Dynamic and static sealing assembly of gas turbine and assembling method

Abstract

The invention discloses a gas turbine dynamic and static seal assembly and an assembling method. The gas turbine dynamic and static sealing assembly comprises a stator body, a rotor body, a fixing plate, a static sealing part and a dynamic sealing part. The rotor body can rotate relative to the stator body. The fixed plate is detachably connected to the stator main body; the static sealing component is connected to the fixing plate and comprises a first sealing piece and a second sealing piece. The movable sealing part is connected to the rotor body and is adjacent to the static sealing part, the first sealing part and the movable sealing part are oppositely arranged in the radial direction of the rotor body at intervals, and the second sealing part and the movable sealing part are arranged in the axial direction of the rotor body at intervals; and the projections of the second sealing element and the movable sealing component in the axial direction of the rotor main body are partially overlapped. The replacement efficiency can be improved, the replacement cost can be reduced, meanwhile, the application range of the sealing assembly can be widened, and the sealing effect is improved.

Description

Technical Field

[0001] The invention belongs to the technical field of gas turbines, and in particular relates to a gas turbine dynamic and static seal component and an assembly method. Background Art

[0002] When the gas turbine is running, the dynamic and static clearance is a key parameter. If the dynamic and static clearance is too large, the gas leakage will be large, affecting the gas work and reducing efficiency. If the dynamic and static clearance is too small, dynamic and static friction will occur, causing unit vibration and affecting operation safety.

[0003] The dynamic and static sealing components in the related art are generally divided into two categories: one category does not allow dynamic and static friction to occur, and this category can be used when the dynamic and static clearance does not change much during operation. The other category allows a certain amount of dynamic and static friction, and the sealing component is replaced after being worn. This category is used when the dynamic and static clearance changes greatly during operation.

[0004] However, both types of seals in the related art have a certain scope of application. The non-abrasive seal can only be used when the gap changes slightly; the abrasive seal is generally used when the gap changes greatly. There is no case where both types of seals are used at the same time. In addition, the abradable seal assembly is usually welded to the stator body or the rotor body, which can easily cause deformation of the body during the welding process. When replacing, the stator or rotor body must be replaced together, which is costly. Summary of the invention

[0005] The present invention aims to solve one of the technical problems in the related art at least to a certain extent.

[0006] To this end, an embodiment of the present invention provides a gas turbine dynamic and static seal assembly, which can improve replacement efficiency and reduce replacement costs, while also expanding the application range of the seal assembly and improving the sealing effect.

[0007] An embodiment of the present invention provides a method for assembling a gas turbine dynamic and static seal assembly.

[0008] The gas turbine dynamic and static seal assembly according to the embodiment of the present invention comprises:

[0009] A stator body and a rotor body, wherein the rotor body is rotatable relative to the stator body;

[0010] A fixing plate, the fixing plate being detachably connected to the stator body;

[0011] A static sealing component, the static sealing component is connected to the fixed plate, and the static sealing component includes a first sealing component and a second sealing component;

[0012] A dynamic sealing component, the dynamic sealing component is connected to the rotor body and is arranged adjacent to the static sealing component, the first seal and the dynamic sealing component are opposite to and spaced apart in the radial direction of the rotor body, the second seal and the dynamic sealing component are spaced apart in the axial direction of the rotor body, and the projections of the second seal and the dynamic sealing component in the axial direction of the rotor body overlap.

[0013] The gas turbine dynamic and static seal assembly of the embodiment of the present invention can improve replacement efficiency and reduce replacement cost, and can also expand the application range of the seal assembly and improve the sealing effect.

[0014] In some embodiments, the stator body has a mounting groove, the fixing plate is arranged in the mounting groove, and a connecting piece is arranged between the stator body and the fixing plate.

[0015] In some embodiments, the width of the slot opening of the mounting slot is smaller than the width of the slot bottom of the mounting slot;

[0016] And / or, a first connecting hole is provided on the stator body, a second connecting hole is provided on the side of the fixing plate facing the bottom of the mounting groove, the first connecting hole corresponds to the second connecting hole, and the connecting member is arranged in the first connecting hole and the second connecting hole.

[0017] In some embodiments, the bottom of the mounting groove has a first section and second sections located on both sides of the first section in the width direction, the first section is recessed in the direction away from the groove opening of the mounting groove to form a sink groove, the fixing plate abuts against the second section, and there is a gap between the fixing plate and the bottom of the sink groove.

[0018] In some embodiments, the depth of the sink is 0.2 mm to 0.3 mm;

[0019] And / or, the width of the second section is 2 mm to 5 mm.

[0020] In some embodiments, the dynamic sealing component is provided with the second seal on both axial sides of the rotor body, a cavity is formed between the first seal and the second seal, and a partial section of the dynamic sealing component is located in the cavity.

[0021] In some embodiments, the dynamic sealing component comprises a first plate, the first plate is connected to the rotor body, the outer edge of the first plate is adjacent to the first sealing member, the second sealing member comprises an annular second plate, and partial sections of the first plate and partial sections of the second plate are both inclined relative to the radial direction of the rotor body so as to form a return gap flow channel in the cavity;

[0022] Or, the dynamic sealing component has a first plate, the first plate is connected to the rotor body, the outer edge of the first plate is adjacent to the first sealing member, and the second sealing member has a second annular plate; the first plate is provided with protrusions on both sides of the axial direction of the rotor body, and the second plate has a bending portion folded toward the first plate to form a return gap flow channel in the cavity.

[0023] In some embodiments, a gap is formed between the second seal and the dynamic seal component in the axial direction of the rotor body.

[0024] In some embodiments, the first seal is a wearable seal, and the second seal and the dynamic seal component are non-wearable seals;

[0025] And / or, the dynamic sealing component is integrally provided with the rotor body.

[0026] The gas turbine dynamic static seal assembly assembly method according to the embodiment of the present invention is used to install the gas turbine dynamic static seal assembly according to any one of the above embodiments, and the assembly method comprises:

[0027] The fixing plate and the static sealing component are connected in groups;

[0028] The fixing plate and the static sealing component are installed on the lower half and the upper half of the stator body and fixed by connecting pieces;

[0029] Placing the rotor body on the lower half of the stator body, and aligning the dynamic sealing component on the rotor body with the first sealing component and the second sealing component on the lower half of the stator body;

[0030] Placing the upper half of the stator body above the lower half of the stator body and the rotor body, and aligning the dynamic sealing component on the rotor body with the first sealing component and the second sealing component on the upper half of the stator body;

[0031] The lower half and the upper half of the stator body are connected. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 It is a schematic diagram of a gas turbine dynamic and static seal assembly (when not in contact with each other) according to an embodiment of the present invention.

[0033] Figure 2 It is a schematic diagram of a gas turbine dynamic and static seal assembly (when rubbing) according to an embodiment of the present invention.

[0034] Figure 3 It is a schematic diagram of the connection between the static sealing component and the stator body according to an embodiment of the present invention.

[0035] Figure 4It is a schematic diagram of the connection between the static sealing component and the stator body from another perspective of an embodiment of the present invention.

[0036] Figure 5 yes Figure 4 Schematic cross-sectional view along the AA axis.

[0037] Figure 6 yes Figure 5 Enlarged schematic diagram of part B in the middle.

[0038] Figure 7 yes Figure 5 Enlarged schematic diagram of part C in the middle.

[0039] Figure 8 It is a schematic diagram of a gas turbine dynamic and static seal assembly according to another embodiment of the present invention.

[0040] Reference numerals:

[0041] 1. stator body; 11. mounting groove; 12. sink groove; 13. first section; 14. second section; 15. first connecting hole;

[0042] 2. Rotor body;

[0043] 3. static sealing component; 31. fixing plate; 32. first sealing member; 33. second sealing member; 34. bending portion; 35. second communicating hole;

[0044] 4. Dynamic sealing component; 41. Raised portion;

[0045] 5. Connectors. DETAILED DESCRIPTION

[0046] Embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used to explain the present invention, but should not be understood as limiting the present invention.

[0047] like Figure 1 and Figure 2 As shown, the gas turbine dynamic and static seal assembly according to the embodiment of the present invention comprises a stator body 1, a rotor body 2, a fixing plate 31, a static seal component 3 and a dynamic seal component 4.

[0048] The rotor body 2 is rotatable relative to the stator body 1. Specifically, the rotor body 2 and the stator body 1 are coaxially arranged. The rotor body 2 can be arranged in the inner cavity of the stator body 1. The circumferential outer edge of the rotor body 2 is adjacent to the side wall of the inner cavity of the stator body 1, and there is a gap between the two. The gas turbine dynamic and static sealing assembly in this embodiment is used to seal the gap. For example, the rotor body 2 is a moving blade, and the stator body 1 is a cylinder body.

[0049] The fixing plate 31 is detachably connected to the stator body 1. The static sealing component 3 is connected to the fixing plate 31, and the static sealing component 3 includes a first sealing member 32 and a second sealing member 33. The static sealing component 3 is a part of the dynamic and static sealing assembly, which is fixed to the stator body 1. When replacement is required, the fixing plate 31 can be directly removed to replace the static sealing component 3.

[0050] The dynamic seal component 4 is another part of the dynamic and static seal assembly. The dynamic seal component 4 is connected to the rotor body 2 and is arranged adjacent to the static seal component 3. The first seal 32 and the dynamic seal component 4 are arranged opposite to each other and spaced apart in the radial direction of the rotor body 2. The second seal 33 and the dynamic seal component 4 are spaced apart in the axial direction of the rotor body 2, and the second seal 33 and the dynamic seal component 4 partially overlap in the axial direction of the rotor body 2. A sealing system is formed between the dynamic seal component 4, the first seal 32, and the second seal 33.

[0051] In the transient process, the gap between the rotor body 2 and the stator body 1 at some positions is reduced, and at this time, the dynamic sealing component 4 and the first sealing component 32 will collide and rub. Figure 2 As shown, since the static seal assembly is detachable, the first seal 32 can be set as a seal that can be abraded. After the first seal 32 is worn, it can be replaced, which greatly reduces the cost of replacement and improves the efficiency of replacement.

[0052] During steady-state operation, the gap between the stator body 1 and the rotor body 2 is relatively stable without interfering with each other, and a stable sealing system is formed between the dynamic sealing component 4 and the first seal 32 and the second seal 33, which can ensure the normal and stable operation of the equipment.

[0053] The gas turbine dynamic static seal assembly of the embodiment of the present invention can improve the replacement efficiency, reduce the replacement cost, and at the same time can also expand the application range of the seal assembly and improve the sealing effect. The present embodiment has good adaptability to the gap, can reasonably set the gap between the rotor body 2 and the stator body 1, and control the gap between the two through the gas turbine dynamic static seal assembly of the present embodiment, thereby improving the sealing effect.

[0054] In this embodiment, "adjacent" means that one component is arranged close to another component, but the two components are not in contact with each other, and there is a certain gap between them. For example, the dynamic seal component 4 is arranged on the rotor body 2, but the dynamic seal component 4 is arranged adjacent to the static seal component 3, so that the dynamic seal component 4 does not contact the first seal 32 and the second seal 33, but a sealing system can be formed between the two, avoiding excessive gaps, reducing gas leakage, improving gas working efficiency, and ensuring safe and stable operation of the unit.

[0055] Other embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0056] like Figure 1-Figure 8 As shown, a gas turbine dynamic and static seal assembly includes a stator body 1, a rotor body 2, a fixing plate 31, a static seal component 3 and a dynamic seal component 4.

[0057] The rotor body 2 is rotatable relative to the stator body 1. Specifically, the rotor body 2 and the stator body 1 are coaxially arranged. The rotor body 2 can be arranged in the inner cavity of the stator body 1. The circumferential outer edge of the rotor body 2 is adjacent to the side wall of the inner cavity of the stator body 1, and there is a gap between the two. The gas turbine dynamic and static sealing assembly in this embodiment is used to seal the gap. For example, the rotor body 2 is a moving blade, and the stator body 1 is a cylinder body.

[0058] The stator body 1 has a mounting groove 11, a fixing plate 31 is arranged in the mounting groove 11, and a connecting member 5 is arranged between the stator body 1 and the fixing plate 31. The fixing plate 31 is detachably connected to the stator body 1. Specifically, a first connecting hole 15 is arranged on the stator body 1, and a second connecting hole is arranged on one side of the fixing plate 31 facing the bottom of the mounting groove 11, the first connecting hole corresponds to the second connecting hole, and the connecting member 5 is arranged in the first connecting hole and the second connecting hole.

[0059] The width of the slot opening of the mounting slot 11 is smaller than the width of the slot bottom of the mounting slot 11. For example, the mounting slot 11 is a T-slot or a wedge-shaped slot. When the fixing plate 31 is arranged in the mounting slot 11, it can be engaged to prevent the fixing plate 31 from falling directly out of the mounting slot 11, thereby improving the stability of the structure and reducing the force on the connector 5.

[0060] The bottom of the mounting groove 11 of the present embodiment has a first section 13 and second sections 14 located on both sides of the first section 13 in the width direction thereof. The first section 13 is recessed in the direction of the groove opening away from the mounting groove 11 to form a sinking groove 12. The fixing plate 31 abuts against the second section 14, and there is a gap between the fixing plate 31 and the bottom of the sinking groove 12.

[0061] The depth of the sink groove 12 is 0.2 mm to 0.3 mm, for example, the depth of the sink groove 12 is 0.2 mm, 0.21 mm, 0.24 mm, 0.25 mm or 0.3 mm, and the width of the second section 14 is 2 mm to 5 mm, for example, the width of the second section 14 is 2 mm, 2.2 mm, 2.4 mm, 3 mm, 3.2 mm, 4 mm or 5 mm. Through the structural design of the mounting groove 11, the force performance of the fixing plate 31 can be optimized, so that the two sides and the middle of the fixing plate 31 form a three-point support effect, improve the stability of the force between the connecting member 5 and the stator body 1 and the fixing plate 31, and ensure that the fixing plate 31 is stably supported in the mounting groove 11.

[0062] The static sealing component 3 is connected to the fixing plate 31, and the static sealing component 3 includes a first sealing member 32 and a second sealing member 33. As a part of the dynamic and static sealing assembly, the static sealing component 3 is fixed to the stator body 1. When replacement is required, the fixing plate 31 can be directly removed to replace the static sealing component 3.

[0063] The dynamic seal component 4 is another part of the dynamic and static seal assembly. The dynamic seal component 4 is connected to the rotor body 2 and is arranged adjacent to the static seal component 3. The first seal 32 and the dynamic seal component 4 are arranged opposite to each other and spaced apart in the radial direction of the rotor body 2. The second seal 33 and the dynamic seal component 4 are spaced apart in the axial direction of the rotor body 2, and the projections of the second seal 33 and the dynamic seal component 4 in the axial direction of the rotor body 2 partially overlap. The dynamic seal component 4 is provided with the second seal 33 on both sides of the axial direction of the rotor body 2. A cavity is formed between the first seal 32 and the second seal 33, and a partial section of the dynamic seal component 4 is located in the cavity. A sealing system is formed between the dynamic seal component 4 and the first seal 32 and the second seal 33.

[0064] In other words, the first seal 32 is located in the radial direction of the dynamic seal component 4 on the rotor body 2, and the second seal 33 is located in the axial direction of the dynamic seal on the rotor body 2. The cavity between the first seal 32 and the two second seals 33 is annular, and its cross section is generally U-shaped.

[0065] The first seal 32 is a wearable seal, and the second seal 33 and the dynamic seal component 4 are non-wear seals. During the operation of the gas turbine, the dynamic seal component 4 rubs against the first seal 32, then the first seal 32 will be worn, and the dynamic seal component 4 will not be worn. Since the second seal 33 is axially spaced from the dynamic seal component 4, no rubbing will occur between the two.

[0066] Optionally, the dynamic sealing component 4 is integrally provided with the rotor body 2, for example, the dynamic sealing component 4 is made of a metal material that is the same as or similar to the material of the rotor body 2, and is integrally formed with the rotor body 2. The first seal 32 and the second seal 33 can be made of a material that is resistant to high temperatures and is easy to wear. When the dynamic sealing component 4 rubs against the first seal 32, the first seal 32 is worn due to rubbing.

[0067] In order to construct a good sealing system using the dynamic sealing component 4 , the first sealing member 32 and the second sealing member 33 , this embodiment provides two different combining methods.

[0068] The structural form of the dynamic sealing component 4, the first sealing member 32 and the second sealing member 33 is:

[0069] like Figure 1 and Figure 2 As shown, the dynamic sealing component 4 has a first plate, the first plate is connected to the rotor body 2, the outer edge of the first plate is adjacent to the first seal 32, the second seal 33 has a second plate in an annular shape, and partial sections of the first plate and partial sections of the second plate are both inclined relative to the radial direction of the rotor body 2 to form a return gap flow channel in the cavity. In other words, partial sections of the first plate in the radial direction of the rotor body 2 are inclined, and partial sections of the second plate in the radial direction of the rotor body 2 are also inclined. For example, the angle between the first plate and the second plate and the radial plane of the rotor body 2 is 10 to 40 degrees, and the first plate and the second plate are roughly parallel, so that the cavity of the static sealing component 3 can be constructed with a return gap flow channel through the dynamic sealing component 4 to inhibit the flow of airflow in the return gap flow channel, thereby achieving a sealing effect.

[0070] The second structural form of the dynamic sealing component 4, the first sealing member 32 and the second sealing member 33 is:

[0071] like Figure 8 As shown, the dynamic sealing component 4 has a first plate, the first plate is connected to the rotor body 2, the outer edge of the first plate is adjacent to the first sealing member 32, and the second sealing member 33 has a second plate in an annular shape; the first plate is provided with protrusions 41 on both sides of the axial direction of the rotor body 2, and the second plate has a bending portion 34 folded toward the first plate, so that a return gap flow channel is formed in the cavity. In other words, the cavity of the static sealing component 3 can be constructed as a return gap flow channel through the first plate, the protrusion 41 on the first plate, and the bending portion 34 on the second plate, so as to suppress the airflow from flowing in the return gap flow channel and achieve a sealing effect.

[0072] The "return gap flow channel" in this embodiment means that in the flow channel, the airflow directions in different sections are different, forming multiple turns. For example, the axial direction of the rotor body 2 has a first direction and a second direction in opposite directions. The airflow direction in one section flows in a direction approximately in the first direction, and the airflow direction in another section flows in a direction approximately perpendicular to the first direction. Alternatively, the airflow direction in another section flows in a direction inclined toward the second direction, thereby increasing the resistance of the airflow, suppressing the flow of the airflow, and achieving a sealing effect.

[0073] In the above embodiment, in order to facilitate the assembly of the stator body 1, the rotor body 2 and the dynamic and static sealing assembly, the second seal 33 and the dynamic sealing component 4 have a gap in the axial direction of the rotor body 2, that is, the projections of the second seal 33 and the dynamic sealing component 4 in the radial direction of the rotor body 2 do not overlap.

[0074] The gas turbine dynamic static seal assembly assembly method according to an embodiment of the present invention is used to install the gas turbine dynamic static seal assembly in any one of the above embodiments, and the assembly method comprises:

[0075] S101, the fixing plate and the static sealing component are connected in groups. After the fixing plate and the static sealing component are assembled and connected together, it is convenient to connect them with the stator body later.

[0076] S102, install a fixing plate and a static sealing component on the lower half and the upper half of the stator body and fix them through a connecting piece. It should be understood that the stator body is divided into an upper half and a lower half, and the rotor body is located between the upper half and the lower half. For example, the stator body is a circular cylinder, and the upper half and the lower half are both semicircular cylinders. When installing the dynamic and static sealing assembly, first install the fixing plate and the static sealing component in the lower half.

[0077] S103, placing the rotor body on the lower half of the stator body, and aligning the dynamic sealing component on the rotor body with the first sealing component and the second sealing component on the lower half of the stator body. Since there is a gap between the second sealing component and the dynamic sealing component in the axial direction of the rotor body, when the rotor body is placed on the lower half of the stator body, no interference occurs, and accurate alignment can be achieved.

[0078] S104, placing the upper part of the stator body on the lower part of the stator body and above the rotor body, and aligning the dynamic sealing component on the rotor body with the first seal and the second seal on the upper part of the stator body. At this point, not only the alignment of the dynamic sealing component on the rotor body with the first seal and the second seal on the upper part is completed, but also the assembly of the stator body is achieved.

[0079] S105, connecting the lower half and the upper half of the stator body, thereby completing the assembly of the stator body and the rotor body, and realizing the installation of the dynamic and static sealing components.

[0080] In the description of the present invention, it is to be understood that the terms “center”, “longitudinal”, “lateral”, “length”, “width”, “thickness”, “up”, “down”, “front”, “back”, “left”, “right”, “vertical”, “horizontal”, “top”, “bottom”, “inside”, “outside”, “clockwise”, “counterclockwise”, “axial”, “radial”, “circumferential”, etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0081] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0082] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral one; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0083] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0084] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the described specific features, structures, materials or characteristics may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0085] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.

Claims

1. A gas turbine dynamic and static seal assembly, characterized in that: include: A stator body and a rotor body, wherein the rotor body is rotatable relative to the stator body; A fixing plate, the fixing plate being detachably connected to the stator body; A static sealing component, the static sealing component is connected to the fixed plate, and the static sealing component includes a first sealing component and a second sealing component; A dynamic sealing component, wherein the dynamic sealing component is connected to the rotor body and is arranged adjacent to the static sealing component, the first seal and the dynamic sealing component are arranged opposite to each other and spaced apart in the radial direction of the rotor body, the second seal and the dynamic sealing component are spaced apart in the axial direction of the rotor body, and the projections of the second seal and the dynamic sealing component in the axial direction of the rotor body partially overlap.

2. The gas turbine dynamic and static seal assembly according to claim 1, characterized in that: The stator body has a mounting groove, the fixing plate is arranged in the mounting groove, and a connecting piece is arranged between the stator body and the fixing plate.

3. The gas turbine dynamic and static seal assembly according to claim 2, characterized in that: The width of the slot opening of the mounting slot is smaller than the width of the slot bottom of the mounting slot; And / or, a first connecting hole is provided on the stator body, a second connecting hole is provided on the side of the fixing plate facing the bottom of the mounting groove, the first connecting hole corresponds to the second connecting hole, and the connecting member is arranged in the first connecting hole and the second connecting hole.

4. The gas turbine dynamic and static seal assembly according to claim 2, characterized in that: The bottom of the mounting groove has a first section and second sections on both sides of the first section in the width direction, the first section is recessed in the direction away from the groove opening of the mounting groove to form a sink, the fixing plate abuts against the second section, and there is a gap between the fixing plate and the bottom of the sink.

5. The gas turbine dynamic and static seal assembly according to claim 4, characterized in that: The depth of the sink is 0.2 mm to 0.3 mm; And / or, the width of the second section is 2 mm to 5 mm.

6. The gas turbine dynamic and static seal assembly according to any one of claims 1 to 5, characterized in that: The dynamic sealing component is provided with the second sealing members on both sides of the rotor body in the axial direction, a cavity is formed between the first sealing member and the second sealing member, and a partial section of the dynamic sealing component is located in the cavity.

7. The gas turbine dynamic and static seal assembly according to claim 6, characterized in that: The dynamic sealing component comprises a first plate, the first plate is connected to the rotor body, the outer edge of the first plate is adjacent to the first sealing member, the second sealing member comprises an annular second plate, partial sections of the first plate and partial sections of the second plate are both inclined relative to the radial direction of the rotor body so as to form a return gap flow channel in the cavity; Or, the dynamic sealing component has a first plate, the first plate is connected to the rotor body, the outer edge of the first plate is adjacent to the first sealing member, and the second sealing member has a second annular plate; the first plate is provided with protrusions on both sides of the axial direction of the rotor body, and the second plate has a bending portion folded toward the first plate to form a return gap flow channel in the cavity.

8. The gas turbine dynamic and static seal assembly according to claim 7, characterized in that: The second seal and the dynamic seal member have a gap in the axial direction of the rotor body.

9. The gas turbine dynamic and static seal assembly according to claim 1, characterized in that: The first seal is a wearable seal, and the second seal and the dynamic seal component are non-wearable seals; And / or, the dynamic sealing component is integrally provided with the rotor body.

10. A method for assembling a gas turbine dynamic and static seal assembly, characterized in that: For installing a gas turbine dynamic and static seal assembly according to any one of claims 1 to 9, the assembly method comprises: The fixing plate and the static sealing component are connected in groups; The fixing plate and the static sealing component are installed on the lower half and the upper half of the stator body and fixed by connecting pieces; Placing the rotor body on the lower half of the stator body, and aligning the dynamic sealing component on the rotor body with the first sealing component and the second sealing component on the lower half of the stator body; Placing the upper half of the stator body above the lower half of the stator body and the rotor body, and aligning the dynamic sealing component on the rotor body with the first sealing component and the second sealing component on the upper half of the stator body; The lower half and the upper half of the stator body are connected.

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