A thermal-fluid coupling analysis method, apparatus, and electronic device

Abstract

This disclosure provides a heat-fluid coupling analysis method, apparatus, and electronic device. The disclosure acquires the heat flow between air and an aerospace component; the heat flow indicates the amount and direction of heat transferred between the air and the aerospace component per unit time; the heat flow is input into an air calculation module to obtain the temperature rise data of the aerospace component along the flow path; the air calculation module determines the temperature rise based on energy conservation; the temperature rise data along the flow path indicates the temperature change data during heat exchange between the air and the aerospace component; based on the heat flow and the temperature rise data along the flow path, a heat-fluid coupling analysis result is generated; the heat-fluid coupling analysis result includes at least: heat flow number, temperature rise data number, preset temperature threshold, heat flow, and temperature rise data along the flow path; the heat-fluid coupling analysis result is presented. In summary, the technical solution provided by this disclosure can improve the accuracy and efficiency of heat-fluid coupling analysis and can adapt to various application scenarios.

Description

Technical Field

[0001] This disclosure relates to the field of thermal-fluid coupling in aviation, and more particularly to a thermal-fluid coupling analysis method, apparatus, and electronic equipment. Background Technology

[0002] Currently, most existing thermal-fluid coupling analyses of airflow and aerospace component temperatures rely on manual estimation based on experience or separate analyses across different software programs. However, manual estimation methods suffer from low accuracy and efficiency, failing to meet the analytical needs of complex operating conditions. Cross-software analysis methods require manual data transfer between the two systems, which is not only time-consuming and labor-intensive but also prone to data bias due to human error. In summary, existing thermal-fluid coupling analyses have low accuracy and efficiency, making them unsuitable for diverse application scenarios. Summary of the Invention

[0003] This disclosure provides a thermal-fluid coupling analysis method, apparatus, and electronic device to address, to some extent, the problems of low accuracy and efficiency of existing thermal-fluid coupling analysis methods, which are difficult to adapt to various application scenarios.

[0004] According to one aspect of this disclosure, a heat-fluid coupling analysis method is provided, the method comprising: acquiring the heat flow between air and an aircraft component; the heat flow being used to indicate the amount of heat transferred between the air and the aircraft component per unit time and the direction of transfer; inputting the heat flow into an air calculation module to obtain the temperature rise data of the aircraft component along the flow path; the air calculation module determining the temperature rise data based on energy conservation; the temperature rise data along the flow path being used to indicate the temperature change data of the air exchanging heat with the aircraft component during the heat transfer process; generating a heat-fluid coupling analysis result based on the heat flow and the temperature rise data along the flow path; the heat-fluid coupling analysis result including at least: heat flow number, temperature rise data number, preset temperature threshold, heat flow, and temperature rise data along the flow path; and presenting the heat-fluid coupling analysis result.

[0005] Furthermore, according to one aspect of the method disclosed herein, obtaining the heat flow between air and an aircraft component includes: determining the contact area between the aircraft component and the air using a cross-sectional profile method; performing thermal analysis calculations on the aircraft component using thermal analysis software to obtain the heat flux density of the aircraft component; the heat flux density is used to indicate the amount of heat transferred per unit area of ​​air contacting the aircraft component; multiplying the contact area by the heat flux density to obtain a heat value; determining the transfer direction as air flowing towards the aircraft component when the initial temperature of the air is greater than or equal to the initial temperature of the aircraft component; determining the transfer direction as air flowing towards the aircraft component when the initial temperature of the air is less than the initial temperature of the aircraft component; and determining the heat value and transfer direction as the heat flow rate.

[0006] Furthermore, according to one aspect of the method of this disclosure, the thermal analysis software includes at least one of the following: ANSYS software and ABAQUS software.

[0007] Furthermore, according to one aspect of the method disclosed herein, heat flow is input into an air calculation module to obtain the temperature rise data along the path of the aerospace component, including: acquiring the rate of change of air internal energy and the heat conduction rate inside the air; establishing a first energy conservation equation; the first energy conservation equation being that the rate of change of air internal energy is equal to the heat conduction rate inside the air minus the heat flow; substituting the heat flow into the first energy conservation equation to obtain the temperature distribution data of the air in the direction of transmission; and integrating the temperature distribution data to obtain the temperature rise data along the path.

[0008] Furthermore, according to one aspect of the method of this disclosure, when the internal energy of the air remains unchanged, a second energy conservation equation is established; the second energy conservation equation states that the heat conduction rate inside the air is equal to the heat flow.

[0009] Furthermore, according to one aspect of the method of this disclosure, when the temperature rise data along the friction path is greater than the wall temperature rise threshold of the aerospace part, the maximum threshold of the temperature rise data along the friction path is determined as the wall temperature rise threshold.

[0010] Furthermore, according to one aspect of the method of this disclosure, heat flow coupling analysis results are generated based on heat flow and friction-induced temperature rise data, including: determining the header of a comma-separated CSV table; the header includes: heat flow number, friction-induced temperature rise data number, preset temperature threshold, heat flow, friction-induced temperature rise data, and blank fields; the blank fields are supplementary information for the heat flow coupling analysis results; the supplementary information includes: data anomaly annotations; the heat flow and friction-induced temperature rise data are converted and numbered and filled into the CSV table to obtain the heat flow coupling analysis results.

[0011] Furthermore, according to one aspect of the method of this disclosure, presenting the results of thermal-fluid coupling analysis includes: converting the results of thermal-fluid coupling analysis into JSON format and presenting them in at least one of the following forms: numerically labeled bar chart, color gradient cloud map, and transfer path trend curve.

[0012] According to another aspect of this disclosure, a heat flow coupling analysis device is provided, comprising: an acquisition unit for acquiring heat flow between air and an aircraft component; the heat flow is used to indicate the amount of heat transferred between air and the aircraft component per unit time and the direction of transfer; a calculation unit for inputting the heat flow into an air calculation module to obtain the temperature rise data of the aircraft component along the flow path; the air calculation module is determined based on energy conservation; the temperature rise data along the flow path is used to indicate the temperature change data of heat exchange between air and the aircraft component during heat transfer; a generation unit for generating heat flow coupling analysis results based on the heat flow and the temperature rise data along the flow path; the heat flow coupling analysis results include at least: heat flow number, temperature rise data number, preset temperature threshold, heat flow, and temperature rise data along the flow path; and a presentation unit for presenting the heat flow coupling analysis results.

[0013] According to another aspect of this disclosure, an electronic device is provided, comprising: a memory for storing computer-readable instructions; and a processor for executing the computer-readable instructions, causing the electronic device to perform the method as described in any embodiment of one aspect.

[0014] This disclosure provides a heat-fluid coupling analysis method, apparatus, and electronic device. The method involves acquiring the heat flow between air and an aircraft component; the heat flow indicates the amount and direction of heat transferred between the air and the aircraft component per unit time; the heat flow is input into an air calculation module to obtain the temperature rise data along the path of the aircraft component; the air calculation module determines the temperature rise based on energy conservation; the temperature rise data along the path indicates the temperature change data during heat exchange between the air and the aircraft component; based on the heat flow and the temperature rise data along the path, a heat-fluid coupling analysis result is generated; the heat-fluid coupling analysis result includes at least: heat flow number, temperature rise data number, preset temperature threshold, heat flow, and temperature rise data along the path; and the heat-fluid coupling analysis result is presented. Compared to existing heat-fluid coupling analysis methods that rely on manual estimation based on experience, manual data transfer, and difficulty in guaranteeing accuracy, this disclosure automates the entire process of heat flow acquisition, temperature rise calculation, result generation, and presentation. Furthermore, based on the principle of energy conservation and a standardized data association mechanism, it significantly improves the accuracy of the analysis results, completely solving the problems of low efficiency, error-proneness, insufficient accuracy, and cross-software transmission associated with manual operation. In summary, the technical solution provided in this disclosure can improve the accuracy and efficiency of thermal-fluid coupling analysis and can be adapted to various application scenarios.

[0015] It should be understood that both the foregoing general description and the following detailed description are exemplary and intended to provide further illustration of the claimed technology. Attached Figure Description

[0016] The above and other objects, features, and advantages of this disclosure will become more apparent from the more detailed description of the embodiments thereof in conjunction with the accompanying drawings. The drawings are provided to further illustrate the embodiments of this disclosure and form part of the specification. They are used together with the embodiments of this disclosure to explain the disclosure and do not constitute a limitation thereof. In the drawings, the same reference numerals generally represent the same components or steps.

[0017] Figure 1 A schematic flowchart of a heat-fluid coupling analysis method provided in an embodiment of this disclosure; Figure 2 A schematic diagram of another complete heat-fluid coupling analysis provided for an embodiment of this disclosure; Figure 3 A schematic view showing the results of a thermal-fluid coupling analysis provided in an embodiment of this disclosure; Figure 4A structural block diagram of a thermal-fluid coupling analysis device provided in an embodiment of this disclosure; Figure 5 This is a hardware block diagram of an electronic device provided in an embodiment of the present disclosure. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of this disclosure more apparent, exemplary embodiments according to this disclosure will now be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are merely some embodiments of this disclosure, and not all embodiments of this disclosure. It should be understood that this disclosure is not limited to the exemplary embodiments described herein.

[0019] Currently, most existing thermal-fluid coupling analyses of airflow and aerospace component temperatures rely on manual estimation based on experience or separate analyses across different software programs. However, manual estimation methods suffer from low accuracy and efficiency, failing to meet the analytical needs of complex operating conditions. Cross-software analysis methods require manual data transfer between the two systems, which is not only time-consuming and labor-intensive but also prone to data bias due to human error. In summary, existing thermal-fluid coupling analyses have low accuracy and efficiency, making them unsuitable for diverse application scenarios.

[0020] Therefore, in response to the aforementioned problems, this disclosure provides a method for heat flux coupling analysis. Compared with existing heat flux coupling analysis methods that rely on manual estimation based on experience, manual data transmission, and difficulty in guaranteeing accuracy, this disclosure can automate the entire process of heat flux acquisition, along-process temperature rise calculation, result generation, and presentation. At the same time, based on the principle of energy conservation and a standardized data association mechanism, it significantly improves the accuracy of analysis results and completely solves the problems of low efficiency, error-proneness, insufficient accuracy, and cross-software transmission caused by manual operation.

[0021] First, this disclosure provides a method for thermal-fluid coupling analysis. Please refer to... Figure 1 , Figure 1 This is a schematic flowchart illustrating a thermal-fluid coupling analysis method provided in an embodiment of this disclosure. Figure 1 As shown, the method includes: In step S101, the heat flow between the air and the aircraft parts is obtained; the heat flow is used to indicate the amount of heat transferred between the air and the aircraft parts per unit time and the direction of transfer. In step S102, the heat flow is input into the air calculation module to obtain the temperature rise data along the path of the aircraft parts; the air calculation module determines the temperature rise based on the law of conservation of energy; the temperature rise data along the path is used to indicate the temperature change data of the air exchanging heat with the aircraft parts during the heat transfer process. In step S103, heat flow coupling analysis results are generated based on heat flow and friction temperature rise data; the heat flow coupling analysis results include at least: heat flow number, friction temperature rise data number, preset temperature threshold, heat flow, and friction temperature rise data; In step S104, the results of the thermal-fluid coupling analysis are presented.

[0022] In this disclosure, heat flow can be understood as a comprehensive parameter of the amount and direction of heat transferred from one side to the other per unit time during the heat exchange process between air and aerospace components. Its value is determined by factors such as the temperature difference between air and aerospace components, contact area, and heat transfer coefficient. The calculation process will be detailed later.

[0023] In this disclosure, the air calculation module can be understood as a dedicated calculation unit built on the principle of energy conservation. It can receive heat flow data and automatically calculate the temperature change after the air exchanges heat with the aviation parts during the flow process. It does not require manual intervention and can effectively avoid the errors caused by empirical estimation. It is suitable for the calculation of the temperature rise along the path under the complex operating conditions of aero engines.

[0024] In this disclosure, the temperature rise data along the flow path can be understood as a specific set of data showing the gradual change in temperature of air as it exchanges heat with the aerospace parts along the flow path and in the direction of heat transfer. This data can accurately reflect the temperature state of air at different locations.

[0025] In this disclosure, the results of the heat-fluid coupling analysis can be understood as a standardized and integrated output of the heat-fluid coupling analysis process and results, including a structured data set containing information such as heat flow, friction-flow temperature rise data and associated numbers, and preset temperature thresholds. The heat flow number and friction-flow temperature rise data number are used to achieve unique association and traceability between the two types of data; the preset temperature threshold is the upper limit standard of air temperature corresponding to the safe operation of aerospace parts, which can be used to quickly determine whether the friction-flow temperature rise data meets the operating conditions.

[0026] Specifically, the following steps can be included when performing heat-fluid coupling analysis: First, fluid and solid domain models of the aero-engine air system are constructed. Next, based on these models, parameters such as the temperature difference, contact area, and heat transfer coefficient between the air and aero-engine components are determined. The heat transferred between the air and aero-engine components per unit time is calculated, and the transfer direction is determined based on their initial temperatures, thus obtaining the heat flow rate. Then, the obtained heat flow rate is input into an air calculation module built based on the principle of energy conservation. The module automatically performs calculations to obtain the temperature rise data along the airflow path, which varies with the flow path. A preset temperature threshold is then used to determine whether the data meets the operating requirements. Finally, unique association numbers are assigned to the heat flow rate and the temperature rise data. The heat flow rate number, the temperature rise data number, the preset temperature threshold, and the heat flow rate and temperature rise data are integrated into a standardized heat-fluid coupling analysis result, which is then presented visually.

[0027] The following will elaborate on how this disclosure obtains the thermal process, including: The contact area between aerospace parts and air is determined using the cross-sectional profile method. Thermal analysis software is used to perform thermal analysis calculations on aerospace parts to obtain their heat flux density; heat flux density is used to indicate the amount of heat transferred per unit area when air comes into contact with the aerospace parts. Multiply the contact area by the heat flux density to obtain the heat value; When the initial temperature of the air is greater than or equal to the initial temperature of the aircraft parts, the transmission direction is determined to be airflow towards the aircraft parts; When the initial temperature of the air is lower than the initial temperature of the aircraft parts, the transmission direction is determined to be from the aircraft parts to the air. The heat value and the direction of transfer are defined as heat flow.

[0028] In this disclosure, the section profile method can be understood as a geometric analysis method that draws a section along a characteristic cross-section of the airflow path, and calculates the area of ​​the contact region between the air and the part through the intersection of the section profile and the wall of the part. The contact area obtained by the section profile method can be understood as the actual area of ​​the contact region where air exchanges heat with the aerospace part during the flow process.

[0029] In this disclosure, the thermal analysis software can be understood as specialized engineering simulation software capable of calculating solid heat conduction and fluid-solid heat transfer, and outputting heat flux density data based on the material properties and boundary temperature conditions of aerospace components. The thermal analysis software disclosed herein may include, but is not limited to, at least one of the following: ANSYS software and ABAQUS software. ANSYS software can quickly solve for the heat flux density distribution on the component wall through its steady-state thermal analysis module, while ABAQUS software is suitable for transient thermal analysis under complex operating conditions; both can meet the heat flux density calculation requirements of this disclosure.

[0030] In this disclosure, heat flux density can be understood as the amount of heat passing through a unit area per unit time, and its value can directly reflect the heat exchange intensity between air and aerospace components.

[0031] Specifically, determining heat flow can include the following steps: First, the 3D geometric model of the aerospace component is imported into the geometric analysis software. Multiple feature sections are selected along the airflow direction, and cross-sections are drawn at each section. Next, the contact area between the air and the aerospace component at each section is calculated using the cross-section method, and the total contact area is obtained. Then, at least one of the material properties and initial temperature conditions of the aerospace component can be input into the thermal analysis software. The temperature boundary on the air side is set, and the thermal analysis calculation is run to output the heat flux density data of the component wall. Furthermore, the total contact area can be multiplied by the heat flux density to calculate the heat transferred between the air and the aerospace component per unit time. Then, the initial temperature of the air and the initial temperature of the aerospace component are collected, and the values ​​of the two are compared to determine the direction of heat transfer. Finally, the heat value and the transfer direction are integrated to form a complete heat flow parameter.

[0032] The following will explain in detail how this disclosure obtains the temperature rise data along the route, including: To obtain the rate of change of internal energy of air and the rate of heat conduction inside the air; Establish the first energy conservation equation; the first energy conservation equation is that the rate of change of the internal energy of air is equal to the conductivity velocity inside the air minus the heat flow. Substituting the heat flow into the first energy conservation equation, we obtain the temperature distribution data of the air in the direction of heat transfer. The temperature distribution data is integrated to obtain the temperature rise data along the path.

[0033] In this disclosure, the rate of change of the internal energy of air can be understood as the rate of change of the internal energy of a unit mass of air over time during the flow process, and its value can directly reflect the dynamic trend of air temperature change.

[0034] In this disclosure, the heat conduction rate inside the air can be understood as the rate of heat conduction in the direction of air flow, which is determined by the thermal conductivity and temperature gradient, and represents the intensity of heat transfer inside the air.

[0035] In this disclosure, the first energy conservation equation can be understood as the governing equation describing the energy conservation relationship in the air flow heat transfer process, reflecting the dynamic balance between changes in the air's internal energy, internal heat conduction, and external heat transfer. For example, the expression of the first energy conservation equation can satisfy the following:

[0036] in, It is expressed as the rate of change of the internal energy of a unit mass of air over time (i.e., the rate of change of the internal energy of air). It is expressed as the thermal conductivity of air. It is represented as the temperature gradient of air in the direction of airflow. It is expressed as the density of air. It is expressed as the heat flow between air and aircraft parts.

[0037] In this disclosure, temperature distribution data can be understood as the set of temperature values ​​at different locations along the air flow path, which is the basic data for calculating the temperature rise along the flow path.

[0038] In this disclosure, integral calculation can be understood as performing integral calculations on temperature distribution data in the direction of air flow to obtain the total temperature change of the air from the initial position to the target position.

[0039] Specifically, acquiring temperature rise data along the friction path can include the following steps: First, heat flow is imported from the heat flow acquisition stage. And determine the density of air. thermal conductivity Next, the first energy conservation equation is established, and by substituting the above parameters, the temperature gradient of the air in the flow direction is obtained. Then, by integrating the temperature gradient, the temperature distribution data of the air in the transmission direction is obtained. Finally, the initial and final positions of the airflow are selected, and the temperature difference between the two points is calculated to obtain the temperature rise data along the flow path.

[0040] It should be noted that when the internal energy of the air within this disclosure does not change, that is, when the rate of change of the internal energy of the space is zero, a second energy conservation equation can be established; the second energy conservation equation states that the rate of heat conduction inside the air is equal to the heat flow.

[0041] In this disclosure, the second energy conservation equation can be understood as a simplified form of the first energy conservation equation under steady-state flow conditions, applicable to scenarios where the air temperature distribution does not change with time. For example, the expression for the second energy conservation equation can satisfy the following:

[0042] This simplified equation can significantly reduce computational complexity and is suitable for the high-efficiency computing needs in engineering scenarios.

[0043] It should also be noted that after obtaining the temperature rise data along the path using the above method, calibration is required based on the wall temperature rise threshold of the aerospace parts. Specifically, the method includes: When the temperature rise along the process exceeds the wall temperature rise threshold of the aerospace part, the maximum threshold of the temperature rise along the process is determined as the wall temperature rise threshold.

[0044] In this disclosure, the wall temperature rise threshold of aerospace components can be understood as the upper limit of the air temperature corresponding to the safe operation of the aerospace components, which is determined by the heat resistance of the component material and the operating conditions. During calibration, the calculated temperature rise data along the flow path is compared with this threshold. If it exceeds the threshold, it is automatically corrected to the upper limit to avoid unreasonable calculation results and ensure the reliability of the analysis.

[0045] The following will describe in detail how this disclosure generates heat-fluid coupling analysis results, including the following methods: Determine the header of the comma-separated CSV table; the header includes: heat flow number, friction-curing data number, preset temperature threshold, heat flow, friction-curing data, and blank fields; blank fields provide supplementary information for the heat-fluid coupling analysis results; supplementary information includes: data anomaly annotations; The heat flow and friction temperature rise data are converted, numbered, and entered into a CSV table to obtain the heat flow coupling analysis results.

[0046] In this disclosure, Comma-Separated Values ​​(CSV) can be understood as a lightweight plain text data exchange format that uses commas as delimiters to separate different data columns.

[0047] In this disclosure, the header can be understood as the column name identifier of a CSV table, used to define the attributes and meaning of each column of data, and is a core element to ensure data readability and automated parsing. The following explains in detail everything contained in the header: The heat flow number can be understood as a unique identifier code assigned to each heat flow data point, used to distinguish heat flow parameters from different sources, locations, or operating conditions. The friction-through temperature rise data number can be understood as a unique identifier code corresponding one-to-one with the heat flow number, used to establish the association between friction-through temperature rise data and heat flow data, ensuring accurate matching of the two core data types. The preset temperature threshold can be understood as a pre-set upper limit value of air temperature corresponding to the safe operation of aerospace parts, serving as a verification standard for judging whether friction-through temperature rise data meets operating condition requirements. Heat flow can be understood as a comprehensive parameter of the heat value and direction transferred between air and aerospace parts per unit time, and is the core input basis for calculating friction-through temperature rise data. Friction-through temperature rise data can be understood as a specific set of values ​​showing the gradual temperature change of air as it exchanges heat with aerospace parts along the flow path, intuitively reflecting the dynamic change characteristics of air temperature. Blank fields can be understood as extended information columns reserved for the results of thermal-fluid coupling analysis. They are used to record supplementary content such as data anomaly annotations, calculation condition descriptions, and data source notes, thereby improving the traceability of the analysis results.

[0048] Specifically, generating heat-fluid coupling analysis results may include the following steps: First, define the header of the CSV table, setting six column names in sequence: Heat Flow Number, Friction Temperature Rise Data Number, Preset Temperature Threshold, Heat Flow, Friction Temperature Rise Data, and Blank Field. Next, assign unique and consecutive numbers to the acquired heat flow and friction temperature rise data, ensuring no duplicates, no gaps, and that the numbers include numeric items for easy sorting. Then, fill in the corresponding columns with the heat flow number, friction temperature rise data number, preset temperature threshold, heat flow value, and friction temperature rise data. Additionally, any abnormal data encountered during the calculation process (such as friction temperature rise data exceeding the preset temperature threshold) can be marked and filled into the blank field. Finally, verify the consistency of the data format in each column of the table, ensuring that no strings are mixed into the numerical data. After verification, save the table as a CSV file to obtain the heat flow coupling analysis results.

[0049] The following will specifically describe how this disclosure presents the results of heat-fluid coupling analysis, including the following methods: The results of the thermal-fluid coupling analysis are converted into JSON format and presented in at least one of the following formats: numerically labeled bar chart, color gradient cloud map, and transfer path trend curve.

[0050] In this disclosure, JSON format can be understood as a lightweight data exchange format based on a key-value pair structure, characterized by clear hierarchy and ease of parsing, and suitable for converting CSV format analysis results into a data structure that can be recognized by a visual interface.

[0051] In this disclosure, the numerically labeled bar chart can be understood as a visual representation of the magnitude of temperature rise data or heat flow along the path by the height of the bar graph, while the specific values ​​are labeled at the top of the bar graph, which facilitates intuitive comparison of temperature changes or heat transfer intensity at different locations.

[0052] In this disclosure, the color gradient cloud map can be understood as a visualization form based on the division of fluid domain units, with different color gradients corresponding to different temperature rise values ​​along the flow path. It can intuitively present the temperature distribution pattern in the fluid domain and quickly locate high temperature areas.

[0053] In this disclosure, the transfer path trend curve can be understood as a curve plotted with the air flow path as the horizontal axis and the temperature rise data along the path as the vertical axis, used to show the trend of air temperature change with the flow process and clearly reflect the dynamic characteristics of the heat transfer process.

[0054] Specifically, the presentation process includes the following steps: First, the thermal-fluid coupling analysis results in CSV format are converted into standard JSON format data of [{'name':'temperature rise along the flow path', 'value': numerical value}]. Then, the JSON format data is imported into the visualization interface, and the presentation format is selected according to the analysis requirements: if it is necessary to compare values ​​at different locations, a bar chart with numerical annotations is generated; if it is necessary to observe the temperature distribution in the fluid domain, a color gradient cloud map is generated and specific values ​​are annotated at the unit level; if it is necessary to analyze the temperature change trend, a transfer path trend curve is generated.

[0055] For example, Figure 2 This is a schematic diagram of another complete heat-fluid coupling analysis process provided for embodiments of this disclosure. From Figure 2 As can be seen, this is a closed-loop iterative thermal-fluid coupling analysis process. The core is to achieve dynamic coordination between thermal analysis and air system calculations. The entire process includes: First, the thermal analysis calculation is initiated, outputting the heat flow between the air and the aircraft components. Then, the heat flow is input into the air system calculation module, which outputs the air's heat transfer characteristics (including temperature rise data along the flow path). The convergence of the calculation results is determined by iterative residual analysis: if the results converge ("Yes"), the process ends; if the results do not converge ("No"), the process proceeds to the "Process Name Index" stage, automatically updating boundary data and restarting the thermal analysis calculation until convergence is achieved. This process, through automated iteration and data interaction, avoids errors caused by manual data transmission, significantly improving the accuracy and efficiency of thermal-fluid coupling analysis.

[0056] For example, Figure 3 This is a schematic view illustrating the results of a thermal-fluid coupling analysis, provided as an embodiment of this disclosure. Figure 3 As can be seen, this is a visualization of the temperature rise along the fluid flow path, which intuitively shows the temperature change characteristics of air under different flow paths, including: Left side view (heating scenario): Air flows from the initial chamber (20000 Pa, 4000.0 K) through the free vortex structure to the target chamber (19000 Pa, 4300.0 K), showing a temperature increase of 30 K along the way. The flow rate is 0.1000 kg / s, clearly reflecting the temperature rise process after the air exchanges heat with the aerospace parts.

[0057] Right side view (cooling scenario): Air flows from the initial chamber (210000 Pa, 4000.0 K) through a path with a perforated plate structure to the target chamber (16000 Pa, 3600.0 K), showing a temperature drop of 40 K along the way, which intuitively presents the temperature reduction effect after the air exchanges heat with the structural components.

[0058] Figure 3The view can visualize the flow path through numerical annotations, allowing designers to quickly determine the rationality of the temperature rise along the flow path under different operating conditions, providing an intuitive reference for optimizing the thermal state of the aero-engine air system.

[0059] This disclosure also provides a thermal-fluid coupling analysis apparatus. Figure 4 A structural block diagram of a thermal-fluid coupling analysis device provided in this disclosure embodiment is shown below. Figure 4 As shown, the heat-fluid coupling analysis device 400 includes: The acquisition unit 401 is used to acquire the heat flow between air and aircraft parts; the heat flow is used to indicate the amount of heat transferred between air and aircraft parts per unit time and the direction of transfer; The calculation unit 402 is used to input the heat flow into the air calculation module to obtain the temperature rise data along the path of the aircraft parts; the air calculation module is determined based on the law of energy conservation; the temperature rise data along the path is used to indicate the temperature change data of the air exchanging heat with the aircraft parts during the heat transfer process. The generation unit 403 is used to generate heat flow coupling analysis results based on heat flow and friction rise data; the heat flow coupling analysis results include at least: heat flow number, friction rise data number, preset temperature threshold, heat flow, and friction rise data; Presentation unit 404 is used to present the results of the thermal-fluid coupling analysis.

[0060] In one exemplary embodiment, the acquisition unit 401 is specifically used to: determine the contact area between the aircraft part and the air using the cross-sectional profile method; perform thermal analysis calculations on the aircraft part using thermal analysis software to obtain the heat flux density of the aircraft part; the heat flux density is used to indicate the amount of heat transferred per unit area of ​​air contacting the aircraft part; multiply the contact area by the heat flux density to obtain the heat value; when the initial temperature of the air is greater than or equal to the initial temperature of the aircraft part, determine the transfer direction as air flowing to the aircraft part; when the initial temperature of the air is less than the initial temperature of the aircraft part, determine the transfer direction as the aircraft part flowing to the air; and determine the heat value and transfer direction as the heat flow rate.

[0061] In one exemplary embodiment, the acquisition unit 401 is specifically used for: thermal analysis software including at least one of the following: ANSYS software and ABAQUS software.

[0062] In one exemplary embodiment, the calculation unit 402 is specifically used to: obtain the rate of change of air internal energy and the heat conduction rate inside the air; establish a first energy conservation equation; the first energy conservation equation is that the rate of change of air internal energy is equal to the conduction rate inside the air minus the heat flow; substitute the heat flow into the first energy conservation equation to obtain the temperature distribution data of the air in the transmission direction; and perform integral calculation on the temperature distribution data to obtain the temperature rise data along the path.

[0063] In one exemplary embodiment, the calculation unit 402 is specifically used to: establish a second energy conservation equation when the internal energy of the air does not change; the second energy conservation equation states that the heat conduction rate inside the air is equal to the heat flow rate.

[0064] In one exemplary embodiment, the calculation unit 402 is specifically used to: determine the maximum threshold of the along-the-path heating data as the wall heating threshold when the along-the-path heating data is greater than the wall heating threshold of the aerospace part.

[0065] In one exemplary embodiment, the generation unit 403 is specifically used to: determine the header of the comma-separated CSV table; the header includes: heat flow number, friction-heating data number, preset temperature threshold, heat flow, friction-heating data, and blank field; the blank field is supplementary information for the heat-fluid coupling analysis results; the supplementary information includes: data anomaly annotation; convert and number the heat flow and friction-heating data and fill them into the CSV table to obtain the heat-fluid coupling analysis results.

[0066] Figure 5 This is a hardware block diagram of an electronic device provided according to an embodiment of the present disclosure. The electronic device 500 according to an embodiment of the present disclosure includes at least a processor; and a memory for storing computer-readable instructions. When the computer-readable instructions are loaded and executed by the processor, the processor performs the thermal-fluid coupling analysis method described in any of the preceding embodiments of the present disclosure.

[0067] Figure 5 The illustrated electronic device 500 specifically includes a central processing unit (CPU) 501, a graphics processing unit (GPU) 502, and a memory 503. These units are interconnected via a bus 504. The CPU 501 and / or GPU 502 can function as the aforementioned processor, and the memory 503 can function as the aforementioned memory storing computer-readable instructions. Furthermore, the electronic device 500 may also include a communication unit 505, a storage unit 506, an output unit 507, an input unit 508, and an external device 509, all of which are also connected to the bus 504.

[0068] In summary, this disclosure provides a heat-fluid coupling analysis method, apparatus, and electronic device. This disclosure acquires the heat flow between air and aerospace components; the heat flow indicates the amount and direction of heat transferred between air and aerospace components per unit time; the heat flow is input into an air calculation module to obtain the temperature rise data along the path of the aerospace components; the air calculation module determines the temperature rise based on energy conservation; the temperature rise data along the path indicates the temperature change data during heat exchange between air and aerospace components; based on the heat flow and temperature rise data, a heat-fluid coupling analysis result is generated; the heat-fluid coupling analysis result includes at least: heat flow number, temperature rise data number, preset temperature threshold, heat flow, and temperature rise data along the path; and the heat-fluid coupling analysis result is presented. Thus, compared to existing heat-fluid coupling analysis methods that rely on manual estimation based on experience, manual data transfer, and difficulty in guaranteeing accuracy, this disclosure can automate the entire process of heat flow acquisition, temperature rise calculation, result generation, and presentation. Furthermore, based on the principle of energy conservation and a standardized data association mechanism, it significantly improves the accuracy of the analysis results, completely solving the problems of low efficiency, error-proneness, insufficient accuracy, and cross-software transmission caused by manual operation. In summary, the technical solution provided in this disclosure can improve the accuracy and efficiency of thermal-fluid coupling analysis and can be adapted to various application scenarios.

[0069] Those skilled in the art will recognize that the units and algorithm steps of the various examples described in conjunction with the embodiments disclosed herein 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 disclosure.

[0070] The basic principles of this disclosure have been described above with reference to specific embodiments. However, it should be noted that the advantages, benefits, and effects mentioned in this disclosure are merely examples and not limitations, and should not be considered as essential features of each embodiment of this disclosure. Furthermore, the specific details disclosed above are for illustrative and facilitative purposes only, and are not limitations. These details do not limit the scope of this disclosure to the necessity of employing the aforementioned specific details for implementation.

[0071] The block diagrams of devices, apparatuses, devices, and systems disclosed herein are merely illustrative examples and are not intended to require or imply that they must be connected, arranged, or configured in the manner shown in the block diagrams. As those skilled in the art will recognize, these devices, apparatuses, devices, and systems can be connected, arranged, and configured in any manner. Words such as “comprising,” “including,” “having,” etc., are open-ended terms meaning “including but not limited to,” and are used interchangeably with them. The terms “or” and “and” as used herein refer to the terms “and / or,” and are used interchangeably with them unless the context clearly indicates otherwise. The term “such as” as used herein refers to the phrase “such as but not limited to,” and is used interchangeably with it.

[0072] Additionally, as used herein, the "or" used in a list of items beginning with "at least one" indicates a separate list, such that a list of, for example, "at least one of A, B, or C" means A or B or C, or AB or AC or BC, or ABC (i.e., A and B and C). Furthermore, the word "exemplary" does not imply that the described example is preferred or better than other examples.

[0073] It should also be noted that in the systems and methods of this disclosure, the components or steps can be decomposed and / or recombined. These decompositions and / or recombinations should be considered as equivalent solutions to this disclosure.

[0074] Various changes, substitutions, and modifications can be made to the technology described herein without departing from the teachings defined by the appended claims. Furthermore, the scope of the claims of this disclosure is not limited to the specific aspects of the processes, machines, manufactures, events, means, methods, and actions described above. Currently existing or later-developed processes, machines, manufactures, events, means, methods, or actions that perform substantially the same function or achieve substantially the same result as the corresponding aspects described herein can be utilized. Therefore, the appended claims include such processes, machines, manufactures, events, means, methods, or actions within their scope.

[0075] The above description of the disclosed aspects is provided to enable any person skilled in the art to make or use this disclosure. Various modifications to these aspects will be readily apparent to those skilled in the art, and the general principles defined herein may be applied to other aspects without departing from the scope of this disclosure. Therefore, this disclosure is not intended to be limited to the aspects shown herein, but rather to be carried out within the widest scope consistent with the principles and novel features disclosed herein.

[0076] The above description has been given for purposes of illustration and description. Furthermore, this description is not intended to limit the embodiments of this disclosure to the forms disclosed herein. Although numerous exemplary aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, alterations, additions, and sub-combinations therein.

Claims

1. A heat-fluid coupling analysis method, characterized in that, The method includes: The heat flow between air and aircraft components is obtained; the heat flow is used to indicate the amount of heat transferred between the air and the aircraft components per unit time and the direction of transfer. The heat flow is input into the air calculation module to obtain the temperature rise data along the path of the aircraft component; the air calculation module determines the temperature rise based on energy conservation; the temperature rise data along the path is used to indicate the temperature change data of the air exchanging heat with the aircraft component during the heat transfer process. Based on the heat flow rate and the friction-flow temperature rise data, a heat flow coupling analysis result is generated; the heat flow coupling analysis result includes at least: heat flow rate number, friction-flow temperature rise data number, preset temperature threshold, heat flow rate, and friction-flow temperature rise data; The results of the heat-fluid coupling analysis are presented.

2. The method according to claim 1, characterized in that, The acquisition of heat flow between air and aircraft components includes: The contact area between the aerospace component and the air is determined using the cross-sectional profile method. The heat flux density of the aerospace component is obtained by performing thermal analysis calculations using thermal analysis software; the heat flux density is used to indicate the amount of heat transferred per unit area when the air contacts the aerospace component. Multiply the contact area by the heat flux density to obtain the heat value; When the initial temperature of the air is greater than or equal to the initial temperature of the aircraft component, the transmission direction is determined to be the air flowing towards the aircraft component; When the initial temperature of the air is lower than the initial temperature of the aircraft component, the transmission direction is determined to be from the aircraft component to the air. The heat value and the direction of transfer are determined as the heat flow rate.

3. The method according to claim 2, characterized in that, The thermal analysis software includes at least one of the following: ANSYS software and ABAQUS software.

4. The method according to claim 1, characterized in that, The step of inputting the heat flow into the air calculation module to obtain the temperature rise data along the path of the aerospace component includes: The rate of change of the internal energy of the air and the heat conduction rate inside the air are obtained; A first energy conservation equation is established; the first energy conservation equation states that the rate of change of the internal energy of the air is equal to the conductivity velocity inside the air minus the heat flow. Substituting the heat flow into the first energy conservation equation, the temperature distribution data of the air in the transmission direction is obtained; The temperature distribution data is integrated to obtain the temperature rise data along the path.

5. The method according to claim 4, characterized in that, When the internal energy of the air remains unchanged, a second energy conservation equation is established; the second energy conservation equation states that the heat conduction rate inside the air is equal to the heat flow.

6. The method according to claim 4, characterized in that, When the temperature rise along the flow path is greater than the wall temperature rise threshold of the aerospace part, the maximum threshold of the temperature rise along the flow path is determined as the wall temperature rise threshold.

7. The method according to claim 1, characterized in that, The generation of heat flux coupling analysis results based on the heat flow and the friction-induced temperature rise data includes: Determine the header of the comma-separated CSV table; the header includes: the heat flow number, the friction-through temperature rise data number, the preset temperature threshold, the heat flow, the friction-through temperature rise data, and a blank field; the blank field is supplementary information for the heat flow coupling analysis results; the supplementary information includes: data anomaly annotation; The heat flow rate and the friction-induced temperature rise data are converted, numbered, and entered into the CSV table to obtain the heat flow coupling analysis results.

8. The method according to claim 1, characterized in that, The presentation of the heat-fluid coupling analysis results includes: The heat-fluid coupling analysis results are converted into JSON format and presented in at least one of the following forms: numerically labeled bar chart, color gradient cloud map, and transfer path trend curve.

9. A heat-fluid coupling analysis device, characterized in that, The device includes: An acquisition unit is used to acquire the heat flow between air and aircraft parts; the heat flow is used to indicate the amount of heat transferred between the air and the aircraft parts per unit time and the direction of transfer; The calculation unit is used to input the heat flow into the air calculation module to obtain the temperature rise data along the path of the aircraft parts; the air calculation module is determined based on the law of energy conservation; the temperature rise data along the path is used to indicate the temperature change data of the air exchanging heat with the aircraft parts during the heat transfer process; The generation unit is used to generate heat flow coupling analysis results based on the heat flow and the friction-through temperature rise data; the heat flow coupling analysis results include at least: heat flow number, friction-through temperature rise data number, preset temperature threshold, heat flow, and friction-through temperature rise data; The presentation unit is used to present the results of the thermal-fluid coupling analysis.

10. An electronic device, characterized in that, include: Memory, used to store computer-readable instructions; as well as A processor for executing the computer-readable instructions, causing the electronic device to perform the method as described in any one of claims 1-8.

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