] According to one embodiment of the present invention, the plurality of adjusting rods are respectively threaded into the plurality of mounting holes.

[0012] According to one embodiment of the present invention, each of the adjusting rods is connected to a rocker arm, and the driving device is connected to a crank, the crank being rotatably connected to the rocker arm.

[0013] According to one embodiment of the present invention, the thickness of the deformable plate gradually decreases from the center to the edge in the axial direction of the casing.

[0014] According to one embodiment of the present invention, the outer surface of the deformable plate is an outwardly convex arc surface.

[0015] According to one embodiment of the present invention, a first sealing ring is provided between the mounting hole and the adjusting rod, and a second sealing ring is provided between each cooperating arc sealing platform and the arc overlapping edge.

[0016] According to one embodiment of the present invention, the movement of the adjusting rod in the radial direction of the casing includes at least a normal position, a starting position, and a full-load position. The adjusting rod in the starting position is further away from the impeller cavity than the adjusting rod in the full-load position. The normal position is located between the starting position and the full-load position. A limiting ring is provided on the outer peripheral surface of the adjusting rod. An inwardly extending stud is provided around the mounting hole. When the adjusting rod is in the starting position, the limiting ring abuts against the inner end face of the stud.

[0017] According to one embodiment of the present invention, the casing includes a body and a mounting plate, the mounting plate being detachably disposed on the body, and the opening being defined by the body on one edge and the mounting plate on the other edge in the axial direction of the casing to allow the deformable plate to be inserted into the opening when the mounting plate is removed.

[0018] According to an embodiment of a second aspect of the present invention, a gas turbine is provided, the gas turbine including the crowned turbine tip clearance mechanical adjustment mechanism described in an embodiment of a first aspect of the present invention.

[0019] The gas turbine according to embodiments of the present invention, by utilizing the crowned turbine blade tip clearance mechanical adjustment mechanism described in the first aspect of the present invention, has advantages such as high reliability and high operating efficiency.

[0020] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0021] The above and / or additional aspects and advantages of the present invention will become apparent and readily understood from the description of the embodiments taken in conjunction with the following drawings, in which:

[0022] Figure 1 This is a partial cross-sectional view of the crowned turbine blade tip clearance mechanical adjustment mechanism according to an embodiment of the present invention.

[0023] Figure 2 This is a schematic diagram of the deformable plate of the crowned turbine blade tip clearance mechanical adjustment mechanism according to an embodiment of the present invention.

[0024] Figure 3 This is a schematic diagram of the crank of the crowned turbine blade tip clearance mechanical adjustment mechanism according to an embodiment of the present invention.

[0025] Reference numerals: 1. Crowned turbine blade tip clearance mechanical adjustment mechanism; 10. Casing; 11. Adjustment chamber; 12. Impeller chamber; 13. Arc sealing platform; 14. Mounting hole; 15. Nozzle; 16. Exhaust hole; 17. Main body; 18. Mounting plate; 19. Stud; 20. Deformation plate; 21. Arc overlapping edge; 30. Honeycomb core; 40. Adjusting rod; 41. Limiting ring platform; 51. Rocker arm; 60. Impeller; 70. Blade crown; 71. Grate teeth; 80. Crank; 81. First positioning pin; 82. Second positioning pin; 91. First sealing ring; 92. Second sealing ring; 100. Fastener. Detailed Implementation

[0026] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0027] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential," etc., indicating orientation or positional relationships, are based on the orientation or positional relationships shown in the accompanying drawings and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, features defined with "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0028] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0029] The crowned turbine blade tip clearance mechanical adjustment mechanism 1 according to an embodiment of the present invention is described below with reference to the accompanying drawings.

[0030] like Figures 1-3As shown, the crowned turbine blade tip clearance mechanical adjustment mechanism 1 according to an embodiment of the present invention includes a casing 10, a deformable plate 20, a honeycomb core 30, a plurality of adjusting rods 40, a drive device, an impeller 60, and a blade crown 70.

[0031] An annular adjustment cavity 11 and an impeller cavity 12 located radially inside the adjustment cavity 11 are formed within the casing 10. An opening is provided between the adjustment cavity 11 and the impeller cavity 12. Both sides of the opening in the axial direction of the casing 10 are provided with arc-shaped sealing platforms 13. The outer wall of the casing 10 has multiple mounting holes 14 spaced circumferentially along the casing 10. The casing 10 has nozzles 15 and exhaust holes 16, both of which communicate with the adjustment cavity 11. A deformable plate 20 covers the opening. Both sides of the deformable plate 20 in the axial direction of the casing 10 have arc-shaped overlapping edges 21 that match the shape of the arc-shaped sealing platforms 13. The two arc-shaped overlapping edges 21 respectively overlap and engage with the two arc-shaped sealing platforms 13. A honeycomb core 30 is provided on the inner surface of the deformable plate 20. Multiple adjustment rods 40 are movably fitted into the multiple mounting holes 14 along the radial direction of the casing 10 and abut against the outer surface of the deformable plate 20. The drive unit is connected to multiple adjusting rods 40 for transmission. The impeller 60 is rotatably disposed within the impeller cavity 12. The blade crown 70 is disposed at the tip of the impeller 60, and the blade crown 70 is provided with serrations 71.

[0032] Specifically, the axial direction of the casing 10 is shown by arrow A in the figure, and the radial direction of the casing 10, i.e. the inward and outward directions of the casing 10, is shown by arrow B in the figure.

[0033] Those skilled in the art will understand that, Figure 1 and Figure 2 Only a schematic diagram of the crowned turbine blade tip clearance mechanical adjustment mechanism 1 is shown in a cross section of the casing 10. The casing 10, the deformable plate 20, and the honeycomb lattice 30 are all rotating bodies passing through this cross section.

[0034] According to an embodiment of the present invention, the crowned turbine blade tip clearance mechanical adjustment mechanism 1, by setting an adjusting rod 40 and a deformable plate 20, can use the driving device to drive the adjusting rod 40 to move in the inward and outward directions, thereby using the end of the adjusting rod 40 that abuts against the deformable plate 20 to drive the deformable plate 20 to deform, changing the degree of inward bending of the deformable plate 20, thereby realizing the active adjustment of the gap size between the inner honeycomb core 30 of the deformable plate 20 and the blade tip 70, and improving the reliability of the gap adjustment. For example, during gas turbine startup or load change, the regulating rod 40 can be driven to move outward, reducing the degree of inward bending of the deformable plate 20, thereby increasing the distance between the deformable plate 20 and the impeller 60, and increasing the distance between the honeycomb lattice 30 and the blade crown 70. This prevents the grates 71 of the blade crown 70 from rubbing against the honeycomb lattice 30, ensuring reliable operation of the gas turbine. When the gas turbine is running stably, the regulating rod 40 can be driven to move inward, increasing the degree of inward bending of the deformable plate 20, thereby reducing the distance between the deformable plate 20 and the impeller 60, reducing the distance between the honeycomb lattice 30 and the blade crown 70, reducing the leakage between the grates 71 and the honeycomb lattice 30, and improving the operating efficiency of the gas turbine.

[0035] Furthermore, by setting nozzle 15 and exhaust port 16, nozzle 15 can be connected to a gas source. Cold or hot air is sprayed into the regulating chamber 11 through nozzle 15 and discharged through exhaust port 16. This utilizes the principle of thermal expansion and contraction to cause the deformable plate 20 to expand or contract, further assisting in the adjustment of the gap between the honeycomb lattice 30 and the blade crown 70, thereby improving the adjustment effect of the gap. For example, when the gas turbine starts up or changes load, hot air is blown into the regulating chamber 11 through nozzle 15, causing the deformable plate 20 to expand due to heat, thereby increasing the gap between the honeycomb lattice 30 and the blade crown 70. When the gas turbine is running stably, cold air is blown into the regulating chamber 11 through nozzle 15, causing the deformable plate 20 to contract due to cold, thereby decreasing the gap between the honeycomb lattice 30 and the blade crown 70. Since the gap adjustment is achieved by driving the deformation of the deformable plate 20 through the regulating rod 40, the amount of gas required for temperature regulation can be reduced, thereby improving volumetric efficiency. Temperature regulation via nozzle 15 can also serve as a backup adjustment method when the adjustment rod 40 fails, thereby further ensuring the adjustment effect of the crowned turbine blade tip clearance mechanical adjustment mechanism 1.

[0036] Furthermore, by setting the arc sealing platform 13 and the arc overlapping edge 21, the arc overlapping edge 21 can remain in contact with the arc sealing platform 13 no matter how the deformable plate 20 is bent under the drive of the adjusting rod 40, thereby improving the sealing performance of the adjusting cavity 11 and preventing the gas injected into the adjusting cavity 11 by the nozzle 15 from leaking out from the gap between the deformable plate 20 and the opening, ensuring the temperature regulation effect of the gas on the deformable plate 20, thereby further ensuring the adjustment effect on the gap between the blade crown 70 and the honeycomb core 30, and also avoiding the leakage of gas causing the leaked airflow to mix with the high-temperature mainstream and affect the turbine's work capacity.

[0037] Therefore, the crowned turbine blade tip clearance mechanical adjustment mechanism 1 according to the present invention can reduce the influence of mainstream gas temperature and pressure changes on the clearance size, and has the advantages of accurate clearance size control and low leakage.

[0038] The crowned turbine blade tip clearance mechanical adjustment mechanism 1 according to a specific embodiment of the present invention is described below with reference to the accompanying drawings.

[0039] In some specific embodiments of the present invention, such as Figures 1-3 As shown, the crowned turbine blade tip clearance mechanical adjustment mechanism 1 according to an embodiment of the present invention includes a casing 10, a deformable plate 20, a honeycomb core 30, a plurality of adjusting rods 40, a drive device, an impeller 60, and a blade crown 70.

[0040] Advantageously, such as Figure 1 As shown, the nozzle 15 and the exhaust port 16 are located on opposite surfaces of the regulating chamber 11 in the axial direction of the casing 10. Specifically, the nozzle 15 and the exhaust port 16 are offset in the radial direction of the casing 10. This prevents the gas injected into the regulating chamber 11 by the nozzle 15 from being directly discharged through the exhaust port 16, thereby ensuring the gas's temperature regulation effect on the deformable plate 20 and the adjustment effect on the gap between the honeycomb core 30 and the blade crown 70.

[0041] Specifically, such as Figure 1 As shown, multiple adjusting rods 40 are threaded into multiple mounting holes 14. This allows the rotation of the adjusting rods 40 to be converted into axial movement through the threaded engagement of the adjusting rods 40 with the mounting holes 14. Consequently, the driving device adjusts the position of the adjusting rods 40 in the inward and outward directions by driving the adjusting rods 40 to rotate.

[0042] Specifically, the number of adjusting rods 40 can be 20, 40, or 80.

[0043] More specifically, such as Figure 1 and Figure 3As shown, each adjusting rod 40 is connected to a rocker arm 51, and the driving device is connected to a crank 80, which is rotatably connected to the rocker arm 51. Specifically, the rocker arm 51 is connected to the adjusting rod 40 via a first positioning pin 81, and the first positioning pin 81 restricts the relative rotation between the rocker arm 51 and the adjusting rod 40. The crank 80 is rotatably connected to the rocker arm 51 via a second positioning pin 82. In this way, the driving device can drive the crank 80, which in turn drives the rocker arm 51, ultimately causing the adjusting rod 40 to rotate.

[0044] Specifically, the driving device may include a crank-slider mechanism. The driving device may be one and connected to multiple adjusting rods 40 respectively, or it may be multiple and connected to multiple adjusting rods 40 respectively.

[0045] More advantageously, such as Figure 2 As shown, the thickness of the deformable plate 20 gradually decreases from the center to the edge in the axial direction of the housing 10. This facilitates the adjustment rod 40 driving the deformable plate 20 to bend inward.

[0046] Furthermore, such as Figure 2 As shown, the outer surface of the deformable plate 20 is an outwardly convex arc surface. This further facilitates the adjusting rod 40 in driving the deformable plate 20 to bend inward.

[0047] Optionally, the thickness difference between the center and the edge of the inner surface of the deformable plate 20 is 0.5 mm. This makes the arc structure of the inner surface of the deformable plate 20 more reasonable.

[0048] Figure 1 A mechanical adjustment mechanism 1 for the tip clearance of a crowned turbine blade is shown, according to some examples of the present invention. For example... Figure 1 As shown, a first sealing ring 91 is provided between the mounting hole 14 and the adjusting rod 40, and a second sealing ring 92 is provided between each mating arc sealing platform 13 and the arc overlapping edge 21. This allows the first sealing ring 91 to seal between the mounting hole 14 and the adjusting rod 40, and the second sealing ring 92 to seal between the arc sealing platform 13 and the arc overlapping edge 21, further improving the sealing performance of the adjusting cavity 11, ensuring the temperature regulation effect of the airflow on the deformable plate 20, and preventing airflow leakage from affecting the operating efficiency of the gas turbine.

[0049] Specifically, both the first sealing ring 91 and the second sealing ring 92 are made of high-temperature resistant materials.

[0050] Specifically, such as Figure 1As shown, the radial movement of the adjusting rod 40 in the casing 10 includes at least a normal position, a starting position, and a full-load position. The adjusting rod 40 in the starting position is further away from the impeller cavity 12 than the adjusting rod 40 in the full-load position. The normal position is located between the starting position and the full-load position. A limiting ring 41 is provided on the outer circumferential surface of the adjusting rod 40, and an inwardly extending stud 19 is provided around the mounting hole 14. When the adjusting rod 40 is in the starting position, the limiting ring 41 abuts against the inner end face of the stud 19. Specifically, the deformation plate 20 is in a deformed state at least when the adjusting rod 40 is in the normal position and the slow-return position. When the gas turbine starts or changes load, the adjusting rod 40 moves to the starting position; when the gas turbine is running stably, the adjusting rod 40 moves to the full-load position. This facilitates adjustment of the distance between the blade crown 70 and the honeycomb lattice 30 in various operating states of the gas turbine.

[0051] More specifically, such as Figure 1 As shown, the casing 10 includes a body 17 and a mounting plate 18, which is detachably mounted on the body 17. One edge of the opening in the axial direction of the casing 10 is defined by the body 17, and the other edge is defined by the mounting plate 18 to allow the deformable plate 20 to be inserted into the opening when the mounting plate 18 is removed. Specifically, the mounting plate 18 is detachably mounted on the body 17 by fasteners 100. This facilitates the installation of the deformable plate 20.

[0052] Specifically, the honeycomb lattice 30 is welded to the inner surface of the deformable plate 20.

[0053] The impeller 60 includes an impeller disk and a plurality of blades spaced apart on the outer circumferential surface of the impeller disk. The blade crown is located at the outer end of the blade.

[0054] The following describes a gas turbine according to an embodiment of the present invention. The gas turbine according to an embodiment of the present invention includes a crowned turbine blade tip clearance mechanical adjustment mechanism 1 according to the above embodiment of the present invention.

[0055] According to the embodiments of the present invention, the gas turbine can ensure the adjustment effect of the gap between the blade crown and the honeycomb lattice by utilizing the crowned turbine tip clearance mechanical adjustment mechanism 1 of the present invention, thereby enabling the gas turbine to have advantages such as high reliability and high operating efficiency.

[0056] For example, when the gas turbine is started from a cold state, rotating the adjusting rod 40 causes the limiting ring platform 41 to fit against the inner end face of the stud 19, which restores the deformation of the deformed plate 20 with welded honeycomb core 30 that has been squeezed, thereby slightly increasing the gap between the grating teeth 71 and the honeycomb core 30 (not exceeding 0.5 mm) and improving the safety of the gas turbine startup.

[0057] When the gas turbine is at full load, the initial clearance is 3mm. When operating under full conditions, the elongation of the impeller 60 with crown turbine is 1mm. The deformed plate 20 with honeycomb core 30 is extruded and welded by adjusting rod 40. When the stroke of adjusting rod 40 is 1mm, it is calculated that the throat height of the sealing clearance can be reduced by about 0.6mm, thereby improving the efficiency of the gas turbine by about 1.5%.

[0058] Other configurations and operations of the gas turbine according to embodiments of the present invention are known to those skilled in the art and will not be described in detail here.

[0059] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "illustrative embodiment," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0060] Although embodiments of the invention have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims

1. A mechanical adjustment mechanism for the tip clearance of a crowned turbine blade, characterized in that, include: The casing has an annular adjustment cavity and an impeller cavity located radially inside the adjustment cavity. An opening is provided between the adjustment cavity and the impeller cavity. An arc sealing platform is provided on both sides of the opening in the axial direction of the casing. The outer wall of the casing has a plurality of mounting holes spaced apart along the circumference of the casing. The deformable plate covers the opening. Both sides of the deformable plate in the axial direction of the casing are provided with arc-shaped overlapping edges that are adapted to the shape of the arc-shaped sealing platform. The two arc-shaped overlapping edges respectively overlap and cooperate with the two arc-shaped sealing platforms. The thickness of the deformable plate gradually decreases from the middle to the edge in the axial direction of the casing. The outer surface of the deformable plate is an outwardly convex arc surface. A honeycomb core cell is disposed on the inner surface of the deformable plate; Multiple adjusting rods are provided, each of which is radially movable along the casing and fits into multiple mounting holes and abuts against the outer surface of the deformable plate. A driving device is connected to a plurality of the adjusting rods in a transmission manner; An impeller, which is rotatably disposed within the impeller cavity; The leaf crown is located at the tip of the impeller blade and has serrated teeth.

2. The crowned turbine blade tip clearance mechanical adjustment mechanism according to claim 1, characterized in that, The casing is provided with a nozzle and an exhaust port, both of which are connected to the adjustment cavity. The nozzle and the exhaust port are located on two opposite surfaces of the adjustment cavity in the axial direction of the casing.

3. The crowned turbine blade tip clearance mechanical adjustment mechanism according to claim 1, characterized in that, The plurality of adjusting rods are threaded into the plurality of mounting holes respectively.

4. The crowned turbine blade tip clearance mechanical adjustment mechanism according to claim 3, characterized in that, Each of the adjusting rods is connected to a rocker arm, and the drive device is connected to a crank, which is rotatably connected to the rocker arm.

5. The crowned turbine blade tip clearance mechanical adjustment mechanism according to claim 1, characterized in that, A first sealing ring is provided between the mounting hole and the adjusting rod, and a second sealing ring is provided between each mating arc sealing platform and the arc overlapping edge.

6. The crowned turbine blade tip clearance mechanical adjustment mechanism according to claim 1, characterized in that, The movement of the adjusting rod in the radial direction of the casing includes at least a normal position, a starting position, and a full-load position. The adjusting rod in the starting position is further away from the impeller cavity than the adjusting rod in the full-load position. The normal position is located between the starting position and the full-load position. A limiting ring is provided on the outer peripheral surface of the adjusting rod. An inwardly extending stud is provided around the mounting hole. When the adjusting rod is in the starting position, the limiting ring abuts against the inner end face of the stud.

7. The crowned turbine blade tip clearance mechanical adjustment mechanism according to claim 1, characterized in that, The casing includes a body and a mounting plate, the mounting plate being detachably disposed on the body, the opening being defined by the body on one edge and by the mounting plate on the other edge in the axial direction of the casing to allow the deformable plate to be inserted into the opening when the mounting plate is removed.

8. A gas turbine, characterized in that, Includes a crowned turbine blade tip clearance mechanical adjustment mechanism according to any one of claims 1-7.

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