A new type of anti-pulsation high-damping film cooling structure and layout method for gas / hydrogen turbine cascade

Abstract

This invention discloses a novel anti-pulsation, high-damping film cooling structure and layout method for gas / hydrogen turbine blade cascades, including two configurations: symmetrical valve islands and asymmetrical valve islands. By embedding several Tesla valve island structures within the film cooling orifices, precise stratified control of airflow at the microscale and unidirectional low-resistance flow of cool gas are achieved. The intelligent and efficient cooling layout method of this invention, based on the turbine blade cascade flow field characteristics and vortex distribution features, precisely controls the anti-pulsation performance and cooling capacity of the film cooling orifices through a zoned application strategy and flow field adaptive methods, providing a theoretical basis and technical support for the efficient cooling layout design of gas turbine and hydrogen turbine blade cascades and the development of advanced cooling systems.

Description

Technical Field

[0001] This invention belongs to the field of aerodynamic heat transfer and high-efficiency thermal protection design technology for gas turbine and hydrogen turbine blade cascades, and specifically relates to the anti-pulsation high-damping film pore configuration and intelligent and efficient layout method of turbine blade cascade with built-in Tesla valve island structure. Background Technology

[0002] Replacing traditional carbon-based fossil fuels with low-carbon / zero-carbon fuels has become an effective way for the gas turbine industry to reduce carbon emissions at the source. Hydrogen, as a carbon-free clean fuel, is the most promising lightweight, high-calorific-value fuel for achieving low-carbon or even zero-carbon emissions from gas turbines. Compared to traditional fossil fuel combustion, hydrogen-blended / all-hydrogen combustion results in more significant pressure pulsation and velocity non-uniformity in the combustion gas. The dramatic increase in water content in the combustion products of hydrogen-blended / all-hydrogen combustion leads to a significant increase in the overall specific heat capacity of the combustion gas, severely affecting the heat transfer characteristics of the downstream turbine. In a highly pulsating and non-uniform operating environment, high-temperature combustion gas can easily invade the turbine disk cavity through discrete film vents in the blade cascades, causing overheating and thermal damage to the turbine disk cavity material. Furthermore, in the typical Brayton cycle of a gas turbine, increasing the turbine inlet temperature can significantly improve cycle thermal efficiency and thrust-to-weight ratio. Currently, the turbine inlet temperature of high-performance gas turbines / aero engines in service has exceeded 2200K, and the extreme high temperature far exceeds the allowable temperature of single-crystal nickel-based alloys. The high thermal failure risk of the turbine blade cascades seriously challenges the operational safety and service life of gas turbines / aero engines.

[0003] High-temperature turbines commonly employ film cooling (FSL) technology to ensure the safe and reliable operation of turbine blades in extreme high-temperature and high-pressure environments. This involves densely distributing tiny film cooling holes on the turbine blade surface, allowing relatively low-temperature, high-pressure gas to pass through these holes and form a cryogenic film layer on the combustion gas side, effectively isolating the high-temperature combustion gas. Currently, research on turbine blade FSL configurations focuses on high cooling efficiency and strong diffusion in ideal, pulsation-free environments. There are still no anti-pulsation, high-damping FSL configurations or intelligent, efficient layout methods applicable to gas turbine and hydrogen turbine blades. Summary of the Invention

[0004] To overcome the shortcomings of the prior art, the present invention aims to provide a novel anti-pulsation high-damping film cooling structure and layout method for gas / hydrogen turbine blades. Addressing the urgent need to prevent gas from intruding into the disk cavity through film cooling holes in strongly pulsating and non-uniform operating environments and to develop efficient turbine cooling technologies, this invention innovatively designs a unidirectional flow film cooling hole configuration with an integrated Tesla valve island structure and a turbine blade cooling layout, providing a theoretical basis and technical support for the design of efficient cooling layouts for gas and hydrogen turbine blades and the development of advanced cooling systems.

[0005] To achieve the above objectives, the technical solution adopted by the present invention is as follows: In a first aspect, the present invention provides a novel anti-pulsation high-damping film cooling structure for gas / hydrogen turbine blades, which mainly involves setting a bypass to form a Tesla valve island structure for a traditional cylindrical film cooling hole; in the Tesla valve island structure, the traditional cylindrical film cooling hole is used as the main flow channel for cold air, and the bypass is used as the secondary flow channel for the valve island, with the inlet and outlet of the secondary flow channel for the valve island connected to the main flow channel for cold air.

[0006] In one embodiment, the Tesla valve island structure can be formed by bypassing only some of the conventional cylindrical film air holes in the turbine blade cascade, while the remaining conventional cylindrical film air holes can remain unchanged.

[0007] In one embodiment, when the blade thickness is sufficient, more bypasses can be provided for a single conventional cylindrical film air hole, thereby forming multiple Tesla valve island structures, which are obviously distributed along the airflow direction.

[0008] In one embodiment, each Tesla valve island structure is formed by two bypasses arranged on a conventional cylindrical film orifice. Along the airflow direction, the bypasses are smoothly connected by an upstream arc segment and a downstream straight segment. Based on the functional requirements of the film orifice, the Tesla valve island structure includes two basic configurations: a symmetrical valve island configuration and an asymmetrical valve island configuration. In the symmetrical valve island configuration, the two bypasses are symmetrically arranged along the main cold air flow channel on the conventional cylindrical film orifice, and the two bypasses can be on the same plane or on different planes. In the asymmetrical valve island configuration, the two bypasses are asymmetrically arranged along the main cold air flow channel on the conventional cylindrical film orifice, and the two bypasses can be on the same plane or on different planes. Furthermore, the asymmetrical arrangement of the asymmetrical valve island configuration includes both differences in the shape / parameters of the two bypasses and differences in their connection positions (inlet and outlet), and can simultaneously possess both of these differences.

[0009] In one embodiment, the inlet and outlet of the film membrane orifice in the symmetrical valve island configuration Tesla valve island structure, and the inlet and outlet of the film membrane orifice in the asymmetrical valve island configuration Tesla valve island structure are both directly located in the main cold air channel; the two bypasses of the symmetrical valve island configuration Tesla valve island structure are the first valve island secondary flow channel, and the two bypasses of the asymmetrical valve island configuration Tesla valve island structure are the second valve island secondary flow channel and the third valve island secondary flow channel. Along the airflow direction, the outlet of the second valve island secondary flow channel is located between the inlet and outlet of the third valve island secondary flow channel, and the inlet of the third valve island secondary flow channel is located between the inlet and outlet of the second valve island secondary flow channel.

[0010] In one embodiment, the diameters D1 and D2 of the main cooling air duct can be determined according to actual cooling requirements, preferably ranging from 0.5 to 1.5 mm; the distance between the inlet of the film cooling hole and the inlet of the secondary flow channel of the valve island is L1, which can be designed according to the actual turbine blade wall thickness; the diameter d1 of the first secondary flow channel of the valve island can be determined according to the degree of pressure pulsation, ranging from 0.5 to 1.5 mm; the diameters d2 and d3 of the second and third secondary flow channels of the valve island can be determined according to the degree of pressure pulsation, both ranging from 0.5 to 1.5 mm, and d2 and d3 can be the same or different.

[0011] The angle between the outlet of the secondary flow channel of the first valve island and the main flow channel of the cold air The angle between the outlet of the secondary flow channel of the second valve island and the main flow channel of the cold air. and the angle between the outlet of the secondary flow channel of the third valve island and the main flow channel of the cold air. The values ​​range for all values ​​from 25° to 50°. and They can be the same or different.

[0012] The inner radius r1 and outer radius r2 of the arc segment of the first valve island secondary flow channel can be designed according to the actual turbine blade wall thickness and the diameter d1 of the first valve island secondary flow channel. The range of r1 is 0.8d1~1.5d1, and the range of r2 is 1.8d1~2.5d1.

[0013] The inner radius r3 and outer radius r4 of the arc segment of the second valve island secondary flow channel can be designed according to the actual turbine blade wall thickness and the diameter d2 of the second valve island secondary flow channel. The range of r3 is 0.8d2~1.5d2, and the range of r4 is 1.8d2~2.5d2.

[0014] The inner radius r5 and outer radius r6 of the arc segment of the third valve island secondary flow channel can be designed according to the actual turbine blade wall thickness and the diameter d3 of the third valve island secondary flow channel. The range of r5 is 0.8d3~1.5d3, and the range of r6 is 1.8d3~2.5d3.

[0015] In one embodiment, the distance L2 between the inlet and outlet of the first valve island secondary flow channel can be designed according to the actual turbine blade wall thickness and the diameter d1 of the first valve island secondary flow channel, with L2 ranging from 4d1 to 6d1. The length L3 of the straight section of the first valve island secondary flow channel can be designed according to the actual turbine blade wall thickness and the diameter d1 of the first valve island secondary flow channel. The range of L3 is 4d1~6d1. L2 and L3 can be the same or different; The distance L7 between the inlet and outlet of the second valve island secondary flow channel can be designed according to the actual turbine blade wall thickness and the diameter d2 of the second valve island secondary flow channel. The range of L7 is 4d2~6d2. The length L8 of the straight section of the second valve island secondary flow channel can be designed according to the actual turbine blade wall thickness and the diameter d2 of the first valve island secondary flow channel. The range of L8 is 4d2~6d2. L7 and L8 can be the same or different; The distance L9 between the inlet and outlet of the third valve island secondary flow channel can be designed according to the actual turbine blade wall thickness and the diameter d3 of the third valve island secondary flow channel. The range of L9 is 4d3~6d3. The length L of the straight section of the secondary flow channel of the third valve island 10 The design can be based on the actual turbine blade wall thickness and the diameter d3 of the secondary flow channel of the third valve island. 10 The design range is 4d3 to 6d3. L9 and L 10 They can be the same or different.

[0016] In one embodiment, the symmetrical valve island configuration and the asymmetrical valve island configuration of the present invention can be manufactured by additive manufacturing technologies such as metal 3D printing.

[0017] In a second aspect, the present invention provides a layout method for the novel gas / hydrogen turbine blade cascade anti-pulsation high-damping film cooling structure. Based on CFD and other technologies, the flow field characteristics and vortex distribution features of the turbine blade cascade are accurately obtained. Based on the differences in cooling requirements and anti-pulsation requirements of the turbine blade cascade, and with the help of machine learning or neural networks, the turbine blade cascade is intelligently and finely divided into regions according to the obtained flow field characteristics and vortex distribution features of the blade cascade.

[0018] In one embodiment, a symmetrical valve island configuration is implemented in each section of the turbine blade endwall. y Directional arrangement or valve island along z Directional arrangement; the valve islands in each section of the turbine blade endwall implement an asymmetric valve island configuration along... y Directional arrangement or valve island along z Orientation; Each section of the turbine blade endwall implements a combined arrangement of symmetrical and asymmetrical valve island configurations; the combined arrangement refers to the simultaneous presence of symmetrical and asymmetrical valve island configurations in the section. The turbine blade endwall is equipped with a sequential arrangement and a cross arrangement of symmetrical valve island configurations in each section to achieve continuous cold air coverage. The sequential arrangement means that the downstream symmetrical valve island configuration and the upstream symmetrical valve island configuration are on the same straight line. The cross arrangement means that the downstream symmetrical valve island configuration is located on the axial extension line of the center of the adjacent upstream symmetrical valve island configuration. The turbine blade endwall is equipped with a sequential arrangement of two asymmetric valve island configurations and a cross arrangement of two asymmetric valve island configurations to achieve continuous cooling air coverage. The sequential arrangement of two refers to the downstream asymmetric valve island configuration being on the same straight line as the upstream asymmetric valve island configuration. The cross arrangement of two refers to the downstream asymmetric valve island configuration being located on the axial extension line of the center of the adjacent upstream asymmetric valve island configuration.

[0019] Compared with existing technologies, this invention achieves precise stratified control of airflow at the microscale and unidirectional low-resistance flow of cool air by incorporating a Tesla valve island structure within the film cooling orifice. Therefore, for turbine blades operating in highly pulsating and non-uniform environments, this invention's intelligent and efficient cooling layout method, based on the turbine blade flow field characteristics and vortex distribution features, precisely controls the anti-pulsation performance and cooling capacity of the film cooling orifice through a zoned application strategy and flow field adaptive method. This suppresses the intrusion of high-temperature combustion gases induced by pressure pulsation, and has significant engineering application value in reducing the risk of turbine blade thermal failure and improving its operational safety. It can also contribute to the research and design of high-efficiency turbine blade cooling technology and high-performance hydrogen turbines. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the symmetrical valve island configuration of the present invention.

[0021] Figure 2 This is a schematic diagram of the asymmetric valve island configuration of the present invention.

[0022] Figure 3 This is a schematic diagram of the overall layout of the turbine blade cascade film perforation structure.

[0023] Figure 4 This is a schematic diagram of the overall layout design of the turbine blade cascade film perforation structure. Detailed Implementation

[0024] The embodiments of the present invention will now be described in detail with reference to the accompanying drawings and examples.

[0025] The air film cooling structure of the present invention is to open a bypass on the conventional cylindrical air film hole to form a Tesla valve island structure, which can be applied to gas turbine blades or hydrogen turbine blades and has the characteristics of anti-pulsation and high damping.

[0026] Specifically, such as Figure 1 and Figure 2As shown, a Tesla valve island structure is formed by two bypasses on a conventional cylindrical film orifice. The bypasses prevent airflow reversal; therefore, in a typical structure, along the airflow direction, the bypasses smoothly connect an upstream arc segment with a downstream straight segment. The flow velocity in the arc segment is slower, and the flow velocity in the straight segment is faster. Tesla valve island structures are divided into two basic forms: symmetrical valve island configuration 12 and asymmetrical valve island configuration 13. In symmetrical valve island configuration 12, the two bypasses are symmetrically arranged along the main cold air flow channel on the conventional cylindrical film orifice, and the two bypasses can be on the same plane or different planes. In asymmetrical valve island configuration 13, the two bypasses are asymmetrically arranged along the main cold air flow channel on the conventional cylindrical film orifice, and the two bypasses can be on the same plane or different planes. The asymmetry of the two bypasses in asymmetrical valve island configuration 13 can be due to differences in size, shape, or connection position.

[0027] The Tesla valve island structure of this invention uses existing conventional cylindrical film cooling orifices as the main cooling air channel and the bypass channels as the secondary flow channels of the valve island. The inlet and outlet of the secondary flow channels of the valve island are connected to the main cooling air channel. The distribution effect of this invention on the turbine blade cascade can be seen by referring to... Figure 3 As shown.

[0028] Further reference Figure 1 As shown, in the symmetrical valve island configuration of the Tesla valve island structure, its film gas inlet 1 and film gas outlet 3 are directly located in the main cooling gas channel, which are actually the inlet and outlet of the conventional cylindrical film gas orifice. Its two bypasses are the secondary flow channels 2 of the first valve island, with identical shape and size parameters. The diameter D1 of the main cooling gas channel can be determined according to the actual cooling requirements, with a preferred range of 0.5~1.5 mm.

[0029] The distance L1 between the inlet of the film cooling orifice 1 and the inlet of the first valve island secondary flow channel 2 can be designed according to the actual turbine blade wall thickness. The distance L4 between the first valve island secondary flow channel 2 and the outlet of the film cooling orifice 3 can be designed according to the turbine blade wall thickness. The diameter d1 of the first valve island secondary flow channel 2 can be determined according to the degree of pressure pulsation in the blade cascade, preferably within the range of 0.5~1.5 mm. The angle between the outlet of the first valve island secondary flow channel 2 and the main flow channel of the cold air is... The angle between the straight section of the first valve island secondary flow channel 2 and the conventional cylindrical film gas orifice (i.e., the angle between the straight section and the conventional cylindrical film gas orifice) can be determined according to the pulsation damping requirements, with a preferred range of 25°~50°. The inner radius r1 and outer radius r2 of the arc section of the first valve island secondary flow channel 2 can be designed based on the actual turbine blade wall thickness and the diameter d1 of the first valve island secondary flow channel 2, with r1 ranging from 0.8d1 to 1.5d1 and r2 ranging from 1.8d1 to 2.5d1. The distance L2 between the inlet and outlet of the first valve island secondary flow channel 2 can be designed based on the turbine blade wall thickness and the diameter d1 of the first valve island secondary flow channel 2, with a preferred range of 4d1~6d1. The length L3 of the straight section of the first valve island secondary flow channel 2 can be designed based on the actual turbine blade wall thickness and the diameter d1 of the first valve island secondary flow channel 2, with a preferred range of 4d1~6d1. L2 and L3 can be the same or different.

[0030] Further reference Figure 2 As shown, in the asymmetric Tesla valve island structure, its film gas inlet 4 and film gas outlet 7 are directly located in the main cold air flow channel, which are actually the inlet and outlet of a traditional cylindrical film gas outlet. Its two bypasses are the second valve island secondary flow channel 5 and the third valve island secondary flow channel 6. The second valve island secondary flow channel 5 and the third valve island secondary flow channel 6 can differ in shape, size, and distribution, thus forming an asymmetric structure. Figure 2 In the illustrated embodiment, the two channels are sequential along the airflow direction. Specifically, the outlet of the second valve island secondary channel 5 is located between the inlet and outlet of the third valve island secondary channel 6, and the inlet of the third valve island secondary channel 6 is located between the inlet and outlet of the second valve island secondary channel 5. The diameter D2 of its main cold air channel can also be determined according to actual cooling requirements, preferably in the range of 0.5~1.5 mm.

[0031] The distance L7 between the inlet and outlet of the second valve island secondary flow channel 5 is designed based on the actual turbine blade cascade wall thickness and the diameter d2 of the second valve island secondary flow channel 5, with a preferred range of 4d2 to 6d2. The straight section length L8 of the second valve island secondary flow channel 5 is designed based on the actual turbine blade cascade wall thickness and the diameter d2 of the first valve island secondary flow channel 5, with a preferred range of 4d2 to 6d2; the two can be the same or different. The diameter d2 of the second valve island secondary flow channel 5 and the diameter d3 of the third valve island secondary flow channel 6 can be determined based on the degree of pressure pulsation, both ranging from 0.5 to 1.5 mm; d2 and d3 can be the same or different. The angle between the outlet of the second valve island secondary flow channel 5 and the main cold air flow channel is... (i.e., the angle between the straight segment and the traditional cylindrical air film orifice) and the angle between the outlet of the third valve island's secondary flow channel 6 and the main cold air flow channel. The value range for (i.e., the angle between the straight segment and the traditional cylindrical air film aperture) is 25°~50°. and The inner radius r3 and outer radius r4 of the arc segment of the second valve island secondary flow channel 5 are designed based on the actual turbine blade cascade wall thickness and the diameter d2 of the second valve island secondary flow channel 5. Preferably, r3 ranges from 0.8d2 to 1.5d2, and r4 ranges from 1.8d2 to 2.5d2. r3 and r4 can be the same or different. The inner radius r5 and outer radius r6 of the arc segment of the third valve island secondary flow channel 6 are designed based on the actual turbine blade cascade wall thickness and the diameter d3 of the third valve island secondary flow channel 6. Preferably, r5 ranges from 0.8d3 to 1.5d3, and r6 ranges from 1.8d3 to 2.5d3. The distance L9 between the inlet and outlet of the third valve island secondary flow channel 6 can be designed based on the actual turbine blade cascade wall thickness and the diameter d3 of the third valve island secondary flow channel 6. Preferably, L9 ranges from 4d3 to 6d3. The length L of the straight section of the third valve island secondary flow channel 6... 10 Based on the actual turbine blade wall thickness and the diameter d3 of the third valve island secondary flow channel 6, the preferred L... 10 The range is 4d3~6d3, L9 and L 10 They can be the same or different.

[0032] The present invention also provides a layout method based on the aforementioned anti-pulsation high-damping film gas hole configuration for gas turbine or hydrogen turbine blade cascades, comprising: First, CFD high-precision numerical simulation technology is used to accurately identify the flow characteristics, secondary flow field characteristics and vortex distribution law inside the turbine blade cascade 11. With the help of artificial intelligence methods such as machine learning and neural networks, the turbine blade cascade is divided into zones. Based on the differences in cooling requirements and anti-pulsation requirements of different regions, an intelligent and refined anti-pulsation high-damping film perforation layout is carried out.

[0033] Among them, such as Figure 4 As shown, based on the differences in cooling requirements and anti-pulsation requirements in the turbine blade endwall 10 region, a symmetrical valve island configuration 12 can be implemented on the wall surface. y Directional arrangement 9 or valve island along z Orientation arrangement 8. In this invention, the following is defined: x The direction is axial. y The direction is circumferential. z The direction is radial.

[0034] Based on the actual turbine blade wall thickness and the degree of regional pressure pulsation, when the blade wall thickness is sufficient and the regional pressure pulsation is large, the valve island edge is preferred. z Directional arrangement 8, when the blade cascade thickness is to be avoided or the regional pressure pulsation is to be small, the valve island is preferably arranged along... y Orientation arrangement.

[0035] Based on the differences in cooling and anti-pulsation requirements in different regions of the turbine blade endwall 10, an asymmetric valve island configuration 13 can be implemented on the wall surface.y Directional arrangement 9 or valve island along z Orientation arrangement 8.

[0036] Based on the cooling and anti-pulsation requirements of different regions of the turbine blade endwall 10, a symmetrical valve island configuration 12 and an asymmetrical valve island configuration 13 can be arranged collaboratively on the wall surface. That is, a symmetrical valve island configuration 12 and an asymmetrical valve island configuration 13 coexist in the partition.

[0037] Based on the actual pressure pulsation level and the degree of gas intrusion prevention in the turbine blade wall area, when the pressure pulsation level in the blade wall area is small and the degree of high-temperature gas intrusion is required to be low, the symmetrical valve island configuration 12 and the asymmetrical valve island configuration 13 are preferably arranged in combination.

[0038] Based on the anti-pulsation requirements and air film coverage continuity requirements of different regions of the turbine blade endwall 10, sequential arrangement-14 and cross arrangement-15 of symmetrical valve island configuration 12 can be implemented on the wall surface.

[0039] Based on the cooling performance requirements of the turbine blade cascade wall area and the actual manufacturing difficulty, when the requirement for continuity of the circumferential air film coverage of the wall is low, the sequential arrangement of 14 is preferred, and when the requirement for continuity of the circumferential air film coverage of the wall is high, the cross arrangement of 15 is preferred.

[0040] Based on the anti-pulsation requirements and air film coverage continuity requirements of different regions of the turbine blade endwall 10, sequential arrangement 2 16 and cross arrangement 2 17 of asymmetric valve island configuration 13 can be implemented on the wall surface.

[0041] The technical principle of this invention is as follows: Based on the traditional cylindrical film cooling orifice configuration, several symmetrical or asymmetrical Tesla valve island structures are incorporated. When cold air flows from the inlet to the outlet, it enters the secondary channel at the inlet of the Tesla valve island structure, forcing some fluid to flow along the valve island structure towards the outlet. At the Tesla valve outlet, it merges with the mainstream flow and flows smoothly out of the film cooling orifice. When high-temperature combustion gas invades from the film cooling orifice outlet, some of it enters the secondary channel of the valve island, where its flow direction changes. It merges with the mainstream flow at the inlet of the secondary channel. At this point, the high-temperature combustion gas in the secondary channel flows in the opposite direction to the mainstream high-temperature combustion gas, generating a flow blocking vortex system and extremely high flow resistance. This achieves unidirectional low-resistance flow of cold air and suppresses the intrusion of high-temperature combustion gas. Based on the strong pulsation and non-uniform smoothness characteristics, an intelligent turbine blade cascade partitioning strategy and an adaptive method for the cold air and combustion gas flow fields are adopted. Through the coordinated arrangement of the film cooling orifice configuration, precise control of anti-pulsation and cooling capacity is achieved.

[0042] In summary, this anti-pulsation high-damping film cooling orifice configuration achieves unidirectional flow of cold air through a built-in Tesla valve island structure, enabling precise stratified control of airflow at the microscale. This suppresses the backflow of high-temperature combustion gas into the cold air chamber, prevents high-temperature combustion gas from invading the turbine disk cavity in a strongly pulsating and non-uniform operating environment, implements a refined and intelligent zoned cooling layout, reduces the risk of turbine blade thermal failure, and provides technical support for the research and development of high-efficiency turbine blade cooling technology and high-performance hydrogen turbines.

[0043] The above description is only a preferred embodiment of the present invention. For those skilled in the art, several improvements can be made without departing from the technical principles of the present invention, and these improvements should be considered within the scope of protection of the present invention.

Claims

1. A novel anti-pulsation high-damping film cooling structure for gas / hydrogen turbine blades, characterized in that, A Tesla valve island structure is formed by setting a bypass for a traditional cylindrical air film orifice; in the Tesla valve island structure, the traditional cylindrical air film orifice is the main flow channel for cold air, and the bypass is the secondary flow channel for the valve island. The inlet and outlet of the secondary flow channel of the valve island are both connected to the main flow channel for cold air.

2. The novel gas / hydrogen turbine blade cascade anti-pulsation high-damping film cooling structure according to claim 1, characterized in that, The Tesla valve island structure is formed by setting bypasses on only a portion of the conventional cylindrical film gas holes of the turbine blade cascade.

3. The novel gas / hydrogen turbine blade cascade anti-pulsation high-damping film cooling structure according to claim 1, characterized in that, A single conventional cylindrical air film orifice is configured with a bypass to form multiple Tesla valve island structures.

4. The novel gas / hydrogen turbine blade cascade anti-pulsation high-damping film cooling structure according to claim 1, 2, or 3, characterized in that, Each of the Tesla valve island structures is formed by setting two bypasses on a conventional cylindrical air film orifice. Along the airflow direction, the bypasses are smoothly connected by an upstream arc segment and a downstream straight segment. The Tesla valve island structure includes a symmetrical valve island configuration (12) and an asymmetrical valve island configuration (13). In the symmetrical valve island configuration (12), the two bypasses are symmetrically arranged on the conventional cylindrical air film orifice along the main cold air flow channel. The two bypasses are on the same plane or different planes. In the asymmetrical valve island configuration (13), the two bypasses are asymmetrically arranged on the conventional cylindrical air film orifice along the main cold air flow channel. The two bypasses are on the same plane or different planes.

5. The novel gas / hydrogen turbine blade cascade anti-pulsation high-damping film cooling structure according to claim 4, characterized in that, The inlet (1) and outlet (3) of the symmetrical valve island configuration Tesla valve island structure, and the inlet (4) and outlet (7) of the asymmetrical valve island configuration Tesla valve island structure are all directly located in the main cold air channel; the two bypasses of the symmetrical valve island configuration Tesla valve island structure are the first valve island secondary channel (2), and the two bypasses of the asymmetrical valve island configuration Tesla valve island structure are the second valve island secondary channel (5) and the third valve island secondary channel (6). Along the airflow direction, the outlet of the second valve island secondary channel (5) is located between the inlet and outlet of the third valve island secondary channel (6), and the inlet of the third valve island secondary channel (6) is located between the inlet and outlet of the second valve island secondary channel (5).

6. The novel gas / hydrogen turbine blade cascade anti-pulsation high-damping film cooling structure according to claim 5, characterized in that, The diameters D1 and D2 of the main cooling channel are determined according to actual cooling requirements, ranging from 0.5 to 1.5 mm; the diameter d1 of the first valve island secondary channel (2) is determined according to the degree of pressure pulsation, ranging from 0.5 to 1.5 mm; the diameters d2 of the second valve island secondary channel (5) and d3 of the third valve island secondary channel (6) are determined according to the degree of pressure pulsation, both ranging from 0.5 to 1.5 mm, and d2 and d3 may be the same or different. The angle between the outlet of the first valve island secondary flow channel (2) and the main flow channel of the cold air is The angle between the outlet of the second valve island secondary flow channel (5) and the main flow channel of the cold air. and the angle between the outlet of the third valve island secondary flow channel (6) and the main flow channel of the cold air. The values ​​range for all values ​​from 25° to 50°. and Same or different.

7. The novel gas / hydrogen turbine blade cascade anti-pulsation high-damping film cooling structure according to claim 5, characterized in that, The inner radius r1 and outer radius r2 of the arc segment of the first valve island secondary flow channel (2) are designed according to the actual turbine blade wall thickness and the diameter d1 of the first valve island secondary flow channel (2). The range of r1 is 0.8d1~1.5d1, and the range of r2 is 1.8d1~2.5d1. The inner radius r3 and outer radius r4 of the arc segment of the second valve island secondary flow channel (5) are designed according to the actual turbine blade wall thickness and the diameter d2 of the second valve island secondary flow channel (5). The range of r3 is 0.8d2~1.5d2, and the range of r4 is 1.8d2~2.5d2. The inner radius r5 and outer radius r6 of the arc segment of the third valve island secondary flow channel (6) are designed according to the actual turbine blade wall thickness and the diameter d3 of the third valve island secondary flow channel (6). The range of r5 is 0.8d3~1.5d3, and the range of r6 is 1.8d3~2.5d3.

8. The novel gas / hydrogen turbine blade cascade anti-pulsation high-damping film cooling structure according to claim 5, characterized in that, The distance L2 between the inlet and outlet of the first valve island secondary flow channel (2) is designed according to the actual turbine blade wall thickness and the diameter d1 of the first valve island secondary flow channel (2), and the range of L2 is 4d1~6d1; The length L3 of the straight section of the first valve island secondary flow channel (2) is designed according to the actual turbine blade wall thickness and the diameter d1 of the first valve island secondary flow channel (2). The range of L3 is 4d1~6d1. L2 and L3 may be the same or different; The distance L7 between the inlet and outlet of the second valve island secondary flow channel (5) is designed according to the actual turbine blade wall thickness and the diameter d2 of the second valve island secondary flow channel (5). The range of L7 is 4d2~6d2. The length L8 of the straight section of the second valve island secondary flow channel (5) is designed according to the actual turbine blade wall thickness and the diameter d2 of the first valve island secondary flow channel (5). The range of L8 is 4d2~6d2. L7 and L8 may be the same or different; The distance L9 between the inlet and outlet of the third valve island secondary flow channel (6) is designed according to the actual turbine blade wall thickness and the diameter d3 of the third valve island secondary flow channel (6). The range of L9 is 4d3~6d3. The length L of the straight section of the third valve island secondary flow channel (6) 10 Based on the actual turbine blade wall thickness and the diameter d3 of the third valve island secondary flow channel (6), L 10 The design range is 4d3 to 6d3. L9 and L 10 Same or different.

9. The layout method of the novel gas / hydrogen turbine blade cascade anti-pulsation high-damping film cooling structure according to any one of claims 1 to 8, characterized in that, The flow field characteristics and vortex distribution features of the turbine blade cascade are obtained. Based on the differences in cooling requirements and anti-pulsation requirements of the turbine blade cascade (11), the turbine blade cascade is intelligently and finely divided into regions by means of machine learning or neural networks, according to the obtained flow field characteristics and vortex distribution features of the blade cascade.

10. The layout method according to claim 9, characterized in that, The valve islands in each section of the turbine blade endwall (10) implement a symmetrical valve island configuration (12) along the valve island edge. y Directional arrangement (9) or valve island along z Directional arrangement (8); the asymmetric valve island configuration (13) is implemented in each section of the turbine blade endwall (10) along the valve island. y Directional arrangement (9) or valve island along z Orientation arrangement (8); The turbine blade endwall (10) is provided with a coordinated arrangement of symmetrical valve island configuration (12) and asymmetrical valve island configuration (13) in each section; the coordinated arrangement means that the section contains both symmetrical valve island configuration (12) and asymmetrical valve island configuration (13). The turbine blade endwall (10) implements a sequential arrangement (14) and a cross arrangement (15) of symmetrical valve island configurations (12) in each section; the sequential arrangement (14) refers to the downstream symmetrical valve island configuration and the upstream symmetrical valve island configuration being on the same straight line; the cross arrangement (15) refers to the downstream symmetrical valve island configuration being located on the axial extension line of the center of the upstream adjacent symmetrical valve island configuration. In each section of the turbine blade endwall (10), asymmetric valve island configurations (13) are implemented in sequential arrangement two (16) and cross arrangement two (17); the sequential arrangement two (16) refers to the downstream asymmetric valve island configuration and the upstream asymmetric valve island configuration being on the same straight line; the cross arrangement two (17) refers to the downstream asymmetric valve island configuration being located on the axial extension line of the center of the upstream adjacent asymmetric valve island configuration.

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