Blade, blade design method, and turbomachine

Abstract

The present application relates to the technical field of turbine blade, disclose a kind of blade, blade design method and turbine, containing chamber and spoiler assembly, chamber is located in the inside of the blade, the blade has oppositely arranged suction side and pressure side, spoiler assembly is located on the inner wall of the chamber, and it includes multiple spoiler columns, which are spaced along the height direction of the blade, at least one of the suction side and the pressure side is provided with the spoiler assembly. Through this design, local high temperature area can be formed by concentrated cooling, the uniformity of wall temperature distribution can be improved, the thermal stress can be reduced, the blade life can be prolonged, and the long-term effective and stable operation can be ensured.

Description

Technical Field

[0001] This invention relates to the field of turbine blade technology, specifically to a blade, a blade design method, and a turbine. Background Technology

[0002] A regularly arranged columnar array within the blade cavity significantly enhances the convective heat transfer intensity between the airflow and the blade's inner wall by disrupting the flow boundary layer, enhancing turbulence, and increasing the heat transfer area. In related technologies, the cooling capacity of conventional, compact turbulence columns inside turbine blades is approaching its limit. Further reducing the spacing or increasing the number of these columns drastically increases flow resistance, leading to diminishing marginal benefits for heat transfer enhancement. This is especially problematic under conditions of low cooling air volume, where insufficient cooling may occur. Summary of the Invention

[0003] This invention provides a blade, a blade design method, and a turbine to solve or improve the problem of localized overheating of turbine blades in a compact space.

[0004] In a first aspect, the present invention provides a blade, comprising: A chamber is located inside the blade, and the blade has a back side and a base side arranged opposite to each other for the flow of cooling fluid. A turbulence-disrupting assembly is disposed on the inner wall of the chamber and includes a plurality of turbulence-disrupting columns spaced apart along the height direction of the blade. The two ends of the turbulence-disrupting columns are respectively connected to the opposite inner wall surfaces of the chamber. The turbulence-disrupting assembly is disposed on at least one of the inner walls of the chamber near the blade back side and the blade base side. The turbulence column is provided with a flow channel for cooling fluid to flow through. The flow channel has a first end and a second end. The first end of the flow channel penetrates the side wall of the turbulence column near the leading edge of the blade, and the second end of the flow channel penetrates the side wall of the turbulence column near the trailing edge of the blade and is inclined towards the back side of the blade or the blade base side, so as to guide the cooling fluid to the side wall of the chamber near the back side of the blade or the blade base side.

[0005] In one optional embodiment, the number of the flow-dispersing components is multiple, and the multiple flow-dispersing components are arranged at intervals along the chord direction. In the chord direction, the flow-dispersing columns of two adjacent flow-dispersing components are staggered from each other, and the cooling fluid forms an alternating flow path when it flows through the flow-dispersing components.

[0006] In one alternative implementation, the flow channel includes: The first perforation section penetrates the side wall of the turbulence column near the leading edge of the blade, and the cooling airflow enters through the side wall of the first perforation section near the leading edge of the blade; The second hole section communicates with the first hole section and penetrates the side wall of the turbulence column near the trailing edge of the blade. The end of the second hole section away from the first hole section is inclined toward the back side of the blade or the blade base side. The cooling fluid impacts the corresponding side wall of the chamber through the second hole section.

[0007] In one alternative embodiment, the flow channel includes at least two second orifice sections, wherein the first orifice section is connected to each of the second orifice sections inside the turbulence column, wherein a portion of the second orifice sections are inclined toward the blade back side and another portion of the second orifice sections are inclined toward the blade base side.

[0008] In one optional embodiment, the angle between the second hole segment inclined toward the back of the leaf and the first hole segment is greater than or less than the angle between the second hole segment inclined toward the leaf basin and the first hole segment, and the two second hole segments form an asymmetrical impact arrangement to adapt to the different heat load distributions on the back of the leaf and the leaf basin.

[0009] In one alternative embodiment, the axis of the first hole segment is perpendicular to the axis of the turbulence column; And / or, the height of the turbulence column is 0.3mm~0.6mm; And / or, the turbulence-disrupting column is a cylindrical structure, and the diameter of the turbulence-disrupting column is 0.3mm~1.0mm; And / or, at least one of the first hole segment and the second hole segment has a diameter of 0.2 mm to 0.4 mm; And / or, the included angle between the first hole segment and the second hole segment is 10°~30°.

[0010] In one optional embodiment, the number of the turbulence components is multiple, and at least some of the turbulence components are disposed in the portion of the chamber near the trailing edge of the blade. The turbulence columns in this portion of the turbulence components are arranged at intervals along the height direction of the blade, and the two ends of the turbulence columns of the turbulence components are respectively connected to the two side walls of the chamber near the back side of the blade and the blade base side, forming a turbulence array in the region of the trailing edge of the blade. And / or, the blade further includes an inner frame, at least a portion of which is disposed in the chamber near the leading edge of the blade and has a gap with the inner wall of the chamber to form a cooling flow path around the inner frame, the turbulence assembly is disposed on the outer wall of the inner frame near the back side of the blade or the blade base side, and the turbulence columns of the turbulence assembly are all connected to the outer wall of the inner frame.

[0011] Secondly, the present invention also provides a blade design method for a blade as described above, the method comprising: Calculate the first heat flux density on the leaf apex side and the second heat flux density on the leaf underside. When the first heat flux density is greater than the second heat flux density, the second end of the flow channel is tilted toward the blade holder side, and the cooling fluid is guided along the second end of the flow channel to the inner wall surface of the blade holder side with a higher heat load. When the first heat flux density is less than the second heat flux density, the second end of the flow channel is tilted toward the blade back side, and the cooling fluid is guided along the second end of the flow channel to the inner wall surface of the blade back side with a higher heat load. When the difference between the first heat flux density and the second heat flux density is less than a preset difference threshold, the second end of the flow channel is set to two, tilted toward the blade back side and the blade holder side respectively, so as to cool both side walls simultaneously.

[0012] In one optional embodiment, the blade design method further includes: When the difference between the first heat flux density and the second heat flux density is less than a preset difference threshold, and the height of the turbulence column is less than 0.45 mm, the second end of the flow channel is tilted toward the back of the blade or the blade basin.

[0013] Thirdly, the present invention also provides a turbine, including blades as described above, and a blade design method as described above.

[0014] The blade provided in this invention is cooled by airflow entering the internal chamber of the blade. A portion of the cooling airflow enters the first hole section from the first end of the flow channel on the side wall of the turbulence column, flows along the hole section, enters the second hole section connected to the first hole section, and is discharged from the inclined second hole section, impacting the side wall of the blade, that is, impacting the inner wall surface of the blade back side or blade base side, forming impact cooling.

[0015] This design, without increasing the chamber size or altering the baffle column, introduces impact cooling through internal flow channels, achieving a superposition of external flow around the blade and internal impact. The inclined design at the second end of the flow channel actively guides the cooling fluid to the sidewall most in need of cooling, i.e., the blade back or blade head side, preventing disordered dispersion of the cooling fluid within the chamber and improving the utilization rate of the cooling airflow. This design achieves concentrated cooling in localized high-temperature areas, improving the uniformity of wall temperature distribution, reducing thermal stress, and extending blade life. Furthermore, the flow channel is completely integrated within the baffle column, without increasing the blade's external dimensions or requiring additional cooling layers, making it suitable for the highly compact space constraints within turbine blades. By choosing to incline the second end towards the blade back or blade head side, targeted enhancement of cooling for a specific sidewall can be achieved. Compared to conventional structures, this baffle structure achieves more efficient cooling with lower airflow, lower flow resistance, and avoids overheating and ablation caused by insufficient cooling of turbine blades in high-cycle-parameter engines.

[0016] The blade design method provided by this invention, since it is based on the blade provided by this invention, can also design the tilt direction of the second end of the flow channel accordingly, and thus can produce the same technical effect as the blade of this invention.

[0017] The turbine provided by the present invention incorporates the blades provided by the present invention, and therefore simultaneously incorporates all the aforementioned technical effects of the blades. Attached Figure Description

[0018] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of the internal structure of the trailing edge of a blade according to an embodiment of the present invention; Figure 2 This is a schematic diagram of the internal structure of the leading edge of a blade according to an embodiment of the present invention; Figure 3 for Figure 1 The diagram shows a single outlet of the flow channel for the turbulence column. Figure 4 for Figure 1 The diagram shows a dual-outlet flow channel of the turbulence column. Figure 5 yes Figure 1 A schematic diagram of the arrangement of the baffle columns shown; Figure 6 This is a flowchart of the blade design method in an embodiment of the present invention.

[0020] Explanation of reference numerals in the attached figures: 1. Blade; 101. Back side of blade; 102. Base side of blade; 103. Inner frame; 1a. Leading edge; 1b. Trailing edge; 2. Chamber; 3. Flow-disrupting assembly; 301. Flow-disrupting column; 3011. Flow channel; 3011a. First end; 3011b. Second end; 3011c. First perforated section; 3011d. Second perforated section; X. Chord length direction; Y. Height direction. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0022] In related technologies, a regularly arranged columnar array within the inner cavity of blade 1 significantly enhances the convective heat transfer intensity between the airflow and the inner wall of blade 1 by disrupting the flow boundary layer, enhancing turbulence, and increasing the heat transfer area. However, in these technologies, the cooling capacity of conventionally compact turbulence-inducing columns 301 inside turbine blade 1 approaches its limit. Further reducing the spacing or increasing the number of these columns 301 will drastically increase flow resistance, leading to diminishing marginal benefits for heat transfer enhancement. This is especially problematic under conditions of low cooling air volume, where insufficient cooling may occur.

[0023] Specifically, when the spacing of the turbulence columns 301 decreases and their number increases, the equivalent hydraulic diameter of the flow channel 3011 decreases, which will cause local contraction or expansion losses, thereby increasing separation losses and leading to an increase in frictional resistance. This results in a sharp increase in total pressure loss. When the structure of the turbulence columns 301 is too dense, the flow becomes a highly turbulent saturated flow state. Adding more turbulence columns 301 can no longer increase the intensity of turbulence, but will instead increase resistance. When the amount of cooling gas is small, the high-resistance structure will cause the flow to decay earlier, and the cooling gas may be excessively dissipated in the inlet area. As a result, it cannot effectively reach the far end or hot spot area, affecting the cooling effect of the turbine blade 1.

[0024] Based on this, in order to solve or improve the problem of local overheating of turbine blade 1 in a compact space, this embodiment of the invention provides a blade 1, a blade design method, and a turbine.

[0025] The following is combined with Figures 1 to 6 This describes a blade 1 provided in an embodiment of the present invention.

[0026] Specifically, blade 1 includes a chamber 2 and a turbulence assembly 3.

[0027] The chamber 2 is located inside the blade 1 and can be used for the flow of cooling fluid, such as a cooling airflow. The blade 1 has a back side 101 and a base side 102 arranged opposite to each other.

[0028] The turbulence-disrupting component 3 is disposed on the inner wall of the chamber 2 and includes a plurality of turbulence-disrupting columns 301 spaced apart along the height direction Y of the blade 1. At least one of the blade back side 101 and the blade basin side 102 is provided with the turbulence-disrupting component 3.

[0029] In addition, the turbulence column 301 is provided with a flow channel 3011 for the flow of cooling fluid. The flow channel 3011 has a first end 3011a and a second end 3011b. The first end 3011a of the flow channel 3011 penetrates the side wall of the turbulence column 301 near the leading edge 1a of the blade 1, and the second end 3011b of the flow channel 3011 penetrates the side wall of the turbulence column 301 near the trailing edge 1b of the blade 1, and is inclined toward the back side 101 or the blade basin side 102, so as to guide the cooling fluid to the side wall of the chamber 2 near the back side 101 or the blade basin side 102.

[0030] In this embodiment, a portion of the cooling airflow enters the internal chamber 2 of the blade 1 through the cooling airflow. The cooling airflow enters from the first end 3011a of the flow channel 3011 on the side wall of the turbulence column 301 and exits from the inclined second end 3011b, impacting the side wall of the chamber 2, that is, the inner wall surface of the chamber 2 near the blade back side 101 or the blade basin side 102, forming impact cooling.

[0031] This configuration, without increasing the size of chamber 2 or altering the baffle column 301, introduces cooling airflow through the internal flow channel 3011. Flowing through the inclined second end 3011b, the cooling fluid is actively guided to the sidewalls of the blade back side 101 or blade head side 102 that require the most cooling. This avoids disordered dispersion of the cooling fluid within chamber 2 and improves the utilization rate of the cooling airflow. This design achieves concentrated cooling in localized high-temperature areas, improves the uniformity of wall temperature distribution, reduces thermal stress, and extends the lifespan of blade 1. Furthermore, the flow channel 3011 is completely integrated within the baffle column 301, without increasing the outer dimensions of blade 1 or adding an extra cooling layer. This design is suitable for the highly compact space constraints within turbine blade 1. By tilting the second end 3011b towards the blade back side 101 or blade head side 102, cooling of a specific sidewall can be specifically enhanced.

[0032] In summary, by setting an inclined flow channel 3011 inside the baffle column 301, there is no need to reduce the spacing of the baffle columns 301 or increase the number of baffle columns 301. This avoids the problems of local flow loss superposition, increased frictional resistance and large total pressure loss caused by structural densification in conventional solutions. It controls the flow resistance and energy dissipation of the cooling airflow. Even if the overall cooling air supply is limited, the cooling airflow will not experience premature flow attenuation due to the high-resistance structure, and the flow delivery capacity can be maintained.

[0033] Meanwhile, some cooling airflow can flow directionally through the flow channel 3011 of the turbulence column 301, actively guiding the airflow to the high-temperature hot spot area on the back side 101 or the blade basin side 102 of the blade 1. This changes the disordered flow state of the cold air under the traditional turbulence structure, reduces the ineffective dissipation of cold air in the inlet area, and allows the limited cooling airflow to reach the far end of the blade 1 and the local overheated position more accurately to form directional impact cooling, improve the efficiency of cold air utilization, and avoid the defects of scattered cold air distribution and insufficient cold air supply in key areas under small cold air volume conditions. Thus, without consuming additional cold air flow, the local heat exchange capacity is enhanced, the temperature distribution of the inner wall of the blade 1 is uniform, and a better overall cooling effect is still achieved under the condition of small cold air volume operation.

[0034] In some embodiments provided by the present invention, there are multiple flow-dispersing components 3, which are arranged at intervals along the chord length direction X. In the chord length direction X, the flow-dispersing columns 301 of two adjacent flow-dispersing components 3 are staggered. The flow-dispersing columns 301 in the front row and the flow-dispersing columns 301 in the back row are arranged alternately in the height direction Y. When the cooling fluid flows through the flow-dispersing components 3, it forms an alternating flow path. The fluid continuously splits, merges and turns between the front and back rows of flow-dispersing columns 301.

[0035] In this embodiment, the cooling fluid flows along the chordal direction X, that is, from the leading edge 1a to the trailing edge 1b. When it encounters the first row of turbulence columns 301, the cooling fluid passes through the gap between the columns due to the obstruction of the turbulence columns 301, forming a flow around the columns. After bypassing the first row, the fluid enters the second row. Since the turbulence columns 301 in the second row are staggered with the turbulence columns 301 in the first row, they alternately form a flow around the column. This process is repeated until the fluid flows out of the turbulence component 3 area.

[0036] By staggering the baffle columns 301 of two adjacent baffle components 3, the actual flow path of the fluid is longer than the straight-line distance, increasing the contact time between the fluid and the baffle columns 301 and the wall, and significantly enhancing the convective heat transfer intensity between the fluid and the baffle columns 301 and the wall. Furthermore, the downstream baffle column 301 is located between the two upstream baffle columns 301, which strengthens the impact effect of the cooling fluid on the downstream baffle column 301, allowing the cooling fluid to better enter the flow channel 3011 of the downstream baffle column 301, enhancing the jetting effect of the flow channel 3011, and thus improving the cooling effect.

[0037] In some embodiments provided by the present invention, the flow channel 3011 includes a first hole section 3011c and a second hole section 3011d.

[0038] The first hole section 3011c penetrates the side wall of the turbulence column 301 near the leading edge 1a of the blade 1, and the cooling airflow enters through the side wall of the first hole section 3011c near the leading edge 1a of the blade.

[0039] The second hole section 3011d is connected to the first hole section 3011c and passes through the side wall of the turbulence column 301 near the trailing edge 1b of the blade 1. The end of the second hole section 3011d away from the first hole section 3011c is inclined toward the blade back side 101 or the blade basin side 102. The cooling fluid impacts the corresponding side wall of the chamber 2 through the second hole section 3011d.

[0040] In this embodiment, the cooling fluid flows along the chord X direction in the chamber 2. When it flows past the side wall of the turbulence column 301 near the leading edge 1a, a portion of the fluid enters the flow channel 3011 from the inlet of the first orifice section 3011c. The fluid flows from the first orifice section 3011c into the second orifice section 3011d that is connected to it. Since the end of the second orifice section 3011d away from the first orifice section 3011c is inclined toward the blade back side 101 or the blade basin side 102, the flow direction of the fluid is deflected and impacts the corresponding side wall of the chamber 2 at an angle.

[0041] This design eliminates the need for additional pipes or chambers 2, achieving impact cooling within the highly compact space of turbine blades 1, thus solving the problem of localized overheating and achieving better cooling with less air volume.

[0042] In some embodiments provided by the present invention, the flow channel 3011 includes at least two second orifice sections 3011d, and the first orifice section 3011c is connected to each of the second orifice sections 3011d inside the turbulence column 301. A portion of the second orifice sections 3011d are inclined toward the blade back side 101, and another portion of the second orifice sections 3011d are inclined toward the blade basin side 102 to adapt to the different heat load requirements of the blade back side 101 and the blade basin side 102.

[0043] In this embodiment, the cooling fluid flows along the chordal direction X in the chamber 2 of the blade 1. It enters the flow channel 3011 from the inlet of the first orifice 3011c on the side wall near the leading edge 1a of the turbulence column 301. The fluid flows along the first orifice 3011c to the bifurcation point and is distributed into each of the second orifices 3011d. It enters the second orifices 3011d that are inclined towards the blade back side 101 and the blade base side 102, respectively, and flows out from the outlet of their respective second orifices 3011d, while impacting the two opposite side walls of the chamber 2.

[0044] Through the bifurcation design of the second orifice section 3011d, each airflow is guided to a target wall, achieving the function of simultaneously cooling both sides of the blade 1. Compared with the single-outlet structure, it achieves double the effective impact coverage in the same space.

[0045] In some embodiments provided by the present invention, the angle between the second hole segment 3011d inclined toward the blade back side 101 and the first hole segment 3011c is greater than or less than the angle between the second hole segment 3011d inclined toward the blade basin side 102 and the first hole segment 3011c. The two second hole segments 3011d form an asymmetrical impact arrangement, so that the cooling gas impacts the blade back side 101 and the blade basin side 102 wall at different angles and paths, adapting to the different heat load distributions of the blade back side 101 and the blade basin side 102.

[0046] In this embodiment, the cooling fluid enters the internal flow channel 3011 through the inlet of the first orifice 3011c on the sidewall near the leading edge 1a of the turbulence column 301. At the bifurcation, the fluid enters the second orifice 3011d facing the blade back side 101 and the second orifice 3011d facing the blade tip side 102, respectively. Due to the different angles, the airflow generated by the second orifice 3011d with a smaller angle is gentler, while the airflow generated by the second orifice 3011d with a larger angle is steeper. These airflows impact the inner wall surfaces of the blade back side 101 and the blade tip side 102, respectively, forming a more concentrated and stronger cooling effect on the high heat load side, while providing moderate cooling on the low heat load side.

[0047] With this design, the heat load on the blade head side 102 and the blade back side 101 of the turbine blade 1 is often asymmetrical in actual operation. By setting different angles, stronger impact cooling can be directed to the hotter side, realizing the on-demand allocation of cooling resources and avoiding waste or insufficiency caused by uniform cooling.

[0048] In some embodiments provided by the present invention, the axis of the first hole segment 3011c is perpendicular to the axis of the turbulence column 301.

[0049] In some embodiments provided by the present invention, the height of the turbulence column 301 is 0.3mm to 0.6mm. This height range is suitable for compact chambers 2 such as the trailing edge 1b of the turbine blade 1 or double-walled structures. When the height is less than 0.45mm, a single outlet flow channel 3011 is used due to manufacturing process limitations. When the height is not less than 0.45mm, a double outlet flow channel 3011 can be selected.

[0050] In some embodiments provided by the present invention, the turbulence column 301 is a cylindrical structure with a diameter of 0.3mm to 1.0mm. The cylindrical structure is simple to process and has clear flow resistance characteristics. The diameter range of the cylindrical structure matches the height range, which can provide sufficient heat exchange area and avoid strength problems caused by the cylindrical structure being too thin.

[0051] In some embodiments provided by the present invention, the diameter of at least one of the first hole segment 3011c and the second hole segment 3011d is 0.2mm to 0.4mm. When the diameter of the first hole segment 3011c and the second hole segment 3011d is too small, it is difficult to process and the flow resistance is too large. When the diameter of the first hole segment 3011c and the second hole segment 3011d is too large, it will weaken the mechanical strength of the turbulence column 301 and make it impossible to arrange in a narrow column.

[0052] In some embodiments provided by the present invention, the included angle between the first hole section 3011c and the second hole section 3011d is 10° to 30°. Within this angle range, the cooling airflow can form an effective impact, while facilitating casting demolding.

[0053] In this embodiment, the cooling airflow enters the internal chamber 2 of the blade 1 and flows along the chordal direction X of the blade 1. Since the axis of the first orifice section 3011c is perpendicular to the axis of the turbulence column 301 and the opening of the first orifice section 3011c faces the leading edge 1a of the blade 1, the upstream flow enters the first orifice section 3011c. At the same time, the fluid outside the turbulence column 301 flows around the column. The fluid enters the internal channel with a diameter of 0.2mm to 0.4mm and is deflected at the second orifice section 3011d. The deflection angle is 10° to 30°. The fluid changes from the chordal direction X of the blade 1 to point towards the back of the blade or the wall of the blade basin side 102. The cooling jet flows out from the outlet of the second orifice section 3011d and impacts the side wall of the chamber 2 at an inclination angle of 10° to 30°, forming a high-intensity heat transfer locally.

[0054] With this configuration, the height and diameter of the turbulence column 301 together determine the slenderness ratio of the column, thereby ensuring the structural strength of the turbulence column 301 under high temperature and high pressure. The vertically arranged first hole section 3011c minimizes the intake resistance, allowing sufficient airflow to enter the flow channel 3011.

[0055] In some embodiments provided by the present invention, there are multiple turbulence components 3, and at least some of the turbulence components 3 are located in the part of the chamber 2 near the trailing edge 1b of the blade 1. The turbulence columns 301 in the part of the turbulence components 3 are arranged at intervals along the height direction Y of the blade 1, and the two ends of the turbulence columns 301 of the turbulence components 3 are respectively connected to the blade back side 101 and the blade basin side 102 of the chamber 2, forming a turbulence array in the region of the trailing edge 1b of the blade 1.

[0056] In this embodiment, since the two ends of the turbulence column 301 are respectively connected to the blade back and the blade basin side 102 wall, the fluid passes through the gap between the turbulence columns 301 to form a flow around it. When the turbulence column 301 in this area is provided with an inclined flow channel 3011, some of the fluid enters the flow channel 3011 and is shot from the outlet to the blade back side 101 or the blade basin side 102.

[0057] With this configuration, the turbulence column 301 connects to both side walls without taking up extra width of chamber 2. Combined with the forked arrangement, the cooling effect of the trailing edge 1b area is improved.

[0058] In some embodiments provided by the present invention, the blade 1 further includes an inner frame 103, at least a portion of which is disposed in the portion of the chamber 2 near the leading edge 1a of the blade 1 and has a gap between it and the inner wall of the chamber 2 to form a cooling flow path around the inner frame 103. The inner frame 103 divides the chamber 2 near the leading edge 1a into two layers: one near the blade back side 101 and the other near the blade base side 102.

[0059] Furthermore, the spoiler assembly 3 is disposed on the outer wall of the inner frame 103 near the blade back side 101 or the blade head side 102, and the spoiler columns 301 of the spoiler assembly 3 are all connected to the outer wall of the inner frame 103. Of course, referring to... Figure 2 Corresponding aerodynamic components 3 can be set on both sides of the inner frame 103.

[0060] In this embodiment, the cooling fluid from the leading edge 1a impact hole or air supply chamber enters the interlayer between the inner frame 103 and the blade back side 101 or blade basin side 102. The fluid flows in the interlayer and flows through the turbulence column 301 array on the outer wall of the inner frame 103, resulting in flow around the fluid.

[0061] With this design, the inner frame 103 can guide the cool air to flow evenly across the entire blade surface, avoiding localized overheating.

[0062] It is understood that the technical features in the above embodiments can be combined with each other. For example, other embodiments provided by the present invention specifically include a turbine blade 1 structure for enhanced cooling. The blade 1 has a back side 101 and a nose side 102 arranged opposite to each other, which together define the external aerodynamic profile of the blade 1. A chamber 2 for guiding the flow of cooling medium is provided inside the blade 1. The chamber 2 is located inside the blade 1. On the inner wall of the chamber 2, a plurality of turbulence components 3 for enhancing heat transfer are arranged. The turbulence components 3 can be in a regular or irregular array form. The specific arrangement of the components can be optimized according to the local heat load distribution. Each turbulence component 3 includes multiple turbulence columns 301 spaced apart along the height direction Y of the blade 1. Furthermore, the turbulence column 301 has a flow channel 3011 inside for the flow of cooling fluid. By introducing an internal flow structure in the turbulence column 301, not only can a flow disturbance be formed outside the column, but cooling can also be achieved inside the column, thereby improving the overall cooling efficiency. The flow channel 3011 can include at least two hole segments, and the hole segments can be interconnected or arranged at a certain angle.

[0063] In some embodiments provided by the present invention, a blade design method is provided for blade 1 as described above, the method comprising: Calculate the first heat flux density on the leaf basin side 102 and the second heat flux density on the leaf back side 101 of the blade 1.

[0064] When the first heat flux density is greater than the second heat flux density, the second end 3011b of the flow channel 3011 is tilted toward the blade basin side 102, and the cooling fluid is guided along the second end 3011b of the flow channel 3011 to the inner wall surface of the blade basin side 102 with a higher heat load, so as to achieve single-sided concentrated impact cooling.

[0065] When the first heat flux density is less than the second heat flux density, the second end 3011b of the flow channel 3011 is tilted toward the blade back side 101, and the cooling fluid is guided along the second end 3011b of the flow channel 3011 to the inner wall surface of the blade back side 101 with a higher heat load, so as to achieve single-sided concentrated impact cooling.

[0066] If the difference between the first heat flux density and the second heat flux density is less than a preset difference threshold, then the second end 3011b of the flow channel 3011 is set to two, which are inclined toward the blade back side 101 and the blade basin side 102 respectively, so that the two jets simultaneously impact the two side walls to achieve bilateral symmetrical or asymmetrical impact cooling.

[0067] In this embodiment, the heat flux density distribution of the inner wall surfaces of the blade basin side 102 and the blade back side 101 under the design conditions is obtained by calculation, and the values ​​on both sides are compared. At the same time, the height of the chamber 2 at the location of the turbulence column 301 is measured. When the heat flux density of the inner wall surface of the blade basin side 102 is significantly greater than that of the inner wall surface of the blade back side 101, and the height of the turbulence column 301 is greater than or equal to 0.45 mm, or the height of the turbulence column 301 is any size that meets the manufacturing conditions of a single outlet, then a single outlet is selected that is tilted toward the blade basin side 102.

[0068] In addition, when the heat flux density on the inner wall of the blade basin side 102 is significantly less than the heat flux density on the inner wall of the blade back side 101, the single outlet is tilted toward the blade back side 101.

[0069] In addition, when the difference between the heat flux density on the inner wall of the blade basin side 102 and the heat flux density on the inner wall of the blade back side 101 is small, that is, the heat loads on both sides are close, and the height of the turbulence column 301 is greater than or equal to 0.45mm, then a double outlet is selected, with the double outlets tilted to both sides respectively.

[0070] Optionally, if the height of the turbulence column 301 is less than 0.45 mm, due to manufacturing process limitations, it is not possible to reliably form the dual-outlet branch flow channel 3011 in such a small space. Even if the heat loads on both sides are similar, the second end 3011b of the flow channel 3011 is still set as a single outlet and tilted towards the side with higher heat flux density.

[0071] This configuration allows for the selection of single-sided or double-sided impact based on the actual heat load distribution. The blades are manufactured according to the selected structure to avoid wasting cooling resources in the low-temperature region. The maximum local cooling effect is achieved with the minimum amount of cold air, significantly improving cooling efficiency. Through threshold design, the selection criteria become operable.

[0072] In some embodiments provided by the present invention, the blade design method further includes: When the difference between the first heat flux density and the second heat flux density is less than a preset difference threshold, and the height of the turbulence column 301 is less than 0.45 mm, the second end 3011b of the flow channel 3011 is tilted toward the blade back side 101 or the blade basin side 102.

[0073] Specifically, when the difference between the first heat flux density and the second heat flux density is less than a preset difference threshold, and the height of the turbulence column 301 is less than 0.45 mm, the dual-outlet structure is not adopted, and only one second end 3011b of the flow channel 3011 is set, so that the second end 3011b of the flow channel 3011 is inclined toward the blade back side 101 or the blade basin side 102. The choice of orientation depends on the relationship between the first heat flux density and the second heat flux density. If the first heat flux density is greater than the second heat flux density, it is inclined toward the blade basin side 102, and vice versa. If the two are equal, either side can be selected.

[0074] In this embodiment, the heat flux density on the blade basin side 102 and the heat flux density on the blade back side 101 are obtained through numerical simulation or experiment, and the difference is calculated. When the difference is less than a preset threshold, it indicates that the heat load on both sides of the wall is similar, and theoretically it is suitable to use dual outlets for simultaneous impact. At the same time, the height of the location of the turbulence column 301 is measured. If the height is less than 0.45mm, the manufacturing feasibility judgment is entered. That is, the heat load is similar, but because the height is too small, the dual outlet branch flow channel 3011 cannot be reliably formed. Therefore, a single outlet structure is selected. At this time, a turbulence column 301 with a single outlet inclined flow channel 3011 is processed. The cooling airflow is ejected from the second end 3011b and impacts the selected side wall.

[0075] This configuration provides the possibility of built-in shock cooling for extremely compact areas such as trailing edge 1b. The method is relatively clear and easy to embed into design software for rapid selection.

[0076] Furthermore, after selecting the structural type, by optimizing the arrangement of the baffle columns 301, as well as structural parameters such as the diameter of the baffle columns 301, the diameter of the internal flow channels 3011 of the baffle columns 301, and the inclination angle of the film cooling hole outlet, the internal heat transfer efficiency of blade 1 can be improved, and the temperature level and thermal stress concentration in the high-temperature region of blade 1 can be reduced. The flow distribution and pressure matching between the baffle columns 301 of blade 1 and other cooling structures are evaluated, and the comprehensive cooling effect and reliability are verified through full three-dimensional fluid-thermal-structure coupling analysis.

[0077] In some embodiments provided by the present invention, a turbine includes blades 1 as described above, and a blade design method as described above.

[0078] In this embodiment, the high-temperature and high-pressure gas generated in the combustion chamber impacts the turbine blades 1, driving the rotor to rotate at high speed, converting the thermal energy of the gas into mechanical energy, driving the compressor and fan, and drawing out a portion of compressed air, which has a relatively low temperature and can be used as a cooling medium, and sent into the turbine blades 1 through the cooling air passage inside the engine.

[0079] In addition, cooling air enters the air inlet of blade 1 and flows into the internal chamber 2. The array of turbulence columns 301 in chamber 2 causes the cooling air to circulate, destroying the boundary layer and enhancing convective heat transfer. Some of the cooling air enters the flow channel 3011 built into the turbulence column 301 and is ejected at high speed from the inclined second end 3011b, impacting the inner wall surface of the blade back or blade basin side 102, forming local high-intensity impact cooling.

[0080] Furthermore, based on the heat load distribution, namely the difference between the first heat flux density and the second heat flux density and the height of the turbulence column 301, the blade 1 may adopt a single-outlet directional impact or a dual-outlet symmetrical or asymmetrical impact. After the internal cooling is completed, the air is discharged from the air film holes on the trailing edge 1b of the blade 1, the blade tip or the wall surface, forming a cooling air film on the outer surface of the blade 1, further isolating the high-temperature combustion gas. The above cooling process is carried out continuously throughout the entire operation of the engine to ensure that the turbine blade 1 is always within the temperature range allowed by the material.

[0081] With this configuration, the cooling structure of blade 1 can withstand higher temperatures, thereby allowing the turbine inlet temperature to be further increased, increasing thrust or power output. The temperature field of blade 1 is more uniform, thermal stress is significantly reduced, the generation of thermal fatigue cracks is reduced, the service life of blade 1 is extended, and the maintenance cost of the engine throughout its entire life cycle is reduced. Compared with the conventional structure, this turbulence structure can achieve a more efficient cooling effect under small cooling air volume conditions, with lower flow resistance, avoiding overheating and ablation caused by insufficient cooling of turbine blade 1 in high-cycle-parameter engines.

[0082] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A blade, characterized in that, include: A chamber (2) is located inside the blade (1), the blade (1) having a back side (101) and a base side (102) arranged opposite to each other. A turbulence-disrupting assembly (3) is disposed on the inner wall of the chamber (2) and includes a plurality of turbulence-disrupting columns (301) spaced apart along the height direction (Y) of the blade (1). The turbulence-disrupting assembly (3) is disposed on at least one of the inner walls of the chamber (2) near the blade back side (101) and the blade basin side (102). The turbulence column (301) is provided with a flow channel (3011) for the flow of cooling fluid. The flow channel (3011) has a first end (3011a) and a second end (3011b). The first end (3011a) of the flow channel (3011) penetrates the side wall of the turbulence column (301) near the leading edge (1a) of the blade (1). The second end (3011b) of the flow channel (3011) penetrates the side wall of the turbulence column (301) near the trailing edge (1b) of the blade (1) and is inclined toward the back side (101) or the blade basin side (102) to guide the cooling fluid to the side wall of the chamber (2) near the back side (101) or the blade basin side (102).

2. The blade according to claim 1, characterized in that, The number of the turbulence components (3) is multiple, and the multiple turbulence components (3) are arranged at intervals along the chord length direction (X) of the blade (1). In the chord length direction (X), the turbulence columns (301) of two adjacent turbulence components (3) are staggered.

3. The blade according to claim 1, characterized in that, The flow channel (3011) includes: The first hole section (3011c) penetrates the side wall of the turbulence column (301) near the leading edge (1a) of the blade (1); The second hole segment (3011d) communicates with the first hole segment (3011c) and penetrates the side wall of the turbulence column (301) near the trailing edge (1b) of the blade (1). The end of the second hole segment (3011d) away from the first hole segment (3011c) is inclined toward the back side (101) of the blade or the leaf basin side (102).

4. The blade according to claim 3, characterized in that, The flow channel (3011) includes at least two second hole segments (3011d), one portion of which is inclined toward the leaf back side (101) and the other portion of which is inclined toward the leaf basin side (102).

5. The blade according to claim 4, characterized in that, The angle between the second hole segment (3011d) inclined toward the leaf back side (101) and the first hole segment (3011c) is greater than or less than the angle between the second hole segment (3011d) inclined toward the leaf basin side (102) and the first hole segment (3011c).

6. The blade according to claim 3, characterized in that, The axis of the first hole segment (3011c) is perpendicular to the axis of the turbulence column (301); And / or, the height of the turbulence column (301) is 0.3mm~0.6mm; And / or, the turbulence column (301) is a cylindrical structure, and the diameter of the turbulence column (301) is 0.3mm~1.0mm; And / or, at least one of the first hole segment (3011c) and the second hole segment (3011d) has a diameter of 0.2 mm to 0.4 mm; And / or, the included angle between the first hole segment (3011c) and the second hole segment (3011d) is 10°~30°.

7. The blade according to any one of claims 1-6, characterized in that, The number of the turbulence components (3) is multiple, and at least part of the turbulence components (3) are located in the part of the chamber (2) near the trailing edge (1b) of the blade (1), and the two ends of the turbulence column (301) of the turbulence component (3) are respectively connected to the two side walls of the chamber (2) near the back side (101) and the blade basin side (102). And / or, the blade (1) further includes an inner frame (103), at least a portion of which is disposed in the cavity (2) near the leading edge (1a) of the blade (1) and has a gap with the inner wall of the cavity (2), the turbulence assembly (3) is disposed on the outer wall of the inner frame (103) near the blade back side (101) or the blade basin side (102), and the turbulence columns (301) of the turbulence assembly (3) are all connected to the outer wall of the inner frame (103).

8. A blade design method, characterized in that, For the blade (1) as described in any one of claims 1-7, the method comprises: Calculate the first heat flux density on the leaf basin side (102) and the second heat flux density on the leaf back side (101) of the blade (1); When the first heat flux density is greater than the second heat flux density, the second end (3011b) of the flow channel (3011) is tilted toward the leaf basin side (102). When the first heat flux density is less than the second heat flux density, the second end (3011b) of the flow channel (3011) is tilted toward the leaf back side (101). When the difference between the first heat flux density and the second heat flux density is less than a preset difference threshold, the second end (3011b) of the flow channel (3011) is set to two, tilted toward the leaf back side (101) and the leaf basin side (102) respectively.

9. The blade design method according to claim 8, characterized in that, The method further includes: When the difference between the first heat flux density and the second heat flux density is less than a preset difference threshold, and the height of the turbulence column (301) is less than 0.45 mm, the second end (3011b) of the flow channel (3011) is tilted toward the back side (101) or the leaf basin side (102).

10. A turbine, characterized in that, Includes a blade (1), wherein the blade (1) is the blade (1) as described in any one of claims 1-7, or is manufactured using the blade (1) design method as described in any one of claims 8-9.

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