Turbine blade tail edge turbulent flow structure of gas turbine

Abstract

The invention discloses a gas turbine blade trailing edge turbulent flow structure which comprises a body, the body comprises a first part, a second part and a third part, the first part and the second part are symmetrically arranged, at least part of the third part is located between the first part and the second part, and the third part is located between the first part and the second part. A first channel is arranged between the first part and the second part, a second channel is arranged between the first part and the third part, a third channel is arranged between the first part and the third part, and the first channel is communicated with the second channel and the third channel. The tail edge turbulent flow structure of the turbine blade of the gas turbine is good in turbulent flow effect and small in flowing resistance to cooling fluid.

Description

Technical Field

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

[0002] Gas turbines have important applications in many fields such as aviation propulsion, ship propulsion, and power generation. With the development of gas turbine technology, the working environment temperature of turbine blades continues to increase. In order to ensure that turbine blades work within the allowable temperature range of high-temperature alloy materials to ensure the life of the blades, higher requirements are put forward for the design of blade cooling structures, which brings more challenges. Traditional cooling structures are increasingly unable to meet the design requirements. It is urgent to propose more efficient cooling structures to improve heat exchange efficiency and extend the life of turbine blades.

[0003] In the related art, a plurality of cylindrical spoiler structures are arranged in the trailing edge area of ​​the turbine blade. On the one hand, the turbulence of the cooling airflow is increased by spoiler flow. The two ends of the spoiler column are respectively connected to the suction surface and the pressure surface. The heat is transferred out after the heat conduction of the spoiler column, thereby increasing the heat exchange area of ​​the inner cavity, which helps to reduce the temperature difference between the suction surface and the pressure surface, make the wall temperature more uniform, and reduce thermal stress. On the other hand, the spoiler column connects the pressure surface and the suction surface, plays a supporting role, and improves the structural strength of the trailing edge of the blade. However, the cylindrical spoiler structure is prone to cause large flow losses, which affects the heat exchange effect. In addition, a vortex zone will be formed on the back of the traditional cylindrical spoiler column. The flow velocity in the vortex zone is very low, and the heat transfer intensity is relatively low, which affects the heat exchange uniformity of the tail of the spoiler column. Therefore, for the cooling of the trailing edge of the turbine blade, it is necessary to design a cooling structure with better cooling effect and smaller flow resistance loss. 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 trailing edge spoiler structure, which has good spoiler effect and small flow resistance to cooling fluid.

[0005] A gas turbine turbine blade trailing edge spoiler structure according to an embodiment of the present invention comprises a main body, wherein the main body comprises a first part, a second part and a third part, wherein the first part and the second part are symmetrically arranged, at least a part of the third part is located between the first part and the second part, a first channel is provided between the first part and the second part, a second channel is provided between the first part and the third part, a third channel is provided between the first part and the third part, and the first channel is connected to the second channel and the third channel.

[0006] The trailing edge spoiler structure of the gas turbine turbine blade in the embodiment of the present invention increases the heat exchange area of ​​the cooling airflow when it flows through the body by setting the first channel, the second channel and the third channel, reduces the flow resistance of the body to the cooling airflow, and the cooling airflows disturb each other when flowing out through the first channel, the second channel and the third channel respectively, which is beneficial for the heat on the turbine blades to be transferred to the cooling airflow through the body, thereby improving the turbulence intensity of the cooling airflow, quickly taking away the heat, and enhancing the heat exchange effect.

[0007] In some embodiments, the first part has a first outer peripheral surface and a first inner peripheral surface, the second part has a second outer peripheral surface and a second inner peripheral surface, the first outer peripheral surface and the second outer peripheral surface are symmetrically arranged, and the first outer peripheral surface and the second outer peripheral surface protrude in directions away from each other, the first inner peripheral surface and the second inner peripheral surface are symmetrically arranged, and the first inner peripheral surface and the second inner peripheral surface protrude in directions approaching each other, and the first channel is formed between the first inner peripheral surface and the second inner peripheral surface.

[0008] In some embodiments, the cross-sectional areas at both ends of the first channel are larger than the cross-sectional area at the middle position of the first channel.

[0009] In some embodiments, the first outer peripheral surface includes a continuous first arc segment, a first transition segment, and a second arc segment, the first arc segment protrudes in a direction away from the first inner peripheral surface, the second arc segment protrudes in a direction away from the first inner peripheral surface, and the curvature radius of the first arc segment and the curvature radius of the second arc segment are both smaller than the curvature radius of the first transition segment.

[0010] In some embodiments, the first transition section is a straight section, and the length of the first transition section is L, where L≥0.

[0011] In some embodiments, one end of the first arc segment is connected to one end of the first inner circumferential surface, the other end of the first arc segment extends toward the first transition segment and is inclined toward a direction away from the first inner circumferential surface, and the end of the second arc segment away from the first transition segment extends toward the other end of the first inner circumferential surface and is inclined toward the first inner circumferential surface.

[0012] In some embodiments, the third part has a first end and a second end, and the outer peripheral contour of the third part includes a third outer peripheral surface, a fourth outer peripheral surface, a third inner peripheral surface and a fourth inner peripheral surface connected in sequence, the first end is located at the connection between the third inner peripheral surface and the fourth inner peripheral surface, the second end is located at the connection between the third outer peripheral surface and the fourth outer peripheral surface, the first end and the second end are both pointed ends, the first end is located between the first inner peripheral surface and the second inner peripheral surface, the second channel is formed between the fourth inner peripheral surface and the first inner peripheral surface, and the third channel is formed between the third inner peripheral surface and the second inner peripheral surface.

[0013] In some embodiments, the second channel and the third channel are symmetrically arranged.

[0014] In some embodiments, a cross-sectional area of ​​an end of the second channel adjacent to the first channel is larger than a cross-sectional area of ​​an end of the second channel distal to the first channel.

[0015] In some embodiments, the body has a first opening, a second opening and a third opening, the first opening is formed at an end of the first channel away from the third part, the second opening is formed at an end of the second channel away from the first channel, the third opening is formed at an end of the third channel away from the first channel, and the second opening and the third opening are symmetrically arranged. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 The figure is a schematic diagram of the arrangement of the spoiler structure at the trailing edge of a gas turbine blade according to an embodiment of the present invention.

[0017] Figure 2 The figure is a top view of the trailing edge spoiler structure of a gas turbine blade according to an embodiment of the present invention.

[0018] Figure 3 It is a three-dimensional schematic diagram of the main body structure of the trailing edge spoiler structure of a gas turbine blade according to an embodiment of the present invention.

[0019] Figure 4 It is a plan view of the main body structure of the trailing edge spoiler structure of a gas turbine blade according to an embodiment of the present invention.

[0020] Figure 5 The figure is a flow diagram of the cooling airflow of the trailing edge spoiler structure of the gas turbine blade of an embodiment of the present invention.

[0021] Figure 6 It is a schematic diagram of the opening of the main body of the trailing edge spoiler structure of a gas turbine blade according to an embodiment of the present invention.

[0022] 1. Main body; 11. First part; 111. First outer peripheral surface; 1111. First arc segment; 1112. First transition segment; 1113. Second arc segment; 112. First inner peripheral surface; 12. Second part; 121. Second outer peripheral surface; 1211. Third arc segment; 1212. Second transition segment; 1213. Fourth arc segment; 122. Second inner peripheral surface; 13. Third part; 131. First end; 132. Second end; 133. Third outer peripheral surface; 134. Fourth outer peripheral surface; 135. Third inner peripheral surface; 136. Fourth inner peripheral surface; 14. First channel; 141. First section; 142. Middle section; 143. Second section; 15. Second channel; 16. Third channel; 171. First interference area; 172. Second interference area; 181. First opening; 182. Second opening; 183. Third opening. DETAILED DESCRIPTION

[0023] 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.

[0024] like Figure 1-6 As shown, the trailing edge spoiler structure of a gas turbine turbine blade according to an embodiment of the present invention comprises a main body 1, the main body 1 comprises a first part 11, a second part 12 and a third part 13, the first part 11 and the second part 12 are symmetrically arranged, at least a part of the third part 13 is located between the first part 11 and the second part 12, a first channel 14 is provided between the first part 11 and the second part 12, a second channel 15 is provided between the first part 11 and the third part 13, a third channel 16 is provided between the second part 12 and the third part 13, and the first channel 14 is connected with the second channel 15 and the third channel 16.

[0025] The trailing edge spoiler structure of the gas turbine turbine blade in the embodiment of the present invention increases the heat exchange area of ​​the cooling airflow when it flows through the body 1 by setting the first channel 14, the second channel 15 and the third channel 16, and reduces the flow resistance of the body 1 to the cooling airflow. In addition, the cooling airflows disturb each other when flowing out through the first channel 14, the second channel 15 and the third channel 16 respectively, which is conducive to the heat on the turbine blades being transferred to the cooling airflow through the body 1, thereby improving the turbulence intensity of the cooling airflow, quickly taking away the heat, and enhancing the heat exchange effect.

[0026] Specifically, there are multiple bodies 1, and the multiple bodies 1 are arranged at intervals on the inner wall surface of the turbine blade. Preferably, the multiple bodies 1 are divided into multiple groups, and the multiple groups of bodies 1 are arranged at intervals along the first direction. Each group includes multiple bodies 1, and the multiple bodies 1 in each group are arranged at intervals along the second direction. The second direction is orthogonal to the first direction, and the multiple bodies 1 in two adjacent groups are arranged in a staggered manner. There is a cooling airflow in the turbine blade. When the cooling airflow can flow from one end of the body 1 to the other end of the body 1, the body 1 can disturb the cooling airflow to improve the cooling effect of the cooling airflow on the turbine blade.

[0027] In some embodiments, the first portion 11 has a first outer circumferential surface 111 and a first inner circumferential surface 112, and the second portion 12 has a second outer circumferential surface 121 and a second inner circumferential surface 122. The first outer circumferential surface 111 and the second outer circumferential surface 121 are symmetrically arranged, and the first outer circumferential surface 111 and the second outer circumferential surface 121 protrude in directions away from each other, the first inner circumferential surface 112 and the second inner circumferential surface 122 are symmetrically arranged, and the first inner circumferential surface 112 and the second inner circumferential surface 122 protrude in directions approaching each other, and the first channel 14 is formed between the first inner circumferential surface 112 and the second inner circumferential surface 122.

[0028] Specifically, the first outer peripheral surface 111 and the first inner peripheral surface 112 are both generally arc-shaped and convex in directions away from each other, and the second outer peripheral surface 121 and the second inner peripheral surface 122 are both generally arc-shaped and convex in directions away from each other, so that the outer contours of the first part 11 and the second part 12 are smooth and streamlined, reducing the flow resistance to the cooling airflow and ensuring the heat exchange effect.

[0029] In some embodiments, the cross-sectional areas at both ends of the first channel 14 are greater than the cross-sectional area at the middle of the first channel 14. Specifically, the first channel 14 has a first section 141, a middle section 142, and a second section 143 connected in sequence, and the first section 141 and the second section 143 are expanded to reduce the flow loss of the cooling airflow at the inlet and outlet at the end of the first channel 14.

[0030] In some embodiments, the first outer peripheral surface 111 includes a continuous first arc segment 1111, a first transition segment 1112 and a second arc segment 1113, the first arc segment 1111 protrudes in a direction away from the first inner peripheral surface 112, the second arc segment 1113 protrudes in a direction away from the first inner peripheral surface 112, and the curvature radius of the first arc segment 1111 and the curvature radius of the second arc segment 1113 are both smaller than the curvature radius of the first transition segment 1112.

[0031] Specifically, the second outer peripheral surface 121 includes a continuous third arc segment 1211, a second transition segment 1212 and a fourth arc segment 1213. The third arc segment 1211 protrudes in a direction away from the second inner peripheral surface 122 and is symmetrically arranged with the first arc segment 1111. The fourth arc segment 1213 protrudes in a direction away from the second inner peripheral surface 122 and is symmetrically arranged with the second arc segment 1113. The second transition segment 1212 and the first transition segment 1112 are symmetrically arranged. The curvature radius of the third arc segment 1211 and the curvature radius of the fourth arc segment 1213 are both smaller than the curvature radius of the second transition segment 1212. By setting the outer contours of the first outer peripheral surface 111 and the second outer peripheral surface 121 as described above, a streamlined outer contour is formed, which can effectively reduce the flow loss of the cooling airflow.

[0032] In some embodiments, the first transition section 1112 is a straight section, and the length of the first transition section 1112 is L, where L≥0. The second transition section 1212 is also a straight section, and the length of the second transition section 1212 is also L. The first transition section 1112 is taken as an example for description below.

[0033] Specifically, when L>0, both the first outer peripheral surface 111 and the second outer peripheral surface 121 have straight sections, which can effectively avoid flow separation of the cooling airflow at the junction of the first arc segment 1111 and the second arc segment 1113. The distance between the first transition segment 1112 and the second transition segment 1212 is W1, and the size of W1 is adjustable, which is convenient for flexible adjustment of the maximum width of the main body 1.

[0034] When L=0, neither the first outer peripheral surface 111 nor the second outer peripheral surface 121 has a straight section, the outer peripheral contours of the first outer peripheral surface 111 and the second outer peripheral surface 121 are streamlined, the outer peripheral contour of the main body 1 is airfoil-shaped, and the maximum width of the main body 1 is W2, that is, the distance between the junction of the first arc segment 1111 and the second arc segment 1113 and the junction of the third arc segment 1211 and the fourth arc segment 1213, W2>W1.

[0035] In some embodiments, one end of the first arc segment 1111 is connected to one end of the first inner circumferential surface 112, the other end of the first arc segment 1111 extends toward the first transition segment 1112 and is inclined toward a direction away from the first inner circumferential surface 112, and the second arc segment 1113 extends from one end of the first transition segment 1112 toward the other end of the first inner circumferential surface 112 and is inclined toward the first inner circumferential surface 112.

[0036] Specifically, one end of the third arc segment 1211 is connected to one end of the second inner circumferential surface 122, the other end of the third arc segment 1211 extends toward the second transition segment 1212 and is inclined toward a direction away from the second inner circumferential surface 122, and the fourth arc segment 1213 extends from one end away from the second transition segment 1212 toward the other end of the second inner circumferential surface 122 and is inclined toward the second inner circumferential surface 122.

[0037] In some embodiments, the third portion 13 has a first end 131 and a second end 132, and the outer peripheral contour of the third portion 13 includes a third outer peripheral surface 133, a fourth outer peripheral surface 134, a third inner peripheral surface 135 and a fourth inner peripheral surface 136 connected in sequence, the first end 131 is located at the connection between the third inner peripheral surface 135 and the fourth inner peripheral surface 136, the second end 132 is located at the connection between the third outer peripheral surface 133 and the fourth outer peripheral surface 134, the first end 131 and the second end 132 are both pointed ends, the first end 131 is located between the first inner peripheral surface 112 and the second inner peripheral surface 122, a second channel 15 is formed between the fourth inner peripheral surface 136 and the first inner peripheral surface 112, and a third channel 16 is formed between the third inner peripheral surface 135 and the second inner peripheral surface 122.

[0038] Specifically, the outer contour of the body 1 is generally an airfoil that expands first and then contracts from the end of the first part 11 away from the third part 13 to the second end 132 of the third part 13. The second end 132 is relatively sharp, so that the body 1 does not have a rear area of ​​the trailing edge. Compared with the traditional cylindrical spoiler structure, the low-speed vortex area behind the body 1 can be well suppressed, and the heat exchange uniformity of the tail of the body 1 is improved. Moreover, the first outer peripheral surface 111 and the second outer peripheral surface 121 have a good guiding effect on the cooling fluid, which can further reduce the flow loss of the cooling fluid. At the same time, the cooling fluid is disturbed by the outlet fluid of the second channel 15 and the third channel 16 at the second arc segment 1113 and the fourth arc segment 1213 of the body 1, and a vortex will be formed and expand to a distance, which enhances the disturbance effect of the cooling fluid on the area between the body 1 and the body 1, and improves the heat exchange effect and efficiency.

[0039] In some embodiments, the second channel 15 and the third channel 16 are symmetrically arranged.

[0040] Specifically, the outlet of the second channel 15 of one of the main bodies 1 in each group and the outlet of the third channel 16 of another adjacent main body 1 can form a first interference area 171. The cold air flowing out of the second channel 15 and the third channel 16 interfere with each other, which can enhance the turbulence of the fluid and enhance heat exchange.

[0041] Specifically, a second interference area 172 can be formed at the outlet of the second channel 15 or the outlet of the third channel 16, and the cooling fluid on the outer peripheral surface of the main body 1 interferes with the cooling fluid flowing out of the outlet of the second channel 15 or the outlet of the third channel 16, which can enhance the turbulence of the fluid and enhance heat exchange.

[0042] In some embodiments, the cross-sectional area of ​​the second channel 15 at one end adjacent to the first channel 14 is larger than the cross-sectional area of ​​the second channel 15 at one end away from the first channel 14 , which can reduce the flow loss of the cooling airflow at the inlet of the second channel 15 .

[0043] Specifically, the cross-sectional area of ​​one end of the third channel 16 adjacent to the first channel 14 is larger than the cross-sectional area of ​​one end of the third channel 16 away from the first channel 14 , which can reduce the flow loss of the cooling airflow at the inlet of the third channel 16 .

[0044] In some embodiments, the body 1 has a first opening 181, a second opening 182 and a third opening 183, the first opening 181 is formed at an end of the first channel 14 away from the third part 13, the second opening 182 is formed at an end of the second channel 15 away from the first channel 14, and the third opening 183 is formed at an end of the third channel 16 away from the first channel 14, and the second opening 182 and the third opening 183 are symmetrically arranged.

[0045] 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.

[0046] 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.

[0047] 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.

[0048] 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.

[0049] 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.

[0050] Although the above embodiments have been shown and described, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations on the present invention. Changes, modifications, substitutions and variations of the above embodiments by those of ordinary skill in the art are all within the scope of protection of the present invention.

Claims

1. A gas turbine blade trailing edge spoiler structure, characterized in that: The invention comprises a body (1), wherein the body (1) comprises a first part (11), a second part (12) and a third part (13), wherein the first part (11) and the second part (12) are symmetrically arranged, at least a part of the third part (13) is located between the first part (11) and the second part (12), a first channel (14) is provided between the first part (11) and the second part (12), a second channel (15) is provided between the first part (11) and the third part (13), a third channel (16) is provided between the first part (11) and the third part (13), and the first channel (14) is connected with the second channel (15) and the third channel (16).

2. The gas turbine blade trailing edge spoiler structure according to claim 1, characterized in that: The first part (11) has a first outer peripheral surface (111) and a first inner peripheral surface (112); the second part (12) has a second outer peripheral surface (121) and a second inner peripheral surface (122); the first outer peripheral surface (111) and the second outer peripheral surface (121) are symmetrically arranged, and the first outer peripheral surface (111) and the second outer peripheral surface (121) protrude in directions away from each other; the first inner peripheral surface (112) and the second inner peripheral surface (122) are symmetrically arranged, and the first inner peripheral surface (112) and the second inner peripheral surface (122) protrude in directions approaching each other; and the first channel (14) is formed between the first inner peripheral surface (112) and the second inner peripheral surface (122).

3. The gas turbine blade trailing edge spoiler structure according to claim 2, characterized in that: The cross-sectional areas at both ends of the first channel (14) are greater than the cross-sectional area at the middle position of the first channel (14).

4. The gas turbine blade trailing edge spoiler structure according to claim 2, characterized in that: The first outer peripheral surface (111) comprises a continuous first arc segment (1111), a first transition segment (1112) and a second arc segment (1113); the first arc segment (1111) protrudes in a direction away from the first inner peripheral surface (112); the second arc segment (1113) protrudes in a direction away from the first inner peripheral surface (112); and the curvature radius of the first arc segment (1111) and the curvature radius of the second arc segment (1113) are both smaller than the curvature radius of the first transition segment (1112).

5. The gas turbine blade trailing edge spoiler structure according to claim 4, characterized in that: The first transition section (1112) is a straight section, and the length of the first transition section (1112) is L, where L≥0.

6. The gas turbine blade trailing edge spoiler structure according to claim 4, characterized in that: One end of the first arc segment (1111) is connected to one end of the first inner circumferential surface (112), the other end of the first arc segment (1111) extends toward the first transition segment (1112) and is inclined in a direction away from the first inner circumferential surface (112), and one end of the second arc segment (1113) away from the first transition segment (1112) extends toward the other end of the first inner circumferential surface (112) and is inclined in a direction toward the first inner circumferential surface (112).

7. The gas turbine blade trailing edge spoiler structure according to claim 3, characterized in that: The third part (13) has a first end (131) and a second end (132); the outer peripheral contour of the third part (13) comprises a third outer peripheral surface (133), a fourth outer peripheral surface (134), a third inner peripheral surface (135) and a fourth inner peripheral surface (136) which are connected in sequence; the first end (131) is located at the connection between the third inner peripheral surface (135) and the fourth inner peripheral surface (136); the second end (132) is located at the connection between the third outer peripheral surface (133) and the fourth outer peripheral surface (134); both the first end (131) and the second end (132) are pointed ends; the first end (131) is located between the first inner peripheral surface (112) and the second inner peripheral surface (122); the second channel (15) is formed between the fourth inner peripheral surface (136) and the first inner peripheral surface (112); and the third channel (16) is formed between the third inner peripheral surface (135) and the second inner peripheral surface (122).

8. The gas turbine blade trailing edge spoiler structure according to claim 7, characterized in that: The second channel (15) and the third channel (16) are arranged symmetrically.

9. The gas turbine blade trailing edge spoiler structure according to claim 7, characterized in that: The cross-sectional area of ​​an end of the second channel (15) adjacent to the first channel (14) is larger than the cross-sectional area of ​​an end of the second channel (15) remote from the first channel (14).

10. The gas turbine blade trailing edge spoiler structure according to claim 4, characterized in that: The body (1) has a first opening (181), a second opening (182) and a third opening (183); the first opening (181) is formed at an end of the first channel (14) away from the third part (13); the second opening (182) is formed at an end of the second channel (15) away from the first channel (14); the third opening (183) is formed at an end of the third channel (16) away from the first channel (14); the second opening (182) and the third opening (183) are symmetrically arranged.

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