CN115688285A - Method for optimizing fuel supply and combustion system of sustainable aviation fuel turbofan engine - Google Patents
Method for optimizing fuel supply and combustion system of sustainable aviation fuel turbofan engine Download PDFInfo
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- CN115688285A CN115688285A CN202211413998.9A CN202211413998A CN115688285A CN 115688285 A CN115688285 A CN 115688285A CN 202211413998 A CN202211413998 A CN 202211413998A CN 115688285 A CN115688285 A CN 115688285A
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Abstract
The invention discloses a method for optimizing a fuel supply and combustion system of a sustainable aviation fuel turbofan engine. The optimization method is based on a digital twin structure system, adopts various digital twin technologies between a virtual model system and a physical entity, and comprises the following steps: establishing a physical entity of the turbofan engine and a virtual model system of the turbofan engine, operating the virtual model system, and performing iterative calculation improvement on oil supply and combustion system structural parameters in the virtual model system to obtain optimal structural parameters; verifying by using a physical model according to the optimal structural parameters to determine the structural parameters of the final oil supply and combustion system; determining data of an oil supply and combustion system in a virtual model system; carrying out actual processing, manufacturing and assembling on the oil supply and combustion system, and optimizing the improved virtual model system by using actual data of the oil supply and combustion system; and perfecting the optimized virtual model system. The invention reduces the optimization time and cost, and has high optimization improvement efficiency and good accuracy.
Description
Technical Field
The invention relates to the technical field of sustainable aviation fuel turbofan engines, in particular to a method for optimizing a fuel supply and combustion system of a sustainable aviation fuel turbofan engine.
Background
The aircraft engine is a typical complex product with complex characteristics in the aspects of structural composition, key technology, performance requirements, manufacturing process, test maintenance, project management, working environment and the like, the design and the manufacture of the aircraft engine relate to multiple disciplines and a large amount of information, high-precision technology in the industrial design, manufacture and information industry is concentrated, and the research and development period is long. The traditional aeroengine development mode cannot meet the increasing requirements of high quality, high performance and low cost of the engine, and the digital and intelligent development mode driven by new information technology is the development trend in the future. The design structure, the manufacturing process and the performance index of the aviation turbofan engine have high requirements, and the aviation turbofan engine is the mainstream aviation power of civil aviation and military aircraft. The development of virtual design and intelligent manufacturing technology for aviation turbofan engines is of great importance.
According to the calculation of the carbon emission in the whole life cycle, the Sustainable Aviation Fuel (SAF) can effectively reduce the carbon dioxide emission by 80 percent. The SAF of the aviation turbofan engine, which is currently 100 percent combusted, faces some challenges in the fuel supply and combustion system, for example, SAF without aromatic compounds causes contraction of a seal ring of the fuel supply system of the aviation turbofan engine, thereby causing a phenomenon of severe oil leakage, so that the SAF must be mixed with the conventional aviation fuel at the present stage, and the mixing ratio should not be higher than 50%, and the mixing ratio of the SAF is currently generally about 10%, so that in order to increase the mixing ratio of the SAF, the problem of sealing of the fuel supply system against the SAF must be solved. For example, the SAF with different viscosity and density has different atomization quality, the original combustion chamber of the combustion system cannot completely adapt to the SAF, phenomena such as mismatching of atomization performance and unstable combustion may occur, and relevant parameters of the combustion chamber need to be optimized.
However, oil supply and combustion systems have met with new challenges in SAF design flexibility, manufacturing, and performance improvement. On one hand, the improvement of an oil supply and combustion system is very complicated due to the introduction of a plurality of new components, such as an oil supply sealing structure, a rotational flow atomization structure and the like, the design, manufacture and assembly of the components need to simultaneously meet the requirements of light weight and high safety of an aeroengine, the transmission and sealing performance of the assembled system structure is often unsatisfactory, the related manufacture and process procedures need to be reasonably planned urgently, and the iterative improvement of real-time recording and feedback and manufacturing process schemes is carried out, so that the intelligent manufacture is realized as far as possible. On the other hand, a plurality of uncertain system parameters such as the sizes of a new sealing structure, the length of an atomization structure and the like are newly introduced, so that the difficulty of multi-target performance improvement is increased.
At present, multi-target improvement on the system parameters mostly depends on repeated tests, a large amount of time and cost are consumed, and the parameters are only selected at intervals in the tests, so that the number of the selected values is limited, and accurate improved values cannot be obtained; or an engine virtual performance simulation model is established, but due to lack of feedback and correction of real-time test data, the virtual and real data are not subjected to fusion analysis, and the accuracy of the performance model needs to be improved. Therefore, it is very challenging to explore a fast and effective improvement method for the design, manufacture and performance of the oil supply and combustion system of the SAF-oriented turbofan engine.
Disclosure of Invention
The present invention is directed to solving at least one of the problems of the prior art. Therefore, the invention aims to provide an optimization method for the fuel supply and combustion system of the sustainable aviation fuel turbofan engine, so that the optimization improvement time and cost of the fuel supply and combustion system of the sustainable aviation fuel turbofan engine are greatly saved, the optimization improvement efficiency is high, and the accuracy is good.
The method for optimizing the fuel supply and combustion system of the sustainable aviation fuel turbofan engine is based on a digital twin structure system, wherein the digital twin structure system comprises a virtual model system, a physical entity, a service system, twin data and interactive connection;
wherein the physical entities comprise actual entity data and actual entity manufacturing and assembly process data;
the virtual model system is used for virtually simulating the physical entity, a plurality of digital twinning technologies are adopted between the virtual model system and the physical entity, the virtual model system comprises a geometric model, a physical model, a behavior model and a regular model, and the geometric model is used for describing the shape, the size, the machining, the manufacturing and the assembling information of each part in the actual entity; the physical model is used for simulation of physical attributes of the real entity; the behavior model is used for receiving data fed back by the actual entity experiment in practice, responding to external driving and disturbance effects, and processing and adjusting the virtual model system; the rule model is used for modeling and simulating the performance rule or rule of the actual entity;
the service system is used for collecting the information of the virtual model system and the physical entity and carrying out fusion analysis on the information;
the twin data comprises data generated by the physical entity, the virtual model system and the service system, the twin data is processed by the service system and then fed back to the virtual model system, the physical entity and the service system to push the operation of the digital twin structure system, and the twin data can be continuously updated and improved along with the generation of real-time data;
the interconnection comprises a plurality of different data transmission modules for interconnecting the physical entity, the virtual model system, the service system and the twin data so that data of the physical entity, the virtual model system, the service system and the twin data are exchanged among the parts;
the method for optimizing the fuel supply and combustion system of the sustainable aviation fuel turbofan engine comprises the following steps:
s1, establishing a virtual model system: the method comprises the steps of carrying out test measurement on power, oil supply and combustion performance of an entity turbofan engine and the entity turbofan engine to obtain multidimensional data to form a physical entity of the turbofan engine, analyzing the obtained multidimensional data and storing the data to a service system, wherein the entity turbofan engine takes sustainable aviation fuel or aviation fuel containing the sustainable aviation fuel as the fuel, and the entity turbofan engine comprises an oil supply and combustion system; establishing a turbofan engine simulation model and a sustainable aviation fuel combustion simulation model to form the virtual model system, and inputting the acquired multidimensional data into a simulation correction module in the virtual model system by the service system;
s2: virtual performance optimization: operating the virtual model system, performing fusion analysis on the simulation behavior and performance result of the virtual model system and the behavior data and performance data in the acquired multidimensional data, and performing iterative calculation improvement on the structural parameters of the oil supply and combustion system in the virtual model system to obtain optimal structural parameters; according to the optimal structural parameters, structural parameters of an oil supply pipeline and an atomization structure in the oil supply and combustion system are improved in a physical model to form an improved physical model, oil supply flow and atomization characteristics and rotor system dynamic characteristics are verified by using the improved physical model, and the final structural parameters of the oil supply and combustion system in the virtual model system are determined;
s3: virtual manufacturing simulation: determining the shape, size, assembly relation and processing and manufacturing data of parts of an oil supply and combustion system in the improved virtual model system according to the final structural parameters of the oil supply and combustion system in the virtual model system to obtain an improved geometric model, and adding materials and process attributes in the improved virtual model system;
s4: the actual manufacturing process comprises the following steps: according to the information provided by the improved virtual model system, actually processing, manufacturing and assembling parts in the oil supply and combustion system to obtain an improved entity turbofan engine, wherein in the process, the actual shapes, sizes, assembly relations, processing and manufacturing data, materials and process data of the parts in the oil supply and combustion system are fed back to the service system to optimize the improved virtual model system;
s5: and (3) real engine test: testing the performance of the power, oil supply and combustion system of the improved entity turbofan engine, feeding back the collected behavior data, performance data and environmental data to the service system, carrying out fusion analysis on the behavior data, performance data and environmental data and the simulation data generated by the optimized virtual model system, and perfecting the optimized virtual model system.
The method for optimizing the fuel supply and combustion system of the sustainable aviation fuel turbofan engine has the advantages that firstly, the method is established on the basis of a digital twin structure system, a digital twin technology is adopted between a virtual model system and a physical entity, and the accuracy of the virtual model system of the turbofan engine established on the basis of the digital twin structure system and the digital twin technology is higher; secondly, a turbofan engine virtual model system with high accuracy is adopted to simulate a multi-target improvement process of structural parameters of an oil supply and combustion system, so that the method has the advantages of high efficiency, high reliability and high accuracy, can obtain an accurate performance improvement result, saves a large amount of time and processing cost, simulates the processes of processing, manufacturing and assembling, is beneficial to improving process management, improving the processing and assembling efficiency, reducing the rejection rate, and is beneficial to realizing full qualification of parts in small-batch manufacturing; and thirdly, feeding back the actual processing and manufacturing processes of an oil supply and combustion system in the turbofan engine and the test result to the virtual model system to obtain a more perfect virtual model system, recording data of virtual-real interaction fusion analysis, facilitating the inheritance of data information and playing an important role in promoting the development of engine engineering improvement technology.
In some embodiments, digital twinning techniques employed between the virtual model system and the physical entity include structural twinning, material twinning, process twinning, behavioral twinning, performance twinning, and environmental twinning;
wherein the structural twinning is the twinning of the structural, appearance and assembly relationship data of the physical entity and the virtual model system; the material twinning is twinning of physical property and dynamic property data of materials used by the physical entity and each part in the virtual model system; the process twinning is twinning of process data of machining, manufacturing and assembling of the physical entity and the virtual model system; the behavior twins are twins of various response data of the physical entity and the virtual model system to the self state or the external environment; the performance twinning is twinning of various performance parameter data of the physical entity and the virtual model system; an environmental twin is a twin of the physical entity with internal environmental and external environmental data in the virtual model system;
correspondingly, in the step S1, the power, oil supply and combustion performance of the entity turbofan engine and the entity turbofan engine are measured by tests, and the obtained multidimensional data includes structural data, material data, process data, behavior data, performance data and environmental data.
In some embodiments, the geometric model is built in CATIA software, the physical model is built in FLUENT software and ABAQUS software, the behavioral model and a one-dimensional whole machine model of the rule model are built in GT-POWER software, and the behavioral model and a three-dimensional combustion model of the rule model are built in Converge software.
In some embodiments, the service system is built in Labview data collection and analysis software and Access database.
In some embodiments, in step S2, the simulation behavior and performance result of the virtual model system and the behavior data and performance data in the acquired multidimensional data are subjected to fusion analysis, specifically, the simulation result of the virtual model system and the fuel supply pressure and flow data, the sealing leakage amount data, the atomization performance data, and the combustion heat release law data in the acquired multidimensional data are subjected to fusion analysis.
In some embodiments, the adding of material and process attributes in the improved virtual model system in step S3 specifically includes adding material attributes in a one-dimensional whole machine model of the geometric model, the physical model, and the behavioral model and the rule model.
In some embodiments, the process twinning is a twinning of process data of the manufacturing and assembly of the physical entity and the virtual model system, wherein the process data of the manufacturing and assembly includes a manufacturing approach, a manufacturing tolerance, a process benchmark, and a process cost model.
In some embodiments, the iterative calculation improvement of the oil supply and combustion system structural parameters in the virtual model system in the step S2 is performed to obtain the optimal structural parameters, and specifically includes the following steps:
s201: selecting the length of an oil supply sealing structure, the total volume of an oil supply pipeline, the length of a fuel oil atomization structure and the diameter of a dilution hole of a combustion diffusion area as optimization factors;
s202: defining the horizontal range and the test times of each optimization factor by using a Latin hypercube sampling method, responding by using a tightness index of reaction oil supply performance, an atomization coefficient of reaction atomization and combustion quality and a combustion efficiency index, performing test calculation in the virtual model system to obtain a test result, fitting a response surface according to the test result, then evaluating the fitting quality of the response surface, if the fitting precision of the response surface is poor, increasing the test times, repeating the step S202, and if the fitting precision of the response surface is good, performing the step S203;
s203: setting an optimization target, performing optimization calculation by using a genetic algorithm to obtain an optimization result of structural parameters of the oil supply and combustion system, rounding the optimization result, simulating the virtual model system with the optimized structural parameters, judging whether the simulation result meets the performance requirement, if so, ending the iterative calculation improvement process to obtain the optimal structural parameters, and otherwise, circularly performing the steps S202 and S203.
In some embodiments, the step S202 of fitting the response surface according to the test result is to fit the response surface according to the test result by using a common least square method, and the fitting order is 2 orders.
In some embodiments, the performing optimization calculation by using a genetic algorithm in step S203 specifically includes the following steps:
setting the maximum sealing degree, the maximum atomization coefficient and the maximum combustion efficiency as improvement targets, setting the weight of each improvement target equal, setting the maximum improvement iteration frequency to be 80-120 times, judging the convergence condition that continuous 15-25 iterations have no change, sampling individuals at each time are 30-50, the mutation rate is 8% -12%, performing hybridization through single-point crossing, selecting the optimal elimination system, performing mutation in a uniform variation mode, and finally obtaining the optimized values of the length of the oil supply sealing structure, the total volume of the oil supply pipeline, the length of the fuel oil atomization structure and the diameter of the dilution hole of the combustion diffusion region.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1 is a block flow diagram of a method for optimizing a fuel supply and combustion system for a sustainable aviation fuel turbofan engine according to an embodiment of the present invention.
Fig. 2 is a block diagram of a digital twin structure system based on an embodiment of the present invention.
FIG. 3 is a schematic diagram of various digital twinning techniques employed between a virtual model system and a physical entity in the present invention.
FIG. 4 is a block diagram of a process for performing iterative improvement of fuel supply and combustion system structural parameters in a virtual model system to obtain optimal structural parameters according to an embodiment of the present invention.
Reference numerals:
digital twinning architecture system 1000
Virtual model system 1 physical entity 2 service system 3 twin data 4
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention and are not to be construed as limiting the present invention.
The method of optimizing the fueling and combustion system for a sustainable aviation fuel turbofan engine of the present invention is described below with reference to fig. 1 through 4.
According to the method for optimizing the fuel supply and combustion system of the sustainable aviation fuel turbofan engine, based on the digital twin structure system 1000, as shown in fig. 2, the digital twin structure system 1000 comprises a virtual model system 1, a physical entity 2, a service system 3, twin data 4 and interactive connection.
Wherein, the physical entity 2 comprises actual entity data and actual entity processing, manufacturing and assembling process data; in the present invention, the physical entity 2 refers to objectively existing data of the turbofan engine and the fuel and combustion system and data of the manufacturing and assembling process of the fuel and combustion system, the turbofan engine includes a plurality of different sensors directly or indirectly arranged on the turbofan engine, and the sensors are used for monitoring the operating state and performance data of the turbofan engine and the fuel and combustion system in real time.
The virtual model system 1 is used for virtually simulating the physical entity 2, and various digital twinning technologies are adopted between the virtual model system 1 and the physical entity 2, such as structure twinning, material twinning, process twinning, behavior twinning, performance twinning and environment twinning. The virtual model system 1 includes four levels of models, namely a geometric model, a physical model, a behavior model and a rule model, wherein the geometric model is used for describing the shape, the size, the processing, the manufacturing and the assembly information of each part in an actual entity, and the geometric model can be established in modeling software such as CATIA. The physical model is used for simulation of physical properties of an entity in practice, for example, the physical model in the invention is used for simulation of oil supply flow and atomization characteristics and rotor system dynamic characteristics, and the physical model can be established in modeling software such as FLUENT and ABAQUS. The behavior model is used for receiving data fed back by an actual entity experiment in practice, responding to external driving and disturbance, and processing and adjusting the virtual model system 1, so that the calculation in the virtual model system 1 is more accurate and reliable; the rule model is used for modeling and simulating a performance rule or rule of an actual entity, so that the virtual model system 1 has a rapid and accurate iterative improvement and prediction function. Specifically, for example, a one-dimensional whole machine model of the behavior model and the rule model may be established in GT-POWER software, and a three-dimensional combustion model of the behavior model and the rule model may be established in conversion software.
The service system 3 is used for collecting information of the virtual model system 1 and the physical entity 2, and performing fusion analysis on the information to provide accurate management and control and reliable operation and maintenance service. For example, the service system 3 will collect the structural parameter information of the fuel supply and combustion system components in the present invention, such as the information of the sealing structure, the atomization enhancing structure, etc., and the improvement and update in the design process will be described and recorded in the service system 3. Specifically, the service system 3 may be built in Labview data collection and analysis software and Access database.
The twin data 4 comprises data generated by the physical entity 2, the virtual model system 1 and the service system 3, the twin data 4 is processed by the service system 3 and then fed back to the virtual model system 1, the physical entity 2 and the service system 3 to push the operation of the digital twin structure system 1000, and the twin data 4 can be continuously updated and improved along with the generation of real-time data. That is, the twin data 4 is a core driver of the operation of the digital twin structure system 1000.
The interconnection comprises a plurality of different data transmission modules for interconnecting the physical entity 2, the virtual model system 1, the service system 3 and the twin data 4, so that the data of the physical entity 2, the virtual model system 1, the service system 3 and the twin data 4 can be exchanged and transmitted among the parts to form an organic whole. The physical entity 2, the virtual model system 1, the service system 3 and the twin data 4 are connected with each other, so that interactive transmission of the twin data 4 is realized, and the consistency of iteration improvement directions of all parts is ensured.
It can be understood that the optimization method is established on the basis of the digital twin structure system 1000, multiple digital twin technologies are adopted between the virtual model system 1 and the physical entity 2, the fuel supply and combustion system of the sustainable aviation fuel turbofan engine is optimized on the basis of the digital twin structure system 1000 and the digital twin technologies, the optimization improvement efficiency is high, and the accuracy is high.
As shown in FIG. 1, the method for optimizing the fuel supply and combustion system of the sustainable aviation fuel turbofan engine comprises the following steps:
s1, establishing a virtual model system 1: the method comprises the steps of carrying out test measurement on power, oil supply and combustion performance of an entity turbofan engine and the entity turbofan engine to obtain multi-dimensional data to form a physical entity 2 of the turbofan engine, analyzing the obtained multi-dimensional data and storing the multi-dimensional data to a service system 3, wherein the entity turbofan engine takes sustainable aviation fuel or aviation fuel containing the sustainable aviation fuel as fuel, and comprises an oil supply and combustion system; that is, the present invention is directed to an improved and optimized fuel supply and combustion system for turbofan engines that is adapted to be fueled by a sustainable aviation fuel or aviation fuel that includes a sustainable aviation fuel. The turbofan engine simulation model and the sustainable aviation fuel combustion simulation model are established to form a virtual model system 1, and the service system 3 inputs the acquired multi-dimensional data into a simulation correction module in the virtual model system 1 so as to improve the accuracy of the virtual model system 1.
S2: virtual performance optimization: and operating the virtual model system 1, and performing fusion analysis on the simulation behavior and performance result of the virtual model system 1 and the behavior data and performance data in the acquired multidimensional data to verify the accuracy of twin simulation of the virtual model system 1. And performing iterative calculation improvement of structural parameters of the oil supply and combustion system in the virtual model system 1 to obtain optimal structural parameters. The iterative calculation improvement of the structural parameters of the oil supply and combustion system in the turbofan engine adopts the multi-objective improvement of experimental design. The experimental design is a research method for systematically researching the relationship between independent variables and dependent variables structurally. The virtual model system 1 adopts a test design method to quickly and reliably improve important structural parameters of the oil supply and combustion system in multiple targets, obtain accurate performance improvement results and save a large amount of processing and test time and cost. The simulation such as the test design multi-objective improvement and the like in the virtual model system 1 has the advantages of high efficiency, high reliability and high accuracy, and simultaneously stores a large amount of effective data in the design and process improvement processes, thereby having an important promotion effect on the development of engineering improvement technology. According to the optimal structural parameters, structural parameters of an oil supply pipeline and an atomization structure in the oil supply and combustion system are improved in the physical model to form an improved physical model, the improved physical model is used for verifying oil supply flowing and atomization characteristics and rotor system dynamic characteristics, and the final structural parameters of the oil supply and combustion system in the virtual model system 1 are determined; it should be noted that the second half of step S2 is physical model verification, mainly on the physical level, such as verification of basic models of oil supply, atomization, and rotor dynamics, and emphasizes verification of the sub-system model, while the first half of step S2 emphasizes the entire virtual model system 1.
S3: virtual manufacturing simulation: determining the shape, size, assembly relationship and manufacturing data of the parts of the fuel supply and combustion system in the improved virtual model system 1 according to the structural parameters of the fuel supply and combustion system in the final virtual model system 1, obtaining the improved geometric model, for example, simulating the processes of machining, manufacturing and assembling to obtain the assembly relationship and manufacturing data, and adding materials and process attributes in the improved virtual model system 1. Materials and process attributes are added into the virtual model system 1, so that the machining and manufacturing process of the oil supply and combustion system entity can be more accurately guided. The simulation of the processes of machining, manufacturing and assembling is beneficial to improving process management, improving machining and assembling efficiency, reducing rejection rate and being beneficial to realizing full qualification of parts in small-batch manufacturing.
S4: the actual manufacturing process comprises the following steps: and actually processing, manufacturing and assembling the parts in the oil supply and combustion system according to the information provided by the improved virtual model system 1 to obtain the improved entity turbofan engine, wherein in the process, the actual shapes, sizes, assembly relations, processing and manufacturing data, materials and process data of the parts in the oil supply and combustion system of the entity turbofan engine are fed back to the service system 3 so as to optimize the improved virtual model system 1.
S5: and (3) real engine test: testing the performance of the power, oil supply and combustion system of the improved entity turbofan engine, feeding back the collected behavior data, performance data and environmental data to the service system 3, performing fusion analysis with the simulation data generated by the optimized virtual model system 1, and perfecting the optimized virtual model system 1. By adopting the test data to feed back and correct the virtual model system 1, the accuracy of the virtual model system 1 can be improved, and the subsequent product management and further optimization are facilitated.
The method for optimizing the fuel supply and combustion system of the sustainable aviation fuel turbofan engine has the advantages that firstly, the method is established on the basis of a digital twin structure system 1000, a digital twin technology is adopted between a virtual model system 1 and a physical entity 2, and the accuracy of the virtual model system 1 of the turbofan engine established on the basis of the digital twin structure system 1000 and the digital twin technology is higher; secondly, a turbofan engine virtual model system 1 with high accuracy is adopted to simulate a multi-target improvement process of structural parameters of an oil supply and combustion system, so that the method has the advantages of high efficiency, high reliability and high accuracy, can obtain an accurate performance improvement result, saves a large amount of time and processing cost, simulates the processes of processing, manufacturing and assembling, is beneficial to improving process management, improving the processing and assembling efficiency, reducing the rejection rate, and is beneficial to realizing full qualification of parts in small-batch manufacturing; and thirdly, feeding back the actual processing and manufacturing process of the oil supply and combustion system in the turbofan engine and the test result to the virtual model system 1 to obtain a more perfect virtual model system 1, recording the data of the virtual-real interaction fusion analysis, facilitating the inheritance of data information and playing an important role in promoting the development of the engine engineering improvement technology.
In some embodiments, as shown in fig. 3, the various digital twinning techniques employed between the virtual model system 1 and the physical entity 2 include structural twinning, material twinning, process twinning, behavioral twinning, performance twinning, and environmental twinning;
specifically, the geometric model in the virtual model system 1 can reflect the structure and assembly relationship of parts in the turbofan engine, the geometric model can be modified and transmitted to the physical entity 2 through the service system 3 to guide the machining, manufacturing and assembly of the turbofan engine, and meanwhile, real-time data of the physical entity 2 can be fed back to the service system 3.
The material twinning is the twinning of the physical property and dynamic property data of the material used by the physical entity 2 and each part in the virtual model system 1, specifically, the material information of the actual tested oil supply and combustion system is fed back to the service system 3 for data fusion analysis, and then transmitted to the virtual model system 1, and the material information in the virtual model system 1 can guide the processing and manufacturing of the oil supply and combustion system.
The process twin is the twin of the process data of the processing, manufacturing and assembling of the physical entity 2 and the virtual model system 1, specifically, the process data of the oil supply and combustion system is fed back to the geometric model through the service system 3, and the process information in the geometric model is corrected on the basis of the process data, so that the improved geometric model can simulate the actual manufacturing process of the oil supply and combustion system and guide the processing and manufacturing of the oil supply and combustion system.
The behavior twins are twins of various response data of the physical entity 2 and the virtual model system 1 to the self state or the external environment, specifically, a twin mirror image of the power, the oil supply and the combustion behavior of the turbofan engine is established in the physical model and the behavior model, the data describing the power, the oil supply and the combustion behavior of the turbofan engine are derived from various data collected by a sensor in the actual turbofan engine, various behavior information collected by the sensor can be fed back to the behavior model and is reproduced in the behavior model and the rule model, and the prediction analysis of the power, the oil supply and the combustion behavior in the virtual model system 1 can guide the improvement of the design scheme of the oil supply and combustion system.
The performance twinning is the twinning of various performance parameter data of the physical entity 2 and the virtual model system 1; specifically, performance data acquired by the test equipment and the sensors are fed back to a one-dimensional complete machine model of the behavior model and the regular model through the service system 3, and are subjected to fusion analysis with performance simulation data of the virtual model system 1, so that the reappearance and prediction of the performance of the oil supply and combustion system are finally realized in the virtual model system 1, and the improvement of the design scheme of the oil supply and combustion system is guided according to the prediction result.
The environment twin is the twin of internal environment and external environment data in the physical entity 2 and the virtual model system 1, specifically, a mirror image of a turbofan engine working environment is established in a one-dimensional whole machine model of the behavior model and the rule model, the mirror image comprises internal environment conditions and external environment conditions in the entity turbofan engine test process, the external environment conditions mainly comprise external environment data such as air pressure, temperature, humidity, noise and vibration intensity, and the internal environment conditions mainly comprise internal environment data such as temperature and pressure. The environmental twin is beneficial to help the virtual model system 1 improve the accuracy of performance prediction for turbofan engines.
Correspondingly, in the step S1, the power, oil supply and combustion performance of the entity turbofan engine and the entity turbofan engine are measured in a test mode, and the obtained multidimensional data comprise structural data, material data, process data, behavior data, performance data and environmental data. In this way, it is advantageous to obtain a highly accurate virtual model system 1 and a high quality of improved optimization results.
In some embodiments, the geometric model is built in CATIA software, the physical model is built in FLUENT software and ABAQUS software, the one-dimensional whole machine model of the behavior model and the rule model is built in GT-POWER software, and the three-dimensional combustion model of the behavior model and the rule model is built in Converge software, so that the simulation effect is good. Wherein the three-dimensional combustion model of the behavioral model and the rules model may include only a simulation model of the fuel supply and combustion system.
In some embodiments, the service system 3 is established in Labview data acquisition and analysis software and an Access database, and the use effect is good.
In some embodiments, in step S2, the simulation behavior and performance result of the virtual model system 1 and the behavior data and performance data in the obtained multidimensional data are subjected to fusion analysis, specifically, the oil supply pressure and flow data, the seal leakage amount data, the atomization performance data, and the combustion heat release law data in the simulation result of the virtual model system 1 and in the obtained multidimensional data are subjected to fusion analysis. Therefore, the method is beneficial to verifying the accuracy of the simulation twinning of the turbofan engine simulation model and the sustainable aviation fuel combustion simulation model.
In some embodiments, the adding of material and process attributes in the improved virtual model system 1 in step S3 includes adding material attributes in a geometric model, a physical model, and a one-dimensional whole machine model of a behavior model and a rule model. It can be understood that adding material attributes to the geometric model can achieve one-to-one correspondence between the oil supply and the geometric model of the combustion system and the use of the material of the oil supply and the combustion system entity; the material attribute is added into the physical model, so that the accuracy of calculation of oil supply pipeline transmission flow characteristics, rotor system dynamics and the like can be improved; material attributes are added into the behavior model and the rule model, so that the calculation is more accurate and reliable, and the improvement strategy is more complete.
In some embodiments, the process twin is a twin of process data of the manufacturing and assembly of the physical entity 2 and the virtual model system 1, wherein the process data of the manufacturing and assembly includes a processing manner, a processing tolerance, a process reference and a process cost model. Therefore, on one hand, the simulation degree of the established virtual model system 1 is higher, and the accuracy is higher; on the other hand, the method is favorable for comprehensively and efficiently guiding the actual processing process of the oil supply and combustion system, is favorable for improving process management, improving processing and assembling efficiency, reducing rejection rate and is favorable for realizing full qualification of parts in small-batch manufacturing.
In some embodiments, the iterative calculation improvement of the fuel supply and combustion system structural parameters in the virtual model system 1 in step S2 is performed to obtain the optimal structural parameters, as shown in fig. 4, and specifically includes the following steps:
s201: selecting the length of an oil supply sealing structure, the total volume of an oil supply pipeline, the length of a fuel oil atomization structure and the diameter of a dilution hole of a combustion diffusion area as optimization factors; namely, the parameters of the oil supply and combustion system are selected as optimization factors.
S202: defining the horizontal range and the test frequency of each optimization factor by using a Latin hypercube sampling method, responding by using a sealing degree index of reaction oil supply performance, an atomization coefficient of reaction atomization and combustion quality and a combustion efficiency index, performing test calculation in a virtual model system 1 to obtain a test result, fitting a response surface according to the test result, evaluating the fitting quality of the response surface, increasing the test frequency if the fitting precision of the response surface is poor, repeating the step S202, and performing the step S203 if the fitting precision of the response surface is good; specifically, for example, the fitting quality of the response surface can be evaluated by adopting an adj.R-sqr index, the adj.R-sqr index has high reliability, the influence of over-fitting can be eliminated, and the adj.R-sqr index values of the response surface of the sealing degree, the atomization coefficient and the combustion efficiency are all above 0.8, which indicates that the response fitting quality is high, and can be applied to subsequent optimization calculation.
S203: setting an optimization target, performing optimization calculation by using a genetic algorithm to obtain an optimization result of structural parameters of the oil supply and combustion system, rounding the optimization result, simulating the virtual model system 1 with the optimized structural parameters, judging whether the simulation result meets the performance requirement, if so, ending the iterative calculation improvement process to obtain the optimal structural parameters, and otherwise, circularly performing the steps S202 and S203. It can be understood that the invention carries out multi-target improvement on the important structural parameters of the oil supply and combustion system by adopting a test design method in the virtual model system 1, the improvement process is rapid and reliable, an accurate performance improvement result can be obtained, and a large amount of processing and test time and cost are saved.
In some embodiments, the response surface is fitted according to the test result in step S202, specifically, the response surface is fitted according to the test result by using a common least square method, and the fitting order is 2 orders.
In some embodiments, the optimization calculation using the genetic algorithm in step S203 specifically includes the following steps:
setting the maximum sealing degree, the maximum atomization coefficient and the maximum combustion efficiency as the improvement targets, setting the weight of each improvement target equal, setting the maximum improvement iteration frequency to be 80-120 times, judging the convergence condition that no change occurs in continuous 15-25 iterations, wherein the sampling individual is 30-50 each time, the mutation rate is 8-12%, hybridizing by single-point crossing, selecting the optimal elimination system, mutating in a uniform variation mode, and finally obtaining the optimized values of the length of the oil supply sealing structure, the total volume of the oil supply pipeline, the length of the fuel oil atomization structure and the diameter of the dilution hole of the combustion diffusion area, thus obtaining the optimized result of the structural parameters of the oil supply and combustion system with good optimization effect.
Preferably, the maximum sealing degree, the maximum atomization coefficient and the maximum combustion efficiency are set as improvement targets, the weight of each improvement target is equal, the maximum improvement iteration frequency is set as 100 times, convergence is judged under the condition that 20 iterations are not changed continuously, the sampling individual is 40 each time, the mutation rate is 10%, hybridization is carried out through single-point crossing, optimal elimination is selected, mutation is carried out in a uniform mutation mode, and finally the optimal values of the length of the oil supply sealing structure, the total volume of the oil supply pipeline, the length of the fuel oil atomization structure and the diameter of the dilution hole in the combustion diffusion region can be obtained.
Optionally, setting the maximum sealing degree, the maximum atomization coefficient and the maximum combustion efficiency as the improvement targets, setting the weight of each improvement target equal, setting the maximum improvement iteration frequency as 80 times, judging the convergence condition that no change occurs in 15 continuous iterations, sampling individuals at each time are 30, and the mutation rate is 8%, performing hybridization through single-point crossing, selecting optimal elimination, performing mutation in a uniform variation mode, and finally obtaining the optimized values of the length of the oil supply sealing structure, the total volume of the oil supply pipeline, the length of the fuel oil atomization structure and the diameter of the dilution hole of the combustion diffusion area, so that the optimized result of the structural parameters of the oil supply and combustion system is obtained, and the optimization effect is good.
Optionally, the maximum sealing degree, the maximum atomization coefficient and the maximum combustion efficiency are set as improvement targets, the weight of each improvement target is equal, the maximum improvement iteration frequency is set as 120 times, convergence is judged under the condition that 25 iterations are not changed continuously, the sampling individual is 50 each time, the mutation rate is 12%, hybridization is carried out through single-point crossing, the optimal elimination system is selected, mutation is carried out in a unified variation mode, and finally the optimized values of the length of the oil supply sealing structure, the total volume of the oil supply pipeline, the length of the fuel oil atomization structure and the diameter of the dilution hole in the combustion diffusion region can be obtained, so that the optimized result of the structural parameters of the oil supply and combustion system is obtained, and the optimized effect is good.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an illustrative embodiment," "an example," "a specific example," or "some examples" or the like are intended to mean that a particular feature, structure, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
While embodiments of the invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.
Claims (10)
1. A method for optimizing a fuel supply and combustion system of a sustainable aviation fuel turbofan engine is characterized in that,
based on a digital twin structure system, the digital twin structure system comprises a virtual model system, a physical entity, a service system, twin data and an interactive connection;
wherein the physical entities comprise actual entity data and actual entity manufacturing and assembly process data;
the virtual model system is used for virtually simulating the physical entity, a plurality of digital twinning technologies are adopted between the virtual model system and the physical entity, the virtual model system comprises a model with four levels of a geometric model, a physical model, a behavior model and a regular model, and the geometric model is used for describing the shape, the size, the processing, the manufacturing and the assembling information of each part in the actual entity; the physical model is used for simulation of physical attributes of the real entity; the behavior model is used for receiving data fed back by the actual entity experiment in practice, responding to external driving and disturbance effects, and processing and adjusting the virtual model system; the rule model is used for modeling and simulating the performance rule or rule of the actual entity;
the service system is used for collecting the information of the virtual model system and the physical entity and carrying out fusion analysis on the information;
the twin data comprises data generated by the physical entity, the virtual model system and the service system, the twin data is processed by the service system and then fed back to the virtual model system, the physical entity and the service system to push the operation of the digital twin structure system, and the twin data can be continuously updated and improved along with the generation of real-time data;
the interconnection comprises a plurality of different data transmission modules for interconnecting the physical entity, the virtual model system, the service system and the twin data so that data of the physical entity, the virtual model system, the service system and the twin data are exchanged among the parts;
the method for optimizing the fuel supply and combustion system of the sustainable aviation fuel turbofan engine comprises the following steps:
s1, establishing a virtual model system: the method comprises the steps of carrying out test measurement on the power, oil supply and combustion performance of an entity turbofan engine and the entity turbofan engine, obtaining multi-dimensional data to form a physical entity of the turbofan engine, analyzing the obtained multi-dimensional data and storing the data to a service system, wherein the entity turbofan engine takes sustainable aviation fuel or aviation fuel containing the sustainable aviation fuel as fuel, and the entity turbofan engine comprises an oil supply and combustion system; establishing a turbofan engine simulation model and a sustainable aviation fuel combustion simulation model to form the virtual model system, and inputting the acquired multidimensional data into a simulation correction module in the virtual model system by the service system;
s2: virtual performance optimization: operating the virtual model system, performing fusion analysis on the simulation behavior and performance result of the virtual model system and the behavior data and performance data in the acquired multidimensional data, and performing iterative calculation improvement on structural parameters of an oil supply and combustion system in the virtual model system to obtain optimal structural parameters; according to the optimal structural parameters, structural parameters of an oil supply pipeline and an atomization structure in the oil supply and combustion system are improved in a physical model to form an improved physical model, oil supply flow and atomization characteristics and rotor system dynamic characteristics are verified by using the improved physical model, and the final structural parameters of the oil supply and combustion system in the virtual model system are determined;
s3: virtual manufacturing simulation: determining the shape, size, assembly relation and processing and manufacturing data of parts of the oil supply and combustion system in the improved virtual model system according to the final structural parameters of the oil supply and combustion system in the virtual model system to obtain an improved geometric model, and adding materials and process attributes in the improved virtual model system;
s4: the actual manufacturing process comprises the following steps: according to the information provided by the improved virtual model system, actually processing, manufacturing and assembling parts in the oil supply and combustion system to obtain an improved entity turbofan engine, wherein in the process, the actual shapes, sizes, assembly relations, processing and manufacturing data, materials and process data of the parts in the oil supply and combustion system are fed back to the service system to optimize the improved virtual model system;
s5: and (3) real engine test: testing the performance of the power, oil supply and combustion system of the improved entity turbofan engine, feeding back the collected behavior data, performance data and environment data to the service system, performing fusion analysis with the simulation data generated by the optimized virtual model system, and perfecting the optimized virtual model system.
2. A sustainable aviation fuel turbofan engine fuel supply and combustion system optimization method according to claim 1 wherein the plurality of digital twinning techniques employed between the virtual model system and the physical entity include structural twinning, material twinning, process twinning, behavioral twinning, performance twinning and environmental twinning;
wherein the structural twinning is the twinning of the structural, appearance and assembly relationship data of the physical entity and the virtual model system; the material twinning is twinning of physical property and dynamic property data of materials used by the physical entity and each part in the virtual model system; the process twinning is twinning of process data of machining, manufacturing and assembling of the physical entity and the virtual model system; the behavior twins are twins of various response data of the physical entity and the virtual model system to the self state or the external environment; the performance twin is the twin of the physical entity and various performance parameter data of the virtual model system; an environmental twin is a twin of the physical entity with internal environmental and external environmental data in the virtual model system;
correspondingly, in the step S1, the power, oil supply and combustion performance of the entity turbofan engine and the entity turbofan engine are measured in a test manner, and the obtained multidimensional data includes structural data, material data, process data, behavior data, performance data and environmental data.
3. A method for optimizing a sustainable aviation fuel turbofan engine fuel supply and combustion system according to claim 1 wherein the geometric model is built in CATIA software, the physical model is built in FLUENT software and ABAQUS software, the behavioral model and a one-dimensional whole machine model of the regular model are built in GT-POWER software, and the three-dimensional combustion model of the behavioral model and the regular model is built in Converge software.
4. A method for optimizing a sustainable aviation fuel turbofan engine fuel supply and combustion system according to claim 1 wherein the service system is built in Labview data collection and analysis software and Access database.
5. A method for optimizing a fuel supply and combustion system of a sustainable aviation fuel turbofan engine according to claim 1, wherein in the step S2, the simulation behavior and performance result of the virtual model system and the behavior data and performance data in the obtained multidimensional data are subjected to fusion analysis, specifically, the fuel supply pressure and flow data, the seal leakage data, the atomization performance data and the combustion heat release rule data in the simulation result of the virtual model system and the obtained multidimensional data are subjected to fusion analysis.
6. A method for optimizing a sustainable aviation fuel turbofan engine fuel supply and combustion system according to claim 1 wherein the adding of material and process attributes in the improved virtual model system in step S3 comprises adding material attributes in a one dimensional whole machine model of the geometric model, the physical model and the behavioral model and the regular model.
7. A sustainable aviation fuel turbofan engine fuel supply and combustion system optimization method according to claim 2 wherein the process twinning is a twinning of process data of manufacturing and assembly of the physical entity and the virtual model system, wherein the process data of manufacturing and assembly includes a manufacturing approach, a manufacturing tolerance, a process reference and a process cost model.
8. The method for optimizing a fuel supply and combustion system of a sustainable aviation fuel turbofan engine according to any one of claims 1 to 7, wherein the iterative calculation improvement of the fuel supply and combustion system structural parameters is performed in the virtual model system in the step S2 to obtain the optimal structural parameters, and the method comprises the following steps:
s201: selecting the length of an oil supply sealing structure, the total volume of an oil supply pipeline, the length of a fuel oil atomization structure and the diameter of a dilution hole of a combustion diffusion area as optimization factors;
s202: defining the horizontal range and the test times of each optimization factor by using a Latin hypercube sampling method, responding by using a sealing degree index of reaction oil supply performance, an atomization coefficient of reaction atomization and combustion quality and a combustion efficiency index, performing test calculation in the virtual model system to obtain a test result, fitting a response surface according to the test result, then evaluating the fitting quality of the response surface, if the fitting precision of the response surface is poor, increasing the test times, repeating the step S202, and if the fitting precision of the response surface is good, performing the step S203;
s203: setting an optimization target, performing optimization calculation by using a genetic algorithm to obtain an optimization result of structural parameters of the oil supply and combustion system, rounding the optimization result, simulating the virtual model system with the optimized structural parameters, judging whether the simulation result meets the performance requirement, if so, ending the iterative calculation improvement process to obtain the optimal structural parameters, and otherwise, circularly performing the steps S202 and S203.
9. The method for optimizing a fuel supply and combustion system of a sustainable aviation fuel turbofan engine according to claim 8, wherein the step S202 fits a response surface according to the test result, specifically, fits a response surface according to the test result by using a common least square method, and the fitting order is 2 nd order.
10. The method for optimizing a fuel supply and combustion system of a sustainable aviation fuel turbofan engine according to claim 9, wherein the applying a genetic algorithm for optimization calculation in step S203 specifically comprises the steps of:
setting the maximum sealing degree, the maximum atomization coefficient and the maximum combustion efficiency as improvement targets, setting the weight of each improvement target equal, setting the maximum improvement iteration frequency to be 80-120 times, judging the convergence condition that continuous 15-25 iterations have no change, sampling individuals at each time are 30-50, the mutation rate is 8% -12%, performing hybridization through single-point crossing, selecting the optimal elimination system, performing mutation in a uniform variation mode, and finally obtaining the optimized values of the length of the oil supply sealing structure, the total volume of the oil supply pipeline, the length of the fuel oil atomization structure and the diameter of the dilution hole of the combustion diffusion region.
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| CN116738872A (en) * | 2023-05-09 | 2023-09-12 | 北京航空航天大学 | Digital twinning-based visual simulation system for comprehensive thermal management of aero-engine |
| CN117473302A (en) * | 2023-12-26 | 2024-01-30 | 广东贝洛新材料科技有限公司 | Method, device, equipment and storage medium for testing structural reliability of automobile parts |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116738872A (en) * | 2023-05-09 | 2023-09-12 | 北京航空航天大学 | Digital twinning-based visual simulation system for comprehensive thermal management of aero-engine |
| CN116738872B (en) * | 2023-05-09 | 2024-01-23 | 北京航空航天大学 | Digital twinning-based visual simulation system for comprehensive thermal management of aero-engine |
| CN117473302A (en) * | 2023-12-26 | 2024-01-30 | 广东贝洛新材料科技有限公司 | Method, device, equipment and storage medium for testing structural reliability of automobile parts |
| CN117473302B (en) * | 2023-12-26 | 2024-03-15 | 广东贝洛新材料科技有限公司 | Method, device, equipment and storage medium for testing structural reliability of automobile parts |
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