Turbine blade trailing edge cooling structure and turbine blade

Abstract

This invention belongs to the field of turbine blade cooling, and specifically discloses a turbine blade trailing edge cooling structure and a turbine blade. The turbine blade trailing edge cooling structure includes a turbulence radiation assembly, which includes a turbulence radiation plate and a turbulence column. The turbulence radiation plate separates the leading and trailing edge surfaces of the blade trailing edge channel, dividing the trailing edge channel into two layers. The turbulence column passes through the turbulence radiation plate, and its two end faces respectively connect to the leading and trailing edge surfaces of the blade trailing edge channel. The turbulence radiation assembly of this invention can enhance the disturbance of the flow field within the channel and provide an extended cold surface, while simultaneously strengthening convective and radiative heat transfer, thereby significantly enhancing the overall cooling performance of the blade trailing edge channel. This effectively improves the problem of significant differences in cooling performance in local areas of the channel and also exhibits a heat transfer self-reinforcing effect.

Description

Technical Field

[0001] This invention belongs to the field of turbine blade cooling, and more specifically, relates to a turbine blade trailing edge cooling structure and a turbine blade. Background Technology

[0002] Turbines, as key components of gas turbines and aero engines, are widely used in aviation, shipbuilding, power generation, and other fields, holding significant importance for industry and national defense. Increasing the turbine inlet temperature can improve the overall performance of gas turbines and aero engines; currently, turbine inlet temperatures can reach as high as 2000K, exceeding the high-temperature resistance limits of advanced composite materials. To ensure component lifespan and operational safety, developing efficient cooling technologies and further enhancing the cooling performance of turbine blades is of paramount importance.

[0003] Turbine blades are generally divided into three parts according to their location: the leading edge region, the middle chord region, and the trailing edge region. To accommodate variations in blade shape, different cooling technologies are used in different regions. The leading edge often employs impingement cooling and film cooling; the middle chord region uses methods such as adding ribs or recesses within the internal cooling channel to improve heat transfer performance; and the trailing edge region often uses turbulence columns, which enhance heat transfer while also providing structural support.

[0004] To ensure aerodynamic performance, the thickness of turbine blades gradually decreases along the trailing edge. Therefore, for the trailing edge region, the internal cooling channels are designed as converging flow channels following the shape of the trailing edge, resulting in a narrower internal space compared to the central region. While the technique of arranging turbulence columns in the cooling channels within the trailing edge region is widely used, its turbulence-causing ability in the core area of ​​the channel is relatively weak.

[0005] Furthermore, existing turbine blade cooling technologies primarily rely on enhanced convection to improve heat transfer performance, neglecting the effective utilization of surface radiation. Turbine blades endure extremely high thermal loads over extended periods, particularly in the trailing edge region near the suction surface. Since fluid transitions often occur near the throat of the suction surface, high-temperature zones frequently exist, making the impact of radiation on the heat transfer process significant. Simultaneously, the temperature of the cooling medium within the channel increases along the flow direction during heat exchange with the structure, and the structural design results in poor localized cooling, leading to significant differences in heat transfer at different locations. This results in uneven temperature distribution and substantial thermal stress. Therefore, effectively improving the cooling performance of the blade trailing edge channel, enhancing heat transfer and temperature uniformity, and reducing thermal stress caused by temperature gradients are crucial. Summary of the Invention

[0006] In view of the above-mentioned defects or improvement needs of the prior art, the present invention provides a turbine blade trailing edge cooling structure and turbine blade, the purpose of which is to improve the overall cooling performance of the blade trailing edge channel, and at the same time effectively improve the problem of huge gaps in cooling performance in local areas of the channel.

[0007] To achieve the above objectives, according to one aspect of the present invention, a turbine blade trailing edge cooling structure is proposed, comprising a turbulence radiation assembly, wherein the turbulence radiation assembly includes a turbulence radiation plate and a turbulence column, wherein:

[0008] The radiating plate is used to separate the leading and trailing edges of the blade trailing edge channel, making the trailing edge channel divided into two layers; the radiating column is used to pass through the radiating plate, and the two end faces of the radiating column are respectively connected to the leading and trailing edges of the blade trailing edge channel. The junction of the radiating column and the radiating plate forms a central corner region, and the junctions of the radiating column with the leading and trailing edges respectively form endwall corner regions.

[0009] As a further preferred embodiment, there are multiple turbulence columns, and the diameter d of the turbulence column and the width W of the trailing edge channel satisfy 0.06W≤d≤0.09W.

[0010] As a further preferred embodiment, the flow spacing S between two adjacent turbulence columns is... x The relationship between the diameter d and the given diameter d satisfies 1.5d≤S x ≤3.5d; spanwise spacing S between two adjacent spoiler columns y The diameter d satisfies 1.5d≤S y ≤3.5d.

[0011] As a further preferred embodiment, the diameter of the turbulence column gradually decreases along the flow direction.

[0012] As a further preferred embodiment, the thickness of the turbulence-radiating plate is 2% to 8% of the diameter of the turbulence column.

[0013] As a further preferred embodiment, the thickness of the turbulence-radiating plate gradually decreases along the flow direction.

[0014] As a further preferred embodiment, the turbulence radiation plate is a corrugated plate or a flat plate with recesses on its surface.

[0015] As a further preferred embodiment, the cross-sectional shape of the turbulence column is circular or streamlined.

[0016] As a further preferred embodiment, both the cooling structure and the trailing edge channel undergo surface treatment to improve their emissivity.

[0017] As a further preferred embodiment, the turbulence radiating plate is located either at the center or offset from the trailing edge channel of the turbine blade.

[0018] According to another aspect of the present invention, a turbine blade is provided in which the aforementioned turbine blade trailing edge cooling structure is installed in the trailing edge channel of the turbine blade.

[0019] In summary, compared with the prior art, the above-described technical solutions conceived by this invention mainly possess the following technical advantages:

[0020] 1. This invention designs a turbulence radiation assembly including a turbulence radiation plate and a turbulence column. Placing it in the trailing edge channel can simultaneously enhance convective heat transfer and radiative heat transfer, improve the overall cooling performance of the turbine blade trailing edge channel, and effectively improve the problem of huge gaps in cooling performance in local areas of the channel. In addition, it has a heat transfer self-enhancing effect, and its cooling performance enhancement effect increases as the heat load increases.

[0021] 2. The leading and trailing edges of the channel are separated by a turbulence-radiating plate, resulting in a two-layer channel. Both layers contain corner regions where the leading edge of the turbulence column meets the wall. Therefore, the turbulence-radiating assembly not only forms horseshoe vortices at the corners where the root of the turbulence column meets the leading and trailing edges of the channel, but also adds horseshoe vortices at the corners where the turbulence column meets the surface of the turbulence-radiating plate. This further intensifies the separation vortex in the backflow zone at the trailing edge of the turbulence column, enhancing fluid turbulence at that location. In other words, through the cooperation of the turbulence-radiating plate and the turbulence column, a secondary flow is added to the core region, increasing the mixing of fluids within the trailing edge channel and thus strengthening convective heat transfer in the core region.

[0022] 3. The turbulence radiation component provides an extended cold surface, which significantly increases the surface area involved in radiative heat transfer, thereby enhancing the radiative heat transfer effect and thus improving the overall cooling performance of the trailing edge channel.

[0023] 4. The heat conduction effect inside the radiant baffle is introduced during the heat exchange process, making the temperature distribution in the trailing edge channel more uniform and enhancing the overall cooling performance.

[0024] 5. This invention designs parameters such as the diameter and spacing of the turbulence-inducing columns to improve the disturbance of the cooling medium within the channel, enhance fluid mixing, and avoid excessively increasing the channel blockage ratio. Specifically, since the turbulence-inducing columns have a disturbing effect on the flow field within the channel, if the diameter of the columns is too small and the spacing is too large, the disturbance will be weakened. However, since the trailing edge channel contracts along the flow direction, and the height of the tail outlet is significantly smaller than that of the channel inlet, the diameter of the turbulence-inducing columns should not be too large, and their arrangement should not be too dense, otherwise it will severely block the flow within the channel. Simultaneously, the blocking effect of turbulence-inducing columns of the same size on the flow area of ​​the contracting channel increases along the flow direction. Therefore, this invention designs the diameter d of the turbulence-inducing columns to satisfy 0.06W≤d≤0.09W with the channel width W, and the diameter of the turbulence-inducing columns gradually decreases along the flow direction; the flow direction spacing S of the turbulence-inducing columns... x The diameter d satisfies 1.5d≤S x≤3.5d, spanwise spacing S of the turbulence columns y The diameter d satisfies 1.5d≤S y ≤3.5d.

[0025] 6. The thickness of the turbulence-radiating plate in this invention is 2% to 8% of the diameter of the turbulence column. This is mainly due to the interaction between the turbulence-radiating plate and the turbulence column. To make the horseshoe vortex / separation vortex more intense, the thickness of the turbulence-radiating plate cannot be too large, otherwise it will reduce the effective working space in the two layers of the channel, affecting the development of the vortex structure. Furthermore, excessive thickness will increase the mass of the turbulence-radiating plate and cause excessive flow resistance. Meanwhile, insufficient thickness may cause deformation and damage during blade operation. In addition, since the diameter of the turbulence column gradually decreases along the flow direction, the thickness of the turbulence-radiating plate can also be reduced accordingly along the flow direction to further adapt to the converging flow channel and reduce flow resistance.

[0026] 7. In this invention, the turbulence-radiating plate can be further designed as a corrugated plate, or have recesses on the surface of a flat plate, so that the turbulence-radiating component induces more secondary flow while forming horseshoe vortices, increasing the degree of disturbance to the cooling medium in the channel and enhancing the mixing between fluids. This further enhances the heat exchange effect of the turbulence-radiating component. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the turbine blade trailing edge cooling structure in an embodiment of the present invention;

[0028] Figure 2 This is a schematic diagram of the arrangement and parameters of the turbulence columns in the turbulence radiation component according to an embodiment of the present invention;

[0029] Figure 3 The diagram shows the changes in the vortex structure within the trailing edge channel when using only the turbulence column and when using the turbulence radiation component of this invention. In the diagram, (a) shows the turbulence column only, and (b) shows the turbulence radiation component of this invention.

[0030] Figure 4 This is a schematic diagram of heat transfer within the trailing edge channel with a turbulence radiation component according to an embodiment of the present invention.

[0031] Figure 5 The following are schematic diagrams of different shapes and surface structures of the turbulence radiation components in the embodiments of the present invention, wherein (a) is a flat plate turbulence radiation plate, (b) is a corrugated plate turbulence radiation plate; (c) in which (1) is a smooth surface turbulence radiation plate, (2) is a surface-recessed turbulence radiation plate; (d) in which (1) is a circular cross-section turbulence column, (2) is a streamlined cross-section turbulence column;

[0032] Figure 6This is a comparison of the heat transfer effects of the trailing edge surfaces of the following three types of trailing edge channels when Re = 10000: the trailing edge channel without considering surface radiation and using only turbulence columns (model NN), the trailing edge channel considering surface radiation but using only turbulence columns (model NY), and the trailing edge channel considering surface radiation and using the turbulence radiation assembly of this invention (model YY).

[0033] Figure 7 This is a comparison of the heat transfer effects of the trailing edge surfaces of the trailing edge channel (model NN) without considering surface radiation and using only turbulence columns, the trailing edge channel (model NY) considering surface radiation but using only turbulence columns, and the trailing edge channel (model YY) considering surface radiation and using the turbulence radiation component of this invention when Re = 30000 in this embodiment of the invention.

[0034] Figure 8 In an embodiment of the present invention, the surface heat flux density of the trailing edge channel structure is q = 10000~30000 W / m. 2 The graph shows the overall heat transfer performance of the trailing edge channel (model YY) considering surface radiation and employing the turbulence radiation component of this invention as a function of heat flux density q, where (a) represents the overall Nusselt number ratio of the channel. As the heat flux density q changes, (b) shows the change of the comprehensive evaluation index η of the channel heat transfer performance with the heat flux density q;

[0035] Figure 9 With Re = 10000 and q = 10000 W / m 2 When using the radiative turbulence assembly (model YY) of the present invention, with the thickness of the turbulence radiating plate being 2%, 4%, and 8% of the diameter of the turbulence column, the changes in cooling performance within the trailing edge channel are shown in the graph. In this graph, (a) represents the overall Nusselt number ratio of the channel. As the thickness of the turbulent radiant plate changes, (b) shows the change of the comprehensive evaluation index η of the channel heat transfer performance with the thickness of the turbulent radiant plate.

[0036] In all the accompanying drawings, the same reference numerals are used to denote the same elements or structures, wherein: 1-tail edge channel, 2-turbulence column, 3-turbulence radiation plate, 4-leading edge surface, 5-tail edge surface, 6-cooling medium. Detailed Implementation

[0037] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention. Furthermore, the technical features involved in the various embodiments of this invention described below can be combined with each other as long as they do not conflict with each other.

[0038] An embodiment of the present invention provides a turbine blade trailing edge cooling structure, such as... Figure 1 As shown, the trailing edge channel 1 of the turbine blade gradually contracts along the flow direction of the cooling medium 6. The cooling structure includes a turbulence radiation assembly disposed within the trailing edge channel 1. The turbulence radiation assembly includes a turbulence radiation plate 3 and a turbulence column 2, wherein:

[0039] The turbulence radiating plate 3 completely separates the leading edge surface 4 and the trailing edge surface 5 of the trailing edge channel; the turbulence column 2 passes through the turbulence radiating plate 3, and the two end surfaces of the turbulence column 2 are respectively connected to the leading edge surface 4 and the trailing edge surface 5 of the trailing edge channel 1.

[0040] The use of turbulent radiation components allows for the influence of heat transfer within the trailing edge channel through various heat transfer mechanisms. The principle and function are as follows:

[0041] (1) The turbulence radiation component can enhance the turbulence of the fluid in the trailing edge channel and strengthen convective heat transfer.

[0042] When the cooling medium flows through the trailing edge channel, the fluid is obstructed by the turbulence column, forming horseshoe vortices at the corners where the root of the turbulence column meets the front and rear edges of the trailing edge channel, respectively; simultaneously, a recirculation zone forms at the trailing edge of the turbulence column, such as... Figure 3 As shown in (a). However, when conventional turbulence columns are arranged only in the trailing edge channel, their turbulence-causing ability in the channel core area (referring to the internal flow area opposite to the near-wall area) is relatively weak.

[0043] With the use of a turbulence-radiating component, the leading and trailing edges are separated by the turbulence-radiating plate within the component, resulting in a two-layered channel. Both layers contain corner regions at the junction of the leading edge of the turbulence column and the wall. Therefore, the turbulence-radiating component not only forms horseshoe vortices at the corners where the root of the turbulence column meets the leading and trailing edges of the channel, but also adds horseshoe vortices at the corners where the turbulence column meets the surface of the turbulence-radiating plate. This further intensifies the separation vortices in the backflow zone at the trailing edge of the turbulence column, enhancing fluid turbulence at that location. Figure 3 As shown in (b). This means that a secondary flow is added to the core region of the channel, increasing the mixing of fluids within the trailing edge channel and thus enhancing convective heat transfer in the core region. Therefore, the enhanced convective heat transfer in the core region is achieved by the formation of more corner regions within the channel, resulting in more vortex structures. This is accomplished by the turbulence-radiation components, with both the turbulence columns and the turbulence-radiation plates being indispensable.

[0044] (2) The turbulent radiation component provides an extended cold surface, increasing the surface area involved in radiative heat transfer.

[0045] Because the blades are subjected to extremely high thermal loads during operation, the existing trailing edge channel structure does not have a large area of ​​relatively low-temperature cold surface. It relies solely on the radiation from the high-temperature wall of the channel, which has a limited effect on improving the overall cooling performance.

[0046] According to this invention, a turbulence-radiating component is provided between the front and rear edge surfaces within the trailing edge channel. The cooling medium's cooling effect on the turbulence-radiating component creates a cold surface with a lower temperature and a larger area, enhancing the radiative heat transfer effect and thus improving the overall cooling performance of the trailing edge channel. Figure 4 As shown, in the trailing edge channel employing the turbulent radiation assembly, in addition to the external heat flow heating the channel wall through convection heat transfer, there is also heat conduction between the channel wall and the turbulent radiation assembly, heat conduction within the turbulent radiation assembly, convection heat transfer between the channel wall and the cooling medium, convection heat transfer between the surface of the turbulent radiation assembly and the cooling medium, and radiation heat transfer between the surface of the turbulent radiation assembly and the channel wall. In particular, the turbulent radiation plate in the turbulent radiation assembly provides a large area of ​​low-temperature cold surface, greatly enhancing the radiation heat transfer with the channel wall. Therefore, the turbulent radiation assembly enhances overall cooling performance by providing a large area of ​​low-temperature cold surface and strengthening radiation heat transfer.

[0047] (3) The turbulence radiation component increases the heat conduction effect.

[0048] As the cooling medium flows in from the trailing edge channel, it is continuously heated as it flows along the high-temperature wall, reducing the temperature difference between the medium and the channel wall. This will have an adverse effect on the cooling performance along the flow path.

[0049] According to the present invention, a turbulence radiation component is provided between the front and rear edge surfaces of the trailing edge channel. During the heat exchange process, the heat conduction effect inside the radiative turbulence plate is introduced, thereby affecting the radiative heat exchange between the radiative turbulence plate and the high-temperature structural surface, as well as the convective heat exchange between the radiative turbulence plate and the cooling working fluid. This makes the temperature distribution in the trailing edge channel more uniform and enhances the overall cooling performance.

[0050] Therefore, compared with existing turbine blade technology, the design of this invention does not adversely affect the structural strength and can rationally utilize various heat transfer modes within the trailing edge channel of the blade under high-temperature conditions. The turbulence-radiation component described in this invention can simultaneously enhance both convective and radiative heat transfer. On one hand, the turbulence-radiation component can create more vortex structures within the trailing edge channel, enhancing the turbulence of the fluid in the core region and increasing the mixing between fluids, thereby strengthening convective heat transfer. On the other hand, the turbulence-radiation component artificially expands the cold surface, significantly increasing the surface area involved in radiative heat transfer, thereby enhancing radiative heat transfer.

[0051] Furthermore, such as Figure 2 As shown, the diameter d of the turbulence column and the width W of the trailing edge channel satisfy 0.06W ≤ d ≤ 0.09W, and the diameter of the turbulence column can gradually decrease along the flow direction; the flow direction spacing S of the turbulence columns... x The relationship between the diameter d and the given diameter d satisfies 1.5d≤S x ≤3.5d; spanwise spacing S of the turbulence-inducing columns yThe relationship between the diameter d and the given diameter d satisfies 1.5d≤S y ≤3.5d; and S x With S y They may not be equal. This is because the turbulence columns have a disturbing effect on the flow field within the channel. If the diameter of the turbulence columns is too small and the spacing between them is too large, the degree of turbulence will be weakened. However, since the trailing channel contracts along the flow direction, the height of the tail outlet is significantly smaller than that of the channel inlet. Therefore, the diameter of the turbulence columns should not be too large and the arrangement should not be too dense. Otherwise, it will seriously block the flow within the channel, and the blocking effect of turbulence columns of the same size on the flow area of ​​the contracting channel will increase along the flow direction.

[0052] Furthermore, compared to smooth rectangular channels, setting up a turbulence-radiating plate in a converging trailing edge channel with conventional turbulence columns is more difficult to implement due to space constraints and varying channel heights. This invention designs the thickness of the turbulence-radiating plate to be 2%–8% of the turbulence column diameter *d*, i.e., 0.02d ≤ δ ≤ 0.08d. This is mainly due to the interaction between the turbulence-radiating plate and the turbulence column. To enhance the horseshoe vortex / separation vortex, the thickness of the turbulence-radiating plate cannot be too large; otherwise, it will reduce the effective working space in the two layers of the channel, affecting the development of the vortex structure. Simultaneously, the enhanced radiative heat transfer in this invention requires ensuring the "heat transfer area" of the turbulence-radiating plate, without excessive thickness. Otherwise, it will increase the mass of the turbulence-radiating plate and cause excessive flow resistance. Therefore, the plate thickness needs to be controlled to avoid significantly increasing the channel's blockage ratio. On the other hand, if the thickness of the turbulence-radiating plate is too small, it may deform and be damaged during blade operation; therefore, the thickness of the turbulence-radiating plate should meet the corresponding strength requirements.

[0053] Furthermore, since the diameter of the turbulence column can gradually decrease along the flow direction, the thickness of the turbulence radiation plate can also be reduced along the flow direction to reduce flow resistance; and the angle between the turbulence radiation plate and the turbulence column can be different from 90° to further adapt to the constricted flow channel.

[0054] Furthermore, the turbulence radiation component and trailing edge channel are surface treated to improve their emissivity, giving them good surface radiation characteristics, thereby making the overall heat exchange performance of the channel more balanced.

[0055] Furthermore, by improving the form of the aforementioned turbulence-radiating component, the enhanced cooling performance can be optimized. For example... Figure 5 As shown, the turbulence-radiating plate on the turbulence-radiating assembly can be, but is not limited to, a flat plate or a corrugated plate. Furthermore, recesses can be provided on the surface of the turbulence-radiating plate to induce more secondary flow while forming horseshoe vortices, increasing the disturbance to the cooling medium within the channel, enhancing fluid mixing, and thus further improving the heat transfer effect of the turbulence-radiating assembly. The cross-sectional shape of the turbulence column is circular or streamlined, improving heat transfer while reducing flow resistance.

[0056] The following are specific examples:

[0057] Cylindrical baffles are arranged in a row between the leading and trailing edges, and smooth baffle radiation plates are installed on the baffles to completely isolate the leading and trailing edges. External heat is introduced through the walls of the channel, and air at a temperature of 723K is selected as the cooling medium, flowing through the channel from the inlet to cool the structure.

[0058] At the same time, the Nusselt ratio is defined as Nu t / Nu0, the comprehensive evaluation index of channel heat transfer performance is η=(Nu t / Nu0) / (f / f0) 1 / 3 Nu0 and f0 are the Nusselt number and drag coefficient of the smooth channel of the undisturbed radiation component, respectively, serving as a benchmark to eliminate the influence of the channel's acceleration effect on the airflow.

[0059] (1) First set of embodiments

[0060] To facilitate comparison of the enhanced cooling performance of the trailing edge channel after adopting the radiation turbulence component of the present invention (model YY), numerical simulations were performed on the trailing edge channel (model NN) without considering surface radiation and using only turbulence pillars, and the trailing edge channel (model NY) considering surface radiation but using only turbulence pillars.

[0061] Figure 6 and Figure 7 When the Reynolds number Re = 10000 and Re = 30000 respectively (the surface heat flux density q of the structure is 10000 W / m), 2 A comparison of the heat transfer performance of the leading and trailing edges of the channel under three conditions: model NN, model NY, and model YY, with Nu as the primary factor. t / Nu0 indicates. It can be seen that by employing the turbulent radiation assembly described in this invention in the trailing edge channel to provide an extended cold surface, convective heat transfer is enhanced by increasing fluid turbulence within the channel while simultaneously strengthening radiative heat transfer. This results in a significant improvement in the overall cooling performance of the channel at different Reynolds numbers.

[0062] When Re = 10000, the highest temperature of the trailing edge channel using the present invention is 933.77 K, and the average temperature is 814.19 K; while without considering surface radiation and using only the turbulence column, the highest temperature is 1288.50 K, and the average temperature is 852.76 K. In comparison, using the present invention reduces the highest temperature and average temperature by 27.53% and 4.52%, respectively, and the temperature distribution is more uniform.

[0063] When Re = 30000, the highest temperature of the trailing edge channel using the present invention is 874.78 K, and the average temperature is 770.64 K; while without considering surface radiation and using only turbulence columns, the highest temperature is 1010.04 K, and the average temperature is 783.45 K. In comparison, using the present invention reduces the highest temperature and average temperature by 13.39% and 1.64%, respectively, and the temperature distribution is more uniform.

[0064] The above embodiments demonstrate that the present invention can improve the overall cooling performance of the trailing edge channel at different Reynolds numbers, and can effectively improve the problem of huge differences in cooling performance in local areas of the channel, and reduce the thermal stress caused by temperature gradient.

[0065] (2) Second set of embodiments

[0066] To demonstrate that the present invention has a heat transfer self-enhancing effect (i.e., the enhancing effect of its cooling performance increases with the increase of the heat load), the heat flux density q on the surface of the structure is 10000~30000W / m. 2 Under the conditions described above, the cooling performance within the trailing edge channel of the present invention (model YY) was numerically simulated.

[0067] Figure 8 With Re = 10000 and q = 10000~30000 W / m 2 The relationship between the enhanced cooling performance of the trailing edge channel after adopting this invention and the change in heat flux density is shown. It can be seen that as the heat flux density increases, the overall Nusselt number of the channel increases compared to... Both the overall heat transfer performance evaluation index η and the heat transfer performance index η both increased, indicating that the present invention has a heat transfer self-enhancing effect. The enhancing effect on cooling performance increases with higher heat loads. For example, when q = 30000 W / m 2 When using the present invention, the highest channel temperature was 1196.85 K and the average temperature was 980.04 K; while without considering surface radiation and using only turbulence columns, the highest temperature was 2370.26 K and the average temperature was 1112.97 K. In comparison, using the present invention reduced the highest and average temperatures by 49.51% and 11.94%, respectively. This result is better than that under the same Re, q = 10000 W / m. 2 The enhanced cooling effect is significantly improved, further demonstrating the heat exchange self-enhancing effect of the present invention.

[0068] (3) Third set of embodiments

[0069] To verify the influence of the parameters of the turbulence column and turbulence radiation plate designed in this invention on the cooling effect, the trailing edge channel width W = 160 mm and the turbulence column diameter d = 12 mm. Figure 9With Re = 10000 and q = 10000 W / m 2 The cooling performance within the trailing edge channel was compared when the thickness of the radiating baffle plate was 2%, 4%, and 8% of the diameter of the baffle column, using the radiating baffle assembly (model YY) of this invention. It can be seen that as the thickness of the radiating baffle plate increases, the overall Nusselt number of the channel increases compared to... The overall heat transfer performance index η increases slightly, but decreases slightly. This is because when the thickness of the turbulent radiation plate increases slightly, the actual flow velocity in the channels on both sides increases, and the convective heat transfer is slightly enhanced; however, the flow resistance in the channels also increases accordingly, resulting in a slight decrease in the overall heat transfer performance index.

[0070] Therefore, although a slight increase in the thickness of the spoiler radiator within a certain range can appropriately increase the flow velocity on both sides, its thickness cannot be too large. Otherwise, it will reduce the effective working space in the separated channels on both sides, affecting the development of the vortex structure. At the same time, excessive thickness will increase the mass of the spoiler radiator and cause excessive flow resistance. However, if the thickness is too small, it may deform and be damaged during blade operation. Therefore, the thickness of the spoiler radiator should be as thin as possible while meeting strength requirements.

[0071] Those skilled in the art will readily understand that the above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A turbine blade trailing edge cooling structure, characterized in that, The system includes a turbulence-radiating assembly, which comprises a turbulence-radiating plate and turbulence-radiating columns, wherein: The radiating baffle is used to separate the leading edge and trailing edge surfaces of the blade trailing edge channel, making the trailing edge channel divided into two layers; the radiating baffle is used to pass through the radiating baffle, and the two end faces of the radiating baffle correspond to the leading edge and trailing edge surfaces of the blade trailing edge channel, respectively. The junction of the radiating baffle and the radiating baffle forms a central corner area, and the junctions of the radiating baffle with the leading edge and the trailing edge surfaces respectively form endwall corner areas. Diameter of the turbulence column With trailing edge channel width satisfy The thickness of the turbulence-radiating plate is 2% to 8% of the diameter of the turbulence column.

2. The turbine blade trailing edge cooling structure as described in claim 1, characterized in that, Flow spacing between two adjacent turbulence columns With diameter Between spanwise spacing between two adjacent spoiler columns With diameter Between .

3. The turbine blade trailing edge cooling structure as described in claim 1, characterized in that, The diameter of the turbulence column gradually decreases along the flow direction.

4. The turbine blade trailing edge cooling structure as described in claim 1, characterized in that, The thickness of the turbulence-radiating plate gradually decreases along the flow direction.

5. The turbine blade trailing edge cooling structure as described in claim 1, characterized in that, The turbulence-radiating plate is a corrugated plate or a flat plate with recesses on its surface; the turbulence-deflecting column has a circular or streamlined cross-sectional shape.

6. The turbine blade trailing edge cooling structure as described in claim 1, characterized in that, The cooling structure and trailing edge channel are both surface-treated to improve their emissivity.

7. The turbine blade trailing edge cooling structure as described in any one of claims 1-6, characterized in that, The turbulence radiating plate is located either in the center or offset from the trailing edge channel of the turbine blade.

8. A turbine blade, characterized in that, The turbine blade trailing edge cooling structure as described in any one of claims 1-7 is installed in the trailing edge channel of the turbine blade.

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