Gas turbine rim sealing structure with pre-rotation function

Abstract

The invention 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 and the side walls of the flow channel grooves are matched 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 symmetric 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 present invention relates to a rim seal structure of a gas turbine with a pre-whirl function, belonging to the field of sealing technology. Background Art

[0002] The most effective way to improve the performance of an aero gas turbine engine is to increase the gas temperature at the turbine inlet. Since the turbine operates under high-temperature and high-speed rotation conditions for a long time, it has to bear high thermal stress and centrifugal stress. To ensure the reliable operation of the engine, the air system of the aero engine needs to provide cooling air for the turbine blades to reduce the temperature of the turbine blades.

[0003] After the cooling air provided by the air system of the aero engine reaches the disk cavity from the internal channel, part of the cooling air is used to prevent the high-temperature mainstream gas from entering the rotating disk cavity. This part of the cooling air is usually called sealing cooling air. In the related art, the aero engine generally uses a labyrinth structure as the rim seal and uses the sealing cooling air to prevent the mainstream high-temperature gas from entering the rotating disk cavity through the labyrinth mechanism. This phenomenon that the mainstream gas enters the disk cavity through the rim seal is called gas intrusion or backflow of gas.

[0004] If the amount of sealing cooling air is insufficient, it will cause the mainstream high-temperature gas to enter the engine through the rim seal structure, resulting in gas intrusion, greatly reducing the life of the engine, and the disk cavity is not heat-resistant and is easily fatally damaged; the deficiency of the labyrinth structure is replaced by the Tesla flow channel in the prior art.

[0005] For example, in the "rim seal structure of a gas turbine disk" announced in the patent No. CN114909188B, a positioning ring is installed between the turbine stator disk and the turbine rotor disk, and a Tesla valve channel is arranged in the positioning ring. The excellent one-way conduction performance of the Tesla valve channel effectively prevents the occurrence of gas intrusion and reduces the amount of sealing cooling air introduced into the disk cavity.

[0006] However, the Tesla valve channel is composed of a first annular groove and a second annular groove in relative movable cooperation, and a straight-through channel is formed between the first annular groove and the second annular groove. When the cooling air in the disk cavity passes through the Tesla valve channel and cools the outer end wall of the turbine rotor disk outward, the cooling air cannot impart circumferential velocity to the fluid when flowing radially outward into the cascade channel. Summary of the Invention

[0007] The purpose of the present invention is to provide a rim seal structure of a gas turbine with a pre-whirl function to solve the problems raised in the above background art.

[0008] The technical solution of the present invention is as follows:

[0009] A rim seal structure of a gas turbine with a pre-whirl function, comprising a moving disk and a stationary disk. More than one set of flow channel grooves are arranged between the moving disk and the stationary disk. A flow blocking component is arranged in the flow channel grooves, 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 includes a first core and a second core. A plurality of sets of pre-whirl rib plates are evenly arranged between the first core and the second core. The length extension direction of the pre-whirl rib plates is inclined to the radial direction of the moving disk.

[0011] Preferably, the flow channel grooves include a moving disk groove arranged on the side wall of the moving disk and a stationary disk groove arranged on the side wall of the stationary disk. The moving disk groove and the stationary disk groove are spliced to form the flow channel groove.

[0012] Preferably, the first core is arranged in the stationary disk groove and there is a spacing between the first core and the inner side wall of the stationary disk groove; the second core is fixed in the moving disk groove and there is a spacing between the second core and the inner side wall of the moving disk groove.

[0013] Preferably, the first core and the second core are symmetrically arranged; 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 moving disk groove through a plurality of sets of uniformly arranged fixing rib plates.

[0015] Preferably, the length extension direction of the fixing rib plates is the same as the length extension direction of the pre-whirl rib plates.

[0016] Preferably, the fixing rib plates and the pre-whirl rib plates are fixed and connected into one body one by one.

[0017] Preferably, a plurality of sets of the fixing rib plates or the pre-whirl rib plates are circumferentially and evenly distributed around the axis of the moving disk.

[0018] Preferably, the included angle between the length extension direction of the pre-whirl rib plates and the radial direction of the moving disk is 30° - 60°.

[0019] Preferably, two adjacent pre-whirl rib plates partially overlap in the radial direction of the moving disk.

[0020] The present invention has the following beneficial effects:

[0021] The present invention realizes the unidirectional flow characteristic based on the geometric structure, without mechanical moving parts, has a simple structure, can be realized by machining, and does not require high-cost processing methods such as additive manufacturing;

[0022] Under the reverse flow condition, reverse flow is generated through the symmetrically shaped Tesla flow channels, strengthening the flow resistance to inhibit the invasion of gas and improving the rim seal performance;

[0023] The inclined pre-whirl ribs impart a circumferential velocity component to the leakage flow, achieving pre-whirl control of the leakage flow. Brief Description of the Drawings

[0024] Figure 1 It is a schematic structural diagram of the present invention;

[0025] Figure 2 is Figure 1 a partially enlarged schematic diagram of A;

[0026] Figure 3 It is a schematic structural diagram of the flow-blocking component of the present invention;

[0027] Figure 4 is Figure 1 an exploded view of;

[0028] Figure 5 It is an exploded view of the flow-blocking component of the present invention.

[0029] The reference numerals in the drawings are represented as:

[0030] 1, moving disk; 11, moving disk groove; 2, stationary disk; 21, stationary disk groove; 3, moving blade; 4, stationary blade; 5, disk cavity; 6, flow-blocking component; 61, first core; 62, second core; 63, fixed rib plate; 64, pre-whirl rib plate. Detailed Description of the Invention

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

[0032] Embodiment:

[0033] A rim seal structure of a gas turbine with a pre-whirl function, as Figures 1 - 5 shown:

[0034] It includes a moving disk 1 and a stationary disk 2. The outer end wall of the moving disk 1 is circumferentially and uniformly provided with moving blades 3, and the outer end wall of the stationary disk 2 is circumferentially and uniformly provided with stationary blades 4. The inner concave sides of the moving disk 1 and the stationary disk 2 close to each other form a disk cavity 5, which is an existing structure and will not be described in detail here.

[0035] On the sides of the moving disk 1 and the stationary disk 2 close to each other, a plurality of groups of grooves are arranged at equal intervals along the radial direction of the moving disk 1. The grooves are relatively located outside the disk cavity 5. The grooves include moving disk grooves 11 opened on the side wall of the moving disk 1 and stationary disk grooves 21 opened on the side wall of the stationary disk 2, and the moving disk grooves 11 and the stationary disk grooves 21 are arranged in one-to-one correspondence.

[0036] Each groove is provided with a corresponding flow-blocking component 6. The flow-blocking component 6 and the inner side wall of the groove cooperate to form a Tesla flow channel structure with a one-way flow from the inside to the outside. During the process of the gas flowing towards the disk cavity 5, it is guided by the flow-blocking component 6 and is inhibited due to its own momentum, thereby avoiding the invasion of the gas.

[0037] The flow blocking component 6 includes a first core 61 and a second core 62 that are fixedly connected as a whole. The first core 61 and the second core 62 can be symmetrically arranged or asymmetrically arranged. In the attached drawings of this specification, a symmetrical arrangement is adopted. A gap is left between the first core 61 and the second core 62 to form a straight channel extending radially along the moving disk 1. The first core 61 is relatively placed in the static disk groove 21 and there is a gap between it and the inner side wall of the static disk groove 21 to avoid friction and collision. The second core 62 is relatively fixed in the moving disk groove 11 and there is a gap between it and the inner side wall of the moving disk groove 11. When the fluid (such as cold air) flows from the outside to the inside, the flow channels formed by the first core 61 and the inner side wall of the static disk groove 21 and the flow channels formed by the second core 62 and the inner side wall of the moving disk groove 11 cooperate to prevent the gas from invading the disk cavity 5.

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

[0039] Multiple groups of pre-whirl rib plates 64 are arranged in the straight channel between the first core 61 and the second core 62. The multiple groups of pre-whirl rib plates 64 are circumferentially and uniformly arranged around the axis of the moving disk 1, and an angle of 30° - 60° is formed between the length extension direction of the pre-whirl rib plates 64 and the radius of the moving disk 1. When the fluid passes through the straight channel of the flow blocking component 6 from the inside to the outside, the pre-whirl rib plates 64 can pre-whirl it so that the fluid obtains a circumferential velocity component when entering the cascade channel. At this time, the main flow aerodynamic loss caused by the fluid will be greatly weakened, and the cooling effect on the outer end wall of the moving disk 1 will be significantly improved.

[0040] Further, on the basis of the above, one side of the pre-whirl rib plate 64 passes through the second core 62 and is fixed to the inner side wall of the moving disk groove 11. The part of the pre-whirl rib plate 64 passing through the second core 62 serves as a fixing rib plate 63. Through the fixing rib plate 63, not only the second core 62 of the flow blocking component 6 is fixed to the inner side wall of the moving disk groove 11, but also a certain gap is left.

[0041] At the same time, the fixing rib plate 63 has the same extension direction as a part of the pre-whirl rib plate 64, avoiding fluid collision caused by different extension directions of the fixing rib plate 63 and the pre-whirl rib plate 64.

[0042] Further, on the basis of the above, as Figure 3 shown, the distance between two adjacent pre-whirl rib plates 64 is small. During the process of the fluid in the disk cavity 5 flowing outwards, the small distance between the two pre-whirl rib plates 64 can ensure the guiding pre-whirl of the fluid and prevent the fluid from directly passing through the distance between the two pre-whirl rib plates 64 along the radius of the moving disk 1.

[0043] Further, on the basis of the foregoing, the first core 61 and the second core 62 are symmetrically arranged, so that the pre-whirl rib plate 64 can be completely accommodated in the straight channel between the first core 61 and the second core 62, and the left and right sides of the pre-whirl rib plate 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 adopt an asymmetric arrangement form, the left and right sides of the pre-whirl rib plate 64 cannot be completely restricted by the first core 61 / the second core 62, and there will be a deviation when the fluid passes through the pre-whirl rib plate 64;

[0045] In summary, the symmetric flow blocking component 6 can better achieve fluid pre-whirl, that is, in the area where the pre-whirl rib plate 64 exists, the fluid can flow more stably; in the case of an asymmetric arrangement, the area where the pre-whirl rib plate 64 exists will be impacted by the branched flow of the Tesla channel, thereby damaging the flow stability of this area and being unfavorable for the realization of the pre-whirl target.

[0046] The above are only the embodiments of the present invention, and do not limit the scope of the patent of the present invention accordingly. Any equivalent structure or equivalent process transformation made by using the content of the specification and drawings of the present invention, or directly or indirectly applied in other related technical fields, shall be equally included in the patent protection scope of the present invention.

Claims

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

2. A gas turbine wheel rim sealing structure with pre-swirl function as claimed in claim 1, characterized in that: The flow channel groove comprises a moving disc groove (11) provided on the side wall of the moving disc (1) and a static disc groove (21) provided on the side wall of the static disc (2), respectively; the moving disc groove (11) and the static disc groove (21) are spliced ​​to form the flow channel groove.

3. A gas turbine wheel rim sealing structure with pre-swirl function as claimed in claim 2, characterized in that: The first core (61) is arranged in the static disc groove (21) and has a spacing with the inner side wall of the static disc groove (21); the second core (62) is fixed in the dynamic disc groove (11) and has a spacing with the inner side wall of the dynamic disc groove (11).

4. A gas turbine wheel rim sealing structure with pre-swirl function as claimed 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 wheel rim sealing structure with pre-swirl function as claimed in claim 3, characterized in that: The second core (62) is fixed to the inner side wall of the moving disc groove (11) via a plurality of groups of evenly arranged fixing ribs (63).

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

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

8. A gas turbine wheel rim sealing structure with pre-swirl function as claimed in claim 6, characterized in that: The plurality of groups of fixed ribs (63) or pre-rotating ribs (64) are evenly distributed in the circumferential direction around the axis of the rotating disk (1).

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

10. A gas turbine wheel rim sealing structure with pre-swirl function as claimed in claim 1, characterized in that: Two adjacent pre-spinning ribs (64) partially overlap in the radial direction of the moving disk (1).

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