Method for detecting global temperature distribution of nacelle loaded with turboprop engine

Abstract

The invention provides a method for detecting global temperature distribution of a nacelle loaded with a turboprop engine, and relates to the technical field of aeronautical engineering.The method comprises the steps that a first nacelle model is generated according to temperature distribution of the surface of the turboprop engine at different stages and the ventilation requirements of air intake and exhaust of the nacelle; extracting a fluid computational domain of the first nacelle model, and performing temperature field and airflow field analysis on the fluid computational domain to obtain a temperature distribution cloud picture and an airflow vector distribution picture of the first nacelle model; if the temperature distribution cloud picture and the airflow vector distribution picture both meet the preset requirements, aerodynamic configuration details and internal solid components of the first nacelle model are added, and a second nacelle model is generated; and performing fluid-structure interaction conjugate heat transfer analysis on the second nacelle model under different working conditions, optimizing the nacelle air intake and exhaust layout according to the result of the conjugate heat transfer analysis, and generating a target nacelle ventilation and heat dissipation scheme. The nacelle has the technical effect that the overall performance and reliability of the nacelle are improved.

Description

Technical Field

[0001] The present application relates to the field of aviation engineering technology, and in particular to a method, device, equipment and storage medium for detecting the global temperature distribution of a nacelle equipped with a turboprop engine. Background Art

[0002] As an efficient aviation power system, turboprop engines are widely used in medium- and short-range air transport and military purposes. However, turboprop engines generate a lot of heat during operation. If the heat management is not effective, the performance and life of the engine will be seriously affected. Therefore, designing a nacelle system that can effectively dissipate heat is crucial to ensure the normal operation of the turboprop engine.

[0003] Traditional nacelle design methods usually rely on simplified models and empirical formulas. Although these methods can solve the thermal management problem to a certain extent, they often have the problem of insufficient accuracy. Specifically, simplified models and empirical formulas are difficult to accurately capture complex thermal flow phenomena, especially when considering different flight states and environmental conditions, and their predicted results may deviate greatly from the actual situation. This lack of accuracy may lead to the neglect of hot spots in the design or excessive heat dissipation in certain areas, thus affecting the overall performance and reliability of the nacelle. Summary of the invention

[0004] The present application provides a method, device, equipment and storage medium for detecting the global temperature distribution of a nacelle equipped with a turboprop engine, which are used to accurately predict and effectively optimize the global temperature distribution of the nacelle, thereby improving the overall performance and reliability of the nacelle.

[0005] In a first aspect, the present application provides a method for detecting the global temperature distribution of a nacelle equipped with a turboprop engine, the method comprising: determining the temperature distribution of the surface of the turboprop engine at different stages and the ventilation requirements of the nacelle intake and exhaust according to the technical parameters and usage requirements of the turboprop engine; generating a first nacelle model according to the temperature distribution of the surface of the turboprop engine at different stages and the ventilation requirements of the nacelle intake and exhaust, wherein the first nacelle model is a nacelle model that ignores aerodynamic shape details and internal solid components; extracting the fluid calculation domain of the first nacelle model, performing temperature field and airflow field analysis on the fluid calculation domain, and obtaining a temperature distribution cloud map and an airflow vector distribution map of the first nacelle model; if the temperature distribution cloud map and the airflow vector distribution map both meet preset requirements, adding the aerodynamic shape details and internal solid components of the first nacelle model to generate a second nacelle model; performing fluid-solid coupling conjugate heat transfer analysis on the second nacelle model under different working conditions, optimizing the layout of the nacelle intake and exhaust according to the results of the conjugate heat transfer analysis, and generating a target nacelle ventilation and heat dissipation scheme.

[0006] By adopting the above technical solutions, based on the technical parameters and usage requirements of the turboprop engine, the engine surface temperature distribution and nacelle ventilation requirements are determined, laying the foundation for subsequent analysis. Then, by generating a simplified first nacelle model and performing temperature field and airflow field analysis, the feasibility of the initial design is quickly evaluated. If the preset requirements are met, the aerodynamic shape details and internal solid components are added to generate a more accurate second nacelle model. Finally, the second nacelle model is subjected to a fluid-solid coupling conjugate heat transfer analysis, considering the heat transfer characteristics under different working conditions, so as to optimize the nacelle intake and exhaust layout and generate the final ventilation and heat dissipation solution. This progressive analysis method not only improves the accuracy of temperature distribution prediction, but also identifies potential problems in the early design stage, reduces later modifications, thereby shortening the design cycle and improving design efficiency. At the same time, by considering the temperature distribution under different flight conditions, the effectiveness of the design scheme under various working conditions is ensured, and the overall performance and reliability of the nacelle are improved.

[0007] Optionally, generating a first nacelle model according to the temperature distribution of the surface of the turboprop engine at different stages and the ventilation requirements of the nacelle intake and exhaust includes: determining basic dimensions of the nacelle according to the temperature distribution of the surface of the turboprop engine at different stages and technical parameters of the turboprop engine; determining positions and dimensions of air inlets and exhaust ports of the nacelle according to ventilation volume requirements and flow rate requirements of the nacelle intake and exhaust; generating a three-dimensional digital model of the first nacelle model in combination with the basic dimensions of the nacelle and the positions and dimensions of the air inlets and exhaust ports of the nacelle; and importing the three-dimensional digital model of the first nacelle model into preset software for meshing and solution domain definition to generate the first nacelle model.

[0008] By adopting the above technical solution, the basic size of the nacelle is determined based on the surface temperature distribution and technical parameters of the turboprop engine, which ensures the compatibility of the nacelle with the engine. Then, the position and size of the air inlet and outlet are determined according to the ventilation volume requirement and flow rate requirement, which directly affects the heat dissipation effect of the nacelle. By combining these key parameters, a three-dimensional digital model of the first nacelle model is generated, laying the foundation for subsequent analysis. Finally, the model is imported into the preset software for meshing and solution domain definition to generate the first nacelle model that can be used for calculation and analysis. This method not only takes into account the thermal characteristics of the engine and the heat dissipation requirements of the nacelle, but also improves the accuracy and analyzability of the model through digital model and professional software processing. The whole process forms a complete chain from parameter determination to digital model and then to calculation model, which greatly improves the efficiency and accuracy of nacelle design.

[0009] Optionally, the extracting of the fluid calculation domain of the first nacelle model, performing temperature field and airflow field analysis on the fluid calculation domain, and obtaining a temperature distribution cloud map and an airflow vector distribution map of the first nacelle model includes: gridding and boundary condition setting of the fluid calculation domain according to the boundary conditions of the turboprop engine under different operating conditions; and iteratively calculating the fluid calculation domain on the basis of the gridding and the boundary condition setting to obtain a temperature distribution cloud map and an airflow vector distribution map of the first nacelle model.

[0010] By adopting the above technical solution, meshing and boundary condition setting are performed according to the boundary conditions of the turboprop engine under different working conditions, which ensures that the calculation model can fully reflect the complexity of the actual working environment. Then, iterative calculations are performed on this basis to obtain temperature distribution cloud maps and airflow vector distribution maps. This method not only takes into account the operating characteristics of the engine under different working conditions, but also improves the reliability of the calculation results through precise meshing and boundary condition setting. The iterative calculation process further ensures the convergence and accuracy of the results. Through this detailed analysis process, designers can more accurately grasp the temperature distribution and airflow characteristics inside the nacelle, provide reliable data support for subsequent design optimization, and help identify potential hot spots or airflow dead spots, so that targeted improvements can be made in the early stages of the design to improve the overall design efficiency and nacelle performance.

[0011] Optionally, after obtaining the temperature distribution cloud map and the airflow vector distribution map of the first nacelle model, it also includes: if the temperature distribution cloud map and / or the airflow vector distribution map do not meet the preset requirements, adjusting the nacelle intake and exhaust layout, and regenerating the first nacelle model until the regenerated temperature distribution cloud map and airflow vector distribution map of the first nacelle model both meet the preset requirements.

[0012] By adopting the above technical solution, when the temperature distribution cloud map and airflow vector distribution map of the first nacelle model do not meet the preset requirements, the method will automatically trigger the adjustment process, modify the nacelle intake and exhaust layout and regenerate the first nacelle model. This process will be repeated until the temperature distribution and airflow field that meet the preset requirements are obtained. This iterative optimization method can quickly identify and solve potential problems in the early stage of design, avoiding bringing unqualified design solutions into the subsequent more complex analysis stage. Through continuous optimization, this method ensures that the design solution entering the second nacelle model stage has good basic performance, thereby reducing the possibility of major modifications in the later stage and shortening the overall design cycle. At the same time, this method also improves the flexibility of design, allowing designers to continuously adjust and improve the nacelle intake and exhaust layout according to the analysis results, and finally obtain a more optimized design solution. This not only improves the heat dissipation efficiency and airflow distribution uniformity of the nacelle, but also lays a solid foundation for subsequent detailed design and analysis, effectively improving the quality and efficiency of the entire nacelle design process.

[0013] Optionally, the layout of the nacelle intake and exhaust is optimized according to the result of the conjugate heat transfer analysis to generate a target nacelle ventilation and heat dissipation scheme, including: extracting the temperature distribution cloud map and the airflow vector distribution map of the second nacelle model from the result of the conjugate heat transfer analysis, and judging whether the second nacelle model has an airflow stagnation area and a high temperature concentration area according to the temperature distribution cloud map and the airflow vector distribution map of the second nacelle model; if the airflow stagnation area and / or the high temperature concentration area exist, the second nacelle model is optimized, wherein if the airflow stagnation area exists, a ventilation airflow guide structure is added to the airflow stagnation area, and if the high temperature concentration area exists, a heat dissipation vent is added to the high temperature concentration area; on the basis of optimizing the second nacelle model, the geometric parameters of the nacelle intake and exhaust layout are optimized; the optimized nacelle intake and exhaust layout is applied to the second nacelle model, and the conjugate heat transfer analysis of fluid-solid coupling is re-performed until the analysis result meets the preset ventilation and heat dissipation performance index; and the target nacelle ventilation and heat dissipation scheme is generated according to the nacelle intake and exhaust layout that meets the preset ventilation and heat dissipation performance index.

[0014] By adopting the above technical scheme, the temperature distribution cloud map and airflow vector distribution map are extracted from the analysis results, and the airflow stagnation area and high temperature concentration area are accurately identified, which provides a clear goal for subsequent optimization. For the identified problem areas, the scheme adopts targeted optimization measures: adding ventilation airflow guide structure in the airflow stagnation area and adding heat dissipation vents in the high temperature concentration area. These measures directly improve the local thermal management effect. Subsequently, the geometric parameters of the nacelle intake and exhaust layout are optimized to further improve the overall heat dissipation performance. By repeatedly performing conjugate heat transfer analysis and optimization of fluid-solid coupling until the preset ventilation and heat dissipation performance indicators are met, the reliability and effectiveness of the final scheme are ensured. This iterative optimization process can not only solve the local thermal management problem, but also achieve overall performance improvement. The final target nacelle ventilation and heat dissipation scheme comprehensively considers the complex thermal flow phenomenon and can maintain excellent heat dissipation performance under various working conditions. This method significantly improves the accuracy and reliability of nacelle design, reduces the need for physical testing, shortens the development cycle, and provides a strong guarantee for the long-term stable operation of turboprop engines.

[0015] Optionally, after generating the target nacelle ventilation and heat dissipation scheme, it also includes: conducting a thermal analysis test on a scaled sample under wind tunnel test conditions to obtain a test temperature cloud map of the scaled sample, wherein the scaled sample is a scaled sample for nacelle thermal analysis made according to the target nacelle ventilation and heat dissipation scheme; calculating the temperature deviation between the test temperature cloud map of the scaled sample and the temperature distribution cloud map of the second nacelle model under the same operating conditions; if the temperature deviation is less than a preset temperature deviation threshold, sending the target nacelle ventilation and heat dissipation scheme to an operator's terminal device, so that the operator can make a nacelle thermal analysis prototype according to the target nacelle ventilation and heat dissipation scheme.

[0016] By adopting the above technical scheme, a scaled sample is made according to the ventilation and heat dissipation scheme of the target nacelle and a thermal analysis test is carried out to obtain the test temperature cloud map, which provides a practical reference for the theoretical analysis results. Subsequently, the temperature deviation is calculated by comparing the test temperature cloud map of the scaled sample with the temperature distribution cloud map of the second nacelle model under the same working conditions. This step effectively verifies the accuracy of the theoretical model. When the temperature deviation is less than the preset threshold, the ventilation and heat dissipation scheme of the target nacelle is sent to the terminal device of the operator, which ensures that the scheme used to make the prototype has been experimentally verified and has high reliability. This method of combining theoretical analysis with experimental verification not only improves the accuracy of the design scheme, but also greatly reduces the risk of problems that may be encountered in the later physical prototype production and testing. By performing scaled verification before the full-size prototype is produced, both R&D costs are saved and the development cycle is shortened.

[0017] Optionally, the method further includes: conducting a flight test on the nacelle thermal analysis prototype under actual flight conditions to obtain measured temperature distribution data of the nacelle thermal analysis prototype under various flight conditions; and verifying and adjusting the target nacelle ventilation and heat dissipation scheme based on the measured temperature distribution data of the nacelle thermal analysis prototype under various flight conditions to generate a final nacelle ventilation and heat dissipation design scheme.

[0018] By adopting the above technical solutions, flight tests were conducted on the nacelle thermal analysis prototype to obtain the measured temperature distribution data under various flight conditions, which provided the most realistic and comprehensive performance feedback for the design scheme. By comparing the data under real flight conditions with the theoretical predictions and wind tunnel test results, the actual effect of the target nacelle ventilation and heat dissipation scheme can be fully evaluated. Based on these measured data, the target scheme was checked and adjusted, and the final nacelle ventilation and heat dissipation design scheme not only took into account the results of theoretical analysis and wind tunnel tests, but also incorporated various complex factors in the real flight environment, such as high altitude low pressure, high-speed airflow, rapid temperature changes, etc. This comprehensive optimization method ensures that the final design scheme can maintain excellent heat dissipation performance in various actual flight conditions, greatly improving the reliability and adaptability of the design.

[0019] In a second aspect, the present application provides a device for detecting the global temperature distribution of a nacelle equipped with a turboprop engine, the device comprising: a determination module, a first generation module, an analysis module, an adjustment module and a second generation module; wherein the determination module is used to determine the temperature distribution of the surface of the turboprop engine at different stages and the ventilation requirements of the nacelle intake and exhaust according to the technical parameters and use requirements of the turboprop engine; the first generation module is used to generate a first nacelle model according to the temperature distribution of the surface of the turboprop engine at different stages and the ventilation requirements of the nacelle intake and exhaust, the first nacelle model being a nacelle model that ignores the details of the aerodynamic shape and the internal solid components; the analysis module is used to determine the temperature distribution of the surface of the turboprop engine at different stages and the ventilation requirements of the nacelle intake and exhaust according to the technical parameters and use requirements of the turboprop engine; the first generation module is used to generate a first nacelle model according to the temperature distribution of the surface of the turboprop engine at different stages and the ventilation requirements of the nacelle intake and exhaust The analysis module is used to extract the fluid calculation domain of the first nacelle model, perform temperature field and airflow field analysis on the fluid calculation domain, and obtain the temperature distribution cloud map and airflow vector distribution map of the first nacelle model; the adjustment module is used to add the aerodynamic shape details and internal solid components of the first nacelle model to generate a second nacelle model if both the temperature distribution cloud map and the airflow vector distribution map meet the preset requirements; the second generation module is used to perform fluid-solid coupling conjugate heat transfer analysis on the second nacelle model under different working conditions, optimize the layout of the nacelle intake and exhaust according to the result of the conjugate heat transfer analysis, and generate a target nacelle ventilation and heat dissipation scheme.

[0020] In a third aspect, the present application provides an electronic device, adopting the following technical solution: comprising a processor, a memory, a user interface and a network interface, the memory being used to store instructions, the user interface and the network interface being used to communicate with other devices, and the processor being used to execute the instructions stored in the memory so that the electronic device executes a computer program such as any of the above-mentioned methods for detecting the global temperature distribution of a nacelle equipped with a turboprop engine.

[0021] In a fourth aspect, the present application provides a computer-readable storage medium, which adopts the following technical solution: storing a computer program that can be loaded by a processor and execute any of the above-mentioned methods for detecting the global temperature distribution of a nacelle equipped with a turboprop engine.

[0022] In summary, the present application includes at least one of the following beneficial technical effects: Based on the technical parameters and usage requirements of the turboprop engine, the engine surface temperature distribution and nacelle ventilation requirements are determined to lay the foundation for subsequent analysis. Then, by generating a simplified first nacelle model and performing temperature field and airflow field analysis, the feasibility of the initial design is quickly evaluated. If the preset requirements are met, the aerodynamic shape details and internal solid components are added to generate a more accurate second nacelle model. Finally, the second nacelle model is subjected to a fluid-solid coupling conjugate heat transfer analysis, considering the heat transfer characteristics under different working conditions, so as to optimize the nacelle intake and exhaust layout and generate the final ventilation and heat dissipation solution. This progressive analysis method not only improves the accuracy of temperature distribution prediction, but also identifies potential problems in the early design stage, reduces later modifications, thereby shortening the design cycle and improving design efficiency. At the same time, by considering the temperature distribution under different flight conditions, the effectiveness of the design scheme under various working conditions is ensured, and the overall performance and reliability of the nacelle are improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a flow chart of a method for detecting the global temperature distribution of a nacelle equipped with a turboprop engine provided in an embodiment of the present application; Figure 2 It is a structural schematic diagram of a device for detecting the global temperature distribution of a nacelle equipped with a turboprop engine provided in an embodiment of the present application; Figure 3 It is a structural schematic diagram of an electronic device provided in an embodiment of the present application.

[0024] Description of reference numerals: 1000, electronic device; 1001, processor; 1002, communication bus; 1003, user interface; 1004, network interface; 1005, memory. DETAILED DESCRIPTION

[0025] In order to enable those skilled in the art to better understand the technical solutions in this specification, the technical solutions in the embodiments of this specification will be clearly and completely described below in conjunction with the drawings in the embodiments of this specification. Obviously, the described embodiments are only part of the embodiments of this application, not all of the embodiments.

[0026] In the description of the embodiments of the present application, words such as "illustrative", "for example" or "for example" are used to indicate examples, illustrations or descriptions. Any embodiment or design described as "illustrative", "for example" or "for example" in the embodiments of the present application should not be interpreted as being more preferred or more advantageous than other embodiments or designs. Specifically, the use of words such as "illustrative", "for example" or "for example" is intended to present related concepts in a concrete way.

[0027] Figure 1 is a flow chart of a method for detecting the global temperature distribution of a nacelle equipped with a turboprop engine provided in an embodiment of the present application. The present application discloses a method for detecting the global temperature distribution of a nacelle equipped with a turboprop engine, such as Figure 1 As shown, the method includes S101-S105.

[0028] S101. Determine the temperature distribution of the surface of the turboprop engine at different stages and the ventilation requirements of the nacelle intake and exhaust according to the technical parameters and usage requirements of the turboprop engine.

[0029] Specifically, a turboprop engine is an aircraft engine that combines the features of a gas turbine engine and a propeller. Its working principle is as follows: air enters the air intake at the front end of the engine, the air is compressed by the compressor, increasing the pressure and temperature, the compressed air enters the combustion chamber, mixes with the fuel and burns, the high-temperature and high-pressure gas drives the turbine to rotate, the turbine drives the compressor and propeller to rotate through the shaft, most of the energy is used to drive the propeller, generating forward thrust, and the remaining gas is discharged from the tail to provide additional thrust. The nacelle is the aerodynamic shell structure surrounding the engine.

[0030] In one example, it is necessary to first collect detailed technical parameters of the turboprop engine, including but not limited to the engine's power, size, weight, operating temperature range, etc. At the same time, it is also necessary to consider the engine's use requirements, such as flight altitude, speed, duration, etc. This information can usually be obtained from the technical manual or specification provided by the engine manufacturer.

[0031] Next, using these technical parameters and usage requirements, combined with the principles of thermodynamics and fluid mechanics, the heat output of the engine at different working stages (such as takeoff, cruising, and landing) is simulated through calculation or simulation software. This process may need to consider the impact of factors such as the combustion process inside the engine, mechanical friction, and exhaust system on the surface temperature distribution. Through this analysis, the temperature distribution diagram of the turboprop engine surface at each working stage can be obtained, and these temperature distribution diagrams will serve as an important basis for the subsequent nacelle design.

[0032] At the same time, the required ventilation volume of the nacelle is calculated based on the heat output of the engine and the operating environment. This calculation needs to take into account the heat dissipation requirements of the engine, the operating temperature requirements of the equipment inside the nacelle, and the external environmental conditions (such as atmospheric temperature, pressure, etc.). Through the heat balance calculation, the ventilation requirements of the nacelle intake and exhaust can be determined, including the required air flow, the approximate location and size of the air inlet and exhaust ports, etc.

[0033] S102, generating a first nacelle model according to the temperature distribution of the surface of the turboprop engine at different stages and the ventilation requirements of the nacelle intake and exhaust, wherein the first nacelle model is a nacelle model that ignores the details of the aerodynamic shape and the internal solid components.

[0034] In one example, the basic geometric dimensions of the nacelle are first determined using the turboprop engine surface temperature distribution data and nacelle ventilation requirement parameters obtained in S101. This includes the length, diameter, and approximate location and size of the air inlet and exhaust ports of the nacelle. Then, a simplified nacelle shape is created using 3D modeling software (such as CATIA, SolidWorks, etc.). This shape should be smooth, without complex curved surfaces or concave-convex structures, and only the main contour features should be retained.

[0035] During the modeling process, the following aspects were focused on: First, according to the size and installation requirements of the engine, the basic space that can accommodate the engine was designed. Second, according to the ventilation requirements calculated in S101, the position and size of the air intake and exhaust ports were set on the model. Finally, considering the temperature distribution of the engine at different working stages, areas that may require additional heat dissipation or insulation were reserved in the model.

[0036] This simplified model does not include internal solid components such as engine brackets, pipes, electronic equipment, etc., nor does it consider external aerodynamic optimization structures such as spoilers, fairings, etc. The purpose of this is to focus on the airflow distribution and temperature field inside the nacelle without being distracted by minor details.

[0037] Although simplified, this model contains the core elements of the nacelle design: basic geometry, intake and exhaust layout, and major thermal management areas. It provides a good starting point for subsequent detailed analysis and optimization.

[0038] With this simplified model, a preliminary computational fluid dynamics (CFD) analysis can be quickly performed to evaluate the airflow distribution and temperature field inside the nacelle. These preliminary results can help designers identify possible problem areas, such as airflow dead zones or heat accumulation areas, thus providing guidance for subsequent detailed design.

[0039] Based on the above embodiment, as an optional implementation, in S102, according to the temperature distribution of the surface of the turboprop engine at different stages and the ventilation requirements of the nacelle intake and exhaust, generating the first nacelle model specifically includes S201-S204: S201. Determine the basic dimensions of the nacelle according to the temperature distribution of the surface of the turboprop engine at different stages and the technical parameters of the turboprop engine.

[0040] S202 determines the position and size of the nacelle air inlet and exhaust port according to the ventilation volume requirement and flow rate requirement of the nacelle air intake and exhaust.

[0041] S203 generates a three-dimensional digital model of the first nacelle model by combining the basic dimensions of the nacelle and the positions and dimensions of the nacelle air inlet and exhaust port.

[0042] S204: Import the three-dimensional digital model of the first nacelle model into a preset software for meshing and solution domain definition to generate the first nacelle model.

[0043] In one example, it is necessary to analyze the surface temperature data of the engine during different flight phases such as takeoff, climb, and cruise, while considering the engine's length, diameter, weight and other technical parameters. With these data, the basic dimensions of the nacelle, such as length, diameter and wall thickness, can be preliminarily determined. This process may require preliminary simulation using thermal analysis software to ensure that the nacelle size can provide sufficient heat dissipation space and structural strength.

[0044] Next, the location and size of the nacelle inlet and outlet are determined based on the ventilation volume and flow rate requirements of the nacelle intake and exhaust. In specific implementation, it is necessary to calculate the amount of cooling air required by the engine under different operating conditions, consider the pressure recovery coefficient of the inlet and the back pressure of the exhaust, and also take into account the overall aerodynamic performance of the aircraft. Through fluid dynamics calculations and preliminary CFD analysis, the optimal location and size of the inlet and outlet can be determined to ensure sufficient cooling effect and minimal increase in drag.

[0045] After determining the basic dimensions and the layout of the intake and exhaust systems, the next step is to generate a three-dimensional digital model of the first nacelle model. This step is usually completed using advanced three-dimensional modeling software (such as CATIA, SolidWorks, etc.). During the modeling process, attention should be paid to the continuity and smoothness of the surface to reduce possible airflow separation and turbulence. At the same time, possible future modifications and optimization needs need to be considered, so the model should have good parametric characteristics. This three-dimensional model includes not only the external contour, but also the main internal structure, such as the support frame, insulation layer, etc.

[0046] Finally, the three-dimensional digital model of the first nacelle model is imported into the preset software for meshing and solution domain definition to generate the final first nacelle model. This step is usually completed using professional CFD preprocessing software (such as ANSYSMeshing, ICEM CFD, etc.). Meshing is a key process that directly affects the accuracy and computational efficiency of subsequent CFD analysis. Finer meshes are required in key areas such as the nacelle surface, inlet and outlet, while relatively coarse meshes can be used in the far field area. At the same time, it is necessary to define an appropriate solution domain, including the internal space of the nacelle and a certain range of external space, to facilitate subsequent flow field and temperature field analysis.

[0047] S103, extracting the fluid calculation domain of the first nacelle model, performing temperature field and airflow field analysis on the fluid calculation domain, and obtaining a temperature distribution cloud map and an airflow vector distribution map of the first nacelle model.

[0048] In one example, the fluid computational domain needs to be extracted from the first nacelle model. This process actually converts the space inside and around the nacelle into a computational mesh that can be used for CFD analysis. Using professional CFD preprocessing software (such as ANSYS Meshing, ICEM CFD, etc.), the first nacelle model is imported and the boundaries of the computational domain are defined. The computational domain usually includes the internal space of the nacelle, the air inlet, the exhaust port, and a certain range of space outside the nacelle to capture the airflow characteristics in and out of the nacelle.

[0049] After defining the computational domain, meshing is required. The quality of the mesh directly affects the accuracy of the computational results, so special attention should be paid. In key areas such as the interior of the nacelle and the inlet and outlet, a finer mesh should be used to capture complex flow and heat transfer phenomena. In the external area away from the nacelle, a relatively coarse mesh can be used to save computational resources.

[0050] Next, use CFD software (such as ANSYS Fluent, STAR-CCM+, etc.) to set boundary conditions and initial conditions. These conditions include: 1. The air flow velocity, temperature and pressure at the air inlet are derived from the engine parameters and usage requirements in S101.

[0051] 2. Pressure conditions at the exhaust port.

[0052] 3. Temperature distribution on the engine surface, which is based on the data obtained in S101.

[0053] 4. Parameters of the external environment such as temperature and pressure.

[0054] 5. After setting all necessary parameters, start the CFD solver for calculation. The calculation process may require multiple iterations to converge to a stable solution. During the calculation process, pay close attention to the residual curve to ensure the reliability of the calculation results.

[0055] After the calculation is completed, the post-processing stage begins. Use visualization tools (such as ANSYS CFD-Post, ParaView, etc.) to process the calculation results and generate temperature distribution cloud maps and airflow vector distribution maps. The temperature distribution cloud map intuitively displays the temperature conditions of various parts of the nacelle through different colors, while the airflow vector distribution map clearly shows the direction and speed of the airflow.

[0056] Based on the above embodiment, as an optional implementation, in S103, extracting the fluid calculation domain of the first nacelle model, performing temperature field and airflow field analysis on the fluid calculation domain, and obtaining the temperature distribution cloud map and airflow vector distribution map of the first nacelle model specifically include S301-S302: S301, meshing the fluid calculation domain and setting boundary conditions according to the boundary conditions of the turboprop engine under different operating conditions.

[0057] S302, based on the grid division and boundary condition setting, iterative calculation is performed on the fluid calculation domain to obtain a temperature distribution cloud map and an airflow vector distribution map of the first nacelle model.

[0058] In one example, the fluid computational domain is meshed and boundary conditions are set according to the boundary conditions of the turboprop engine under different working conditions. In specific implementation, it is necessary to consider the characteristics of the engine under different working conditions such as ground idling, take-off, and cruising. These characteristics include engine surface temperature distribution, exhaust temperature and velocity, intake conditions, etc. Meshing usually uses professional CFD preprocessing software such as ANSYS Meshing or ICEM CFD. In key areas such as the nacelle surface, inlet and outlet, finer meshes are required to capture complex flow and heat transfer phenomena. In the far field area, relatively coarse meshes can be used to save computing resources. The boundary conditions include velocity, temperature, and pressure conditions at the inlet and outlet, thermal flow conditions on the nacelle wall, and environmental conditions in the far field. These boundary conditions should be set based on the technical parameters of the engine and the expected working environment.

[0059] Next, based on the meshing and boundary condition settings completed by S301, the fluid calculation domain is iteratively calculated to obtain the temperature distribution cloud map and airflow vector distribution map of the first nacelle model. This step is usually completed using a professional CFD solver such as ANSYS Fluent or OpenFOAM. During the calculation process, it is necessary to select an appropriate turbulence model (such as the k-ε model or the SST k-ω model) and a solution algorithm to accurately simulate complex flow and heat transfer phenomena. Iterative calculations usually require setting appropriate convergence criteria, including residual levels, changes in physical quantities at monitoring points, etc. After the calculation is completed, a detailed temperature distribution cloud map and airflow vector distribution map can be obtained.

[0060] After obtaining the temperature distribution cloud map and airflow vector distribution map of the first nacelle model, the following steps are also included: If the temperature distribution cloud map and / or the airflow vector distribution map do not meet the preset requirements, the nacelle intake and exhaust layout is adjusted, and the first nacelle model is regenerated until the temperature distribution cloud map and the airflow vector distribution map of the regenerated first nacelle model meet the preset requirements.

[0061] In one example, clear preset requirements need to be set first, including the maximum allowable temperature, temperature limits around key components, airflow velocity range, pressure distribution, etc. These preset requirements should be formulated based on the engine's technical specifications, safety standards, and performance goals. Subsequently, the temperature distribution cloud map and airflow vector distribution map of the first nacelle model are carefully analyzed, focusing on temperature distribution, airflow distribution, pressure distribution, and hot spots. If the analysis results do not meet the preset requirements, the nacelle intake and exhaust layout needs to be adjusted. This may include modifying the location, size, or shape of the air inlet, adjusting the design of the exhaust system, redesigning the internal guide structure, adding additional cooling channels or heat dissipation structures in key areas, and optimizing the nacelle shape.

[0062] After each adjustment, the first nacelle model needs to be regenerated, the 3D digital model needs to be updated, the meshing and solution domain needs to be redefined, and then the CFD analysis needs to be performed again to obtain a new temperature distribution cloud map and airflow vector distribution map. This process needs to be repeated until the temperature distribution cloud map and airflow vector distribution map of the regenerated first nacelle model meet the preset requirements.

[0063] S104: If the temperature distribution cloud map and the airflow vector distribution map both meet preset requirements, the aerodynamic shape details and internal solid components of the first nacelle model are added to generate a second nacelle model.

[0064] In one example, the temperature distribution cloud map and airflow vector distribution map obtained in S103 need to be carefully evaluated first to ensure that they meet the pre-set performance requirements. These requirements may include that the maximum temperature does not exceed a certain threshold, the airflow distribution uniformity reaches a certain level, and the cooling effect of key parts meets the standards. Only when these basic performance indicators are met can the next step of detailed design be carried out.

[0065] After meeting the preset requirements, start adding aerodynamic shape details and internal solid components to the first nacelle model. This process is usually carried out using advanced 3D modeling software (such as CATIA, NX, etc.). Specifically, the following aspects need to be considered: Aerodynamic shape details: According to the overall aerodynamic design requirements of the aircraft, various aerodynamic optimization structures are added to the outer surface of the nacelle, such as fairings, spoilers, etc. These structures can improve the aerodynamic integration of the nacelle and the fuselage, reduce resistance, and improve flight efficiency.

[0066] Internal solid components: add engine brackets, various piping systems (such as fuel, lubricating oil, electrical, etc.), firewalls, maintenance channels and other internal structures necessary in actual engineering. The layout of these components needs to consider the temperature distribution and airflow field characteristics analyzed in S103 to ensure that they do not significantly affect the heat dissipation and ventilation performance of the nacelle.

[0067] Intake and exhaust system details: Based on the analysis results of S103, the shape and structure of the intake and exhaust ports are refined, which may include adding guide vanes, regulating valves, etc. to further optimize the airflow organization.

[0068] Material properties: Assign appropriate material properties to each component in the model, including density, thermal conductivity, specific heat capacity, etc. These properties are crucial for subsequent thermal and structural analysis.

[0069] Connection details: Design the connection methods between components, such as bolt connections, welding, etc., to ensure the integrity and assemblability of the model.

[0070] In the process of adding these details, it is necessary to always keep an eye on the overall performance and ensure that the new structures and components do not significantly affect the good performance that has been proven in S103. It may be necessary to make multiple local adjustments and optimizations to find a balance between functionality and engineering feasibility.

[0071] S105, performing fluid-solid coupling conjugate heat transfer analysis on the second nacelle model under different working conditions, optimizing the layout of the nacelle intake and exhaust according to the results of the conjugate heat transfer analysis, and generating a target nacelle ventilation and heat dissipation scheme.

[0072] In one example, you first need to select appropriate multi-physics coupling analysis software, such as ANSYS Workbench, COMSOL Multiphysics, etc. These software can handle fluid dynamics and heat conduction problems at the same time, and realize conjugate heat transfer analysis of fluid-solid coupling.

[0073] The specific analysis process is as follows: First, based on the second nacelle model generated in S104, a complete calculation model including a fluid domain and a solid domain is established. The fluid domain includes the air space inside and around the nacelle, and the solid domain includes all solid components such as the nacelle structure and the engine casing.

[0074] Next, define different operating conditions. These operating conditions should cover the main operating states of the turboprop engine, such as ground idle, takeoff, cruise, climb, etc. Each operating condition has its own specific parameters such as engine power output, ambient temperature, flight speed, etc.

[0075] Then, set the corresponding boundary conditions and initial conditions for each operating condition. This includes the air velocity and temperature at the air inlet, the heat flux density on the engine surface, the ambient temperature and pressure, etc. At the same time, it is also necessary to define material properties such as thermal conductivity, specific heat capacity, density, etc. These data should be based on the actual selected materials.

[0076] After setting all parameters, start the solver for calculation. Conjugate heat transfer analysis will simultaneously solve the Navier-Stokes equations and energy equations in the fluid domain, as well as the heat conduction equations in the solid domain, and achieve continuous heat transfer at the fluid-solid interface. This method can accurately simulate the cooling effect of the fluid on the solid, and the heating effect of the solid on the fluid.

[0077] After the calculation is completed, enter the post-processing stage. The analysis results should include detailed temperature distribution, heat flow distribution, air flow velocity field, etc. Pay special attention to the following aspects: The temperature distribution inside the nacelle, especially the location and temperature value of the high temperature area.

[0078] Temperature conditions around critical components such as engine interfaces, electronic equipment, etc.

[0079] Temperature distribution on the nacelle surface to assess whether there is a risk of overheating.

[0080] The efficiency of the intake and exhaust system, including the ability to organize airflow and remove heat.

[0081] Based on these analysis results, the nacelle intake and exhaust layout is optimized. This may include: Adjust the location, size, or shape of air intakes to improve cooling air distribution.

[0082] Optimize the design of the exhaust system to ensure that heat can be discharged effectively.

[0083] Add additional cooling channels or flow guide structures in critical hot spots.

[0084] Redesigned internal insulation for improved heat management.

[0085] After multiple iterations and optimizations, the target nacelle ventilation and cooling solution is finally generated, which should be able to maintain good thermal management performance under all considered working conditions.

[0086] Based on the above embodiment, as an optional implementation, in S105, according to the result of conjugate heat transfer analysis, the layout of the nacelle intake and exhaust is optimized, and the target nacelle ventilation and heat dissipation scheme is generated, which specifically includes S501-S505: S501, extracting a temperature distribution cloud map and an airflow vector distribution map of the second nacelle model from the results of the conjugate heat transfer analysis, and judging whether there is an airflow stagnation area and a high temperature concentration area in the second nacelle model according to the temperature distribution cloud map and the airflow vector distribution map of the second nacelle model.

[0087] S502, if there is an airflow stagnation area and / or a high temperature concentration area, the second nacelle model is optimized, wherein if there is an airflow stagnation area, a ventilation airflow guide structure is added to the airflow stagnation area, and if there is a high temperature concentration area, a heat dissipation vent is added to the high temperature concentration area.

[0088] S503, based on the optimization of the second nacelle model, the geometric parameters of the nacelle intake and exhaust layout are optimized.

[0089] S504, applying the optimized nacelle intake and exhaust layout to the second nacelle model, and re-performing the fluid-solid coupling conjugate heat transfer analysis until the analysis results meet the preset ventilation and heat dissipation performance indicators.

[0090] S505, generating a target nacelle ventilation and heat dissipation scheme according to a nacelle intake and exhaust layout that meets preset ventilation and heat dissipation performance indicators.

[0091] In one example, the temperature distribution cloud map and airflow vector distribution map of the second nacelle model are extracted from the results of the conjugate heat transfer analysis. These diagrams provide detailed information on the heat distribution and airflow movement inside the nacelle, which is an important basis for judging the rationality of the design. By carefully analyzing these diagrams, designers can identify whether there are airflow stagnation areas and high temperature concentration areas. The existence of these areas may cause local overheating, degradation of material performance, and even affect the normal operation of the engine, so they must be dealt with in a timely manner.

[0092] If airflow stagnation areas or high-temperature concentrated areas are found, the second nacelle model needs to be optimized in a targeted manner. For airflow stagnation areas, adding ventilation airflow guide structures is an effective solution. This structure can guide fresh air into the stagnation area, promote air circulation, and thus improve local heat loss. For high-temperature concentrated areas, adding heat dissipation vents can directly improve the heat dissipation efficiency of the area. The specific implementation of these optimization measures needs to take into account the overall structure and space limitations of the nacelle to ensure that there is no negative impact on other functions.

[0093] After completing these local optimizations, the next step is to fully optimize the geometric parameters of the nacelle intake and exhaust layout. This includes adjusting the position, size, and shape of the intake and exhaust ports, as well as the design of the internal flow guide structure, so that the air flow distribution is more uniform and the heat dissipation is more efficient. The optimization of geometric parameters usually requires the combination of computational fluid dynamics (CFD) software and parametric design tools to find the best design solution through multiple iterations.

[0094] The optimized nacelle intake and exhaust layout needs to be applied to the second nacelle model again, and a new round of fluid-solid coupling conjugate heat transfer analysis needs to be performed to ensure that the new design has indeed improved the ventilation and heat dissipation performance. If the analysis results still do not meet the preset ventilation and heat dissipation performance indicators, it is necessary to continue to optimize and analyze until the requirements are met. This iterative process may need to be repeated multiple times, and each time targeted adjustments will be made based on the results of the previous round of analysis.

[0095] Finally, when the analysis results meet the preset ventilation and heat dissipation performance indicators, the target nacelle ventilation and heat dissipation scheme can be generated based on the optimized nacelle intake and exhaust layout. This scheme not only includes the final geometric design, but also a detailed performance analysis report to provide guidance for subsequent manufacturing and testing.

[0096] After generating the target nacelle ventilation and cooling plan, it also includes: A thermal analysis test is conducted on a scaled sample under wind tunnel test conditions to obtain a test temperature cloud map of the scaled sample, wherein the scaled sample is a scaled sample for thermal analysis of a nacelle made according to a ventilation and heat dissipation scheme for the target nacelle; a temperature deviation between the test temperature cloud map of the scaled sample and a temperature distribution cloud map of a second nacelle model under the same working condition is calculated; if the temperature deviation is less than a preset temperature deviation threshold, the ventilation and heat dissipation scheme for the target nacelle is sent to a terminal device of an operator, so that the operator can make a nacelle thermal analysis prototype according to the ventilation and heat dissipation scheme for the target nacelle.

[0097] In one example, a scaled-down sample for thermal analysis of the nacelle is made according to the ventilation and heat dissipation scheme of the target nacelle. The use of a scaled-down sample instead of a full-size model is based on cost control and test convenience. The scaled-down sample needs to be similar to the actual nacelle in terms of geometry, material properties and key details to ensure the representativeness of the test results. A thermal analysis test is conducted on this scaled-down sample under wind tunnel test conditions to simulate the temperature distribution in the actual working environment. This process usually involves the use of equipment such as infrared thermal imagers or thermocouples to obtain temperature data on the surface and key internal locations of the scaled-down sample, and finally generate a test temperature cloud map.

[0098] Next, the test temperature cloud map of the scaled sample is compared with the temperature distribution cloud map of the second nacelle model under the same working conditions. By calculating the temperature deviation between the two, the accuracy of the simulation model can be quantitatively evaluated. The calculation of temperature deviation may involve point-to-point comparison or comparison of average temperature in key areas. The specific method should be determined according to actual needs and data characteristics.

[0099] The purpose of setting a preset temperature deviation threshold is to establish an objective standard for judging whether the simulation results are acceptable. The determination of this threshold should take into account factors such as measurement error, scaling effect, and the tolerance range of actual engineering applications. If the calculated temperature deviation is less than the preset temperature deviation threshold, it can be considered that the simulation results are in good consistency with the actual situation, and the target nacelle ventilation and heat dissipation scheme is reliable.

[0100] After verification, the target nacelle ventilation and cooling scheme is sent to the operator's terminal device so that they can make a nacelle thermal analysis prototype based on this scheme. This step marks the transition of the design from a virtual environment to actual production. The operators may include engineers, technicians, and production personnel, who will make a full-scale prototype based on the received scheme.

[0101] The method also includes: conducting a flight test on a nacelle thermal analysis prototype under actual flight conditions to obtain measured temperature distribution data of the nacelle thermal analysis prototype under various flight conditions; verifying and adjusting a target nacelle ventilation and heat dissipation scheme based on the measured temperature distribution data of the nacelle thermal analysis prototype under various flight conditions to generate a final nacelle ventilation and heat dissipation design scheme.

[0102] In one example, a nacelle thermal analysis prototype is flight tested under real flight conditions. Real flight conditions include low temperatures at high altitudes, high-speed airflow, changes in engine operating conditions, etc. Flight tests usually involve multiple flight phases, such as takeoff, climb, cruise, descent, and landing, as well as different flight speeds and altitudes. In each flight state, temperature distribution data of the nacelle thermal analysis prototype needs to be collected. This is usually achieved by installing temperature sensors at key locations in the nacelle, which can record and transmit temperature data in real time. At the same time, auxiliary measurements such as infrared thermal imagers may be used to obtain more comprehensive temperature distribution information.

[0103] After obtaining the measured temperature distribution data of the nacelle thermal analysis prototype under various flight conditions, the next step is to verify and adjust the ventilation and cooling scheme of the target nacelle. This process involves comparing and analyzing the measured data with previous simulation results and wind tunnel test data. Through this comparison, the performance of the ventilation and cooling scheme of the target nacelle in actual flight can be evaluated and possible problems or deficiencies can be identified. For example, it may be found that the temperature of certain areas in specific flight conditions is higher than expected, or that the effect of certain ventilation structures in actual flight is not as ideal as predicted by simulation.

[0104] Based on these analysis results, the engineering team needs to make necessary adjustments and optimizations to the ventilation and heat dissipation scheme of the target nacelle. This may include modifying the heat dissipation structure in certain areas, adjusting the location or size of the vents, improving the internal flow design, etc. Each adjustment should be based on measured data and engineering analysis, with the goal of solving the problems found and further improving the overall performance of the nacelle.

[0105] After these checks and adjustments, the final nacelle ventilation and heat dissipation design will be generated. This plan not only includes the final geometric design and structural details, but also should include a complete performance data report, temperature distribution predictions under various flight conditions, and maintenance and operation recommendations. This final plan represents a fully verified and optimized nacelle design, laying a solid foundation for subsequent mass production and practical application.

[0106] Based on the above method, the present application also discloses a device for detecting the global temperature distribution of a nacelle equipped with a turboprop engine, such as Figure 2 As shown, Figure 21 is a schematic diagram of the structure of a device for detecting the global temperature distribution of a nacelle equipped with a turboprop engine provided in an embodiment of the present application, the device comprising: a determination module, a first generation module, an analysis module, an adjustment module and a second generation module; wherein the determination module is used to determine the temperature distribution of the surface of the turboprop engine at different stages and the ventilation requirements of the nacelle intake and exhaust according to the technical parameters and use requirements of the turboprop engine; the first generation module is used to generate a first nacelle model according to the temperature distribution of the surface of the turboprop engine at different stages and the ventilation requirements of the nacelle intake and exhaust, the first nacelle model being a model that ignores the details of the aerodynamic shape and the internal solid components A nacelle model; an analysis module, used to extract the fluid calculation domain of the first nacelle model, perform temperature field and airflow field analysis on the fluid calculation domain, and obtain a temperature distribution cloud map and an airflow vector distribution map of the first nacelle model; an adjustment module, used to add aerodynamic shape details and internal solid components of the first nacelle model to generate a second nacelle model if both the temperature distribution cloud map and the airflow vector distribution map meet preset requirements; a second generation module, used to perform fluid-solid coupled conjugate heat transfer analysis on the second nacelle model under different working conditions, optimize the layout of the nacelle intake and exhaust according to the results of the conjugate heat transfer analysis, and generate a target nacelle ventilation and heat dissipation plan.

[0107] It should be noted that: when the device provided in the above embodiment realizes its function, only the division of the above functional modules is used as an example. In actual application, the above functions can be assigned to different functional modules as needed, that is, the internal structure of the device is divided into different functional modules to complete all or part of the functions described above. In addition, the device and method embodiments provided in the above embodiment belong to the same concept, and the specific implementation process is detailed in the method embodiment, which will not be repeated here.

[0108] See also Figure 3 , is a schematic diagram of the structure of an electronic device provided in an embodiment of the present application. Figure 3 As shown, the electronic device 1000 may include: at least one processor 1001 , at least one network interface 1004 , a user interface 1003 , a memory 1005 , and at least one communication bus 1002 .

[0109] The communication bus 1002 is used to realize the connection and communication between these components.

[0110] The user interface 1003 may include a display screen (Display) and a camera (Camera). Optionally, the user interface 1003 may also include a standard wired interface and a wireless interface.

[0111] The network interface 1004 may optionally include a standard wired interface or a wireless interface (such as a WI-FI interface).

[0112] Among them, the processor 1001 may include one or more processing cores. The processor 1001 uses various interfaces and lines to connect various parts in the entire server, and executes various functions of the server and processes data by running or executing instructions, programs, code sets or instruction sets stored in the memory 1005, and calling data stored in the memory 1005. Optionally, the processor 1001 can be implemented in at least one hardware form of digital signal processing (Digital Signal Processing, DSP), field programmable gate array (Field-Programmable Gate Array, FPGA), and programmable logic array (Programmable Logic Array, PLA). The processor 1001 can integrate one or a combination of a central processing unit (Central Processing Unit, CPU), a graphics processing unit (Graphics Processing Unit, GPU) and a modem. Among them, the CPU mainly processes the operating system, user interface and application programs; the GPU is responsible for rendering and drawing the content to be displayed on the display screen; the modem is used to process wireless communications. It can be understood that the above-mentioned modem may not be integrated into the processor 1001, and it can be implemented separately through a chip.

[0113] Among them, the memory 1005 may include a random access memory (Random Access Memory, RAM) and may also include a read-only memory (Read-Only Memory). Optionally, the memory 1005 includes a non-transitory computer-readable storage medium. The memory 1005 can be used to store instructions, programs, codes, code sets or instruction sets. The memory 1005 may include a program storage area and a data storage area, wherein the program storage area may store instructions for implementing an operating system, instructions for at least one function (such as a touch function, a sound playback function, an image playback function, etc.), instructions for implementing the above-mentioned various method embodiments, etc.; the data storage area may store data involved in the above-mentioned various method embodiments, etc. The memory 1005 may optionally also be at least one storage device located away from the aforementioned processor 1001. As Figure 3 As shown, the memory 1005 as a computer storage medium may include an operating system, a network communication module, a user interface module, and an application program for a method for detecting the global temperature distribution of a nacelle equipped with a turboprop engine.

[0114] exist Figure 3In the electronic device 1000 shown, the user interface 1003 is mainly used to provide an input interface for the user and obtain data input by the user; and the processor 1001 can be used to call an application program stored in the memory 1005 for a method for detecting the global temperature distribution of a nacelle equipped with a turboprop engine. When executed by one or more processors, the electronic device executes one or more of the methods described in the above embodiments.

[0115] An electronic device readable storage medium stores instructions, which, when executed by one or more processors, enable the electronic device to execute one or more of the methods described in the above embodiments.

[0116] It should be noted that, for the aforementioned method embodiments, for the sake of simplicity, they are all described as a series of action combinations, but those skilled in the art should be aware that the present application is not limited by the order of the actions described, because according to the present application, certain steps can be performed in other orders or simultaneously. Secondly, those skilled in the art should also be aware that the embodiments described in the specification are all preferred embodiments, and the actions and modules involved are not necessarily required for the present application.

[0117] In the above embodiments, the description of each embodiment has its own emphasis. For parts that are not described in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0118] In the several embodiments provided in the present application, it should be understood that the disclosed devices can be implemented in other ways. For example, the device embodiments described above are only schematic, such as the division of the units, which is only a logical function division. There may be other division methods in actual implementation, such as multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some service interfaces, and the indirect coupling or communication connection of devices or units can be electrical or other forms.

[0119] The units described as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[0120] In addition, each functional unit in each embodiment of the present application may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit. The above-mentioned integrated unit may be implemented in the form of hardware or in the form of software functional units.

[0121] If the integrated unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable memory. Based on this understanding, the technical solution of the present application, or the part that contributes to the prior art, or all or part of the technical solution can be embodied in the form of a software product, which is stored in a memory and includes several instructions for a computer device (which can be a personal computer, server or network device, etc.) to execute all or part of the steps of the method described in each embodiment of the present application. The aforementioned memory includes: various media that can store program codes, such as USB flash drives, mobile hard drives, magnetic disks or optical disks.

[0122] The above is only an exemplary embodiment of the present disclosure, and the scope of the present disclosure cannot be limited thereto. That is, any equivalent changes and modifications made according to the teachings of the present disclosure are still within the scope of the present disclosure. After considering the specification and practicing the disclosure here, those skilled in the art will easily think of other embodiments of the present disclosure. This application is intended to cover any modification, use or adaptation of the present disclosure, which follows the general principles of the present disclosure and includes common knowledge or customary technical means in the technical field not recorded in the present disclosure. The description and examples are only regarded as exemplary, and the scope and spirit of the present disclosure are defined by the claims.

Claims

1. A method for detecting the global temperature distribution of a nacelle equipped with a turboprop engine, characterized in that: The method comprises: Determine the temperature distribution of the surface of the turboprop engine at different stages and the ventilation requirements of the nacelle intake and exhaust according to the technical parameters and use requirements of the turboprop engine; generating a first nacelle model according to the temperature distribution of the surface of the turboprop engine at different stages and the ventilation requirements of the nacelle intake and exhaust, wherein the first nacelle model is a nacelle model ignoring aerodynamic shape details and internal solid components; Extracting a fluid calculation domain of the first nacelle model, performing temperature field and airflow field analysis on the fluid calculation domain, and obtaining a temperature distribution cloud map and an airflow vector distribution map of the first nacelle model; If both the temperature distribution cloud map and the airflow vector distribution map meet preset requirements, adding the aerodynamic shape details and internal solid components of the first nacelle model to generate a second nacelle model; The second nacelle model is subjected to fluid-solid coupling conjugate heat transfer analysis under different working conditions. According to the result of the conjugate heat transfer analysis, the layout of the nacelle intake and exhaust is optimized to generate a target nacelle ventilation and heat dissipation scheme.

2. The method for detecting the global temperature distribution of a nacelle equipped with a turboprop engine according to claim 1, characterized in that: The step of generating a first nacelle model according to the temperature distribution of the surface of the turboprop engine at different stages and the ventilation requirements of the nacelle intake and exhaust, comprises: Determining basic dimensions of the nacelle according to temperature distribution of the surface of the turboprop engine at different stages and technical parameters of the turboprop engine; Determine the position and size of the nacelle air inlet and exhaust port according to the ventilation volume requirement and flow rate requirement of the nacelle air intake and exhaust; Generate a three-dimensional digital model of the first nacelle model in combination with the basic dimensions of the nacelle, the positions and dimensions of the air inlet and the air outlet of the nacelle; The three-dimensional digital model of the first nacelle model is imported into a preset software for meshing and solution domain definition to generate a first nacelle model.

3. The method for detecting the global temperature distribution of a nacelle equipped with a turboprop engine according to claim 1, characterized in that: The extracting of the fluid calculation domain of the first nacelle model, performing temperature field and airflow field analysis on the fluid calculation domain, and obtaining a temperature distribution cloud map and an airflow vector distribution map of the first nacelle model include: According to the boundary conditions of the turboprop engine under different working conditions, meshing the fluid calculation domain and setting boundary conditions; On the basis of the grid division and the boundary condition setting, the fluid calculation domain is iteratively calculated to obtain a temperature distribution cloud map and an airflow vector distribution map of the first nacelle model.

4. The method for detecting the global temperature distribution of a nacelle equipped with a turboprop engine according to claim 1, characterized in that: After obtaining the temperature distribution cloud map and the airflow vector distribution map of the first nacelle model, the method further includes: If the temperature distribution cloud map and / or the airflow vector distribution map do not meet the preset requirements, the nacelle intake and exhaust layout is adjusted, and the first nacelle model is regenerated until the temperature distribution cloud map and the airflow vector distribution map of the regenerated first nacelle model both meet the preset requirements.

5. The method for detecting the global temperature distribution of a nacelle equipped with a turboprop engine according to claim 1, characterized in that: The method of optimizing the layout of the nacelle intake and exhaust according to the result of the conjugate heat transfer analysis to generate a target nacelle ventilation and heat dissipation scheme includes: extracting a temperature distribution cloud map and an airflow vector distribution map of the second nacelle model from the result of the conjugate heat transfer analysis, and judging whether the second nacelle model has an airflow stagnation area and a high temperature concentration area according to the temperature distribution cloud map and the airflow vector distribution map of the second nacelle model; If the airflow stagnation area and / or the high temperature concentration area exist, the second nacelle model is optimized, wherein if the airflow stagnation area exists, a ventilation airflow guide structure is added to the airflow stagnation area, and if the high temperature concentration area exists, a heat dissipation vent is added to the high temperature concentration area; On the basis of optimizing the second nacelle model, optimizing the geometric parameters of the nacelle intake and exhaust layout; Applying the optimized nacelle intake and exhaust layout to the second nacelle model, and re-performing the fluid-solid coupling conjugate heat transfer analysis until the analysis results meet the preset ventilation and heat dissipation performance indicators; The target nacelle ventilation and heat dissipation scheme is generated based on the nacelle intake and exhaust layout that meets the preset ventilation and heat dissipation performance indicators.

6. The method for detecting the global temperature distribution of a nacelle equipped with a turboprop engine according to claim 1, characterized in that: After generating the target nacelle ventilation and heat dissipation scheme, the method further includes: Conducting a thermal analysis test on a scaled sample under wind tunnel test conditions to obtain a test temperature cloud diagram of the scaled sample, wherein the scaled sample is a nacelle thermal analysis scaled sample manufactured according to the target nacelle ventilation and heat dissipation scheme; Calculating the temperature deviation between the test temperature cloud map of the scaled sample and the temperature distribution cloud map of the second nacelle model under the same working condition; If the temperature deviation is less than a preset temperature deviation threshold, the target nacelle ventilation and heat dissipation scheme is sent to a terminal device of an operator, so that the operator can make a nacelle thermal analysis prototype according to the target nacelle ventilation and heat dissipation scheme.

7. The method for detecting the global temperature distribution of a nacelle equipped with a turboprop engine according to claim 6, characterized in that: The method further comprises: Under real flight conditions, a flight test is conducted on the nacelle thermal analysis prototype to obtain measured temperature distribution data of the nacelle thermal analysis prototype under various flight conditions; According to the measured temperature distribution data of the nacelle thermal analysis prototype under various flight conditions, the ventilation and heat dissipation scheme of the target nacelle is checked and adjusted to generate a final ventilation and heat dissipation design scheme of the nacelle.

8. A device for detecting the global temperature distribution of a nacelle equipped with a turboprop engine, characterized in that: The device comprises: a determination module, a first generation module, an analysis module, an adjustment module and a second generation module; wherein, The determination module is used to determine the temperature distribution of the surface of the turboprop engine at different stages and the ventilation requirements of the nacelle intake and exhaust according to the technical parameters and use requirements of the turboprop engine; The first generating module is used to generate a first nacelle model according to the temperature distribution of the surface of the turboprop engine at different stages and the ventilation requirements of the nacelle intake and exhaust, wherein the first nacelle model is a nacelle model that ignores aerodynamic shape details and internal solid components; The analysis module is used to extract the fluid calculation domain of the first nacelle model, perform temperature field and airflow field analysis on the fluid calculation domain, and obtain a temperature distribution cloud map and an airflow vector distribution map of the first nacelle model; The adjustment module is used for adding the aerodynamic shape details and internal solid components of the first nacelle model to generate a second nacelle model if both the temperature distribution cloud map and the airflow vector distribution map meet preset requirements; The second generation module is used to perform fluid-solid coupling conjugate heat transfer analysis on the second nacelle model under different working conditions, optimize the layout of the nacelle intake and exhaust according to the result of the conjugate heat transfer analysis, and generate a target nacelle ventilation and heat dissipation plan.

9. An electronic device, characterized in that: It includes a processor, a memory, a user interface and a network interface, the memory is used to store instructions, the user interface and the network interface are used to communicate with other devices, and the processor is used to execute the instructions stored in the memory so that the electronic device executes the method as described in any one of claims 1-7.

10. A computer-readable storage medium, characterized in that: A computer program is stored which can be loaded by a processor and execute the method according to any one of claims 1 to 7.

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