A turbine seal structure

Abstract

The utility model relates to a gas turbine sealing technical field especially relates to a turbine comb tooth seal structure, including the gas seal body, the gas seal body includes a plurality of circumferential splicing gas seal body arc segment, a plurality of concave-convex structures, a plurality of concave-convex structures are continuously distributed and form the comb tooth gas seal on two gas seal body arc segments of splicing, sealing sheet, the utility model discloses, due to the setting of concave-convex structure, first through the design of local gas seal, make the clearance of gas seal body's axial can be closely contacted, avoid the stress concentration problem due to thermal expansion simultaneously, improve the sealing effect between the connecting surface of two gas seal body arc segments of splicing, and the comb tooth gas seal formed by the continuously distributed multiple concave-convex structures, reduce the flow rate and flow of airflow, can also prevent airflow from flowing directly from the clearance between the gas seal body arc segment, improve the efficiency of gas turbine greatly, thereby always keep good sealing state, improve the overall sealing performance.

Description

Technical Field

[0001] This utility model relates to the field of gas turbine sealing technology, and in particular to a turbine comb-tooth sealing structure. Background Technology

[0002] The statements herein provide only background information in relation to this invention and do not necessarily constitute prior art.

[0003] When a gas turbine is working, sealing is a key aspect to ensure its efficient and safe operation, and it generally involves a variety of structural designs.

[0004] Currently, to prevent friction and collision between the rotor and stator, gas seals are installed in the gaps between them for effective sealing, improving unit efficiency and ensuring safe operation of the gas turbine. However, existing gas seals consist of multiple gas seal segments, and the existing connection method between these segments is a flat-head connection, which allows airflow to flow directly through the gaps between the gas seal segments, resulting in significant air leakage. Utility Model Content

[0005] The purpose of this utility model is to address the aforementioned shortcomings by providing a turbine comb-tooth sealing structure.

[0006] To solve the above technical problems, the present invention adopts the following technical solution: a turbine comb sealing structure, including an air seal body located at the center of the turbine nozzle ring, the air seal body including multiple air seal body arc segments spliced ​​along the circumference, the multiple air seal body arc segments spliced ​​together to form a complete ring; Multiple sets of concave and convex structures are arranged along the axial direction of the gas seal body on the two spliced ​​arc segments of the gas seal body. The multiple sets of concave and convex structures are continuously distributed on the two spliced ​​arc segments of the gas seal body to form a comb-tooth gas seal, which is used to seal the axial direction of the gas seal body. A sealing plate is disposed on the two spliced ​​arc segments of the gas seal body and close to the inner end of the gas seal body. The sealing plate is installed and inserted along the axial direction of the gas seal body to seal the radial direction of the gas seal body.

[0007] Furthermore, the concave-convex structure includes a protrusion and a groove, the protrusion being disposed on a straight end face of each of the gas seal body arc segments, and the groove being disposed on another straight end face of each of the gas seal body arc segments; The operation involves splicing one of the gas seal body arc segments to another adjacent gas seal body arc segment, whereby the protrusion on one gas seal body arc segment will fit into the groove on the other gas seal body arc segment to form a partial gas seal.

[0008] Furthermore, the groove is provided with a reserved space for the expansion and change of the protrusion.

[0009] Furthermore, the sealing sheet has a sealing groove on its exterior and on the two interlocking gas seal segments for matching use; The sealing sheet can freely expand and contract within the sealing groove.

[0010] The beneficial effects of this utility model are reflected in: This invention, due to the design of the concave-convex structure, firstly, through the local air seal design, allows for tight contact in the axial gaps of the air seal body, while avoiding stress concentration caused by thermal expansion. This improves the sealing effect between the connecting surfaces of the two spliced ​​air seal body arc segments. Furthermore, the comb-tooth air seal formed by multiple continuously distributed concave-convex structures causes the airflow to suddenly narrow and accelerate as it passes through each structure, resulting in a partial decrease in pressure. This decomposes the total pressure difference across each concave-convex structure, making the pressure difference before and after each structure very small, thus reducing the airflow velocity and flow rate. Additionally, the sealing sheet can freely expand and contract within the sealing groove, adapting to deformation caused by temperature changes and preventing airflow from directly passing through the gaps between the air seal body arc segments. This reduces interstage leakage in the gas turbine, significantly improving the efficiency of the gas turbine and maintaining a consistently good sealing condition, thereby enhancing the overall sealing performance. Attached Figure Description

[0011] Figure 1 This is a three-dimensional structural view of two spliced ​​gas seal segments in one embodiment of the present invention. Figure 2 This is a top view of two spliced ​​gas seal segments in one embodiment of the present invention; Figure 3 This is a three-dimensional structural view of an air seal body composed of multiple air seal body arc segments in one embodiment of the present invention.

[0012] In the picture: 1. Gas seal arc segment; 2. Sealing sheet; 3. Protrusion; 4. Groove. Detailed Implementation

[0013] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only a part of the embodiments of the present utility model, and not all of them. Unless otherwise specified, the embodiments and features in the embodiments of this application can be combined with each other. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present utility model.

[0014] Please see Figure 1-3This utility model discloses a turbine comb sealing structure, including an air seal body located at the center of the turbine nozzle ring. The air seal body includes multiple air seal body arc segments 1 spliced ​​together in the circumferential direction, and the multiple air seal body arc segments 1 spliced ​​together form a complete ring. Multiple sets of concave and convex structures are arranged along the axial direction of the gas seal body on the two spliced ​​arc segments 1 of the gas seal body. The multiple sets of concave and convex structures are continuously distributed on the two spliced ​​arc segments 1 of the gas seal body to form a comb-tooth gas seal, which is used to seal the axial direction of the gas seal body. A sealing piece 2 is disposed on the two spliced ​​arc segments 1 of the gas seal body and close to the inner end of the gas seal body. The sealing piece 2 is installed and inserted along the axial direction of the gas seal body to seal the radial direction of the gas seal body.

[0015] In specific implementation, a ring is formed by sequentially splicing multiple gas seal body arc segments 1 along the circumference to form a gas seal body located at the center of the turbine nozzle ring. During the splicing of two adjacent gas seal body arc segments 1, a comb-tooth gas seal is formed by assembling multiple sets of concave and convex structures continuously distributed on the two gas seal body arc segments 1. At this time, when the airflow passes through a concave and convex structure, the flow channel suddenly narrows, the flow velocity increases, and the pressure decreases. This causes the total pressure difference to be decomposed on each concave and convex structure. The pressure difference before and after each concave and convex structure is very small, which reduces the flow velocity and flow rate of the airflow, effectively increases the sealing effect of the gas seal body, and realizes the axial sealing function of the gas seal body. Furthermore, by inserting a sealing piece 2 between the two gas seal arc segments 1 and near the inner end of the gas seal along the axial direction of the gas seal, the radial direction of the gas seal can be effectively sealed, preventing airflow from flowing directly through the gap between the gas seal arc segments 1. This can reduce the leakage between gas turbine stages and greatly improve the efficiency of the gas turbine.

[0016] It should be noted that the contact surface between the sealing sheet 2 and the gas seal body has undergone special surface treatment, which improves wear resistance and corrosion resistance, thereby extending the service life of the overall structure.

[0017] In one embodiment, the concave-convex structure includes a protrusion 3 and a groove 4. The protrusion 3 is disposed on a straight end face of each of the gas seal body arc segments 1, and the groove 4 is disposed on another straight end face of each of the gas seal body arc segments 1. When one of the gas seal arc segments 1 is spliced ​​to another adjacent gas seal arc segment 1, the protrusion 3 on one gas seal arc segment 1 will fit into the groove 4 on the other gas seal arc segment 1 to form a partial gas seal. This design, through the integrally formed protrusion 3 on one straight end face of the gas seal arc segment 1 and the machined groove 4 on another straight end face of the gas seal arc segment 1, allows the protrusion 3 and groove 4 of adjacent gas seal arc segments 1 to form a complete ring during the assembly process. When heated, the protrusion 3 can expand along the groove 4, allowing the axial gap of the gas seal to make close contact, thus improving the sealing effect between the connecting surfaces of the two spliced ​​gas seal arc segments 1.

[0018] In one embodiment, the groove 4 is provided with a reserved space for the expansion and change of the protrusion 3. This design, by machining the reserved space in the groove 4, ensures that when the protrusion 3 expands due to heat, the protrusion 3 will be in close contact with the groove 4, and the reserved space will be used for the expansion and filling of the protrusion 3, providing a directional and controllable space and avoiding stress generation.

[0019] It should be noted that when "stress" is constrained, it may exceed the yield limit of the material, causing permanent deformation of the component, or even direct cracking or breakage.

[0020] In one embodiment, the sealing sheet 2 has a sealing groove on its exterior and on the two interlocking gas seal segments 1 for use; The sealing sheet 2 can freely expand and contract within the sealing groove. With this design, the sealing grooves machined on the two gas seal body arc segments 1, and the sealing sheet 2 freely expanding and contracting within the sealing grooves, will make tight contact with the inside of the sealing groove after the sealing sheet 2 expands due to heat, effectively sealing the radial direction of the gas seal body and effectively preventing airflow from flowing directly through the gap between the gas seal body arc segments 1.

[0021] It should be noted that if the embodiments of this utility model involve directional indicators (such as up, down, left, right, front, back, etc.), the directional indicators are only used to explain the relative positional relationship and movement of the components in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicators will also change accordingly.

[0022] Furthermore, if the embodiments of this utility model involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of indicated technical features. Therefore, features defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. If the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this utility model.

[0023] Additionally, "multiple" refers to two or more.

[0024] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A turbine comb-tooth sealing structure, comprising a gas seal body located at the center of a turbine nozzle ring, characterized in that: The gas seal body includes multiple gas seal body arc segments (1) spliced ​​together along the circumference, and the multiple gas seal body arc segments (1) spliced ​​together form a complete ring; Multiple sets of concave and convex structures are arranged along the axial direction of the gas seal body on the two spliced ​​arc segments (1) of the gas seal body. The multiple sets of concave and convex structures are continuously distributed on the two spliced ​​arc segments (1) of the gas seal body to form a comb-tooth gas seal, which is used to seal the axial direction of the gas seal body. A sealing piece (2) is disposed on the two spliced ​​gas seal segments (1) and close to the inner end of the gas seal. The sealing piece (2) is installed and inserted along the axial direction of the gas seal to seal the radial direction of the gas seal.

2. The turbine comb-tooth sealing structure according to claim 1, characterized in that: The concave-convex structure includes a protrusion (3) and a groove (4). The protrusion (3) is disposed on a straight end face of each of the gas seal arc segments (1), and the groove (4) is disposed on another straight end face of each of the gas seal arc segments (1). When one of the gas seal segments (1) is spliced ​​to another adjacent gas seal segment (1), the protrusion (3) on the gas seal segment (1) will fit into the groove (4) on the other gas seal segment (1) to form a local gas seal.

3. The turbine comb-tooth sealing structure according to claim 2, characterized in that: The groove (4) is provided with a reserved space for the expansion and change of the protrusion (3).

4. The turbine comb-tooth sealing structure according to claim 1, characterized in that: The sealing sheet (2) has a sealing groove on its exterior and on the two gas seal segments (1) that are joined together. The sealing sheet (2) can freely expand and contract within the sealing groove.

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