Cooling structure and airfoil

Abstract

A cooling structure and an airfoil, the cooling structure comprising a target wall for being impacted by a cooling gas, the cooling gas impacting a target point of the target wall; the cooling structure further comprising a side wall protruding from the target wall to form a cooling passage; the cooling structure further comprising a first spoiler structure, the first spoiler structure being arranged between the target point and the side wall, the first spoiler structure protruding from the target wall, the first spoiler structure having a slope surface for applying disturbance to the cooling gas after impacting the target point and lifting the cooling gas flow to the side wall, a high heat transfer coefficient region being formed by the slope surface of the first spoiler structure and the side wall, the cooling gas flow inside the cooling passage being optimized, the cooling efficiency being improved, and the heat load being effectively reduced.

Description

Technical Field

[0001] This invention relates to aircraft engine cooling design, specifically to a cooling structure and airfoil. Background Technology

[0002] The improvement in the performance indicators of aero engines has led to a continuous increase in the temperature at the combustion chamber exit, which poses a considerable technical challenge to the cooling design of its airfoil components. Summary of the Invention

[0003] The purpose of this invention is to provide a cooling structure and airfoil for improving the cooling effect of the airfoil.

[0004] In a first aspect, the present invention provides a cooling structure. According to an embodiment of the present invention, the cooling structure includes a target wall, the target wall being impacted by cooling gas, the cooling gas impacting a target point of the target wall;

[0005] The cooling structure also includes a sidewall that extends from the target wall to form a cooling channel;

[0006] The cooling structure further includes a first turbulence structure disposed between the target point and the side wall. The first turbulence structure protrudes from the target wall and has a slope to turbulently apply cooling air after impacting the target point and lift the cooling airflow toward the side wall.

[0007] In one or more embodiments, the number of target points is multiple, and the multiple target points are arranged along the extension direction of the cooling channel;

[0008] Multiple of the first turbulence structures are arranged along the extension direction of the cooling channel.

[0009] In one or more embodiments, a plurality of the first turbulence structures along the extension direction of the cooling channel are continuously integrated into a single unit.

[0010] In one or more embodiments, the plurality of the first turbulence structures in the extending direction of the cooling channel are spaced apart.

[0011] In one or more embodiments, the cooling structure further includes a firing wall located on the opposite side of the target wall and connecting the two side walls to form a closed cooling channel;

[0012] The firing wall has impact holes for cooling gas to flow into the cooling channel through the impact holes and impact the target wall;

[0013] The number of impact holes is multiple, and the multiple impact holes are arranged along the extension direction of the cooling channel.

[0014] In one or more embodiments, the target wall has gas film pores for cooling gas to flow out of the cooling channel through the gas film pores and form a gas film;

[0015] The number of air film holes is multiple, and the multiple air film holes are arranged along the extension direction of the cooling channel.

[0016] In one or more embodiments, the cooling structure further includes a second turbulence structure recessed from the target wall, the second turbulence structure having a concave surface for cooling gas to form a backflow therein;

[0017] The second turbulence structure is disposed between the target point and the first turbulence structure, such that the second turbulence structure is located upstream of the first turbulence structure. The cooling gas first flows through the second turbulence structure to form a backflow, and then flows through the first turbulence structure to be disturbed and lifted.

[0018] In one or more embodiments, the number of target points is multiple, and the multiple target points are arranged along the extension direction of the cooling channel;

[0019] Multiple first turbulence structures are arranged along the extension direction of the cooling channel;

[0020] Multiple second turbulence structures are arranged along the extension direction of the cooling channel.

[0021] In one or more embodiments, a plurality of the first turbulence structures along the extension direction of the cooling channel are continuously integrated into a single unit.

[0022] In one or more embodiments, the plurality of the first turbulence structures in the extending direction of the cooling channel are spaced apart.

[0023] In one or more embodiments, a plurality of the second turbulence structures along the extension direction of the cooling channel are continuously integrated into a single unit.

[0024] In one or more embodiments, the plurality of the second turbulence structures in the extending direction of the cooling channel are spaced apart.

[0025] In one or more embodiments, the cooling structure further includes a firing wall located on the opposite side of the target wall and connecting the two side walls to form a closed cooling channel;

[0026] The firing wall has impact holes for cooling gas to flow into the cooling channel through the impact holes and impact the target wall;

[0027] The number of impact holes is multiple, and the multiple impact holes are arranged along the extension direction of the cooling channel.

[0028] In one or more embodiments, the target wall has gas film pores for cooling gas to flow out of the cooling channel through the gas film pores and form a gas film;

[0029] The number of air film holes is multiple, and the multiple air film holes are arranged along the extension direction of the cooling channel.

[0030] Secondly, the present invention provides an airfoil, wherein, according to an embodiment of the present invention, the airfoil includes the aforementioned cooling structure, the cooling channel extends radially along the airfoil, and the targeting wall is part of the outer wall of the airfoil.

[0031] The embodiments of the present invention have at least one of the following beneficial effects:

[0032] 1. A high heat transfer coefficient region is formed on the slope and sidewall of the first turbulence structure to optimize the cooling airflow inside the cooling channel, improve cooling efficiency, and effectively reduce heat load.

[0033] 2. Compared with the traditional turbulence column connecting the outer and inner walls, the first turbulence structure has smaller thermal and centrifugal loads and better reliability.

[0034] 3. A high heat transfer coefficient region is formed on the concave surface of the second turbulence structure to optimize the cooling airflow inside the cooling channel, improve cooling efficiency, and effectively reduce heat load. Attached Figure Description

[0035] The above and other features, properties and advantages of the present invention will become more apparent from the following description taken in conjunction with the accompanying drawings and embodiments, wherein:

[0036] Figure 1 This is a three-dimensional schematic diagram of the cooling structure;

[0037] Figure 2 This is a schematic diagram of the cross-section of the cooling structure;

[0038] Figure 3 This is a schematic diagram of the cross-section of the cooling structure;

[0039] Figure 4 This is a schematic diagram of the cross-section of the cooling structure;

[0040] Figure 5 This is a partial schematic diagram of the cross-section of the cooling structure;

[0041] Figure 6 This is a partial schematic diagram of the cross-section of the cooling structure;

[0042] Figure 7 This is a partial schematic diagram of the cross-section of the cooling structure;

[0043] Figure 8This is a partial schematic diagram of the cross-section of the cooling structure;

[0044] Figure 9 This is a partial schematic diagram of the cross-section of the cooling structure;

[0045] Figure 10 This is a partial schematic diagram of the cross-section of the cooling structure;

[0046] Figure 11 This is a three-dimensional schematic diagram of the cooling structure;

[0047] Figure 12 This is a schematic diagram of the cross-section of the cooling structure;

[0048] Figure 13 This is a three-dimensional schematic diagram of the cooling structure;

[0049] Figure 14 This is a schematic diagram of the cross-section of the cooling structure;

[0050] Figure 15 This is a schematic diagram of the cross-section of the cooling structure;

[0051] Figure 16 This is a three-dimensional schematic diagram of the cooling structure;

[0052] Figure 17 This is a schematic diagram of the cross-section of the cooling structure;

[0053] Figure 18 This is a schematic diagram of the cross-section of the cooling structure;

[0054] Figure 19 This is a three-dimensional schematic diagram of the cooling structure;

[0055] Figure 20 This is a schematic diagram of the cross-section of the cooling structure;

[0056] Figure 21 This is a schematic diagram of the cross-section of the cooling structure;

[0057] Figure 22 This is a schematic diagram of the cross-section of the airfoil.

[0058] Figure label:

[0059] 1-Cooling structure;

[0060] 2-Cooling channel;

[0061] 3-Target wall;

[0062] 4-First sidewall;

[0063] 5-Second sidewall;

[0064] 6-Shooting wall;

[0065] 7-First turbulence structure;

[0066] 8-Impact hole;

[0067] 9-Air film pores;

[0068] 10 - Second turbulence structure;

[0069] 11-Airfoil;

[0070] 12-front edge;

[0071] 13-tail margin;

[0072] 14-Cavity;

[0073] 15-Target. Detailed Implementation

[0074] The present invention will be further described below with reference to specific embodiments and accompanying drawings. More details are set forth in the following description in order to provide a full understanding of the present invention. However, the present invention can obviously be implemented in many other ways different from those described herein. Those skilled in the art can make similar extensions and derivations based on actual application situations without departing from the spirit of the present invention. Therefore, the scope of protection of the present invention should not be limited by the content of this specific embodiment.

[0075] It should be noted that these and other accompanying drawings are merely examples and are not drawn to scale, and should not be construed as limiting the scope of protection of the present invention.

[0076] The terms “first”, “second”, etc., are used interchangeably to distinguish one feature from another and are not intended to indicate that each feature must be located in the position shown in the figure in each embodiment.

[0077] To ensure the reliable operation of high-pressure turbine blades under high-temperature conditions, advanced cooling technologies and design solutions are constantly being explored. In terms of cooling methods, internal cooling of turbine blades typically employs impingement cooling and enhanced convection cooling, while the external blade body relies primarily on film cooling for protection. Impingement cooling, with its high local heat transfer coefficient, effectively promotes heat exchange between the impinging jet and the turbine blade wall, making it a highly efficient cooling method. Building upon this, a double-wall cooling technology has been developed, combining internal impingement and enhanced convection cooling with film cooling to maximize turbine blade protection and achieve high cooling efficiency.

[0078] Arranging turbulence columns within a double-walled channel is a technique to enhance convection and promote heat conduction. The two ends of the turbulence column connect to the inner and outer walls of the double-walled channel, respectively. However, for turbine blades, especially turbine moving blades, the significant temperature difference between the inner and outer walls, and consequently the large temperature difference at the two ends of the turbulence column, subjects it to a substantial thermal load. Combined with centrifugal loads, this leads to strength and reliability issues for the turbulence column. Within the double-walled channel, the high-speed jet of cool gas impacts the impact point on the target surface, creating a locally high heat transfer coefficient region at the impact point. Extending outwards from the impact point, the heat transfer coefficient generally decreases. Therefore, the heat transfer process in areas some distance from the impact point is weakened, resulting in poorer cooling.

[0079] Example 1

[0080] Figures 1 to 3 A cooling structure 1 is shown, wherein, Figure 2 This is a cross-sectional view of cooling structure 1 perpendicular to the extending direction of cooling channel 2. Figure 3 This is a cross-sectional view of the cooling structure 1 parallel to the target wall 3.

[0081] like Figure 1 and Figure 2 As shown, the cooling structure 1 includes a target wall 3, a first sidewall 4, and a second sidewall 5. The first sidewall 4 and the second sidewall 5 are arranged opposite to each other and protrude from the target wall 3 to form a cooling channel 2. Figure 1 and Figure 2 In the illustrated embodiment, the first sidewall 4 and the second sidewall 5 are perpendicular to the target wall 3 and are parallel to each other. The extending direction of the cooling channel 2 is parallel to the first sidewall 4 and the second sidewall 5, and is shown in the Y direction in the figure. The lateral direction of the cooling channel 2 is perpendicular to the extending direction of the cooling channel 2 and perpendicular to the first sidewall 4 and the second sidewall 5, and is shown in the X direction in the figure. The lateral width of the cooling channel 2 is limited to 3-5 mm, and the "lateral width" is the distance between the first sidewall 4 and the second sidewall 5. For example, the lateral width of the cooling channel 2 is 3 mm. The angle between the first sidewall 4 and the second sidewall 5 and the target wall 3 is not limited to 90 degrees; in other embodiments, it can be other angles.

[0082] The target wall 3 is used to be impacted by cooling gas. The jet of cooling gas flows from between the first side wall 4 and the second side wall 5 to the target wall 3, impacting the target point 15 of the target wall 3. The target point 15 is a small area on the target wall 3 impacted by the jet of cooling gas. Figures 1 to 3 In the illustrated embodiment, the number of target points 15 is multiple, such as... Figure 3 As shown, multiple target points 15 are arranged at equal intervals along the extension direction of the cooling channel 2, forming a row, and the row of target points 15 is located on the center line of the target wall 3. The term "multiple" means two or more.

[0083] Continue to refer to Figure 1 and Figure 2 The cooling structure 1 also includes a first turbulence structure 7, which protrudes from the target wall 3. The first turbulence structure 7 has a slope for disturbing the cooling air after impacting the target point 15 and lifting the cooling airflow toward one of the first sidewall 4 and the second sidewall 5. A first turbulence structure 7 is located between the sidewall receiving the lifted cooling air and each target point 15. Figures 1 to 3 In the illustrated embodiment, both the first sidewall 4 and the second sidewall 5 receive the lifted cooling air. A first turbulence structure 7 is provided between each target point 15 in the aforementioned row of target points 15 and the first sidewall 4 laterally. Each target point 15 is also provided with a first turbulence structure 7 between it and the second sidewall 5 laterally. This forms two rows of first turbulence structures 7 evenly spaced along the extension direction of the cooling channel 2 on the target wall 3, symmetrical about the row of target points 15. Each first turbulence structure 7 is a semi-circular rib with a semi-circular cross-section, extending along the extension direction of the cooling channel 2. After the jet cooling air impacts the target point 15, it flows from the target point 15 along the wall surface of the target wall 3 towards the periphery of the target point 15, with a portion flowing laterally to form a crossflow. One crossflow flows towards the first turbulence structure 7 on one side of the target point 15. At the first turbulence structure 7, the windward arc-shaped surface of the semi-circular ribs provides a slope. The crossflow washes over this arc-shaped surface and is lifted by it, leaving the target wall 3 and flowing towards the first side wall 4, thus washing over the first side wall 4. Another crossflow flows towards the first turbulence structure 7 on the other side of the target point 15. At the first turbulence structure 7, the windward arc-shaped surface of the semi-circular ribs provides a slope. The crossflow washes over this arc-shaped surface and is lifted by it, leaving the target wall 3 and flowing towards the second side wall 5, thus washing over the second side wall 5. The aforementioned "turbulence" refers to the change in the flow state of the crossflow during the process of washing over the slope and being lifted. The crossflow impacts and convects heat transfer on the surface of the first turbulence structure 7, which intensifies the heat transfer process in the relevant area and significantly increases the high heat transfer coefficient.

[0084] The lateral distance between the target point 15 and the first turbulence structure 7 has an upper limit, so that the crossflow originating from the target point 15 has sufficient kinetic energy to scour the windward slope and lift it towards the corresponding sidewall when it reaches the slope. Simultaneously, the lateral distance between the target point 15 and the first turbulence structure 7 has a lower limit, so that the first turbulence structure 7 does not enter the target point 15 and its surrounding area, thus not reducing the cooling effect of that area. The lateral distance between the first turbulence structure 7 and the corresponding sidewall has an upper limit, so that the crossflow detaching from the slope carries sufficient kinetic energy to scour the corresponding sidewall.

[0085] The first turbulence-disrupting structure 7 is not limited to a semi-circular rib with a semi-circular cross-sectional shape. In one or more other embodiments, the first turbulence-disrupting structure 7 is a semi-elliptical rib with a semi-elliptical cross-sectional shape, the windward curved surface of the semi-elliptical rib providing a slope. In yet another embodiment, the first turbulence-disrupting structure 7 is as follows: Figure 5 The triangular rib shown has a triangular cross-section shape. Figure 5 In the middle, a triangular protrusion is positioned between the target point 15 and the second sidewall 5 laterally. The inclined surface of the triangular protrusion provides a slope, lifting the crossflow towards the second sidewall 5. Figure 5 The air film vent 9 is omitted from the display. In yet another embodiment, the first turbulence structure 7 is as follows: Figure 6 The trapezoidal rib shown has a trapezoidal cross-section shape. Figure 6 In the middle, trapezoidal ribs are positioned between the target point 15 and the second sidewall 5 laterally. The inclined surfaces of the trapezoidal ribs provide a slope, lifting the crossflow towards the second sidewall 5. Figure 6 The depiction of the air film vent 9 is omitted. In one or more other embodiments, the first turbulence structure 7 is a rib with a different cross-sectional shape, such that the rib has a windward slope that lifts the crossflow.

[0086] The aforementioned first spoiler structure 7 has a lateral width of 0.1 to 0.5 mm and a protrusion height of 0.1 to 0.3 mm. For example, the first spoiler structure 7 with a semi-circular protrusion has a lateral width of 0.2 mm and a protrusion height of 0.1 mm.

[0087] Continue to refer to Figure 1 and Figure 3 Multiple first turbulence structures 7 extending in the direction of the cooling channel 2 are continuously connected as a whole. In each column, each first turbulence structure 7 is connected to other adjacent first turbulence structures 7 in the direction of the extension of the cooling channel 2 to form a whole. That is, in the aforementioned column of target points 15, a first turbulence structure 7 is also provided between the gap between each pair of adjacent target points 15 and the transverse direction of the first sidewall 4, and the first turbulence structure 7 is connected end to end with the first turbulence structure 7 between the target point 15 and the transverse direction of the first sidewall 4. Similarly, a first turbulence structure 7 is also provided between each gap and the transverse direction of the second sidewall 5, and the first turbulence structure 7 is connected end to end with the first turbulence structure 7 between the target point 15 and the transverse direction of the second sidewall 5. The beneficial effect of this setting is that, in addition to the crossflow, the portion of the cooling airflow that originates from the target point 15, adheres to the wall of the target wall 3, and flows in other directions will scour the first turbulence structure 7 between the gap and the corresponding side wall. This portion of the cooling airflow is disturbed and lifted, flowing towards scour the corresponding side wall, thereby optimizing the cooling airflow inside the cooling channel, improving cooling efficiency, and effectively reducing the heat load.

[0088] Figure 4A cross-sectional view of the cooling structure 1 parallel to the target wall 3 is shown in another embodiment. In this embodiment, a plurality of first turbulence structures 7 in the extending direction of the cooling channel 2 are spaced apart. In each column, each first turbulence structure 7 is spaced apart from other first turbulence structures 7 adjacent in the extending direction of the cooling channel 2. That is, no first turbulence structure 7 is provided between the aforementioned gap and the lateral direction of the first sidewall 4 and the second sidewall 5.

[0089] Continue to refer to Figure 1 and Figure 2 For example, the cooling structure 1 further includes a firing wall 6 located opposite the target wall 3. The firing wall 6 is connected to a first side wall 4 and a second side wall 5 on its lateral sides, thereby forming a closed cooling channel 2. The firing wall 6 has impact holes 8 that penetrate the firing wall 6, having an inlet on the outer wall surface and an outlet on the inner wall surface. Cooling gas enters the impact hole 8 through the inlet and flows out in jet form at the outlet, entering the cooling channel 2 and impacting the target wall 3. The jet of cooling gas flowing out of one impact hole 8 impacts one target point 15 on the target wall 3. For example, there are multiple impact holes 8, which are arranged at equal intervals along the extension direction of the cooling channel 2 on the firing wall 6, forming a row. The spacing between two adjacent impact holes 8 is, for example, 4 mm. This row of impact holes 8 is located on the centerline of the firing wall 6, thereby forming the aforementioned row of target points 15 on the centerline of the target wall 3. The diameter of the impact hole 8 is 0.8 to 1.5 mm, for example, 1 mm. The ratio of the impact distance to the diameter of the impact hole 8 is (0.5~1):1, where the impact distance is the distance from the outlet of the impact hole 8 to the target point 15. To prevent the first turbulence structure 7 from entering the target point 15 and its surrounding area, the lateral distance between the centerline of the first turbulence structure 7 row and the centerline of the impact hole 8 row is greater than or equal to the diameter of the impact hole 8. For example, this lateral distance is 1 mm.

[0090] Continue to refer to Figures 1 to 3 For example, the target wall 3 has gas film holes 9 that penetrate the target wall 3, having an inlet located on the inner wall surface and an outlet located on the outer wall surface. Cooling gas in the cooling channel 2 enters the gas film holes 9 through the inlet and flows out through the outlet, forming a gas film on the outer wall surface of the target wall 3. For example, there are multiple gas film holes 9, which are arranged at equal intervals along the extension direction of the cooling channel 2 on the target wall 3, forming a row. The inlet of this row of gas film holes 9 is located on the centerline of the inner wall surface of the target wall 3. The distance between two adjacent gas film holes 9 in the extension direction of the cooling channel 2 is smaller than the distance between two adjacent impact holes 8 in the extension direction of the cooling channel 2. The distance between two gas film holes 9 is, for example, 2 mm. The central axis of the gas film hole 9 is parallel to the outer wall surface of the target wall 3. Figure 2The cross-section shown has an angle of 30 to 60 degrees, so that the direction of high-temperature gas flow between the gas film orifice 9 and the outer side of the target wall 3 is at an angle of 30 to 60 degrees. On the inner wall of the target wall 3, the inlet of the gas film orifice 9 and the target point 15 are staggered in the extension direction of the cooling channel 2 to prevent the jet cooling gas from directly entering the inlet of the gas film orifice 9 and flowing out of the cooling channel 2 through the gas film orifice 9, thereby reducing the cooling effect. The diameter of the gas film orifice 9 is 0.2 to 0.8 mm, exemplarily 0.6 mm.

[0091] During the cooling process of cooling structure 1, high heat transfer coefficient regions are formed at target point 15, the slope of the first turbulence structure 7, and the corresponding inner wall surface, thereby optimizing the cooling airflow inside cooling channel 2, improving cooling efficiency, and effectively reducing heat load. In addition, compared with the traditional turbulence column connecting the outer and inner walls, the first turbulence structure 7 bears less thermal and centrifugal loads and has better reliability.

[0092] Example 2

[0093] Example 2 uses the same component designations and some content as Example 1, with the same designations used to represent the same or similar components, and selectively omitting descriptions of the same technical content. For explanations of the omitted parts, please refer to Example 1; Example 2 will not repeat them.

[0094] In Embodiment 2, the cooling structure 1 does not include the first turbulence structure 7, but includes the second turbulence structure 10. Figure 7 A partial structure of the cooling structure 1 on the second sidewall 5 is shown. Figure 7 The display of air film pore 9 is omitted. Figure 7 In the illustrated embodiment, the first turbulence structure 7 is replaced by the second turbulence structure 10. Except for the difference between the second turbulence structure 10 and the first turbulence structure 7, the cooling structure 1 is completely the same as in Embodiment 1.

[0095] like Figure 7 As shown, the second turbulence structure 10 has a recessed structure from the target wall 3, that is, the second turbulence structure 10 has a concave surface for the cooling gas to form a recirculation therein. Each target point 15 in the aforementioned row of target points 15 has a second turbulence structure 10 between it and the first sidewall 4 laterally and between it and the second sidewall 5 laterally, thereby forming two rows of second turbulence structures 10 evenly spaced along the extension direction of the cooling channel 2 on the target wall 3. The two rows of second turbulence structures 10 are symmetrical about the row of target points 15. The second turbulence structure 10 between each target point 15 in the aforementioned row of target points 15 and the corresponding sidewall laterally is not limited to one, but can also be multiple, that is, two or more. Figure 8 In the illustrated embodiment, each target point 15 has two second flow-disrupting structures 10 laterally between it and the corresponding sidewall, thereby forming four rows of second flow-disrupting structures 10 on the target wall 3. Figure 8The display of air film pore 9 is omitted.

[0096] Each second turbulence structure 10 is a semi-circular groove with a semi-circular cross-section. The semi-circular groove extends along the cooling channel 2. After the jet cooling gas impacts the target point 15, it flows from the target point 15 along the wall of the target wall 3 towards the periphery of the target point 15. Part of it flows laterally, forming a crossflow. The crossflow flows towards the second turbulence structure 10 on the lateral side of the target point 15. At the second turbulence structure 10, part of the crossflow flows along the semi-circular concave surface of the semi-circular groove, thereby forming a backflow within the concave surface. This creates a high heat transfer coefficient region on the concave surface of the second turbulence structure 10, improving cooling efficiency and cooling effect.

[0097] The lateral distance between the target point 15 and the second turbulence structure 10 has an upper limit so that the crossflow originating from the target point 15 has sufficient kinetic energy to form a backflow when it reaches the concave surface. At the same time, the lateral distance between the target point 15 and the second turbulence structure 10 has a lower limit so that the second turbulence structure 10 does not enter the target point 15 and its surrounding original local high heat transfer coefficient region, and will not reduce the cooling effect of the local high heat transfer coefficient region.

[0098] The second flow-disrupting structure 10 is not limited to a semi-circular groove with a semi-circular cross-sectional shape. In one or more embodiments, the second flow-disrupting structure 10 is a semi-elliptical groove with a semi-elliptical cross-sectional shape and a semi-elliptical concave surface, causing the inflowing crossflow to form a backflow. In yet another embodiment, the second flow-disrupting structure 10 is a triangular groove with a triangular cross-sectional shape and a triangular concave surface, causing the inflowing crossflow to form a backflow. In yet another embodiment, the second flow-disrupting structure 10 is a trapezoidal groove with a trapezoidal cross-sectional shape and a trapezoidal concave surface, causing the inflowing crossflow to form a backflow. In yet another embodiment, the second flow-disrupting structure 10 is a groove with other cross-sectional shapes, the cross-sectional shape of which causes the groove to have a concave surface that causes the inflowing crossflow to form a backflow.

[0099] The aforementioned second turbulence structure 10 has a lateral width of 0.1 to 0.5 mm and a recess depth of 0.1 to 0.3 mm.

[0100] Multiple second turbulence structures 10 extending along the cooling channel 2 are continuously integrated into a single unit. In each column, each second turbulence structure 10 is connected to other adjacent second turbulence structures 10 along the extension direction of the cooling channel 2, forming a single unit. That is, in the aforementioned column of target points 15, a second turbulence structure 10 is also provided between the gap between each pair of adjacent target points 15 and the transverse direction of the first sidewall 4, and this second turbulence structure 10 is connected end-to-end with the second turbulence structure 10 between the target point 15 and the first sidewall 4. Similarly, a second turbulence structure 10 is also provided between each gap and the transverse direction of the second sidewall 5, and this second turbulence structure 10 is connected end-to-end with the second turbulence structure 10 between the target point 15 and the second sidewall 5. The beneficial effect of this arrangement is that, in addition to the crossflow, a portion of the cooling airflow originating from the target point 15, adhering to the wall of the target wall 3, and flowing in other directions will flow to the second turbulence structure 10 between the gap and the corresponding sidewall, forming a backflow, thereby improving cooling efficiency and cooling effect.

[0101] In one or more embodiments, the plurality of second turbulence structures 10 in the extending direction of the cooling channel 2 are spaced apart. In each column, each second turbulence structure 10 is spaced apart from other adjacent second turbulence structures 10 in the extending direction of the cooling channel 2. That is, no second turbulence structure 10 is provided between the aforementioned gap and the lateral direction of the first sidewall 4 and the second sidewall 5.

[0102] In order to prevent the second turbulence structure 10 from entering the target point 15 and the original local high heat transfer coefficient region around it, the lateral distance between the center line of the second turbulence structure 10 and the center line of the impact hole 8 is greater than or equal to the aperture of the impact hole 8. For example, the lateral distance is 1 mm.

[0103] Example 3

[0104] Example 3 uses the component designations and some content from Example 1, with the same designations used to represent the same or similar components, and selectively omitting descriptions of the same technical content. For explanations of the omitted parts, please refer to Example 1; Example 3 will not repeat them.

[0105] Based on the cooling structure 1 of Embodiment 1, the cooling structure 1 of Embodiment 3 further includes a second turbulence structure 10. The addition of the second turbulence structure 10 forms a composite turbulence structure with the first turbulence structure 7, further improving the cooling efficiency and cooling effect based on the cooling structure 1 of Embodiment 1. Figure 9 A partial structure of the cooling structure 1 on the second sidewall 5 is shown. Figure 9 The display of air film pore 9 is omitted. For example... Figure 9As shown, the second turbulence structure 10 is recessed from the target wall 3, and has a concave surface for the cooling gas to form a recirculation therein. A second turbulence structure 10 is provided between each of the two rows of first turbulence structures 7 and each target point 15 laterally, thus forming two rows of second turbulence structures 10 evenly spaced along the extension direction of the cooling channel 2 on the target wall 3. The two rows of second turbulence structures 10 are symmetrical about one row of target points 15. The second turbulence structure 10 between each target point 15 and the corresponding sidewall laterally is not limited to one, but can also be multiple, i.e., two or more. For example, each target point 15 has two second turbulence structures 10 between it and the corresponding sidewall laterally, thus forming four rows of second turbulence structures 10 on the target wall 3.

[0106] Each second turbulence structure 10 is a semi-circular groove with a semi-circular cross-section. The semi-circular groove extends along the cooling channel 2. After the jet cooling gas impacts the target point 15, it flows from the target point 15 along the wall of the target wall 3 towards the periphery of the target point 15, with a portion flowing laterally to form a crossflow. From the perspective of the crossflow, the second turbulence structure 10 is located upstream of the first turbulence structure 7. The crossflow first flows towards the second turbulence structure 10 on the lateral side of the target point 15. At the second turbulence structure 10, part of the crossflow flows along the semi-circular concave surface of the semi-circular groove, thus forming a backflow within the concave surface. This creates a high heat transfer coefficient region on the concave surface of the second turbulence structure 10, improving cooling efficiency and cooling effect.

[0107] The lateral distance between the target point 15 and the second turbulence structure 10 has an upper limit so that the crossflow originating from the target point 15 has sufficient kinetic energy to form a backflow when it reaches the concave surface. At the same time, the lateral distance between the target point 15 and the second turbulence structure 10 has a lower limit so that the second turbulence structure 10 does not enter the target point 15 and its surrounding original local high heat transfer coefficient region, and will not reduce the cooling effect of the local high heat transfer coefficient region.

[0108] The second flow-disrupting structure 10 is not limited to a semi-circular groove with a semi-circular cross-sectional shape. In one or more embodiments, the second flow-disrupting structure 10 is a semi-elliptical groove with a semi-elliptical cross-sectional shape and a semi-elliptical concave surface, causing the inflowing crossflow to form a backflow. In yet another embodiment, the second flow-disrupting structure 10 is a triangular groove with a triangular cross-sectional shape and a triangular concave surface, causing the inflowing crossflow to form a backflow. In yet another embodiment, the second flow-disrupting structure 10 is a trapezoidal groove with a trapezoidal cross-sectional shape and a trapezoidal concave surface, causing the inflowing crossflow to form a backflow. In yet another embodiment, the second flow-disrupting structure 10 is a groove with other cross-sectional shapes, the cross-sectional shape of which causes the groove to have a concave surface that causes the inflowing crossflow to form a backflow.

[0109] The aforementioned second turbulence structure 10 has a lateral width of 0.1 to 0.5 mm and a recess depth of 0.1 to 0.3 mm.

[0110] Multiple second turbulence structures 10 extending along the cooling channel 2 are continuously integrated into a single unit. In each column, each second turbulence structure 10 is connected to other adjacent second turbulence structures 10 along the extension direction of the cooling channel 2, forming a single unit. That is, in the aforementioned column of target points 15, a second turbulence structure 10 is also provided between the gap between each pair of adjacent target points 15 and the transverse direction of the first sidewall 4, and this second turbulence structure 10 is connected end-to-end with the second turbulence structure 10 between the target point 15 and the first sidewall 4. Similarly, a second turbulence structure 10 is also provided between each gap and the transverse direction of the second sidewall 5, and this second turbulence structure 10 is connected end-to-end with the second turbulence structure 10 between the target point 15 and the second sidewall 5. The beneficial effect of this arrangement is that, in addition to the crossflow, a portion of the cooling airflow originating from the target point 15, adhering to the wall of the target wall 3, and flowing in other directions will flow to the second turbulence structure 10 between the gap and the corresponding sidewall, forming a backflow, thereby improving cooling efficiency and cooling effect.

[0111] In one or more embodiments, the plurality of second turbulence structures 10 in the extending direction of the cooling channel 2 are spaced apart. In each column, each second turbulence structure 10 is spaced apart from other adjacent second turbulence structures 10 in the extending direction of the cooling channel 2. That is, no second turbulence structure 10 is provided between the aforementioned gap and the lateral direction of the first sidewall 4 and the second sidewall 5.

[0112] In order to prevent the second turbulence structure 10 from entering the target point 15 and the original local high heat transfer coefficient region around it, the lateral distance between the center line of the second turbulence structure 10 and the center line of the impact hole 8 is greater than or equal to the aperture of the impact hole 8. For example, the lateral distance is 1 mm.

[0113] Continue to refer to Figure 9 The crossflow then flows towards the first turbulence structure 7, which is located between the second turbulence structure 10 and the corresponding sidewall. At the first turbulence structure 7, the crossflow scours the windward slope of the first turbulence structure 7 and is lifted by the slope, flowing towards the corresponding sidewall and thus scouring the corresponding sidewall. Figure 9 In the illustrated embodiment, the first turbulence structure 7 and the second turbulence structure 10 are spaced apart laterally and are separated laterally by the inner wall surface of a target wall 3. Figure 10 In another embodiment shown, the first turbulence structure 7 and the second turbulence structure 10 are connected laterally and are not separated by the inner wall surface of the target wall 3. Figure 10 The display of air film pore 9 is omitted.

[0114] Example 4

[0115] Figure 11 and Figure 12 The cooling structure 1 of Embodiment 4 is shown, wherein Figure 12 This is a cross-sectional view of the cooling structure 1 parallel to the target wall 3. Embodiment 4 uses the component designations and some content from Embodiment 1, where the same designations are used to represent the same or similar components, and descriptions of identical technical content are selectively omitted. For explanations of the omitted parts, please refer to Embodiment 1; Embodiment 4 will not repeat them.

[0116] like Figure 11 and Figure 12 As shown, the multiple first turbulence structures 7 in the extending direction of the cooling channel 2 are spaced apart. In each column, each first turbulence structure 7 is spaced apart from other first turbulence structures 7 adjacent in the extending direction of the cooling channel 2. That is, no first turbulence structure 7 is provided between the aforementioned gap and the lateral direction of the first sidewall 4 and the second sidewall 5. The length of each first turbulence structure 7 in the extending direction of the cooling channel 2 is 1.5 mm.

[0117] Continue to refer to Figure 11 For example, the target wall 3 is provided with two rows of film-forming holes 9. In each row of first turbulence structures 7, the film-forming holes 9 are disposed between two adjacent first turbulence structures 7 in the extending direction of the cooling channel 2, forming a composite row in which the film-forming holes 9 and the first turbulence structures 7 are alternately arranged in the extending direction of the cooling channel 2. In this composite row, the film-forming holes 9 are arranged at equal intervals along the extending direction of the cooling channel 2. The aperture of the film-forming holes 9 is exemplarily 0.6 mm. The central axis of the film-forming holes 9 has an angle of 30 to 60 degrees with the outer wall surface of the target wall 3, so that the direction of high-temperature gas flow outside the outer wall surface of the film-forming holes 9 has an angle of 30 to 60 degrees.

[0118] In one or more embodiments, analogous to Embodiment 2, the first turbulence structure 7 is replaced by the second turbulence structure 10. In yet another embodiment, analogous to Embodiment 3, the second turbulence structure 10 is added to form a composite turbulence structure with the first turbulence structure 7.

[0119] Example 5

[0120] Figures 13 to 15 The cooling structure 1 of Embodiment 5 is shown, wherein, Figure 14 This is a cross-sectional view of the cooling structure 1 parallel to the target wall 3. Figure 15 This is a cross-sectional view of the cooling structure 1 in the direction perpendicular to the extension of the cooling channel 2. Embodiment 5 uses the component designations and some content of Embodiment 1, where the same designations are used to represent the same or similar components, and descriptions of the same technical content are selectively omitted. For explanations of the omitted parts, please refer to Embodiment 1; Embodiment 5 will not repeat them.

[0121] In Example 5, the lateral width of cooling channel 2 is 3 mm. Figures 13 to 15 As shown, there are multiple target points 15, which are arranged at equal intervals along the extension direction of the cooling channel 2 to form a row. This row of target points 15 is located transversely between the center line of the first sidewall 4 and the center line of the target wall 3. For example, the transverse distance between this row of target points 15 and the first sidewall 4 is 1 mm. There are also multiple impact holes 8, which are arranged at equal intervals along the extension direction of the cooling channel 2 on the firing wall 6 to form a row. This row of impact holes 8 is located transversely between the center line of the first sidewall 4 and the center line of the firing wall 6. For example, the transverse distance between this row of impact holes 8 and the first sidewall 4 is 1 mm, thereby forming the aforementioned row of target points 15 on the target wall 3. The diameter of the impact hole 8 is, for example, 1 mm.

[0122] Continue to refer to Figures 13 to 15 Each of the aforementioned target points 15 in the row of target points 15 is provided with a first turbulence structure 7 in the lateral direction between it and the second sidewall 5, thereby forming a row of first turbulence structures 7 evenly spaced along the extension direction of the cooling channel 2 on the target wall 3. The crossflow formed after the jet cooling gas impacts the target point 15 scours the slope of the first turbulence structure 7, disturbs and lifts it, and scours the second sidewall 5 as it flows towards the air film hole 9. In order to prevent the first turbulence structure 7 from entering the target point 15 and the original local high heat transfer coefficient area around it, the lateral distance between the row of first turbulence structures 7 and the center line of the row of impact holes 8 is greater than or equal to the aperture of the impact hole 8. For example, this lateral distance is 1 mm.

[0123] Continue to refer to Figures 13 to 15 The number of air film holes 9 is multiple, and the multiple air film holes 9 are arranged at equal intervals along the extension direction of the cooling channel 2 on the target wall 3 to form a row. The entrance of the row of air film holes 9 is located between the first turbulence structure 7 and the second sidewall 5. The diameter of the air film holes 9 is exemplarily 0.6 mm, and the number of air film holes 9 is 1.5-2.5 times the number of impact holes 8.

[0124] In one or more embodiments, the number of air film holes 9 is multiple. In the aforementioned first turbulence structure 7, the air film holes 9 are disposed between two adjacent first turbulence structures 7 in the extending direction of the cooling channel 2, forming a composite column in which the air film holes 9 and the first turbulence structures 7 are alternately arranged in the extending direction of the cooling channel 2. In this composite column, the air film holes 9 are arranged at equal intervals along the extending direction of the cooling channel 2.

[0125] In one or more embodiments, the row of impact holes 8 is located transversely between the center line of the second sidewall 5 and the center line of the firing wall 6, and the row of target points 15 is located transversely between the center line of the second sidewall 5 and the center line of the target wall 3. Each target point 15 in the row of target points 15 is provided with a first turbulence structure 7 between the transverse direction of the first sidewall 4, which is used to lift the crossflow direction to scour the first sidewall 4. The inlet of a row of air film holes 9 is located between the row of first turbulence structures 7 and the transverse direction of the first sidewall 4.

[0126] In one or more embodiments, analogous to Embodiment 2, the first turbulence structure 7 is replaced by the second turbulence structure 10. In yet another embodiment, analogous to Embodiment 3, the second turbulence structure 10 is added to form a composite turbulence structure with the first turbulence structure 7.

[0127] Example 6

[0128] Figures 16 to 18 The cooling structure 1 of Embodiment 6 is shown, wherein, Figure 17 This is a cross-sectional view of cooling structure 1 perpendicular to the extending direction of cooling channel 2. Figure 18 This is a cross-sectional view of the cooling structure 1 parallel to the target wall 3. Embodiment Six uses the component designations and some content from Embodiment One, employing the same designations to represent the same or similar components, and selectively omitting descriptions of identical technical content. For explanations of the omitted parts, please refer to Embodiment One; Embodiment Six will not repeat them.

[0129] like Figures 16 to 18 As shown, the cooling channel 2 has a relatively large lateral width of 6 to 8 mm. For example, the lateral width of the cooling channel 2 is 6 mm.

[0130] exist Figures 16 to 18 In the illustrated embodiment, there are multiple target points 15, which are arranged at equal intervals along the extension direction of the cooling channel 2 to form multiple columns. "Multiple" refers to two or more, exemplarily two columns. The two columns of target points 15 are located on both sides of the center line of the target wall 3 and are symmetrical about the center line of the target wall 3. For example, the lateral distance between each column of target points 15 and the center line of the target wall 3 is 1 mm.

[0131] A first turbulence structure 7 is set at the lateral midpoint between two adjacent target points 15, as shown in the reference. Figures 16 to 18In the aforementioned two columns of target points 15, a first flow-disrupting structure 7 is provided in the lateral middle of every two target points 15. Furthermore, in the aforementioned two columns of target points 15, each target point 15 is also provided with a first flow-disrupting structure 7 in the lateral direction between it and its adjacent sidewall. This results in three columns of first flow-disrupting structures 7 evenly spaced along the extension direction of the cooling channel 2 on the target wall 3. One column of first flow-disrupting structures 7 is located at the center line of the target wall 3, and the other two columns are symmetrical about the center line of the target wall 3. For example, the lateral distance between the two columns of first flow-disrupting structures 7 and the center line of the target wall 3 is 2 mm. One column of first flow-disrupting structures 7 is provided between the sidewall and the adjacent column of target points 15 in the lateral direction, and two columns of first flow-disrupting structures 7 are provided between the sidewall and the column of target points 15 that are far away in the lateral direction.

[0132] The first turbulence structure 7, located at the center line of the target wall 3, is used to turbulent the cooling air and lift the cooling airflow toward the first side wall 4 and the second side wall 5. (Continue referring to...) Figure 17 and Figure 18 The crossflow originating from target point 15 on the left side of the diagram flows to the right, scouring the windward slope on the left side of the first turbulence structure 7 in the middle. It is disturbed and lifted, leaving the target wall 3 and flowing towards the second side wall 5, thus scouring the second side wall 5. Similarly, the crossflow originating from target point 15 on the right side of the diagram flows to the left, scouring the windward slope on the right side of the first turbulence structure 7 in the middle. It is disturbed and lifted, leaving the target wall 3 and flowing towards the first side wall 4, thus scouring the first side wall 4. The first turbulence structure 7 in this column has two windward slopes in the transverse direction, exemplarily, semi-circular ribs with a semi-circular cross-sectional shape.

[0133] Two rows of first turbulence structures 7, located on either side of the centerline of the target wall 3, are used to turbulent the cooling air and lift the cooling airflow toward one of the first sidewall 4 and the second sidewall 5. (Continue referring to...) Figure 17 and Figure 18 The crossflow originating from target point 15 on the left side of the figure flows to the left, scouring the windward slope of the first turbulence structure 7 on the left side of the figure. It is disturbed and lifted, leaving the wall of the target wall 3, and flows to the first side wall 4, thus scouring the first side wall 4. The crossflow originating from target point 15 on the right side of the figure flows to the right, scouring the windward slope of the first turbulence structure 7 on the right side of the figure. It is disturbed and lifted, leaving the wall of the target wall 3, and flows to the second side wall 5, thus scouring the second side wall 5.

[0134] Continue to refer to Figure 16 and Figure 18In the first perturbation structure 7 located on the center line of the target wall 3, each first perturbation structure 7 is spaced apart from other adjacent first perturbation structures 7 in the extending direction of the cooling channel 2. In the two columns of first perturbation structures 7 located on both sides of the center line of the target wall 3, each first perturbation structure 7 is connected to other adjacent first perturbation structures 7 in the extending direction of the cooling channel 2, forming a whole.

[0135] Continue to refer to Figure 16 and Figure 17 Multiple impact holes 8 are arranged at equal intervals along the extension direction of the cooling channel 2 on the firing wall 6, forming two rows. The spacing between two adjacent impact holes 8 in the extension direction of the cooling channel 2 is 4 mm for example. The two rows of impact holes 8 are located on both sides of the center line of the firing wall 6 and are symmetrical about the center line of the firing wall 6. The ratio of the lateral spacing of two adjacent rows of impact holes 8 to the diameter of the impact hole 8 is (2-4):1. For example, the lateral distance between each row of impact holes 8 and the center line of the firing wall 6 is 1 mm, thereby forming the aforementioned two rows of target points 15 on the target wall 3. The diameter of the impact hole 8 is 1 mm for example.

[0136] Continue to refer to Figures 16 to 18 For example, the target wall 3 is provided with three rows of air film holes 9. One row of air film holes 9 is located on the centerline of the target wall 3, forming a composite row with a row of first turbulence structures 7 located on the centerline of the target wall 3. In this composite row, the air film holes 9 are positioned between two adjacent first turbulence structures 7 in the extending direction of the cooling channel 2, and the air film holes 9 and the first turbulence structures 7 are alternately arranged in the extending direction of the cooling channel 2, with the air film holes 9 arranged at equal intervals along the extending direction of the cooling channel 2. Another row of air film holes 9 is located between the first sidewall 4 and the transverse left row of first turbulence structures 7 in the figure, with multiple air film holes 9 arranged at equal intervals in the extending direction of the cooling channel 2. A third row of air film holes 9 is located between the second sidewall 5 and the transverse right row of first turbulence structures 7 in the figure, with multiple air film holes 9 arranged at equal intervals in the extending direction of the cooling channel 2.

[0137] In one or more embodiments, analogous to Embodiment 2, the first turbulence structure 7 is replaced by the second turbulence structure 10. In yet another embodiment, analogous to Embodiment 3, the second turbulence structure 10 is added to form a composite turbulence structure with the first turbulence structure 7.

[0138] Example 7

[0139] Figures 19 to 21 The cooling structure 1 of Embodiment 7 is shown, wherein, Figure 20 This is a cross-sectional view of cooling structure 1 perpendicular to the extending direction of cooling channel 2. Figure 21This is a cross-sectional view of the cooling structure 1 parallel to the target wall 3. Embodiment Seven uses the component designations and some content from Embodiment One, employing the same designations to represent the same or similar components, and selectively omitting descriptions of identical technical content. For explanations of the omitted parts, please refer to Embodiment One; Embodiment Seven will not repeat them.

[0140] like Figures 19 to 21 As shown, the cooling channel 2 has a relatively large lateral width of 6 to 8 mm. For example, the lateral width of the cooling channel 2 is 7 mm.

[0141] exist Figures 19 to 21 In the illustrated embodiment, there are multiple target points 15, which are arranged at equal intervals along the extension direction of the cooling channel 2 to form multiple columns. "Multiple" refers to two or more, exemplarily two columns. The two columns of target points 15 are located on both sides of the center line of the target wall 3 and are symmetrical about the center line of the target wall 3. For example, the lateral distance between each column of target points 15 and the center line of the target wall 3 is 1.5 mm.

[0142] A first turbulence structure 7 is set at the lateral midpoint between two adjacent target points 15, as shown in the reference. Figures 19 to 21 In the aforementioned two rows of target points 15, two first flow-disrupting structures 7 are arranged laterally between every two target points 15. Furthermore, in the aforementioned two rows of target points 15, each target point 15 is also laterally positioned between itself and its adjacent sidewall, thus forming four rows of first flow-disrupting structures 7 evenly spaced along the extension direction of the cooling channel 2 on the target wall 3. Two rows of first flow-disrupting structures 7 are laterally close to the centerline of the target wall 3, located between the two rows of target points 15, and are symmetrical about the centerline of the target wall 3. The lateral distance between these two rows of first flow-disrupting structures 7 and the centerline of the target wall 3 is, for example, 0.5 mm. The other two rows of first flow-disrupting structures 7 are laterally away from the centerline of the target wall 3, located between the corresponding sidewall and the lateral distance of an adjacent row of target points 15. These two rows of first flow-disrupting structures 7 are also symmetrical about the centerline of the target wall 3, and the lateral distance between these two rows of first flow-disrupting structures 7 and the centerline of the target wall 3 is, for example, 2.5 mm. There is a first perturbation structure 7 between the sidewall and the adjacent target 15 columns laterally, and three first perturbation structures 7 between the sidewall and the distant target 15 columns laterally.

[0143] Two rows of first turbulence structures 7, located near the centerline of the target wall 3, are used to disturb the cooling air and lift the cooling airflow toward one of the first sidewall 4 and the second sidewall 5. (Continue referring to...) Figure 20 and Figure 21The crossflow originating from target point 15 on the left side of the diagram flows to the right, scouring the windward slope of the first turbulence structure 7 on the left side of the center line of the target wall 3. It is disturbed and lifted, leaving the wall surface of the target wall 3 and flowing towards the second side wall 5, thereby scouring the second side wall 5. The crossflow originating from target point 15 on the right side of the diagram flows to the left, scouring the windward slope of the first turbulence structure 7 on the right side of the center line of the target wall 3. It is disturbed and lifted, leaving the wall surface of the target wall 3 and flowing towards the first side wall 4, thereby scouring the first side wall 4.

[0144] Two rows of first turbulence structures 7, located away from the centerline of the target wall 3, are used to turbulent the cooling air and lift the cooling airflow toward one of the first sidewall 4 and the second sidewall 5. (Continue referring to...) Figure 20 and Figure 21 The crossflow originating from target point 15 on the left side of the figure flows to the left, scouring the windward slope of the first turbulence structure 7 between the first sidewall 4 and target point 15. It is disturbed and lifted, leaving the wall surface of the target wall 3, and flows to the first sidewall 4, thus scouring the first sidewall 4. The crossflow originating from target point 15 on the right side of the figure flows to the right, scouring the windward slope of the first turbulence structure 7 between the second sidewall 5 and target point 15. It is disturbed and lifted, leaving the wall surface of the target wall 3, and flows to the second sidewall 5, thus scouring the second sidewall 5.

[0145] Continue to refer to Figure 19 and Figure 21 In all four columns of the aforementioned first turbulence structure 7, each first turbulence structure 7 is connected to other first turbulence structures 7 adjacent to each other in the extension direction of the cooling channel 2, forming a whole.

[0146] Continue to refer to Figure 19 and Figure 20 Multiple impact holes 8 are arranged at equal intervals along the extension direction of the cooling channel 2 on the firing wall 6, forming two rows. The spacing between two adjacent impact holes 8 in the extension direction of the cooling channel 2 is 4 mm for example. The two rows of impact holes 8 are located on both sides of the center line of the firing wall 6 and are symmetrical about the center line of the firing wall 6. The ratio of the lateral spacing of two adjacent rows of impact holes 8 to the diameter of the impact hole 8 is (2-4):1. For example, the lateral distance between each row of impact holes 8 and the center line of the firing wall 6 is 1.5 mm, thereby forming the aforementioned two rows of target points 15 on the target wall 3. The diameter of the impact hole 8 is 1 mm for example.

[0147] Continue to refer to Figures 19 to 21For example, the target wall 3 is provided with three rows of air film holes 9. One row of air film holes 9 is located at the centerline of the target wall 3, and the plurality of air film holes 9 therein are arranged at equal intervals along the extending direction of the cooling channel 2. Another row of air film holes 9 is located between the first sidewall 4 and the leftmost row of the first turbulence-disrupting structures 7 in the figure, and the plurality of air film holes 9 therein are arranged at equal intervals along the extending direction of the cooling channel 2. A third row of air film holes 9 is located between the second sidewall 5 and the rightmost row of the first turbulence-disrupting structures 7 in the figure, and the plurality of air film holes 9 therein are arranged at equal intervals along the extending direction of the cooling channel 2.

[0148] In one or more embodiments, analogous to Embodiment 2, the first turbulence structure 7 is replaced by the second turbulence structure 10. In yet another embodiment, analogous to Embodiment 3, the second turbulence structure 10 is added to form a composite turbulence structure with the first turbulence structure 7.

[0149] Example 8

[0150] Example 8 uses the same component designations and some content as the previous examples, with the same designations used to represent the same or similar components, and selectively omitting descriptions of the same technical content. For explanations of the omitted parts, please refer to the previous examples; Example 8 will not repeat them.

[0151] Figure 22 The airfoil 11 of embodiment eight is shown. The airfoil 11 in the figure is exemplarily a high-pressure turbine blade of an aircraft engine, having a root and a tip, extending radially from the root to the tip, and also having a leading edge 12 and a trailing edge 13. The chord direction of the airfoil 11 points to the central axis connecting the leading edge 12 and the trailing edge 13. Figure 22 This is a cross-sectional view of the airfoil 11 perpendicular to the radial direction.

[0152] like Figure 22 As shown, the airfoil 11 includes the aforementioned cooling structure 1 for cooling the airfoil 11. Figure 22 In the illustrated embodiment, there are multiple cooling structures 1. Cooling channels 2 extend radially along the airfoil 11, meaning the extension direction of the cooling channels 2 is consistent with the radial direction of the airfoil 11, and the transverse direction of the cooling channels 2 is generally consistent with the chordal direction of the airfoil 11. The target wall 3 of the cooling structure 1 becomes part of the outer wall of the airfoil 11, and the target walls 3 of multiple cooling structures 1 successively form the outer wall of the airfoil 11. The air film hole 9 has an angle of 30 to 60 degrees with the flow direction of the high-temperature gas outside the outer wall of the airfoil 11. The firing walls 6 of multiple cooling structures 1 successively form the sidewalls of the cavity 14, which is used for cooling gas flow. The impact holes 8 on the firing walls 6 connect to the cavity 14 of the airfoil 11, and the cooling gas in the cavity 14 enters the cooling channel 2 through the impact holes 8. In two adjacent cooling structures 1, the first sidewall 4 of one cooling structure 1 merges with the second sidewall 5 of the other cooling structure 1.

[0153] Although the present invention has been disclosed above with reference to embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present invention.

Claims

1. A cooling structure, characterized in that, The cooling structure includes a target wall, which is used to be impacted by cooling gas, and the cooling gas impacts the target point of the target wall. The cooling structure also includes a sidewall that extends from the target wall to form a cooling channel; The cooling structure further includes a first turbulence structure, which is disposed between the target point and the side wall. The first turbulence structure protrudes from the target wall and has a slope to turbulently apply cooling air after impacting the target point and lift the cooling airflow toward the side wall. The cooling structure further includes a second turbulence structure, which is recessed from the target wall and has a concave surface for the cooling gas to form a backflow therein; The second turbulence structure is disposed between the target point and the first turbulence structure, such that the second turbulence structure is located upstream of the first turbulence structure. The cooling gas first flows through the second turbulence structure to form a backflow, and then flows through the first turbulence structure to be disturbed and lifted.

2. The cooling structure according to claim 1, characterized in that, The number of target points is multiple, and the multiple target points are arranged along the extension direction of the cooling channel; Multiple of the first turbulence structures are arranged along the extension direction of the cooling channel.

3. The cooling structure according to claim 2, characterized in that, The multiple first turbulence structures in the extension direction of the cooling channel are continuously integrated into a whole.

4. The cooling structure according to claim 2, characterized in that, The plurality of the first turbulence structures in the extending direction of the cooling channel are spaced apart.

5. The cooling structure according to claim 2, characterized in that, The cooling structure also includes a firing wall located on the opposite side of the target wall, and the two side walls are connected to form a closed cooling channel; The firing wall has impact holes for cooling gas to flow into the cooling channel through the impact holes and impact the target wall; The number of impact holes is multiple, and the multiple impact holes are arranged along the extension direction of the cooling channel.

6. The cooling structure according to claim 2, characterized in that, The target wall has gas film pores for cooling gas to flow out of the cooling channel through the gas film pores and form a gas film; The number of air film holes is multiple, and the multiple air film holes are arranged along the extension direction of the cooling channel.

7. The cooling structure according to claim 1, characterized in that, The number of target points is multiple, and the multiple target points are arranged along the extension direction of the cooling channel; Multiple first turbulence structures are arranged along the extension direction of the cooling channel; Multiple second turbulence structures are arranged along the extension direction of the cooling channel.

8. The cooling structure according to claim 7, characterized in that, The multiple first turbulence structures in the extension direction of the cooling channel are continuously integrated into a whole.

9. The cooling structure according to claim 7, characterized in that, The plurality of the first turbulence structures in the extending direction of the cooling channel are spaced apart.

10. The cooling structure according to claim 7, characterized in that, The multiple second turbulence structures in the extension direction of the cooling channel are continuously integrated into a whole.

11. The cooling structure according to claim 7, characterized in that, The plurality of the second turbulence structures in the extending direction of the cooling channel are spaced apart.

12. The cooling structure according to claim 7, characterized in that, The cooling structure also includes a firing wall located on the opposite side of the target wall, and the two side walls are connected to form a closed cooling channel; The firing wall has impact holes for cooling gas to flow into the cooling channel through the impact holes and impact the target wall; The number of impact holes is multiple, and the multiple impact holes are arranged along the extension direction of the cooling channel.

13. The cooling structure according to claim 7, characterized in that, The target wall has gas film pores for cooling gas to flow out of the cooling channel through the gas film pores and form a gas film; The number of air film holes is multiple, and the multiple air film holes are arranged along the extension direction of the cooling channel.

14. An airfoil component, characterized in that, The airfoil includes a cooling structure as described in any one of claims 1 to 13, the cooling channel extending radially along the airfoil, and the targeting wall being part of the outer wall of the airfoil.

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