Multi-condition thermal management test system applied to aero-engine

Abstract

The application discloses a multi-working-condition thermal management test system applied to an aero-engine and relates to the technical field of engine test.The test system comprises a thrust detection module, wherein the thrust detection module detects the thrust data generated by the aero-engine during operation.The cooling simulation module compares the difference data under the conditions of no acceleration and dynamic acceleration, the load adjustment module and the inertia compensation algorithm adjust the load and the lag time of the cooling medium flow in real time through the difference data, the load adjustment module controls the load adjustment module according to the difference data, and the inertia compensation algorithm adjusts the reaction time of the equipment in the cooling device based on the difference parameters.Through the real-time adjustment of the load and the lag time of the cooling medium flow, the influence of inertia on the cooling device is simulated, so that the obtained test data can adapt to the thermal management requirements under different working conditions, and the evaluation accuracy of the system performance is ensured.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of engine testing, in particular to a multi-working-condition thermal management test system applied to an aero-engine. BACKGROUND

[0002] By simulating the thermal load of the aero-engine under different working conditions, the performance of the thermal management system in terms of heat dissipation, heating and temperature control is evaluated, the stability and reliability of the thermal management system under different working conditions are tested, and it is ensured that the engine can safely and efficiently operate under various conditions. According to the test results, the control strategy of the thermal management system is optimized, and the heat dissipation capacity and working efficiency of the system are improved.

[0003] For example, patent publication No. "CN118310753A" entitled "Aero-engine thermal management semi-physical test system" includes a monitoring interface, a simulation machine, a data transmission network and a physical entity. The simulation machine and the physical entity are connected through the data transmission network. The simulation machine includes an engine thermal management simulation model and a controller connected thereto. The physical entity includes a working medium supply simulation device and a heat exchanger. The above-mentioned application realizes the digital transformation of the aero-engine thermal management system, can reduce the risk and cost of aero-engine thermal management test, shorten the development time, and provide a test basis for researching the aero-engine thermal management system.

[0004] The above-mentioned application needs to fix the position of the aero-engine when performing thermal management test on the aero-engine, and the fixed aero-engine is tested. However, in actual flight, the speed change of the aero-engine will affect the change of the external airflow data of the engine, and the speed change of the engine will cause the engine to be affected by the acceleration change. When the engine is affected by the acceleration change, the liquid cooling medium in the cooling device inside the engine is affected by inertia, which will affect the operation of the cooling device. However, in the test, since the aero-engine is fixed, the influence of inertia on the cooling device is not convenient to realize. Therefore, a multi-working-condition thermal management test system applied to an aero-engine is invented. SUMMARY

[0005] The purpose of the present application is to provide a multi-working-condition thermal management test system applied to an aero-engine to solve the problems raised in the background art.

[0006] To achieve the above-mentioned purpose, the present application provides the following technical solution: a multi-working-condition thermal management test system applied to an aero-engine, the test system comprising:

[0007] The thrust detection module detects the thrust data generated by the aero-engine during operation.

[0008] The input module is used to control and detect the operating parameters of the aero-engine.

[0009] The external simulation module simulates the external data of the aero-engine, and the external data includes test airflow data, and the test airflow data includes natural airflow and relative airflow data.

[0010] The information processing module establishes a first correlation between the relative airflow data, the speed of the aero-engine, and the airflow resistance by a correlation method, and the external simulation module adjusts the airflow data in the external simulation module based on the relative airflow data.

[0011] The flight simulation module obtains acceleration change data by a flight simulation method.

[0012] The cooling simulation module establishes a cooling device model in the computer, and the cooling device model performs cooling simulation under no acceleration change to obtain basic operating parameters, and the cooling device model performs cooling simulation in combination with the acceleration change data to obtain simulation operating parameters of the cooling device model in the acceleration change simulation, and difference data between the basic operating parameters and the simulation operating parameters is obtained by a comparison method, an inertia compensation algorithm is established, and the inertia compensation algorithm obtains an adjustment of a lag time of the cooling device based on the difference parameters.

[0013] The load adjustment module is installed in the cooling device, and the load adjustment module is controlled by a simulation algorithm and the difference data to adjust the flow load of the cooling medium in the cooling device, and the reaction time of the equipment in the cooling device is adjusted by the lag time.

[0014] The total control module realizes the test under different working conditions by a total control method.

[0015] The data monitoring and acquisition module acquires the internal and external temperature data of the aero-engine and the cooling parameter data of the cooling device in the test.

[0016] Further, the flight simulation method includes: a virtual model of the aircraft is established by a computer to obtain a virtual aircraft, the thrust data is input into the virtual aircraft to realize the operation of the virtual aircraft, the speed data of the virtual aircraft is acquired, and a dynamic balance between the relative airflow data and the thrust data is adjusted by a balance adjustment method, and the acceleration change data is acquired based on the movement data.

[0017] Further, the cooling simulation module includes:

[0018] A virtual model of the cooling device is established by computer modeling technology, and the virtual model can simulate the equipment in the cooling device.

[0019] In the virtual model, the cooling device is simulated by the acceleration change data to simulate the dynamic changes of the aircraft in different flight stages and acceleration conditions in actual flight;

[0020] The cooling medium flow in the cooling device is simulated by the acceleration change data, and the inertial influence in the cooling medium is analyzed, including the flow speed, pressure distribution and flow load of the cooling medium.

[0021] Further, the correlation method comprises obtaining a second correlation between the relative airflow data in the external data and the virtual aircraft speed, obtaining a third correlation between the airflow resistance and the aircraft engine speed, and combining the second correlation data and the third correlation data to obtain a first correlation between the relative airflow data, the aircraft engine speed data and the resistance.

[0022] Further, the simulation algorithm comprises: obtaining a load adjustment strategy according to the difference data, and the load adjustment strategy is applied to adjust the load parameters in the load adjustment module.

[0023] The method for obtaining the load adjustment strategy comprises: the simulation algorithm adjusts the internal parameters of the load adjustment module according to the difference data, simulates the change of the parameters of the load adjustment module, realizes that the running state of the cooling device under no inertia is equal to the running state of the cooling device under corresponding inertia, records the changed parameters in the load adjustment module, and obtains the load adjustment strategy.

[0024] Further, the total control method comprises: controlling the input parameters in the input module, simulating the speed data of the virtual aircraft in different working conditions, obtaining the relative airflow data in combination with the first correlation, adjusting the devices inside the external simulation module based on the relative airflow data, adjusting the lag time of the cooling device and the load adjustment module according to the difference data, and the data monitoring and acquisition module real-time acquires the internal and external temperature data of the aircraft engine and the cooling parameter data of the cooling device in the test.

[0025] Further, the inertia compensation algorithm comprises: quantifying the lagging influence of the acceleration change data on the cooling medium flow by a second-order differential equation to obtain the lag time.

[0026] The reaction time of the equipment in the cooling device is adjusted by the lag time, the cooling device model and the lag time are used to simulate the running state of the cooling device in actual working conditions, and the reaction time of the equipment in the cooling device is measured.

[0027] Further, the comparison method comprises:

[0028] According to the application scene of the cooling device and the demand of load adjustment, the comparison index is selected, and the comparison index comprises the flow load difference, temperature change difference and pressure change difference of the cooling medium.

[0029] Point-by-point comparison: compare the base operating parameters and simulation operating parameters point by point according to the time points, analyze the difference of the comparison index at each time point under each working condition;

[0030] Trend analysis: analyze the overall change trend of the comparison index in the base operating parameters and simulation operating parameters;

[0031] Difference degree evaluation: calculate and obtain the difference data between the base operating parameters and the simulation operating parameters according to the difference and the overall change trend.

[0032] Compared with the prior art, the beneficial effects of the present application are:

[0033] The multi-working-condition thermal management test system applied to the aero-engine, the cooling simulation module compares the difference data under the conditions of no acceleration and dynamic acceleration, the load adjustment module and the inertia compensation algorithm adjust the load and the lag time of the cooling medium flow in real time through the difference data, the load adjustment module controls the load adjustment module according to the difference data, and the inertia compensation algorithm adjusts the reaction time of the equipment in the cooling device based on the difference parameters. By adjusting the load and the lag time of the cooling medium flow in real time, the influence of inertia on the cooling device is simulated, so that the test data obtained can adapt to the thermal management demand under different working conditions, and the evaluation accuracy of the system performance is ensured.

[0034] At the same time, the external simulation module combines natural airflow and relative airflow data for simulation, dynamically simulates operation under different flight conditions, simulates the influence of airflow on the aero-engine under complex real working conditions, and automatically adjusts the dynamic balance of thrust and airflow data based on the virtual aircraft model of the flight simulation module and the balance adjustment method, and real-time association of actual thrust data and acceleration change of the virtual aircraft, significantly improves the accuracy of matching between engine thrust output and flight state.

[0035] The external simulation module combines natural airflow and relative airflow data for comprehensive simulation, which can dynamically reproduce the operating environment of the aero-engine under different flight conditions. Such simulation not only improves the accuracy of the test, but also helps to deeply understand the thermal load of the aero-engine under different airflow environments in actual flight, and then the internal and external temperature data and cooling parameter data can be obtained for subsequent optimization of the thermal management system control strategy. BRIEF DESCRIPTION OF DRAWINGS

[0036] Figure 1 Schematic diagram for calculating the inertia influence of the present application;

[0037] Figure 2 Schematic diagram for adjusting the cooling device in the test of the present application;

[0038] Figure 3 Figure 1 is a schematic diagram of the test system of the present application. DETAILED DESCRIPTION

[0039] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by a person of ordinary skill in the art without creative work fall within the protection scope of the present application.

[0040] As shown in Figure 1 - Figure 3 The present application provides a technical solution: a multi-working-condition thermal management test system applied to an aero-engine, the test system comprising:

[0041] a thrust detection module: the thrust detection module detects the thrust data generated by the aero-engine in operation;

[0042] an input module: the input module is used for controlling and detecting the operation parameters of the aero-engine;

[0043] an external simulation module: the external simulation module simulates the external data of the aero-engine, the external data comprising test airflow data, the test airflow data comprising natural airflow and relative airflow data;

[0044] an information processing module: a first correlation between the relative airflow data, the speed of the aero-engine and the airflow resistance is established by a correlation method, and the external simulation module adjusts the airflow data in the external simulation module based on the relative airflow data;

[0045] a flight simulation module: acceleration change data is obtained by a flight simulation method;

[0046] a cooling simulation module: a cooling device model is established in a computer, the cooling device model performs cooling simulation under no acceleration change to obtain basic operation parameters, the cooling device model performs cooling simulation in combination with the acceleration change data to obtain simulation operation parameters of the cooling device model in acceleration change simulation, difference data between the basic operation parameters and the simulation operation parameters is obtained by a comparison method, an inertia compensation algorithm is established, and the inertia compensation algorithm obtains adjustment of the hysteresis time of the cooling device based on the difference parameters;

[0047] a load adjustment module: the load adjustment module is installed in the cooling device, the load adjustment module is controlled by a simulation algorithm and the difference data to adjust the flow load of the cooling medium in the cooling device, and the reaction time of the equipment in the cooling device is adjusted by the hysteresis time;

[0048] a total control module: the test under different working conditions is realized by a total control method;

[0049] Data monitoring and acquisition module: acquire the internal and external temperature data of the aero-engine in the test and the cooling parameter data of the cooling device.

[0050] The simulation aircraft method comprises: establishing a virtual model of the aircraft by computer to obtain a virtual aircraft, inputting the thrust data into the virtual aircraft to realize the operation of the virtual aircraft, acquiring the speed data of the virtual aircraft, and adjusting the dynamic balance between the relative airflow data and the thrust data by the balance adjustment method, and acquiring the acceleration change data based on the movement data.

[0051] The cooling simulation module comprises:

[0052] The virtual model of the cooling device is established by computer modeling technology, and the virtual model can simulate the equipment in the cooling device;

[0053] In the virtual model, the cooling device is simulated by the acceleration change data to simulate the dynamic changes of the aircraft in different flight stages and acceleration conditions in actual flight;

[0054] The flow of the cooling medium in the cooling device is simulated by the acceleration change data, and the inertial influence in the cooling medium is analyzed, including the flow speed, pressure distribution and flow load of the cooling medium.

[0055] The correlation method comprises: acquiring a second correlation between the relative airflow data in the external data and the speed of the virtual aircraft, acquiring a third correlation between the airflow resistance and the speed of the aero-engine, and combining the second correlation data and the third correlation data to acquire a first correlation between the relative airflow data, the speed data of the aero-engine and the resistance.

[0056] The simulation algorithm comprises: simulating the load adjustment strategy according to the difference data, and the load adjustment strategy is applied to adjust the load parameters in the load adjustment module;

[0057] The method for obtaining the load adjustment strategy comprises: the simulation algorithm adjusts the internal parameters of the load adjustment module according to the difference data, simulates the change of the parameters of the load adjustment module, realizes that the running state of the cooling device under no inertia is equal to the running state of the cooling device under corresponding inertia, records the changed parameters in the load adjustment module, and obtains the load adjustment strategy.

[0058] The total control method comprises: controlling the input parameters in the input module, simulating the speed data of the virtual aircraft in different working conditions, acquiring the relative airflow data in combination with the first correlation, adjusting the devices inside the external simulation module based on the relative airflow data by the external simulation module, adjusting the lag time of the cooling device and the load adjustment module according to the difference data by the cooling device, and acquiring the internal and external temperature data of the aero-engine in the test and the cooling parameter data of the cooling device by the data monitoring and acquisition module.

[0059] The inertia compensation algorithm comprises: quantifying the hysteresis effect of the acceleration change data on the cooling medium flow through a second-order differential equation to obtain a hysteresis time;

[0060] The reaction time of the equipment in the cooling device is adjusted through the hysteresis time, the cooling device model and the hysteresis time are used to simulate the operation of the cooling device under actual working conditions, and the reaction time of the equipment in the cooling device is measured.

[0061] The comparison method comprises:

[0062] The comparison index is selected according to the application scene and the load adjustment requirement of the cooling device, and the comparison index comprises a flow load difference, a temperature change difference and a pressure change difference of the cooling medium;

[0063] Point-by-point comparison: the basic operation parameters and the simulation operation parameters are compared point by point according to time points, and the difference of the comparison index at each time point under each working condition is analyzed;

[0064] Trend analysis: the overall change trend of the comparison index in the basic operation parameters and the simulation operation parameters is analyzed;

[0065] Difference degree evaluation: the difference data between the basic operation parameters and the simulation operation parameters are calculated and obtained according to the difference and the overall change trend.

[0066] When the thermal management test of the aero-engine under multiple working conditions is carried out, the aero-engine needs to be fixed in position, and the thrust detection module detects the thrust data generated by the aero-engine under different working conditions while fixing the position of the aero-engine. By detecting the thrust generated by the aero-engine during operation, the thrust data is obtained, which is substituted into the simulation aircraft to obtain the acceleration change data of the simulation aircraft under different working conditions based on the thrust data.

[0067] The multiple working conditions of the engine refer to the processes of taking off, climbing and landing, and the specific content of the multiple working conditions is the prior art. During the processes, the engine will have acceleration change, and the process of acceleration change includes acceleration, deceleration and change of moving direction. Inertia refers to the property of an object to maintain a state of rest or uniform linear motion. During the process of acceleration change, the inertia of the engine will affect the thermal management.

[0068] The external simulation module is the basic part of the system, and its main function is to simulate the airflow and temperature conditions of the aero-engine in the actual environment. By controlling the airflow speed, direction and temperature parameters, the working environment of the aero-engine under different flight altitudes, speeds and weather conditions can be simulated, which helps to more realistically reflect the thermal load of the aero-engine in the actual flight process, and provides accurate environmental basis for subsequent thermal management performance testing. At the same time, considering that the position of the aero-engine is fixed in the test, but in actual situation, the aero-engine is in a moving state, therefore, when controlling the airflow speed, the relative airflow data of the aero-engine relative to the external airflow in the test needs to be considered, and the influence on the virtual aircraft is simulated through the aero-engine thrust data, so as to obtain the moving data of the aircraft. Based on the moving data of the aircraft, the relative airflow data is obtained, and the natural airflow refers to the airflow condition in the natural environment. When used, a natural airflow environment can be designed to simulate the thermal management test under different working conditions and different natural airflow environments. The test airflow data includes natural airflow and relative airflow data. The relative airflow data is controlled by the speed of the simulated aircraft, and the natural airflow refers to the natural airflow condition in the external environment.

[0069] Through the relative airflow data and the moving data, the moving data is corrected to obtain the theoretical moving data. The relative airflow data will affect the moving data of the virtual aircraft, and the moving data will also affect the relative airflow data. The two influence each other to obtain the second correlation between the relative airflow data in the external data and the speed of the virtual aircraft. There will also be airflow resistance in the moving process, and the third correlation between the airflow resistance and the speed of the aero-engine is obtained. The second correlation and the third correlation are combined to obtain the first correlation between the relative airflow data, the speed data of the aero-engine and the resistance. The moving data is combined with time to obtain acceleration change data. The system records data at the same time, and also records the corresponding time.

[0070] The acceleration change data acts on the cooling device, which will affect the cooling medium in the cooling device. Since the position of the aero-engine is fixed in the test, there is no inertia in the test, which will not affect the cooling device. However, in actual situation, the existence of inertia will affect the cooling device. Acceleration change can affect the flow state of cooling medium. In the cooling system, the flow characteristics of cooling medium are crucial to heat transfer effect. When acceleration changes, the flow rate, flow direction and flow state of cooling medium may change, thereby affecting its heat transfer performance. Therefore, the influence of acceleration change on the cooling device needs to be simulated in the test. The influence of acceleration change on the cooling device and thermal management in actual situation is simulated. The cooling device cools the key parts in the engine.

[0071] The input module is responsible for controlling the operating parameters of the aero-engine under different working conditions, so as to simulate the input parameters under different working conditions. By controlling the key parameters such as fuel supply, intake pressure and rotating speed of the aero-engine, the working state of the aero-engine under different working conditions such as take-off, climbing, cruising, descending and landing can be simulated.

[0072] The operation method of the test system comprises: controlling the aero-engine by the input module to start the aero-engine, controlling the operating parameters by the input module to start the aero-engine, the aero-engine generating thrust during the starting process, detecting the thrust data by the thrust detection module, and simulating the flight of the virtual aircraft based on the thrust data. Meanwhile, the natural airflow is designed in advance during the simulation, and the relative airflow data is obtained based on the moving speed and the simulated height of the virtual aircraft during the movement of the virtual aircraft. The test airflow data is obtained by combining the relative airflow data and the natural airflow. The external simulation module adjusts the external airflow data of the aero-engine in the test by the test airflow data, and the correlation test under different natural airflows is realized by designing different natural airflows.

[0073] The cooling device comprises an oil system in the aero-engine. The oil system transmits the absorbed heat to the cooling device such as an oil radiator outside the engine through circulation, and then the cooled oil is sent back to the inside of the engine after heat dissipation, so as to maintain the temperature of each component in the engine within a proper range and ensure the stability of the engine performance. The oil system is used for assisting the engine in heat dissipation in the thermal management. The thermal management test system comprehensively detects the thermal response capability and performance of the cooling device of the aero-engine, which can provide an important basis for the thermal management design of the aero-engine, optimize the structure and parameter setting of the thermal management system, and improve the overall performance of the engine.

[0074] Due to the inertia in actual flight, the liquid cooling medium in the cooling device is affected by inertia during the acceleration change in the actual flight process, and the cooling effect of the cooling device is affected due to the influence of inertia on the liquid cooling medium in the cooling device. The thrust data generated by the aero-engine under different working conditions and the operating parameters of the aero-engine under different working conditions are obtained. The movement data is obtained by acting the thrust data and the test airflow data on the virtual aircraft, and the acceleration data of the virtual aircraft is obtained by combining the actual movement data.

[0075] The comparison method comprises point-by-point comparison, trend analysis and difference evaluation method, and comprehensively analyzes the difference data in the cooling system, including flow load and pressure, to provide a scientific basis for the load adjustment strategy. Through analyzing the difference data, the internal pressure and flow load of the cooling medium in the cooling device are adjusted to approach the data in the simulation operation parameters. The load adjustment module operates according to the load adjustment strategy, and the cooling device adjusts the reaction time of the equipment in the cooling device through the lag time. The load adjustment module adjusts the flow load of the cooling medium in the cooling device and adjusts the reaction time of the equipment in the cooling device to simulate the operation of the cooling device under the existence of inertia. Based on the simulated operation of the cooling device under the existence of inertia, the corresponding thermal management data in the test is obtained, and the data about the cooling device can be more consistent with the operation of the cooling device in actual flight, which provides effective support for the use of subsequent test data and the optimization of the thermal management system.

[0076] For the cooling device in thermal management, inertia will affect the cooling medium of the cooling device. Since the cooling medium itself has inertia, especially liquid cooling medium, the liquid cooling medium will affect the operation of the cooling device due to inertia in the acceleration stage. The flow rate and pressure distribution change of the liquid cooling medium will directly affect the heat transfer coefficient. In the acceleration stage, due to the uneven distribution of flow rate and pressure, the heat transfer coefficient may change, thereby affecting the cooling efficiency. Due to the inertia of the liquid, the cooling medium may have a delay when the corresponding temperature changes. This delay will cause the cooling device to have a performance decline when responding to sudden heat load. Therefore, inertia will affect the thermal management performance of the cooling device, especially the cooling device using liquid cooling medium. Since the mass of the liquid cooling medium is larger, its inertia is also larger. The liquid cooling medium needs to transfer and convert energy when the corresponding temperature changes. Due to the effect of inertia, this energy transfer and conversion process will not be completed immediately, but will take a certain time, which leads to a delay in the response of the cooling liquid to temperature changes. When the cooling liquid needs to change the flow rate to respond to temperature changes, the change of the flow rate will not occur immediately due to the effect of inertia. This delay in flow rate change will further affect the temperature response speed of the cooling liquid. Due to the effect of inertia, the temperature response of the cooling liquid is delayed, resulting in reduced heat dissipation efficiency.

[0077] By moving data combined with time, the acceleration change data under different working conditions is obtained, and the acceleration change is applied to the cooling simulation module to simulate without inertia and with inertia. Since it is computer simulation, both simulations can be realized by adjusting the parameters in the computer. The simulation without inertia corresponds to the operation of the internal cooling device of the aero-engine in the test. Since the position of the aero-engine is fixed during the test, the inertia has no effect on the cooling device. The cooling device model combined with the acceleration change data performs cooling simulation corresponding to the operation of the internal cooling device of the aero-engine in the actual situation. In the running process, the inertia has an effect on the cooling device. By comparing the difference between the basic operation parameters and the simulation operation parameters, the difference data is obtained. Based on the difference data, the operation of the cooling device in the test is simulated to the operation of the cooling device in the actual situation. Through the load adjustment module, the flow load of the cooling medium in the cooling device is adjusted, and the reaction time of the equipment in the cooling device is adjusted. In this way, the cooling device can simulate the operation under the actual situation and with the inertia effect in the test. Through the external simulation module combined with natural airflow and relative airflow data, different flight conditions are simulated dynamically. The influence of airflow on the aero-engine under complex real working conditions is simulated. Based on the virtual aircraft model of the flight simulation module and the balance adjustment method, the actual thrust data is associated with the acceleration change of the virtual aircraft in real time, and the dynamic balance of the thrust and airflow data is automatically adjusted, which significantly improves the accuracy of the engine thrust output and flight state matching.

[0078] The hysteresis effect of the cooling medium flow can be regarded as the second-order dynamic response of the acceleration change. When the cooling medium (such as liquid lubricating oil) changes in acceleration, the inertia effect will cause dynamic hysteresis of flow velocity, pressure distribution and flow load. When the aircraft accelerates, the liquid medium tends to maintain the original state due to inertia, causing flow rate adjustment delay, which affects the heat dissipation efficiency. The second-order differential equation is used to describe the dynamic influence of inertia on the cooling medium. The equation form can be: Wherein, m represents the equivalent inertial mass of the cooling medium, c is the damping coefficient (reflecting the flow resistance), k is the stiffness coefficient (reflecting the medium elasticity), F(t) is the dynamic force caused by acceleration change, x is the displacement of the cooling medium, by solving the equation, the hysteresis response of the cooling medium flow rate, pressure and other parameters can be quantified, the time domain response of the flow rate is obtained, and the hysteresis time t is extracted, the hysteresis time R represents the adjustment ability of the cooling device to acceleration change, which is inversely proportional to the hysteresis time t, and the reaction time refers to the time difference from receiving the control signal to the actual action of the actuator (such as valve, pump) in the cooling device, the inertia effect will prolong this time, resulting in control delay, the cooling device model and the hysteresis time are simulated to simulate the running of the cooling device under actual working conditions, and the reaction time of the equipment in the cooling device is measured, the cooling simulation module compares the difference data under the conditions of no acceleration and dynamic acceleration, the load adjustment module and the inertia compensation algorithm adjust the load and hysteresis time of the cooling medium flow in real time according to the difference data, the load adjustment module controls the load adjustment module according to the difference data, and the inertia compensation algorithm adjusts the reaction time of the equipment in the cooling device based on the difference parameters. By adjusting the load and hysteresis time of the cooling medium flow in real time, the influence of inertia on the cooling device is simulated, so that the test data obtained can adapt to the thermal management demand under different working conditions, and the accuracy of system performance evaluation is ensured.

[0079] The test airflow data is considered to be a combination of natural airflow and relative airflow data, and under different working conditions, the natural airflow and engine movement data do not change, the relative airflow data is affected by the movement data, and the test airflow data will affect the thrust data. Therefore, the test airflow data and speed data are combined and simulated by a virtual aircraft to obtain movement data.

[0080] The dynamic balance between the relative airflow data and the thrust data is adjusted by the balance adjustment method. When the engine operates to generate thrust, the thrust data is input to the virtual aircraft, so that the virtual aircraft starts to move. When the virtual aircraft starts to move, the relative airflow data changes from zero. When the virtual aircraft is stationary, the relative airflow data is zero, which means that there is no relative airflow data at this time. The change of the relative airflow data will affect the virtual aircraft. At this time, in order to ensure the smooth operation of the virtual aircraft, the thrust data will be adjusted to ensure the speed of the virtual aircraft. The size of the speed will affect the relative airflow data, and the thrust data will affect the size of the speed. Therefore, the dynamic balance between the relative airflow data and the thrust data is realized in the process of mutual influence. The thrust data is controlled by the operating parameters of the aero-engine. Through the dynamic balance between the two, the operation of the virtual aircraft is realized.

[0081] The cooling parameter data includes the heat absorption data after cooling, the cycle number and the temperature change of the cooling medium. The internal and external temperature data of the engine under different working conditions can provide an important basis for the thermal management design of the aero-engine, help engineers identify potential thermal management problems, optimize the structure and parameter settings of the thermal management system, and improve the overall performance of the engine. The internal and external temperature data of the engine under different working conditions includes each system inside the engine, which includes the cooling system, lubrication system, thermal protection system and other thermal management related components of the aero-engine. After obtaining the internal and external temperature data, the internal and external temperature data can be divided according to the system or component for subsequent processing. According to the test results, the control strategy of the thermal management system is optimized to improve the heat dissipation capacity and working efficiency of the system. Through the adaptive control technology, the thermal management system can automatically adjust the working mode according to different flight conditions and select the best thermal management path. The external simulation module combines natural airflow and relative airflow data for comprehensive simulation, which can dynamically reproduce the operating environment of the aero-engine under different flight conditions. This simulation not only improves the accuracy of the test, but also helps to better understand the thermal load of the aero-engine under different airflow environments in actual flight, and further enables the internal and external temperature data and cooling parameter data to be obtained for subsequent optimization of the control strategy of the thermal management system.

[0082] Although embodiments of the present application have been shown and described, it is to be understood that various modifications, substitutions, replacements and changes can be made to these embodiments without departing from the principles and spirit of the present application, and the scope of the present application is defined by the appended embodiments and their equivalents.

Claims

1. A multi-condition thermal management test system applied to an aero-engine, characterized in that, The test system comprises: a thrust detection module: the thrust detection module detects the thrust data generated by the aero-engine during operation; an input module: the input module is used for controlling and detecting the operating parameters of the aero-engine; an external simulation module: the external simulation module simulates external data of the aero-engine, and the external data comprises test airflow data, and the test airflow data comprises natural airflow and relative airflow data; an information processing module: a first correlation between the relative airflow data, the speed of the aero-engine and the airflow resistance is established through a correlation method, and the external simulation module adjusts the airflow data in the external simulation module based on the relative airflow data; a flight simulation module: acceleration change data is obtained through a flight simulation method; a cooling simulation module: a cooling device model is established in the computer, the cooling device model is simulated under no acceleration change to obtain basic operating parameters, and the cooling device model is simulated in combination with the acceleration change data to obtain simulation operating parameters of the cooling device model in the acceleration change simulation, difference data between the basic operating parameters and the simulation operating parameters is obtained through a comparison method, an inertia compensation algorithm is established, and the inertia compensation algorithm is used to obtain a lag time for adjusting the cooling device based on the difference parameters; a load adjustment module: the load adjustment module is installed in the cooling device, and the load adjustment module is controlled through a simulation algorithm and the difference data to adjust the flow load of the cooling medium in the cooling device, and the reaction time of the equipment in the cooling device is adjusted through the lag time; a total control module: the test under different working conditions is realized through a total control method; a data monitoring and acquisition module: internal and external temperature data of the aero-engine and cooling parameter data of the cooling device in the test are acquired.

2. The multi-condition thermal management test system for aero-engines according to claim 1, characterized in that: The flight simulation method comprises the following steps: a virtual model of the aircraft is established through the computer to obtain a virtual aircraft, the thrust data is input into the virtual aircraft to realize the operation of the virtual aircraft, the speed data of the virtual aircraft is acquired, the dynamic balance between the relative airflow data and the thrust data is adjusted through a balance adjustment method, and the acceleration change data is acquired based on the movement data.

3. The multi-condition thermal management test system for aero-engines according to claim 1, characterized in that: The cooling simulation module comprises: a virtual model of the cooling device is established through computer modeling technology, and the virtual model can simulate the equipment in the cooling device; the cooling device is simulated in the virtual model through the acceleration change data to simulate the dynamic change of the aircraft under different flight stages and acceleration conditions in actual flight; the flow of the cooling medium in the cooling device is simulated through the acceleration change data, and the inertia influence of the cooling medium is analyzed, and the inertia influence comprises the flow speed, pressure distribution and flow load of the cooling medium.

4. The multi-condition thermal management test system for aero-engines according to claim 1, characterized in that: The correlation method comprises the following steps: a second correlation between the relative airflow data in the external data and the speed of the virtual aircraft is acquired, a third correlation between the airflow resistance and the speed of the aero-engine is acquired, and a first correlation between the relative airflow data, the speed data of the aero-engine and the resistance is acquired in combination with the second correlation data and the third correlation data.

5. The multi-condition thermal management test system for aero-engines according to claim 1, characterized in that: The simulation algorithm comprises the following steps: a load adjustment strategy is simulated according to the difference data, and the load adjustment strategy is applied to adjust the load parameters in the load adjustment module. The method for obtaining the load adjustment strategy comprises: adjusting internal parameters of the load adjustment module according to the difference data by the simulation algorithm, changing the parameters of the load adjustment module under simulation control, realizing that the running state of the cooling device under no inertia is equal to the running state of the cooling device under corresponding inertia, recording the changed parameters in the load adjustment module, and obtaining the load adjustment strategy.

6. The multi-condition thermal management test system for aero-engines according to claim 4, characterized in that: The total control method comprises: controlling input parameters in the input module, simulating speed data of the virtual aircraft in flight under different working conditions, obtaining relative airflow data in combination with the first correlation, adjusting devices inside the external simulation module based on the relative airflow data, adjusting the lag time of the cooling device and the load adjustment module according to the difference data, and real-time obtaining of the internal and external temperature data of the aero-engine and the cooling parameter data of the cooling device in the test by the data monitoring and obtaining module.

7. The multi-condition thermal management test system for aero-engines according to claim 1, characterized in that: The inertia compensation algorithm comprises: quantifying the lagging influence of acceleration change data on the flow of the cooling medium through a second-order differential equation, and obtaining the lag time; The reaction time of the equipment in the cooling device is adjusted through the lag time, the cooling device model and the lag time are used to simulate the running state of the cooling device under actual working conditions, and the reaction time of the equipment in the cooling device is measured.

8. The multi-condition thermal management test system for aero-engines according to claim 1, characterized in that: The comparison method comprises: According to the application scene of the cooling device and the demand of load adjustment, a comparison index is selected, the comparison index comprises flow load difference, temperature change difference and pressure change difference of the cooling medium; Point-by-point comparison: the basic running parameters and the simulation running parameters are compared point by point according to the time points, the difference of the comparison index in each time point under each working condition is analyzed; Trend analysis: the overall change trend of the comparison index in the basic running parameters and the simulation running parameters is analyzed; Difference degree evaluation: the difference data between the basic running parameters and the simulation running parameters is calculated and obtained according to the difference and the overall change trend.

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