Combustion and spraying combination overall design method

Abstract

The invention belongs to the field of ground heavy duty gas turbines, and discloses an overall design method of a combustion-spraying combination, which comprises the following steps: obtaining overall thermodynamic parameters based on performance requirements of the combustion-spraying combination; on the basis of the total thermodynamic parameters and the inlet and outlet radiuses, a meridian flow channel design is obtained through a flow channel optimization method; based on the meridian flow channel design, adopting a parametric modeling method to obtain a flow surface model; based on the flow surface model, a three-dimensional accumulation method is adopted to obtain an initial configuration of the turbine blade; and based on combustion design, cooling design and pneumatic design performance, checking and optimizing the initial configuration of the turbine blade to obtain an optimized blade configuration and a combustion and spraying combined body pneumatic design scheme.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of ground heavy gas turbines, and particularly relates to a general design method of a fuel injection combination. BACKGROUND

[0002] As a core power equipment of modern industry, the performance of a gas turbine directly affects the energy conversion efficiency and operation economy. Current research and development of heavy gas turbines mainly focuses on key fields such as improving the turbine inlet temperature, optimizing the combustion system and improving the cooling technology. International advanced technologies have achieved breakthroughs by adopting new high-temperature resistant materials, efficient cooling structures and low-emission combustion chamber designs. In the aspect of combustion chamber-turbine integrated design, the existing technologies mostly adopt a modular optimization strategy: the combustion system design mainly solves the problems of fuel mixing and low-pollution combustion, and the turbine system focuses on the improvement of aerodynamic performance and thermal protection design. Typical technical solutions include lean oil premixed combustion technology, composite cooling structure and the like, which to some extent realize the balance between pollution control and efficiency improvement. In addition, the combustion chamber-turbine integrated design concept proposed by the academic circle provides a new idea for system integration by optimizing the transition section structure to reduce cooling gas consumption.

[0003] However, the existing technologies still have obvious limitations: first, the traditional design process handles the aerodynamic, combustion and cooling links independently, lacks systematic coordination, and it is difficult to achieve overall performance optimization; second, the high-temperature non-uniform flow field and residual swirl at the outlet of the combustion chamber will significantly deteriorate the working environment of the turbine blades, and the existing methods cannot effectively solve this multi-field coupling problem; third, local optimization often leads to a trade-off between performance, such as reducing the combustion temperature to reduce the cooling burden, but at the expense of cycle efficiency; finally, the existing design methods rely on experience and trial and error, and have a long development cycle and high cost, which is difficult to meet the rapid iteration demand. These problems seriously restrict the development of gas turbines towards higher efficiency and environmental protection.

[0004] Therefore, the present application proposes a general design method of a fuel injection combination. SUMMARY

[0005] To solve the above technical problems, the present application proposes a general design method of a fuel injection combination to solve the problems existing in the above-mentioned prior art.

[0006] To achieve the above-mentioned purpose, the present application provides a general design method of a fuel injection combination, comprising:

[0007] obtaining overall thermodynamic parameters based on performance requirements of the fuel injection combination;

[0008] adopting a flow channel optimization method to obtain meridian flow channel design based on the overall thermodynamic parameters and the inlet and outlet radii;

[0009] Based on the meridian flow channel design, a flow surface modeling method is adopted to obtain a flow surface modeling;

[0010] Based on the flow surface modeling, a three-dimensional accumulation method is adopted to obtain a turbine blade initial configuration;

[0011] Based on the combustion design, cooling design and aerodynamic performance checking and optimization, the turbine blade initial configuration is optimized to obtain an optimized blade configuration and a turbine blade aerodynamic design scheme.

[0012] Optionally, the overall thermodynamic parameters include: total temperature, flow rate, pressure ratio, rotor blade radial distribution requirement, turbine inter-stage distribution.

[0013] Optionally, the process of obtaining the meridian flow channel design by the flow channel optimization method includes:

[0014] Based on the overall thermodynamic parameters and the inlet and outlet radii, the meridian flow channel shape is designed;

[0015] Based on the meridian flow channel shape, the flow characteristics of the airflow in the flow channel are analyzed;

[0016] Based on the flow characteristics, the geometric shape of the upper and lower walls of the meridian flow channel is optimized to meet the aerodynamic performance requirements of the combustion chamber and turbine components, and the meridian flow channel design is obtained.

[0017] Optionally, the process of obtaining the flow surface modeling based on the meridian flow channel design includes:

[0018] Based on the meridian flow channel design, the blade leading edge, trailing edge and blade profile thickness parameters are determined;

[0019] The blade shape is iteratively optimized using blade profile design theory and optimization algorithms, and CFD simulation analysis is combined to reduce airflow separation and vortex loss;

[0020] Based on the airflow separation and vortex loss, the blade installation angle and circumferential position distribution that meet the aerodynamic performance requirements are determined.

[0021] Optionally, the process of obtaining the turbine blade initial configuration based on the flow surface modeling includes:

[0022] Based on the meridian flow channel design, a meridian flow channel is obtained;

[0023] The meridian flow channel and the flow surface modeling are converted into a three-dimensional entity model;

[0024] The size, shape and position of each component in the three-dimensional entity model are adjusted, and three-dimensional modeling software is used for virtual assembly and interference checking to obtain a turbine blade initial configuration.

[0025] Optionally, the process of optimizing the turbine blade initial configuration based on the combustion design, cooling design and aerodynamic design performance checking to obtain the optimized blade configuration and the fuel injection combined aerodynamic design scheme comprises the following steps:

[0026] determining the blade thermal load distribution based on the combustion chamber outlet flow field characteristics;

[0027] designing a cooling channel arrangement scheme based on the blade thermal load distribution;

[0028] analyzing the influence of the combustion chamber outlet swirl on the cooling film and verifying the blade aerodynamic performance through CFD simulation;

[0029] based on the blade aerodynamic performance, performing structural strength checking by using finite element analysis, iteratively adjusting the blade configuration until a blade configuration and a fuel injection combined aerodynamic design scheme meeting the requirements of combustion compatibility, cooling effectiveness and aerodynamic performance are obtained.

[0030] The application also provides a computer comprising a memory, a processor and a computer program stored on the memory and executable on the processor, wherein the processor implements a fuel injection combined overall design method when executing the computer program.

[0031] The application also provides a storage medium having a computer program stored thereon, wherein the program is executed by a processor to implement a fuel injection combined overall design method.

[0032] Compared with the prior art, the application has the following advantages and technical effects:

[0033] The application effectively solves the problem of insufficient coordination between the combustion chamber and the turbine components in the traditional design through a systematic design process and multiple iterations and optimizations. The method firstly starts from the overall thermodynamic parameters, optimizes the air flow channel through the meridian flow passage design, then completes the blade modeling in combination with the parameterized modeling, and finally realizes the overall performance improvement through the multidisciplinary collaborative optimization. BRIEF DESCRIPTION OF DRAWINGS

[0034] The accompanying drawings, which form a part of this application, are included to provide a further understanding of the application and are incorporated in and constitute a part of this application. The embodiments of the application illustrated in the drawings, and their description, are used to explain the application and are not intended to limit the application. In the drawings:

[0035] Figure 1 The accompanying drawings, which form a part of this application, are included to provide a further understanding of the application and are incorporated in and constitute a part of this application. The embodiments of the application illustrated in the drawings, and their description, are used to explain the application and are not intended to limit the application. In the drawings:

[0036] Figure 2 The accompanying drawings, which form a part of this application, are included to provide a further understanding of the application and are incorporated in and constitute a part of this application. The embodiments of the application illustrated in the drawings, and their description, are used to explain the application and are not intended to limit the application. In the drawings:

[0037] Figure 3 The accompanying drawings, which form a part of this application, are included to provide a further understanding of the application and are incorporated in and constitute a part of this application. The embodiments of the application illustrated in the drawings, and their description, are used to explain the application and are not intended to limit the application. In the drawings:

[0038] Figure 4 Optimization algorithm schematic diagram for the embodiment of the application;

[0039] Figure 5 Aerodynamic elastic stability checking schematic diagram for the embodiment of the application. DETAILED DESCRIPTION

[0040] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0041] It should be noted that the steps shown in the flowchart of the accompanying drawings can be executed in a computer system such as a group of computer executable instructions, and although the logical order is shown in the flowchart, in some cases, the steps shown or described herein can be executed in an order different from that shown herein.

[0042] Embodiment one

[0043] The present application provides a systematic gas dynamic overall design process of a fuel injection combination, which solves the problem that the performance and cooling efficiency are difficult to be considered in the traditional design caused by the independent of each link through multi-step collaborative optimization and iteration, and improves the aerodynamic performance and operation stability of the fuel injection combination under complex working conditions.

[0044] The present application provides a kind of overall gas dynamic design scheme and its design process of combustion chamber turbine combination for the problems existing in the design of existing combustion chamber turbine combination. The scheme covers the complete design steps from aerodynamic parameter distribution to blade configuration output, including the aerodynamic parameters such as total temperature and total pressure of main flow and secondary flow according to overall aerodynamic parameter distribution, design meridian flow passage, design two-dimensional section blade parameter, complete three-dimensional accumulation, carry out aeroelastic stability check, heat shock check, and carry out cooling design on the basis of blade profile. Multiple steps are repeatedly iterated and optimized, and finally the optimized blade configuration is output.

[0045] In the detailed design process, first, according to the overall performance requirements of the combustion turbine combined unit, the aerodynamic parameters of the main flow and the secondary flow are distributed to ensure that the aerodynamic performance of the entire system is optimal. This process mainly uses one-dimensional pipe network calculation method to solve the pressure and temperature values of the node position through pressure and energy balance equations, so as to realize the distribution of the aerodynamic parameters of the main flow and the secondary flow. Then, based on the distributed aerodynamic parameters and the inlet and outlet radii, the meridian flow passage is designed to optimize the flow field distribution to meet the aerodynamic requirements of the combustion chamber and turbine components. After the meridian flow passage is designed, the two-dimensional section blade parameters are further designed, and the aerodynamic efficiency of the blade is improved through geometric parameter optimization. Subsequently, based on the two-dimensional section parameters, the three-dimensional stacking design of the blade is completed to form the preliminary configuration of the blade, and the three-dimensional shape of the blade is optimized through numerical simulation and experimental verification.

[0046] In order to ensure the safety and reliability of the design, the present application also pays special attention to the aeroelastic stability check and the thermal acoustic oscillation check. Through advanced calculation methods and experimental means, the aeroelastic characteristics and thermal acoustic stability of the blade in actual operation are evaluated to avoid blade damage caused by aeroelastic problems or thermal acoustic oscillation. Based on the blade type, cooling design is carried out in combination with cooling requirements to optimize the layout and structure of the cooling channel and ensure the heat dissipation efficiency of the blade in high temperature environment, prolonging the service life of the blade.

[0047] The main part of the present application is based on the overall performance requirements of the combustion turbine combined unit, combined with the actual working conditions, the entire design process is systematically and finely optimized. The combustion turbine combined unit is composed of combustion chamber, turbine guide vane, turbine blade, cooling system and other key components, and the high efficient collaborative work is realized between each component through the optimization of aerodynamic design.

[0048] The aerodynamic design scheme of the present application is carried out on the basis of the existing overall performance scheme (previously determined aerodynamic and thermodynamic parameters of each component position), combined with the actual engineering requirements and laboratory conditions, the aerodynamic design of the combustion chamber and turbine components is optimized. The final specific aerodynamic design scheme is presented, which is convenient for the explanation and description of the present application, and also provides a basis for real aerodynamic test. Through the systematic aerodynamic design process, the efficient operation of the combustion chamber and turbine components under complex working conditions is ensured, and a complete solution for the overall aerodynamic design of the combustion turbine combined unit is provided. Through the aerodynamic design scheme of the present application, the performance and reliability of the combustion turbine combined unit can be significantly improved, the design cost and cycle can be reduced, and important technical support is provided for the development of modern industrial power system.

[0049] As Figure 1As shown, the embodiment provides a general design method of the fuel injection combination. The method optimizes the aerodynamic design process for the complex structure and multi-disciplinary coupling characteristics of the fuel injection combination, and adopts a systematic step-by-step design strategy. The application carries out the aerodynamic design process through the overall parameters, completes the preliminary aerodynamic airfoil iteration, then adjusts the aerodynamic design according to the combustion scheme design, and finally completes the iteration task with the cooling design unit and sends it to the aerodynamic design for performance checking. Specifically, the method comprises the following steps:

[0050] Obtaining overall thermodynamic parameters based on the performance requirements of the fuel injection combination; obtaining meridional flow passage design by using a flow passage optimization method based on the overall thermodynamic parameters and the inlet and outlet radii; obtaining flow surface modeling by using a parameterized modeling method based on the meridional flow passage design; obtaining turbine blade initial configuration by using a three-dimensional stacking method based on the flow surface modeling; and optimizing the turbine blade initial configuration based on the combustion design, cooling design and aerodynamic design performance checking to obtain the optimized blade configuration and the aerodynamic design scheme of the fuel injection combination.

[0051] Further, the process of obtaining the meridional flow passage design by using the flow passage optimization method comprises: designing the meridional flow passage shape based on the overall thermodynamic parameters and the inlet and outlet radii; analyzing the flow characteristics of the airflow in the flow passage based on the meridional flow passage shape; and optimizing the geometric shape of the upper and lower walls of the meridional flow passage based on the flow characteristics to meet the aerodynamic performance requirements of the combustion chamber and turbine components, thereby obtaining the meridional flow passage design.

[0052] Specifically, first, the overall thermodynamic parameters are determined, which provide a basis for subsequent design. The overall thermodynamic parameters include total temperature, flow rate, pressure ratio, blade radial distribution requirements, turbine inter-stage distribution, etc. Then, the meridional flow passage, flow surface modeling, three-dimensional design, combustion design, cooling design and aerodynamic design performance checking are sequentially performed. Through this systematic design process, the mutual influence of each link can be fully considered in the early stage of design, repeated modification in the later stage can be avoided, the design efficiency is greatly improved, and the design cycle is shortened. At the same time, this method can better coordinate the relationship between each design link during application, and ensure that the overall performance of the fuel injection combination is optimal.

[0053] As a specific embodiment of the present embodiment, the combustion chamber and turbine integrated configuration can be designed in three axial sections, namely the front section, the middle section, and the rear section. The front section is the combustion chamber, the rear section is the guide vane, and the middle section is the transition section. First, the turbine guide vane aerodynamic design (from rear to front) and the annular combustion chamber aerodynamic design (from front to rear) are completed independently, respectively. Then, the guide vane front side and the annular combustion chamber aerodynamic baffle profile are designed to be integrated. This process actually retains the annular combustion chamber vertical air inlet, smooth transition to the guide vane blade (transition section). Finally, the transition section is extended forward to the combustion chamber inlet. At this time, the combustion process in the flame tube and the gas flow expansion and acceleration turning process in the guide vane need to be considered comprehensively, involving the problems of combustion and aerodynamics. In the aerodynamic scheme design stage, the combustion problem is not considered, and the working medium is regarded as hot air. By designing the gas flow expansion and acceleration turning flow channel that meets the target requirements, the feasibility of different unit body quantity arrangements is verified, and the required axial length of the turning section under different unit body quantity conditions is studied.

[0054] As a specific embodiment of the present embodiment, the combustion design is an important part of the fuel injection combined design, and its purpose is to ensure that the fuel can be fully burned in the combustion chamber to generate sufficient heat and thrust. During the combustion design process, the structure of the combustion chamber, the fuel injection method, the ignition method, etc. need to be determined according to the overall thermodynamic parameters and the requirements of the aerodynamic design. By optimizing the structure of the combustion chamber and the combustion process, the combustion efficiency can be effectively improved, and the emission of pollutants can be reduced. At the same time, the combustion design also needs to be closely coordinated with the aerodynamic design to ensure that the high-temperature and high-pressure gas generated by combustion can smoothly enter the aerodynamic components to realize effective energy conversion.

[0055] As a specific embodiment of the present embodiment, since the fuel injection combined body will generate high temperature during operation, cooling design is needed to ensure the normal operation of the components. Cooling design mainly includes the design of cooling channels, the selection of cooling medium, and the determination of cooling method. In the cooling channel design, the cooling channel needs to be reasonably arranged according to the temperature distribution and thermal load of the component to ensure that the cooling medium can effectively take away the heat of the component. At the same time, selecting appropriate cooling medium and cooling method, such as air cooling, liquid cooling, etc., is also the key of cooling design. Cooling design needs to be coordinated with aerodynamic design and combustion design to ensure that the cooling requirements are met while not affecting the aerodynamic performance and combustion efficiency.

[0056] As a specific embodiment of the present embodiment, after completing the design of each link described above, the aerodynamic design performance is checked. Through CFD simulation analysis and wind tunnel test, etc., the aerodynamic performance of the fuel injection combination is comprehensively evaluated, including aerodynamic efficiency, thrust, pressure distribution, temperature distribution and other parameters. If the performance does not meet the design requirements, the related design links need to be adjusted and optimized until the expected aerodynamic performance indicators are reached. The aerodynamic design performance check is the last step of the whole design process, and is also the key link to ensure the success of the fuel injection combination design.

[0057] Further, based on the overall thermodynamic parameters, the meridian flow passage is designed, and by optimizing the shape of the meridian flow passage, the loss of airflow can be effectively reduced and the aerodynamic performance can be improved. In the design process, the acceleration, deceleration and turning characteristics of the airflow need to be considered comprehensively, and advanced computational fluid dynamics (CFD) technology is used for simulation analysis to ensure that the design of the meridian flow passage can meet the requirements of aerodynamic performance.

[0058] The meridian flow passage and the flow surface modeling are combined for three-dimensional design. Three-dimensional design is to convert two-dimensional meridian flow passage and flow surface modeling into three-dimensional solid model, which can more directly show the internal structure and airflow flow of the fuel injection combination. In the three-dimensional design process, the size, shape and position of each component need to be adjusted to ensure the assembly relationship between each component and the continuity of the airflow passage. At the same time, by using the powerful function of three-dimensional modeling software, virtual assembly and interference check of the fuel injection combination are carried out, and problems existing in the design are found and solved in time.

[0059] On the basis of the meridian flow passage design, the flow surface modeling is carried out. The flow surface modeling mainly determines the shape and distribution of the blade, including the leading edge, trailing edge, blade thickness and other parameters. The shape of the blade plays a key role in the flow of the airflow, and reasonable blade modeling can effectively improve the aerodynamic efficiency and reduce the separation and vortex loss of the airflow. By using advanced blade design theory and optimization algorithm, combined with CFD simulation analysis, the shape of the blade is repeatedly iterated and optimized, and finally the blade modeling that meets the requirements of aerodynamic performance is obtained.

[0060] Meridian flow passage is located at the core position of the overall structural scheme, and the flow characteristics of the main gas passing through it are significantly affected by the shape of the flow passage. In the design of meridian flow passage, through calculation and optimization, it is ensured that the gas flow in the flow passage is smooth and the energy loss is reduced. At the same time, the shape and size of the meridian flow passage directly affect the aerodynamic performance, so it needs to be iterated repeatedly in the design process to achieve the best aerodynamic effect. Regarding the optimization design of meridian flow passage, aerodynamic calculation simulation is carried out, and the results show that the flow field has tended to be uniform at the cross section, so the adopted meridian flow passage design scheme is feasible. As shown in Figure 2 , the meridian flow passage presents geometric characteristics in structure, and the shape of its upper and lower walls is designed to adapt to the flow requirements of the main gas. In terms of flow surface modeling, the shape and distribution of the blades are key factors. The parameters such as the leading edge, trailing edge and thickness of the blades are calculated and optimized to ensure that the blades can effectively guide the airflow. Through the use of advanced blade shape design theory and optimization algorithm, combined with numerical simulation, the shape of the blade is iteratively optimized, and through large data samples, a full three-dimensional neural network structure is constructed to form direct optimization from configuration to aerodynamic parameters, and genetic algorithm is used for optimization. The finally determined blade shape can effectively reduce the separation and vortex loss of the airflow and improve the aerodynamic efficiency. In the process of flow surface modeling, the installation angle and circumferential position of the blade are also considered to achieve the best flow pattern. Regarding the optimization design of the blade, detailed aerodynamic calculation simulation is carried out, and the results show that the flow field has tended to be uniform at the cross section, so the adopted blade design scheme is feasible. As shown in Figure 2 , the distribution of the blades on the flow surface presents geometric characteristics, and their shape and position are carefully designed to adapt to the flow requirements of the airflow. In the three-dimensional design stage, the meridian flow passage and flow surface modeling are combined to form a complete three-dimensional model. Using three-dimensional modeling software, the meridian flow passage and blade shape are integrated to ensure the size, shape and position of each component are accurate and meet the assembly requirements. In the three-dimensional design process, virtual assembly and interference checking are carried out to ensure the assembly relationship between components and the coherence of the airflow passage. Through simulation analysis, the rationality and feasibility of the design are verified. Regarding the optimization of three-dimensional design, detailed aerodynamic calculation simulation is carried out, and the results show that the flow field has tended to be uniform at the cross section, so the adopted three-dimensional design scheme is feasible, and the specific design content is not repeated. As shown in Figure 2 , the three-dimensional model presents geometric characteristics in structure, and the overall layout and mutual relationship of each component are carefully designed to adapt to the flow requirements of the airflow. Finally, the aerodynamic configuration of the ground fuel and jet combined body with three different unit quantities is formed as shown in Figure 2 .

[0061] Furthermore, the process of obtaining the flow surface shape using parametric modeling methods includes: determining the leading edge, trailing edge, and airfoil thickness parameters of the blade based on the meridional channel design; iteratively optimizing the blade shape using airfoil design theory and optimization algorithms, and reducing airflow separation and vortex losses by combining CFD simulation analysis; and determining the blade mounting angle and circumferential position distribution that meet aerodynamic performance requirements based on airflow separation and vortex losses.

[0062] Furthermore, the process of obtaining the initial configuration of the turbine blade based on the flow surface shape and using the three-dimensional stacking method includes: obtaining the meridional flow channel based on the meridional flow channel design; converting the meridional flow channel and flow surface shape into a three-dimensional solid model; adjusting the size, shape and position of each component in the three-dimensional solid model, and using three-dimensional modeling software to perform virtual assembly and interference checks to obtain the initial configuration of the turbine blade.

[0063] Furthermore, the process of optimizing the initial turbine blade configuration based on combustion design, cooling design, and aerodynamic design performance verification to obtain the optimized blade configuration and aerodynamic design scheme of the combustion-injection system includes: determining the blade heat load distribution based on the flow field characteristics at the combustion chamber outlet; designing the cooling channel layout scheme based on the blade heat load distribution; analyzing the influence of the combustion chamber outlet swirl on the cooling film and verifying the blade aerodynamic performance through CFD simulation; verifying the structural strength based on the blade aerodynamic performance using finite element analysis, iteratively adjusting the blade configuration until a blade configuration and aerodynamic design scheme of the combustion-injection system that meets the requirements of combustion compatibility, cooling effectiveness, and aerodynamic performance are obtained.

[0064] like Figure 3 As shown, rapid optimization iterative calculations are performed for the design of the combustion injection system. Currently, the original blade profile (⑧) has been obtained. The parameterized blade profile (⑨) is obtained through parametric fitting. Based on this, database samples (⑩) are generated using parameter control and CFD numerical simulation. Finally, an ANN approximation function is used to fit the target function definition to generate... The optimization matrix is ​​then filtered according to the optimization objective to obtain the final result. To optimize airfoil profiles, the above methods combine parametric modeling with neural networks and genetic algorithms to optimize basic aerodynamic airfoil designs. The logic of the artificial neural network algorithm is as follows: Figure 4 As shown.

[0065] like Figure 5 As shown, after completing the aerodynamic design of the overall scheme, its aeroelastic stability characteristics were checked. The airfoil designed and manufactured was then used to complete the model using self-programmed MATLAB code. Natural frequency vibration modes are extracted, and based on this, the extracted modes are... Natural frequency vibration modes The modal displacement and load mapping are mapped to the boundary of the fluid calculation domain as time-varying boundary conditions set to the calculation software. After the above setting and calculation are completed, the unsteady simulation under the loaded modal vibration condition is determined, the unsteady boundary conditions are given, and the unsteady simulation calculation of the fluid domain is carried out. The energy work and damping calculation in the period are carried out, the coupling characteristics between the vibration mode and the unsteady disturbance are analyzed, and the aeroelasticity check under each blade design condition is calculated.

[0066] The above describes the aero design step of the overall scheme, for the combustion design and cooling design, the aero design provides a design scene for the combustion design, and a one-dimensional flow loss calculation network is given, the combustion design department adopts chemical reaction one-dimensional flow path design to carry out key scheme design work on the combustion scheme of the fuel injection combination, adopts secondary combustion, according to the given opening position of the fuel injection combination under different unit numbers, designs the secondary combustion outflow flow, and gives the design parameters such as the maximum cooling flow and the minimum wall thickness of the cooling design team. The above design steps are carried out by the combustion and cooling design team, and if there is a design defect in the design, the design is returned to the aero design step for optimization design. The above integrated process can help the parameter transmission between the upstream and downstream departments and help the designers to carry out the development and design of the new fuel injection combination.

[0067] The application designs a fuel injection combination overall design method, constructs a full-process integrated scheme covering overall thermodynamic parameters, meridian flow passage, flow surface modeling, three-dimensional design, combustion design, cooling design and aero design performance check from the architecture, and describes the development of a new fuel injection combination configuration. By organically combining each design link, a systematic aero design process is formed, the concept of "full-process collaborative design" is proposed, the traditional design mode of independent links is broken, the coupling difficulty between links is reduced, and the aero parameter derivative design based on multidisciplinary optimization is proposed. Advanced computational fluid dynamics (CFD) technology and optimization algorithm are used to collaboratively optimize each design link, so as to achieve the purpose of replacing local optimization with overall optimization. The above scheme innovates on the basis of traditional aero design, maintains the high performance requirement of the fuel injection combination, greatly improves the design efficiency, simplifies the design process, and significantly reduces the design cost, and can be applied to the overall aero design of the ground heavy gas turbine fuel injection combination.

[0068] The application also provides a computer comprising a memory, a processor and a computer program stored on the memory and executable on the processor, and the processor implements a fuel injection combination overall design method when executing the computer program.

[0069] The application further provides a storage medium, which stores a computer program, and the computer program is executed by a processor to realize the method.

[0070] The above merely describes the preferred embodiments of the present application, but the protection scope of the present application is not limited thereto, and any person skilled in the art can easily think of the changes or replacements within the technical scope disclosed by the present application, which should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A method of overall design of a combined cycle power plant, characterized in that, The method comprises the following steps: obtaining overall thermodynamic parameters based on performance requirements of the fuel injection combination; obtaining meridian flow passage design by using a flow passage optimization method based on the overall thermodynamic parameters and inlet and outlet radii; obtaining flow surface modeling by using a parameterized modeling method based on the meridian flow passage design; obtaining turbine blade initial configuration by using a three-dimensional accumulation method based on the flow surface modeling; optimizing the turbine blade initial configuration based on combustion design, cooling design and aerodynamic design performance checking to obtain an optimized blade configuration and an aerodynamic design scheme of the fuel injection combination.

2. The general design method of a fuel injection and jet combination according to claim 1, characterized in that, The overall thermodynamic parameters include total temperature, flow rate, pressure ratio, rotor blade radial distribution requirements and turbine stage distribution.

3. The overall design method of a fuel injection unit according to claim 1, characterized in that, The process of obtaining the meridian flow passage design by using the flow passage optimization method comprises: designing meridian flow passage shapes based on the overall thermodynamic parameters and inlet and outlet radii; analyzing flow characteristics of air flow in the flow passage based on the meridian flow passage shapes; optimizing geometrical shapes of upper and lower walls of the meridian flow passage based on the flow characteristics to meet aerodynamic performance requirements of the combustion chamber and turbine components to obtain the meridian flow passage design.

4. The general design method of a fuel injection and jet combination according to claim 3, characterized in that, The process of obtaining the flow surface modeling by using the parameterized modeling method based on the meridian flow passage design comprises: determining blade leading edge, trailing edge and blade profile thickness parameters based on the meridian flow passage design; iteratively optimizing blade shapes by using blade profile design theory and optimization algorithms and combining CFD simulation analysis to reduce air flow separation and vortex loss; determining blade installation angles and circumferential position distributions meeting aerodynamic performance requirements based on the air flow separation and vortex loss.

5. The overall design method of a fuel injection and jet combination according to claim 4, characterized in that, The process of obtaining the turbine blade initial configuration by using the three-dimensional accumulation method based on the flow surface modeling comprises: obtaining meridian flow passages based on the meridian flow passage design; converting the meridian flow passages and the flow surface modeling into three-dimensional entity models; adjusting sizes, shapes and positions of components in the three-dimensional entity models and performing virtual assembly and interference checking by using three-dimensional modeling software to obtain the turbine blade initial configuration.

6. The overall design method of a fuel injection unit according to claim 1, wherein The process of optimizing the turbine blade initial configuration based on the combustion design, the cooling design and the aerodynamic design performance checking to obtain the optimized blade configuration and the aerodynamic design scheme of the fuel injection combination comprises: determining blade heat load distribution based on flow field characteristics of the combustion chamber outlet; designing a cooling passage arrangement scheme based on the blade heat load distribution; analyzing influences of combustion chamber outlet swirl on cooling air film and verifying blade aerodynamic performance by CFD simulation; performing structural strength checking by using finite element analysis based on the blade aerodynamic performance, iteratively adjusting the blade configuration until a blade configuration meeting combustion compatibility, cooling effectiveness and aerodynamic performance requirements and an aerodynamic design scheme of the fuel injection combination are obtained.

7. A computer comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, characterized in that, The processor executes the computer program to implement the overall design method of the fuel injection combination.

8. A storage medium having stored thereon a computer program, characterized in that The program is executed by the processor to implement the overall design method of the fuel injection combination.

Images