Method and apparatus for design evaluation of an aeroengine fuel and lubricating oil system

Abstract

The application relates to a method and device for evaluating the design of an aero-engine fuel system and an oil system. The method comprises the following steps: obtaining system design parameters, system operation data and system coupling logic information of each system associated with the fuel system and the oil system, and operation associated information of the aero-engine, and constructing system simulation models of each system; then performing model association processing on the system simulation models to obtain a fuel-oil simulation model, simulating the operation process of the fuel system and the oil system through the fuel-oil simulation model, obtaining simulation operation results, identifying abnormal information between the fuel system and the oil system through a performance evaluation strategy, comprehensively evaluating the fuel system and the oil system to obtain evaluation results. The method can improve the comprehensiveness and accuracy of the evaluation of the fuel system and the oil system.

Description

Technical Field

[0001] This application relates to the field of data generation technology, and in particular to a design evaluation method and apparatus for an aircraft engine fuel system and lubrication system. Background Technology

[0002] With the rapid development of the aero-engine industry, aero-engine simulation technology has been widely applied in design optimization and troubleshooting processes. However, joint simulation between related systems is insufficient. Fuel and lubricating oil systems, as complex hydraulic systems with varying flow rates, loads, and temperatures, exchange heat through fuel / lubricating oil radiators. Currently, heat exchange between the fuel and lubricating oil systems is only estimated based on rated values ​​or empirical data. With the advancement of aero-engine technology, especially the advent of variable-cycle engines, the temperature of fuel and lubricating oil systems is gradually increasing, approaching the limits for normal operation under certain conditions. Therefore, it is necessary to conduct design evaluations of fuel and lubricating oil systems under different operating conditions to assist engineers in optimizing and improving these systems.

[0003] Traditional design evaluation methods for fuel and lubricating oil systems involve manual design evaluation. During the evaluation, the analysis and research are carried out on a single system basis, and only boundary conditions are set for related systems. A model is built to analyze and evaluate the fuel and lubricating oil system. However, a single system has poor perception of changes in engine status, resulting in poor accuracy in the evaluation of the fuel and lubricating oil system. Summary of the Invention

[0004] Therefore, it is necessary to provide a design evaluation method, apparatus, computer equipment, computer-readable storage medium, and computer program product for aircraft engine fuel systems and lubrication systems to address the aforementioned technical problems.

[0005] In a first aspect, this application provides a design evaluation method for an aircraft engine fuel system and lubrication system, including:

[0006] The system design parameters of each system associated with the fuel system and lubricating oil system, the system operation data of each system, the system coupling logic information between each system, and the operation association information of the aero-engine are obtained. Based on the system design parameters of each system and the system operation data of each system, a system simulation model of each system is constructed.

[0007] Based on the system coupling logic information between the systems, the simulation models of the systems are processed by model association to obtain the fuel and lubricating oil simulation model. Based on the operation association information of the aero-engine, the system simulation strategy of the fuel and lubricating oil simulation model is generated.

[0008] Based on the system simulation strategy, the operation process of the fuel system and the lubricating oil system is simulated through the fuel and lubricating oil simulation model to obtain simulation results. Based on the simulation results, abnormal information between the fuel system and the lubricating oil system is identified through a performance evaluation strategy.

[0009] Based on the abnormal information between the fuel system and the lubricating oil system, the fuel system and the lubricating oil system are evaluated and processed through a system evaluation strategy to obtain the design evaluation results of the fuel system and the lubricating oil system.

[0010] Optionally, the step of constructing a system simulation model for each system based on the system design parameters and system operation data of each system includes:

[0011] Obtain the system operation model for each system, and adjust the system operation model for each system based on the system design parameters to obtain the target system operation model for each system;

[0012] For each system, based on the system operation data, the system operation control parameters are calculated using the system operation control algorithm. Based on the system operation control parameters, the target system operation model is adjusted to obtain the system simulation model.

[0013] Optionally, the step of performing model association processing on the simulation models of each system based on the system coupling logic information between the systems to obtain the lubricating oil simulation model includes:

[0014] Based on the system coupling logic information between the systems, the data coupling mode between the systems and the data interaction mode between the systems are identified;

[0015] Based on the data coupling method and data interaction method between the systems, a data interaction instruction generation logic is generated between the systems. Based on the data interaction instruction generation logic, the system simulation models of the systems are spliced ​​together to obtain the lubricating oil simulation model.

[0016] Optionally, the system simulation strategy for generating the fuel and lubricating oil simulation model based on the operational correlation information of the aero-engine includes:

[0017] Based on the operational association information, the environmental data of the aero-engine under each operational condition and the control command information under each operational condition are identified;

[0018] Based on the environmental data of the operating conditions, the environmental parameters of each environmental type of the operating conditions are identified, and based on the control command information of each operating condition, the sub-control commands of each system corresponding to each operating condition are identified.

[0019] The environmental parameters of each environmental type for each operating condition, as well as the sub-control commands of each system corresponding to each operating condition, are used as the system simulation strategy for the fuel and lubricating oil simulation model.

[0020] Optionally, based on the system simulation strategy, the simulation of the operation process of the fuel system and the lubricating oil system using the fuel-lubricating oil simulation model to obtain simulation results includes:

[0021] For each operating condition, based on the environmental parameters of each environmental type of the operating condition, the system environmental parameters of the fuel and lubricating oil simulation model are adjusted to obtain the target fuel and lubricating oil simulation model corresponding to the operating condition.

[0022] Based on the target fuel and lubricating oil simulation model, the operation process of the fuel system and the lubricating oil system is simulated through the sub-control commands of each system corresponding to the operating condition, and the simulation operation data of each system corresponding to the operating condition is obtained. The simulation operation data of all systems is used as the simulation operation result.

[0023] Optionally, the performance evaluation strategy includes a sub-performance evaluation strategy for each system. The step of identifying abnormal information between the fuel system and the lubricating oil system based on the simulation results through the performance evaluation strategy includes:

[0024] For each operating condition, based on the simulation operating data of each system corresponding to the operating condition, the sub-performance evaluation strategy of each system is used to identify the system performance data of each system.

[0025] Based on the system performance data of each system, abnormal performance information of each system is identified, and the abnormal performance information of all systems is used as the sub-abnormal performance information of the operating condition.

[0026] All sub-abnormal performance information of all operating conditions is used as abnormal information between the fuel system and the lubricating oil system.

[0027] Secondly, this application also provides a design evaluation device for an aircraft engine fuel system and lubrication system, comprising:

[0028] The acquisition module is used to acquire the system design parameters of each system associated with the fuel system and lubricating oil system, the system operation data of each system, the system coupling logic information between each system, and the operation association information of the aero-engine, and to construct the system simulation model of each system based on the system design parameters and the system operation data of each system.

[0029] The generation module is used to perform model association processing on the simulation models of each system based on the system coupling logic information between each system to obtain a fuel and lubricating oil simulation model, and to generate a system simulation strategy for the fuel and lubricating oil simulation model based on the various operational association information of the aero-engine.

[0030] The identification module is used to simulate the operation of the fuel system and the lubricating oil system based on the system simulation strategy and the fuel-lubricating oil simulation model, obtain the simulation operation results, and identify abnormal information between the fuel system and the lubricating oil system based on the simulation operation results and the performance evaluation strategy.

[0031] The evaluation module is used to evaluate the fuel system and the lubricating oil system based on the abnormal information between them and through a system evaluation strategy, so as to obtain the design evaluation results of the fuel system and the lubricating oil system.

[0032] Optionally, the acquisition module is specifically used for:

[0033] Obtain the system operation model for each system, and adjust the system operation model for each system based on the system design parameters to obtain the target system operation model for each system;

[0034] For each system, based on the system operation data, the system operation control parameters are calculated using the system operation control algorithm. Based on the system operation control parameters, the target system operation model is adjusted to obtain the system simulation model.

[0035] Optionally, the generation module is specifically used for:

[0036] Based on the system coupling logic information between the systems, the data coupling mode between the systems and the data interaction mode between the systems are identified;

[0037] Based on the data coupling method and data interaction method between the systems, a data interaction instruction generation logic is generated between the systems. Based on the data interaction instruction generation logic, the system simulation models of the systems are spliced ​​together to obtain the lubricating oil simulation model.

[0038] Optionally, the generation module is specifically used for:

[0039] Based on the operational association information, the environmental data of the aero-engine under each operational condition and the control command information under each operational condition are identified;

[0040] Based on the environmental data of the operating conditions, the environmental parameters of each environmental type of the operating conditions are identified, and based on the control command information of each operating condition, the sub-control commands of each system corresponding to each operating condition are identified.

[0041] The environmental parameters of each environmental type for each operating condition, as well as the sub-control commands of each system corresponding to each operating condition, are used as the system simulation strategy for the fuel and lubricating oil simulation model.

[0042] Optionally, the identification module is specifically used for:

[0043] For each operating condition, based on the environmental parameters of each environmental type of the operating condition, the system environmental parameters of the fuel and lubricating oil simulation model are adjusted to obtain the target fuel and lubricating oil simulation model corresponding to the operating condition.

[0044] Based on the target fuel and lubricating oil simulation model, the operation process of the fuel system and the lubricating oil system is simulated through the sub-control commands of each system corresponding to the operating condition, and the simulation operation data of each system corresponding to the operating condition is obtained. The simulation operation data of all systems is used as the simulation operation result.

[0045] Optionally, the identification module is specifically used for:

[0046] For each operating condition, based on the simulation operating data of each system corresponding to the operating condition, the sub-performance evaluation strategy of each system is used to identify the system performance data of each system.

[0047] Based on the system performance data of each system, abnormal performance information of each system is identified, and the abnormal performance information of all systems is used as the sub-abnormal performance information of the operating condition.

[0048] All sub-abnormal performance information of all operating conditions is used as abnormal information between the fuel system and the lubricating oil system.

[0049] Thirdly, this application provides a computer device. The computer device includes a memory and a processor, the memory storing a computer program, and the processor executing the computer program to implement the steps of the method described in any one of the first aspects.

[0050] Fourthly, this application provides a computer-readable storage medium having a computer program stored thereon that, when executed by a processor, implements the steps of the method described in any one of the first aspects.

[0051] Fifthly, this application provides a computer program product. The computer program product includes a computer program that, when executed by a processor, implements the steps of the method described in any one of the first aspects.

[0052] The aforementioned design evaluation method and apparatus for aero-engine fuel and lubricating oil systems involves acquiring system design parameters of each associated system, system operation data of each system, system coupling logic information between each system, and operational correlation information of the aero-engine. Based on the system design parameters and system operation data of each system, a system simulation model of each system is constructed. Based on the system coupling logic information between the systems, the simulation models are correlated to obtain a fuel-lubricating oil simulation model. A system simulation strategy for the fuel-lubricating oil simulation model is generated based on the operational correlation information of the aero-engine. Based on the system simulation strategy, the operation of the fuel and lubricating oil systems is simulated using the fuel-lubricating oil simulation model to obtain simulation results. Based on the simulation results, anomalies between the fuel and lubricating oil systems are identified using a performance evaluation strategy. Based on the anomalies between the fuel and lubricating oil systems, an evaluation strategy is used to assess the fuel and lubricating oil systems, resulting in a design evaluation result for the fuel and lubricating oil systems. This solution establishes a joint simulation model of the fuel and lubrication systems for aero-engines by combining the fuel system, lubrication system, and related systems. This ensures that the simulated results more closely approximate actual operating conditions, avoiding the problem of poor perception of engine state changes by a single system, which could affect the simulation's realism. Furthermore, this solution evaluates the simulation results under different operating conditions, providing design assessment results for the aero-engine's fuel and lubrication systems. The assessment results include evaluation information for both the fuel and lubrication systems under different operating conditions, improving the comprehensiveness and accuracy of the evaluation. Attached Figure Description

[0053] To more clearly illustrate the technical solutions in the embodiments or related technologies of this application, the accompanying drawings used in the description of the embodiments or related technologies will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0054] Figure 1 This is a flowchart illustrating the design evaluation method for an aircraft engine fuel system and lubrication system in one embodiment;

[0055] Figure 2 This is a schematic diagram of the operational structure of a combustion lubricating oil simulation model in one embodiment;

[0056] Figure 3 This is a schematic diagram of the fuel system in one embodiment;

[0057] Figure 4 This is a schematic diagram of the lubricating oil system in one embodiment;

[0058] Figure 5 This is a schematic diagram of the circuit structure of a combustion lubricating oil simulation model in one embodiment;

[0059] Figure 6 This is a flowchart illustrating a design evaluation example of an aircraft engine fuel system and lubrication system in one embodiment;

[0060] Figure 7 This is a structural block diagram of a design evaluation device for an aircraft engine fuel system and lubrication system in one embodiment.

[0061] Figure 8 This is an internal structural diagram of a computer device in one embodiment. Detailed Implementation

[0062] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the scope of this application.

[0063] The design evaluation method for aero-engine fuel systems and lubricating oil systems provided in this application embodiment can be applied to the design evaluation environment of aero-engine fuel systems and lubricating oil systems. This method can be applied to a terminal, a server, or a system including both a terminal and a server, and is implemented through interaction between the terminal and the server. The terminal can be, but is not limited to, various personal computers, laptops, mid-range computers, etc. The terminal establishes a joint simulation model of the aero-engine fuel and lubricating oil systems by combining the fuel system, the lubricating oil system, and the related systems. This makes the simulation results closer to the actual operating results during the simulation of the fuel and lubricating oil systems, avoiding the problem of poor perception of engine state changes by a single system, which affects the simulation's realism. Then, this solution further evaluates the simulation results according to different operating conditions by combining the aforementioned systems, thereby obtaining the design evaluation results of the aero-engine fuel system and lubricating oil system. The evaluation results include evaluation information of the fuel system and lubricating oil system under different operating conditions, improving the comprehensiveness and accuracy of the evaluation.

[0064] In one exemplary embodiment, such as Figure 1 As shown, a design evaluation method for an aircraft engine fuel system and lubricating oil system is provided. Taking the application of this method to a terminal as an example, the method includes the following steps S101 to S104. Wherein:

[0065] Step S101: Obtain the system design parameters of each system associated with the fuel system and lubricating oil system, the system operation data of each system, the system coupling logic information between each system, and the operation association information of the aero-engine, and construct the system simulation model of each system based on the system design parameters and system operation data of each system.

[0066] In this embodiment, in response to the information upload operation by the staff, the terminal acquires the system design parameters, system operation data, system coupling logic information between the systems, and the operational association information of the aero-engine associated with the fuel system and lubricating oil system. These systems include, but are not limited to, the fuel system, lubricating oil system, fuel / lubricating oil radiator system, air system and control system, and transmission system. The system design parameters are the structural parameters and operational control parameters designed by the staff. The system operation data are the operational commands of each system during aero-engine operation. The system coupling logic information between the systems characterizes the data interaction logic when data between the systems interacts. The operational association information of the aero-engine includes the environmental data of the aero-engine under various operating conditions and the control command information of each system under each operating condition. Finally, based on the system design parameters and system operation data of each system, the terminal constructs a system simulation model for each system. The system simulation model is a joint transient simulation model obtained by splicing together the transient models of each system. The transient models of each system include, but are not limited to, the engine performance transient model, control system model, fuel system model, air system model, transmission system model, bearing cavity model, and lubricating oil system model. The specific construction process will be explained in detail later.

[0067] Step S102: Based on the system coupling logic information between each system, perform model association processing on the simulation models of each system to obtain the fuel and lubricating oil simulation model, and generate the system simulation strategy of the fuel and lubricating oil simulation model based on the various operational association information of the aero-engine.

[0068] In this embodiment, the terminal performs model association processing on the simulation models of each system based on the system coupling logic information between the systems to obtain a fuel and lubricating oil simulation model. Based on the operational association information of the aero-engine, it generates a system simulation strategy for the fuel and lubricating oil simulation model. The system simulation strategy of the fuel and lubricating oil simulation model includes environmental parameters for each environmental type under different operating conditions of the aero-engine, as well as sub-control commands for each system corresponding to each operating condition. The specific generation process will be explained in detail later.

[0069] Step S103: Based on the system simulation strategy, the operation process of the fuel system and the lubricating oil system is simulated through the fuel and lubricating oil simulation model to obtain the simulation results. Based on the simulation results, abnormal information between the fuel system and the lubricating oil system is identified through the performance evaluation strategy.

[0070] In this embodiment, the terminal, based on a system simulation strategy, simulates the operation of the fuel system and lubricating oil system using a fuel and lubricating oil simulation model to obtain simulation results. Based on these results, a performance evaluation strategy is used to identify abnormal information between the fuel system and the lubricating oil system. The performance evaluation strategy includes sub-evaluation strategies for each system, used to comprehensively evaluate the various parameters and operational performance of each system. The specific evaluation process will be described in detail later.

[0071] Step S104: Based on the abnormal information between the fuel system and the lubricating oil system, the fuel system and the lubricating oil system are evaluated and processed through a system evaluation strategy to obtain the design evaluation results of the fuel system and the lubricating oil system.

[0072] In this embodiment, the terminal evaluates the fuel system and lubricating oil system based on abnormal information between them using a system evaluation strategy, thereby obtaining the design evaluation results for the fuel system and lubricating oil system. The abnormal information between the fuel system and lubricating oil system differs under each operating condition. Based on this abnormal information under each operating condition, the terminal performs design evaluations on the aspects corresponding to different abnormal information using a pre-set system evaluation strategy, thus obtaining the design evaluation results for the fuel system and lubricating oil system. This system evaluation strategy includes sub-evaluation strategies for each design aspect of the fuel system and lubricating oil system, where each sub-evaluation strategy corresponds to an evaluation value for a different range of abnormal information. Then, after evaluating the aspects to which all abnormal information belongs, the terminal sums the obtained evaluation values ​​to obtain the design evaluation results for the fuel system and lubricating oil system. These design aspects include: mechanical aspects (adjusting sliding friction); hydraulic aspects (adjusting throttling area); electrical aspects (flow characteristics of the electro-hydraulic conversion device); heat generation aspects (fuel system return flow rate); and heat exchange aspects (fuel system flow rate, lubricating oil tank volume, booster pump efficiency, and heat exchanger area).

[0073] Based on the above scheme, a joint simulation model of the fuel and lubrication systems of an aero-engine is established by combining the fuel system, lubrication system, and related systems. This makes the simulation results closer to the actual operating results during the simulation of the fuel and lubrication systems, avoiding the problem of poor perception of engine state changes by a single system, which affects the realism of the simulation. Then, by combining the above systems and performing performance evaluations on the simulation results under different operating conditions, this scheme obtains the design evaluation results of the aero-engine's fuel and lubrication systems. The evaluation results include assessment information of the fuel and lubrication systems under different operating conditions, improving the comprehensiveness and accuracy of the evaluation.

[0074] Optionally, based on the system design parameters and system operation data of each system, a system simulation model for each system is constructed, including: obtaining the system operation model of each system, and adjusting the system operation model of each system based on the system design parameters of each system to obtain the target system operation model of each system; for each system, based on the system operation data, calculating the system operation control parameters of the system through the system operation control algorithm, and adjusting the target system operation model of the system based on the system operation control parameters to obtain the system simulation model of the system.

[0075] In this embodiment, the terminal acquires the system operation model of each system and adjusts the system operation model of each system based on the system design parameters of each system to obtain the target system operation model of each system. The system operation model of each system can be a single-system model already constructed by the staff. The components of each system include, but are not limited to:

[0076] a) The components of the fuel system include at least a booster pump, spring, actuating valve, electro-hydraulic conversion device, throttling element, filter element, and sensing element, and have at least the functions of fuel boosting, fuel metering, fuel cut-off when stopping, mechanical actuation, electro-hydraulic conversion, position feedback, and heat generation and heat exchange of mechanical and hydraulic systems.

[0077] b) The components of the lubricating oil system shall include at least an oil tank, an oil supply pump, an oil return pump, a filter element, a throttling element, a sensing element, a one-way valve, a differential pressure switch, and an oil-gas separator, and shall have at least the functions of lubricating oil pressurization, lubricating oil distribution to various cooling components, heat generation and heat exchange in the bearing cavity, and oil-gas separation.

[0078] c) The fuel / oil heat exchanger is a key component for heat exchange, cooling the lubricating oil while heating the fuel.

[0079] d) The air system consists of a pressure source and a flow source. The pressure, flow rate and temperature change with the engine status and participate in the heat exchange calculation of the lubricating oil system.

[0080] Then, for each system, the terminal calculates the system's operation control parameters based on the system's operational data and the system's operation control algorithm. Based on these parameters, it adjusts the target system operation model to obtain the system's simulation model. The system operation control algorithm for each system is a calculation formula relating the control commands or control parameters corresponding to each piece of operational data for that system. This calculation formula is preset by the operator on the terminal.

[0081] Based on the above scheme, by combining the system operation data of each system of the aero-engine, the system operation model of each system is adjusted to improve the similarity between the constructed system simulation model of each system and the various systems of the aero-engine.

[0082] Optionally, based on the system coupling logic information between the systems, the simulation models of each system are processed to obtain a fuel and lubricating oil simulation model. This includes: identifying the data coupling method and data interaction method between the systems based on the system coupling logic information; generating data interaction instruction generation logic between the systems based on the data coupling method and data interaction method between the systems; and splicing the system simulation models of each system based on the data interaction instruction generation logic to obtain the fuel and lubricating oil simulation model.

[0083] In this embodiment, the terminal identifies the data coupling methods and data interaction methods between the systems based on the system coupling logic information. Then, based on the data coupling and interaction methods, the terminal generates data interaction instruction generation logic for each system, and uses this logic to stitch together the system simulation models of each system to obtain the lubricating oil simulation model. Figure 2 The diagram shown is a schematic of the operational structure of a fuel and lubricating oil simulation model. Within this simulation model, as shown... Figure 3 Figure 4 shows the structural schematic diagram of the fuel system; Figure 5 shows the structural schematic diagram of the lubricating oil system; as shown in Figure 6. Figure 5 The diagram shown is a schematic diagram of the circuit structure of the lubricating oil simulation model.

[0084] Specifically, for example, the transient performance model of an engine: based on the fuel quantity and adjustment mechanism position output by the transient model of the fuel system, as well as the mechanical output of the transmission system, parameters such as engine thrust, speed, temperature, and efficiency are calculated. This dynamically simulates the engine's performance under different operating conditions.

[0085] Control system model: Read the speed feedback signal of the engine transient model, calculate the fuel flow control command according to the throttle input command and control algorithm; then read the LVDT (Linear Variable Displacement Transducer) feedback value output by the fuel system transient model, calculate the current control command value according to the above fuel quantity control command and control algorithm, and give it to the fuel system transient model.

[0086] Fuel system model: Based on the current control command value given by the control system model and the speed signal output by the engine performance transient model, the fuel pressure and flow rate and the position of the regulating mechanism are calculated and output to the engine performance transient model. At the same time, the LVDT displacement signal is fed back to the control system model for fuel flow control.

[0087] Fuel / Lubricating Oil Heat Exchanger Model: Lubricating oil and fuel oil exchange heat through a heat exchanger. This model dynamically adjusts the heat exchange rate based on transient thermodynamic conditions.

[0088] Air system model: Based on the speed and power changes output by the engine transient model, an airflow with a certain temperature and flow rate is generated and heat exchange is calculated with the lubricating oil system model.

[0089] Transmission system model: The heat generation characteristics of each component (bearing, gearbox, etc.) are calculated based on the engine transient model speed and load changes, and heat exchange is calculated with the lubricating oil system model. The heat exchange characteristics change with engine speed and load.

[0090] Bearing cavity model: Calculates the heat generation characteristics as the external environment changes with the transient model of the engine, and exchanges heat with the transient model of the lubricating oil system.

[0091] The lubricating oil system model: Based on the engine performance transient model's output speed signal, it supplies lubricating oil at a certain pressure and flow rate to the transmission system and bearing chamber, and feeds back the model's temperature and pressure to the control system model to ensure stable system operation. Simultaneously, the lubricating oil system model calculates the heat changes during the lubricating oil circulation process based on the heat exchange of the transmission system model, fuel / lubricating oil heat exchanger model, air system model, and external environment, obtaining the lubricating oil temperature values ​​at various locations in the lubricating oil circulation loop.

[0092] The main sources of heat in the lubricating oil system include: 1. heat generated by bearing friction; 2. heat generated by friction of the bearing cavity sealing device; 3. external heat transferred from the bearing cavity wall through convection and conduction, heat from hot air leakage, and heat exchanged between the oil tank and other accessory pipelines and the external environment; 4. heat generated by power loss of the lubricating oil supply pump and return pump; and 5. heat generated by efficiency loss of the gear transmission device.

[0093] The total power loss of a bearing can be divided into two parts: the frictional power loss of the moving surfaces and the churning power loss of the lubricating oil inside the bearing.

[0094] Heat generated by friction in roller bearings:

[0095] q1=CZρl 2 u 3 β′

[0096] Where: C - total bearing resistance coefficient, C: C1+C2, C1 - friction coefficient, C2 - resistance coefficient; Z - number of rolling elements; ρ - lubricating oil density, Kg / m3; u - cage circumferential speed, m / s; l - roller length, m; β′ - influence coefficient of radial clearance on power loss.

[0097] Heat generated by friction in ball bearings:

[0098] q1=CZρd 2 u 3

[0099] Where: C - total bearing resistance coefficient; Z - number of rolling elements; ρ - oil density, Kg / m3; u - cage circumferential speed, m / s; d - roller length, m.

[0100] Friction generates heat in the sealing device:

[0101] q2=Fμ=2πRNμ[(P1-P2)(LK)LS+(P1-P2)δnl1+W] / 60

[0102] K = 1 / 3[1 + 1 / (1 + P2 / P1)]

[0103] Where: R—sealing radius, m; N—spindle speed, r / min; μ—friction coefficient; Pl—air chamber pressure, Pa; P2—bearing chamber pressure, Pa; L—sealing flange width, m; S—sealing surface circumference, S=2πR, m; δ—contact gap, m; n—number of joints; 11—flange width at joint, m; W—spring force, N.

[0104] Air leakage brings heat:

[0105] q′3=GC P Δt

[0106] Air system leakage:

[0107]

[0108] Where: D - runway diameter, m; T - air chamber temperature, K; P1 - air chamber pressure, MPa; P2 - oil chamber pressure, MPa;

[0109] Heat exchange between the external environment and the bearing cavity:

[0110] q″3=λΔtL+αΔtA

[0111] In the formula: λ - heat dissipation coefficient, which can be found in the material handbook. Δt - temperature difference between the inside and outside of the bearing cavity; α - convective heat transfer coefficient; A - convective exchange area, which is related to gas / liquid flow.

[0112] Oil tank convective heat exchange:

[0113] q″′3=αΔtA

[0114] Heat generated by efficiency losses in the lubricating oil supply and return pumps:

[0115] q4=pQ(1-ηη)

[0116] Where: p - pump outlet pressure, Pa; Q - pump flow rate, m3 / s; η - gear pump total efficiency.

[0117] Heat generated by mechanical efficiency loss in gear transmission mechanisms:

[0118] q5 = 745.7N(1-η)

[0119] In the formula: N—total power, W; η represents the total transmission efficiency, which is generally taken as 0.9.

[0120] Heat generated by the lubricating oil system:

[0121]

[0122] The heat sources of a fuel system can be divided into external and internal factors. External factors include heat exchange between the fuel / oil radiator and the external environment. Internal factors mainly consist of the power losses within the fuel system itself, which are ultimately converted into heat within the fuel system. These include: booster pump efficiency losses, pressure losses along the flow path, and flow losses (mainly from system return fuel).

[0123] The heat exchange principle of the external environment Q1 is the same as that of the lubricating oil system.

[0124] The efficiency loss at the booster pump is divided into centrifugal pump efficiency loss and gear pump efficiency loss.

[0125] Heat generated by centrifugal pump efficiency loss:

[0126] Q2=HQρg(1-η)

[0127] Where: H—pump head, m; Q—pump flow rate, m3 / s; ρ—fuel density, kg / m3; η—gear pump overall efficiency.

[0128] The gear pump efficiency loss generates heat Q3.

[0129] Heat generated by pressure loss in the fuel system:

[0130] Q4=ΔP1*Q

[0131] In the formula: ΔP—flow resistance of the fuel system, usually the difference between the pressure after the fuel pump and the pressure at the fuel system outlet; Q—working flow rate of fuel, usually the flow rate of fuel supplied to the final actuator.

[0132] Heat generated by flow loss in the fuel system:

[0133] Q5=ΔP2*Q 回

[0134] Where: ΔP2—the difference between the pump outlet pressure and the return oil pressure, pa; Q 回 — Fuel system return flow rate, m3 / s (the difference between the fuel pump outlet flow rate and the metered flow rate).

[0135] Heat generated by the fuel system:

[0136]

[0137] In the lubricating oil system, two-phase flow and the high-temperature inner wall of the bearing cavity require convective heat transfer. The air outside the bearing cavity is in motion and also undergoes convective heat transfer with the outer wall of the bearing cavity. These forced convection heat transfer methods are quite unique and difficult to manage.

[0138] Formula for the forced convection heat transfer coefficient between the outer surface of the engine rotating shaft and the lubricating oil:

[0139]

[0140] The fuel / oil radiator uses a shell-and-tube design, with fuel flowing inside the tubes and oil flowing inside the outer shell.

[0141] Dimensionless functional relations:

[0142] ε = f(NTU, C*, M)

[0143] In the formula: M—flow pattern; ε—radiator heat transfer efficiency, representing the ratio of the actual heat transfer of the radiator to the theoretical maximum heat transfer; NTU—number of heat transfer units, a dimensionless measure of the radiator's "heat transfer scale," expressed as:

[0144]

[0145] Where: A—heat transfer area of ​​the radiator, m2; Wmin—smaller heat capacity flow rate between the hot and cold fluids, W / K; K—overall heat transfer coefficient, W / m2.K.

[0146] Heat transfer coefficient:

[0147]

[0148] In the formula: α0 and α f These represent the surface heat transfer coefficients, W / m².K, of the heat exchange tubes inside (tube side) and outside (shell side), respectively; A fA0 and δ represent the contact areas between the heat exchanger tubes and the tube-side and shell-side fluids, respectively, in m2; δ—heat exchanger tube wall thickness, in m; γ p — Thermal conductivity of the heat exchanger tube, W / mK.

[0149] The average convective temperature difference varies depending on the flow pattern:

[0150]

[0151] Theoretically, it is assumed that the amount of heat removed by the fuel system through the radiator is equal to the amount of heat dissipated by the lubricating oil system.

[0152] Q=KΔtS

[0153] Hydraulic component design:

[0154] The lubricating oil supply is determined by the total heat of the lubricating oil system, assuming the characteristics of the lubricating oil medium are known.

[0155]

[0156] Oil supply gear pump flow rate Q = 2πdmbn × 10 -6 Given a fixed structure, the flow rate is mainly determined by the rotational speed of the lubricating oil pump. The volumetric efficiency and mechanical efficiency of the gear pump are usually 0.70 to 0.95, which are selected according to the working pressure and structural form of the pump.

[0157] Considering that a large amount of air dissolves in the lubricating oil solution during the return oil circuit, and that gear pumps are inefficient, the return oil pump flow rate is usually designed to be 2 to 3 times the inlet oil pump flow rate to ensure the oil suction capacity of the return oil system.

[0158] The volume of the oil tank is the sum of the maximum oil consumption during engine operation and the amount of oil stored to ensure that the oil supply pump can draw oil from the tank and meet the allowable oil pressure for normal engine lubrication.

[0159] V = V K +V b +V p +V t

[0160] In the formula: V b —Do not use lubricating oil volume; V k —Available lubricating oil volume; V p —Expansion space; V t —The volume of lubricating oil swallowed.

[0161] Engine oil filters commonly use mesh filters. Currently, with increasing demands for filtration precision, the filter element's filtration precision has decreased to 10µm or even 3µm. The required flow area for the oil filter is:

[0162]

[0163] Oil filter pressure loss:

[0164]

[0165] The one-way valve is located after the lubricating oil filter element. Its main function is to prevent siphoning. That is, when the lubricating oil pump is not working, the one-way valve uses spring force to prevent the lubricating oil tank from supplying oil to the system.

[0166] The bypass valve is connected in parallel with the lubricating oil filter and the one-way valve. When the filter becomes clogged and the pressure difference reaches a certain limit, the bypass valve opens, and the lubricating oil system supplies oil directly without filtration, preventing the bearing cavity and gear transmission device from overheating and seizing.

[0167] To achieve a constant flow rate of lubricating oil at all flight altitudes, the oil volume remains essentially constant from the ground to high altitudes. A pressure regulating valve allows excess flow pumped out by the pump to return to the pump inlet, thus maintaining a constant flow of lubricating oil to the engine. The design parameters of the pressure regulating valve primarily regulate the pressure value, which is determined by the engine piping damping coefficient and the required oil supply for all engine operating conditions.

[0168] The relationship between the pressure difference between the inlet and outlet lubricating oil of the pressure regulating valve and the flow rate can be obtained from the pipeline pressure drop formula:

[0169]

[0170] The diameter of the nozzle is:

[0171] d=[4Q[ρ / (2gΔP)] 0.5 / (μπ) 0.5 ]

[0172] The piping of the lubrication system is subjected to loads such as constant liquid pressure, bending, thermal deformation, and alternating stress generated by the vibration of the power unit. The diameter, length, and direction of the piping should meet the resistance requirements of the system.

[0173] Diameter of pipelines in various parts of the lubricating oil system

[0174] Fuel system module design:

[0175] Gear pump oil supply flow rate Q = 2πdmbn × 10 -6 The volumetric efficiency and mechanical efficiency of gear pumps are typically between 0.70 and 0.95.

[0176] To ensure that the fuel system pressure does not exceed the limit and to protect the booster pump, a safety valve is usually installed after the high-pressure pump. The safety valve and the high-pressure pump are connected in parallel. When the system pressure exceeds the limit, the safety valve opens, and the high-pressure oil after the gear pump returns to the front of the pump through the safety valve, forming an internal circulation.

[0177] Fuel systems typically use mesh oil filters. Generally, a two-stage oil filter is installed at the high-pressure pump outlet: the coarse filter supplies fuel to the metering valve and differential pressure valve, while the fine filter supplies fuel to the constant pressure valve and servo valve. Currently, with increasing demands for filtration precision, filter element filtration accuracy has decreased to 3µm or even smaller. The required flow area for the oil filter is:

[0178]

[0179] The fuel metering module consists of a metering valve, a constant pressure valve, a differential pressure valve, a metering servo valve, and a displacement sensor.

[0180] The main design parameter of the metering valve is the metering orifice area, which ensures the maximum metering flow rate and the moving speed of the metering valve.

[0181] Its flow rate output:

[0182]

[0183] Affected by hydraulic pressure:

[0184]

[0185] The main function of the constant pressure valve is to provide constant pressure fuel to the metering servo valve, ensuring stable output of servo oil. The constant pressure valve converts high-pressure oil into constant pressure oil through orifice throttling. When the oil pressure flowing out of the constant pressure valve reaches the set value, the constant pressure oil acts on the upper end of the valve core, balancing with the spring force at the lower end of the valve core and the force generated by the low-pressure oil, thus achieving constant pressure output.

[0186] In a steady state:

[0187] P r *A1=P df *A1+F s

[0188] Among them, F s =-kx+F0 is the spring force, and its high-pressure flow input is:

[0189]

[0190] The parking module consists of a booster valve, a parking valve, and a parking solenoid valve. During normal operation, metered fuel passes through the booster valve and then into the parking valve, which supplies fuel to the engine. When the parking solenoid valve operates, the fuel pressure changes from low to high pressure. The high-pressure fuel shuts off the parking valve and the engine interface, connecting it to the low-pressure interface. After the booster valve, the fuel returns to the gear pump, creating an internal fuel circulation system.

[0191] Based on the above scheme, the systems are linked and combined by using the system coupling logic information between the systems, thereby obtaining the combustion and lubricating oil simulation model, which improves the accuracy and comprehensiveness of the constructed combustion and lubricating oil simulation model.

[0192] Optionally, a system simulation strategy for generating a fuel and lubricant simulation model based on various operational correlation information of the aero-engine includes: identifying environmental data of the aero-engine under various operating conditions and control command information under various operating conditions based on operational correlation information; identifying environmental parameters of various environmental types under various operating conditions based on environmental data of various operating conditions, and identifying sub-control commands of each system corresponding to each operating condition based on control command information of each operating condition; and using the environmental parameters of various environmental types under each operating condition and the sub-control commands of each system corresponding to each operating condition as the system simulation strategy for the fuel and lubricant simulation model.

[0193] In this embodiment, the terminal identifies the environmental data and control command information of the aero-engine under various operating conditions based on operational association information. The environmental data includes sub-environmental data ranges for different environmental types, such as temperature ranges (for ambient temperature), airflow speed ranges (for airflow speed), air pressure ranges (for air pressure), and humidity ranges (for humidity). Then, based on the environmental data of each operating condition, the terminal identifies the environmental parameters for each environmental type and, based on the control command information for each operating condition, identifies the sub-control commands for each system corresponding to each operating condition. The environmental parameters for each environmental type are the ranges of environmental parameter values ​​obtained after parameterizing the environmental data ranges for each environmental type. The terminal presets parameterization programs for each environmental type and combines these programs to convert the sub-environmental data ranges for each environmental type into the ranges of environmental parameter values ​​for that environmental type.

[0194] Then, the terminal uses the environmental parameters of each environmental type for each operating condition, as well as the sub-control commands of each system corresponding to each operating condition, as the system simulation strategy for the fuel and lubricating oil simulation model.

[0195] Based on the above scheme, by decomposing and transforming the various operational information, we can obtain the environmental parameters of each environmental type for each operational condition, as well as the sub-control instructions of each system corresponding to each operational condition, thereby improving the simulation realism of each operational condition.

[0196] Optionally, based on the system simulation strategy, the operation process of the fuel system and lubricating oil system is simulated through a fuel and lubricating oil simulation model to obtain simulation results. This includes: for each operating condition, adjusting the system environment parameters of the fuel and lubricating oil simulation model based on the environmental parameters of each environmental type of the operating condition to obtain the target fuel and lubricating oil simulation model corresponding to the operating condition; based on the target fuel and lubricating oil simulation model, simulating the operation process of the fuel system and lubricating oil system through the sub-control commands of each system corresponding to the operating condition to obtain the simulation operation data of each system corresponding to the operating condition, and using the simulation operation data of all systems as the simulation results.

[0197] In this embodiment, for each operating condition, the terminal adjusts the system environment parameters of the fuel and lubricating oil simulation model based on the environmental parameters of each environmental type under that operating condition, thus obtaining the target fuel and lubricating oil simulation model corresponding to the operating condition. Then, based on the target fuel and lubricating oil simulation model, the terminal simulates the operation of the fuel system and lubricating oil system through sub-control commands for each system corresponding to the operating condition, obtaining the simulation operation data for each system corresponding to the operating condition, and using the simulation operation data of all systems as the simulation operation result.

[0198] Specifically, the terminal establishes dynamic interaction interfaces between the aircraft engine fuel and lubricating oil systems and the engine performance model, control system, and air system. This enables mechanical, hydraulic, electrical, and thermal coupling between the aircraft engine fuel and lubricating oil systems and the control system, engine performance, air system, and transmission system. The output parameters of each system continuously and dynamically change with the engine status. The interface format is shown in Table 1.

[0199] Table 1

[0200]

[0201]

[0202] The terminal acquires the dynamic change sequence of each parameter output by each system, and obtains the simulation operation data of each system.

[0203] Based on the above scheme, dynamic simulation is performed through the constructed dynamic interactive interface to obtain simulation operation data of each system, thereby ensuring the comprehensiveness and practicality of the obtained simulation operation data.

[0204] Optionally, a performance evaluation strategy, including a sub-performance evaluation strategy for each system, is used to identify abnormal information between the fuel system and the lubricating oil system based on simulation results. This includes: for each operating condition, identifying the system performance data of each system based on the simulation data of each system corresponding to the operating condition, and using the sub-performance evaluation strategy for each system; identifying abnormal performance information of each system based on the system performance data of each system, and using the abnormal performance information of all systems as sub-abnormal performance information of the operating condition; and using the sub-abnormal performance information of all operating conditions as abnormal information between the fuel system and the lubricating oil system.

[0205] In this embodiment, for each operating condition, the terminal identifies the system performance data of each system based on the simulation operation data of each system corresponding to that operating condition, using a sub-performance evaluation strategy for each system. Then, based on the system performance data of each system, the terminal identifies abnormal performance information for each system and uses the abnormal performance information of all systems as sub-abnormal performance information for the operating condition. Finally, the terminal uses the sub-abnormal performance information of all operating conditions as abnormal information between the fuel system and the lubricating oil system. Specifically, the performance evaluation process includes, for example, the performance evaluation process for the fuel system and the lubricating oil system:

[0206] Mechanical aspects: Does the speed of movement meet the preset conditions?

[0207] rotational speed Fuel metering flow Electrical signals The process of a valve jumping from level 0 to level 1.

[0208] Response speed requirement: The adjustment speed of the valve displacement shall not exceed the maximum allowable adjustment time.

[0209] rotational speed Fuel metering flow The process of a valve jumping from level 1 to level 0.

[0210] Response speed requirement: The adjustment speed of the valve displacement shall not exceed the maximum allowable adjustment time.

[0211] Electrical aspects: Does the response time meet the preset conditions?

[0212] rotational speed Fuel metering flow Electrical signal mark The process by which an electrical signal c jumps from 0 to 1.

[0213] Response time requirement: The settling time of the outlet quality flow rate shall not exceed the maximum allowable settling time.

[0214] In terms of hydraulics: whether the system pressure, flow accuracy, and fluctuation meet the preset conditions.

[0215] Mass flow rate: rotational speed Electrical signal signs Stop signal

[0216] Accuracy requirement: The value should be within the range of [reference value, usually a function of a, b, c, d] ± [allowable error].

[0217] Volatility requirement: The numerical range shall not exceed the maximum allowable volatility.

[0218] Pressure: Rotation speed is Electrical signal signs Stop signal

[0219] Accuracy requirement: The value should be within the range of [reference value, usually a constant] ± [allowable error, usually a constant].

[0220] Heat generation and heat exchange: Whether the temperature of the fuel oil and lubricating oil system meets the preset operating conditions.

[0221] rotational speed Fuel flow Electrical signals

[0222] The short-term temperature of the fuel should not exceed 130℃, and the short-term operating temperature should not exceed 163℃.

[0223] The working temperature of the lubricating oil shall not exceed 200℃.

[0224] Based on the above scheme, by evaluating the performance of different systems according to different performance evaluation strategies, the comprehensiveness and accuracy of the analysis of the operation of each system of the aero-engine are ensured, thereby effectively improving the accuracy of subsequent adjustments to the system design parameters of the fuel system and lubricating oil system.

[0225] This application also provides a design evaluation example for an aircraft engine fuel system and lubrication system, such as... Figure 6 As shown, the specific processing procedure includes the following steps:

[0226] Step S601: Obtain the system design parameters of each system associated with the fuel system and lubricating oil system, the system operation data of each system, the system coupling logic information between each system, and the operation association information of the aero-engine.

[0227] Step S602: Obtain the system operation model of each system, and adjust the system operation model of each system based on the system design parameters of each system to obtain the target system operation model of each system.

[0228] Step S603: For each system, based on the system's operating data, calculate the system's operating control parameters using the system's operating control algorithm, and adjust the system's target system operating model based on the system's operating control parameters to obtain the system's simulation model.

[0229] Step S604: Based on the system coupling logic information between each system, identify the data coupling mode between each system and the data interaction mode between each system.

[0230] Step S605: Based on the data coupling method and data interaction method between the systems, generate the data interaction instruction generation logic between the systems, and based on the data interaction instruction generation logic between the systems, stitch together the system simulation models of the systems to obtain the lubricating oil simulation model.

[0231] Step S606: Based on the operational association information, identify the environmental data of the aero-engine under each operational condition, as well as the control command information under each operational condition.

[0232] Step S607: Based on the environmental data of the operating conditions, identify the environmental parameters of each environmental type of the operating conditions, and based on the control command information of each operating condition, identify the sub-control commands of each system corresponding to each operating condition.

[0233] Step S608: Use the environmental parameters of each environmental type for each operating condition, as well as the sub-control commands of each system corresponding to each operating condition, as the system simulation strategy for the fuel and lubricating oil simulation model.

[0234] Step S609: For each operating condition, adjust the system environment parameters of the fuel and lubricating oil simulation model based on the environmental parameters of each environmental type of the operating condition to obtain the target fuel and lubricating oil simulation model corresponding to the operating condition.

[0235] Step S610: Based on the target fuel and lubricating oil simulation model, the operation process of the fuel system and lubricating oil system is simulated through the sub-control commands of each system corresponding to the operating conditions, and the simulation operation data of each system corresponding to the operating conditions is obtained. The simulation operation data of all systems is used as the simulation operation result.

[0236] Step S611: For each operating condition, based on the simulation operating data of each system corresponding to the operating condition, identify the system performance data of each system through the sub-performance evaluation strategy of each system.

[0237] Step S612: Based on the system performance data of each system, identify the abnormal performance information of each system, and take the abnormal performance information of all systems as the sub-abnormal performance information of the operating conditions.

[0238] Step S613: Treat the sub-abnormal performance information of all operating conditions as abnormal information between the fuel system and the lubricating oil system.

[0239] It should be understood that although the steps in the flowcharts of the embodiments described above are shown sequentially according to the arrows, these steps are not necessarily executed in the order indicated by the arrows. Unless explicitly stated herein, there is no strict order restriction on the execution of these steps, and they can be executed in other orders. Moreover, at least some steps in the flowcharts of the embodiments described above may include multiple steps or multiple stages. These steps or stages are not necessarily completed at the same time, but can be executed at different times. The execution order of these steps or stages is not necessarily sequential, but can be performed alternately or in turn with other steps or at least some of the steps or stages of other steps.

[0240] Based on the same inventive concept, this application also provides a design evaluation apparatus for an aircraft engine fuel system and lubricating oil system for implementing the design evaluation method for the aircraft engine fuel system and lubricating oil system described above. The solution provided by this apparatus is similar to the solution described in the above method. Therefore, the specific limitations of one or more embodiments of the design evaluation apparatus for an aircraft engine fuel system and lubricating oil system provided below can be found in the limitations of the design evaluation method for the aircraft engine fuel system and lubricating oil system described above, and will not be repeated here.

[0241] In one exemplary embodiment, such as Figure 7 As shown, a design evaluation device for an aircraft engine fuel system and lubricating oil system is provided, comprising: an acquisition module 710, a generation module 720, an identification module 730, and an evaluation module 740, wherein:

[0242] The acquisition module 710 is used to acquire the system design parameters of each system associated with the fuel system and the lubricating oil system, the system operation data of each system, the system coupling logic information between each system, and the operation association information of the aero-engine, and to construct the system simulation model of each system based on the system design parameters of each system and the system operation data of each system.

[0243] The generation module 720 is used to perform model association processing on the simulation models of each system based on the system coupling logic information between each system to obtain a fuel and lubricating oil simulation model, and to generate a system simulation strategy for the fuel and lubricating oil simulation model based on the various operational association information of the aero-engine.

[0244] The identification module 730 is used to simulate the operation process of the fuel system and the lubricating oil system based on the system simulation strategy and the fuel-lubricating oil simulation model, obtain simulation operation results, and identify abnormal information between the fuel system and the lubricating oil system based on the simulation operation results and the performance evaluation strategy.

[0245] The evaluation module 740 is used to evaluate the fuel system and the lubricating oil system based on the abnormal information between the fuel system and the lubricating oil system, and to obtain the design evaluation results of the fuel system and the lubricating oil system through a system evaluation strategy.

[0246] Optionally, the acquisition module 710 is specifically used for:

[0247] Obtain the system operation model for each system, and adjust the system operation model for each system based on the system design parameters to obtain the target system operation model for each system;

[0248] For each system, based on the system operation data, the system operation control parameters are calculated using the system operation control algorithm. Based on the system operation control parameters, the target system operation model is adjusted to obtain the system simulation model.

[0249] Optionally, the generation module 720 is specifically used for:

[0250] Based on the system coupling logic information between the systems, the data coupling mode between the systems and the data interaction mode between the systems are identified;

[0251] Based on the data coupling method and data interaction method between the systems, a data interaction instruction generation logic is generated between the systems. Based on the data interaction instruction generation logic, the system simulation models of the systems are spliced ​​together to obtain the lubricating oil simulation model.

[0252] Optionally, the generation module 720 is specifically used for:

[0253] Based on the operational association information, the environmental data of the aero-engine under each operational condition and the control command information under each operational condition are identified;

[0254] Based on the environmental data of the operating conditions, the environmental parameters of each environmental type of the operating conditions are identified, and based on the control command information of each operating condition, the sub-control commands of each system corresponding to each operating condition are identified.

[0255] The environmental parameters of each environmental type for each operating condition, as well as the sub-control commands of each system corresponding to each operating condition, are used as the system simulation strategy for the fuel and lubricating oil simulation model.

[0256] Optionally, the identification module 730 is specifically used for:

[0257] For each operating condition, based on the environmental parameters of each environmental type of the operating condition, the system environmental parameters of the fuel and lubricating oil simulation model are adjusted to obtain the target fuel and lubricating oil simulation model corresponding to the operating condition.

[0258] Based on the target fuel and lubricating oil simulation model, the operation process of the fuel system and the lubricating oil system is simulated through the sub-control commands of each system corresponding to the operating condition, and the simulation operation data of each system corresponding to the operating condition is obtained. The simulation operation data of all systems is used as the simulation operation result.

[0259] Optionally, the identification module 730 is specifically used for:

[0260] For each operating condition, based on the simulation operating data of each system corresponding to the operating condition, the sub-performance evaluation strategy of each system is used to identify the system performance data of each system.

[0261] Based on the system performance data of each system, abnormal performance information of each system is identified, and the abnormal performance information of all systems is used as the sub-abnormal performance information of the operating condition.

[0262] All sub-abnormal performance information of all operating conditions is used as abnormal information between the fuel system and the lubricating oil system.

[0263] The modules in the aforementioned design evaluation device for the aircraft engine fuel system and lubrication system can be implemented entirely or partially through software, hardware, or a combination thereof. These modules can be embedded in or independent of the processor in a computer device, or stored in the memory of a computer device as software, so that the processor can call and execute the corresponding operations of each module.

[0264] In one exemplary embodiment, a computer device is provided, which may be a terminal, and its internal structure diagram may be as follows: Figure 8As shown, the computer device includes a processor, memory, input / output interface, communication interface, display unit, and input device. The processor, memory, and input / output interface are connected via a system bus, and the communication interface, display unit, and input device are also connected to the system bus via the input / output interface. The processor provides computational and control capabilities. The memory includes non-volatile storage media and internal memory. The non-volatile storage media stores the operating system and computer programs. The internal memory provides an environment for the operation of the operating system and computer programs stored in the non-volatile storage media. The input / output interface is used for exchanging information between the processor and external devices. The communication interface is used for wired or wireless communication with external terminals; wireless communication can be achieved through Wi-Fi, mobile cellular networks, NFC (Near Field Communication), or other technologies. When the computer program is executed by the processor, it implements a design evaluation method for an aircraft engine fuel system and lubrication system. The display unit is used to form a visually visible image and can be a display screen, projection device, or virtual reality imaging device. The display screen can be an LCD screen or an e-ink screen. The input device of the computer device can be a touch layer covering the display screen, or buttons, trackballs, or touchpads set on the casing of the computer device, or external keyboards, touchpads, or mice, etc.

[0265] Those skilled in the art will understand that Figure 8 The structure shown is merely a block diagram of a portion of the structure related to the present application and does not constitute a limitation on the computer device to which the present application is applied. Specific computer devices may include more or fewer components than those shown in the figure, or combine certain components, or have different component arrangements.

[0266] In one exemplary embodiment, a computer device is provided, including a memory and a processor, the memory storing a computer program that, when executed by the processor, implements the steps of a design evaluation method for an aircraft engine fuel system and lubrication system.

[0267] In one embodiment, a computer-readable storage medium is provided having a computer program stored thereon, which, when executed by a processor, implements the steps of a design evaluation method for an aircraft engine fuel system and lubrication system.

[0268] In one embodiment, a computer program product is provided, including a computer program that, when executed by a processor, implements the steps of a design evaluation method for an aircraft engine fuel system and lubrication system.

[0269] It should be noted that the user information (including but not limited to user device information, user personal information, etc.) and data (including but not limited to data used for analysis, data stored, data displayed, etc.) involved in this application are all information and data authorized by the user or fully authorized by all parties, and the collection, use and processing of the relevant data must comply with relevant regulations.

[0270] Those skilled in the art will understand that all or part of the processes in the methods of the above embodiments can be implemented by a computer program instructing related hardware. The computer program can be stored in a non-volatile computer-readable storage medium, and when executed, it can include the processes of the embodiments of the above methods. Any references to memory, databases, or other media used in the embodiments provided in this application can include at least one of non-volatile and volatile memory. Non-volatile memory can include read-only memory (ROM), magnetic tape, floppy disk, flash memory, optical memory, high-density embedded non-volatile memory, resistive random access memory (ReRAM), magnetic random access memory (MRAM), ferroelectric random access memory (FRAM), phase change memory (PCM), graphene memory, etc. Volatile memory can include random access memory (RAM) or external cache memory, etc. By way of illustration and not limitation, RAM can take many forms, such as Static Random Access Memory (SRAM) or Dynamic Random Access Memory (DRAM). The databases involved in the embodiments provided in this application may include at least one type of relational database and non-relational database. Non-relational databases may include, but are not limited to, blockchain-based distributed databases. The processors involved in the embodiments provided in this application may be general-purpose processors, central processing units, graphics processing units, digital signal processors, programmable logic devices, quantum computing-based data processing logic devices, etc., and are not limited to these.

[0271] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0272] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of this patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this application should be determined by the appended claims.

Claims

1. A design evaluation method for an aircraft engine fuel system and lubrication system, characterized in that, The method includes: The system design parameters of each system associated with the fuel system and lubricating oil system, the system operation data of each system, the system coupling logic information between each system, and the operation association information of the aero-engine are obtained. Based on the system design parameters of each system and the system operation data of each system, a system simulation model of each system is constructed. Based on the system coupling logic information between the systems, the data coupling mode between the systems and the data interaction mode between the systems are identified; Based on the data coupling method and data interaction method between the systems, a data interaction instruction generation logic is generated between the systems. Based on the data interaction instruction generation logic, the system simulation models of the systems are spliced ​​together to obtain the lubricating oil simulation model. The control system model reads the speed feedback signal from the engine transient model, calculates the fuel flow control command based on the throttle input command and control algorithm, and then reads the linear displacement sensor feedback value output by the fuel system transient model. Based on the above fuel flow control command and control algorithm, it calculates the current control command value and sends it to the fuel system transient model. Fuel system model: Based on the current control command value given by the control system model and the speed signal output by the engine performance transient model, the fuel pressure and flow rate and the position of the regulating mechanism are calculated and output to the engine performance transient model. At the same time, the displacement signal of the linear displacement sensor is fed back to the control system model for fuel flow control. Fuel / Lubricating Oil Heat Exchanger Model: Lubricating oil and fuel oil exchange heat through a heat exchanger. This model dynamically adjusts the heat exchange rate based on transient thermodynamic conditions. Air system model: Based on the speed and power changes output by the engine transient model, calculate and generate an airflow with a certain temperature and flow rate, and perform heat exchange calculations with the lubricating oil system model; Transmission system model: The heat generation characteristics of each component are calculated based on the engine transient model speed and load changes, and heat exchange is calculated with the lubricating oil system model. The heat exchange characteristics change with engine speed and load. Bearing cavity model: Calculates the heat generation characteristics as the external environment changes with the transient model of the engine, and exchanges heat with the transient model of the lubricating oil system; Lubricating oil system model: Based on the speed signal output by the engine performance transient model, a certain pressure and flow rate of lubricating oil is supplied to the transmission system and bearing cavity, and the model temperature and pressure are fed back to the control system model to ensure the stable operation of the system; at the same time, the lubricating oil system model calculates the heat change during the lubricating oil circulation process based on the heat exchange of the transmission system model, the heat exchange of the fuel / lubricating oil heat exchanger model, the heat exchange of the air system model, and the heat exchange of the external environment system, and obtains the lubricating oil temperature value at each position in the lubricating oil circulation loop; A system simulation strategy for generating the fuel and lubricating oil simulation model based on the operational correlation information of the aero-engine; Based on the system simulation strategy, the operation process of the fuel system and the lubricating oil system is simulated through the fuel and lubricating oil simulation model to obtain simulation results. Based on the simulation results, abnormal information between the fuel system and the lubricating oil system is identified through a performance evaluation strategy. Based on the abnormal information between the fuel system and the lubricating oil system, the fuel system and the lubricating oil system are evaluated and processed through a system evaluation strategy to obtain the design evaluation results of the fuel system and the lubricating oil system.

2. The method according to claim 1, characterized in that, The construction of system simulation models for each system, based on the system design parameters and system operation data of each system, includes: Obtain the system operation model for each system, and adjust the system operation model for each system based on the system design parameters to obtain the target system operation model for each system; For each system, based on the system operation data, the system operation control parameters are calculated using the system operation control algorithm. Based on the system operation control parameters, the target system operation model is adjusted to obtain the system simulation model.

3. The method according to claim 1, characterized in that, The system simulation strategy for generating the fuel and lubricating oil simulation model based on the operational correlation information of the aero-engine includes: Based on the operational association information, the environmental data of the aero-engine under each operational condition and the control command information under each operational condition are identified; Based on the environmental data of the operating conditions, the environmental parameters of each environmental type of the operating conditions are identified, and based on the control command information of each operating condition, the sub-control commands of each system corresponding to each operating condition are identified. The environmental parameters of each environmental type for each operating condition, as well as the sub-control commands of each system corresponding to each operating condition, are used as the system simulation strategy for the fuel and lubricating oil simulation model.

4. The method according to claim 3, characterized in that, Based on the system simulation strategy, the operation process of the fuel system and the lubricating oil system is simulated through the fuel and lubricating oil simulation model to obtain simulation results, including: For each operating condition, based on the environmental parameters of each environmental type of the operating condition, the system environmental parameters of the fuel and lubricating oil simulation model are adjusted to obtain the target fuel and lubricating oil simulation model corresponding to the operating condition. Based on the target fuel and lubricating oil simulation model, the operation process of the fuel system and the lubricating oil system is simulated through the sub-control commands of each system corresponding to the operating condition, and the simulation operation data of each system corresponding to the operating condition is obtained. The simulation operation data of all systems is used as the simulation operation result.

5. The method according to claim 4, characterized in that, The performance evaluation strategy includes a sub-performance evaluation strategy for each system. Based on the simulation results, the performance evaluation strategy identifies abnormal information between the fuel system and the lubricating oil system, including: For each operating condition, based on the simulation operating data of each system corresponding to the operating condition, the sub-performance evaluation strategy of each system is used to identify the system performance data of each system. Based on the system performance data of each system, abnormal performance information of each system is identified, and the abnormal performance information of all systems is used as the sub-abnormal performance information of the operating condition. All sub-abnormal performance information of all operating conditions is used as abnormal information between the fuel system and the lubricating oil system.

6. A design evaluation device for an aircraft engine fuel system and lubrication system, characterized in that, The device includes: The acquisition module is used to acquire the system design parameters of each system associated with the fuel system and lubricating oil system, the system operation data of each system, the system coupling logic information between each system, and the operation association information of the aero-engine, and to construct the system simulation model of each system based on the system design parameters and the system operation data of each system. A generation module is used to identify the data coupling methods and data interaction methods between the systems based on the system coupling logic information between them; based on the data coupling methods and data interaction methods between the systems, it generates data interaction instruction generation logic between the systems, and based on the data interaction instruction generation logic between the systems, it splices the system simulation models of the systems to obtain a fuel / lubricating oil simulation model; wherein, the control system model: reads the speed feedback signal of the engine transient model, calculates the fuel flow control command according to the throttle input command and control algorithm; then reads the linear displacement sensor feedback value output by the fuel system transient model, calculates the current control command value according to the above fuel flow control command and control algorithm, and sends it to the fuel system transient model; wherein, the fuel system model: based on the current control command value given by the control system model and the speed signal output by the engine performance transient model, calculates the fuel pressure and flow rate and the position of the regulating mechanism output to the engine performance transient model, and simultaneously feeds back the displacement signal of the linear displacement sensor to the control system model for fuel flow control; fuel / lubricating oil heat exchanger model: The lubricating oil and fuel exchange heat through a heat exchanger. This model dynamically adjusts the heat exchange rate based on transient thermodynamic conditions. The air system model calculates and generates an airflow of a certain temperature and flow rate based on the engine's transient output speed and power, and performs heat exchange calculations with the lubricating oil system model. The transmission system model calculates the heat generation characteristics of each component based on the engine's transient speed and load changes, and performs heat exchange calculations with the lubricating oil system model; these heat exchange characteristics vary with engine speed and load. The bearing cavity model calculates the heat generation characteristics as the external environment changes with the engine's transient environment and exchanges heat with the lubricating oil system transient model. Lubricating oil system model: Based on the speed signal output from the engine performance transient model, a certain pressure and flow rate of lubricating oil is supplied to the transmission system and bearing cavity, and the model temperature and pressure are fed back to the control system model to ensure stable system operation; at the same time, the lubricating oil system model calculates the heat change during the lubricating oil circulation process based on the heat exchange of the transmission system model, the heat exchange of the fuel / lubricating oil heat exchanger model, the heat exchange of the air system model, and the heat exchange of the external environment system, and obtains the lubricating oil temperature value at each position in the lubricating oil circulation loop; based on the various operational correlation information of the aero-engine, a system simulation strategy for the fuel / lubricating oil simulation model is generated; The identification module is used to simulate the operation of the fuel system and the lubricating oil system based on the system simulation strategy and the fuel-lubricating oil simulation model, obtain the simulation operation results, and identify abnormal information between the fuel system and the lubricating oil system based on the simulation operation results and the performance evaluation strategy. The evaluation module is used to evaluate the fuel system and the lubricating oil system based on the abnormal information between them, and to obtain the design evaluation results of the fuel system and the lubricating oil system through a system evaluation strategy.

7. The apparatus according to claim 6, characterized in that, The acquisition module is specifically used for: Obtain the system operation model for each system, and adjust the system operation model for each system based on the system design parameters to obtain the target system operation model for each system; For each system, based on the system operation data, the system operation control parameters are calculated using the system operation control algorithm. Based on the system operation control parameters, the target system operation model is adjusted to obtain the system simulation model.

8. A computer device comprising a memory and a processor, wherein the memory stores a computer program, characterized in that, When the processor executes the computer program, it implements the steps of the method according to any one of claims 1 to 5.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, it implements the steps of the method according to any one of claims 1 to 5.

10. A computer program product, comprising a computer program, characterized in that, When the computer program is executed by a processor, it implements the steps of the method according to any one of claims 1 to 5.

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