A blade with multi-channel double-jet cyclone cooling structure and engine

Abstract

The application discloses a blade with a multi-channel double-jet flow cyclone cooling structure and an engine, and belongs to the technical field of gas turbines and aero-engines. The overall double-wall structure is adopted, a leading edge gas supply chamber and a leading edge cyclone cooling cavity penetrating through the height of the blade are arranged at the leading edge of the blade, double jets are provided through the cooling channels on both sides of the leading edge of the blade, a larger heat exchange area is possessed, and the wall jet can simultaneously and efficiently cool the pressure side of the leading edge and the suction side of the leading edge. The cooling gas flowing out of the leading edge cyclone cooling cavity can simultaneously form wall jets in the pressure side secondary cooling channel and the suction side secondary cooling channel to perform secondary cooling on the pressure side of the leading edge and the suction side of the leading edge, and the utilization rate of the cooling gas is improved. The relatively independent cooling structure units formed by the cooling channels avoid the generation of cross flow in the leading edge cyclone cooling cavity, so that the heat exchange of the cooling target surface is more uniform.

Description

Technical Field

[0001] This invention belongs to the field of gas turbine and aero-engine technology, specifically relating to a blade and engine with a multi-channel dual-jet swirl cooling structure. Background Technology

[0002] The growing awareness of environmental protection and efficient energy use is driving the energy and power industry's demand for higher-performance, higher-power gas turbines and aero engines. Increasing turbine inlet temperature is a direct way to meet this demand. Gas turbine blades are critical hot-end components, bearing extremely high thermal loads, especially the leading edge which faces direct impact from high-temperature exhaust gases, exceeding the tolerance temperature of its base material. Therefore, more efficient cooling technologies are needed to reduce the operating temperature of turbine blades and extend their service life.

[0003] Existing turbine blade cooling methods mainly include internal cooling, external cooling, and combined cooling. Internal cooling methods used for the blade leading edge include impingement cooling and swirling cooling. Impingement cooling utilizes a high-speed jet of cold gas impacting the leading edge target surface; the high-frequency velocity variation of the cold gas near the stagnation point generates strong convective heat transfer, thus carrying away heat. Swirling cooling utilizes the high-speed rotational motion of the cold gas jet within the leading edge chamber to enhance heat transfer intensity.

[0004] The main drawbacks of cooling schemes such as impact and swirling cooling are that, on the one hand, the mixing of the crossflow generated after the cold air impacts the target surface with the cold air jet will reduce the cooling efficiency of the cold air; on the other hand, the crossflow will force the cold air jet to deflect, which will weaken the impact of the cold air on the target surface and thus weaken the heat transfer intensity. Summary of the Invention

[0005] In order to overcome the shortcomings of the prior art, the present invention aims to provide a blade and engine with a multi-channel dual-jet swirl cooling structure. The structure is reasonably designed and can effectively reduce or even suppress the crossflow effect in the leading edge cooling chamber, thereby improving the leading edge cooling effect of the blade.

[0006] This invention is achieved through the following technical solution:

[0007] This invention discloses a blade with a multi-channel dual-jet swirl cooling structure, including a leading-edge dual-jet swirl cooling zone, a mid-chord cooling zone, and a trailing-edge rib turbulence cooling zone disposed inside the blade;

[0008] The leading edge dual-jet swirl cooling zone includes a leading edge air supply chamber that extends through the blade height and a leading edge swirl cooling chamber. The two sides of the leading edge air supply chamber are connected to the leading edge swirl cooling chamber through several pressure-side cooling jet channels and suction-side cooling jet channels, respectively.

[0009] The mid-chord cooling zone includes a mid-chord air supply chamber, a mid-chord pressure-side cooling channel, and a mid-chord suction-side cooling channel. The mid-chord pressure-side cooling channel is located between the outer and inner solid walls of the pressure side, and several pressure-side jet impact holes are arranged in an array on the inner solid wall of the pressure side. The mid-chord suction-side cooling channel is located between the outer and inner solid walls of the suction side, and several suction-side jet impact holes are arranged in an array on the inner solid wall of the suction side. The mid-chord air supply chamber is connected to the mid-chord pressure-side cooling channel through the pressure-side jet impact holes and to the mid-chord suction-side cooling channel through the suction-side jet impact holes. Several ribs are provided in both the mid-chord pressure-side cooling channel and the mid-chord suction-side cooling channel.

[0010] The trailing edge rib turbulence cooling zone includes a trailing edge cooling channel located inside the trailing edge of the blade, and several trailing edge ribs are provided in the trailing edge cooling channel.

[0011] One side of the leading edge swirl cooling chamber is connected to the middle chord pressure side cooling channel through the pressure side secondary cooling channel, and the other side is connected to the middle chord suction side cooling channel through the suction side secondary cooling channel. Both the pressure side secondary cooling channel and the suction side secondary cooling channel are connected to the beginning of the trailing edge cooling channel, and the end of the trailing edge cooling channel is connected to the cooling gas outlet on the blade.

[0012] Preferably, the middle chord air supply chamber includes several independent air supply chambers separated by chamber partitions, and the two ends of the chamber partitions are fixedly connected to the inner solid wall on the pressure side and the inner solid wall on the suction side, respectively.

[0013] Preferably, the inner walls of the leading edge swirl cooling chamber and the leading edge air supply chamber are both smooth curved surfaces.

[0014] Preferably, the leading edge swirl cooling cavity is cylindrical, and the pressure-side cooling jet channel, the suction-side cooling jet channel, the pressure-side secondary cooling channel, and the suction-side secondary cooling channel are all located in the tangential direction of the leading edge swirl cooling cavity.

[0015] Preferably, a pressure-side cooling jet channel, a suction-side cooling jet channel, a pressure-side secondary cooling channel, and a suction-side secondary cooling channel constitute a cooling structure unit; the pressure-side secondary cooling channel and the suction-side secondary cooling channel are located on one side of the pressure-side cooling jet channel and the suction-side cooling jet channel.

[0016] Preferably, a pressure-side cooling jet channel, a suction-side cooling jet channel, two pressure-side secondary cooling channels, and two suction-side secondary cooling channels constitute a cooling structure unit; the two pressure-side secondary cooling channels are located on both sides of the pressure-side cooling jet channel and the suction-side cooling jet channel, respectively, and the two suction-side secondary cooling channels are located on both sides of the pressure-side cooling jet channel and the suction-side cooling jet channel, respectively.

[0017] More preferably, the cross-sectional area of ​​the pressure-side cooling jet channel is equal to that of the suction-side cooling jet channel, the cross-sectional area of ​​the pressure-side secondary cooling channel and the suction-side secondary cooling channel on the blade root side is 30% to 40% of that of the pressure-side cooling jet channel, and the cross-sectional area of ​​the pressure-side secondary cooling channel and the suction-side secondary cooling channel on the blade tip side is 60% to 70% of that of the pressure-side cooling jet channel.

[0018] Preferably, the pressure-side cooling jet channel and the suction-side cooling jet channel are located at the same height; the pressure-side secondary cooling channel and the suction-side secondary cooling channel are located at the same height.

[0019] Preferably, the pressure-side cooling jet channel, the suction-side cooling jet channel, the pressure-side secondary cooling channel, and the suction-side secondary cooling channel are parallel to each other.

[0020] The present invention discloses an engine comprising a plurality of blades having the above-described multi-channel dual-jet swirl cooling structure.

[0021] Compared with the prior art, the present invention has the following beneficial technical effects:

[0022] This invention discloses a blade with a multi-channel dual-jet swirling cooling structure. The blade employs a double-wall structure, with a leading-edge air supply chamber and a leading-edge swirling cooling chamber extending through the blade's height at the leading edge. Dual jets are provided through cooling channels on both sides of the leading edge, resulting in a larger heat exchange area. This allows the wall jets to simultaneously and efficiently cool both the leading-edge pressure and suction sides. High-speed injected cold air forms large-scale vortices in the swirling cooling chamber. The high-speed rotation of these large vortices significantly thins the thermal boundary layer at the wall surface. The large radial velocity and pressure gradient of the cold air vortices enhance momentum exchange, thereby increasing turbulence intensity and significantly enhancing heat transfer. The cooling air exiting the leading-edge swirling cooling chamber simultaneously forms wall jets in both the pressure-side and suction-side secondary cooling channels, providing secondary cooling to both the leading-edge pressure and suction sides, thus improving the utilization rate of the cooling air. Compared to the traditional double-walled structure inside the blade, this design retains the structural advantages of a double-walled structure in the leading edge region while avoiding the adverse effects of crossflow in leading edge impact cooling and leading edge swirl cooling methods. Simultaneously, the relatively independent cooling structural units formed by each cooling channel prevent crossflow in the leading edge swirl cooling chamber. Compared to traditional leading edge swirl cooling structures, the relatively independent leading edge swirl cooling chamber in this application reduces the attenuation rate of circumferential motion, resulting in more uniform heat transfer on the cooling target surface. In the mid-chord cooling zone, the cooling gas in the mid-chord air supply chamber impacts the outer solid walls on both the pressure and suction sides through jet impact holes, and further enhances heat transfer in the cooling zone through rib turbulence. In the trailing edge rib turbulence cooling zone, the cooling gas carries away heat from the trailing edge region through the turbulence effect of the trailing edge ribs, ultimately flowing out of the blade. Attached Figure Description

[0023] Figure 1 This is a outline view of the blade of the present invention;

[0024] Figure 2 yes Figure 1 AA section diagram;

[0025] Figure 3 yes Figure 1 BB cross-section diagram;

[0026] Figure 4 This is a schematic diagram of the cooling structure unit of Embodiment 1;

[0027] Figure 5 yes Figure 1 A schematic diagram of the double-layered wall inside the blade after being cut at the AA section;

[0028] Figure 6 yes Figure 1 A schematic diagram of the double-layered wall inside the blade after the BB section is cut off;

[0029] Figure 7 This is a schematic diagram of the cooling structure unit in Example 2;

[0030] Figure 8 This is a schematic diagram of the cooling structure unit in Example 3;

[0031] Figure 9 This is a schematic diagram of the velocity distribution in the transverse cross section of a traditional swirl cooling chamber;

[0032] Figure 10 This is a schematic diagram of the velocity distribution in the transverse cross section of the cooling jet channel in Example 1;

[0033] Figure 11 This is a schematic diagram of the velocity distribution in the transverse cross section of the secondary cooling channel in Example 1;

[0034] Figure 12 This is a schematic diagram of the Nusselt number distribution on a traditional swirl-cooled heat exchange target surface;

[0035] Figure 13 This is a schematic diagram of the Nusselt number distribution on the pressure-side heat exchange target surface in Example 1;

[0036] Figure 14 This is a schematic diagram of the Nusselt number distribution on the suction-side heat exchange target surface in Example 1;

[0037] Figure 15 This is a comparison curve of the circumferential average Nusselt number of the leading edge cooling chamber along the blade height direction between conventional swirl cooling and the leading edge cooling chamber of Embodiment 1 of the present invention;

[0038] Figure 16This is a bar chart comparing the average Nusselt number of the heat exchange surface area between traditional swirl cooling and Embodiment 1 of the present invention.

[0039] In the diagram: 1 is the leading edge dual-jet swirling cooling zone, 2 is the leading edge air supply chamber, 3 is the pressure-side rib turbulence cooling zone, 4 is the middle chord first air supply chamber, 5 is the middle chord second air supply chamber, 6 is the suction-side rib turbulence cooling zone, 7 is the trailing edge rib turbulence cooling zone, 8 is the cooling structure unit, 9 is the pressure-side cooling jet channel, 10 is the suction-side cooling jet channel, 11 is the leading edge swirling cooling chamber, 12 is the pressure-side secondary cooling channel, 13 is the suction-side secondary cooling channel, 14 is the pressure-side inner solid wall, 15 is the suction-side outer solid wall, 16 is the pressure-side jet impact hole, 17 is the suction-side jet impact hole, 18 is the trailing edge rib, 19 is the pressure-side outer solid wall, 20 is the suction-side inner solid wall, 21 is the suction-side rib, and 22 is the pressure-side rib. Detailed Implementation

[0040] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. This description is intended to explain the invention and not to limit it.

[0041] The blade of the present invention has a multi-channel dual-jet swirl cooling structure, including a leading-edge dual-jet swirl cooling zone 1, a mid-chord cooling zone, and a trailing-edge rib turbulence cooling zone 7 disposed inside the blade.

[0042] The leading edge dual-jet swirl cooling zone 1 includes a leading edge air supply chamber 2 that extends through the blade height and a leading edge swirl cooling chamber 11. The two sides of the leading edge air supply chamber 2 are connected to the leading edge swirl cooling chamber 11 through several pressure-side cooling jet channels 9 and suction-side cooling jet channels 10, respectively.

[0043] The mid-chord cooling zone includes a mid-chord air supply chamber, a mid-chord pressure-side cooling channel, and a mid-chord suction-side cooling channel. The mid-chord pressure-side cooling channel is located between the outer solid wall 19 and the inner solid wall 14 on the pressure side, and several pressure-side jet impact holes 16 are arranged in an array on the inner solid wall 14. The mid-chord suction-side cooling channel is located between the outer solid wall 15 and the inner solid wall 20 on the suction side, and several suction-side jet impact holes 17 are arranged in an array on the inner solid wall 20. The mid-chord air supply chamber is connected to the mid-chord pressure-side cooling channel through the pressure-side jet impact holes 16 and to the mid-chord suction-side cooling channel through the suction-side jet impact holes 17. Several ribs are provided in both the mid-chord pressure-side cooling channel and the mid-chord suction-side cooling channel.

[0044] The trailing edge rib turbulence cooling zone 7 includes a trailing edge cooling channel located inside the trailing edge of the blade, and a number of trailing edge ribs 18 are provided in the trailing edge cooling channel.

[0045] One side of the leading edge swirl cooling chamber 11 is connected to the middle chord pressure side cooling channel through the pressure side secondary cooling channel 12, and the other side is connected to the middle chord suction side cooling channel through the suction side secondary cooling channel 13. Both the pressure side secondary cooling channel 12 and the suction side secondary cooling channel 13 are connected to the starting end of the trailing edge cooling channel, and the end of the trailing edge cooling channel is connected to the cooling gas outlet on the blade.

[0046] In a preferred embodiment of the present invention, the central air supply chamber includes several independent air supply chambers separated by chamber partitions, the two ends of which are fixedly connected to the inner solid wall 14 on the pressure side and the inner solid wall 20 on the suction side, respectively.

[0047] In a preferred embodiment of the present invention, the inner walls of the leading edge swirl cooling chamber 11 and the leading edge air supply chamber 2 are both smooth curved surfaces.

[0048] In a preferred embodiment of the present invention, the leading edge swirl cooling cavity 11 is cylindrical, and the pressure-side cooling jet channel 9, the suction-side cooling jet channel 10, the pressure-side secondary cooling channel 12, and the suction-side secondary cooling channel 13 are all located in the tangential direction of the leading edge swirl cooling cavity 11.

[0049] In a preferred embodiment of the present invention, a pressure-side cooling jet channel 9, a suction-side cooling jet channel 10, a pressure-side secondary cooling channel 12, and a suction-side secondary cooling channel 13 constitute a cooling structure unit 8; the pressure-side secondary cooling channel 12 and the suction-side secondary cooling channel 13 are located on one side of the pressure-side cooling jet channel 9 and the suction-side cooling jet channel 10.

[0050] In a preferred embodiment of the present invention, a pressure-side cooling jet channel 9, a suction-side cooling jet channel 10, two pressure-side secondary cooling channels 12, and two suction-side secondary cooling channels 13 constitute a cooling structure unit 8; the two pressure-side secondary cooling channels 12 are respectively located on both sides of the pressure-side cooling jet channel 9 and the suction-side cooling jet channel 10, and the two suction-side secondary cooling channels 13 are respectively located on both sides of the pressure-side cooling jet channel 9 and the suction-side cooling jet channel 10.

[0051] Further optimized, the cross-sectional area of ​​the pressure-side cooling jet channel 9 is equal to that of the suction-side cooling jet channel 10, the cross-sectional area of ​​the pressure-side secondary cooling channel 12 and the suction-side secondary cooling channel 13 on the blade root side is 30% to 40% of that of the pressure-side cooling jet channel 9, and the cross-sectional area of ​​the pressure-side secondary cooling channel 12 and the suction-side secondary cooling channel 13 on the blade tip side is 60% to 70% of that of the pressure-side cooling jet channel 9.

[0052] In a preferred embodiment of the present invention, the pressure-side cooling jet channel 9 and the suction-side cooling jet channel 10 are located at the same height; the pressure-side secondary cooling channel 12 and the suction-side secondary cooling channel 13 are located at the same height.

[0053] In a preferred embodiment of the present invention, the pressure-side cooling jet channel 9, the suction-side cooling jet channel 10, the pressure-side secondary cooling channel 12, and the suction-side secondary cooling channel 13 are parallel to each other.

[0054] The engine of the present invention includes a plurality of blades having the above-described multi-channel dual-jet swirling cooling structure.

[0055] The blades with the aforementioned multi-channel dual-jet swirl cooling structure operate as follows:

[0056] In the leading edge dual-jet swirl cooling zone 1, the cooling gas in the leading edge air supply chamber 2 is injected into the leading edge swirl cooling chamber 11 through the pressure side cooling jet channel 9 and the suction side cooling jet channel 10;

[0057] The cooling gas in the leading edge swirl cooling chamber 11 cools the solid wall of the leading edge of the blades while flowing radially, and then turns 90 degrees to enter the pressure side secondary cooling channel 12 and the suction side secondary cooling channel 13, and then enters the pressure side rib turbulence cooling zone 3 and the suction side rib turbulence cooling zone 6 respectively.

[0058] In the pressure-side ribbed turbulence cooling zone 3, the cooling gas in the middle chord air supply chamber impacts and cools the outer solid wall 19 of the pressure side through the pressure-side jet impact hole 16, and further enhances the heat exchange of the cooling zone through the turbulence of the pressure-side rib 2). Similarly, in the suction-side ribbed turbulence cooling zone 6, the cooling gas in the middle chord air supply chamber impacts and cools the outer solid wall 15 of the suction side through the suction-side jet impact hole 17, and further enhances the heat exchange of the cooling zone through the turbulence of the suction-side rib 21.

[0059] Cooling gas flows from the outlet of the pressure-side ribbed turbulence cooling zone 3 and the outlet of the suction-side ribbed turbulence cooling zone 6 into the trailing edge ribbed turbulence cooling zone 7.

[0060] In the trailing edge rib turbulence cooling zone 7, the cooling gas carries away the heat from the trailing edge region through the turbulence effect of the ribs, and finally flows out from the trailing edge rib turbulence cooling zone 7 and merges into the mainstream combustion gas.

[0061] The present invention will be further explained and illustrated below with a specific embodiment:

[0062] like Figures 1-6As shown, the blade with a multi-channel dual-jet swirl cooling structure in this embodiment includes: a leading edge dual-jet swirl cooling zone 1, a leading edge air supply chamber 2, a pressure-side rib turbulence cooling zone 3, a middle chord first air supply chamber 4, a middle chord second air supply chamber 5, a suction-side rib turbulence cooling zone 6, and a trailing edge rib turbulence cooling zone 7.

[0063] like Figure 2 As shown, multiple cooling structure units 8 are arranged along the blade height in the leading edge dual-jet cooling zone 1.

[0064] like Figure 2 , Figure 5 As shown, the outlet of the leading edge air supply chamber 2 is directly connected to the inlet of the pressure side cooling jet channel 9 and the inlet of the suction side cooling jet channel 10, respectively; the inlet of the leading edge vortex cooling chamber 11 is directly connected to the outlet of the pressure side cooling jet channel 9 and the outlet of the suction side cooling jet channel 10, respectively.

[0065] like Figure 3 , Figure 6 As shown, the outlet of the leading edge swirl cooling chamber 11 is connected to the inlet of the pressure-side secondary cooling channel 12 and the inlet of the suction-side secondary cooling channel 13, respectively; the inlet of the pressure-side rib turbulence cooling zone 3 and the inlet of the suction-side rib turbulence cooling zone 6 are connected to the outlet of the pressure-side secondary cooling channel 12 and the outlet of the suction-side secondary cooling channel 13, respectively; the flow cross-sectional areas of the pressure-side cooling jet channel 9, the suction-side cooling jet channel 10, the pressure-side secondary cooling channel 12, and the suction-side secondary cooling channel 13 are equal.

[0066] like Figures 2 to 6 As shown, the pressure-side ribbed turbulence cooling zone 3 is enclosed by the outer pressure-side solid wall 19 and the inner pressure-side solid wall 14, connected in the middle by the pressure-side ribbed 22. The suction-side ribbed turbulence cooling zone 6 is enclosed by the outer suction-side solid wall 15 and the inner suction-side solid wall 20, connected in the middle by the suction-side ribbed 21. Multiple rows of pressure-side jet impact holes 16 and suction-side jet impact holes 17 are respectively formed on the inner pressure-side solid wall 14 and the inner suction-side solid wall 20. The pressure-side ribbed turbulence cooling zone 3 is connected to the first air supply chamber 4 and the second air supply chamber 5 of the middle chord through the pressure-side jet impact holes 16; the suction-side ribbed turbulence cooling zone 6 is connected to the first air supply chamber 4 and the second air supply chamber 5 of the middle chord through the suction-side jet impact holes 17. The trailing edge rib turbulence cooling zone 7 is formed by the outer solid wall 19 on the pressure side and the outer solid wall 20 on the suction side, and is connected in the middle by the trailing edge rib 18. The inlet of the trailing edge rib turbulence cooling zone 7 is connected to the outlet of the pressure side rib turbulence cooling zone 3 and the outlet of the suction side rib turbulence cooling zone 6.

[0067] The cooling method for the aforementioned blades is as follows:

[0068] like Figure 2 As shown, the cooling gas in the leading edge air supply chamber 2 is injected into the leading edge swirling cooling chamber 11 through the pressure-side cooling jet channel 9 and the suction-side cooling jet channel 10. The arrows indicate the flow direction of the cooling gas. The cooling gas flows at high speed in the pressure-side cooling jet channel 9 and the suction-side cooling jet channel 10 to scour the outer solid wall of the blade, thereby achieving wall cooling of the leading edge region of the outer solid wall 19 on the pressure side and the outer solid wall 15 on the suction side. The cooling gas enters the leading edge swirling cooling chamber 11 and undergoes high-speed swirling motion. The thermal boundary layer is weakened and thinned by the shearing effect of the fluid rotation, which greatly enhances the local heat transfer intensity and effectively reduces the heat load in the leading edge region.

[0069] like Figure 3 As shown, the cooling air flows along the blade height direction in the leading-edge swirling cooling chamber 11, then turns 90 degrees and enters the pressure-side secondary cooling channel 12 and the suction-side secondary cooling channel 13. Similarly, during high-speed flow, it washes over the outer solid wall of the blade, achieving wall cooling again on the leading edge regions of the pressure-side outer solid wall 19 and the suction-side outer solid wall 15. The cooling air then exits the secondary cooling channels and enters the pressure-side ribbed turbulence cooling zone 3 and the suction-side ribbed turbulence cooling zone 6, respectively. This achieves multiple uses of the cooling air.

[0070] like Figure 2 and Figure 3 As shown, in the pressure-side rib turbulence cooling zone 3, the cooling gas in the first air supply chamber 4 and the second air supply chamber 5 of the middle chord impacts the outer solid wall 19 of the pressure side through the pressure-side jet impact hole 16, thereby achieving impact cooling of the outer solid wall 19 of the pressure side; similarly, in the suction-side rib turbulence cooling zone 6, the cooling gas in the first air supply chamber 4 and the second air supply chamber 5 of the middle chord impacts the outer solid wall 15 of the suction side through the suction-side jet impact hole 17, thereby achieving impact cooling of the outer solid wall 15 of the suction side.

[0071] The pressure-side rib 22 and suction-side rib 21 can respectively enhance the disturbance of the cooling air in the pressure-side rib turbulence cooling zone 3 and suction-side rib turbulence cooling zone 6, increase the turbulence characteristics of the cooling air, thereby significantly enhancing heat transfer, and also enhancing the structural strength of the blade.

[0072] The cooling air eventually flows from the outlet of the pressure-side ribbed turbulence cooling zone 3 and the outlet of the suction-side ribbed turbulence cooling zone 6 into the trailing edge ribbed turbulence cooling zone 7. Similarly, the cooling air will carry away more heat under the turbulence of the trailing edge ribs 18, and then flow out from the trailing edge into the mainstream.

[0073] like Figure 7As shown, this embodiment also provides a cooling structure unit in which cooling gas flows in the opposite direction to the blade height in the leading edge swirl cooling chamber 11, and then turns 90 degrees to enter the pressure-side secondary cooling channel 12 and the suction-side secondary cooling channel 13. This cooling structure unit makes the radial flow direction of the cooling gas in the leading edge swirl cooling chamber 11 of the moving blade opposite to the direction of the centrifugal force it receives.

[0074] like Figure 8 As shown, the present invention also provides a cooling structure unit with two secondary cooling channels on both the pressure side and the suction side. Cooling gas flows simultaneously in the leading-edge swirling cooling chamber 11 along the blade height direction and in the opposite direction, then turns 90 degrees and enters the pressure-side secondary cooling channel 12 and the suction-side secondary cooling channel 13 respectively. Unlike the two cooling structure units mentioned above, this cooling structure unit has a taller leading-edge swirling cooling chamber 11, thus providing a larger heat exchange area at the turbine blade leading edge, thereby enhancing the heat exchange effect. Furthermore, since the cooling gas flows in the leading-edge swirling cooling chamber 11 in the opposite direction to the blade height, to ensure the consistency of the cooling gas flow in the secondary cooling channels, the cross-sectional area of ​​the secondary cooling channel near the blade tip is designed to be 30%–40% of the cross-sectional area of ​​the cooling jet channel, and the cross-sectional area of ​​the secondary cooling channel near the blade root is designed to be 60%–70% of the cross-sectional area of ​​the cooling jet channel.

[0075] like Figure 9 , Figure 10 As shown, compared with traditional swirling cooling, the leading-edge dual jet in the structure of this invention can enhance the swirling characteristics of the cooling gas in the leading-edge swirling cooling cavity 11, increase the velocity gradient near the wall, further weaken the boundary layer thickness, and thus improve the cooling performance of the heat exchange target surface.

[0076] like Figure 11 As shown, the cooling gas flowing out of the leading edge swirl cooling chamber 11 can simultaneously form a wall jet in the pressure side secondary cooling channel and the suction side secondary cooling channel to perform secondary cooling on the leading edge pressure side and the leading edge suction side, thereby improving the utilization rate of the cooling gas.

[0077] like Figures 12 to 16 As shown, compared with conventional swirl cooling, the heat exchange area in the structure of this invention is increased by approximately 25%, thus allowing for a wider cooling area in the leading edge region of the turbine blade. Furthermore, the average Nusselt number of the heat exchange surface area in the structure of this invention is approximately 9% higher than that of conventional swirl cooling, meaning that the multi-channel dual-jet swirl cooling structure for gas turbine blades proposed in this invention has superior overall cooling performance. Simultaneously, the design of relatively independent cooling structure units in the structure of this invention avoids crossflow in the leading edge cooling chamber, resulting in more uniform heat exchange on the cooling target surface. In contrast, the crossflow in conventional swirl cooling reduces the utilization rate of the cooling jet and deteriorates the heat exchange uniformity of the chamber surface.

[0078] The above description is only a part of the embodiments of the present invention. Although some terms are used in the present invention, the possibility of using other terms is not excluded. The use of these terms is merely for the convenience of describing and explaining the essence of the present invention, and interpreting them as any kind of additional limitation would contradict the spirit of the present invention. The above description is only to further illustrate the content of the present invention through embodiments to facilitate easier understanding, but it does not mean that the embodiments of the present invention are limited to this. Any technical extension or re-creation based on the present invention is protected by the present invention.

Claims

1. A blade with a multi-channel dual-jet swirling cooling structure, characterized in that, It includes a leading edge double jet swirl cooling zone (1), a middle chord cooling zone, and a trailing edge rib turbulence cooling zone (7) located inside the blade; The leading edge dual-jet swirl cooling zone (1) includes a leading edge air supply chamber (2) that spans the blade height and a leading edge swirl cooling chamber (11). The two sides of the leading edge air supply chamber (2) are connected to the leading edge swirl cooling chamber (11) through several pressure-side cooling jet channels (9) and suction-side cooling jet channels (10), respectively. The middle chord cooling zone includes the middle chord air supply chamber, the middle chord pressure-side cooling channel, and the middle chord suction-side cooling channel; The pressure-side cooling channel of the middle chord is located between the outer solid wall (19) and the inner solid wall (14) of the pressure side, and several pressure-side jet impact holes (16) are arranged in an array on the inner solid wall (14) of the pressure side; the suction-side cooling channel of the middle chord is located between the outer solid wall (15) and the inner solid wall (20) of the suction side, and several suction-side jet impact holes (17) are arranged in an array on the inner solid wall (20) of the suction side; the air supply chamber of the middle chord is connected to the pressure-side cooling channel of the middle chord through the pressure-side jet impact holes (16), and is connected to the suction-side cooling channel of the middle chord through the suction-side jet impact holes (17); several ribs are provided in both the pressure-side cooling channel and the suction-side cooling channel of the middle chord; The trailing edge rib turbulence cooling zone (7) includes a trailing edge cooling channel located inside the trailing edge of the blade, and a number of trailing edge ribs (18) are provided in the trailing edge cooling channel. One side of the leading edge swirl cooling chamber (11) is connected to the middle chord pressure side cooling channel through the pressure side secondary cooling channel (12), and the other side is connected to the middle chord suction side cooling channel through the suction side secondary cooling channel (13). Both the pressure side secondary cooling channel (12) and the suction side secondary cooling channel (13) are connected to the starting end of the trailing edge cooling channel, and the end of the trailing edge cooling channel is connected to the cooling gas outlet on the blade.

2. The blade with a multi-channel dual-jet swirling cooling structure according to claim 1, characterized in that, The middle string air supply chamber includes several independent air supply chambers separated by chamber partitions. The two ends of the chamber partitions are fixedly connected to the inner solid wall (14) on the pressure side and the inner solid wall (20) on the suction side, respectively.

3. The blade with a multi-channel dual-jet swirling cooling structure according to claim 1, characterized in that, The inner walls of the leading edge swirling cooling chamber (11) and the leading edge air supply chamber (2) are both smooth curved surfaces.

4. The blade with a multi-channel dual-jet swirling cooling structure according to claim 1, characterized in that, The leading edge swirl cooling chamber (11) is cylindrical, and the pressure side cooling jet channel (9), the suction side cooling jet channel (10), the pressure side secondary cooling channel (12) and the suction side secondary cooling channel (13) are all located in the tangential direction of the leading edge swirl cooling chamber (11).

5. The blade with a multi-channel dual-jet swirling cooling structure according to claim 1, characterized in that, A pressure-side cooling jet channel (9), a suction-side cooling jet channel (10), a pressure-side secondary cooling channel (12), and a suction-side secondary cooling channel (13) constitute a cooling structure unit (8); the pressure-side secondary cooling channel (12) and the suction-side secondary cooling channel (13) are located on one side of the pressure-side cooling jet channel (9) and the suction-side cooling jet channel (10).

6. The blade with a multi-channel dual-jet swirling cooling structure according to claim 1, characterized in that, A pressure-side cooling jet channel (9), a suction-side cooling jet channel (10), two pressure-side secondary cooling channels (12) and two suction-side secondary cooling channels (13) constitute a cooling structure unit (8); the two pressure-side secondary cooling channels (12) are located on both sides of the pressure-side cooling jet channel (9) and the suction-side cooling jet channel (10), respectively, and the two suction-side secondary cooling channels (13) are located on both sides of the pressure-side cooling jet channel (9) and the suction-side cooling jet channel (10), respectively.

7. The blade with a multi-channel dual-jet swirling cooling structure according to claim 6, characterized in that, The cross-sectional area of ​​the pressure-side cooling jet channel (9) is equal to that of the suction-side cooling jet channel (10). The cross-sectional area of ​​the pressure-side secondary cooling channel (12) and the suction-side secondary cooling channel (13) on the blade root side is 30% to 40% of that of the pressure-side cooling jet channel (9). The cross-sectional area of ​​the pressure-side secondary cooling channel (12) and the suction-side secondary cooling channel (13) on the blade tip side is 60% to 70% of that of the pressure-side cooling jet channel (9).

8. The blade with a multi-channel dual-jet swirling cooling structure according to claim 1, characterized in that, The pressure-side cooling jet channel (9) and the suction-side cooling jet channel (10) are located at the same height; the pressure-side secondary cooling channel (12) and the suction-side secondary cooling channel (13) are located at the same height.

9. The blade with a multi-channel dual-jet swirling cooling structure according to claim 1, characterized in that, The pressure-side cooling jet channel (9), the suction-side cooling jet channel (10), the pressure-side secondary cooling channel (12), and the suction-side secondary cooling channel (13) are parallel to each other.

10. An engine, characterized in that, The blades include those with a multi-channel dual-jet swirling cooling structure as described in any one of claims 1 to 9.

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