Gas turbine blade and gas turbine

Abstract

This invention discloses a gas turbine blade and a gas turbine. The gas turbine blade includes a blade body and a rib structure. Cooling channels are provided within the blade wall of the blade body, located at the leading edge and / or mid-chord portion of the blade body. The cooling channels penetrate the blade body along its spanwise direction. The rib structure is disposed within the cooling channels and includes multiple first rib groups and multiple second rib groups arranged alternately along the spanwise direction. The blade body has an airfoil on a cross-section perpendicular to the spanwise direction. Each first rib group includes multiple first ribs arranged at intervals along the airfoil, and each second rib group includes multiple second ribs arranged at intervals along the airfoil, with the first and second ribs arranged in a cross-sectional manner. The gas turbine blade of this invention can improve the cooling performance of the blade, avoiding high heat loads on the gas turbine blade during operation, thereby ensuring the reliability of gas turbine operation.

Description

Technical Field

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

[0002] Gas turbines are internal combustion power machines widely used in aerospace, power generation, and shipbuilding. Gas turbine blades are one of the key components; during operation, the heat generated by the internal combustion of fuel drives the blades to perform work, thus converting internal energy into mechanical energy. However, in related technologies, gas turbine blades experience high heat loads during operation, and traditional cooling structures such as column ribs have limited cooling capacity, resulting in low cooling performance and reduced operational reliability. Summary of the Invention

[0003] The present invention aims to at least partially solve one of the technical problems in the related art.

[0004] To address this, this invention proposes a gas turbine blade that improves the cooling performance of the blade, avoids high heat loads on the gas turbine blade during operation, and thus ensures the reliability of gas turbine operation.

[0005] The present invention also proposes a gas turbine including the above-described blades.

[0006] The gas turbine blades of this embodiment of the invention include:

[0007] The leaf body has a cooling channel located at the leading edge and / or mid-chord of the leaf body within its leaf wall, and the cooling channel extends through the leaf body along its spanwise direction.

[0008] The rib structure is disposed within the cooling channel. The rib structure includes multiple first rib groups and multiple second rib groups arranged alternately along the spanwise direction. The blade body has a blade profile line on a cross section perpendicular to the spanwise direction. Each first rib group includes multiple first ribs arranged at intervals along the blade profile line. Each second rib group includes multiple second ribs arranged at intervals along the blade profile line. The first ribs and second ribs are arranged in a cross pattern.

[0009] The gas turbine blades of this invention can improve the cooling performance of the blades, avoid the high heat load of the gas turbine blades during use, and thus ensure the reliability of gas turbine operation.

[0010] In some embodiments, the cooling channel includes:

[0011] An air intake chamber and an exhaust port are provided in the spanwise direction, wherein the air intake chamber is located at one end of the blade body and the exhaust port is located at the other end of the blade body;

[0012] A cooling chamber extends along the spanwise direction and connects between the air intake chamber and the exhaust port, and the rib structure is disposed within the cooling chamber.

[0013] In some embodiments, there are multiple cooling channels, and the air intake chambers of at least two of the cooling channels are arranged in communication.

[0014] In some embodiments, there are multiple exhaust ports, which are spaced apart along the extension direction of the blade line.

[0015] In some embodiments, there are multiple cooling channels, which are spaced apart along the extension direction of the blade profile, and each cooling channel extends along the blade profile.

[0016] In some embodiments, the extending direction of the first rib forms a first angle with the blade profile line, and the extending direction of the second rib forms a second angle with the blade profile line, wherein the first angle and the second angle are the same.

[0017] In some embodiments, the angles of both the first included angle and the second included angle do not exceed 60 degrees.

[0018] In some embodiments, at least one of the first rib and the second rib includes a plurality of rib segments arranged at spanwise intervals, and the gap between two adjacent rib segments is available for airflow.

[0019] In some embodiments, the number of rib segments in the first or second rib is 3 to 6.

[0020] The gas turbine in this embodiment of the invention includes gas turbine blades as described in any of the above embodiments. Attached Figure Description

[0021] Figure 1 This is a three-dimensional schematic diagram of the blade body of a gas turbine blade according to an embodiment of the present invention.

[0022] Figure 2 yes Figure 1 A top view of the middle lobe.

[0023] Figure 3 This is a schematic diagram of the blade body and rib structure of a gas turbine blade according to an embodiment of the present invention.

[0024] Figure 4 This is a schematic diagram of the cooling channel according to an embodiment of the present invention.

[0025] Figure 5 This is a schematic diagram of two rib structures within the cooling channel of an embodiment of the present invention.

[0026] Figure 6 This is a three-dimensional schematic diagram of the rib structure according to an embodiment of the present invention.

[0027] Figure 7 yes Figure 6 A partially enlarged schematic diagram of the central rib structure.

[0028] Figure 8 yes Figure 6 A top view of the central rib structure.

[0029] Figure 9 This is a three-dimensional schematic diagram of a rib structure according to another embodiment of the present invention.

[0030] Figure 10 yes Figure 9 A top view of the rib structure.

[0031] Figure 11 yes Figure 9 A magnified three-dimensional schematic diagram of a portion of the central rib structure.

[0032] Figure 12 yes Figure 9 Front view schematic diagram of the central rib structure.

[0033] Figure 13 This is a schematic diagram of the outer wall surface of the blade body and the inner rib surface of the rib structure in an embodiment of the present invention.

[0034] Figure 14 This is a schematic diagram comparing the Nu-Re curves of the inner cavity in an embodiment of the present invention.

[0035] Figure label:

[0036] Blade body 1; cooling channel 11; air intake chamber 111; cooling chamber 112; exhaust port 113;

[0037] Rib structure 2; First rib group 21; First rib 211; Second rib group 22; Second rib 221; Rib segment 23; Gap 24. Detailed Implementation

[0038] Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0039] The gas turbine blade of this embodiment of the invention includes a blade body 1 and a rib structure 2. For example... Figure 1 and Figure 2 As shown, the leaf body 1 can be a ring structure. For example, the leaf body 1 can be formed by a leaf wall of a certain thickness. The interior of the leaf body 1 is hollow, and the cross-section (perpendicular to the span) of the leaf body 1 can be roughly teardrop-shaped.

[0040] The leading edge of leaf body 1 is the anterior part of leaf body 1, the trailing edge of leaf body 1 is the posterior part of leaf body 1, and the midline of leaf body 1 can be considered as the part of leaf body 1 adjacent to the leading edge. For example... Figure 2 As shown, cooling channels 11 can be provided in the blade wall of both the leading edge and the middle chord portion of the blade body 1. This allows the cooling channels 11 to be arranged in areas of the blade body 1 with higher temperatures during use, thereby ensuring effective cooling and heat exchange. The cooling channels 11 penetrate the blade body 1 along its spanwise direction.

[0041] like Figure 3 As shown, during use, cooling gas can flow into the cooling channel 11 through one end, and then flow along the cooling channel 11 and out of the blade body from the other end of the cooling channel 11. During the flow in the cooling channel 11, the cooling gas can achieve heat exchange, thereby achieving cooling of the blade body 1.

[0042] like Figure 3 As shown, the rib structure 2 is fixed within the cooling channel 11. The rib structure 2 may include a first rib group 21 and a second rib group 22, such as... Figure 6 As shown, there can be multiple first rib groups 21 and multiple second rib groups 22, and the multiple first rib groups 21 and multiple second rib groups 22 can be arranged alternately along the spanwise direction of the blade body 1.

[0043] The leaf body 1 has a leaf-shaped line on its cross-section perpendicular to the spanwise direction. The leaf-shaped line can be considered as a curve that characterizes the curvature of the leaf wall. For example... Figure 7 and Figure 8 As shown, each first rib group 21 includes multiple first ribs 211 arranged in parallel and spaced apart. For example, the first ribs 211 can be rectangular plates. The multiple first ribs 211 can be arranged at equal intervals along the extension direction of the blade line. Each second rib group 22 also includes multiple second ribs 221 arranged in parallel and spaced apart. For example, the second ribs 221 can also be rectangular plates. The multiple second ribs 221 can be arranged at equal intervals along the extension direction of the blade line.

[0044] It should be noted that in the first rib group 21 and the second rib group 22 located in the same cooling channel 11, the extending direction of each first rib 211 can be arranged to intersect with the extending direction of each second rib 221. That is, along the spanwise direction, the projection of each first rib 211 and the projection of each second rib 221 can be X-shaped. In this case, the rib structure 2 can be regarded as Figure 5 Configuration 1 in the middle.

[0045] Therefore, multiple mesh structures can be formed within the rib structure 2 along the spanwise direction of the blade body 1, thereby meeting the usage requirements of cooling airflow flowing along the rib structure 2.

[0046] In the gas turbine blades of this embodiment, the multiple first rib groups 21 and multiple second rib groups 22 arranged in a cross pattern can form a honeycomb structure. This structural design can enhance the disturbance of cooling airflow, strengthen heat transfer and improve internal heat transfer, and greatly increase the heat transfer area, thereby improving the overall cooling performance of the blades. This allows for higher inlet temperatures at the gas inlet and reduces the overall cooling air volume of the components, which is beneficial to improving the overall efficiency of the gas turbine. It also avoids the situation of high heat load on the trailing edge of the gas turbine blades during operation, ensuring the reliability of gas turbine operation.

[0047] In some embodiments, such as Figure 4 As shown, the cooling channel 11 includes an air intake chamber 111, an exhaust port 113 and a cooling chamber 112. Along the spanwise direction, the air intake chamber 111 is located at one end of the blade body 1, specifically at the blade root end of the blade body 1, and the exhaust port 113 is located at the other end of the blade body 1, specifically at the blade tip end of the blade body 1.

[0048] The cooling cavity 112 extends along the longitudinal direction and connects between the intake cavity 111 and the exhaust port 113. The rib structure 2 is disposed within the cooling cavity 112. For example, the two ends of each first rib 211 of the first rib group 21 can be respectively arranged between two cavity walls opposite to the cooling cavity 112, and the two ends of each second rib 221 of the second rib group 22 can also be respectively connected to two cavity walls opposite to the cooling cavity 112. The specific connection method can be welding, integral casting, etc.

[0049] The cooling chamber 112 provides installation space for the arrangement of the fin structure 2 and corresponds to the blade wall of the blade body 1 in the higher temperature region, ensuring the cooling and heat exchange effect and meeting the flow requirements.

[0050] The air intake chamber 111 can increase the volume at the inlet of the cooling channel, thereby buffering and reducing the airflow velocity, so that the cooling airflow can flow into the cooling chamber 112 relatively evenly and uniformly, which is beneficial to improving heat exchange efficiency.

[0051] The exhaust port 113 can throttle the flow, thereby ensuring that the cooling gas can be fully heat-exchanged in the cooling chamber 112, and can also increase the airflow speed from the exhaust port 113.

[0052] In some embodiments, there are multiple cooling channels 11, and the air intake chambers 111 of at least two cooling channels 11 are arranged in communication. For example, as Figure 2 As shown, there can be four cooling channels 11. The four cooling channels 11 can be arranged at intervals along the extension direction of the blade profile. The air inlet chambers 111 of the four cooling channels 11 can be evenly located at the blade root of the blade body 1. The air inlet chambers 111 of the four cooling channels 11 can be fully connected to form a large air inlet chamber 111. This allows the cooling airflow entering the air inlet chamber 111 to be evenly distributed to the four cooling chambers 112, thereby achieving consistency and synchronization of air intake in the four cooling chambers 112, which is beneficial to improving heat exchange efficiency.

[0053] In some embodiments, there are multiple exhaust ports 113, which are spaced apart along the extension direction of the airfoil line. For example, as Figure 3 and Figure 4 As shown, the top side of the blade wall of the blade body 1 can be provided with multiple circular tube structures, each of which extends along the spanwise direction. The multiple circular tube structures are all connected to the corresponding cooling chamber 112, and the hollow interior of each of the multiple circular tube structures forms an exhaust hole 113. This ensures the uniformity of gas exhaust within the cooling chamber 112.

[0054] In some embodiments, such as Figure 2 As shown, there are multiple cooling channels 11, specifically four, and in some other embodiments, three, five, six, etc. The multiple cooling channels 11 are arranged at intervals along the extension direction of the blade profile line, and each cooling channel 11 extends along the blade profile line. Thus, the arrangement of the cooling channels 11 can match the shape of the blade wall of the blade body 1, thereby ensuring the cooling effect.

[0055] In some embodiments, the extending direction of the first rib 211 forms a first angle with the blade profile line, and the extending direction of the second rib 221 forms a second angle with the blade profile line, wherein the first angle and the second angle are the same.

[0056] For example, such as Figure 8 As shown, the blade wall of the blade body 1 may include an inner wall surface and an outer wall surface. The inner wall surface and the outer wall surface may be arranged in parallel. The blade profile line may be an arc line between the inner wall surface and the outer wall surface, and the distance between the blade profile line and the inner wall surface may be the same as the distance between the blade profile line and the outer wall surface.

[0057] Therefore, the angle between the extending direction of the first rib 211 and the airfoil line can also be considered as the angle formed by the extending direction of the first rib 211 and the inner or outer wall surface of the blade body 1, which is angle α. Similarly, the angle between the extending direction of the second rib 221 and the airfoil line can also be considered as the angle formed by the extending direction of the second rib 221 and the inner or outer wall surface of the blade body 1, which is angle β. The inclination directions of the first rib 211 and the second rib 221 can be opposite, and the angle α can be the same as the angle β.

[0058] Therefore, the rib structure 2 can be arranged symmetrically about the wall thickness direction of the blade body 1. This structural design is conducive to further improving heat exchange efficiency and cooling effect.

[0059] In some embodiments, the angles of the first included angle and the second included angle do not exceed 60 degrees. For example, the included angles of the first rib 211 of the first rib group 21 and the second rib 221 of the second rib group 22 of the adjacent first rib group 21 in the cooling channel 11 can be opposites of each other. Specifically, the angle of the first included angle can be from 0 degrees to 60 degrees, while the angle of the second included angle can be from -60 degrees to 0 degrees.

[0060] Preferably, the first included angle can be 45 degrees, and the second included angle can also be 45 degrees. This allows the lower limit of the aperture of the mesh formed in the rib structure 2 to be larger, thereby ensuring the smooth flow of air in the rib structure 2.

[0061] In some embodiments, at least one of the first rib 211 and the second rib 221 includes a plurality of rib segments 23, the plurality of rib segments 23 being arranged at intervals along the spanwise direction, and the gap 24 between two adjacent rib segments 23 being available for airflow.

[0062] For example, the first rib 211 and the second rib 221 can both be separately arranged and combined by multiple rib segments 23. In this case, the rib structure 2 can be regarded as Figure 5 Configuration two in the text. Specifically, such as... Figures 9 to 12 As shown, both the first rib 211 and the second rib 221 may include four rib segments 23. In some other embodiments, the first rib 211 and the second rib 221 may also include three, five, six or other numbers of rib segments 23.

[0063] The multiple rib segments 23 of the first rib 211 are arranged at equal intervals along the spanwise direction of the blade body 1, and there is a gap 24 between each adjacent rib segment 23 of the first rib 211. Similarly, the multiple rib segments 23 of the second rib 221 are also arranged at equal intervals along the spanwise direction of the blade body 1, and there is also a gap 24 between each adjacent rib segment 23 of the second rib 221.

[0064] Therefore, the cooling gas flowing along the spanwise direction in the cooling chamber 112 can generate flow perpendicular to the spanwise direction through each gap 24. This flow pattern will intensify the disturbance of the cooling airflow in the cooling chamber 112 and prolong the stagnation time of the cooling airflow in the cooling chamber 112, thereby further enhancing the heat exchange effect.

[0065] It should be noted that the above Figure 5 In configuration one, the first rib 211 and the second rib 221 are both independent and complete ribs, while in configuration two, the first rib 211 and the second rib 221 are divided into multiple rib segments 23, which can be regarded as a further separation and division of the first rib 211 and the second rib 221 in configuration one.

[0066] In some other embodiments, one of the first rib 211 and the second rib 221 may take the form of a structure with multiple rib segments 23.

[0067] In some embodiments, the number of rib segments 23 in the first rib 211 or the second rib 221 is 3 to 6. For example, as Figure 11 and Figure 12 As shown, the number of rib segments 23 in each first rib 211 is the same as the number of rib segments 23 in each second rib 221, and the number of rib segments 23 in each rib can be 3, 4, 5, 6, etc. Within this range, the rib segments 23 can have a better cooling and heat exchange effect.

[0068] The gas turbine of an embodiment of the present invention is described below.

[0069] The gas turbine in this embodiment of the invention includes turbine blades, which can be the gas turbine blades described in any of the above embodiments. For example... Figure 12 As shown, the outer wall surface of the turbine blade can be regarded as the surface of the blade body 1 facing outward, and the inner rib surface of the rib structure 2 can be regarded as the surface of the first rib 211 or the second rib 221 facing inward to the blade body 1.

[0070] like Figure 13 As shown in the graph, the above-mentioned figures are presented respectively. Figure 5 A schematic diagram comparing the curves of configurations one and two on the outer wall and inner rib surfaces. As can be seen from the diagram, when the temperature ratio between the inner cavity of blade body 1 and the cooling gas is 2, the Nusselt number (Nu) of the two honeycomb structure channels (configuration one and configuration two) is 20% to 40% higher than that of the traditional channel under the same Reynolds number (RE). Furthermore, considering the two honeycomb structure channels, the heat exchange area is significantly larger than that of the traditional channel. Therefore, the actual cooling effect is superior, allowing for a higher inlet temperature at the gas turbine inlet and a lower overall cooling air volume, thus improving the overall operating efficiency of the gas turbine.

[0071] In the description of this invention, 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 invention and simplifying the description, and are not intended to 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 invention.

[0072] 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 invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0073] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "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 them; 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 explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0074] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of 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.

[0075] In this invention, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of the invention. 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.

[0076] Although the above embodiments have been shown and described, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Any changes, modifications, substitutions and variations made to the above embodiments by those skilled in the art are within the protection scope of the present invention.

Claims

1. A gas turbine blade, characterized by, include: The leaf body has a cooling channel located at the leading edge and / or mid-chord of the leaf body within its leaf wall, and the cooling channel extends through the leaf body along its spanwise direction. The rib structure is disposed within the cooling channel. The rib structure includes multiple first rib groups and multiple second rib groups arranged alternately along the spanwise direction. The blade body has a blade profile line on a cross section perpendicular to the spanwise direction. Each first rib group includes multiple first ribs arranged at intervals along the blade profile line. Each second rib group includes multiple second ribs arranged at intervals along the blade profile line. The first ribs and second ribs are arranged in a cross pattern.

2. The gas turbine vane of claim 1, wherein The cooling channel includes: An air intake chamber and an exhaust port are provided in the spanwise direction, wherein the air intake chamber is located at one end of the blade body and the exhaust port is located at the other end of the blade body; A cooling chamber extends along the spanwise direction and connects between the air intake chamber and the exhaust port, and the rib structure is disposed within the cooling chamber.

3. The gas turbine blade according to claim 2, characterized in that, There are multiple cooling channels, and the air intake chambers of at least two of the cooling channels are connected.

4. The gas turbine blade according to claim 2, characterized in that, There are multiple exhaust holes, which are arranged at intervals along the extension direction of the blade line.

5. The gas turbine blade according to claim 1, characterized in that, There are multiple cooling channels, which are arranged at intervals along the extension direction of the blade profile, and each cooling channel extends along the blade profile.

6. The gas turbine blade according to any one of claims 1-5, characterized in that, The first rib extends at a first angle to the blade profile line, and the second rib extends at a second angle to the blade profile line. The first angle and the second angle are the same.

7. The gas turbine blade according to claim 6, characterized in that, The angles of both the first included angle and the second included angle do not exceed 60 degrees.

8. The gas turbine blade according to claim 6, characterized in that, At least one of the first rib and the second rib includes a plurality of rib segments, the plurality of rib segments being arranged at intervals along the spanwise direction, and the gap between two adjacent rib segments being open to airflow.

9. The gas turbine blade according to claim 8, characterized in that, The number of rib segments in the first or second rib is 3 to 6.

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

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