A hydrogen combustion turbine blade cooling system, hydrogen combustion gas turbine

Abstract

The application belongs to a cooling system, and aims at the technical problem that the traditional air cooling method cannot meet the higher cooling efficiency requirement of a turbine blade, and provides a hydrogen combustion turbine blade cooling system and a hydrogen combustion turbine, which comprise a hydrogen turbine supercharging device, and are sequentially connected to make hydrogen flow through a first pressure fuel pump, a second pressure fuel pump, a heat exchanger and a regenerator, and the inlet of the first pressure fuel pump is connected to a hydrogen source. The first pressure fuel pump and the second pressure fuel pump are used for sequentially supercharging hydrogen. The heat exchange medium of the heat exchanger is hydrogen combustion turbine lubricating oil. The heat source of the regenerator is the heat in high-temperature combustion gas discharged by the hydrogen combustion turbine, the regenerator is provided with two outlets, the first outlet is connected to an inner cooling channel inlet, and the second outlet is connected to the hydrogen turbine supercharging device. The inner cooling channel outlet located in the chord region of the turbine blade to be cooled is connected to the inlet of the hydrogen turbine supercharging device, and the outlet of the hydrogen turbine supercharging device is connected to the combustion chamber of the hydrogen combustion turbine.

Description

Technical Field

[0001] The present application relates to a cooling system, and specifically to a hydrogen gas engine turbine blade cooling system and a hydrogen gas turbine. Background Art

[0002] Amidst the global trend of energy transformation and climate change response, hydrogen energy is becoming increasingly strategically important in the energy mix. Hydrogen gas turbines, with their high efficiency and zero carbon emissions, have become a core research area in the field of hydrogen power equipment.

[0003] High-temperature turbine blades are a critical component of hydrogen combustion engines. Raising the turbine rotor inlet temperature can effectively improve the engine's thermal efficiency and output power. Turbine blades are subjected to high temperatures exceeding the melting point of the metal, high stress, and severe corrosion. Therefore, advanced cooling technologies are urgently needed to ensure safe and reliable operation. However, traditional air cooling methods, due to their insufficient cooling capacity, are unable to meet the demand for higher cooling efficiency for turbine blades. Summary of the Invention

[0004] This application addresses the technical problem that current traditional air cooling methods cannot meet the demand for higher cooling efficiency of turbine blades, and provides a hydrogen gas turbine turbine blade cooling system and a hydrogen gas turbine.

[0005] In order to achieve the above objectives, this application adopts the following technical solutions:

[0006] In a first aspect, the present application provides a hydrogen combustion engine turbine blade cooling system, comprising a hydrogen turbocharger, and a first pressure fuel pump, a second pressure fuel pump, a heat exchanger, and a regenerator connected in sequence to allow hydrogen to flow through;

[0007] The inlet of the first pressure fuel pump is connected to a hydrogen source; the first pressure fuel pump and the second pressure fuel pump are used to pressurize the hydrogen in sequence;

[0008] The heat exchange medium of the heat exchanger is the lubricating oil of the hydrogen combustion engine, which is used to preheat the hydrogen;

[0009] The heat source of the regenerator is the heat in the high-temperature combustion gas discharged from the hydrogen engine turbine. The regenerator is provided with two outlets. The first outlet is connected to the inlet of the internal cooling channel located in the mid-chord area of ​​the turbine blade to be cooled, for secondary preheating of the hydrogen. The second outlet is connected to the hydrogen turbocharger.

[0010] The outlet of the internal cooling channel located in the mid-chord area of ​​the turbine blade to be cooled is connected to the inlet of the hydrogen turbocharger, and the outlet of the hydrogen turbocharger is connected to the combustion chamber of the hydrogen combustion engine. The hydrogen turbocharger is used to pressurize the hydrogen before entering the combustion chamber.

[0011] Furthermore, ribs are provided on two opposite inner walls of the inner cooling channel.

[0012] Furthermore, the ribs are V-shaped.

[0013] Furthermore, each of the fins includes multiple sections of sub-fins, and gaps are left between adjacent sub-fins; the gaps between two adjacent fins are staggered.

[0014] Furthermore, the ratio of the distance between two adjacent fins to the fin height is in the range of 3 to 6.

[0015] Furthermore, the dimensions of the fins include:

[0016] According to the heat exchange requirements, the ratio of the fin height to the inner cooling channel height should be greater than 0.25;

[0017] Alternatively, considering the heat exchange requirements and hydrogen flow requirements, the ratio of the fin height to the inner cooling channel height is less than 0.05.

[0018] Furthermore, the ratio of the height to the width of the rib is 1.

[0019] Furthermore, the ribs are arranged to be inclined relative to the surface on which the ribs are installed, and the inclination angle of the ribs is 30° to 90°.

[0020] In a second aspect, the present application proposes a hydrogen gas turbine, comprising a combustion chamber and a turbine; and also comprising the above-mentioned hydrogen gas engine turbine blade cooling system.

[0021] Furthermore, air cooling channels are provided on the leading edges and trailing edges of the turbine blades in the turbine.

[0022] Compared with the prior art, this application has the following beneficial effects:

[0023] The present application proposes a hydrogen engine turbine blade cooling system, comprising a hydrogen turbocharger, and a first pressure fuel pump, a second pressure fuel pump, a heat exchanger, and a regenerator, which are sequentially connected to allow hydrogen to flow through. Hydrogen fuel is directly used as a coolant for the turbine blades. The hydrogen fuel is first preliminarily heated in a heat exchanger, then enters a regenerator to reach a suitable temperature, and then undergoes efficient convection cooling through the internal cooling channels of the turbine blades. After absorbing the heat generated by the turbine blades, it returns to the turbocharger cycle, ultimately providing high-efficiency fuel for the hydrogen engine. This process avoids the energy loss and air consumption caused by the additional heat exchange link of the cold air cooling heat exchanger in the existing hydrogen turbine engine cycle, and can further improve the overall efficiency of the hydrogen engine. In addition, the present application saves air extracted from the compressor for turbine blade cooling, which can improve the overall efficiency of the hydrogen engine. Preheating the hydrogen through the turbine blades can also further improve the overall efficiency of the hydrogen engine and significantly enhance the cooling effect of the turbine blades.

[0024] The present application also proposes a hydrogen gas turbine having all the advantages of the above-mentioned hydrogen gas engine turbine blade cooling system. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following is a brief introduction to the drawings required for use in the embodiments. It should be understood that the following drawings only illustrate certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying any creative work.

[0026] Figure 1 This is a schematic diagram of the hydrogen efficient cooling system for hydrogen combustion engine turbine blades in the present invention;

[0027] Figure 2 Schematic diagram of the hydrogen / air dual-medium cooling structure of the turbine blades in the present invention;

[0028] Figure 3 This is a flow chart of the design method of the cooling structure of the hydrogen-cooled ribbed channel of the turbine blade in the present invention;

[0029] Figure 4 This is a schematic diagram of the structure of the hydrogen cooling ribbed channel of the turbine blade in the present invention;

[0030] Figure 5 A diagram showing various fin forms in the hydrogen cooling ribbed channel of the turbine blade of the present invention;

[0031] Figure 6 A diagram showing various arrangements of fins in the hydrogen cooling ribbed channel of the turbine blade of the present invention;

[0032] Figure 7 Scale diagram of various fins in the hydrogen cooling ribbed channel of the turbine blade of the present invention;

[0033] Figure 8 Schematic diagram of the numerical calculation model of the hydrogen cooling ribbed channel of the turbine blade in the present invention;

[0034] Figure 9 Schematic diagram of the grid model of the hydrogen cooling ribbed channel of the turbine blade in the present invention; wherein (a) is the solid domain and (b) is the fluid domain;

[0035] Figure 10 Schematic diagram comparing the numerical calculation results of the hydrogen-cooled ribbed channels of the turbine blades in the present invention; (a) is the air cooling result, and (b) is the hydrogen cooling result.

[0036] Among them, 1-hydrogen tank, 2-first pressure fuel pump, 3-second pressure fuel pump, 4-heat exchanger, 5-regenerator, 6-hydrogen turbocharger 6, 7-turbine, 8-combustion chamber, 9-blade trailing edge, 10-blade leading edge, 11-internal cooling channel, 12-fin, 13-air film hole, 14-cooling hole, 15-straightening section, 16-ribbed channel, 17-heating wall. DETAILED DESCRIPTION

[0037] To make the objectives, technical solutions, and advantages of the embodiments of the present application more clear, the technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Generally, the components of the embodiments of the present application described and shown in the drawings herein can be arranged and designed in various different configurations.

[0038] Therefore, the following detailed description of the embodiments of the present application provided in the accompanying drawings is not intended to limit the scope of the present application for protection, but merely represents selected embodiments of the present application. All other embodiments obtained by persons of ordinary skill in the art based on the embodiments in the present application without creative work are within the scope of protection of the present application.

[0039] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, it does not need to be further defined or explained in subsequent drawings.

[0040] In the description of the embodiments of the present application, it should be noted that if the terms "upper", "lower", "horizontal", "inner", etc. appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the accompanying drawings, or the orientation or position relationship in which the product of the invention is usually placed when in use. This is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation. Therefore, it should not be understood as a limitation on the present application. In addition, the terms "first", "second", etc. are only used to distinguish the description and should not be understood as indicating or implying relative importance.

[0041] In addition, if the term "horizontal" appears, it does not mean that the component must be absolutely horizontal, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0042] In the description of the embodiments of this application, it should also be noted that, unless otherwise expressly specified or limited, the terms "disposed," "installed," "connected," and "connected" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections or electrical connections; they can refer to direct connections or indirect connections through an intermediate medium; and they can refer to internal connections between two components. Those skilled in the art can understand the specific meanings of the above terms in this application based on specific circumstances.

[0043] The efficient performance of hydrogen gas turbines depends heavily on the performance of their core components, high-temperature turbine blades. These blades operate in extreme environments, withstanding temperatures far exceeding the melting point of their metals while also contending with immense stress and the challenges of corrosive media. Therefore, ensuring the stable operation of turbine blades under these extreme conditions is crucial for improving the overall performance of hydrogen gas turbines. While traditional air cooling technology can alleviate the thermal load on the blades to a certain extent, its limitations are becoming increasingly apparent as performance requirements for hydrogen gas turbines continue to rise, particularly as turbine rotor inlet temperatures continue to rise to improve thermal efficiency and output power. Its insufficient cooling capacity makes it difficult to meet the urgent need for efficient cooling in modern hydrogen gas turbines.

[0044] Against this backdrop, the search for new, efficient cooling fluids is particularly urgent. Hydrogen, as a medium with unique physical properties, has a high thermal conductivity, meaning it can transfer heat more quickly. Its high specific heat capacity allows it to absorb more heat without significantly increasing its temperature. Its high thermal diffusivity helps distribute heat more evenly within the blade, while its low density reduces the mechanical burden of the cooling system on the blade. These properties make hydrogen an ideal alternative to traditional air cooling fluids, and it is expected to play a significant role in improving turbine blade cooling efficiency.

[0045] Compared to air, hydrogen has the characteristics of high thermal conductivity, high specific heat capacity, high thermal diffusivity and low density. Therefore, when considering new cooling media, hydrogen becomes a very promising option. However, the cooling structure and design method of hydrogen at the scale and operating conditions of turbine blades need to be further studied and explored. It is necessary to conduct in-depth research on the flow characteristics, heat transfer mechanism and compatibility of hydrogen with other materials at the blade scale and actual operating conditions. At the same time, it is also necessary to design a targeted cooling structure to ensure that hydrogen can efficiently remove the heat generated by the blades without affecting the mechanical properties and stability of the blades.

[0046] Based on the above situation, the present application proposes a hydrogen gas engine turbine blade cooling system and a hydrogen gas turbine. The present application is described in detail below with reference to embodiments and drawings.

[0047] like Figure 1As shown, a hydrogen combustion engine turbine blade cooling system is characterized by comprising a hydrogen turbocharger 6, and a first pressure fuel pump 2, a second pressure fuel pump 3, a heat exchanger 4 and a regenerator 5 connected in sequence to allow hydrogen to flow through;

[0048] The inlet of the first pressure fuel pump 2 is connected to a hydrogen source; the first pressure fuel pump 2 and the second pressure fuel pump 3 are used to sequentially pressurize the hydrogen. In practical applications, hydrogen can be stored in a hydrogen tank 1, which stores high-pressure hydrogen for cooling and combustion as a hydrogen source. The first pressure fuel pump 2 transfers hydrogen from storage to the system, providing power for subsequent processes. The second pressure fuel pump 3 can further increase the pressure of the hydrogen, ensuring that it can be effectively delivered to various parts of the hydrogen engine that require high pressure.

[0049] The heat exchange medium of the heat exchanger 4 is the lubricating oil of the hydrogen combustion engine, which is used to preheat the hydrogen. At the same time, the hydrogen is also used to cool the lubricating oil to improve efficiency.

[0050] The heat source of the regenerator 5 is the heat from the high-temperature exhaust gas from the hydrogen engine turbine 7. The regenerator 5 has two hydrogen outlets. The first outlet is connected to the inlet of the internal cooling channel 11 in the mid-chord region of the turbine blade to be cooled, for secondary preheating of the hydrogen. The second outlet is directly connected to the hydrogen turbocharger 6. The regenerator 5 recovers the heat from the high-temperature exhaust gas from the turbine 7 to preheat the hydrogen before entering the turbine blade cooling channel, thereby improving efficiency.

[0051] The outlet of the internal cooling channel 11, located in the mid-chord region of the turbine blades to be cooled, connects to the inlet of the hydrogen turbocharger 6, which in turn connects to the combustion chamber 8 of the hydrogen engine. The hydrogen turbocharger 6 is used to pressurize the hydrogen before it enters the combustion chamber 8. The turbine 7 converts the kinetic energy of the high-temperature combustion gases from the hydrogen into mechanical energy, which is then output as power. The hydrogen turbocharger 6 uses the exhaust gas energy to compress the intake air, increasing the hydrogen density and thus improving combustion efficiency. The combustion chamber 8 is where the hydrogen and air mix and ignite, generating high-temperature, high-pressure gases that propel the turbine blades.

[0052] This application addresses the existing technical issues of low cooling efficiency for hydrogen engine turbine blades and the difficulty in improving overall engine efficiency. Using hydrogen for turbine blade cooling is of great scientific and practical significance for ensuring the safe and reliable operation and efficiency improvement of hydrogen engines. It will also promote independent technological innovation and breakthroughs in the field of high-end hydrogen power equipment, promote the upgrading of clean energy power systems, enhance the competitive position of hydrogen energy technology, and play a vital role in helping achieve the dual carbon goals.

[0053] In this embodiment, the principle of efficient hydrogen cooling in the internal cooling channel 11 of the mid-chord region of the hydrogen engine turbine blade is as follows: hydrogen fuel is initially heated in the lubricating oil / hydrogen heat exchanger 4, then enters the regenerator 5 to reach a suitable temperature. It then undergoes efficient convection cooling through the internal cooling channel 11 of the turbine blade mid-chord region, absorbing heat generated by the blades before returning to the turbine 7 for supercharging and ultimately providing high-efficiency fuel for the hydrogen engine. This process avoids the energy loss and air consumption associated with the additional heat exchange step of the cold air cooling heat exchanger 4, further improving the overall efficiency of the hydrogen engine.

[0054] In some embodiments of the present application, fins 12 are provided on the two opposite inner walls of the inner cooling channel 11 to further improve the cooling effect. The principle of efficient cooling of the fins 12 in the inner cooling channel 11 is as follows: fin 12 turbulence cooling is one of the most widely used cooling methods in the chord area of ​​the turbine blade of a gas engine. It refers to the arrangement of periodically distributed fin 12 turbulent devices on the pressure and suction surfaces of the turbine blade. The turbulence effect of the fins 12 increases the heat exchange between the cold fluid and the heated wall surface, thereby enhancing the heat transfer performance of the inner cooling channel 11. Furthermore, by reasonably adjusting the form, arrangement and scale of the fins 12, the heat transfer performance and cooling effect of the inner cooling channel 11 in the chord area of ​​the hydrogen engine turbine blade can be further improved.

[0055] As an optimized structural design of the fins 12 , the aspect ratio of the hydrogen cooling channel can be in the range of 0.25-4.

[0056] In practical applications, the form, arrangement, and dimensions of the fins 12 can be designed based on practical needs. Specifically, the design process for hydrogen-cooled ribbed channel cooling structures, encompassing experimental design, geometric modeling, meshing, numerical calculations, post-processing, and data analysis, can be employed. This approach can provide a reference for designers of efficient cooling structures for hydrogen turbine blades. The introduction of fins 12 not only increases the heat exchange area but also promotes turbulent flow of the cooling medium (hydrogen) within the channel, thereby enhancing both heat conduction and convection.

[0057] The following is the working process of the above hydrogen engine turbine blade cooling system:

[0058] Step 1: The hydrogen fuel is preliminarily heated through the lubricating oil / hydrogen heat exchanger 4 .

[0059] Step 2: The pre-heated hydrogen is passed into the regenerator 5 and heated to a suitable temperature.

[0060] Step 3: hydrogen at a suitable temperature is introduced into the inner cooling channel 11 of the mid-chord region of the turbine blade to perform efficient convection cooling on the turbine blade and also to reheat the hydrogen.

[0061] In step 4, the heated hydrogen after cooling is passed into the turbine 7 for supercharging to further increase the pressure of the hydrogen.

[0062] Step 5: The pressurized hydrogen is introduced into the combustion chamber 8 of the hydrogen engine to provide high-efficiency fuel for the hydrogen engine.

[0063] Accordingly, this application also proposes a hydrogen gas turbine, comprising a combustion chamber 8 and a turbine 7, as well as the aforementioned hydrogen gas turbine blade cooling system. Hydrogen and air mix and burn within the combustion chamber 8, producing high-temperature, high-pressure combustion gas. This combustion gas then drives the turbine 7, which in turn drives the compressor and other equipment. The hydrogen gas turbine blade cooling system effectively cools the turbine blades in the high-temperature operating environment of the hydrogen gas turbine.

[0064] like Figure 2 The figure shows a schematic diagram of a turbine blade of the present application. A cooling hole 14 is provided at the trailing edge 9 of the blade for cooling by air. An air film hole 13 is provided at the leading edge 10 of the blade for cooling by air. An internal cooling channel 11 is provided in the mid-chord area of ​​the blade between the leading edge 10 and the trailing edge 9 of the blade. A rib 12 is provided at the bottom of the internal cooling channel 11. The cooling hole 14 allows cooling air to flow out from the inside of the blade and directly act on the surface of the blade, effectively taking away the heat generated by high-speed rotation and high-temperature environment, thereby reducing the operating temperature of the blade and extending its service life. The air film hole 13 sprays cooling air at a certain angle and distribution to form a thin air film covering the surface of the blade. This air film not only acts as a heat insulator, but also reduces the direct erosion of the high-temperature combustion gas on the blade, further protecting the blade from high-temperature erosion.

[0065] like Figure 4 The figure shows a schematic diagram of a cooling structure type of the cooling channel 11 in the mid-chord area of ​​the hydrogen combustion engine turbine blade. Ribs 12, column ribs and impact holes can be set at the bottom of the cooling channel 11. For example, the ribs 12 are used as the cooling structure of the cooling channel 11 in the mid-chord area of ​​the hydrogen combustion engine turbine blade, and the rib 12 structure is arranged on the upper and lower walls of the channel, and then the shape of the ribs 12 is determined.

[0066] like Figure 5The figure shows a schematic diagram of the concentrated form of ribs 12, which are straight ribs, inclined ribs, V-shaped ribs, and W-shaped ribs from left to right. As an example, the ratio of the height to the width of the ribs 12 is 1. The height and width of the ribs 12 are equal, which can increase the heat exchange area while maintaining the smooth flow of the fluid in the channel. When the height and width are equal, the ribs 12 can provide a more uniform cooling effect and are less likely to cause excessive congestion of the fluid in the channel. The ratio of the height of the ribs 12 to the height of the channel ranges from 0.05 to 0.25. This ratio range determines the amount of space occupied by the ribs 12 in the channel. A smaller ratio means that the ribs 12 are relatively short, which has less obstruction to the fluid flow, but the heat exchange area is also relatively small. A larger ratio provides a larger heat exchange area, but may increase the flow resistance of the fluid. The ratio of the spacing between fins 12 to their height ranges from 3 to 6. This ratio determines the density of the fins 12. A smaller ratio means that the fins 12 are more densely packed, providing better heat transfer, but may also increase fluid pressure loss. A larger ratio reduces interference between fins 12, facilitating smooth fluid flow, but may result in relatively weaker heat transfer. The fins 12 have an inclination angle of 30° to 90°. The inclination angle of the fins 12 refers to the angle between the fins 12 and the bottom of the channel. A smaller inclination angle may facilitate smooth fluid flow and reduce flow resistance, while a larger inclination angle may provide a larger heat transfer area and enhance cooling.

[0067] like Figure 6The figure shows a schematic diagram of various rib 12 arrangements. From left to right, they are solid ribs, broken ribs, multiple ribs arranged in a straight line, and multiple ribs arranged in a staggered line. For broken ribs, the ratio of the break spacing to the channel width can range from 0.25 to 0.5. For multiple ribs arranged in a straight line and multiple ribs arranged in a staggered line, the ratio of the spacing between the ribs 12 in both directions to the rib height can range from 3 to 6. Solid ribs refer to ribs 12 arranged continuously and unbroken within the channel. This arrangement provides a larger heat transfer area and helps enhance the cooling effect. However, solid ribs may also increase the flow resistance of the fluid. Therefore, a trade-off needs to be made between cooling efficiency and fluid dynamic performance. Broken ribs refer to ribs 12 that are broken at a certain distance within the channel, forming a discontinuous rib arrangement. This arrangement can reduce the flow resistance of the fluid while still maintaining a certain heat transfer area. The ratio of the break spacing to the channel width can be adjusted according to the specific cooling requirements and fluid dynamic performance. A larger break spacing helps reduce flow resistance but may reduce heat transfer efficiency. A smaller break spacing provides a larger heat transfer area but may increase flow resistance. Multi-rib sequential arrangement means that multiple ribs 12 are arranged in the same direction in sequence within the channel. This arrangement is convenient for processing and manufacturing, and the spacing between the ribs 12 can be controlled relatively evenly. The ratio of the spacing between the ribs 12 in two directions to the height of the ribs 12 can be adjusted to optimize the cooling efficiency and fluid dynamics performance. A larger spacing helps reduce flow resistance, but may reduce heat transfer efficiency. A smaller spacing provides a larger heat transfer area, but may increase flow resistance and manufacturing costs. Multi-rib staggered arrangement means that multiple ribs 12 are arranged in a staggered manner within the channel. This arrangement can more effectively utilize the channel space, increase the heat transfer area, and may improve the flow characteristics of the fluid. For multi-rib staggered arrangement, the ratio of the spacing between the ribs 12 in two directions to the height of the ribs 12 is also in the range of 3 to 6. By reasonably adjusting the spacing and arrangement of the ribs 12, a higher heat transfer efficiency can be achieved while maintaining a lower flow resistance.

[0068] like Figure 7 The figure below shows a schematic diagram of various fin 12 sizes. These sizes can be categorized as large (the ratio of fin 12 height to channel height is greater than 0.25), standard (the ratio is between 0.05 and 0.25), and micro (the ratio is less than 0.05). Considering only heat exchange requirements, the ratio of fin 12 height to internal cooling channel 11 height can be set to greater than 0.25, i.e., a large size. Considering both heat exchange and hydrogen flow requirements, the ratio can be set to less than 0.05, i.e., a micro size.

[0069] like Figure 3As shown, to verify the effectiveness of the fin 12 structure, Python programming was used to conduct a DOE (Design of Experiments) experiment (DOE) after determining the fin 12 configuration. This experiment determined the factors and levels involved in the hydrogen cooling ribbed channels of hydrogen-burning turbine blades and developed a calculation schedule. It should be noted that DOE is a statistical method used to plan experiments, collect data, and analyze results to effectively identify and control key factors affecting a system or process. Python provides a variety of libraries and tools to assist in DOE.

[0070] Taking the 90° ribbed channel 16 as an example, the high heat transfer performance of hydrogen and the high cooling performance of the inner cooling channel 11 in the mid-chord area of ​​the turbine blade using hydrogen as the cooling medium were verified. Figure 8 As shown, the parametric modeling of the hydrogen cooling ribbed channel 16 of the hydrogen combustion engine turbine blade is completed by secondary development based on the open source CAD software FreeCAD, including the cooling channel solid domain, the cooling structure solid domain and the hydrogen fluid domain; hydrogen enters from the hydrogen inlet, enters the ribbed channel 16 through the rectifying section 15 on the hydrogen inlet side, and then flows out from the rectifying section 15 on the hydrogen outlet side; the ribbed channel 16 has a heating wall 17.

[0071] like Figure 9 As shown in the figure, a hybrid grid scheme combining multi-block structured grids and unstructured grids is used to carry out the grid division of the hydrogen cooling ribbed channel of the hydrogen gas engine turbine blade, where (a) is the solid domain and (b) is the fluid domain. For component areas with simpler structures, hexahedral structured grids are used to reduce the number of grids. For component areas with complex structures, hybrid grids or polyhedral grids are used to reduce the time cost of grid division and finally perform reasonable grid division. The grid division work is completed by the open source software Gmsh. Then, the boundary conditions are set and numerical calculations are performed. The Reynolds number at the inlet is 30000, the inlet temperature is 300 K, the outlet pressure is 101 kPa, and the wall heat flux density is 3000 W·m -2 A preliminary calculation is carried out under the working conditions. Figure 10 Figure 2 shows the post-processing results of hydrogen flow and heat transfer within the cooling ribbed channels of a hydrogen engine turbine blade using the open-source software ParaView. (a) shows the results for air cooling, and (b) shows the results for hydrogen cooling. Compared to air cooling, the maximum wall temperature of the hydrogen-cooled ribbed channel decreased by 20.85% (approximately 83 K), the average wall temperature decreased by 17.77% (approximately 67 K), and the wall heat transfer coefficient increased by 5.93 times. Furthermore, the friction coefficient of the hydrogen-cooled ribbed channel (approximately 0.0375) was slightly lower than that of the air-cooled ribbed channel (approximately 0.0398).

[0072] According to the DOE case schedule, a large number of numerical calculations were performed across a wide range of parameters. Python programming was used to process and analyze the results, including data cleaning, data completion, normalization, graphing, and describing how cooling performance changes with various parameters. Based on the resulting data, machine learning algorithms were used to construct a predictive model for the cooling performance of the hydrogen-cooled ribbed channels in hydrogen-fired turbine blades and optimize their structural parameters. Machine learning algorithms used to construct the predictive model include neural networks, decision trees, random forests, and support vector machines. Machine learning algorithms used for structural parameter optimization include genetic algorithms, particle swarm algorithms, simulated annealing algorithms, and ant colony algorithms.

[0073] According to the optimization results, a criterion formula for the correlation between the cooling channel performance and the optimal structural parameter combination was fitted, and the design criteria for the hydrogen cooling ribbed channel of hydrogen gas engine turbine blades were summarized.

[0074] The verification results also show that hydrogen can not only significantly improve the heat transfer effect, but also save cooling air extracted from the compressor. Moreover, hydrogen is the main fuel source of hydrogen combustion engines, making the idea of ​​using hydrogen as a cooling medium for turbine blades feasible.

[0075] The above are merely preferred embodiments of the present application and are not intended to limit the present application. Those skilled in the art will readily appreciate that various modifications and variations are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present application shall be included within the scope of protection of the present application.

Claims

1. A hydrogen combustion engine turbine blade cooling system, characterized in that: It comprises a hydrogen turbocharger (6), and a first pressure fuel pump (2), a second pressure fuel pump (3), a heat exchanger (4) and a regenerator (5) which are sequentially connected to allow hydrogen to flow through. The inlet of the first pressure fuel pump (2) is connected to a hydrogen source; the first pressure fuel pump (2) and the second pressure fuel pump (3) are used to pressurize the hydrogen in sequence; The heat exchange medium of the heat exchanger (4) is the lubricating oil of the hydrogen combustion engine, which is used to preheat the hydrogen; The heat source of the regenerator (5) is the heat in the high-temperature combustion gas discharged from the hydrogen engine turbine (7). The regenerator (5) is provided with two outlets, the first outlet being connected to the inlet of the inner cooling channel (11) located in the mid-chord area of ​​the turbine blade to be cooled, for secondary preheating of the hydrogen, and the second outlet being connected to the hydrogen turbocharger (6); The outlet of the inner cooling channel (11) located in the mid-chord area of ​​the turbine blade to be cooled is connected to the inlet of the hydrogen turbocharger (6), and the outlet of the hydrogen turbocharger (6) is connected to the combustion chamber (8) of the hydrogen combustion engine. The hydrogen turbocharger (6) is used to pressurize the hydrogen before entering the combustion chamber (8).

2. The hydrogen combustion engine turbine blade cooling system according to claim 1, characterized in that: Ribs (12) are provided on two opposite inner walls of the inner cooling channel (11).

3. The hydrogen engine turbine blade cooling system according to claim 2, characterized in that: The ribs (12) are V-shaped.

4. The hydrogen combustion engine turbine blade cooling system according to claim 2, characterized in that: Each of the fins (12) comprises a plurality of sub-fins (12), with gaps being left between adjacent sub-fins (12); and the gaps between two adjacent fins (12) are staggered.

5. The hydrogen combustion engine turbine blade cooling system according to claim 4, characterized in that: The ratio of the distance between two adjacent fins (12) to the height of the fins (12) ranges from 3 to 6.

6. The hydrogen combustion engine turbine blade cooling system according to claim 2, characterized in that: The dimensions of the fins (12) include: According to the heat exchange requirements, the ratio of the height of the fin (12) to the height of the inner cooling channel (11) is greater than 0.25; Alternatively, in combination with heat exchange requirements and hydrogen flow requirements, the ratio of the height of the fins (12) to the height of the inner cooling channel (11) is made less than 0.

05.

7. The hydrogen combustion engine turbine blade cooling system according to claim 2, characterized in that: The ratio of the height to the width of the fin (12) is 1.

8. The hydrogen engine turbine blade cooling system according to claim 2, characterized in that: The ribs (12) are arranged to be inclined relative to the surface on which the ribs (12) are installed, and the inclination angle of the ribs (12) is 30° to 90°.

9. A hydrogen gas turbine comprising a combustion chamber (8) and a turbine (7); characterized in that: It also includes the hydrogen combustion engine turbine blade cooling system according to any one of claims 1 to 8.

10. The hydrogen gas turbine according to claim 9, characterized in that: Air cooling channels are provided on the leading edge (10) and the trailing edge (9) of the turbine blades in the turbine (7).

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