Passive adjustment structure of turbine rim seal gap and gas turbine with same

Abstract

The application discloses a turbine rim sealing gap passive adjustment structure and a gas turbine with the same. The turbine rim sealing gap passive adjustment structure comprises a casing, a rotating disc, a static disc, a rotating disc sealing ring arranged on an end surface of the rotating disc, a static disc sealing ring arranged on an end surface of the static disc, a containing groove arranged on the static disc, the rotating disc sealing ring extending into the containing groove, a first gap formed between the rotating disc sealing ring and the static disc sealing ring, an annular platform arranged on an inner circumferential surface of the containing groove, a second gap formed between the annular platform and the rotating disc sealing ring, a moving blade, a static blade, an adjustment cavity arranged on the end surface of the static disc, an adjustment chamber arranged in the adjustment cavity, a plurality of grids arranged on the adjustment cavity, the adjustment chamber and the containing groove being communicated through a guide hole, a jet hole arranged between every two adjacent grids, and a third gap formed between the grid and the rotating disc sealing ring. The turbine rim sealing gap passive adjustment structure has the advantages of good sealing effect and the like.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of gas turbine manufacturing, in particular to a turbine rim seal gap passive adjustment structure and a gas turbine with the same. BACKGROUND

[0002] Gas turbines are mainly applied in power generation and ship fields. In the power grid system dominated by renewable energy, the power generation gas turbine needs to have the ability of quick start and quick load change. In the ship field, the working condition of the marine gas turbine often changes to meet different speed requirements.

[0003] The disc cavity system is an important subsystem in the secondary air system of the gas turbine, which functions to cool the rotating disc and the stationary disc, provide cold air to the moving blade, and realize the rotating and stationary sealing, etc. It mainly includes a casing, a rotating disc and a stationary disc. The stationary disc is fixedly arranged in the casing, and the rotating disc is rotatably arranged in the casing. The casing and the rotating disc, and the casing and the stationary disc form a main flow passage for the gas flow to pass through. The disc cavity is formed between the stationary disc and the rotating disc. The rim seal is a common structure of the disc cavity system, which mainly includes a rotating disc seal ring and a stationary disc seal ring, etc., and is used for sealing between the main flow passage and the disc cavity to prevent the gas in the main flow passage from invading the disc cavity. Since the rotating disc needs to rotate, the rim seal structure needs to have a gap to prevent the rotating disc from rubbing against the stationary disc during rotation.

[0004] The turbine rim seal structure in the related art mainly includes a stationary disc seal ring extending from the end face of the stationary disc to the rotating disc and a rotating disc seal ring extending from the end face of the rotating disc to the stationary disc. The two cooperate with each other to improve the sealing effect. However, since the gas temperature in the disc cavity of the gas turbine is about 200-300℃, and the gas temperature in the main flow passage is more than 1000℃, the stationary disc seal ring closer to the main flow passage expands under the action of high temperature, which increases the flow area of the gap between the rotating disc seal ring and the stationary disc seal ring. On the one hand, it leads to an increase in leakage, and on the other hand, it is easy to cause the gas to invade the disc cavity, thereby reducing the service life of the rotating disc, the stationary disc and the sealing structure.

[0005] Therefore, part of the disc cavity system of the gas turbine is further provided with a grate on the stationary disc, which forms a sealing gap with the inner side of the rotating disc seal ring. The multi-stage rim seal improves the sealing effect. However, since the gas invades between the rotating disc seal ring and the stationary disc seal ring from time to time, the temperature on the outer side of the rotating disc seal ring is relatively high, which easily leads to expansion of the rotating disc seal ring, and easily leads to an increase in the gap between the rotating disc seal ring and the grate, thereby causing the gas to invade. However, if the radial sealing gap of the rotating disc seal ring and the grate is reduced in order to prevent the gas from invading, it is easy to cause the grate to rub against the stationary disc during the quick start or load change operation of the gas turbine. Especially, in order to improve the efficiency of the gas turbine, the temperature at the turbine inlet is getting higher and higher, which further increases the difficulty of controlling the sealing gap. SUMMARY

[0006] The present application aims to at least solve one of the technical problems existing in the prior art. To this end, the present application provides a turbine rim seal gap passive adjustment structure, which has the advantages of good sealing effect and the like.

[0007] The present application also provides a gas turbine with the turbine rim seal gap passive adjustment structure.

[0008] To achieve the above-mentioned purpose, according to the embodiment of the first aspect of the present application, a turbine rim seal gap passive adjustment structure is provided, which comprises: a casing; a rotating disc rotatably arranged in the casing and spaced apart from the inner circumferential surface of the casing; a stationary disc arranged in the casing and spaced apart from the inner circumferential surface of the casing, a main flow passage being formed between the rotating disc and the casing and between the stationary disc and the casing, a disc cavity being formed between the rotating disc and the stationary disc, an end surface of the rotating disc towards the stationary disc being provided with a rotating disc seal ring, an end surface of the stationary disc towards the rotating disc being provided with a stationary disc seal ring, the stationary disc seal ring being located radially outward of the rotating disc seal ring in the casing, the stationary disc being provided with a receiving groove, the receiving groove being located radially inward of the stationary disc seal ring in the casing, the rotating disc seal ring extending into the receiving groove, a first gap being formed between the outer circumferential surface of the rotating disc seal ring and the inner circumferential surface of the stationary disc seal ring and communicating with the receiving groove, the inner circumferential surface of the receiving groove being provided with a ring platform, a second gap being formed between the ring platform and the rotating disc seal ring and communicating with the receiving groove; a moving blade arranged on the outer circumferential surface of the rotating disc and spaced apart from the casing; a stationary blade arranged on the outer circumferential surface of the stationary disc and connected to the inner circumferential surface of the casing; an adjusting cavity arranged on the end surface of the stationary disc towards the rotating disc and radially inward of the receiving groove in the casing, an adjusting chamber being arranged in the adjusting cavity, a plurality of grids being arranged on the circumferential surface of the adjusting cavity radially outward of the casing and spaced apart in the axial direction of the casing, the adjusting chamber and the receiving groove being communicated through a guide hole, a jet hole communicating with the adjusting chamber being arranged between each adjacent two grids, and a third gap being formed between the grid and the inner circumferential surface of the rotating disc seal ring.

[0009] The turbine rim seal gap passive adjustment structure according to the embodiment of the present application has the advantages of good sealing effect and the like.

[0010] In addition, the turbine rim seal gap passive adjustment structure according to the above-mentioned embodiment of the present application can also have the following additional technical features:

[0011] According to an embodiment of the present application, the guide hole is in communication with the inner circumferential surface of the accommodating groove and a side surface of the adjusting cavity axially away from the rotating disc, respectively.

[0012] According to an embodiment of the present application, each of the jet holes is located at the center of two adjacent labyrinth teeth in the axial direction of the casing.

[0013] According to an embodiment of the present application, the guide holes are multiple and arranged at intervals in the circumferential direction of the casing.

[0014] According to an embodiment of the present application, the jet holes are multiple and arranged at intervals in the circumferential direction of the casing.

[0015] According to an embodiment of the present application, the inner circumferential surface of the rotating disc sealing ring is formed with honeycomb cells, and the third gap is defined by the honeycomb cells and the labyrinth teeth.

[0016] According to an embodiment of the present application, the stationary vanes are multiple and arranged at intervals in the circumferential direction of the stationary disc, and the rotating vanes are multiple and arranged at intervals in the circumferential direction of the rotating disc.

[0017] According to an embodiment of the present application, the adjusting cavity comprises an adjusting cavity body and a mounting plate, the adjusting cavity body is integrally formed with the stationary disc, the mounting plate is detachably mounted on the adjusting cavity body, and the labyrinth teeth are arranged on the mounting plate.

[0018] According to an embodiment of the present application, multiple sealing rings are arranged between the mounting plate and the adjusting cavity body.

[0019] According to an embodiment of the second aspect of the present application, a gas turbine is provided, which comprises the turbine rim sealing gap passive adjustment structure according to the embodiment of the first aspect of the present application.

[0020] According to the gas turbine of the embodiment of the present application, by using the turbine rim sealing gap passive adjustment structure according to the embodiment of the first aspect of the present application, the advantages of good sealing effect and the like are achieved.

[0021] Additional aspects and advantages of the present application will be in part apparent and in part pointed out hereinafter. BRIEF DESCRIPTION OF DRAWINGS

[0022] The above and / or additional aspects and advantages of the present application will become apparent and be readily understood from the following description, taken in conjunction with the accompanying drawings, in which:

[0023] Figure 1 is a partial sectional view of a turbine rim sealing gap passive adjustment structure according to an embodiment of the present application.

[0024] Figure 2 is Figure 1 is an enlarged view of A in FIG. 1.

[0025] Reference signs: turbine rim seal gap passive adjustment structure 1, casing 10, main flow passage 11, disc cavity 12, first gap 13, second gap 14, third gap 15, rotating disc 20, rotating disc seal ring 21, honeycomb core 22, stationary disc 30, stationary disc seal ring 31, accommodating groove 32, ring table 33, guide hole 34, moving blade 40, stationary blade 50, adjustment cavity 60, adjustment cavity body 61, mounting plate 62, adjustment cavity chamber 63, grid 64, jet hole 65, fastener 66, seal ring 67. DETAILED DESCRIPTION

[0026] Embodiments of the present application are described below by referring to the drawings, which are shown by way of illustration, and are not intended to be limiting of the application unless otherwise specified. The following examples are illustrative of specific embodiments of the application, and are not meant to be limiting in any way.

[0027] In the description of the present application, it is to be understood that the orientations or positional relationships indicated by the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like are based on the orientations or positional relationships shown in the drawings, and are merely intended to facilitate the description of the present application and simplify the description, and are not intended to indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be construed as limiting the present application. In addition, features defined with "first", "second" can explicitly or implicitly include one or more of the features. In the description of the present application, unless otherwise specified, the meaning of "a plurality of" is two or more.

[0028] In the description of the present application, it should be noted that, unless otherwise specified and limited, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium, or it can be connected inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0029] A turbine rim seal gap passive adjustment structure 1 according to an embodiment of the present application is described below with reference to the drawings.

[0030] As Figure 1 and Figure 2 shown, the turbine rim seal gap passive adjustment structure 1 according to the embodiment of the present application comprises a casing 10, a rotating disc 20, a stationary disc 30, a moving blade 40, a stationary blade 50 and an adjusting cavity 60.

[0031] The rotating disc 20 is rotatably arranged in the casing 10 and the outer circumferential surface of the rotating disc 20 is spaced apart from the inner circumferential surface of the casing 10. The stationary disc 30 is arranged in the casing 10 and the outer circumferential surface of the rotating disc 20 is spaced apart from the inner circumferential surface of the casing 10, and a main flow channel 11 is formed between the rotating disc 20 and the casing 10 and between the stationary disc 30 and the casing 10, and a disc cavity 12 is formed between the rotating disc 20 and the stationary disc 30.

[0032] An end surface of the rotating disc 20 facing the stationary disc 30 is provided with a rotating disc seal ring 21, and an end surface of the stationary disc 30 facing the rotating disc 20 is provided with a stationary disc seal ring 31, the stationary disc seal ring 31 is located radially outward of the rotating disc seal ring 21, the stationary disc 30 is provided with a receiving groove 32 located radially inward of the stationary disc seal ring 31, the rotating disc seal ring 21 extends into the receiving groove 32, a first gap 13 is formed between the outer circumferential surface of the rotating disc seal ring 21 and the inner circumferential surface of the stationary disc seal ring 31 and communicates with the receiving groove 32, and the inner circumferential surface of the receiving groove 32 is provided with a ring platform 33, and a second gap 14 is formed between the ring platform 33 and the rotating disc seal ring 21 and communicates with the receiving groove 32.

[0033] The moving blade 40 is arranged on the outer circumferential surface of the rotating disc 20 and spaced apart from the casing 10. The stationary blade 50 is arranged on the outer circumferential surface of the stationary disc 30 and connected to the inner circumferential surface of the casing 10. The adjusting cavity 60 is arranged on the end surface of the stationary disc 30 facing the rotating disc 20 and radially inward of the receiving groove 32 of the casing 10, and the adjusting cavity 60 is provided with an adjusting chamber 63, and the adjusting cavity 60 is provided with a plurality of labyrinth teeth 64 spaced apart in the axial direction of the casing 10 on the circumferential surface radially outward of the adjusting cavity 60, the adjusting chamber 63 and the receiving groove 32 communicate through a guide hole 34, and a jet hole 65 communicating with the adjusting chamber 63 is arranged between each adjacent two labyrinth teeth 64, and three gaps 15 are formed between the labyrinth teeth 64 and the inner circumferential surface of the rotating disc seal ring 21.

[0034] Specifically, the radial direction of the casing 10, i.e. the inner and outer direction, is shown by arrow B in the figure, and the axial direction of the casing 10 is shown by arrow C in the figure.

[0035] It should be understood that, Figure 1 and Figure 2 only a schematic view of one section of the turbine rim seal gap passive adjustment structure 1 in the circumferential direction of the casing 10 is shown, and the casing 10, the rotating disc 20, the stationary disc 30 and the adjusting cavity 60 are all revolution bodies passing through this section.

[0036] The skilled in the art can understand that when the rotating disc 20 rotates, the airflow from the disc cavity 12 to the main flow channel 11 is generated, and the high-temperature gas in the main flow channel 11 cannot easily invade the disc cavity 12 under the action of the airflow, but it is difficult to completely avoid.

[0037] The turbine rim sealing gap passive adjustment structure 1 according to the embodiment of the present application can prevent the high-temperature gas in the main flow channel 11 from easily invading the disc cavity 12 by the cooperation of the rotating disc sealing ring 21 and the static disc sealing ring 31.

[0038] In addition, by arranging the accommodating groove 32, when the gas invades the first gap 13, the accommodating groove 32 can store and buffer the invading high-temperature gas, so that the high-temperature gas cannot easily further invade the disc cavity 12 through the second gap 14.

[0039] In addition, by arranging the adjusting cavity 60, the adjusting cavity 60 is provided with an adjusting chamber 63, the adjusting cavity 60 is provided with a plurality of grids 64 spaced along the axial direction of the casing 10 on the circumferential surface of the radial outer side of the casing 10, the adjusting chamber 63 and the accommodating groove 32 are communicated through the guide hole 34, the jet hole 65 communicating the adjusting chamber 63 is arranged between each adjacent two grids 64, and the three gaps 15 are formed between the grid 64 and the inner circumferential surface of the rotating disc sealing ring 21. In this way, the high-temperature gas invading the accommodating groove 32 through the first gap 13 is mixed with the airflow inside the disc cavity 12 in the accommodating groove 32 to form a mixed gas flow of 600-800 degrees Celsius, the mixed gas flow is introduced into the adjusting chamber 63 of the adjusting cavity 60 through the guide hole 34, and then the mixed gas flow in the adjusting chamber 63 is sprayed between the plurality of grids 64 through the jet hole 65, and then returns to the accommodating groove 32 through the third gap 15 and the second gap 14, and then part of the airflow returns to the adjusting chamber 63 through the guide hole 34 again, and part of the airflow enters the main flow channel 11 through the first gap 13. Thus, by guiding the mixed gas flow in the accommodating groove 32 to the adjusting cavity 60 through the guide hole 34 and guiding the mixed gas flow between the adjacent grids 64 through the jet hole 65, the adjusting cavity 60 and the grid 64 can be expanded due to heating, the diameter of the adjusting cavity 60 and the grid 64 is increased, and thus the distance between the outer end of the grid 64 and the inner circumferential surface of the rotating disc sealing ring 21 is reduced, further preventing the high-temperature gas from invading the disc cavity 12, and reducing the leakage amount of the high-temperature gas leaking to the disc cavity 12.

[0040] That is, by applying the turbine rim sealing gap passive adjustment structure 1, the labyrinth 64 and the rotating disc sealing ring 21 can have a larger gap before the gas turbine is started, so that the labyrinth 64 is less likely to be scratched during the starting process of the gas turbine. During the process from starting to full load of the gas turbine, the static disc sealing ring 31 expands due to the high-temperature gas in the main flow channel 11, the rotating disc sealing ring 21 expands due to the high-temperature gas invading between the rotating disc sealing ring 21 and the static disc sealing ring 31, the guide holes 34 and the jet holes 65 guide the mixed gas flow in the containing groove 32 to the adjusting cavity 60 and the labyrinth 64, so that the adjusting cavity 60 and the labyrinth 64 expand due to heat, compared with the prior art in which only the static disc sealing ring and the rotating disc sealing ring expand, the third gap 15 between the labyrinth 64 and the rotating disc sealing ring 21 can be controlled within a reasonable range, which can facilitate avoiding the high-temperature gas invading the disc cavity 12 through the third gap 15, achieving passive adjustment of the sealing gap between the labyrinth and the rotating disc sealing ring, reducing the leakage amount of the high-temperature gas leaking to the disc cavity 12, improving the sealing effect of the turbine rim sealing gap passive adjustment structure 1, and prolonging the service life of the gas turbine.

[0041] Therefore, the turbine rim sealing gap passive adjustment structure 1 has the advantages of good sealing effect and the like.

[0042] Hereinafter, the turbine rim sealing gap passive adjustment structure 1 according to an embodiment of the present application will be described with reference to the accompanying drawings.

[0043] In some embodiments of the present application, as shown in Figure 1 and Figure 2 The turbine rim sealing gap passive adjustment structure 1 according to an embodiment of the present application includes a casing 10, a rotating disc 20, a static disc 30, a moving blade 40, a static blade 50, and an adjusting cavity 60.

[0044] Specifically, as shown in Figure 1 and Figure 2 The guide holes 34 are respectively in communication with the inner circumferential surface of the containing groove 32 and the side surface of the adjusting cavity 63 away from the rotating disc 20 in the axial direction of the casing 10. In this way, the mixed gas flow in the containing groove 32 can be guided to the adjusting cavity 60.

[0045] Advantageously, as shown in Figure 1 and Figure 2 The jet holes 65 are located at the centers of two adjacent labyrinths 64 in the axial direction of the casing 10. Those skilled in the art can understand that each jet hole 65 is located at the center of two adjacent labyrinths 64 in the axial direction of the casing 10. In this way, the heating of the labyrinth 64 can be more uniform.

[0046] Optionally, as shown in Figure 1 and Figure 2As shown, the two grate teeth 64 and the one jet hole 65 are provided.

[0047] More advantageously, the guide hole 34 is provided in plurality and is spaced along the circumference of the casing 10. In this way, the heating of the adjustment cavity 60 is more uniform.

[0048] Further, the jet hole 65 is provided in plurality and is spaced along the circumference of the casing 10. In this way, the heating of the grate tooth 64 is more uniform.

[0049] More specifically, as shown in Figure 1 and Figure 2 the inner circumferential surface of the rotating seal ring 21 is formed with honeycomb cells 22, and the third gap 15 is defined by the honeycomb cells 22 and the grate tooth 64. In this way, the honeycomb cells 22 can be used to form a unique sealing airflow, further improving the sealing effect at the third gap 15 and reducing the leakage at the third gap 15.

[0050] Further, the stationary blade 50 is provided in plurality and is spaced along the circumference of the stationary disc 30, and the rotating blade 40 is provided in plurality and is spaced along the circumference of the rotating disc 20. In this way, the disc cavity system of the gas turbine can be formed.

[0051] Figure 1 and Figure 2 A turbine rim seal gap passive adjustment structure 1 according to some examples of the present application is shown. As shown in Figure 1 and Figure 2 the adjustment cavity 60 includes an adjustment cavity body 61 and a mounting plate 62, the adjustment cavity body 61 is formed integrally with the stationary disc 30, and the mounting plate 62 is detachably mounted on the adjustment cavity body 61, and the grate tooth 64 is provided on the mounting plate 62. In this way, the adjustment cavity body 61 and the mounting plate 62 can be machined separately, facilitating the arrangement of the adjustment cavity 60. In addition, the grate tooth 64 is provided on the mounting plate 62, which can facilitate the replacement of the grate tooth 64 when the grate tooth 64 is worn out.

[0052] Specifically, as shown in Figure 1 and Figure 2 a plurality of sealing rings 67 are provided between the mounting plate 62 and the adjustment cavity body 61. Specifically, the plurality of sealing rings 67 are spaced along the radial direction of the casing 10. In this way, the sealing between the mounting plate 62 and the adjustment cavity body 61 can be improved, avoiding the leakage of airflow between the mounting plate 62 and the adjustment cavity body 61.

[0053] Specifically, the mounting plate 62 is detachably mounted on the adjustment cavity body 61 by means of the fastener 66. In this way, the mounting plate 62 can be easily disassembled and the sealing between the mounting plate 62 and the adjustment cavity body 61 can be improved.

[0054] A gas turbine according to an embodiment of the present application will be described below. The gas turbine according to an embodiment of the present application includes the turbine rim seal gap passive adjustment structure 1 according to the above-described embodiment of the present application.

[0055] The gas turbine according to an embodiment of the present application has the advantages of good sealing effect and the like by utilizing the turbine rim seal gap passive adjustment structure 1 according to the above-described embodiment of the present application.

[0056] Other configurations and operations of the gas turbine according to an embodiment of the present application are known to those skilled in the art and will not be described in detail here.

[0057] In the description of the present specification, the description referring to the terms "one embodiment", "some embodiments", "exemplary embodiment", "example", "specific example", or "some examples" and the like means 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 application. The exemplary description of the above terms in the present specification does not necessarily mean the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in an appropriate manner.

[0058] Although the embodiments of the present application have been shown and described, it is understood that various changes, modifications, substitutions and variations can be made therein without departing from the principles and spirit of the present application, the scope of which is defined by the claims and their equivalents.

Claims

1. A passive adjustment structure for the sealing gap of a turbine rim, characterized in that, include: Casing; A turntable, which is rotatably disposed within the housing and whose outer peripheral surface is spaced apart from the inner peripheral surface of the housing; A stationary disc is disposed within the housing, with its outer circumferential surface spaced apart from the inner circumferential surface of the housing. Main channels are formed between the turntable and the housing, and between the stationary disc and the housing. A disc cavity is formed between the turntable and the stationary disc. A turntable sealing ring is provided on the end face of the turntable facing the stationary disc, and a stationary disc sealing ring is provided on the end face of the stationary disc facing the turntable. The stationary disc sealing ring is located radially outside the turntable sealing ring in the housing. A receiving groove is provided on the stationary disc, radially inside the stationary disc sealing ring in the housing. The turntable sealing ring extends into the receiving groove. A first gap communicating with the receiving groove is formed between the outer circumferential surface of the turntable sealing ring and the inner circumferential surface of the stationary disc sealing ring. An annular platform is provided on the inner circumferential surface of the receiving groove, and a second gap communicating with the receiving groove is formed between the annular platform and the turntable sealing ring. A moving blade is disposed on the outer circumferential surface of the turntable and spaced apart from the casing; A stationary blade is disposed on the outer peripheral surface of the stationary plate and connected to the inner peripheral surface of the casing; An adjustment cavity is provided on the end face of the stationary disc facing the turntable and located radially inside the receiving groove of the housing. The adjustment cavity is provided with an adjustment chamber. The adjustment cavity is provided with a plurality of grates spaced axially along the outer side of the housing on the circumferential surface of the housing. The adjustment chamber and the receiving groove are connected through guide holes. A jet hole connecting the adjustment chamber is provided between each pair of adjacent grates. A third gap is formed between the grates and the inner circumferential surface of the turntable sealing ring.

2. The passive adjustment structure for turbine rim sealing clearance according to claim 1, characterized in that, The guide hole is connected to the inner circumferential surface of the receiving groove and the adjustment chamber on the side of the casing away from the turntable in the axial direction.

3. The passive adjustment structure for turbine rim sealing clearance according to claim 1, characterized in that, The jet orifice is located at the center of two adjacent teeth in the axial direction of the casing.

4. The passive adjustment structure for turbine rim sealing clearance according to claim 1, characterized in that, The guide holes are multiple and spaced apart circumferentially along the casing.

5. The passive adjustment structure for turbine rim sealing clearance according to claim 1, characterized in that, The jet holes are multiple and spaced apart circumferentially along the casing.

6. The passive adjustment structure for turbine rim sealing clearance according to claim 1, characterized in that, The inner circumferential surface of the turntable sealing ring is formed with a honeycomb core, and the third gap is defined by the honeycomb core and the comb teeth.

7. The passive adjustment structure for turbine rim sealing clearance according to claim 1, characterized in that, The stationary blades are multiple and spaced apart circumferentially along the stationary disk, and the moving blades are multiple and spaced apart circumferentially along the turntable.

8. The passive adjustment structure for turbine rim sealing clearance according to claim 1, characterized in that, The adjustment cavity includes an adjustment cavity body and a mounting plate. The adjustment cavity body is integrally formed with the stationary disc. The mounting plate is detachably mounted on the adjustment cavity body, and the grating teeth are provided on the mounting plate.

9. The passive adjustment structure for turbine rim sealing clearance according to claim 8, characterized in that, Multiple sealing rings are provided between the mounting plate and the main body of the adjustment cavity.

10. A gas turbine, characterized in that, Includes a passive adjustment structure for the turbine rim sealing clearance according to any one of claims 1-9.

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