Gas turbine rim sealing structure with pre-rotation function

Abstract

The utility model relates to a gas turbine rim sealing structure with a pre-rotation function, which comprises a movable disc and a static disc, more than one group of flow channel grooves are arranged between the movable disc and the static disc, flow choking components are arranged in the flow channel grooves, and the flow choking components are matched with the side walls of the flow channel grooves to form a Tesla valve channel; the flow choking part comprises a first part core and a second part core, a plurality of groups of pre-rotating rib plates are uniformly arranged between the first part core and the second part core, and the length extension direction of the pre-rotating rib plates is inclined to the radial direction of the movable disc; reverse flow is generated through the symmetrical Tesla flow channels under the working condition of reverse flow, flow resistance is enhanced, gas invasion is restrained, and the sealing performance of the rim is improved; the inclined pre-rotation fins endow the leakage flow with a circumferential velocity component, and pre-rotation control over the leakage flow is achieved.

Description

TECHNICAL FIELD

[0001] The utility model relates to a gas turbine rim seal structure with pre-rotation function belongs to sealing technical field. BACKGROUND

[0002] The most effective method to improve the performance of an aero gas turbine engine is to increase the turbine inlet gas temperature. Since the turbine works at high temperature and high speed for a long time, it needs to withstand high thermal stress and centrifugal stress. In order to ensure the reliable operation of the engine, the aero engine air system needs to provide turbine blade cooling air to reduce the turbine blade temperature.

[0003] After the cooling air provided by the aero engine air system reaches the disc cavity from the internal passage, part of the cooling air is used to prevent the high-temperature main flow gas from entering the rotating disc cavity. This part of the cooling air is usually called sealing cooling air. In related technologies, the aero engine generally uses a grate structure as a rim seal, and prevents the main flow high-temperature gas from entering the rotating disc cavity through the sealing cooling air. This phenomenon of the main flow gas entering the disc cavity through the rim seal is called gas intrusion or gas backflow.

[0004] If the amount of sealing cooling air is insufficient, the main flow high-temperature gas will enter the engine through the rim seal structure, causing gas intrusion, greatly reducing the service life of the engine, and the disc cavity is not heat-resistant and is easily damaged. The grate structure is replaced by a Tesla flow channel in the prior art;

[0005] For example, the patent number CN114909188B announced "a gas turbine turbine disc rim seal structure", the turbine static disc and the turbine rotating disc are installed with the positioning ring, the positioning ring is provided with the Tesla valve channel, the excellent one-way conduction performance of the Tesla valve channel effectively prevents the occurrence of gas intrusion, and reduces the effect of the amount of sealing cooling air entering the disc cavity;

[0006] However, the Tesla valve channel is composed of a first annular groove and a second annular groove in relative movement, and a straight-through channel is formed between the first annular groove and the second annular groove. When the cooling air in the disc cavity cools the outer end wall of the turbine rotating disc through the Tesla valve channel, the cooling air cannot give the fluid a circumferential speed when it flows radially outward into the blade channel. UTILITY MODEL CONTENTS

[0007] The utility model aims to provide a gas turbine rim seal structure with pre-rotation function to solve the problems raised in the above background technology.

[0008] The technical scheme of the utility model is as follows:

[0009] A gas turbine rim seal structure with a pre-rotation function, comprising a dynamic disc and a static disc, a plurality of flow channel grooves are arranged between the dynamic disc and the static disc, a flow blocking component is arranged in the flow channel groove, and the flow blocking component and the side wall of the flow channel groove cooperate to form a Tesla valve channel.

[0010] The flow blocking component comprises a first core and a second core, and a plurality of pre-rotation rib plates are uniformly arranged between the first core and the second core, and the length extension direction of the pre-rotation rib plates is inclined to the radial direction of the dynamic disc.

[0011] Preferably, the flow channel groove comprises a dynamic disc groove arranged on the side wall of the dynamic disc and a static disc groove arranged on the side wall of the static disc, and the dynamic disc groove and the static disc groove are spliced to form the flow channel groove.

[0012] Preferably, the first core is arranged in the static disc groove and has a spacing between the first core and the inner side wall of the static disc groove, and the second core is fixed in the dynamic disc groove and has a spacing between the second core and the inner side wall of the dynamic disc groove.

[0013] Preferably, the first core and the second core are symmetrically arranged, and a straight channel is formed between the first core and the second core.

[0014] Preferably, the second core is fixed to the inner side wall of the dynamic disc groove through a plurality of uniformly arranged fixing rib plates.

[0015] Preferably, the length extension direction of the fixing rib plate is consistent with the length extension direction of the pre-rotation rib plate.

[0016] Preferably, the fixing rib plate and the pre-rotation rib plate are fixed and integrated one by one.

[0017] Preferably, a plurality of the fixing rib plates or the pre-rotation rib plates are uniformly distributed in a circumferential direction around the dynamic disc axis.

[0018] Preferably, the included angle between the length extension direction of the pre-rotation rib plate and the radial direction of the dynamic disc is 30°-60°.

[0019] Preferably, the two adjacent pre-rotation rib plates partially overlap in the radial direction of the dynamic disc.

[0020] The utility model has the following beneficial effects:

[0021] The utility model realizes the one-way flow characteristic based on a geometric structure, does not need a mechanical moving part, is simple in structure, can be realized by machining, and does not need high-cost machining methods such as additive manufacturing;

[0022] In a reverse flow working condition, reverse flow is generated through the symmetrical Tesla flow channel, flow resistance is strengthened, gas invasion is inhibited, and the rim seal performance is improved.

[0023] The inclined pre-rotation ribs impart a circumferential velocity component to the leakage flow, thereby achieving pre-rotation control of the leakage flow. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the structure of this utility model;

[0025] Figure 2 for Figure 1 A magnified view of part A;

[0026] Figure 3 This is a schematic diagram of the flow-blocking component structure of this utility model;

[0027] Figure 4 for Figure 1 Exploded view;

[0028] Figure 5 This is an exploded view of the flow-blocking component of this utility model.

[0029] The reference numerals in the figure are as follows:

[0030] 1. Moving disc; 11. Moving disc groove; 2. Stationary disc; 21. Stationary disc groove; 3. Moving blade; 4. Stationary blade; 5. Disc cavity; 6. Flow-blocking component; 61. First core; 62. Second core; 63. Fixed rib; 64. Pre-rotation rib. Detailed Implementation

[0031] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments.

[0032] Example:

[0033] A gas turbine rim seal structure with pre-swirl function, such as Figures 1-5 As shown:

[0034] It includes a moving disk 1 and a stationary disk 2. Moving blades 3 are evenly arranged around the outer end wall of the moving disk 1, and stationary blades 4 are evenly arranged around the outer end wall of the stationary disk 2. The moving disk 1 and the stationary disk 2 are close to each other and are recessed on one side to form a disk cavity 5. This is the existing structure and will not be described in detail.

[0035] On the side of the moving disk 1 and the stationary disk 2 that are close to each other, multiple sets of grooves are provided at equal intervals along the radial direction of the moving disk 1. The grooves are located on the outer side of the disk cavity 5. The grooves include the moving disk groove 11 opened on the side wall of the moving disk 1 and the stationary disk groove 21 opened on the side wall of the stationary disk 2. The moving disk groove 11 and the stationary disk groove 21 are provided in a one-to-one correspondence.

[0036] Each groove is provided with a corresponding flow-blocking component 6. The flow-blocking component 6 and the inner sidewall of the groove cooperate to form a Tesla flow channel structure with unidirectional flow from the inside to the outside. During the flow of gas into the disk cavity 5, it is guided by the flow-blocking component 6 and suppressed due to its own momentum, thereby preventing gas intrusion.

[0037] The flow-blocking component 6 includes a first core 61 and a second core 62 fixedly connected as one piece. The first core 61 and the second core 62 can be arranged symmetrically or asymmetrically. The accompanying drawings of this specification show a symmetrical arrangement. A gap is left between the first core 61 and the second core 62 to form a straight channel extending radially along the moving plate 1. The first core 61 is placed opposite each other in the stationary plate groove 21 and a gap is left between it and the inner sidewall of the stationary plate groove 21 to avoid friction and collision. The second core 62 is fixed opposite each other in the moving plate groove 11 and a gap is left between it and the inner sidewall of the moving plate groove 11. When the fluid (such as cold air) flows from the outside to the inside, the flow channel formed by the first core 61 and the inner sidewall of the stationary plate groove 21, and the flow channel formed by the second core 62 and the inner sidewall of the moving plate groove 11 cooperate to prevent the gas from entering the plate cavity 5.

[0038] The straight channel between the first core 61 and the second core 62 is used for the outward flow of fluid within the disk cavity 5 to cool the outer end walls of the moving disk 1 and / or the stationary disk 2.

[0039] Multiple sets of pre-swirl ribs 64 are arranged in the straight channel between the first core 61 and the second core 62. These pre-swirl ribs 64 are evenly arranged circumferentially around the axis of the moving disk 1, and the length extension direction of the pre-swirl ribs 64 forms an angle of 30°-60° with the radial direction of the moving disk 1. When fluid flows from the inside to the outside through the straight channel of the flow-blocking component 6, the pre-swirl ribs 64 can pre-swirl it, allowing the fluid to acquire a circumferential velocity component when entering the blade channel. This significantly reduces the mainstream aerodynamic losses caused by the fluid, and significantly improves the cooling effect on the outer end wall of the moving disk 1.

[0040] Furthermore, based on the above, one side of the pre-rotating rib 64 passes through the second core 62 and is fixed to the inner wall of the moving plate groove 11. The part of the pre-rotating rib 64 that passes through the second core 62 serves as the fixing rib 63. The fixing rib 63 not only fixes the second core 62 of the flow-blocking component 6 to the inner wall of the moving plate groove 11 but also leaves a certain gap.

[0041] Meanwhile, the fixed rib 63 extends in the same direction as the pre-rotating rib 64, thus avoiding fluid collision caused by the fixed rib 63 and the pre-rotating rib 64 extending in different directions.

[0042] Furthermore, based on the preceding text, such as Figure 3 As shown, the spacing between two adjacent pre-swirl ribs 64 is small. During the outward flow of fluid in the disk cavity 5, the small spacing between the two pre-swirl ribs 64 can ensure that the fluid is pre-swirled and guided, preventing the fluid from directly passing through the spacing between the two pre-swirl ribs 64 along the radial direction of the moving disk 1.

[0043] Furthermore, based on the above, the first core 61 and the second core 62 are symmetrically arranged so that the pre-rotating rib 64 can be fully accommodated in the straight channel between the first core 61 and the second core 62, and the left and right sides of the pre-rotating rib 64 are respectively restricted by the side walls of the first core 61 and the second core 62.

[0044] If the first core 61 and the second core 62 are arranged asymmetrically, the left and right sides of the pre-swirling rib plate 64 cannot be completely restricted by the first core 61 / second core 62, and there will be a displacement when the fluid passes through the pre-swirling rib plate 64.

[0045] In summary, the symmetrical flow-blocking component 6 can better achieve fluid pre-swirl, that is, in the area where the pre-swirl rib 64 exists, the fluid can flow more stably; while in the case of the asymmetrical arrangement, the area where the pre-swirl rib 64 exists will be impacted by the Tesla flow channel branch flow, thereby destroying the flow stability in this area and hindering the achievement of the pre-swirl target.

[0046] The above description is merely an embodiment of this utility model and does not limit the patent scope of this utility model. Any equivalent structural or procedural transformations made based on the description and drawings of this utility model, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this utility model.

Claims

1. A gas turbine rim sealing structure with pre-swirl function, comprising a moving disc (1) and a stationary disc (2), wherein a set of one or more flow channel grooves are provided between the moving disc (1) and the stationary disc (2), characterized in that: A flow-blocking component (6) is provided in the flow channel groove, and the flow-blocking component (6) and the side wall of the flow channel groove cooperate to form a Tesla valve channel; The flow-blocking component (6) includes a first core (61) and a second core (62). Multiple sets of pre-rotation ribs (64) are uniformly arranged between the first core (61) and the second core (62). The length extension direction of the pre-rotation ribs (64) is inclined to the radial direction of the moving disk (1).

2. The gas turbine rim sealing structure with pre-swirl function as described in claim 1, characterized in that: The flow channel groove includes a moving disk groove (11) disposed on the side wall of the moving disk (1) and a stationary disk groove (21) disposed on the side wall of the stationary disk (2). The moving disk groove (11) and the stationary disk groove (21) are joined together to form the flow channel groove.

3. The gas turbine rim sealing structure with pre-swirl function as described in claim 2, characterized in that: The first core (61) is disposed in the stationary plate groove (21) and there is a gap between it and the inner sidewall of the stationary plate groove (21); the second core (62) is fixed in the moving plate groove (11) and there is a gap between it and the inner sidewall of the moving plate groove (11).

4. A gas turbine rim sealing structure with pre-swirl function as described in claim 3, characterized in that: The first core (61) and the second core (62) are symmetrically arranged; a straight channel is formed between the first core (61) and the second core (62).

5. A gas turbine rim sealing structure with pre-swirl function as described in claim 3, characterized in that: The second core (62) is fixed to the inner wall of the moving plate groove (11) by multiple sets of evenly arranged fixing ribs (63).

6. A gas turbine rim sealing structure with pre-swirl function as described in claim 5, characterized in that: The length extension direction of the fixed rib (63) is consistent with the length extension direction of the pre-rotating rib (64).

7. A gas turbine rim sealing structure with pre-swirl function as described in claim 6, characterized in that: The fixed rib (63) and the pre-rotating rib (64) are fixedly connected as a whole in a one-to-one correspondence.

8. A gas turbine rim seal structure with pre-swirl function as described in claim 6, characterized in that: Multiple sets of fixed ribs (63) or pre-rotating ribs (64) are evenly distributed around the axis of the rotating disk (1).

9. A gas turbine rim seal structure with pre-swirl function as described in claim 1, characterized in that: The angle between the length extension direction of the pre-rotating rib (64) and the radial direction of the moving disk (1) is 30°-60°.

10. A gas turbine rim sealing structure with pre-swirl function as described in claim 1, characterized in that: The two adjacent pre-rotating ribs (64) partially overlap radially on the moving disk (1).

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