Methods, devices, equipment, and media for online damage control of hot-end components in aero-engines.

Abstract

This application discloses a method, apparatus, device, and medium for online control of damage to hot-end components of an aero-engine. The method includes the following steps: S1, establishing a time-varying damage dynamics model of the hot-end component and calculating the model parameters; S2, online reconstruction of the control design model; S3, constructing control commands considering instantaneous damage quantities; S4, real-time optimization control, establishing an optimization function and solving for the control quantity to control the engine; S5, repeating the aforementioned steps until the control task at all times is completed. This application achieves the effect of online precise control of damage within the entire envelope of the aero-engine. By using instantaneous damage quantities, it avoids the phenomenon that the accumulation of damage quantities leads to an increase in their weight in the optimization objective, preventing the increase of tracking error of the main control parameters and the decline of transient performance after long-term use of the aero-engine. This application significantly improves the operational safety and service life of aero-engines, assists in the health management of aero-engines, has low computational load, and has a significant damage reduction effect.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and in particular to a method, apparatus, equipment, and medium for online control of damage to hot-end components of an aero-engine. Background Technology

[0002] Hot-end components of aero-engines operate in the harshest environment, enduring prolonged exposure to high temperatures, high pressures, and high mechanical loads. This makes them highly susceptible to various types of damage, significantly reducing component lifespan and engine health, and in severe cases, leading to catastrophic failures. The various transient state regulation processes of the engine are key factors causing damage to hot-end components. Traditional aero-engine transient state regulation only considers performance requirements, neglecting the damage caused to hot-end components. Currently, existing online damage control methods for aero-engines are mainly divided into two categories:

[0003] (1) Modify the transition state control plan of the aero-engine or limit the rotor acceleration: This type of method obtains the rules or experience of reducing the damage of the hot end components of the aero-engine by qualitatively analyzing the factors affecting the hot end components. Based on this, the engine transition state control plan is modified or additional rotor acceleration limit conditions are applied to avoid component damage caused by drastic changes in pressure, temperature, speed and other factors during acceleration.

[0004] (2) Engine damage control methods based on real-time optimization: These methods construct a real-time optimization controller for the engine and incorporate engine component damage or lifespan into the optimization objective. This allows for the calculation of control quantities that consider both engine acceleration performance and component damage, thereby controlling the engine's acceleration process and reducing component damage. It is worth noting that these methods primarily rely on the Manson-Coffin theory to establish static prediction models when considering component damage or lifespan, without taking into account the time-varying and dynamic characteristics of damage.

[0005] The above method has the following drawbacks:

[0006] (1) The methods of modifying the transition state control plan of the aero-engine or limiting the rotor acceleration are only qualitative methods, which rely on experience or a large number of experiments. In addition, considering the significant differences in the steady-state and dynamic characteristics of the engine within the entire flight envelope and the complexity of the operating state, this qualitative method not only fails to achieve the best loss reduction effect, but may also significantly reduce the engine's transition state performance;

[0007] (2) The engine damage control method based on real-time optimization does not consider the time-varying and dynamic characteristics of hot-end component damage. The established static damage prediction model cannot be well integrated with the system dynamic model, resulting in the inability to accurately consider the instantaneous damage of components during the optimization process. In addition, directly embedding complex damage models into the optimization process will also lead to excessive computation.

[0008] (3) Most methods do not directly consider component damage in order to simplify the design. Instead, they consider indirect parameters such as stress, strain or temperature related to damage. This approach ignores the complex nonlinear relationship between these indirect parameters and damage, thus reducing the damage reduction effect. Summary of the Invention

[0009] This application provides an online control method for damage to hot-end components of aero-engines, which addresses the technical problems of existing technologies that can only qualitatively assess damage, have insufficient optimization accuracy, require large computational loads, and have limited damage reduction effects.

[0010] This application is achieved through the following solution:

[0011] A method for online damage control of hot-end components in an aero-engine, comprising the following steps:

[0012] S1. Establish a time-varying damage dynamics model for the hot-end component and calculate the model parameters;

[0013] S2. Online reconstruction of the control design model: The time-varying damage dynamics model is fused with the aero-engine model. The control-oriented fused control design model is reconstructed in real time during each control cycle, and the final fused control design model parameters are calculated.

[0014] S3. Construct control instructions that take into account instantaneous damage amount, wherein the control instructions include master control parameter instructions and virtual control instructions that are positively correlated with instantaneous damage amount;

[0015] S4. Real-time optimization control: Establish and solve the optimization function to obtain the control increment at time k. And sum the control quantity at time k-1 with the control increment at time k. The engine is controlled as a control variable;

[0016] S5. Repeat the above steps until the control tasks for all moments are completed.

[0017] Further, step S1 specifically includes the following steps:

[0018] S11. Establish a time-varying damage dynamics model for the hot-end component and calculate the model parameters as follows:

[0019] ;

[0020] In the formula, the system matrix of the time-varying damage dynamics model is: The input matrix of the time-varying damage dynamics model is ,in, , , These are the parameters of the linear model of the aero-engine's steady-state point, which is:

[0021] ;

[0022] Where k1 is the rate of change of damage relative to the rate of change of damage-related parameters. The gain coefficient k1;

[0023] S12. Considering the elastic damage caused by radial stress in a high-pressure turbine disk, select... These are state parameters, including the high-voltage rotor speed. and low-pressure rotor speed The rate of change of damage-related parameters is taken as Then the gain coefficient The calculation is as follows:

[0024] ;

[0025] In the formula, These are constants related to the turbine disk structure. The density of the turbine disk material. The outer diameter of the high-pressure shaft. The outer diameter of the turbine disk. For stress, For reference stress, The fatigue strength coefficient, The fatigue strength index is given by: where the stress is calculated as follows:

[0026] ;

[0027] In the formula, ω is the rotor angular velocity;

[0028] Further, step S2 includes the following steps:

[0029] S21. Integrate the time-varying damage dynamics model with the aero-engine model, reconstruct the control-oriented fusion control design model in real time during each control cycle, and calculate the model matrix parameters. , , , :

[0030] ;

[0031] In the formula, For the state of the fusion model, For the output of the fusion model, the parameters of each model matrix are calculated as follows:

[0032] ;

[0033] S22. The fusion control design model is processed according to the control cycle. Discretize to obtain , , , Discretized model parameters , , , Integral control is introduced into the discretized fusion control design model and model parameters to obtain the final control design model parameters and control design model.

[0034] Further, in step S22, the fusion control design model is processed according to the control cycle. During discretization, the forward Euler method is used for discretization. The discretized fusion control design model and model parameters are as follows:

[0035] ;

[0036] ;

[0037] By introducing integral control, the final control design model parameters are obtained:

[0038] .

[0039] Furthermore, step S3 specifically includes the following steps:

[0040] S31. Construct control instructions that consider instantaneous damage, control instructions at time k. Build as:

[0041] ;

[0042] In the formula, Master control parameter commands, For damaging virtual instructions, Designed as follows:

[0043] ;

[0044] In the formula, and Take a positive integer. The larger the component, the less damage it will sustain. , The instantaneous damage is represented and estimated in real time using the following formula:

[0045] ;

[0046] Among them, T s To control the cycle.

[0047] Furthermore, step S4 specifically includes the following steps:

[0048] S41. Real-time optimization control: Establish the following optimization function and solve it to obtain the control increment at time k. and will The engine is controlled as a control variable:

[0049] (13);

[0050] In the formula, R and R are the tracking error weighting matrix and the control quantity weighting matrix, respectively, both of which are diagonal matrices. , As the balance factor, q j This represents the weighted value of the tracking error for the j-th instruction. and These are the lower and upper limits of the control quantity, respectively. and These are the lower and upper limits of the output, respectively.

[0051] Furthermore, step S3 specifically includes the following steps:

[0052] S32. Real-time update of estimated instantaneous damage. The health management top-level controller of the aircraft engine is transmitted to the health management top-level controller, which dynamically adjusts the balance factor according to the flight mission. The dynamic adjustment strategy is as follows:

[0053] (14);

[0054] in, The larger the value, the less damage to the component. The smaller the value, the better the tracking performance of the master control parameters.

[0055] This application also provides an online damage control device for hot-end components of an aero-engine, comprising:

[0056] The time-varying damage dynamics model establishment module is used to establish a time-varying damage dynamics model for hot-end components and calculate model parameters;

[0057] The online reconstructing module for the control design model is used for online reconstruction of the control design model. It integrates the time-varying damage dynamics model with the aero-engine model, reconstructs the control-oriented fusion control design model in real time during each control cycle, and calculates the final fusion control design model parameters.

[0058] A control instruction construction module is used to construct control instructions that take into account instantaneous damage, wherein the control instructions include master control parameter instructions and virtual control instructions that are positively correlated with instantaneous damage.

[0059] The real-time optimization control module is used for real-time optimization control. It establishes and solves the optimization function to obtain the control increment at time k. And sum the control quantity at time k-1 with the control increment at time k. The engine is controlled as a control variable;

[0060] The loop control module is used to repeat the aforementioned steps until the control task for all time periods is completed.

[0061] This application also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the steps of the online damage control method for hot-end components of the aero-engine.

[0062] This application also provides a storage medium including a stored program that, when the program is executed, controls the device where the storage medium is located to perform the steps of the online damage control method for hot-end components of an aero-engine.

[0063] Compared with the prior art, this application has the following advantages:

[0064] This application provides a method, apparatus, device, and medium for online control of damage to hot-end components of aero-engines. The method employs a time-varying damage dynamics model and a model-based control method, enabling the control process to consider instantaneous component damage, thereby achieving precise online damage control within the entire envelope of the aero-engine. Because this application uses instantaneous damage quantities rather than absolute quantities, it avoids the phenomenon of damage accumulation leading to an increased weight in the optimization objective, preventing increased tracking errors of main control parameters (such as engine speed) and decreased transient performance after long-term use of the aero-engine. This application can significantly improve the operational safety and service life of aero-engines, assist in aero-engine health management, has low computational load, and exhibits significant damage reduction effects.

[0065] In addition to the purposes, features, and advantages described above, this application has other purposes, features, and advantages. A further detailed description of this application will be provided below with reference to the figures. Attached Figure Description

[0066] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application.

[0067] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, for those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0068] Figure 1 This is a schematic flowchart of a preferred embodiment of the online damage control method for hot-end components of an aero-engine.

[0069] Figure 2 This is a schematic diagram of the control system architecture of a preferred embodiment of this application.

[0070] Figure 3 This is a schematic diagram comparing the damage amount after using the method of the preferred embodiment of this application with that of the prior art.

[0071] Figure 4 This is a schematic diagram comparing the speed change during acceleration using the method of the preferred embodiment of this application with that of the prior art.

[0072] Figure 5 This is a schematic diagram of an online damage control device module for hot-end components of an aero-engine, according to a preferred embodiment of this application.

[0073] Figure 6 This is a schematic block diagram of an electronic device according to a preferred embodiment of this application.

[0074] Figure 7 This is an internal structural diagram of a computer device according to a preferred embodiment of this application. Detailed Implementation

[0075] It should be understood that the specific embodiments described herein are merely illustrative of the technical solutions of this application and are not intended to limit this application.

[0076] To better understand the technical solution of this application, a detailed description will be provided below in conjunction with the accompanying drawings and specific implementation methods.

[0077] It should be noted that the executing entity in this embodiment can be a computing service device with data processing, network communication, and program execution functions, such as a tablet computer, personal computer, or mobile phone, or an online damage control device for hot-end components of an aero-engine capable of performing the above functions. The following description uses an online damage control device for hot-end components of an aero-engine as the executing entity to illustrate this embodiment and the subsequent embodiments.

[0078] like Figure 1 As shown, a preferred embodiment of this application provides a method for online control of damage to hot-end components of an aero-engine, including the following steps:

[0079] S1. Establish a time-varying damage dynamics model for the hot-end component and calculate the model parameters;

[0080] S2. Online reconstruction of the control design model: The time-varying damage dynamics model is fused with the aero-engine model. The control-oriented fused control design model is reconstructed in real time during each control cycle, and the final fused control design model parameters are calculated.

[0081] S3. Construct control instructions that take into account instantaneous damage amount, wherein the control instructions include master control parameter instructions and virtual control instructions that are positively correlated with instantaneous damage amount;

[0082] S4. Real-time optimization control: Establish and solve the optimization function to obtain the control increment at time k. And sum the control quantity at time k-1 with the control increment at time k. The engine is controlled as a control variable;

[0083] S5. Repeat the above steps until the control tasks for all moments are completed.

[0084] The advantages of the online damage control method for hot-end components of aero-engines provided in this embodiment compared to existing technologies include:

[0085] This embodiment designs a time-varying damage dynamics model for the component and performs online reconstruction of the control design model, which can be well integrated with the system dynamic model. This allows for precise consideration of the component's instantaneous damage during the optimization process. Compared with the traditional static damage prediction model, the online control method in this embodiment can achieve precise online control of component damage.

[0086] This embodiment designs a virtual control command for component damage, which is integrated with the main control parameter command. Combined with the optimization problem solution, it can operate stably during the long-term use of the aero-engine. Compared with the traditional method, the online control method of this embodiment avoids the phenomenon that the accumulation of damage leads to an increase in its weight in the optimization objective, and prevents the main control parameter (such as speed) tracking error from increasing and the transient performance from declining after the aero-engine has been used for a long period of time.

[0087] Compared with methods such as modifying the transient control plan of an aero-engine or limiting rotor acceleration, the online control method in this embodiment quantitatively considers the impact of component damage on the engine transient control process and adopts model-based control, which is suitable for controlling the magnitude of component damage within the entire envelope of an aero-engine.

[0088] Preferably, step S1 specifically includes the following steps:

[0089] S11. Establish a time-varying damage dynamics model for the hot-end component and calculate the model parameters as follows:

[0090] ;

[0091] In the formula, the system matrix of the time-varying damage dynamics model is: The input matrix of the time-varying damage dynamics model is ,in, , , These are the linear models of the steady-state point of the aero-engine (see equation). The parameters of the aero-engine steady-state linear model are as follows:

[0092] ;

[0093] Where k1 is the rate of change of damage relative to the rate of change of damage-related parameters. The gain coefficient k1;

[0094] S12. Considering the elastic damage caused by radial stress in a high-pressure turbine disk, select... These are state parameters, including the high-voltage rotor speed. and low-pressure rotor speed The rate of change of damage-related parameters is taken as Then the gain coefficient The calculation is as follows:

[0095] ;

[0096] In the formula, These are constants related to the turbine disk structure. The density of the turbine disk material. The outer diameter of the high-pressure shaft. The outer diameter of the turbine disk. For stress, For reference stress, The fatigue strength coefficient, The fatigue strength index is given by: where the stress is calculated as follows:

[0097] ;

[0098] In the formula, ω is the rotor angular velocity.

[0099] This embodiment establishes a time-varying damage dynamics model for hot-end components and calculates model parameters through steps S11-S12. Its advantages include: enabling the control process to consider instantaneous damage to components, thereby achieving the effect of online precise control of damage within the entire envelope of the aero-engine.

[0100] Preferably, step S2 includes the following steps:

[0101] S21. Integrate the time-varying damage dynamics model with the aero-engine model, reconstruct the control-oriented fusion control design model in real time during each control cycle, and calculate the model matrix parameters. , , , :

[0102] ;

[0103] In the formula, For the state of the fusion model, For the output of the fusion model, the parameters of each model matrix are calculated as follows:

[0104] ;

[0105] S22. The fusion control design model is processed according to the control cycle. Discretize to obtain , , , Discretized model parameters , , , Integral control is introduced into the discretized fusion control design model and model parameters to obtain the final control design model parameters and control design model.

[0106] This embodiment realizes real-time online reconstruction of the control design model through steps S21~S22, which has the following advantages: introducing integral action to reduce instruction tracking error.

[0107] Further, in step S22, the fusion control design model is processed according to the control cycle. During discretization, the forward Euler method is used for discretization. The discretized fusion control design model and model parameters are as follows:

[0108] ;

[0109] ;

[0110] By introducing integral control, the final control design model parameters are obtained:

[0111] .

[0112] This embodiment uses the forward Euler method for discretization to obtain the discretized fusion control design model and model parameters. Its advantages include: simplicity of implementation and low computational cost. The forward Euler method is an explicit method with simple calculation formulas, easy to program, and suitable for the rapid computation requirements of real-time control systems. Simultaneously, the parameters are traceable and easy to adjust. During discretization, the model parameters have clear physical meanings, facilitating parameter adjustment according to actual needs such as the sampling period, thus improving the system's flexibility and adaptability. Numerical stability is controllable. With an appropriate sampling period, the forward Euler method can guarantee the numerical stability of the system, meeting practical engineering requirements. In addition, the inverse difference method, zero-order hold method, etc., can also be used for discretization.

[0113] Preferably, step S3 specifically includes the following steps:

[0114] S31. Construct control instructions that consider instantaneous damage, control instructions at time k. Build as:

[0115] ;

[0116] In the formula, Master control parameter commands, For damaging virtual instructions, Designed as follows:

[0117] ;

[0118] In the formula, and Take a positive integer. The larger the component, the less damage it will sustain. , Represents the instantaneous damage amount and is estimated in real time by updating the following formula.

[0119] ;

[0120] Among them, T s To control the cycle, A dam B is the system matrix of the time-varying damage dynamics model. dam This is the input matrix for the time-varying damage dynamics model.

[0121] This embodiment uses S31 to construct control commands that take into account instantaneous damage. Its advantages include: since instantaneous damage is used instead of absolute damage, the phenomenon that damage accumulation leads to an increase in its weight in the optimization objective is avoided, and the tracking error of main control parameters (such as speed) and the decline in transient performance are prevented after long-term use of the aero-engine.

[0122] Preferably, step S4 specifically includes the following steps:

[0123] S41. Real-time optimization control: Establish the following optimization function and solve it to obtain the control increment at time k. and will The engine is controlled as a control variable:

[0124] (14);

[0125] In the formula, R and R are the tracking error weighting matrix and the control quantity weighting matrix, respectively, both of which are diagonal matrices. , As the balance factor, q j This represents the weighted value of the tracking error for the j-th instruction. and These are the lower and upper limits of the control quantity, respectively. and These are the lower and upper limits of the output, respectively.

[0126] This embodiment uses S41 to achieve real-time optimization control. Its advantages include: it can simultaneously consider the two objectives of high command tracking accuracy and low damage. In addition, besides using formula (14) for optimization, it can also use quadratic programming, sequential quadratic programming, heuristic algorithms, nonlinear optimization methods, etc. for optimization.

[0127] Preferably, step S3 further includes the following steps:

[0128] S32. Real-time update of estimated instantaneous damage. The health management top-level controller of the aircraft engine is transmitted to the health management top-level controller, which dynamically adjusts the balance factor according to the flight mission. The dynamic adjustment strategy is as follows:

[0129] (13);

[0130] in, The larger the value, the less damage to the component. The smaller the value, the better the tracking performance of the master control parameters.

[0131] Compared with existing technologies, this embodiment provides a two-way interaction method with the top-level health management controller. This method can provide real-time feedback on component damage status and receive adjustment commands from the top-level health management controller, achieving online adjustment of component damage according to different flight missions, thereby balancing the tracking performance of main control parameters with the magnitude of component damage. The two-way interaction method with the top-level health management controller of the aero-engine is not limited to interaction or parameters; any parameters representing the optimization target based on the component damage status are acceptable.

[0132] This application has been verified through simulation and experiments, proving the feasibility of its technical solution and its ability to significantly improve the modeling accuracy, real-time simulation capability, and fault diagnosis accuracy of aero-engines. In ground simulation verification, a high-precision digital prototype was used to dynamically simulate typical operating conditions of a certain type of aero-engine (such as high-altitude low temperature and high-speed cruise). The error between the output key performance parameters (such as thrust, fuel consumption rate, and temperature field distribution) and the actual measured data was controlled within 5%, demonstrating excellent simulation accuracy.

[0133] This application has been verified through simulation and experiments, proving the feasibility of its technical solution. Taking the acceleration process of a turbofan engine as an example, Figure 3 For comparison of turbine disk damage, Figure 4 As can be seen from the comparison of speed changes, the method of this application results in lower turbine disk damage without sacrificing acceleration performance. Therefore, the method of this application is feasible.

[0134] like Figure 5 As shown, another preferred embodiment of this application also provides an online damage control device for hot-end components of an aero-engine, comprising:

[0135] The time-varying damage dynamics model establishment module is used to establish a time-varying damage dynamics model for hot-end components and calculate model parameters;

[0136] The online reconstructing module for the control design model is used for online reconstruction of the control design model. It integrates the time-varying damage dynamics model with the aero-engine model, reconstructs the control-oriented fusion control design model in real time during each control cycle, and calculates the final fusion control design model parameters.

[0137] A control instruction construction module is used to construct control instructions that take into account instantaneous damage, wherein the control instructions include master control parameter instructions and virtual control instructions that are positively correlated with instantaneous damage.

[0138] The real-time optimization control module is used for real-time optimization control. It establishes and solves the optimization function to obtain the control increment at time k. And sum the control quantity at time k-1 with the control increment at time k. The engine is controlled as a control variable;

[0139] The loop control module is used to repeat the aforementioned steps until the control task for all time periods is completed.

[0140] The online damage control device for hot-end components of aero-engines provided in this application employs the online damage control method for hot-end components of aero-engines described in the above embodiments. This method addresses the technical problems of existing technologies, such as qualitative analysis only, insufficient optimization accuracy, large computational load, and limited damage reduction effects. Compared with existing technologies, the beneficial effects of the online damage control device for hot-end components of aero-engines provided in this application are the same as those of the online damage control method for hot-end components of aero-engines provided in the above embodiments. Furthermore, other technical features of the online damage control device for hot-end components of aero-engines are the same as those disclosed in the methods of the above embodiments, and will not be repeated here.

[0141] like Figure 6 As shown, a preferred embodiment of this application also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the steps of the online control method for damage to hot-end components of an aero-engine described in the above embodiments.

[0142] The electronic device provided in this application employs the online damage control method for hot-end components of aero-engines described in the above embodiments, which can solve the technical problems of existing technologies that can only perform qualitative analysis, have insufficient optimization accuracy, require large computational loads, and have limited damage reduction effects. Compared with the prior art, the beneficial effects of the electronic device provided in this application are the same as those of the online damage control method for hot-end components of aero-engines provided in the above embodiments, and other technical features of the electronic device are the same as those disclosed in the methods of the above embodiments, and will not be repeated here.

[0143] like Figure 7 As shown, a preferred embodiment of this application also provides a computer device, which may be a terminal or a liveness detection server, and its internal structure diagram may be as follows. Figure 7As shown, the computer device includes a processor, memory, and a network interface connected via a system bus. The processor provides computing and control capabilities. The memory includes a non-volatile storage medium and internal memory. The non-volatile storage medium stores the operating system and computer programs. The internal memory provides an environment for the operation of the operating system and computer programs in the non-volatile storage medium. The network interface is used to communicate with other external computer devices via a network connection. When the computer program is executed by the processor, it implements the steps of the aforementioned online damage control method for hot-end components of an aero-engine.

[0144] Those skilled in the art will understand that Figure 7 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.

[0145] The computer equipment provided in this application, employing the online damage control method for hot-end components of aero-engines described in the above embodiments, can solve the technical problems of existing technologies that can only perform qualitative analysis, have insufficient optimization accuracy, require large computational loads, and have limited damage reduction effects. Compared with the prior art, the beneficial effects of the computer equipment provided in this application are the same as those of the online damage control method for hot-end components of aero-engines provided in the above embodiments, and other technical features in the electronic equipment are the same as those disclosed in the methods of the above embodiments, and will not be repeated here.

[0146] A preferred embodiment of this application also provides a storage medium, the storage medium including a stored program, which, when the program is executed, controls the device where the storage medium is located to perform the steps of the online control method for damage to hot-end components of an aero-engine in the above embodiments.

[0147] It should be noted that the steps shown in the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions, and although a logical order is shown in the flowchart, in some cases the steps shown or described may be executed in a different order than that shown here.

[0148] If the functions described in this embodiment are implemented as software functional units and sold or used as independent products, they can be stored in one or more computing device-readable storage media. Based on this understanding, the parts of this application's embodiments that contribute to the prior art or the technical solutions can be embodied in the form of a software product. This software product is stored in a storage medium and includes several instructions to cause a computing device (which may be a personal computer, server, mobile computing device, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this application. The aforementioned storage media include: USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, optical disks, and other media capable of storing program code.

[0149] Those skilled in the art will understand that embodiments of this application can be provided as methods, systems, or computer program products. Therefore, this application can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this application can take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code. The solutions in the embodiments of this application can be implemented in various computer languages, such as the object-oriented programming language Java and the interpreted scripting language JavaScript.

[0150] This application is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of this application. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart... Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0151] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1The function specified in one or more boxes.

[0152] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0153] This application also provides a computer program product, including a computer program that, when executed by a processor, implements the steps of the above-described method for online control of damage to hot-end components of an aero-engine.

[0154] The computer program product provided in this application can solve the technical problems of existing technologies, such as only being able to perform qualitative analysis, insufficient optimization accuracy, large computational load, and limited damage reduction effect. Compared with the prior art, the beneficial effects of the computer program product provided in this application are the same as those of the online control method for damage of hot-end components of aero-engines provided in the above embodiments, and will not be repeated here.

[0155] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application.

[0156] Obviously, those skilled in the art can make various modifications and variations to this application without departing from the spirit and scope of this application. Therefore, if such modifications and variations fall within the scope of the claims of this application and their equivalents, this application also intends to include such modifications and variations.

Claims

1. A method for online control of damage to hot-end components of an aero-engine, characterized in that, Including the following steps: S1. Establish a time-varying damage dynamics model for the hot-end component and calculate the model parameters; S2. Online reconstruction of the control design model: The time-varying damage dynamics model is fused with the aero-engine model. The control-oriented fused control design model is reconstructed in real time during each control cycle, and the final fused control design model parameters are calculated. S3. Construct control instructions that take into account instantaneous damage amount, wherein the control instructions include master control parameter instructions and virtual control instructions that are positively correlated with instantaneous damage amount; S4. Real-time optimization control: Establish and solve the optimization function to obtain the control increment Δu(k) at time k, and use the sum of the control quantity at time k-1 and the control increment at time k, u(k-1)+Δu(k), as the control quantity to control the engine. S5. Repeat the above steps until the control tasks for all moments are completed.

2. The method for online control of damage to hot-end components of an aero-engine according to claim 1, characterized in that, Step S1 specifically includes the following steps: S11. Establish a time-varying damage dynamics model for the hot-end component and calculate the model parameters as follows: In the formula, the system matrix of the time-varying damage dynamics model is A. dam =k1E a A a The input matrix of the time-varying damage dynamics model is B. dam =k1E a B a , where A a E a B a These are the parameters of the linear model of the aero-engine's steady-state point, which is: Where k1 is the rate of change of damage relative to the rate of change of damage-related parameters. The gain coefficient k1; S12. Considering the elastic damage caused by radial stress in a high-pressure turbine disk, select x = [N H N L ] T These are state parameters, including the high-voltage rotor speed N. H and low-pressure rotor speed N L The rate of change of damage-related parameters is taken as The gain coefficient k1 is calculated as follows: In the formula, υ is a constant related to the turbine disk structure, ρ is the density of the turbine disk material, a0 is the outer diameter of the high-pressure shaft, b0 is the outer diameter of the turbine disk, σ is the stress, and σ r For reference stress, σ′ f Let be the fatigue strength coefficient, and b be the fatigue strength exponent. The stress is calculated as follows: In the formula, ω is the rotor angular velocity.

3. The method for online control of damage to hot-end components of an aero-engine according to claim 2, characterized in that, Step S2 includes the following steps: S21. Integrate the time-varying damage dynamics model with the aero-engine model, reconstruct the control-oriented fusion control design model in real time during each control cycle, and calculate the model matrix parameters A. aug B aug C aug D aug : In the formula, x aug =[x,δ e ] T For the state of the fusion model, y aug =[y,δ e ] T For the output of the fusion model, the parameters of each model matrix are calculated as follows: S22. The fusion control design model is applied according to the control period T. s Discretize to obtain A respectively aug B aug C aug D aug Discretized model parameters A d B d C d D d Integral control is introduced into the discretized fusion control design model and model parameters to obtain the final control design model parameters and control design model.

4. The method for online control of damage to hot-end components of an aero-engine according to claim 3, characterized in that, In step S22, the fusion control design model is processed according to the control period T. s During discretization, the forward Euler method is used for discretization. The discretized fusion control design model and model parameters are as follows: A d =I+T s A aug ,B d =T s B aug ,C d =C aug ,D d =D aug (8) By introducing integral control, the final control design model parameters are obtained:

5. The method for online control of damage to hot-end components of an aero-engine according to claim 4, characterized in that, Step S3 specifically includes the following steps: S31. Construct control instructions that consider instantaneous damage. The control instruction r(k) at time k is constructed as follows: r(k)=[r mc (k),r dam (k)] T (10) In the formula, r mc (k) is the master control parameter instruction, r dam (k) represents the damage virtual instruction, r dam (k) is designed as follows: In the formula, n z j takes positive integer values; the larger j is, the less damage the component will suffer. j = n z =3,δ e The instantaneous damage is represented and estimated in real time using the following formula: δ e (k+1)=δ e (k)+T s A dam x(k)+T s B dam u(k) (12) Among them, T s To control the cycle.

6. The method for online control of damage to hot-end components of an aero-engine according to claim 5, characterized in that, Step S4 specifically includes the following steps: S41. Real-time optimization control: Establish the following optimization function and solve it to obtain the control increment Δu(k) at time k, and use u(k-1)+Δu(k) as the control quantity to control the engine: In the formula, Q and R are the tracking error weighting matrix and the control quantity weighting matrix, respectively, both of which are diagonal matrices, where Q = diag([q1,q2,...,k δ q j ]), k δ As the balance factor, q j This represents the weighted value of the tracking error for the j-th instruction. U and These are the lower and upper limits of the control quantity, respectively. Y and These are the lower and upper limits of the output, respectively.

7. The method for online control of damage to hot-end components of an aero-engine according to claim 6, characterized in that, Step S3 further includes the following steps: S32. Real-time update of the estimated instantaneous damage δ e The health management information is transmitted to the top-level controller of the aircraft engine, which dynamically adjusts the balance factor k based on the flight mission. δ The dynamic adjustment strategy is as follows: Where, k δ The larger the value of k, the less damage to the component. δ The smaller the value, the better the tracking performance of the master control parameters.

8. An online damage control device for hot-end components of an aero-engine, characterized in that, include: The time-varying damage dynamics model establishment module is used to establish a time-varying damage dynamics model for hot-end components and calculate model parameters; The online reconstructing module for the control design model is used for online reconstruction of the control design model. It integrates the time-varying damage dynamics model with the aero-engine model, reconstructs the control-oriented fusion control design model in real time during each control cycle, and calculates the final fusion control design model parameters. A control instruction construction module is used to construct control instructions that take into account instantaneous damage, wherein the control instructions include master control parameter instructions and virtual control instructions that are positively correlated with instantaneous damage. The real-time optimization control module is used for real-time optimization control. It establishes and solves the optimization function to obtain the control increment Δu(k) at time k. The sum of the control quantity at time k-1 and the control increment at time k, u(k-1)+Δu(k), is used as the control quantity to control the engine. The loop control module is used to repeat the aforementioned steps until the control task for all time periods is completed.

9. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the computer program, it implements the steps of the online control method for damage to hot-end components of an aero-engine as described in any one of claims 1 to 7.

10. A storage medium comprising a stored program that, when the program is executed, controls a device in which the storage medium is located to perform the steps of the online damage control method for hot-end components of an aero-engine as described in any one of claims 1 to 7.

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