Gas turbine blade and gas turbine

Abstract

The present invention discloses a gas turbine blade and a gas turbine, wherein the gas turbine blade comprises a blade body, a plurality of first spoilers and a plurality of second spoilers, wherein the blade body has a cooling channel, the first spoilers and the second spoilers are respectively arranged on the inner wall surface of the cooling channel, and the plurality of first spoilers and the plurality of second spoilers are alternately arranged in the length direction of the blade body, and the size of the first spoiler in the thickness direction of the blade body is smaller than the size of the second spoiler in the thickness direction of the blade body. The gas turbine blade of the present invention can improve the cooling efficiency of the blade.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a gas turbine blade and a gas turbine. Background Art

[0002] The blades of a gas turbine are one of the key components of the gas turbine, used to convert the thermal energy of the gas into mechanical work of the turbine. Therefore, the structure of the blades of a gas turbine will affect the performance of the turbine and even the entire gas turbine. Gas turbines are usually directly exposed to a high heat load environment, especially at the blade body and top of the blade. The heat load increases significantly, causing the blades to be easily oxidized and damaged. Therefore, in order to ensure the normal and reliable operation of the blades, the blades need to be effectively cooled.

[0003] However, the cooling method of the gas turbine blades in the related art has poor heat exchange effect and cooling efficiency. Summary of the invention

[0004] The present invention aims to solve one of the technical problems in the related art at least to a certain extent. To this end, an embodiment of the present invention provides a gas turbine blade, which can improve the cooling efficiency of the blade.

[0005] A gas turbine blade according to an embodiment of the present invention comprises: a blade body having a cooling channel therein; a plurality of first spoilers and a plurality of second spoilers, wherein the first spoilers and the second spoilers are respectively arranged on the inner wall surface of the cooling channel, and the plurality of first spoilers and the plurality of second spoilers are alternately arranged in the length direction of the blade body, and a size of the first spoiler in the thickness direction of the blade body is smaller than a size of the second spoiler in the thickness direction of the blade body.

[0006] The gas turbine blades according to the embodiments of the present invention can improve the cooling efficiency of the blades.

[0007] In some embodiments, the cooling flow channel has a first side wall surface and a second side wall surface in the thickness direction of the blade body, a plurality of the first spoilers are respectively arranged on the first side wall surface and the second side wall surface, a plurality of the second spoilers are respectively arranged on the first side wall surface and the second side wall surface, the plurality of the first spoilers and the plurality of the second spoilers located on the first side wall surface are alternately arranged in the length direction of the blade body, and / or the plurality of the first spoilers and the plurality of the second spoilers located on the second side wall surface are alternately arranged in the length direction of the blade body.

[0008] In some embodiments, the first spoiler located on the first side wall surface and the second spoiler located on the second side wall surface are arranged relative to each other in the thickness direction of the blade body, and / or the second spoiler located on the first side wall surface and the first spoiler located on the second side wall surface are arranged relative to each other in the thickness direction of the blade body.

[0009] In some embodiments, a dimension of the first spoiler in the thickness direction of the blade body is A, a dimension of the second spoiler in the thickness direction of the blade body is B, and 0.2B≤A≤0.5B.

[0010] In some embodiments, a dimension of the first spoiler in the length direction of the blade body is smaller than or equal to a dimension of the second spoiler in the length direction of the blade body.

[0011] In some embodiments, the cooling channel has an inlet and an outlet, the spacing distance between two adjacent second spoilers is C, the distance between one of the first spoilers between two adjacent second spoilers and one of the second spoilers adjacent to the inlet is D, and 0.2C≤D≤0.5C.

[0012] In some embodiments, the first spoiler and the second spoiler are arranged in parallel.

[0013] In some embodiments, the length direction of the first spoiler forms an angle with the width direction of the blade body, and / or the length direction of the second spoiler forms an angle with the width direction of the blade body.

[0014] In some embodiments, the first spoiler and the second spoiler are integrally formed with the blade body.

[0015] A gas turbine according to an embodiment of the present invention comprises a gas turbine blade as described in any one of the above embodiments.

[0016] The gas turbine according to the embodiment of the present invention can improve the cooling efficiency of the blades and the performance of the gas turbine. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic structural diagram of a gas turbine blade according to an embodiment of the present invention.

[0018] Figure 2 yes Figure 1 A side view of a gas turbine blade is shown in FIG.

[0019] Figure 3 yes Figure 1 A cross-sectional view of a gas turbine blade is shown in FIG.

[0020] Figure 4 It is a schematic structural diagram of a gas turbine blade according to another embodiment of the present invention.

[0021] Reference numerals:

[0022] Blade body 1, cooling channel 11, inlet 111, outlet 112,

[0023] The first spoiler 2 and the second spoiler 3 . DETAILED DESCRIPTION

[0024] Embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used to explain the present invention, but should not be understood as limiting the present invention.

[0025] A gas turbine blade according to an embodiment of the present invention comprises a blade body 1, a plurality of first spoilers 2 and a plurality of second spoilers 3, wherein a cooling channel 11 is provided in the blade body 1, the first spoilers 2 and the second spoilers 3 are respectively arranged on the inner wall surface of the cooling channel 11, and the plurality of first spoilers 2 and the plurality of second spoilers 3 are alternately arranged in the length direction of the blade body 1, and the size of the first spoiler 2 in the thickness direction of the blade body 1 is smaller than the size of the second spoiler 3 in the thickness direction of the blade body 1.

[0026] Specifically, Figure 1 As described above, the cooling channel 11 passes through the gas turbine blade in the left-right direction, and the first spoiler 2 and the second spoiler 3 are respectively arranged on the inner wall surface of the cooling channel 11. Figure 3 As shown, the size of the first spoiler 2 in the up-down direction is smaller than the size of the second spoiler 3 in the up-down direction, that is, the height of the first spoiler 2 is lower than the height of the second spoiler 3 .

[0027] The gas turbine blade of the embodiment of the present invention can disturb the cold air and destroy its boundary layer to enhance the heat exchange capacity by setting the first spoiler 2 and the second spoiler 3. At the same time, the heat exchange area of ​​the cooling channel 11 is increased to increase the heat exchange amount. Since the height of the first spoiler 2 is lower than the height of the second spoiler 3, under a large amount of cold air, the flow field behind the first spoiler 2 and the second spoiler 3 is less affected, and the re-attachment effect of the cold air will not be affected, and the heat exchange can be increased at the angle of increasing the heat exchange area. Under low working conditions, the cold air will drop rapidly after bypassing the second spoiler 3, and attach in front of the first spoiler 2, and the boundary layer will gradually thicken. During the flow process, the cold air will be affected by the first spoiler 2, and the boundary layer will be interrupted by the first spoiler 2, forming a new spoiler effect, and obtaining better cooling capacity. At the same time, the heat exchange area can be increased, and increasing the heat exchange amount can improve the cooling efficiency of the blade.

[0028] In some embodiments, the cooling channel is arranged in the thickness direction of the blade body 1 (eg Figure 1The blade body 1 has a first side wall surface and a second side wall surface (in the up and down direction shown in the figure), a plurality of first spoilers 2 are respectively arranged on the first side wall surface and the second side wall surface, a plurality of second spoilers 3 are respectively arranged on the first side wall surface and the second side wall surface, the plurality of first spoilers 2 and the plurality of second spoilers 3 located on the first side wall surface are alternately arranged in the length direction of the blade body 1, and / or the plurality of first spoilers 2 and the plurality of second spoilers 3 located on the second side wall surface are alternately arranged in the length direction of the blade body 1.

[0029] Specifically, Figure 1 As shown, a plurality of first spoilers 2 are respectively arranged on the upper wall and the lower wall of the cooling channel, and the number of the first spoilers 2 arranged on the upper wall and the lower wall of the cooling channel is the same, a plurality of second spoilers 3 are respectively arranged on the upper wall and the lower wall of the cooling channel, and the number of the second spoilers 3 arranged on the upper wall and the lower wall of the cooling channel is the same, and the number of the first spoilers 2 located on the upper wall of the cooling channel is the same as the number of the second spoilers 3 located on the upper wall of the cooling channel, and the number of the first spoilers 2 located on the lower wall of the cooling channel is the same as the number of the second spoilers 3 located on the lower wall of the cooling channel.

[0030] The first spoiler 2 located on the upper wall of the cooling runner and the second spoiler 3 located on the upper wall of the cooling runner are evenly spaced in the left-right direction, or the first spoiler 2 located on the lower wall of the cooling runner and the second spoiler 3 located on the lower wall of the cooling runner are evenly spaced in the left-right direction, or the first spoiler 2 located on the upper wall of the cooling runner and the second spoiler 3 located on the upper wall of the cooling runner are evenly spaced in the left-right direction and the first spoiler 2 located on the lower wall of the cooling runner and the second spoiler 3 located on the lower wall of the cooling runner are evenly spaced in the left-right direction.

[0031] The gas turbine blades of the embodiment of the present invention are provided with alternately arranged first spoilers 2 and second spoilers 3. Under low operating conditions, the cold air will quickly drop after bypassing the second spoiler 3, and will adhere in front of the first spoiler 2. The boundary layer will gradually thicken. During the flow, the cold air will be affected by the first spoiler 2, and the boundary layer will be interrupted by the first spoiler 2, forming a new spoiler effect and obtaining better cooling capacity.

[0032] In some embodiments, the first spoiler 2 located on the first side wall surface and the second spoiler 3 located on the second side wall surface are arranged relative to each other in the thickness direction of the blade body 1, and / or the second spoiler 3 located on the first side wall surface and the first spoiler 2 located on the second side wall surface are arranged relative to each other in the thickness direction of the blade body 1.

[0033] Specifically, Figure 3As shown, the first spoiler 2 located on the upper wall of the cooling channel 11 and the second spoiler 3 located on the lower wall of the cooling channel 11 are arranged relative to each other in the up-down direction, or the first spoiler 2 located on the upper wall of the cooling channel 11 and the second spoiler 3 located on the lower wall of the cooling channel 11 are arranged relative to each other in the up-down direction, or the first spoiler 2 located on the upper wall of the cooling channel 11 and the second spoiler 3 located on the lower wall of the cooling channel 11 are arranged relative to each other in the up-down direction and the first spoiler 2 located on the upper wall of the cooling channel 11 and the second spoiler 3 located on the lower wall of the cooling channel 11 are arranged relative to each other in the up-down direction.

[0034] In the gas turbine blade of the embodiment of the present invention, the first spoiler 2 located on the upper end surface of the cooling channel 11 and the second spoiler 3 located on the lower end surface of the cooling channel 11 are arranged opposite to each other in the up-down direction, and the second spoiler 3 located on the upper end surface of the cooling channel 11 and the first spoiler 2 located on the lower end surface of the cooling channel 11 are arranged opposite to each other in the up-down direction, so that the size of the cooling flow channel in the up-down direction gradually changes in the direction extending from the inlet 111 to the outlet 112.

[0035] In other words, the size of the cooling channel in the vertical direction changes from left to right in alternating sizes. Since the size of the cooling channel changes in the left and right directions and is zigzag, it can not only increase the length of the cold air flowing in the cooling channel 11, but also, under low working conditions, the cold air will quickly decrease after bypassing the second spoiler 3, and attach to the first spoiler 2, and the boundary layer will gradually thicken. During the flow process, the cold air will be affected by the first spoiler 2, and the boundary layer will be interrupted by the first spoiler 2, forming a new spoiler effect, and obtaining better cooling capacity. At the same time, the heat exchange area can be increased, and increasing the heat exchange can improve the cooling efficiency of the blade.

[0036] In some embodiments, the dimension of the first spoiler 2 in the thickness direction of the blade body 1 is A, the dimension of the second spoiler 3 in the thickness direction of the blade body 1 is B, and 0.2B≤A≤0.5B.

[0037] It should be noted that the size of the first spoiler 2 in the vertical direction is A, the size of the second spoiler 3 in the vertical direction is B, and 0.2B≤A≤0.5B, for example, A=0.2B, 0.3B, 0.35B, 0.34B or 0.5B. When the size A of the first spoiler 2 in the vertical direction is less than 0.2B, under low working conditions, the cold air cannot be attached in front of the first spoiler 2, so that the boundary layer cannot be gradually thickened, and a new spoiler effect cannot be formed at the first spoiler 2, which leads to cooling failure. When the size A of the first spoiler 2 in the vertical direction is greater than 0.5B, the first spoiler 2 increases the obstruction to the circulation of cold air, so that the circulation of cold air in the cooling channel 11 is obstructed, thereby affecting the cooling effect of the entire blade body 1.

[0038] In some embodiments, the dimension of the first spoiler 2 in the length direction of the blade body 1 is less than or equal to the dimension of the second spoiler 3 in the length direction of the blade body 1 .

[0039] Specifically, Figure 3 As shown, when the size of the first spoiler 2 in the left-right direction is smaller than the size of the second spoiler 3 in the left-right direction, since the size of the first spoiler 2 in the up-down direction is smaller than the size of the second spoiler 3 in the up-down direction, when the size of the first spoiler 2 in the left-right direction is smaller than the size of the second spoiler 3, it is easier for the cold air to form a new spoiler effect at the first spoiler 2, thereby improving the cooling capacity of the gas turbine blade. However, when the size of the first spoiler 2 in the left-right direction is larger than the size of the second spoiler 3, the circulation of the cold air at the first spoiler 2 is blocked, thereby reducing the cooling effect of the entire blade body 1.

[0040] In some embodiments, the cooling channel has an inlet 111 and an outlet 112, the spacing distance between two adjacent second spoilers 3 is C, the distance between a first spoiler 2 between two adjacent second spoilers 3 and a second spoiler 3 adjacent to the inlet 111 of the two adjacent second spoilers 3 is D, and 0.2C≤D≤0.5C.

[0041] Specifically, Figure 3 As shown, the spacing distance between two adjacent second spoilers 3 in the left-right direction is C, the spacing distance between the left side surface of the first spoiler 2 between the two second spoilers 3 and the right end surface of the left second spoiler 3 of the two second spoilers 3 in the left-right direction is D, and 0.2C≤D≤0.5C. For example, D=0.2C, 0.3C, 0.4C or 0.5C.

[0042] For the gas turbine blade of the embodiment of the present invention, when the distance D between the left side of the first spoiler 2 between the two second spoilers 3 and the right end face of the second spoiler 3 on the left side of the two second spoilers 3 in the left-right direction is less than 0.2C, it is easy to cause the cold air passing through the second spoiler 3 to fail to attach to the first spoiler 2 in time, affecting the cooling effect. When the distance D between the left side of the first spoiler 2 between the two second spoilers 3 and the right end face of the second spoiler 3 on the left side of the two second spoilers 3 in the left-right direction is greater than 0.5C, it is easy to increase the retention time of the cold air at the first spoiler 2, affecting the circulation time of the cold air in the cooling channel 11, thereby reducing the cooling effect.

[0043] In some embodiments, the first spoiler 2 and the second spoiler 3 are arranged in parallel.

[0044] Specifically, Figure 2As shown, the first spoiler 2 and the second spoiler 3 extend in both front-to-back directions, and the first spoiler 2 and the first spoiler 2 are arranged parallel to each other. The first spoiler 2 and the second spoiler 3 are arranged in parallel, so that the cold air at each location on the first spoiler 2 and the second spoiler 3 can be evenly attached, thereby improving the cooling effect.

[0045] In some embodiments, the cooling channel has an inlet 111 and an outlet 112 , the length direction of the first spoiler 2 forms an angle with the width direction of the blade body 1 , and / or the length direction of the second spoiler 3 forms an angle with the width direction of the blade body 1 .

[0046] Specifically, the first spoiler 2 and the second spoiler 3 both extend in the front-rear direction, and the first spoiler 2 is arranged obliquely in the left-right direction, or the second spoiler 3 is arranged obliquely in the left-right direction, or the first spoiler 2 and the second spoiler 3 are arranged obliquely.

[0047] Optionally, the adjacent first spoiler 2 and second spoiler 3 have different inclination directions. For example, the first spoiler 2 is arranged obliquely from front to back, and the second spoiler 3 is arranged from back to front. The connected first spoiler 2 and second spoiler 3 are arranged in an eight-shape, thereby increasing the length of the cold air flowing in the cooling channel 11 and improving the cooling effect.

[0048] In some embodiments, the first spoiler 2 and the second spoiler 3 are integrally formed with the blade body 1 .

[0049] For example, the first spoiler 2 and the second spoiler 3 can also be detachably connected to the blade body 1 by welding. The first spoiler 2 and the second spoiler 3 are formed in one piece to avoid cooling failure caused by the outflow of cold air through the gap between the first spoiler 2 and the second spoiler 3 and the blade body 1. The one-piece forming can not only improve the cooling effect, but also improve the structural strength of the gas turbine blade.

[0050] A gas turbine according to an embodiment of the present invention comprises a gas turbine blade according to any one of the above embodiments.

[0051] The gas turbine of the embodiment of the present invention can improve the cooling efficiency of the blades and the performance of the gas turbine by adopting the gas turbine blades of the above embodiment.

[0052] In the description of the present invention, it is to be understood that the terms “center”, “longitudinal”, “lateral”, “length”, “width”, “thickness”, “up”, “down”, “front”, “back”, “left”, “right”, “vertical”, “horizontal”, “top”, “bottom”, “inside”, “outside”, “clockwise”, “counterclockwise”, “axial”, “radial”, “circumferential”, etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0053] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0054] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral one; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0055] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0056] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the described specific features, structures, materials or characteristics may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0057] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.

Claims

1. A gas turbine blade, characterized in that: include: A blade body, wherein the blade body has a cooling channel; A plurality of first spoilers and a plurality of second spoilers, wherein the first spoilers and the second spoilers are respectively arranged on the inner wall surface of the cooling channel, and the plurality of first spoilers and the plurality of second spoilers are alternately arranged in the length direction of the blade body, and the size of the first spoiler in the thickness direction of the blade body is smaller than the size of the second spoiler in the thickness direction of the blade body; The cooling channel has a first side wall surface and a second side wall surface in the thickness direction of the blade body, a plurality of the first spoilers are respectively arranged on the first side wall surface and the second side wall surface, a plurality of the second spoilers are respectively arranged on the first side wall surface and the second side wall surface, the plurality of the first spoilers and the plurality of the second spoilers located on the first side wall surface are alternately arranged in the length direction of the blade body, and / or the plurality of the first spoilers and the plurality of the second spoilers located on the second side wall surface are alternately arranged in the length direction of the blade body; The first spoiler located on the first side wall surface and the second spoiler located on the second side wall surface are arranged opposite to each other in the thickness direction of the blade body, and / or the second spoiler located on the first side wall surface and the first spoiler located on the second side wall surface are arranged opposite to each other in the thickness direction of the blade body; Under low operating conditions, the cold air quickly drops after bypassing the second spoiler and attaches in front of the first spoiler, and the boundary layer gradually thickens. During the flow, the cold air will be affected by the first spoiler, and the boundary layer will be interrupted by the first spoiler, forming a new spoiler effect.

2. The gas turbine blade according to claim 1, characterized in that: The dimension of the first spoiler in the thickness direction of the blade body is A, the dimension of the second spoiler in the thickness direction of the blade body is B, and 0.2B≤A≤0.5B.

3. The gas turbine blade according to claim 1, characterized in that: The dimension of the first spoiler in the length direction of the blade body is smaller than or equal to the dimension of the second spoiler in the length direction of the blade body.

4. The gas turbine blade according to claim 1, characterized in that: The cooling channel has an inlet and an outlet, the spacing distance between two adjacent second spoilers is C, the distance between one of the first spoilers between two adjacent second spoilers and one of the second spoilers adjacent to the inlet is D, and 0.2C≤D≤0.5C.

5. The gas turbine blade according to claim 1, characterized in that: The first spoiler and the second spoiler are arranged in parallel.

6. The gas turbine blade according to claim 1, characterized in that: The length direction of the first spoiler forms an angle with the width direction of the blade body, and / or the length direction of the second spoiler forms an angle with the width direction of the blade body.

7. The gas turbine blade according to any one of claims 1 to 6, characterized in that: The first spoiler, the second spoiler and the blade body are integrally formed.

8. A gas turbine, characterized in that: The invention comprises the gas turbine blade according to any one of claims 1 to 7.

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