Aero-engine fuel oil heat exchanger conformal design method and system

Abstract

This invention discloses a conformal design method and system for aero-engine fuel and lubricating oil heat exchangers, comprising: obtaining the modeling space of the heat exchange core; performing hexahedral conformal partitioning on the modeling space to obtain a hexahedral space composed of hexahedral elements; constructing heat exchange elements; predicting the heat transfer of each heat exchange element at the current position based on the deformation matrix between each hexahedral element and the standard hexahedral element and the inlet heat transfer boundary conditions, and determining the initial heat exchange element at the current position; using the outlet heat transfer boundary conditions of the initial heat exchange element as the inlet heat transfer boundary conditions of the neighboring positions, determining candidate heat exchange elements for the neighboring positions of the current position; determining the element combination with the largest total heat transfer based on the candidate heat exchange elements of all neighboring positions, thereby determining the element combination at the current position; obtaining the heat exchange core based on the element combination at each position; and obtaining the overall structure of the heat exchanger based on the heat exchange core and the shape of the heat exchanger. This improves the overall heat transfer performance.

Description

Technical Field

[0001] This invention relates to the field of lubricating oil heat exchanger design technology, and in particular to a conformal design method and system for aero-engine lubricating oil heat exchangers. Background Technology

[0002] The statements in this section are merely background information related to the present invention and do not necessarily constitute prior art.

[0003] A heat exchanger is a device that enables heat exchange between hot and cold fluids. In the design of aero-engine heat exchangers, considering the requirements of aerodynamics and structural space compactness, the geometry of the parts is often constructed using free-form curves and surfaces. Consequently, the modeling space reserved for the layout of the heat exchanger is usually an irregular, non-circular region.

[0004] Currently, there are generally two approaches to the technical solutions. One is to find the largest inscribed regular body (such as a cuboid or cylinder) within the irregular design domain as the modeling space for the heat exchange core. The other is to treat the entire irregular region as the modeling space and generate the heat exchange core by filling it with geometric microstructures. The first approach suffers from the inability to effectively utilize the design space, resulting in low heat exchange efficiency. The second approach involves performing Boolean intersection calculations with the irregular shape after filling with microstructures, and the trimming of the boundary region significantly degrades the structure's mechanical and heat exchange performance. Therefore, how to maintain the shape while effectively ensuring the heat exchange area and improving heat exchange efficiency within the irregular design domain is a key issue in heat exchanger design.

[0005] On the other hand, due to the complex internal geometry of the heat exchanger core and the huge number of mesh panels, the overall simulation analysis calculation is large and costly. Therefore, in traditional heat exchanger design, a series of simple shapes are usually designed as heat exchange elements, and empirical formulas and correction coefficients are used to calculate the basic elements arranged according to certain rules, so as to approximate the overall heat exchange efficiency. However, this makes it difficult for traditional methods to automatically adjust and optimize the designed structure based on the actual temperature field and other reverse-driven algorithms. Summary of the Invention

[0006] To address the aforementioned issues, this invention proposes a conformal design method and system for aero-engine fuel and lubricating oil heat exchangers. Starting with the design and analysis of heat exchange units, it enables efficient modeling and analysis of fuel and lubricating oil heat exchangers, achieving conformal preservation and automatic optimization of heat exchange structures within irregular design domains, thereby improving overall heat exchange performance.

[0007] To achieve the above objectives, the present invention adopts the following technical solution:

[0008] In a first aspect, the present invention provides a conformal design method for an aero-engine fuel oil heat exchanger, comprising:

[0009] Obtain the modeling space of the heat exchange core, and perform hexahedral conformal partitioning on the modeling space to obtain a hexahedral space composed of hexahedral elements;

[0010] Construct heat exchange units, predict the heat transfer of each heat exchange unit at the current position based on the deformation matrix between each hexahedral unit and the standard hexahedral unit and the inlet heat transfer boundary conditions, and determine the initial heat exchange unit at the current position accordingly.

[0011] The outlet heat exchange boundary condition of the initial heat exchange unit is used as the inlet heat exchange boundary condition of the neighboring location. Candidate heat exchange units are determined for the neighboring locations of the current location. Based on the candidate heat exchange units of all neighboring locations, the unit combination with the largest total heat exchange is determined, thereby determining the unit combination of the current location.

[0012] The heat exchange core is obtained by combining the units at each location, and the overall structure of the heat exchanger is obtained by combining the heat exchange core and the shape of the heat exchanger.

[0013] As an alternative implementation, the heat exchange boundary conditions include fuel inlet flow rate, lubricating oil inlet flow rate, fuel inlet temperature, and lubricating oil inlet temperature.

[0014] As an alternative implementation, by setting the inlet temperature and inlet velocity of the two fluids and applying a deformation matrix to the heat exchange unit, a heat exchange performance dataset under different deformation states is obtained through simulation analysis of the heat exchange unit. This dataset is then used to train a neural network for predicting heat exchange performance, which includes heat transfer, outlet velocity of the two fluids, and outlet temperature.

[0015] As an alternative implementation, the heat exchange unit is constructed based on a three-period minimal surface.

[0016] As an alternative implementation, the heat exchange unit with the largest heat exchange capacity is selected as the initial heat exchange unit at the current location.

[0017] As an alternative implementation, during the process of determining the unit combination at the current location, a fuel connectivity graph is generated based on the fuel inlet and outlet positions in the candidate heat exchange units, and a lubricating oil connectivity graph is generated based on the lubricating oil inlet and outlet positions. The validity of the fuel connectivity graph and the lubricating oil connectivity graph is checked respectively, so as to select the unit combination with the largest total heat exchange under the condition that the fuel connectivity graph and the lubricating oil connectivity graph are directed acyclic graphs.

[0018] As an alternative implementation, the heat exchange core is obtained by taking the union of the unit combinations at each location, and the overall structure of the heat exchanger is obtained by taking the union of the heat exchange core and the heat exchanger outline.

[0019] Secondly, the present invention provides a conformal design system for an aero-engine fuel oil heat exchanger, comprising:

[0020] The space processing module is configured to obtain the modeling space of the heat exchange core, perform hexahedral conformal partitioning on the modeling space, and obtain a hexahedral space composed of hexahedral elements;

[0021] The unit construction module is configured to construct heat exchange units. It predicts the heat transfer of each heat exchange unit at the current position based on the deformation matrix between each hexahedral unit and the standard hexahedral unit and the inlet heat transfer boundary conditions, and determines the initial heat exchange unit at the current position accordingly.

[0022] The layout optimization module is configured to use the outlet heat exchange boundary condition of the initial heat exchange unit as the inlet heat exchange boundary condition of the neighboring positions to determine candidate heat exchange units for the neighboring positions of the current position, and to determine the unit combination with the largest total heat exchange based on the candidate heat exchange units of all neighboring positions, thereby determining the unit combination of the current position.

[0023] The structure determination module is configured to obtain the heat exchange core based on the unit combination at each location, and to obtain the overall structure of the heat exchanger based on the heat exchange core and the shape of the heat exchanger.

[0024] Thirdly, the present invention provides an electronic device including a memory and a processor, and computer instructions stored in the memory and running on the processor, wherein the computer instructions, when executed by the processor, perform the method described in the first aspect.

[0025] Fourthly, the present invention provides a computer-readable storage medium for storing computer instructions, which, when executed by a processor, perform the method described in the first aspect.

[0026] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0027] This invention proposes a conformal design method and system for aero-engine fuel and lubricating oil heat exchangers. By conformally partitioning the heat exchange space, the integrity of the unit structure is ensured, and the performance loss in the boundary area caused by the cutting of the heat exchange core and the irregular design domain is avoided.

[0028] This invention proposes a conformal design method and system for fuel and lubricating oil heat exchangers for aero-engines, which utilizes a three-period minimal surface as the basic heat exchange unit to achieve efficient spatial partitioning of fuel and lubricating oil within the heat exchange domain.

[0029] This invention proposes a conformal design method and system for aero-engine fuel and lubricating oil heat exchangers. Based on the simulation analysis of the elements, a heat exchange performance dataset is constructed. Under given boundary conditions, the heat exchange performance is efficiently predicted, and based on this, the element layout is efficiently adjusted and optimized to improve the overall heat exchange efficiency. It also realizes the heat exchanger optimization design driven by performance requirements and can automatically solve for the heat exchange structure that meets the requirements.

[0030] Advantages of additional aspects of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0031] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an improper limitation of the invention.

[0032] Figure 1 This is a flowchart of the conformal design method for an aero-engine fuel-lubricating oil heat exchanger provided in Embodiment 1 of the present invention;

[0033] Figures 2(a)-2(c) This is an example diagram of a typical basic heat exchange unit provided in Embodiment 1 of the present invention;

[0034] Figure 3 This is a schematic diagram of the deformation mapping of a regular hexahedral unit provided in Embodiment 1 of the present invention;

[0035] Figure 4 This is a schematic diagram of the conformal partitioning of the heat exchange space provided in Embodiment 1 of the present invention;

[0036] Figure 5 This is a schematic diagram of the heat exchange unit filling provided in Embodiment 1 of the present invention;

[0037] Figure 6 This is a flowchart of the heat exchange unit layout optimization provided in Embodiment 1 of the present invention. Detailed Implementation

[0038] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0039] It should be noted that the following detailed descriptions are exemplary and intended to provide further illustration of the invention. Unless otherwise specified, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains.

[0040] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments of the present invention. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. Furthermore, it should be understood that the terms “comprising” and “having”, and any variations thereof, are intended to cover non-exclusive inclusion, for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0041] Where there is no conflict, the embodiments and features in the embodiments of the present invention can be combined with each other.

[0042] Example 1

[0043] The rapid development of advanced manufacturing processes such as additive manufacturing, especially the advancements in metal additive manufacturing technology represented by laser sintering in processing precision, deformation control, and the range of materials that can be manufactured, has made it possible to design and manufacture novel heat exchange structures with complex geometries. Based on this, and addressing the problems and shortcomings of traditional aero-engine fuel oil heat exchanger design methods, this embodiment proposes a conformal design method for aero-engine fuel oil heat exchangers, starting with the design and analysis of heat exchange units. This method enables efficient modeling and analysis of fuel oil heat exchangers, achieving conformal preservation and automatic optimization of heat exchange structures within irregular design domains, thereby improving overall heat exchange performance.

[0044] Specifically, it includes:

[0045] Obtain the modeling space of the heat exchange core, and perform hexahedral conformal partitioning on the modeling space to obtain a hexahedral space composed of hexahedral elements;

[0046] Construct heat exchange units, predict the heat transfer of each heat exchange unit at the current position based on the deformation matrix between each hexahedral unit and the standard hexahedral unit and the inlet heat transfer boundary conditions, and determine the initial heat exchange unit at the current position accordingly.

[0047] The outlet heat exchange boundary condition of the initial heat exchange unit is used as the inlet heat exchange boundary condition of the neighboring location. Candidate heat exchange units are determined for the neighboring locations of the current location. Based on the candidate heat exchange units of all neighboring locations, the unit combination with the largest total heat exchange is determined, thereby determining the unit combination of the current location.

[0048] The heat exchange core is obtained by combining the units at each location, and the overall structure of the heat exchanger is obtained by combining the heat exchange core and the shape of the heat exchanger.

[0049] The following is combined with Figure 1 The method of this embodiment will be described in detail.

[0050] Step (1): Establishment and partitioning of the heat exchanger core modeling space;

[0051] Step (1-1): Based on the structural design and layout requirements of the aero-engine body and its accessories, determine the geometric shape S of the fuel-oil heat exchanger, and the fuel inlet Fuel on S. in Fuel export out Lubricating oil inlet lube in and lubricating oil outlet lube out The modeling space C of the heat exchange core is obtained by offsetting the thickness d inward from the geometric shape S.

[0052] Step (1-2): To avoid the element trimming problems caused by the intersection of the heat exchange core H and the modeling space C in traditional methods, the modeling space C is hexahedral conformally partitioned, thereby generating a hexahedral space {Cell} composed of a series of hexahedral elements. i}

[0053] Step (2): Construction of heat exchange unit and prediction of heat exchange performance;

[0054] Step (2-1): Selection of heat exchange unit; The heat exchange unit must meet the requirements of good spatial partitioning properties, that is, it must have two independent subspaces within the unit to achieve heat exchange between two fluids through a solid interface. Various geometric microstructures, including hollow rods, flat plates, and curved sheets, can achieve this goal. This embodiment uses a typical geometric microstructure among curved sheets—the Triplyperiodic Minimal Surface (TPMS)—as an example for illustration.

[0055] Step (2-2): Construction of the heat exchange unit. For example... Figures 2(a)-2(c) As shown, the TPMS unit cell divides the space into C1 within a standard cubic unit cell. A and C B Two independent sub-regions, simultaneously divided into C on the six outer surfaces of the cube. Ai and C Bi Two independent subregions, where the subscript i represents the index of each face of the cube. Therefore, for a TPMS unit cell, different {C} values ​​can be used. Ai} and {C Bi The location and quantity of heat exchange units can be combined to serve as inlets and outlets for fuel oil and lubricating oil, resulting in a variety of different heat exchange units.

[0056] Step (2-3): Prediction of heat transfer performance of heat exchange unit. Given the type of geometric microstructure unit (e.g., Gyroid, Diamond, etc. in TPMS) and the heat transfer boundary conditions, computational fluid dynamics (CFD) simulation is used to obtain the heat transfer performance of the heat exchange unit.

[0057] In other words, by setting a set of inlet temperature {T} and inlet flow velocity {V}, simulation analysis of the heat exchange unit can yield a dataset of its heat exchange performance. Furthermore, since the modeling space uses a hexahedral conformal partition, the heat exchange unit has an irregular hexahedral shape. Therefore, a deformation matrix {M} is applied to the heat exchange unit to obtain heat exchange performance datasets under different deformation states, such as... Figure 3 As shown.

[0058] The heat transfer boundary conditions include the physical properties of the two fluids, the inlet and outlet locations, the inlet velocity, and the inlet temperature; the heat transfer performance includes the heat transfer capacity, the outlet velocity of the two fluids, and the outlet temperature.

[0059] Step (2-4): Since the heat exchange performance of the heat exchange unit changes nonlinearly with the geometry of the heat exchange unit and the heat exchange boundary conditions, and it is impossible to enumerate and analyze all states, this embodiment adopts a data-driven approach to establish an efficient mapping between the geometric parameters and heat exchange boundary conditions of the heat exchange unit and the heat exchange performance.

[0060] Specifically, by establishing an end-to-end MLP deep neural network, the heat transfer performance dataset is used as input to train the neural network, thereby enabling it to predict heat transfer performance. For a newly given heat transfer unit, given the inlet temperature {T}, inlet flow velocity {V}, and deformation matrix M, the heat transfer performance of the heat transfer unit at the current location can be predicted.

[0061] Step (3): Optimize the layout of the heat exchange unit;

[0062] like Figure 4-6 As shown, step (3-1): Based on the hexahedral space {Cell i}, obtain each hexahedral cell. i The set of deformation matrices corresponding to the standard hexahedral element {M i Then, the heat exchange capacity is predicted by combining the inlet position of the two fluids in the heat exchanger and the heat exchange boundary conditions. The heat exchange unit with the largest heat exchange capacity Q is taken as the initial heat exchange unit at the current position.

[0063] Step (3-2): In this embodiment, taking the initial heat exchange unit u at the inlet position as an example, the outlet heat exchange boundary condition of the initial heat exchange unit u is predicted through step (2-4), and it is used as the neighborhood position nu. i Given the inlet heat transfer boundary conditions, predict the heat transfer of heat transfer units in the neighborhood again, and select the top n as candidate heat transfer units in the neighborhood {nu i};

[0064] If a greedy approach is used, selecting the optimal heat exchange unit at the current position each time might cause the overall structure to fall into a local optimum. Therefore, this embodiment uses a beam search approach, selecting the top n heat exchange units with the highest heat exchange capacity as candidate heat exchange units. To avoid the combinatorial explosion problem caused by a large number of units, a breadth-first search strategy is adopted. After searching all neighborhood positions of u, the total heat exchange capacity of the candidate heat exchange unit combination sum{Qnu} is calculated. i}

[0065] Step (3-3): Connectivity Graph Construction and Validity Detection. Based on the inlet and outlet positions of the two fluids (i.e., fuel oil and lubricating oil) in the candidate heat exchange units, fuel oil connectivity graph G1 and lubricating oil connectivity graph G2 are generated respectively. To avoid local internal circulation of the fluid, the validity of G1 and G2 is detected. Under the condition that G1 and G2 are directed acyclic graphs, the unit combination with the largest total heat transfer is selected, thereby determining the unit selection of u.

[0066] Step (3-4): Generate the heat exchange core. After traversing all candidate heat exchange units and performing step (3-2), the route with the largest total heat exchange is obtained, and the unit structure corresponding to this route is taken as the final heat exchange core structure {u} at the current position.

[0067] Step (4): Based on the heat exchange unit type and its geometric parameters corresponding to each position in the heat exchange space, the heat exchange core can be obtained by taking the union of each unit. The heat exchange core and the heat exchanger outline can be combined to generate the final required overall structure of the heat exchanger.

[0068] Example 2

[0069] This embodiment provides a conformal design system for an aero-engine fuel oil heat exchanger, including:

[0070] The space processing module is configured to obtain the modeling space of the heat exchange core, perform hexahedral conformal partitioning on the modeling space, and obtain a hexahedral space composed of hexahedral elements;

[0071] The unit construction module is configured to construct heat exchange units. It predicts the heat transfer of each heat exchange unit at the current position based on the deformation matrix between each hexahedral unit and the standard hexahedral unit and the inlet heat transfer boundary conditions, and determines the initial heat exchange unit at the current position accordingly.

[0072] The layout optimization module is configured to use the outlet heat exchange boundary condition of the initial heat exchange unit as the inlet heat exchange boundary condition of the neighboring positions to determine candidate heat exchange units for the neighboring positions of the current position, and to determine the unit combination with the largest total heat exchange based on the candidate heat exchange units of all neighboring positions, thereby determining the unit combination of the current position.

[0073] The structure determination module is configured to obtain the heat exchange core based on the unit combination at each location, and to obtain the overall structure of the heat exchanger based on the heat exchange core and the shape of the heat exchanger.

[0074] It should be noted that the above modules correspond to the steps described in Embodiment 1, and the examples and application scenarios implemented by the above modules and the corresponding steps are the same, but are not limited to the content disclosed in Embodiment 1. It should also be noted that the above modules, as part of the system, can be executed in a computer system such as a set of computer-executable instructions.

[0075] In further embodiments, the following is also provided:

[0076] An electronic device includes a memory and a processor, as well as computer instructions stored in the memory and running on the processor, wherein the computer instructions, when executed by the processor, perform the method described in Embodiment 1. For brevity, further details are omitted here.

[0077] It should be understood that in this embodiment, the processor can be a central processing unit (CPU), or it can be other general-purpose processors, digital signal processors (DSPs), application-specific integrated circuits (ASICs), programmable gate arrays (FPGAs), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. The general-purpose processor can be a microprocessor or any conventional processor, etc.

[0078] Memory may include read-only memory and random access memory, and provides instructions and data to the processor. A portion of memory may also include non-volatile random access memory. For example, memory may also store information about the device type.

[0079] A computer-readable storage medium for storing computer instructions, which, when executed by a processor, perform the method described in Embodiment 1.

[0080] The method in Example 1 can be directly implemented by a hardware processor, or implemented by a combination of hardware and software modules within the processor. The software modules can reside in readily available storage media in the field, such as random access memory, flash memory, read-only memory, programmable read-only memory, electrically erasable programmable memory, or registers. This storage medium is located in memory, and the processor reads information from the memory and, in conjunction with its hardware, completes the steps of the above method. To avoid repetition, a detailed description is not provided here.

[0081] Those skilled in the art will recognize that the units, i.e., algorithm steps, of the various examples described in connection with this embodiment can be implemented in electronic hardware or a combination of computer software and electronic hardware. Whether these functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementation should not be considered beyond the scope of this application.

[0082] While the specific embodiments of the present invention have been described above in conjunction with the accompanying drawings, this is not intended to limit the scope of protection of the present invention. Those skilled in the art should understand that various modifications or variations that can be made by those skilled in the art without creative effort based on the technical solutions of the present invention are still within the scope of protection of the present invention.

Claims

1. A conformal design method for an aero-engine fuel-lubricating oil heat exchanger, characterized in that, include: Obtain the modeling space of the heat exchange core, and perform hexahedral conformal partitioning on the modeling space to obtain a hexahedral space composed of hexahedral elements; Construct heat exchange units, predict the heat transfer of each heat exchange unit at the current position based on the deformation matrix between each hexahedral unit and the standard hexahedral unit and the inlet heat transfer boundary conditions, and determine the initial heat exchange unit at the current position accordingly. In this process, by setting the inlet temperature and inlet velocity of the two fluids and applying a deformation matrix to the heat exchange unit, the heat exchange unit is simulated and analyzed to obtain a dataset of heat exchange performance under different deformation states. This dataset is then used to train a neural network for predicting heat exchange performance, which includes heat exchange, outlet velocity of the two fluids, and outlet temperature. The outlet heat exchange boundary condition of the initial heat exchange unit is used as the inlet heat exchange boundary condition of the neighboring location. Candidate heat exchange units are determined for the neighboring locations of the current location. Based on the candidate heat exchange units of all neighboring locations, the unit combination with the largest total heat exchange is determined, thereby determining the unit combination of the current location. In the process of determining the unit combination at the current position, a fuel connectivity graph is generated based on the fuel inlet and outlet positions in the candidate heat exchange units, and a lubricating oil connectivity graph is generated based on the lubricating oil inlet and outlet positions. The validity of the fuel connectivity graph and the lubricating oil connectivity graph is checked respectively, so as to select the unit combination with the largest total heat exchange under the condition that the fuel connectivity graph and the lubricating oil connectivity graph are directed acyclic graphs. The heat exchange core is obtained by combining the units at each location, and the overall structure of the heat exchanger is obtained by combining the heat exchange core and the shape of the heat exchanger.

2. The conformal design method for an aero-engine fuel-lubricating oil heat exchanger as described in claim 1, characterized in that, The heat exchange boundary conditions include fuel inlet velocity, lubricating oil inlet velocity, fuel inlet temperature, and lubricating oil inlet temperature.

3. The conformal design method for an aero-engine fuel-lubricating oil heat exchanger as described in claim 1, characterized in that, The heat exchange unit is constructed based on a three-period minimal surface.

4. The conformal design method for an aero-engine fuel oil heat exchanger as described in claim 1, characterized in that, The heat exchange unit with the largest heat exchange capacity is selected as the initial heat exchange unit for the current position.

5. The conformal design method for an aero-engine fuel oil heat exchanger as described in claim 1, characterized in that, The heat exchange core is obtained by taking the union of the unit combinations at each location, and the overall structure of the heat exchanger is obtained by taking the union of the heat exchange core and the heat exchanger outline.

6. A conformal design system for an aero-engine fuel-lubricating oil heat exchanger, characterized in that, include: The space processing module is configured to obtain the modeling space of the heat exchange core, perform hexahedral conformal partitioning on the modeling space, and obtain a hexahedral space composed of hexahedral elements; The unit construction module is configured to construct heat exchange units. It predicts the heat transfer of each heat exchange unit at the current position based on the deformation matrix between each hexahedral unit and the standard hexahedral unit and the inlet heat transfer boundary conditions, and determines the initial heat exchange unit at the current position accordingly. In this process, by setting the inlet temperature and inlet velocity of the two fluids and applying a deformation matrix to the heat exchange unit, the heat exchange unit is simulated and analyzed to obtain a dataset of heat exchange performance under different deformation states. This dataset is then used to train a neural network for predicting heat exchange performance, which includes heat exchange, outlet velocity of the two fluids, and outlet temperature. The layout optimization module is configured to use the outlet heat exchange boundary condition of the initial heat exchange unit as the inlet heat exchange boundary condition of the neighboring positions to determine candidate heat exchange units for the neighboring positions of the current position, and to determine the unit combination with the largest total heat exchange based on the candidate heat exchange units of all neighboring positions, thereby determining the unit combination of the current position. In the process of determining the unit combination at the current position, a fuel connectivity graph is generated based on the fuel inlet and outlet positions in the candidate heat exchange units, and a lubricating oil connectivity graph is generated based on the lubricating oil inlet and outlet positions. The validity of the fuel connectivity graph and the lubricating oil connectivity graph is checked respectively, so as to select the unit combination with the largest total heat exchange under the condition that the fuel connectivity graph and the lubricating oil connectivity graph are directed acyclic graphs. The structure determination module is configured to obtain the heat exchange core based on the unit combination at each location, and to obtain the overall structure of the heat exchanger based on the heat exchange core and the shape of the heat exchanger.

7. An electronic device, characterized in that, It includes a memory and a processor, as well as computer instructions stored in the memory and running on the processor, which, when executed by the processor, perform the method according to any one of claims 1-5.

8. A computer-readable storage medium, characterized in that, Used to store computer instructions, which, when executed by a processor, perform the method described in any one of claims 1-5.

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