Gas turbine blade manufacturing method, gas turbine blade, and gas turbine

Abstract

The application provides a gas turbine blade manufacturing method, a gas turbine blade and a gas turbine. The gas turbine blade manufacturing method comprises the following steps: manufacturing a spoiler according to a preset shape; connecting multiple spoilers to each other and arranging the multiple spoilers in a spaced manner along the height direction of a blade body of the gas turbine blade to form a spoiler assembly; and fixing the spoiler assembly in a cooling cavity of the blade body, and the distance between the spoiler and the inner wall surface of the blade body is less than or equal to a preset value. Therefore, the gas turbine blade manufacturing method according to the application facilitates the manufacturing of the gas turbine blade with the spoiler having a complex structure and a good spoiler effect.

Description

Technical Field

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

[0002] Gas turbine inlet temperatures are very high. To reduce blade temperature, multiple cooling structures are typically designed inside the blades to cool the blade walls. Due to limitations in casting technology, relatively simple cooling structures, such as turbulence columns and fins, are generally used in related technologies. Complex and efficient cooling structures are generally not feasible to manufacture by casting. Summary of the Invention

[0003] This invention aims to at least partially solve one of the technical problems in related technologies. To this end, embodiments of this invention provide a method for manufacturing gas turbine blades, gas turbine blades, and a gas turbine.

[0004] The gas turbine blade manufacturing method of this invention includes the following steps:

[0005] Manufacture the spoiler according to the preset shape;

[0006] Multiple of the aforementioned turbulence-inducing elements are connected to each other and spaced apart along the height direction of the gas turbine blade body to form a turbulence-inducing assembly.

[0007] The turbulence-disrupting component is fixed inside the cooling cavity of the blade body, and the distance between the turbulence-disrupting component and the inner wall surface of the blade body is less than or equal to a preset value.

[0008] Therefore, the gas turbine blade manufacturing method according to the present invention facilitates the manufacture of gas turbine blades with complex structures and good turbulence effects.

[0009] In some embodiments, a plurality of the spoilers are connected by a bracket.

[0010] In some embodiments, the spoiler assembly is welded to the inner wall surface of the blade body and the spoiler abuts against the inner wall surface of the blade.

[0011] In some embodiments, the inner wall surface of the blade body includes a first inner wall surface and a second inner wall surface connected together. The first inner wall surface and the second inner wall surface are disposed opposite to each other in the thickness direction of the blade body. The first inner wall surface and the second inner wall surface define the cooling cavity. Both the first inner wall surface and the second inner wall surface are arc-shaped surfaces.

[0012] The plurality of said spoilers include a plurality of first spoilers and a plurality of second spoilers;

[0013] The step of connecting the plurality of said spoilers to each other and arranging them at intervals along the height direction of the blade body includes:

[0014] Multiple first aerodynamic components are spaced apart on the bracket along the height direction of the blade body;

[0015] Multiple second aerodynamic elements are spaced apart on the support along the height direction of the blade body;

[0016] The step of fixing the baffle assembly inside the cooling cavity and ensuring that the distance between the baffle assembly and the inner wall of the blade body is less than or equal to a preset value includes:

[0017] The turbulence-inducing component is placed inside the cooling cavity with an interference fit, the first turbulence-inducing component abuts against the first inner wall surface, and the second turbulence-inducing component abuts against the second inner wall surface.

[0018] In some embodiments, the support includes a connecting column, a plurality of first connecting rods and a plurality of second connecting rods, wherein the length direction of the connecting column is the height direction of the blade body, each first spoiler is connected to the connecting column through at least one first connecting rod, and each second spoiler is connected to the connecting column through at least one second connecting rod.

[0019] The step of fixing the baffle assembly inside the cooling cavity and ensuring that the distance between the baffle assembly and the inner wall of the blade body is less than or equal to a preset value includes:

[0020] The turbulence-inducing component is fixed to the inner wall surface of the blade;

[0021] The portion of the bracket extending outside the cooling chamber is removed.

[0022] In some embodiments, the cooling cavity has cold air inlets on both sides of the blade body in the height direction.

[0023] The gas turbine blade manufacturing method further includes the following steps:

[0024] An end cap is provided on the blade body to cover the cold air inlet, and the end cap has a plurality of cold air holes that penetrate through it along the height direction of the blade body.

[0025] The gas turbine blade manufacturing method of this invention further includes the following steps:

[0026] A partition plate is provided inside the cooling cavity to divide the cooling cavity into multiple sub-cavities arranged sequentially along the length direction of the blade body;

[0027] The turbulence assembly is disposed in at least one of the plurality of said sub-cavities.

[0028] The gas turbine blade manufacturing method of this invention further includes the following steps:

[0029] An impact hole is provided through the blade body, and the impact hole is staggered from the turbulence element on the inner wall surface of the blade.

[0030] The present invention also proposes a gas turbine blade, comprising:

[0031] The blade body has a cooling cavity and an impact hole communicating with the cooling cavity;

[0032] A flow-dissipating assembly is disposed within the cooling cavity. The flow-dissipating assembly includes a support and multiple flow-dissipating elements. The multiple flow-dissipating elements are disposed on the support and spaced apart along the height direction of the blade body. The distance between the flow-dissipating elements and the inner wall surface of the blade body is less than or equal to a preset value. On a cross-section perpendicular to the thickness direction of the blade body, the projection of the flow-dissipating element is at least one of a rectangle, a corrugated shape, a triangle, and a trapezoid.

[0033] The present invention also proposes a gas turbine, including the gas turbine blades described above. Attached Figure Description

[0034] Figure 1 This is a schematic diagram of a gas turbine blade according to an embodiment of the present invention.

[0035] Figure 2 This is a top view of a gas turbine blade according to an embodiment of the present invention.

[0036] Figure 3 This is a schematic diagram of a spoiler and a support according to an embodiment of the present invention.

[0037] Figure label:

[0038] Gas turbine blades 100;

[0039] Blade body 1, cooling cavity 11, first inner wall surface 12, second inner wall surface 13, impact hole 14, sub-cavity 15, partition plate 16;

[0040] spoiler 2, first spoiler 21, second spoiler 22;

[0041] Bracket 3, connecting column 31, first connecting rod 32, second connecting rod 33. Detailed Implementation

[0042] 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.

[0043] The method for manufacturing gas turbine blades according to embodiments of the present invention is described below with reference to the accompanying drawings. Figures 1 to 3 As shown, the gas turbine blade manufacturing method according to an embodiment of the present invention includes the following steps:

[0044] The spoiler 2 is manufactured according to a preset shape. Specifically, the spoiler 2 is manufactured independently on the outside of the blade body 1 according to a preset shape, which reduces the manufacturing difficulty of the spoiler 2 so as to make the spoiler 2 more precise, and thus facilitates the manufacture of a spoiler 2 with a complex structure and good turbulence effect.

[0045] Multiple agitators 2 are connected to each other and spaced apart along the height direction of the blade body 1 of the gas turbine blade 100 to form an agitator assembly. The agitator assembly is fixed in the cooling cavity 11 of the blade body 1 and the distance between the agitator 2 and the inner wall surface of the blade body 1 is less than or equal to a preset value, thereby manufacturing the gas turbine blade 100.

[0046] Specifically, connecting multiple baffles 2 to form a baffle assembly can reduce the installation difficulty of the baffles 2, thereby improving the installation efficiency and accuracy of the baffles 2. In other words, connecting multiple baffles 2 to form a baffle assembly can reduce the manufacturing difficulty of the gas turbine blade 100 and improve the installation accuracy of the multiple baffles 2 within the gas turbine blade 100.

[0047] The height direction of the blade body 1 of the gas turbine blade 100 is the direction of cooling gas delivery. Multiple baffles 2 are arranged at intervals along the height direction of the blade body 1 of the gas turbine blade 100, and the distance between the baffles 2 and the inner wall surface of the blade body 1 is less than or equal to a preset value. This allows the multiple baffles 2 of the baffle assembly to turbulently turbulent the cooling gas flow when the cooling gas is delivered into the cooling chamber 11. This makes it easier for more cooling gas in the cooling chamber 11 to exchange heat with the inner wall surface of the blade body 1, thereby improving the cooling effect of the cooling gas on the blade body 1. The baffles 2 with complex structure and good turbulence effect can further improve the cooling effect of the cooling gas on the blade body 1, so as to reduce the temperature of the gas turbine blade 100 during operation.

[0048] Therefore, the gas turbine blade manufacturing method according to the present invention facilitates the manufacture of gas turbine blades 100 with complex structures and good turbulence effects of the turbulence element 2.

[0049] The present invention also proposes a gas turbine blade 100. The manufacturing method of the gas turbine blade according to the present invention will be specifically described below with reference to the gas turbine blade 100 according to the embodiments of the present invention.

[0050] like Figures 1 to 3 As shown, the gas turbine blade 100 according to an embodiment of the present invention includes a blade body 1 and a turbulence assembly.

[0051] The blade body 1 has a cooling cavity 11 and an impact hole 14 communicating with the cooling cavity 11. Specifically, the inner wall surface of the blade body 1 defines the cooling cavity 11, and the extending direction of the cooling cavity 11 is consistent with the height direction of the blade body 1. The height direction of the blade body 1 can be the vertical direction, such as... Figure 1 As shown by the arrow in the image.

[0052] like Figure 2 As shown, in some embodiments, the inner wall surface of the blade body 1 includes a first inner wall surface 12 and a second inner wall surface 13 connected to each other. The first inner wall surface 12 and the second inner wall surface 13 are arranged opposite to each other in the thickness direction of the blade body 1, defining a cooling cavity 11. Both the first inner wall surface 12 and the second inner wall surface 13 are arc-shaped surfaces. Specifically, the blade body 1 is a long and narrow arc-shaped cylinder, and both the thickness direction and the length direction of the blade body 1 are horizontal. For example, the thickness direction of the blade body 1 is (generally) the front-rear direction, and the first inner wall surface 12 is located in front of the second inner wall surface 13. The length direction of the blade body 1 is (generally) the left-right direction, and the leading edge of the blade body 1 is located to the right of the trailing edge of the blade body 1. The leading edge and trailing edge of the blade body 1 are determined according to the flow direction of the external high-temperature fluid. The front-rear direction and the left-right direction are as follows. Figure 2 As shown by the arrow in the image.

[0053] The turbulence-disrupting assembly is located within the cooling chamber 11 and includes a support 3 and multiple turbulence-disrupting elements 2. In a cross-section perpendicular to the thickness direction of the blade body 1, the projection of each turbulence-disrupting element 2 is at least one of a rectangle, a corrugated shape, a triangle, or a trapezoid. Specifically, the turbulence-disrupting elements 2 are manufactured according to a predetermined shape to produce a turbulence-disrupting element 2 with a complex structure and good turbulence-disrupting effect.

[0054] In the gas turbine blade manufacturing method, multiple flow disruptors 2 are connected to each other and spaced apart along the height direction of the blade body 1 of the gas turbine blade 100 to form a flow disruptor assembly. Specifically, the multiple flow disruptors 2 are connected by a support 3, such that the multiple flow disruptors 2 are disposed on the support 3 and spaced apart along the height direction of the blade body 1, so that the multiple flow disruptors 2 can sequentially disrupt the cooling gas entering the cooling chamber 11. The multiple flow disruptors 2 include multiple first flow disruptors 21 and multiple second flow disruptors 22.

[0055] The step of connecting multiple spoilers 2 to each other and arranging them at intervals along the height direction of the blade body 1 includes:

[0056] Multiple first aerodynamic components 21 are spaced apart on the support 3 along the height direction of the blade body 1;

[0057] Multiple second spoilers 22 are spaced apart on the support 3 along the height direction of the blade body 1.

[0058] like Figures 1 to 3 As shown, the support 3 includes a connecting column 31, multiple first connecting rods 32, and multiple second connecting rods 33. The length direction of the connecting column 31 is the height direction of the blade body 1. Each first aerodynamic component 21 is connected to the connecting column 31 via at least one first connecting rod 32, and each second aerodynamic component 22 is connected to the connecting column 31 via at least one second connecting rod 33. For example, the length direction of the connecting column 31 is vertical, with multiple first connecting rods 32 on the front side of the connecting column 31 and multiple second connecting rods 33 on the rear side. The multiple first aerodynamic components 21 are spaced apart along the vertical direction, and each first aerodynamic component 21 is connected to at least one first connecting rod 32. The multiple second aerodynamic components 22 are spaced apart along the vertical direction, and each second aerodynamic component 22 is connected to at least one second connecting rod 33.

[0059] Optionally, the spoiler 2, the bracket 3, the first connecting rod 32, and the second connecting rod 33 can all be made of non-high-temperature resistant alloys to reduce costs. For example, the spoiler 2, the bracket 3, the first connecting rod 32, and the second connecting rod 33 can be made of materials such as iron alloys, aluminum alloys, and copper.

[0060] The distance between the spoiler 2 and the inner wall surface of the blade body 1 is less than or equal to a preset value. For example, the distance between the spoiler 2 and the inner wall surface of the blade body 1 is less than or equal to 0.5 mm.

[0061] In some embodiments, the turbulence assembly is welded to the inner wall surface of the blade body 1, and the turbulence member 2 abuts against the inner wall surface of the blade. This can improve the cooling effect of the cooling gas on the gas turbine blade 100. Specifically, the turbulence member 2 abuts against the inner wall surface of the blade, and at least a portion of the ends of the plurality of turbulence members 2 are welded to the inner wall surface of the blade body 1 so that the turbulence assembly is securely connected to the blade body 1.

[0062] like Figure 1 and Figure 2 As shown, in some embodiments, the step of fixing the baffle assembly within the cooling cavity 11 and ensuring that the distance between the baffle 2 and the inner wall of the blade body 1 is less than or equal to a preset value includes:

[0063] The aerodynamic assembly is interference-fitted into the cooling cavity 11. The first aerodynamic element 21 abuts against the first inner wall surface 12, and the second aerodynamic element 22 abuts against the second inner wall surface 13. Specifically, after the first aerodynamic element 21 and the second aerodynamic element 22 are connected to the bracket 3, the positions of the first aerodynamic element 21 and the second aerodynamic element 22 are controlled. Then, by utilizing the difference in expansion between the blade body 1 and the aerodynamic assembly (aerodynamic element 2, bracket 3, first connecting rod 32 and second connecting rod 33), thermal expansion and contraction are achieved, resulting in an interference fit between the aerodynamic assembly and the cooling cavity 11. The inner wall surface of the blade body 1 is smoothed to facilitate the entry of the aerodynamic assembly into the cooling cavity 11. The first aerodynamic element 21 abuts against the first inner wall surface 12, and the second aerodynamic element 22 abuts against the second inner wall surface 13. Then, the first aerodynamic element 21 is welded to the first inner wall surface 12, and the second aerodynamic element 22 is welded to the second inner wall surface 13, so that the aerodynamic assembly and the blade body 1 are securely connected.

[0064] In some embodiments, the step of fixing the turbulence assembly within the cooling cavity 11 and ensuring that the distance between the turbulence member 2 and the inner wall surface of the blade body 1 is less than or equal to a preset value includes: fixing the turbulence assembly to the inner wall surface of the blade; and cutting off the portion of the support 3 extending outside the cooling cavity 11. Specifically, the turbulence assembly extends into the cooling cavity 11 through a relatively long support 3, and cutting off the portion of the support 3 extending outside the cooling cavity 11 allows the turbulence assembly to be adapted to the size of the blade body 1.

[0065] In some embodiments, the cooling chamber 11 has cold air inlets on both sides in the height direction of the blade body 1, through which cooling gas enters and exits the cooling chamber 11. For example, the cooling chamber 11 has cold air inlets on both sides in the vertical direction.

[0066] The method for manufacturing gas turbine blades also includes the following steps:

[0067] An end cap is provided on the blade body 1 to cover the cold air inlet. The end cap has multiple cold air holes that penetrate through it along the height direction of the blade body 1. This allows cooling gas to enter the cooling chamber 11 through the cold air holes on the end cap.

[0068] In some embodiments, the gas turbine blade manufacturing method further includes the following steps:

[0069] A partition plate 16 is provided inside the cooling cavity 11 to divide the cooling cavity 11 into a plurality of sub-cavities 15 arranged sequentially along the length direction of the blade body 1. Specifically, the thickness direction (generally) of the partition plate 16 is consistent with the length direction of the blade body 1, and there are multiple partition plates 16 arranged at intervals along the length direction of the blade body 1, so that the plurality of sub-cavities 15 are arranged sequentially along the length direction of the blade body 1.

[0070] like Figure 1 and Figure 2As shown, a flow-turbulence component is provided in at least one of the plurality of sub-cavities 15. This allows for flow-turbulence of the cooling gas within at least one of the plurality of sub-cavities 15 (at least a portion of the cooling cavity 11) to improve the cooling effect of the blade body 1. For example, a partition plate 16 divides the cooling cavity 11 into four sub-cavities 15. The sub-cavity 15 located at the trailing edge has an opening away from the leading edge, and an inner shell is provided within the sub-cavity 15 located at the trailing edge. The inner shell and the blade body 1 define a cooling interlayer cavity. Flow-turbulence components are provided in the sub-cavities 15 located at the middle and leading edges of the blade body 1.

[0071] In some embodiments, the gas turbine blade manufacturing method further includes the following steps:

[0072] like Figure 1 As shown, an impact hole 14 is provided through the blade body 1, and the impact hole 14 is staggered from the turbulence member 2 on the inner wall surface of the blade. This allows the cooling gas in the cooling chamber 11 to flow out through the impact hole 14 and form a cooling airflow layer on the outer surface of the blade body 1.

[0073] The present invention also proposes a gas turbine, wherein the gas turbine according to an embodiment of the present invention includes gas turbine blades 100 according to an embodiment of the present invention.

[0074] 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.

[0075] 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.

[0076] 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.

[0077] 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.

[0078] 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.

[0079] 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 method of manufacturing a gas turbine blade, characterized by, The method comprises the following steps: manufacturing a spoiler according to a preset shape; connecting a plurality of the spoilers to each other and spacing them along the height direction of a blade body of a gas turbine blade to form a spoiler assembly; fixing the spoiler assembly in a cooling cavity of the blade body and spacing the spoilers from the inner wall surface of the blade body by a distance less than or equal to a preset value; connecting the plurality of spoilers by a support; welding the spoiler assembly to the inner wall surface of the blade body and abutting the spoilers against the inner wall surface of the blade body; the inner wall surface of the blade body comprises a first inner wall surface and a second inner wall surface connected to each other, the first inner wall surface and the second inner wall surface are oppositely arranged in the thickness direction of the blade body, and the first inner wall surface and the second inner wall surface define the cooling cavity, and the first inner wall surface and the second inner wall surface are both arc surfaces; the plurality of spoilers comprises a plurality of first spoilers and a plurality of second spoilers; the step of connecting the plurality of spoilers to each other and spacing them along the height direction of the blade body comprises: spacedly arranging the plurality of first spoilers on the support along the height direction of the blade body; spacedly arranging the plurality of second spoilers on the support along the height direction of the blade body; the step of fixing the spoiler assembly in the cooling cavity and spacing the spoilers from the inner wall surface of the blade body by a distance less than or equal to a preset value comprises: the spoiler assembly is arranged in the cooling cavity in an interference fit with the cooling cavity, the first spoilers are abutted against the first inner wall surface, and the second spoilers are abutted against the second inner wall surface.

2. The method according to claim 1, wherein the support comprises a connecting column, a plurality of first connecting rods, and a plurality of second connecting rods, the length direction of the connecting column is the height direction of the blade body, each first spoiler is connected to the connecting column by at least one first connecting rod, and each second spoiler is connected to the connecting column by at least one second connecting rod; the step of fixing the spoiler assembly in the cooling cavity and spacing the spoilers from the inner wall surface of the blade body by a distance less than or equal to a preset value comprises: fixing the spoiler assembly on the inner wall surface of the blade body; and cutting off the part of the support that protrudes out of the cooling cavity.

3. The method according to claim 1, wherein the cooling cavity has air inlets on both sides in the height direction of the blade body, the method further comprises the following steps: providing an end cover on the blade body to cover the air inlets, the end cover being provided with a plurality of air holes penetrating the end cover along the height direction of the blade body.

4. The gas turbine vane manufacturing method of claim 1, wherein, The method further comprises the following steps: providing a partition plate in the cooling cavity to divide the cooling cavity into a plurality of sub-cavities arranged in sequence in the length direction of the blade body; providing the spoiler assembly in at least one of the plurality of sub-cavities.

5. The gas turbine blade manufacturing method of any one of claims 1-4, wherein, The method further comprises the following steps: An impact hole is arranged through the blade body and is staggered with the spoiler on the inner wall surface of the blade body.

6. A gas turbine blade manufactured by the method of any one of claims 1 to 5, characterized by, The turbine blade comprises A blade body having a cooling cavity and an impact hole communicating with the cooling cavity; A spoiler assembly arranged in the cooling cavity, the spoiler assembly comprising a support and a plurality of spoilers arranged on the support and spaced along the height direction of the blade body, the distance between the spoilers and the inner wall surface of the blade body being less than or equal to a preset value, and the projection of the spoilers on a cross section perpendicular to the thickness direction of the blade body being one of a rectangle, a corrugated shape, a triangle, and a trapezoid.

7. A gas turbine engine characterized by, The turbine blade of claim 6. The turbine blade of claim 6.

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