Turbine moving blade and gas turbine

Abstract

This disclosure relates to the field of turbine blade technology, specifically to a turbine blade and a gas turbine. The turbine blade of an embodiment of this disclosure includes a crown, a first sealing grate, and a second sealing grate. The crown includes a leading edge and a trailing edge. The first and second sealing grate are spaced apart on one side of the crown and located between the leading and trailing edges. The first sealing grate has a notch extending along its extension direction, which reduces the contact area between the first sealing grate and high-heat-load areas. The turbine blade of the embodiment of this disclosure has good heat dissipation capabilities and improves service life.

Description

Technical Field

[0001] This disclosure relates to the field of turbine blade technology, specifically to a turbine blade and a gas turbine. Background Technology

[0002] As a core component following the combustion chamber, the turbine faces a harsh operating environment caused by high-temperature and high-pressure combustion gases. In related technologies, gas turbine blades adopt an integrated blade crown and blade body design to avoid aerodynamic losses caused by tip leakage flow. However, the high-temperature leakage flow impacting the blade crown will generate a high heat load area, causing ablation damage to the blade crown, thereby compromising the reliability and service life of the gas turbine. Summary of the Invention

[0003] This disclosure aims to at least partially address one of the technical problems in the related art.

[0004] Therefore, embodiments of this disclosure propose a turbine blade that has good heat dissipation capabilities and improves service life.

[0005] Embodiments of this disclosure also propose a gas turbine.

[0006] The turbine blades of embodiments of this disclosure include:

[0007] The crown portion includes a leading edge and a trailing edge; The first sealing tooth and the second sealing tooth are spaced apart on one side of the crown and located between the front edge and the rear edge. The first sealing tooth has a notch extending along the extension direction of the first sealing tooth. The notch is used to reduce the contact area between the first sealing tooth and the high heat load area.

[0008] The turbine blade of this disclosure, by providing a notch on the first sealing grate, reduces heat conduction between the high heat load area and the first sealing grate, thereby achieving a cooling design for the crown. This facilitates the reduction of the crown's surface temperature and prevents crown ablation damage. Simultaneously, the notch can guide the flow direction of the axial leakage flow in the blade crown cavity area, reducing the angle when the leakage flow mixes with the circumferential crossflow and intrusion mainstream behind the sealing grate, thus reducing mixing losses and further reducing leakage losses. This improves the turbine blade's heat dissipation capacity, operational stability, and service life.

[0009] In some possible implementations, the crown has a cooling hole on the side near the leading edge, the cooling hole being located between the two sidewalls of the notch, and the turbine blade also includes a blade body fixedly connected to the crown, the blade body having a cooling channel communicating with the cooling hole, the cooling channel being used to deliver cooling gas to the cooling hole.

[0010] In some possible implementations, a first guide rib and a second guide rib are fixedly disposed on the crown, the first guide rib and the second guide rib are disposed on both radial sides of the cooling hole, the first guide rib and the second guide rib restrict the flow channel for the cooling gas to pass through, and the end of the flow channel is connected to the notch.

[0011] In some possible implementations, the height dimensions of the first guide rib and the second guide rib are equal. The height dimension of the first guide rib is defined as N, the height dimension of the first sealing tooth is defined as S, and the depth dimension of the notch is defined as H. The height dimension of the first guide rib satisfies the following formula: N=SH.

[0012] In some possible implementations, the first guide rib is disposed between the two side walls of the notch, and the second guide rib is disposed between the two side walls of the notch.

[0013] In some possible implementations, both the first guide rib and the second guide rib are arc-shaped structures.

[0014] In some possible implementations, the blade, the crown, the first guide rib, and the second guide rib are integrally formed.

[0015] In some possible implementations, the distance between the first sealing tooth and the second sealing tooth is defined as L, the distance between the first sealing tooth and the front edge is defined as E, and the distance between the second sealing tooth and the rear edge is defined as F. The distance between the first sealing tooth and the second sealing tooth satisfies the following formula: L > E, and L > F.

[0016] In some possible implementations, the depth of the notch is smaller than the height of the first sealing tooth, and the notch has rounded corners between its sidewalls and bottom.

[0017] In some possible implementations, the notches are provided at multiple intervals along the extension direction of the first sealing teeth.

[0018] The gas turbines of the embodiments of this disclosure include the turbine blades described in any of the above embodiments. Attached Figure Description

[0019] Figure 1 This is a first-view structural schematic diagram of a turbine blade according to an embodiment of the present disclosure.

[0020] Figure 2 This is a second-view structural schematic diagram of a turbine blade according to an embodiment of the present disclosure.

[0021] Figure 3 This is a third-view structural schematic diagram of a turbine blade according to an embodiment of the present disclosure.

[0022] Figure 4 This is a schematic diagram of the structure of the first sealing tooth in the turbine blade of an embodiment of the present disclosure.

[0023] Figure label: Crown 1; Leading edge 11; Rear edge 12; Cooling hole 13; First guide rib 14; Second guide rib 15; First sealing teeth 2; notch 21; The second seal is made of the comb teeth 3; Blade 4; Cooling channel 41. Detailed Implementation

[0024] Embodiments of this disclosure are described in detail below, with examples of these embodiments illustrated in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this disclosure, and should not be construed as limiting it.

[0025] The following is a reference appendix. Figures 1 to 4 Turbine blades according to embodiments of the present disclosure.

[0026] like Figure 1 , Figure 2 and Figure 4 As shown, the turbine blade of the present disclosure includes a crown 1, a first sealing tooth 2, and a second sealing tooth 3. The crown 1 includes a leading edge 11 and a trailing edge 12.

[0027] The first sealing tooth 2 and the second sealing tooth 3 are spaced apart on one side of the crown 1 and located between the front edge 11 and the rear edge 12. The first sealing tooth 2 has a notch 21 extending along its extension direction. The notch 21 is used to reduce the contact area between the first sealing tooth 2 and the high heat load area. It should be noted that the high heat load area is the heat accumulation area between the crown 1 and the inner wall of the turbine shell; the notch 21 is obtained by experimentally determining the location of the high heat load area and directionally cutting off the corresponding high heat load area on the first sealing tooth 2.

[0028] When the turbine blades of the present disclosure are in use, the first sealing grate 2 rotates with the crown 1. The notch 21 on the first sealing grate 2 reduces the heat conduction area between the first sealing grate 2 and the high heat load area, which facilitates the reduction of the overall temperature of the first sealing grate 2 and the crown 1, thereby achieving cooling protection for the crown 1, reducing heat damage to the crown 1, and improving the service life of the crown 1.

[0029] The turbine blade of the present disclosure, by providing a notch 21 on the first sealing grate 2, reduces heat conduction between the high heat load area and the first sealing grate 2, thereby achieving a cooling design for the crown 1. This facilitates the reduction of the surface temperature of the crown 1 and prevents the crown 1 from being burned and damaged. At the same time, the notch 21 can also guide the flow direction of the axial leakage flow in the blade crown cavity area, reducing the angle when the leakage flow mixes with the circumferential crossflow and intrusion mainstream behind the sealing teeth, reducing mixing losses, thereby further reducing leakage losses, improving the heat dissipation capacity of the turbine blade, the stability of the turbine blade during operation, and the service life of the turbine blade.

[0030] In some possible implementations, such as Figures 1 to 4 As shown, a cooling hole 13 is provided on the side of the crown 1 near the leading edge 11. The cooling hole 13 is located between the two side walls of the notch 21. The turbine blade also includes a blade body 4 fixedly connected to the crown 1. The blade body 4 is provided with a cooling channel 41 communicating with the cooling hole 13. The cooling channel 41 is used to deliver cooling gas to the cooling hole 13.

[0031] In this embodiment, by setting up cooling channels 41 and cooling holes 13, the cooling gas flowing inside the blade 4 can reach the notch 21 through the cooling channels 41 and cooling holes 13, thereby cooling down the first sealing teeth 2 and the crown 1, and further improving the reliability and service life of the crown 1.

[0032] In some possible implementations, such as Figure 1 , Figure 2 and Figure 4 As shown, it also includes a first guide rib 14 and a second guide rib 15 fixedly disposed on the crown 1. The first guide rib 14 and the second guide rib 15 are disposed on both radial sides of the cooling hole 13. The first guide rib 14 and the second guide rib 15 restrict the flow channel for cooling gas to pass through. The end of the flow channel is connected to the notch 21.

[0033] In this embodiment, by setting the first guide rib 14 and the second guide rib 15, a guide channel is restricted on the side of the first sealing grate 2 near the leading edge 11. The cooling air discharged through the cooling hole 13 can be transported to the notch 21 along the guide channel. The guide channel effectively guides the cooling gas to cover the high heat load area, improves the local cooling efficiency of the first sealing grate 2 and the crown 1, further enhances the reliability of the crown 1 and increases the service life of the crown 1.

[0034] In some possible implementations, such as Figure 4As shown, the height dimension of the first guide rib 14 and the height dimension of the second guide rib 15 are equal. The height dimension of the first guide rib 14 is defined as N, the height dimension of the first sealing grate tooth 2 is defined as S, and the depth dimension of the notch 21 is defined as H. The height dimension of the first guide rib 14 satisfies the following formula: N=SH.

[0035] In this embodiment, by limiting the height of the first guide rib 14 and the second guide rib 15, that is, the distance between the top surface of the first guide rib 14 and the second guide rib 15 and the crown 1 is equal to the distance between the bottom surface of the notch 21 and the crown 1, the guiding effect of the guide channel limited between the first guide rib 14 and the second guide rib 15 on the cooling gas is improved, further improving the heat dissipation effect on the first sealing grate 2 and the crown 1, thereby enhancing the reliability of the crown 1 and increasing the service life of the crown 1.

[0036] In some other possible implementations, depending on the actual working conditions, the distance between the top surface of the first guide rib 14 and the second guide rib 15 and the crown 1 may be set to be greater than or less than the distance between the bottom surface of the notch 21 and the crown 1.

[0037] In some possible implementations, the first guide rib 14 is disposed between the two side walls of the notch 21, and the second guide rib 15 is disposed between the two side walls of the notch 21. By restricting the position of the first guide rib 14 and the second guide rib 15 relative to the notch 21, the local cooling effect of the cooling gas guided by the guide channel on the first sealing grate 2 and the crown 1 is improved, thereby enhancing the reliability of the crown 1 and increasing the service life of the crown 1.

[0038] In some possible implementations, such as Figure 1 , Figure 2 and Figure 4 As shown, both the first guide rib 14 and the second guide rib 15 are arc-shaped structures. The arc-shaped first guide rib 14 and the second guide rib 15 facilitate the flow of cooling air in the guide channel, reduce the loss of cooling energy of the cooling air, and improve the local cooling effect on the first sealing grate 2 and the crown 1.

[0039] In some possible implementations, the blade 4, crown 1, first guide rib 14 and second guide rib 15 are integrally formed to enhance the overall structural strength of the turbine blade, thereby improving the reliability and service life of the crown 1 during use.

[0040] In some possible implementations, such as Figure 2As shown, the distance between the first sealing tooth 2 and the second sealing tooth 3 is defined as L, the distance between the first sealing tooth 2 and the front edge 11 is defined as E, and the distance between the second sealing tooth 3 and the rear edge 12 is defined as F. The distance between the first sealing tooth 2 and the second sealing tooth 3 satisfies the following formula: L > E, and L > F.

[0041] In this embodiment, the distance between the first sealing tooth 2 and the second sealing tooth 3 is set to be greater than the distance between the first sealing tooth 2 and the front edge 11 and the distance between the second sealing tooth 3 and the rear edge 12, respectively. This facilitates the adjustment of the weight distribution of the crown 1, thereby reducing leakage loss of the crown 1 during use. At the same time, it enhances the thermal protection of the second sealing tooth 3, preventing the first sealing tooth 2, the second sealing tooth 3 and the crown 1 from being burned and damaged, and improving the service life of the crown 1.

[0042] In some possible implementations, the depth dimension of the notch 21 is smaller than the height dimension of the first sealing grate 2, and the rounded corners between the sidewall and bottom surfaces of the notch 21 improve the connection strength between the first sealing grate 2 and the crown 1, enhance the reliability and sealing performance of the first sealing grate 2 and the crown 1 during use, and facilitate the reduction of leakage losses.

[0043] In some possible implementations, multiple notches 21 are provided at intervals along the extension direction of the first sealing tooth 2. By providing multiple notches 21, it is convenient to enhance the cooling of the first sealing tooth 2, reduce the contact area between the first sealing tooth 2 and the high heat load area, thereby reducing the surface temperature of the crown 1 and the first sealing tooth 2, preventing the crown 1 from being burned and damaged, and improving the protection effect on the first sealing tooth 2 and the crown 1.

[0044] The embodiments of this disclosure also provide a gas turbine. The gas turbine of the embodiments of this disclosure includes the turbine blades of any of the above embodiments. By employing the turbine blades of any of the above embodiments, the gas turbine of the embodiments of this disclosure reduces leakage losses, improves the stability and reliability of the gas turbine during operation, and extends the service life of the gas turbine.

[0045] In the description of this disclosure, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this disclosure and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this disclosure.

[0046] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this disclosure, "a plurality of" means at least two, such as two, three, etc., unless otherwise expressly and specifically defined.

[0047] In this disclosure, unless otherwise expressly specified and limited, the terms "installation," "connection," "linking," "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between components; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this disclosure according to the specific circumstances.

[0048] In this disclosure, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0049] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of this disclosure. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0050] Although embodiments of the present disclosure have been shown and described above, it is to be understood that the above embodiments are exemplary and should not be construed as limiting the present disclosure. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present disclosure.

Claims

1. A turbine blade, characterized in that, include: The crown portion includes a leading edge and a trailing edge; The first sealing tooth and the second sealing tooth are spaced apart on one side of the crown and located between the front edge and the rear edge. The first sealing tooth has a notch extending along the extension direction of the first sealing tooth. The notch is used to reduce the contact area between the first sealing tooth and the high heat load area.

2. The turbine blade according to claim 1, characterized in that, The crown has a cooling hole on the side near the leading edge, the cooling hole being located between the two sidewalls of the notch. The turbine blade also includes a blade body fixedly connected to the crown, the blade body having a cooling channel communicating with the cooling hole, the cooling channel being used to deliver cooling gas to the cooling hole.

3. The turbine blade according to claim 2, characterized in that, It also includes a first guide rib and a second guide rib fixedly disposed on the crown. The first guide rib and the second guide rib are disposed on both radial sides of the cooling hole. The first guide rib and the second guide rib restrict the flow channel for the cooling gas to pass through. The end of the flow channel is connected to the notch.

4. The turbine blade according to claim 3, characterized in that, The height of the first guide rib is equal to the height of the second guide rib. The height of the first guide rib is defined as N, the height of the first sealing tooth is defined as S, and the depth of the notch is defined as H. The height of the first guide rib satisfies the following formula: N=SH.

5. The turbine blade according to claim 3, characterized in that, The first guide rib is disposed between the two side walls of the notch, and the second guide rib is disposed between the two side walls of the notch.

6. The turbine blade according to claim 3, characterized in that, Both the first and second guide ribs are arc-shaped structures; and / or, The blade, the crown, the first guide rib, and the second guide rib are integrally formed.

7. The turbine blade according to any one of claims 1-6, characterized in that, The distance between the first sealing tooth and the second sealing tooth is defined as L, the distance between the first sealing tooth and the front edge is defined as E, and the distance between the second sealing tooth and the rear edge is defined as F. The distance between the first sealing tooth and the second sealing tooth satisfies the following formula: L > E, and L > F.

8. The turbine blade according to any one of claims 1-6, characterized in that, The depth of the notch is less than the height of the first sealing tooth, and the notch has rounded corners between its sidewall and bottom surface.

9. The turbine blade according to claim 1, characterized in that, The notches are provided at intervals along the extension direction of the first sealing teeth.

10. A gas turbine, characterized in that, Includes the turbine blades as described in any one of claims 1-9.

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