A turbine blade having a biomimetic lobe-shaped regenerative cooling passage

Abstract

The application discloses a turbine blade with a bionic leaf-shaped regenerative cooling channel, which comprises an outlet cooling channel, a main leaf vein cooling channel, at least four secondary leaf vein cooling channels, at least two transition cooling channels and a plurality of branch leaf vein cooling channels. A cooling fluid inlet is used to introduce cooling fluid, which is uniformly delivered to the outlet cooling channel through the main leaf vein cooling channel, the secondary leaf vein cooling channel, the branch leaf vein cooling channel and the transition cooling channel in sequence, and finally discharged through two cooling fluid outlets to complete the cooling of the turbine blade. The application solves the problems of uneven blade cooling and poor overall cooling effect of the existing turbine blade with a single rotary cooling channel.

Description

[Technical Field]

[0001] This invention belongs to the field of turbine blade cooling channel technology, specifically relating to a turbine blade with a biomimetic leaf-shaped regenerative cooling channel. [Background Technology]

[0002] With the development of aviation technology, the performance of turbine-based combined cycle (TBCC) engines has been continuously improving, leading to a sustained increase in turbine inlet temperature and significantly increasing the thermal load on turbine blades. Under these circumstances, efficient cooling of the high-temperature components of the turbine becomes particularly important. In recent years, the improvement in engine performance is partly attributed to advancements in cooling technology. Common turbine blade cooling methods include internal convection cooling and external film cooling. In internal convection cooling, the internal cooling channel often uses a single rotating cooling channel. However, this rotating cooling channel is limited by factors such as limited heat exchange area and insufficient contact between the cool air and the hot wall surface, resulting in uneven cooling of the turbine blades, especially the blade body. Furthermore, the temperature at the blade tip, leading edge, and trailing edge remains essentially unchanged after cooling. Therefore, the cooling of TBCC engine turbine blades remains a pressing technical problem, as it has a significant impact on improving the performance and reliability of TBCC engines. [Summary of the Invention]

[0003] The purpose of this invention is to provide a turbine blade with a biomimetic leaf-shaped regenerative cooling channel to solve the problem of uneven cooling and poor overall cooling effect when using a single rotating cooling channel for existing turbine blades.

[0004] The present invention adopts the following technical solution: a turbine blade with a biomimetic leaf-shaped regenerative cooling channel, comprising a turbine blade and a biomimetic leaf-shaped regenerative cooling channel disposed within the blade, wherein the turbine blade has a blade body; the bottom end and the top end of the blade body are the blade root and the blade tip, respectively; the two sides of the blade body are the blade leading edge and the blade trailing edge, respectively.

[0005] The biomimetic leaf-shaped regenerative cooling channel includes:

[0006] An outlet cooling channel is located inside the blade, which is a cooling channel that runs through the edges of the blade's leading edge, tip, and trailing edge; the two intersections of the outlet cooling channel with the blade root are coolant outlets.

[0007] A main vein cooling channel is vertically positioned at the center of the leaf body; one end of the main vein cooling channel intersects with the leaf root at the coolant inlet, while the other end is not connected to the outlet cooling channel.

[0008] At least four secondary leaf vein cooling channels are symmetrically arranged on the left and right sides of the main leaf vein cooling channel, and all are inclined towards the leaf tip; one end of each secondary leaf vein cooling channel is connected to the main leaf vein cooling channel, and the other end is not connected to the outlet cooling channel.

[0009] At least two transition cooling channels are symmetrically arranged on the left and right sides of the main leaf vein cooling channel; each transition cooling channel is located between two adjacent secondary leaf vein cooling channels; one end of each transition cooling channel is connected to the outlet cooling channel, and the other end is not connected to the main leaf vein cooling channel.

[0010] Multiple branch leaf vein cooling channels are channels that branch out from the upper and lower sides of each secondary leaf vein cooling channel; among them, each branch leaf vein cooling channel below the two secondary leaf vein cooling channels near the leaf root extends to both sides and connects to the outlet cooling channel; all branch leaf vein cooling channels between each secondary leaf vein cooling channel and the adjacent transition cooling channel converge into the transition cooling channel; each branch leaf vein cooling channel above the two secondary leaf vein cooling channels near the leaf tip is connected to the outlet cooling channel;

[0011] The cross-sectional area of ​​the cooling channels of the main vein, secondary vein, transitional cooling channels, and branch veins decreases progressively.

[0012] The coolant inlet is used to introduce the cooling fluid, which is then uniformly delivered to the outlet cooling channel through the main blade cooling channel, secondary blade cooling channel, branch blade cooling channel and transition cooling channel. Finally, the coolant is discharged through two coolant outlets to complete the cooling of the turbine blades.

[0013] Furthermore, the secondary leaf vein cooling channels located on the same side as the main leaf vein cooling channel are parallel to each other and spaced apart.

[0014] Furthermore, each transition cooling channel is parallel to the adjacent secondary vein cooling channel.

[0015] Furthermore, each transition cooling channel is located in the middle between two adjacent secondary vein cooling channels.

[0016] Furthermore, the cooling channels of each branch vein located on the same side as each secondary vein cooling channel are parallel to each other.

[0017] Furthermore, the main vein cooling channel, secondary vein cooling channel, transition cooling channel, and branch vein cooling channel have the same cross-sectional shape;

[0018] When the cross-sectional shape is rectangular, let the lengths of the long sides of the cross-sections of the main vein cooling channel, secondary vein cooling channel, transition cooling channel and branch vein cooling channel be L_main, L_secondary, L_transition and L_branch respectively, then L_main > L_secondary > L_transition > L_branch.

[0019] Furthermore, the length of the long side of the cross-section of each branch vein cooling channel is equal to the spacing width between two adjacent branch vein cooling channels.

[0020] Furthermore, when the cross-sectional shape is square, let the side lengths of the cross-sections of the main vein cooling channel, secondary vein cooling channel, transition cooling channel, and branch vein cooling channel be l_main, l_secondary, l_transition, and l_branch respectively, then l_main > l_secondary > l_transition > l_branch.

[0021] Furthermore, when the cross-sectional shape is circular, let the diameters of the main vein cooling channel, secondary vein cooling channel, transition cooling channel, and branch vein cooling channel be R_main, R_secondary, R_transition, and R_branch, respectively. Then, R_main > R_secondary > R_transition > R_branch.

[0022] Furthermore, the cross-sectional dimensions should meet the following requirements:

[0023] Ltransition > 2Lbranch, Lsecondary > 2Ltransition, Lmain > 2Lsecondary;

[0024] Alternatively, l transition > 2l branch, l secondary > 2l transition, l primary > 2l secondary;

[0025] Alternatively, Rtransition > 2Rbranch, Rsecondary > 2Rtransition, Rmain > 2Rsecondary.

[0026] The beneficial effects of this invention are:

[0027] First, this invention incorporates multiple cooling channels within the turbine blade body, with the positions of each channel mimicking the vein arrangement of a leaf. The inlet collection chamber of the regenerative cooling channel is arranged similarly to the main vein of a leaf, i.e., the main vein cooling channel. The remaining cooling channels are arranged mimicking the secondary and lateral veins of a leaf, i.e., secondary vein cooling channels and lateral vein cooling channels. The dimensions of each cooling channel are determined based on the required pressure difference. The cooling fluid within the secondary vein cooling channels flows independently in multiples, causing the flow boundary layer and thermal boundary layer to redevelop. This redevelopment of the boundary layers leads to an increase in the convective heat transfer coefficient within each cooling channel, thereby enhancing the cooling effect.

[0028] Secondly, the regenerative cooling channel inside the turbine blade adopts a layout of one coolant inlet and two coolant outlets, which realizes the uniformity of the flow rate of the internal cooling fluid, achieves the purpose of uniform cooling, and also improves the efficiency of convective heat transfer.

[0029] In addition, the cooling fluid after cooling the turbine blades is finally transported to the combustion chamber for combustion. Since the cooling fluid undergoes decomposition during the cooling process, it can release the heat absorbed during decomposition when it enters the combustion chamber for combustion, thus improving the energy utilization rate. [Attached Image Description]

[0030] Figure 1 This is a schematic diagram of the structure of a turbine blade with a biomimetic leaf-shaped regenerative cooling channel according to the present invention;

[0031] Figure 2 This is a schematic diagram of the layout of the regenerative cooling channels inside a turbine blade with a biomimetic leaf-shaped regenerative cooling channel according to the present invention.

[0032] Among them, 101. Leading edge of the blade, 102. Blade, 103. Root of the blade, 104. Tip of the blade, 105. Tail edge of the blade; 201. Main vein cooling channel, 202. Secondary vein cooling channel, 203. Transition cooling channel, 204. Branch vein cooling channel, 205. Outlet cooling channel, 206. Coolant inlet, 207. Coolant outlet.

Detailed Implementation Methods

[0033] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments.

[0034] This invention provides a turbine blade with a biomimetic leaf-shaped regenerative cooling channel, such as... Figure 1 As shown, the device includes turbine blades and a biomimetic leaf-shaped regenerative cooling channel disposed within the blades. The turbine blade has a blade body 102, one end of which is a blade root 103, and the other end is a blade tip 104. One side of the blade body 102 is a blade leading edge 101, and the other side is a blade trailing edge 105.

[0035] like Figure 2 As shown, both the turbine blade body and the cooling channel are axisymmetric structures. The biomimetic blade-shaped regenerative cooling channel specifically includes:

[0036] An outlet cooling channel 205 is provided inside the blade body 102. It is a cooling channel that runs through the edges of the blade leading edge 101, blade tip 104 and blade trailing edge 105. The cooling channel is in an inverted U-shape. The two intersections of the outlet cooling channel 205 and the blade root 103 are coolant outlets 207.

[0037] A main vein cooling channel 201 is vertically positioned at the center of the blade body 102, running from the blade root 103 to the blade tip 104. One end of the main vein cooling channel 201 intersects with the blade root 103 at the coolant inlet 206, while the other end is not connected to the outlet cooling channel 205. Since the main vein cooling channel 201 acts as the inlet collection chamber for the cooling fluid at this location, it is essential to ensure that the main vein cooling channel 201 is located in the middle of the blade. This guarantees uniform flow distribution and achieves uniform cooling of the blade. The cooling fluid in the turbine blade adopts a one-in-two-out configuration, ensuring that the flow trend of the cooling fluid in the upper and lower parts of the turbine blade is essentially the same.

[0038] At least four secondary leaf vein cooling channels 202 are symmetrically arranged on the left and right sides of the main leaf vein cooling channel 201, and are all inclined towards the leaf tip 104. One end of each secondary leaf vein cooling channel 202 is connected to the main leaf vein cooling channel 201, and the other end is not connected to the outlet cooling channel 205.

[0039] At least two transition cooling channels 203 are symmetrically arranged on the left and right sides of the main leaf vein cooling channel 201; each transition cooling channel 203 is located between two adjacent secondary leaf vein cooling channels 202; one end of each transition cooling channel 203 is connected to the outlet cooling channel 205, and the other end is not connected to the main leaf vein cooling channel 201.

[0040] Multiple branch vein cooling channels 204 branch out from the upper and lower sides of each secondary vein cooling channel 202. Specifically, each branch vein cooling channel 204 below the two secondary vein cooling channels 202 near the leaf root 103 extends to the left and right sides and connects to the outlet cooling channel 205. All branch vein cooling channels 204 between each secondary vein cooling channel 202 and the adjacent transition cooling channel 203 converge into the transition cooling channel 203. Each branch vein cooling channel 204 above the two secondary vein cooling channels 202 near the leaf tip 104 connects to the outlet cooling channel 205. The layout of the branch vein cooling channels 204 is mainly based on the shape of the secondary vein cooling channels 202 and the blade. During the layout process, the length of each cooling channel should not be too long, and the inclination angle should not be too large.

[0041] The cross-sectional areas of the main blade cooling channel 201, secondary blade cooling channel 202, transition cooling channel 203, and branch blade cooling channel 204 decrease progressively. This arrangement ensures a suitable pressure difference between the different channels, thereby driving the flow of coolant. The multi-stage distributed cooling channels can maximize the exchange of convective heat transfer area, change its heat exchange boundary, and ultimately achieve uniform cooling of the turbine blades.

[0042] In use, the coolant inlet 206 is used to introduce the cooling fluid, which is then uniformly delivered to the outlet cooling channel 205 through the main blade cooling channel 201, the secondary blade cooling channel 202, the branch blade cooling channel 204 and the transition cooling channel 203 in sequence, and finally discharged through the two coolant outlets 207 to achieve the cooling of the turbine blades.

[0043] In some embodiments, the secondary vein cooling channels 202 located on the same side of the main vein cooling channel 201 are parallel to each other and spaced apart. The parallel and spaced arrangement allows the cooling fluid to flow uniformly within the channels, producing a uniform cooling effect, and the parallel and spaced arrangement helps to prevent localized overheating.

[0044] In some embodiments, each transition cooling channel 203 is parallel to the adjacent secondary vein cooling channel 202. The parallel arrangement of the transition cooling channels 203 and the secondary vein cooling channels 202 facilitates modular design, allowing for the addition or reduction of the number of cooling channels as needed.

[0045] In some embodiments, each transition cooling channel 203 is located in the middle between two adjacent secondary vein cooling channels 202. Placing the transition cooling channel 203 in the middle ensures uniform distribution of cooling fluid, and its central location reduces the flow distance of the cooling fluid within the channel, thereby reducing pressure loss.

[0046] In some embodiments, the branch vein cooling channels 204 on the same side of each secondary vein cooling channel 202 are parallel to each other.

[0047] In some embodiments, the main vein cooling channel 201, the secondary vein cooling channel 202, the transition cooling channel 203, and the branch vein cooling channel 204 have the same cross-sectional shape. For example, the cross-sectional shape can be rectangular, square, or circular.

[0048] When the cross-sectional shape is rectangular, the lengths of the long sides of the cross-sections of the main vein cooling channel 201, the secondary vein cooling channel 202, the transition cooling channel 203, and the branch vein cooling channel 204 are L_main, L_secondary, L_transition, and L_branch, respectively, then L_main > L_secondary > L_transition > L_branch; the width of the cross-section is designed to adapt to the thickness of the blade.

[0049] In some embodiments, when the cross-sectional shape is rectangular, the length of the long side of each branch vein cooling channel 204 is equal to the spacing width between two adjacent branch vein cooling channels 204. This arrangement can achieve uniform cooling and expand the cooling range.

[0050] In some embodiments, when the cross-sectional shape is square, the side lengths of the cross-sections of the main vein cooling channel 201, the secondary vein cooling channel 202, the transition cooling channel 203, and the branch vein cooling channel 204 are l_main, l_secondary, l_transition, and l_branch, respectively, then l_main > l_secondary > l_transition > l_branch.

[0051] In some embodiments, when the cross-sectional shape is circular, the diameters of the cross-sections of the main vein cooling channel 201, the secondary vein cooling channel 202, the transition cooling channel 203, and the branch vein cooling channel 204 are R_main, R_secondary, R_transition, and R_branch, respectively, then R_main > R_secondary > R_transition > R_branch.

[0052] In some embodiments, the cross-sectional dimensions are set to meet the following requirements:

[0053] Ltransition > 2Lbranch, Lsecondary > 2Ltransition, Lmain > 2Lsecondary;

[0054] Alternatively, l transition > 2l branch, l secondary > 2l transition, l primary > 2l secondary;

[0055] Alternatively, Rtransition > 2Rbranch, Rsecondary > 2Rtransition, Rmain > 2Rsecondary.

[0056] Setting the above dimensions to a ratio of two or more ensures a reasonable pressure difference between the two cooling channels and the flow rate of the cooling fluid within the channels.

[0057] When arranging the cooling channels inside the turbine blades, the channels should not be designed to be too narrow or too wide. Overly narrow channels will result in higher flow resistance, while overly wide channels may cause the cooling fluid to have excessively high velocity in the center of the channel and insufficient velocity near the channel wall, thus reducing heat exchange efficiency. To ensure pressure drop in the cooling channels inside the turbine blades, this invention employs a large number of parallel branch-vein cooling channels 204, with each branch-vein cooling channel 204 having a relatively short flow length.

[0058] Taking four secondary blade cooling channels 202 as an example, the main blade cooling channel 201, secondary blade cooling channel 202, transition cooling channel 203, and branch blade cooling channel 204 all have rectangular cross-sectional shapes. Let Lmain = X, Lsecondary = X / 4, Ltransition = X / 8, and Lbranch = X / 16. It can be seen that the secondary blade cooling channel 202 is in a low-pressure region compared to the main blade cooling channel 201. The fluid flow is driven by the pressure difference. The pressure difference between the secondary blade cooling channel 202 and the main blade cooling channel 201 ensures the flow velocity and stability of the cooling fluid. The secondary blade cooling channel 202 is smaller than the main blade cooling channel 201. Therefore, when the cooling fluid enters the secondary blade cooling channel 202 from the main blade cooling channel 201 in four separate channels, the uniformity of the cooling fluid distribution is ensured, thereby guaranteeing uniform cooling of the turbine blades.

[0059] Lbranch = Lsecondary / 4. This arrangement ensures a pressure gradient between the secondary vein cooling channel 202 and the secondary vein cooling channel 204 during the cooling fluid flow. This guarantees both the flow rate of the cooling fluid and its uniform entry into each secondary vein cooling channel 204, thereby improving the convective heat transfer area and the cooling efficiency of the blades. Ltransition = Lsecondary / 2. The transition cooling channel 203 is connected to the outlet cooling channel 205, therefore the pressure in the transition cooling channel 203 is relatively low. Due to the pressure difference, the cooling fluid flows from the secondary vein cooling channel 202 through each secondary vein cooling channel 204 and then merges into the transition cooling channel 203, finally exiting the turbine blades from the outlet cooling channel 205.

[0060] Both coolant outlets 207 can also be connected to the combustion chamber. When the cooling fluid is kerosene, the kerosene that has cooled the turbine blades will flow out of the two coolant outlets 207 and enter the combustion chamber for combustion. The kerosene flowing out of the turbine blades will enter the combustion chamber through external pipes and be burned. Since the kerosene carries away the heat from the turbine blades when cooling them, the kerosene can undergo cracking. When it enters the combustion chamber for combustion, it can release the heat absorbed during cracking, improving energy utilization and achieving regenerative cooling.

[0061] This invention relates to a turbine blade suitable for TBCC engines and featuring a biomimetic leaf-shaped regenerative cooling channel. The cooling channels are arranged to mimic the shape of a leaf vein, with the main vein cooling channel 201, which serves as the inlet liquid collection chamber, positioned similarly to the main vein of a leaf. The remaining cooling channels are arranged in accordance with the secondary and lateral veins of a leaf.

[0062] Multiple turbine blades are evenly arranged on the turbine engine to form turbine blade channels. The turbine blades are in a thermal environment formed by the high-temperature main combustion gas flow. The root of the turbine blade is provided with a coolant inlet 206 and a coolant outlet 207. The pre-cooling cooling fluid flows in from the coolant inlet 206, flows through each stage of cooling channels, and removes the heat from the turbine blade through heat exchangers. It then flows out of the turbine blade from the coolant outlet 207, thereby achieving the effect of cooling the turbine blade.

[0063] Example: This example is for Figure 2 The cooling effect of the turbine blade with the biomimetic leaf-shaped regenerative cooling channel shown was verified by simulation.

[0064] The cooling fluid was kerosene. Three different kerosene flow rates were used in the simulation analysis. The specific experimental data are shown in Table 1.

[0065] Table 1. Simulation conditions and results of kerosene cooling

[0066]

[0067] Table 1 shows the simulated operating conditions of the turbine blade with a biomimetic leaf-shaped regenerative cooling channel in this embodiment using kerosene cooling. As can be seen from Table 1, different kerosene flow rates can all achieve good cooling effects on the blade. Generally, increasing the kerosene flow rate will also increase the cooling temperature difference. In actual use, the kerosene flow rate can be adjusted according to the cooling requirements of the blade.

[0068] Comparative Example: This comparative example simulates and verifies the cooling effect of a turbine blade using a single rotary cooling channel. In this example, the cooling fluid in the single cooling channel is kerosene with a single inlet and outlet, and the kerosene flow rate is set to 0.5 kg / s. The initial surface temperature of the turbine blade is set to 1000 K, and the convective heat transfer coefficient of the turbine blade surface is set to 2000 W / (m²). 2 K), the kerosene inlet temperature is 300K.

[0069] The simulation results of the comparative scale show that the temperature differences at the blade body, blade tip, blade leading edge, and blade trailing edge before and after turbine blade cooling are shown in Table 2.

[0070] The data in Table 2 show that the temperature difference across the blade ranges from 70K to 350K, indicating a highly uneven cooling effect. The temperature difference at the blade tip varies less, and the cooling effect is also uneven. The temperatures at the leading and trailing edges of the blade remain largely unchanged, indicating an unsatisfactory cooling effect.

[0071] Table 2 Comparison of cooling effects between the embodiments and the comparative examples

[0072]

[0073] Because existing technologies commonly use single cooling channels in series cooling, a large cross-sectional area leads to excessively high flow velocities within the channel. Specifically, the cooling medium flows at a high velocity in the center of the first half of the channel, while the velocity near the wall is too low, resulting in low heat exchange efficiency. Conversely, the flow velocity decreases in the latter half of the channel, thus improving heat exchange efficiency. Reducing the cross-sectional area of ​​the cooling channel and increasing its length causes the cooling medium to absorb more heat in the earlier channels, reducing the cooling efficiency of subsequent channels and leading to uneven cooling. Furthermore, blockage or damage to any part of the series-connected channels can cause the entire cooling system to fail.

[0074] The cooling effect of the comparative example and this embodiment at a kerosene flow rate of 0.5 kg / s was compared. Table 2 shows the temperature difference of various parts of the blade after cooling in this embodiment. The data in Table 2 shows that the temperature difference before and after cooling in this embodiment is 180 K to 220 K, indicating a good and uniform cooling effect. The cooling effect at the blade tip is more uniform compared to the comparative example. Furthermore, because this application arranges the outlet cooling channel 205 around the turbine blade, the cooling effect near the leading and trailing edges of the blade in this embodiment is also improved compared to the comparative example.

[0075] Because the flow of cooling fluid in a single cooling channel is driven solely by the pressure difference between the inlet and outlet, the biomimetic leaf-shaped regenerative cooling channel of this invention drives the cooling fluid in different regions of the turbine blades by varying pressure differences. Furthermore, compared to a single channel, the flow boundary layer and thermal boundary layer exhibit more significant changes. The one-inlet, two-outlet layout achieves enhanced cooling and uniform cooling. Simultaneously, the biomimetic leaf-shaped regenerative cooling channel used in this invention is a parallel cooling system. This parallel cooling channel layout ensures sufficient cooling fluid in each channel, improving cooling efficiency. Moreover, even if one channel fails, the others can continue to operate, preventing complete failure of the cooling system.

Claims

1. A turbine blade with a biomimetic leaf-shaped regenerative cooling channel, characterized in that, The invention includes turbine blades and a biomimetic leaf-shaped regenerative cooling channel disposed within the blades. The turbine blades have a blade body (102); the bottom end and the top end of the blade body (102) are the blade root (103) and the blade tip (104), respectively; the two sides of the blade body (102) are the blade leading edge (101) and the blade trailing edge (105), respectively. The biomimetic leaf-shaped regenerative cooling channel includes: An outlet cooling channel (205) is provided inside the blade (102), which is a cooling channel that runs through the edge of the blade leading edge (101), the blade tip (104) and the blade trailing edge (105); the two intersections of the outlet cooling channel (205) and the blade root (103) are both coolant outlets (207); A main vein cooling channel (201) is vertically set at the center of the inside of the leaf body (102); one end of the main vein cooling channel (201) intersects with the leaf root (103) at the coolant inlet (206), and the other end is not connected to the outlet cooling channel (205); At least four secondary vein cooling channels (202) are symmetrically arranged on the left and right sides of the main vein cooling channel (201), and all are inclined towards the leaf tip (104); one end of each secondary vein cooling channel (202) is connected to the main vein cooling channel (201), and the other end is not connected to the outlet cooling channel (205); At least two transition cooling channels (203) are symmetrically arranged on the left and right sides of the main leaf vein cooling channel (201); each transition cooling channel (203) is located between two adjacent secondary leaf vein cooling channels (202); one end of each transition cooling channel (203) is connected to the outlet cooling channel (205), and the other end is not connected to the main leaf vein cooling channel (201); Multiple branch vein cooling channels (204) are channels branching out from the upper and lower sides of each of the secondary vein cooling channels (202); wherein, each branch vein cooling channel (204) below the two secondary vein cooling channels (202) near the leaf root (103) extends to both sides and connects to the outlet cooling channel (205); each branch vein cooling channel (204) between each secondary vein cooling channel (202) and the adjacent transition cooling channel (203) converges to the transition cooling channel (203); each branch vein cooling channel (204) above the two secondary vein cooling channels (202) near the leaf tip (104) is connected to the outlet cooling channel (205); The cross-sectional areas of the main vein cooling channel (201), secondary vein cooling channel (202), transition cooling channel (203) and branch vein cooling channel (204) decrease progressively. The coolant inlet (206) is used to introduce cooling fluid, which is then uniformly transported to the outlet cooling channel (205) through the main blade cooling channel (201), the secondary blade cooling channel (202), the branch blade cooling channel (204), and the transition cooling channel (203) in sequence, and finally discharged through the two coolant outlets (207) to complete the cooling of the turbine blades.

2. A turbine blade with a biomimetic leaf-shaped regenerative cooling channel as described in claim 1, characterized in that, The secondary leaf vein cooling channels (202) located on the same side as the main leaf vein cooling channel (201) are parallel to each other and spaced apart.

3. A turbine blade with a biomimetic leaf-shaped regenerative cooling channel as described in claim 2, characterized in that, Each of the aforementioned transition cooling channels (203) is parallel to the adjacent of the aforementioned secondary vein cooling channels (202).

4. A turbine blade with a biomimetic leaf-shaped regenerative cooling channel as described in claim 3, characterized in that, Each of the aforementioned transition cooling channels (203) is located in the middle between two adjacent secondary vein cooling channels (202).

5. A turbine blade with a biomimetic leaf-shaped regenerative cooling channel as described in claim 1 or 2, characterized in that, The branch vein cooling channels (204) located on the same side of each secondary vein cooling channel (202) are parallel to each other.

6. A turbine blade with a biomimetic leaf-shaped regenerative cooling channel as described in claim 1 or 2, characterized in that, The main leaf vein cooling channel (201), secondary leaf vein cooling channel (202), transition cooling channel (203) and branch leaf vein cooling channel (204) have the same cross-sectional shape; When the cross-sectional shape is rectangular, the lengths of the long sides of the cross-sections of the main vein cooling channel (201), secondary vein cooling channel (202), transition cooling channel (203) and branch vein cooling channel (204) are L main, L secondary, L transition and L branch, respectively, then L main > L secondary > L transition > L branch.

7. A turbine blade with a biomimetic leaf-shaped regenerative cooling channel as described in claim 6, characterized in that, The length of the long side of the cross section of each of the branch vein cooling channels (204) is equal to the spacing width between two adjacent branch vein cooling channels (204).

8. A turbine blade with a biomimetic leaf-shaped regenerative cooling channel as described in claim 6, characterized in that, When the cross-sectional shape is square, let the side lengths of the cross-sections of the main vein cooling channel (201), secondary vein cooling channel (202), transition cooling channel (203) and branch vein cooling channel (204) be lmain, lsecondary, ltransition and lbranch respectively, then lmain > lsecondary > ltransition > lbranch.

9. A turbine blade with a biomimetic leaf-shaped regenerative cooling channel as described in claim 8, characterized in that, When the cross-sectional shape is circular, let the diameter of the cross-section of the main vein cooling channel (201), the secondary vein cooling channel (202), the transition cooling channel (203), and the branch vein cooling channel (204) be R_main, R_secondary, R_transition, and R_branch respectively, then R_main > R_secondary > R_transition > R_branch.

10. A turbine blade with a biomimetic leaf-shaped regenerative cooling channel as described in claim 9, characterized in that, The cross-sectional dimensions are set to meet the following requirements: Ltransition > 2Lbranch, Lsecondary > 2Ltransition, Lmain > 2Lsecondary; Alternatively, l transition > 2l branch, l secondary > 2l transition, l primary > 2l secondary; Alternatively, Rtransition > 2Rbranch, Rsecondary > 2Rtransition, Rmain > 2Rsecondary.

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