Aero-engine, thermal management method and system, and computer readable medium

Abstract

The invention relates to an aero-engine, a thermal management method, a thermal management system and a computer readable medium. The thermal management method comprises the steps that S1, input parameters are received, and the input parameters comprise engine operation condition parameters; the power source rated parameters comprise the power source rated rotating speed and the power source rated power corresponding to each heat sink of the multiple heat sinks; the temperature parameters comprise the heat sink temperature of a radiator inlet corresponding to each heat sink; parameters of the radiator, and the radiating efficiency of the radiator corresponding to each heat sink; a heating part of the engine generates heat and lubricating oil flow; s2, energy efficiency optimization calculation is carried out according to the input parameters, and the optimization target is the power source rotating speed corresponding to each heat sink of the multiple heat sinks; and S3, outputting control parameters, wherein the control parameters comprise the optimized power source rotating speeds of the plurality of heat sinks.

Description

Technical Field

[0001] The present invention relates to the field of aircraft engines, and in particular to an aircraft engine, a thermal management method, a thermal management system and a computer-readable medium. Background Art

[0002] As the global awareness of protecting energy and the environment continues to increase, the requirements and restrictions on aircraft engine technical indicators are becoming more stringent. The future development goals of civil aviation engines focus on safety and reliability, fuel consumption, noise control, and pollution emissions. In terms of technological development, various OEMs continue to pursue higher economy and environmental protection in the research and development of commercial aircraft engines. In particular, under the background of "green aviation", engine manufacturers improve the cycle efficiency of traditional structural turbofan engines by improving thermal efficiency and bypass ratio, and carry out research on cycle parameter optimization, aerodynamic design improvement, and component durability design to improve engine performance and durability and reduce engine fuel consumption. Some new engine concepts, such as geared turbofan engines (GTF) and electric propulsion engines, will gradually be accepted by the market.

[0003] As the performance requirements of future aircraft become higher and higher, the thermal load of aircraft engines will become larger and larger, while the heat sink of fuel will be reduced, which will inevitably bring quite severe challenges in thermal management. First of all, advanced aircraft engines are developing towards higher speeds, loads and temperatures, and the heat transferred from high-temperature parts to lubricating oil is increasing. This is a severe challenge for the design of the main heat sink fuel system of the lubricating oil system. Taking the GTF configuration engine as an example, compared with the traditional configuration turbofan engine, the GTF engine has the advantages of low fuel consumption, low noise and low maintenance cost, but its core component fan drive gearbox has large power transmission and large heat dissipation, and is restricted by the engine flow channel and heat dissipation capacity. The allowed oil supply and return space and lubricating oil demand are very harsh, resulting in excessive heat generation of the gearbox during operation, which causes the system transmission efficiency to decrease and affects the gear transmission performance. At the same time, future aircraft emphasize fuel economy and propulsion system efficiency. The fuel flow cannot be increased without limit, but may be reduced, and the amount of fuel that can be used for heat dissipation is more limited. It can be seen that with the improvement of aircraft engine performance, as the main heat sink and cold source of the engine lubricating oil system and aircraft, the heat dissipation pressure borne by fuel is increasing. Excessively high fuel temperature will not only reduce the control accuracy and reliability of the engine fuel control system and shorten the service life of fuel accessories, but will also greatly reduce the cooling efficiency of the fuel on the lubricating oil.

[0004] As the performance of aircraft engines continues to improve, aircraft engines will adopt a large number of highly integrated electronic devices or new configuration technologies such as GTF. The heat dissipation demand is constantly rising. In addition, due to the heat loads generated by the power system, power system, hydraulic system, etc., the heat dissipation capacity of traditional heat sinks is also close to the limit. For example, the use of external air is subject to many restrictions, and the effective available fuel volume decreases as the fuel consumption decreases. The temperature limit of the cooled electronic equipment and the coking of the fuel also limit the maximum value allowed for the fuel.

[0005] Therefore, the art needs an aircraft engine, a thermal management method, a thermal management system, and a computer-readable medium to introduce more heat sink media (air, hydrogen, coolant, etc.), precisely control the heat sink flow, and achieve reasonable and optimal distribution of heat in the entire system to achieve the purpose of temperature regulation with minimal energy consumption. Summary of the invention

[0006] An object of the present invention is to provide a thermal management method.

[0007] An object of the present invention is to provide a thermal management system.

[0008] An object of the present invention is to provide an aircraft engine.

[0009] An object of the present invention is to provide a computer-readable storage medium.

[0010] A thermal management method according to a first aspect of the present invention is used for an aircraft engine, wherein the aircraft engine includes multiple heat sinks, and the thermal management method includes: S1. receiving input parameters, wherein the input parameters include: engine operating condition parameters; power source rated parameters, including the power source rated speed and power source rated power corresponding to each heat sink of the multiple heat sinks; temperature parameters, including the heat sink temperature at the radiator inlet corresponding to each heat sink; radiator parameters, the heat dissipation efficiency of the radiator corresponding to each heat sink; the heat generated by the heat-generating components of the engine and the lubricating oil flow rate; S2. performing energy efficiency optimization calculation according to the input parameters, wherein the optimization target is the power source speed corresponding to each heat sink of the multiple heat sinks, and the boundary conditions include: temperature limit, the lubricating oil temperature, and each heat sink temperature not exceeding the temperature threshold; the fuel flow rate must meet the engine working requirements; speed range: 0% to 100% rated speed, when the speed is 0, it means that the heat sink does not participate in heat exchange; S3. outputting control parameters, including: the optimized power source speed of the multiple heat sinks.

[0011] In the technical solution introduced above, energy efficiency optimization calculation can be used to achieve precise control of multiple heat sink power sources, reduce design margins, and reduce the weight and cost of the engine thermal management system.

[0012] In one or more embodiments, in S1: the engine operating parameters include at least: the altitude, Mach number, and temperature difference of the aircraft where the engine is located; the power source rated parameters include at least: fan rated speed, fan rated power, fuel pump rated speed, and fuel pump rated power; the temperature parameters include at least: the fuel temperature at the inlet of the main fuel and lubricating oil radiator, and the air temperature at the inlet of the air and lubricating oil radiator; the radiator parameters include at least: the heat dissipation efficiency of the main fuel and lubricating oil radiator, and the heat dissipation efficiency of the air and lubricating oil radiator.

[0013] In one or more embodiments, in S2, the energy efficiency optimization calculation includes: based on the inlet temperatures of the multiple heat sinks input in S1, the lubricating oil flow rate, the heat generation of the engine's heating components, the radiator heat exchange efficiency and other parameters, the flow rate of each of the multiple heat sinks, the lubricating oil and the outlet temperature of each of the multiple heat sinks are obtained by establishing a system thermal network model.

[0014] In one or more embodiments, in S2, the energy efficiency optimization calculation algorithm includes an evolutionary algorithm, a swarm intelligence algorithm, a simulated annealing algorithm, and a neural network algorithm.

[0015] In one or more embodiments, in S2, the algorithm for energy efficiency optimization calculation includes a machine learning algorithm.

[0016] A computer readable medium according to a second aspect of the present invention has a computer program thereon, and the program is executed by a processor to implement the steps of the thermal management method according to the first aspect.

[0017] According to a third aspect of the present invention, a thermal management system for an aircraft engine comprises: a memory for storing instructions executable by a processor; and a processor for executing the instructions to implement the thermal management method according to any one of claims 1 to 4.

[0018] In one or more embodiments, the thermal management system further includes a display module for displaying the energy efficiency optimization status of the thermal management system.

[0019] In one or more embodiments, the processor is integrated into a full authority digital engine controller.

[0020] An aircraft engine according to a fourth aspect of the present invention comprises the thermal management system as described in the third aspect. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which:

[0022] Figure 1It is a schematic block diagram of the structure of an aircraft engine including multiple heat sinks according to an embodiment of the present application.

[0023] Figure 2 It is a flow chart of a thermal management method according to an embodiment of the present application.

[0024] Figure 3 It is a schematic block diagram of the structure of an aircraft engine according to an embodiment of the present application.

[0025] Figure 4 It is a schematic block diagram of a thermal management system according to an embodiment of the present application.

[0026] Reference numerals:

[0027] 200-Thermal Management System

[0028] 201-Memory

[0029] 202-Processor

[0030] 203-Display module

[0031] 204-Full Authority Digital Engine Controller. DETAILED DESCRIPTION

[0032] The present invention is further described below in conjunction with specific embodiments and drawings. More details are elaborated in the following description to facilitate a full understanding of the present invention. However, the present invention can obviously be implemented in a variety of other ways different from the description herein. Those skilled in the art can make similar generalizations and deductions based on actual application situations without violating the connotation of the present invention. Therefore, the protection scope of the present invention should not be limited by the content of this specific embodiment.

[0033] At the same time, the present application uses specific words to describe the embodiments of the present application, such as "one embodiment", "an embodiment", and / or "some embodiments" to refer to a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "one embodiment" or "an embodiment" mentioned twice or more in different locations in this specification does not necessarily refer to the same embodiment. In addition, certain features, structures or characteristics in one or more embodiments of the present application can be appropriately combined.

[0034] It should be noted that in the following embodiments, the aircraft engines introduced in the following embodiments take aircraft and their turbofan engines as examples, but are not limited to them. For example, they can also be new generation aircraft engines, such as but not limited to GTF aircraft engines, hybrid electric propulsion engines, etc.

[0035] In the following embodiments, four heat sinks are used as an example for multiple heat sinks, namely air, fuel, a first heat sink, and a second heat sink, but this is not limiting. In actual applications, technicians in this field can increase or decrease the number of heat sink media types as needed, and the thermal management method introduced below is also applicable.

[0036] refer to Figure 1 As shown, the lubricating oil drawn from the lubricating oil tank by the lubricating oil supply pump is cooled in turn by the second radiator, the first radiator, the main fuel and lubricating oil radiator and the air lubricating oil radiator. The cooled lubricating oil goes to the engine bearings, gearboxes, motors and other components to take away the heat, and then is pumped back to the lubricating oil tank by the lubricating oil return pump. This is repeated to ensure that the engine does not overheat under any operating conditions. The fan is used to draw air into the air lubricating oil radiator, the fuel pump provides fuel to the main fuel and lubricating oil radiator, the first heat sink power source is used to provide the first heat sink to the first radiator, and the second heat sink provides the second heat sink to the second radiator. The main fuel and lubricating oil radiator here means the radiator through which the main fuel circuit at the outlet of the fuel pump flows, and exchanges heat with the lubricating oil, so it is called the main fuel and lubricating oil radiator.

[0037] Thermal management mainly includes temperature management and energy optimization. Temperature management ensures that the temperature of components does not exceed the allowable temperature level within the engine operating envelope, and also ensures that the temperature of heat sinks such as lubricating oil and fuel does not exceed the limit; energy optimization refers to achieving system temperature regulation with minimal energy consumption to improve engine performance.

[0038] Multiple heat sinks refers to the use of lubricating oil to cool heat-generating components such as aircraft engine bearings, gearboxes, and motors, and the use of multiple heat sink media such as fuel, air, and coolant to cool and dissipate the lubricating oil through a heat sink / lubricating oil radiator.

[0039] Energy efficiency optimization refers to the use of target optimization algorithms to obtain the optimal solution for the energy consumption of each heat sink power source while ensuring that the temperature of each heat sink is within the temperature limit, ensuring that the temperature of the system is regulated with minimal energy consumption.

[0040] like Figure 2 As shown, in some embodiments, the thermal management method includes:

[0041] S1. Receive input parameters, the input parameters include:

[0042] Engine operating parameters;

[0043] The rated parameters of the power source include the rated speed and the rated power of the power source corresponding to each of the plurality of heat sinks;

[0044] Temperature parameters, including heat sink temperature at the heat sink inlet corresponding to each heat sink;

[0045] Radiator parameters, heat dissipation efficiency of each radiator corresponding to the heat sink;

[0046] The heat generated by the engine's heat generating components and the oil flow.

[0047] Specifically, for example, the following parameters may be used:

[0048] Engine operating parameters include altitude H, Mach number Ma, and temperature difference dT; the temperature difference here means the difference between the ambient temperature and the standard atmospheric temperature 288.15K.

[0049] The rated parameters of the heat sink power source include: rated speed and rated power, and performance curves (flow speed curve mn and power speed curve Wn), including fan rated speed N1, fan rated power P1, fuel pump rated speed N2, fuel pump rated power P2, first heat sink power source speed N3, first heat sink power source rated power P3, second heat sink power source speed N4, second heat sink power source rated power P4.

[0050] The temperature parameters include the temperature before the heat sink enters the heat sink / lubricating oil radiator, including the fuel temperature Tfuel_in at the inlet of the main fuel and lubricating oil radiator, the air temperature Tair_in at the inlet of the air and lubricating oil radiator, the first heat sink temperature T1_in at the inlet of the first radiator, and the second heat sink temperature T2_in at the inlet of the second radiator.

[0051] The radiator parameters include the performance curves (heat exchange efficiency) of each heat sink / lubricating oil radiator, including the cooling efficiency ε1 of the main fuel and lubricating oil radiator, the cooling efficiency ε2 of the air and lubricating oil radiator, the cooling efficiency ε3 of the first radiator and the cooling efficiency ε4 of the second radiator.

[0052] The heat generated by the engine's heat-generating components, including the heat generated by bearings, gearboxes, motors and other components Q, and the lubricating oil flow m.

[0053] S2. Perform energy efficiency optimization calculation according to the input parameters, the optimization target is the power source speed corresponding to each heat sink of the multiple heat sinks, and the boundary conditions include:

[0054] Temperature limit, lubricating oil temperature, and each heat sink temperature do not exceed the temperature threshold; for example, the fuel temperature does not exceed 120°C, the lubricating oil temperature does not exceed 160°C, and the other heat sinks do not exceed the corresponding temperature thresholds.

[0055] The fuel flow rate must meet the engine's operating requirements;

[0056] Speed ​​range: 0% to 100% rated speed. When the speed is 0, it means that the heat sink does not participate in heat exchange.

[0057] For multiple heat sinks, the specific energy efficiency optimization algorithm can be:

[0058] Given the inlet temperature of each heat sink, the oil flow rate, the heat generation Q of the engine's hot parts, the heat exchange efficiency of the radiator and other parameters, the flow rate of each heat sink (obtained according to the current speed of its power source and the flow-speed relationship curve), the outlet temperature of the oil and fuel and other heat sinks can be obtained by establishing a system thermal network model:

[0059] [Tfuel, Toil1, Toil2, Tair, T1, T2] = f (n1, n2, n3, n4, m, ε1, ε2, ε3, ε4)

[0060] Formula (1)

[0061] Among them, Tfuel is the fuel temperature after the main fuel and lubricating oil radiator, Toil1 is the lubricating oil temperature after the return oil pump, Toil2 is the lubricating oil temperature after the fuel supply pump, Tair is the air temperature after the air and lubricating oil radiator, T1 is the first heat sink temperature after the first radiator, and T2 is the second heat sink temperature after the second radiator.

[0062] Similarly, the energy consumption of the heat sink power source is related to the actual speed n, the rated speed N and the rated power P. The energy consumption of the heat sink power source is calculated according to the power source power performance curve. Taking the fan energy efficiency as an example, the fan speed is n1, the fan rated speed is N1, and the rated power is P1. The corresponding energy consumption W1 is:

[0063] W1=f(n1,N1,P1) Formula (2)

[0064] The total heat sink energy consumption calculation formula is as follows:

[0065]

[0066] The optimization objective can be expressed as

[0067]

[0068] According to the optimization objectives and optimization constraints, the energy efficiency problem of multiple heat sinks can be optimized and solved through intelligent optimization algorithms (evolutionary algorithms, swarm intelligence algorithms, simulated annealing algorithms, neural network algorithms, etc. and machine learning algorithms). Among them, evolutionary algorithms, swarm intelligence algorithms, simulated annealing algorithms and neural network algorithms can be classified as traditional intelligent optimization algorithms. The main idea is a search optimization method based on natural phenomena, using certain rules to gradually approach the optimal solution. For example, when using the genetic algorithm in the evolutionary algorithm to solve the energy efficiency optimization problem of multiple heat sinks, first randomly generate a set of variables as the initial value according to the range of variation of the optimization variable (the speed of each power source), and calculate the corresponding fitness function value (that is, the total heat sink energy consumption of the system). The ideas of "natural selection" and "population inheritance" are adopted, and after crossover and mutation, a better next generation is produced, so that it gradually evolves towards the optimal solution until the optimal solution is produced.

[0069] Machine learning algorithms are mainly optimization algorithms based on data analysis developed under the background of artificial intelligence, mainly including linear regression algorithms, support vector machine algorithms, logistic regression algorithms, reinforcement learning algorithms, etc. For the multi-heat sink optimization control method of the aircraft engine thermal management system mentioned in the present invention, a reinforcement learning algorithm can be used for solution. The learning strategy is mainly to approximate the minimum value of the objective function, and a certain learning strategy is added to improve the solution speed. For example, add the condition "using fuel as the main heat sink, and give priority to increasing the fuel pump speed". When solving, first determine the fuel pump speed, and then add the condition "reduce the fan after-induction air as much as possible". When solving, choose the lowest fan speed as much as possible.

[0070] S3. Output control parameters, including:

[0071] The power source rotation speed of the plurality of heat sinks is optimized.

[0072] For example, the optimized rotation speeds of the power sources of the heat sinks include: the fan rotation speed n1_opt, the fuel pump rotation speed n2_opt, the first heat sink power source rotation speed n3_opt, and the second heat sink power source rotation speed n4_opt.

[0073] Although the above method is illustrated and described as a series of actions for simplicity of explanation, it should be understood and appreciated that these steps are not limited by the order of the actions, because according to one or more embodiments, some actions may occur in a different order and / or concurrently with other actions from those illustrated and described herein or not illustrated and described herein but understandable to those skilled in the art.

[0074] According to another aspect of the present invention, a computer-readable medium is also provided.

[0075] The computer-readable medium provided by the present disclosure has computer instructions thereon. When the computer instructions are executed by a processor, the program can be executed by the processor to implement the steps executed by the program in the thermal management method of the aircraft engine as described in the above embodiment.

[0076] refer to Figure 4 As shown, in some embodiments, the thermal management system 200 includes: a memory 201 for storing instructions executable by a processor; a processor 202 for executing the instructions to implement the steps executed by the program in the thermal management method of the aircraft engine as described in the above embodiments.

[0077] In addition, the thermal management system 200 may also include a display module 203 for displaying the energy efficiency optimization of the thermal management system, so that the aircraft engine monitoring and maintenance workers can know the operation of the aircraft engine in time, or provide the aircraft operator with the operation of the engine to help him pay attention to the energy consumption of the engine in time. The display module 203 can have a variety of forms of expression. For example, in an aircraft, the display module 203 can be a dashboard or a display screen, or even a head-up display (HUD) of a pilot's helmet, and on the ground, the display module 203 can be a computer screen, a mobile screen, etc. of a maintenance person.

[0078] It can be understood that the processor 202 in the previous embodiment, such as a system on a chip (SOC), a microcontroller, a microprocessor (e.g., a single-chip microcomputer), a reduced instruction set computer (RISC), an application-specific integrated circuit (ASIC), an application-specific instruction integrated processor (ASIP), a central processing unit (CPU), a graphics processing unit (GPU), a physical processing unit (PPU), a microcontroller unit, a digital signal processor (DSP), a field programmable gate array (FPGA), an advanced RISC machine (ARM), a programmable logic device (PLD), any circuit or processor capable of performing one or more functions, etc., can be a combination of one or more, such as in an aircraft. Figure 3 As shown, the processor 202 may be an electronic controller integrated in the engine, namely a full authority digital engine controller 204 (FADEC), to further improve the integration of the thermal management system.

[0079] For specific control, please refer to Figure 3As shown, the input of the thermal management system is the speed and temperature parameters obtained from the thermal management system through sensor measurement, as well as the engine operating condition parameters transmitted from the engine electronic controller through the data bus. After receiving the input, the energy efficiency optimization controller runs the optimization control algorithm, and at the same time corrects the internal thermal network model according to the temperature / speed and other parameters measured by the sensor in real time to ensure the accuracy of the thermal network model, thereby ensuring the accuracy of the optimization control algorithm. The output of the multiple heat sink energy efficiency optimization control devices is the optimized speed of each heat sink power source, and it is output to each heat sink power source. Each heat sink power source adjusts the actual speed according to the controller output until the actual speed is equal to the optimized speed value. In actual applications, this multi-heat sink energy efficiency optimization control device can be dynamically adjusted or adjusted according to different working conditions to achieve comprehensive thermal management of aircraft engines.

[0080] In summary, the beneficial effects of the aircraft engine, thermal management method, system and computer-readable medium introduced in the above embodiments include but are not limited to, through energy efficiency optimization calculation, precise control of multiple heat sink power sources can be achieved, reducing the design margin, and reducing the weight and cost of the engine thermal management system.

[0081] The steps of the method described in conjunction with the embodiments disclosed herein may be embodied directly in hardware, in a software module executed by a processor, or in a combination of the two. The software module may reside in a RAM memory, a flash memory, a ROM memory, an EPROM memory, an EEPROM memory, a register, a hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art. An exemplary storage medium is coupled to a processor so that the processor can read and write information from / to the storage medium. In an alternative, a storage medium may be integrated into a processor. The processor and the storage medium may reside in an ASIC. The ASIC may reside in a user terminal. In an alternative, the processor and the storage medium may reside in a user terminal as discrete components.

[0082] In one or more exemplary embodiments, the functions described may be implemented in hardware, software, firmware, or any combination thereof. If implemented as a computer program product in software, each function may be stored on or transmitted by a computer-readable medium as one or more instructions or codes. Computer-readable media include both computer storage media and communication media, including any medium that facilitates the transfer of a computer program from one place to another. Storage media may be any available medium that can be accessed by a computer. As an example and not limitation, such a computer-readable medium may include RAM, ROM, EEPROM, CD-ROM or other optical disk storage, disk storage or other magnetic storage device, or any other medium that can be used to carry or store the desired program code in the form of an instruction or data structure and can be accessed by a computer. Any connection is also properly referred to as a computer-readable medium. For example, if the software is transmitted from a website, server, or other remote source using a coaxial cable, fiber optic cable, twisted pair, digital subscriber line (DSL), or wireless technologies such as infrared, radio, and microwaves, the coaxial cable, fiber optic cable, twisted pair, DSL, or wireless technologies such as infrared, radio, and microwaves are included in the definition of the medium. Disk and disc as used herein include compact disc (CD), laser disc, optical disc, digital versatile disc (DVD), floppy disk and Blu-ray disc, wherein disk often reproduces data magnetically, while disc reproduces data optically with lasers. Combinations of the above should also be included within the scope of computer-readable media.

[0083] Although the present invention is disclosed as above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. A thermal management method for an aircraft engine, wherein the aircraft engine comprises multiple heat sinks, characterized in that: The thermal management method comprises: S1. Receive input parameters, the input parameters include: Engine operating parameters; Rated parameters of the power source of the heat sink, including the rated speed and rated power of the power source corresponding to each heat sink of the multiple heat sinks; Temperature parameters, including heat sink temperature at the heat sink inlet corresponding to each heat sink; Radiator parameters, heat dissipation efficiency of each radiator corresponding to the heat sink; The heat generated by the engine's heat generating components and the oil flow rate; S2. Perform energy efficiency optimization calculation according to the input parameters, the optimization target is the power source speed corresponding to each heat sink of the multiple heat sinks, and the boundary conditions include: Temperature limit, the lubricating oil temperature and each heat sink temperature do not exceed the temperature threshold; The fuel flow rate must meet the engine's operating requirements; Speed ​​range: 0%~100% rated speed. When the speed is 0, it means that the heat sink does not participate in heat exchange. S3. Output control parameters, including: The power source rotation speed of the plurality of heat sinks is optimized.

2. The thermal management method according to claim 1, characterized in that: In said S1: The engine operating parameters at least include: the altitude, Mach number, and temperature difference of the aircraft where the engine is located. The rated parameters of the heat sink power source at least include: the rated speed of the fan, the rated power of the fan, the rated speed of the fuel pump, and the rated power of the fuel pump; The temperature parameters at least include: the fuel temperature at the inlet of the main fuel and lubricating oil radiator, and the air temperature at the inlet of the air and lubricating oil radiator; The radiator parameters at least include: the heat dissipation efficiency of the main fuel oil radiator and the heat dissipation efficiency of the air oil radiator.

3. The thermal management method according to claim 1, characterized in that: In S2, the energy efficiency optimization calculation includes: According to the inlet temperatures of the multiple heat sinks input in S1, the lubricating oil flow rate, the heat generated by the engine heating components, the heat exchange efficiency of the radiator and other parameters, the flow rate of each heat sink, the lubricating oil and the outlet temperature of each heat sink of the multiple heat sinks are obtained by establishing a system thermal network model.

4. The thermal management method according to claim 1, characterized in that: In S2, the energy efficiency optimization calculation algorithm includes an evolutionary algorithm, a swarm intelligence algorithm, a simulated annealing algorithm, and a neural network algorithm.

5. The thermal management method according to claim 1, characterized in that: In S2, the energy efficiency optimization calculation algorithm includes a machine learning algorithm.

6. A readable medium having a computer program thereon, characterized in that The program is executed by a processor to implement the steps of the thermal management method according to any one of claims 1 to 5.

7. A thermal management system (200) for an aircraft engine, characterized in that: include: A memory (201) for storing instructions executable by a processor; A processor (202) is used to execute the instructions to implement the thermal management method according to any one of claims 1 to 5.

8. The thermal management system (200) according to claim 7, characterized in that: It also includes a display module (203) for displaying the energy efficiency optimization status of the thermal management system.

9. The thermal management system (200) according to claim 7, characterized in that: The processor (202) is integrated into a Full Authority Digital Engine Control (FADEC).

10. An aircraft engine, characterized in that: The thermal management system (200) comprises a plurality of heat sinks and the thermal management system (200) according to any one of claims 7 to 9.

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