Emission control method and device of water injection aero-engine and computer equipment

Abstract

The invention relates to an emission control method and device of a water injection aero-engine and computer equipment. The method comprises the steps that system architecture information of an emission control system of the water injection aero-engine and flight operation information of the water injection aero-engine are acquired, and a self-adaptive control model of the emission control system is constructed based on the system architecture information; based on the flight operation information, generating simulation stage thrust information of each operation stage, and based on the simulation stage thrust information of each operation stage, identifying simulation engine operation information of each operation stage; generating a simulation operation result of each operation stage through a self-adaptive control model based on the operation information of each simulation engine, and identifying a system control scheme of each operation stage based on the simulation operation result of each operation stage; therefore, the system is controlled to operate. By adopting the method, the nitrogen oxide emission control efficiency of the aero-engine can be improved.

Description

Technical Field

[0001] The present application relates to the technical field of aeroengines, and particularly to a method, device and computer equipment for controlling emissions of a water-injected aeroengine. Background Art

[0002] When the flame combustion temperature is higher than 1516K, the emissions of nitrogen oxides will increase significantly. The combustion flame temperature has a significant impact on the rate of nitrogen oxides generated during the combustion process. Due to the high calorific value of hydrogen fuel, the combustion temperature in the combustion chamber is higher than that of a conventional kerosene engine. The high flame temperature is likely to cause the generation of NOx. However, a large amount of nitrogen oxides will cause environmental pollution. Therefore, how to reduce the NOx emissions of hydrogen fuel engines is the current research focus.

[0003] The existing technology is a dry method, that is, a lean premixed combustion chamber can be used to prevent the emission of NOx. However, the dry method is more prone to flameout and thermoacoustic oscillations. At the same time, the dry method requires the design of control strategies for multiple valves, the controller design is cumbersome, the cost is high, and the cumbersome controller design will affect the efficiency conversion ratio of the aeroengine, resulting in a low control efficiency for the nitrogen oxide emissions of the aeroengine. Summary of the Invention

[0004] Based on this, in view of the above technical problems, it is necessary to provide a method, device, computer equipment, computer-readable storage medium and computer program product for controlling emissions of a water-injected aeroengine.

[0005] In a first aspect, the present application provides a method for controlling emissions of a water-injected aeroengine, including:

[0006] Obtaining the system architecture information of the emissions control system of the water-injected aeroengine and the flight operation information of the water-injected aeroengine, and based on the system architecture information, constructing an adaptive control model of the emissions control system;

[0007] Generating simulated stage thrust information for each of the operation stages based on the flight operation information, and identifying simulated engine operation information for each of the operation stages based on the simulated stage thrust information for each of the operation stages;

[0008] Generating simulated operation results for each of the operation stages through the adaptive control model based on the simulated engine operation information for each of the operation stages, and identifying a system control scheme for each of the operation stages based on the simulated operation results for each of the operation stages;

[0009] Controlling the emissions control system of the water-injected aeroengine to execute the stage operation tasks for each of the operation stages based on the system control scheme for each of the operation stages.

[0010] Optionally, constructing the adaptive control model of the emissions control system based on the system architecture information includes:

[0011] Based on the system architecture information, identify the operation information of each device structure and the operation association information between each device structure, and based on the operation information of each device structure, identify the operation parameters corresponding to the device operation logic of each device structure;

[0012] Based on the operation parameters corresponding to the device operation logic of each device structure, construct the structure operation model of each device structure, and based on the operation association information between each device structure, identify the connection information between each device structure and the data interaction logic parameters between each device structure;

[0013] Based on the connection information between each device structure, perform structure connection processing on each device structure to obtain the associated operation model of the emissions control system, and add the data interaction logic parameters between each device structure to the associated operation model to obtain the adaptive control model of the emissions control system.

[0014] Optionally, generating the simulated stage thrust information for each operation stage based on the flight operation information includes:

[0015] Split the flight operation information into sub-flight operation information for each operation stage, and for each operation stage, based on the sub-flight operation information of the operation stage, identify the flight thrust information of the operation stage and the duration of the operation stage;

[0016] Use the flight thrust information of the operation stage and the duration of the operation stage as the simulated stage thrust information of the operation stage.

[0017] Optionally, identifying the simulated engine operation information for each operation stage based on the simulated stage thrust information for each operation stage includes:

[0018] Based on the flight thrust information for each operation stage, query the engine operation database to obtain the engine operation degree information for each operation stage;

[0019] Based on the engine operation degree information for each operation stage, query the engine operation database to obtain the stage operation data range of each device structure corresponding to each operation stage and the engine input information of the water injection aero engine corresponding to each operation stage;

[0020] Based on the stage operation data ranges of each of the device structures, generate combinations of simulated operation data for each engine in the operation stage, and use the combinations of simulated operation data for each engine corresponding to each operation stage and the engine input information of the water-injected aeroengine corresponding to each operation stage as the simulated engine operation information for each operation stage.

[0021] Optionally, generating simulated operation results for each of the operation stages based on each of the simulated engine operation information through the adaptive control model includes:

[0022] For each operation stage, based on the combinations of simulated operation data for each engine in the operation stage, execute the stage operation process of the operation stage through the adaptive control model to obtain the emission information corresponding to each combination of simulated operation data for each engine;

[0023] Use the emission information corresponding to each of the combinations of simulated operation data as the simulated operation result for the operation stage.

[0024] Optionally, identifying the system control schemes for each of the operation stages based on the simulated operation results for each of the operation stages includes:

[0025] For each operation stage, generate the correlation distribution information between the stage operation data of each of the device structures and the nitrogen oxide emissions based on the emission information corresponding to each combination of simulated operation data in the operation stage;

[0026] Based on the correlation distribution information, identify the target stage operation data of each of the device structures corresponding to the lowest nitrogen oxide emissions and the target emission information corresponding to the target stage operation data of each of the device structures, and based on the target stage operation data of each of the device structures, simulate the operation process of each of the device structures through the adaptive control model to obtain the device operation flow of each of the device structures and the simulated emission information for the operation stage;

[0027] Use the target emission information corresponding to the target stage operation data of each of the device structures and the simulated emission information for the operation stage as the emission deviation information for the operation stage, and in the case where the emission deviation information is greater than the deviation information threshold, return to execute the step of, based on the combinations of simulated operation data for each engine in the operation stage, executing the stage operation process of the operation stage through the adaptive control model to obtain the stage operation data of each of the device structures corresponding to each combination of simulated operation data for each engine and the emission information corresponding to each combination of simulated operation data for each engine;

[0028] When the emission deviation information is greater than the deviation information threshold, a system control scheme for the operation phase is generated based on the device operation processes of the device structures obtained in the last iteration and the target phase operation data of the device structures obtained in the last iteration.

[0029] In a second aspect, the present application further provides an emission control device for a water-injected aeroengine, including:

[0030] An acquisition module, configured to acquire the system architecture information of the emission control system of the water-injected aeroengine and the flight operation information of the water-injected aeroengine, and construct an adaptive control model of the emission control system based on the system architecture information;

[0031] An identification module, configured to generate the simulated stage thrust information of each operation phase based on the flight operation information, and identify the simulated engine operation information of each operation phase based on the simulated stage thrust information of each operation phase;

[0032] A generation module, configured to generate the simulated operation results of each operation phase through the adaptive control model based on the simulated engine operation information of each operation phase, and identify the system control scheme of each operation phase based on the simulated operation results of each operation phase;

[0033] A control module, configured to control the emission control system of the water-injected aeroengine to execute the stage operation tasks of each operation phase based on the system control scheme of each operation phase.

[0034] Optionally, the acquisition module is specifically configured to:

[0035] Based on the system architecture information, identify the operation information of each device structure and the operation association information between each device structure, and identify each operation parameter corresponding to the device operation logic of each device structure based on the operation information of each device structure;

[0036] Based on each operation parameter corresponding to each device operation logic, construct a structure operation model of each device structure, and identify the connection information between each device structure and the data interaction logic parameters between each device structure based on the operation association information between each device structure;

[0037] Based on the connection information between each device structure, perform structure connection processing on each device structure to obtain an associated operation model of the emission control system, and add the data interaction logic parameters between each device structure to the associated operation model to obtain an adaptive control model of the emission control system.

[0038] Optionally, the recognition module is specifically configured to:

[0039] Split the flight operation information into sub-flight operation information for each operation stage, and for each operation stage, based on the sub-flight operation information of the operation stage, identify the flight thrust information of the operation stage and the duration of the operation stage;

[0040] Use the flight thrust information of the operation stage and the duration of the operation stage as the simulated stage thrust information of the operation stage.

[0041] Optionally, the recognition module is specifically configured to:

[0042] Query the engine operation database based on the flight thrust information of each operation stage to obtain the engine operation degree information of each operation stage;

[0043] Query the engine operation database based on the engine operation degree information of each operation stage to obtain the stage operation data range of each equipment structure corresponding to each operation stage and the engine input information of the water-injected aeroengine corresponding to each operation stage;

[0044] Generate the engine simulation operation data combinations of the operation stage based on the stage operation data range of each equipment structure, and use the engine simulation operation data combinations corresponding to each operation stage and the engine input information of the water-injected aeroengine corresponding to each operation stage as the simulated engine operation information of each operation stage.

[0045] Optionally, the generation module is specifically configured to:

[0046] For each operation stage, based on the engine simulation operation data combinations of the operation stage, execute the stage operation process of the operation stage through the adaptive control model to obtain the emission information corresponding to each engine simulation operation data combination;

[0047] Use the emission information corresponding to each simulation operation data combination as the simulated operation result of the operation stage.

[0048] Optionally, the generation module is specifically configured to:

[0049] For each operation stage, generate the correlation distribution information between the stage operation data of each equipment structure and the nitrogen oxide emissions based on the emission information corresponding to the simulation operation data combinations of the operation stage;

[0050] Based on the associated distribution information, identify the target stage operation data of each of the device structures corresponding to the emissions of the lowest nitrogen oxide emissions, and the target emission information corresponding to the target stage operation data of each of the device structures. Then, based on the target stage operation data of each of the device structures, through the adaptive control model, simulate the operation process of each of the device structures to obtain the device operation flow of each of the device structures and the simulated emission information of the operation stage.

[0051] Based on the target emission information corresponding to the target stage operation data of each of the device structures and the simulated emission information of the operation stage, use them as the emission deviation information of the operation stage. When the emission deviation information is greater than the deviation information threshold, return to execute the step of performing the stage operation process of the operation stage through the adaptive control model based on each combination of engine simulated operation data of the operation stage, and obtain the stage operation data of each device structure corresponding to each combination of engine simulated operation data and the emission information corresponding to each combination of engine simulated operation data.

[0052] Until the emission deviation information is greater than the deviation information threshold, generate the system control scheme for the operation stage based on the device operation flow of each of the device structures obtained from the last iteration and the target stage operation data of each of the device structures obtained from the last iteration.

[0053] In a third aspect, the present application provides a computer device. The computer device includes a memory and a processor. The memory stores a computer program, and when the processor executes the computer program, it implements the steps of the method described in any one of the first aspects.

[0054] In a fourth aspect, the present application provides a computer-readable storage medium. A computer program is stored thereon, and when the computer program is executed by a processor, it implements the steps of the method described in any one of the first aspects.

[0055] In a fifth aspect, the present application provides a computer program product. The computer program product includes a computer program, and when the computer program is executed by a processor, it implements the steps of the method described in any one of the first aspects.

[0056] The above-mentioned emission control method, device and computer equipment for water-injected aeroengines obtain the system architecture information of the emission control system of the water-injected aeroengine and the flight operation information of the water-injected aeroengine, and construct an adaptive control model of the emission control system based on the system architecture information; generate simulated stage thrust information for each of the operation stages based on the flight operation information, and identify the simulated engine operation information for each of the operation stages based on the simulated stage thrust information for each of the operation stages; generate simulated operation results for each of the operation stages through the adaptive control model based on each of the simulated engine operation information, and identify the system control scheme for each of the operation stages based on the simulated operation results for each of the operation stages; control the emission control system of the water-injected aeroengine to execute the stage operation tasks for each of the operation stages based on the system control scheme for each of the operation stages. In this solution, by constructing an emission control system for a water-injected aeroengine, the flame temperature is reduced by injecting water vapor into the aeroengine to reduce nitrogen oxide emissions, avoiding the problem of cumbersome controller design. Moreover, in actual control, this solution constructs an adaptive control model of the above system to simulate the engine operation information of the water-injected aeroengine in different operation stages, thereby generating a system control scheme for each operation stage, ensuring that while reducing the flame temperature by injecting water vapor, the nitrogen oxide emissions in different operation stages are minimized, so as to improve the control accuracy of nitrogen oxide emissions. Finally, this solution adaptively generates the target system control scheme for different operation stages through simulation analysis, thus eliminating the cumbersome steps of designing multiple controllers and generating multiple control strategies for manual valve control, and adaptively and efficiently generating the emission control scheme for the aeroengine in different operation stages, thereby comprehensively improving the management and control efficiency of nitrogen oxide emissions of the aeroengine. BRIEF DESCRIPTION OF THE DRAWINGS

[0057] In order to more clearly illustrate the technical solutions in the embodiments of the present application or related technologies, the following will briefly introduce the drawings required for the description of the embodiments or related technologies. Obviously, the following drawings are only some embodiments of the present application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0058] Figure 1 It is a schematic diagram of the system structure of the emission control system of a water-injected aeroengine in an embodiment;

[0059] Figure 2 It is a schematic flowchart of the emission control method of a water-injected aeroengine in an embodiment;

[0060] Figure 3Schematic diagram of the engine structure of a water-injected aeroengine in an embodiment;

[0061] Figure 4 Schematic diagram of the stage decomposition in each operation stage in an embodiment;

[0062] Figure 5 Schematic flow diagram of the emissions control example of a water-injected aeroengine in an embodiment;

[0063] Figure 6 Block diagram of the structure of the emissions control device of a water-injected aeroengine in an embodiment;

[0064] Figure 7 Internal structure diagram of a computer device in an embodiment. Detailed implementation manners

[0065] In order to make the objectives, technical solutions and advantages of the present application clearer and more understandable, the present application will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0066] The emissions control method of the water-injected aeroengine provided by the embodiments of the present application can be applied to the emissions control system of the water-injected aeroengine, such as Figure 1As shown, it is the system operation structure diagram of the emission control system of a water-injected aeroengine. In this system operation structure diagram, a metering valve, a water vapor injection valve, and a state space prediction model are respectively connected to the water-injected aeroengine. The metering valve, the water vapor injection valve, and the state space prediction model are respectively connected to an adaptive emission controller. Among them, for the hydrogen flow rate of this system, a metering valve needs to be connected in series in front of the engine to provide hydrogen with a certain flow rate and pressure. The water vapor needs an injection valve to inject a certain mass of water vapor into the combustion chamber to reduce the nitrogen oxide emissions in the combustion chamber. After the water-injected aeroengine receives two control quantities, it will reach a new operating point. At this time, the speed sensor will obtain a speed measurement value, which is also the scheduling parameter of the LPV model (i.e., the state space prediction model), so as to obtain a new predicted state space model. The adaptive MPC controller (i.e., the adaptive emission controller) uses the predicted state space model to perform internal optimization calculations, and then obtains a water injection command quantity and a hydrogen command quantity, which are transmitted to the metering valve to generate the actual hydrogen quantity leading to the engine, and are transmitted to the water vapor injection valve to generate the actual water injection quantity leading to the engine. Among them, this system can be applied to a terminal, which can be but is not limited to the control computers of various aeroengines, etc. The terminal constructs an adaptive control model of the above system, thereby simulating the engine operation information of the water-injected aeroengine at different operation stages, and then generating a system control scheme for each operation stage, so as to ensure the lowest nitrogen oxide emissions in different operation stages while reducing the flame temperature by means of injecting water vapor, so as to improve the control accuracy of nitrogen oxide emissions. Finally, through the method of simulation analysis, this solution adaptively generates the target system control scheme for different operation stages, thereby eliminating the cumbersome design of multiple controllers and the cumbersome steps of generating multiple control strategies for manual valve control, and thus adaptively and efficiently generating the emission control scheme of the aeroengine at different operation stages, thereby comprehensively improving the control efficiency of nitrogen oxide emissions of the aeroengine.

[0067] In an exemplary embodiment, as Figure 2 shown, a method for controlling emissions of a water-injected aeroengine is provided. Taking the application of this method to a terminal as an example, it includes the following steps S201 to S204. Among them:

[0068] Step S201: Obtain the system architecture information of the emission control system of the water-injected aeroengine and the flight operation information of the water-injected aeroengine, and construct an adaptive control model of the emission control system based on the system architecture information.

[0069] In this embodiment, the terminal obtains the system architecture information of the emission control system of the water-injected aeroengine in response to the information uploading operation of the staff. The system architecture information includes the structures of the devices included in the system, as well as the connection relationships, operation modes, and association information between the device structures. As Figure 2 shown, it is a schematic diagram of the structure of the adaptive emission control unit included in the system. As Figure 3 shown, it is a schematic diagram of the structure of the water-injected aeroengine included in the system. The connection relationships between the device structures and the data interaction relationships between the device structures are marked in the above two schematic diagrams. Then, the terminal obtains the flight operation information of the water-injected aeroengine. The flight operation information includes sub-flight operation information of each operation stage. The water-injected aeroengine is a single-shaft turbojet engine J85-13. The operation stage is as Figure 4 shown as the LTO cycle stage, and this cycle stage consists of four stages: approach stage, taxi stage, takeoff stage, and climb stage. The thrust level and duration of each stage are respectively:

[0070] (1) Takeoff: (100% available thrust) for 0.7 minutes;

[0071] (2) Climb: (85% available thrust) for 2.2 minutes;

[0072] (3) Approach: (30% available thrust) for 4.0 minutes;

[0073] (4) Taxi: (7% available thrust) for 26 minutes.

[0074] The specific recognition process will be described in detail later.

[0075] Step S202: Generate simulated stage thrust information for each operation stage based on the flight operation information, and identify the simulated engine operation information for each operation stage based on the simulated stage thrust information for each operation stage.

[0076] In this embodiment, the terminal generates simulated stage thrust information for each operation stage based on flight operation information, and identifies simulated engine operation information for each operation stage based on the simulated stage thrust information for each operation stage. Among them, the simulated stage thrust information includes the flight thrust information of this operation stage and the duration of this operation stage, and the simulated engine operation information for each operation stage includes the combination of simulated operation data of each engine corresponding to each operation stage and the engine input information of the water injection aeroengine corresponding to each operation stage. Among them, the combination of simulated operation data of each engine includes the single simulated operation data of each equipment structure. The engine input information includes input information such as the content information of the input air, the mass data of liquid hydrogen, and the density of water vapor. The specific identification process will be described in detail later.

[0077] Step S203: Based on the simulated engine operation information for each operation stage, generate simulated operation results for each operation stage through an adaptive control model, and identify the system control scheme for each operation stage based on the simulated operation results for each operation stage.

[0078] In this embodiment, the terminal generates simulated operation results for each operation stage through an adaptive control model based on the simulated engine operation information for each operation stage, and identifies the system control scheme for each operation stage based on the simulated operation results for each operation stage. Among them, the system control scheme for each operation stage is the control scheme with the lowest emission of nitrogen oxide emissions under the conditions of this operation stage. The system control scheme includes the equipment operation process of each equipment structure and the target stage operation data of each equipment structure. The specific generation process will be described in detail later.

[0079] Step S204: Based on the system control scheme for each operation stage, control the emission control system of the water injection aeroengine to execute the stage operation tasks for each operation stage.

[0080] In this embodiment, the terminal controls the emission control system of the water injection aeroengine to execute the stage operation tasks for each operation stage based on the system control scheme for each operation stage. Among them, the stage operation tasks for each operation stage are that the terminal controls the above system to execute the system control scheme corresponding to different stages during different operation stages, so as to control the operation process of each equipment structure.

[0081] Based on the above solution, by constructing the adaptive control model of the above system, the engine operation information of the water-injected aeroengine at different operation stages is simulated, and the system control scheme for each operation stage is generated, so that while reducing the flame temperature in the way of injecting water vapor, the nitrogen oxide emissions at different operation stages are ensured to be the lowest, so as to improve the control accuracy of the nitrogen oxide emissions. Finally, through the simulation analysis method, this solution adaptively generates the target system control scheme for different operation stages, thus eliminating the cumbersome design of multiple controllers and the cumbersome steps of generating multiple control strategies for manual valve control, and thus adaptively and efficiently generating the emission control scheme of the aeroengine at different operation stages, thereby comprehensively improving the control efficiency of the nitrogen oxide emissions of the aeroengine.

[0082] Optionally, based on the system architecture information, construct an adaptive control model of the emission control system, including: based on the system architecture information, identify the operation information of each device structure and the operation association information between each device structure, and based on the operation information of each device structure, identify the operation parameters corresponding to the device operation logic of each device structure; based on the operation parameters corresponding to each device operation logic, construct the structure operation model of each device structure, and based on the operation association information between each device structure, identify the connection information between each device structure and the data interaction logic parameters between each device structure; based on the connection information between each device structure, perform structure connection processing on each device structure to obtain the associated operation model of the emission control system, and add the data interaction logic parameters between each device structure to the associated operation model to obtain the adaptive control model of the emission control system.

[0083] In this embodiment, the terminal, based on the system architecture information, identifies the operation information of each device structure and the operation association information between each device structure, and based on the operation information of each device structure, identifies the operation parameters corresponding to the device operation logic of each device structure. Specifically, the terminal queries the historical operation data of each device structure in the engine operation database of the water-injected aeroengine to obtain the operation information of each device structure. Then, the terminal queries the operation data range corresponding to different device operation logics in the historical operation data of each device structure. Finally, the terminal, through the parameter conversion strategy, converts each operation data range into the operation parameters of each device structure. Among them, the terminal presets the parameter conversion strategy for each device structure, and this parameter conversion strategy is used to convert the operation data of each device structure into operation parameters. And this parameter conversion strategy is obtained by the staff through the operation modeling method after a large number of simulation simulations of the simulation process between the operation data of the device structure and the model operation parameters of the structure operation model, and the association information between the operation data of each device structure and the operation parameters is used as this parameter conversion strategy.

[0084] Based on the operating parameters corresponding to the operating logics of each device, the terminal constructs a structural operating model for each device structure, and based on the operating association information between the device structures, identifies the connection information between the device structures and the data interaction logic parameters between the device structures. Among them, the data interaction logic parameter is the associated data corresponding to the association information between the input data and the output data in each data interaction process in the data interaction logic information between the device structures. After parameterization processing, the obtained data interaction logic parameter. For example, the data interaction logic between the metering valve and the adaptive emission controller is that after the adaptive emission controller inputs the hydrogen instruction amount into the metering valve, the metering valve identifies the hydrogen amount to be input into the water injection aero-engine based on the hydrogen instruction amount. Among them, the association information is the hydrogen instruction amount, and the associated data is to convert the hydrogen instruction amount into the hydrogen amount. Then, the terminal presets the conversion program between the hydrogen instruction amount and the hydrogen amount in the metering valve. Then, the terminal converts the hydrogen instruction amount into the hydrogen amount, and after parameterizing the hydrogen amount, obtains the input hydrogen parameter that the model needs to simulate as the data interaction logic parameter.

[0085] Based on the connection information between the device structures, the terminal performs structural connection processing on the device structures to obtain an associated operating model of the emission control system, and adds the data interaction logic parameters based on the device structures to the associated operating model to obtain an adaptive control model of the emission control system.

[0086] Based on the above solution, by combining the operating information, operating association information, and connection information between the device structures, an adaptive control model of the emission control system is constructed, improving the simulation accuracy and model adaptability of constructing the adaptive control model.

[0087] Optionally, based on the flight operation information, simulated stage thrust information for each operation stage is generated, including: splitting the flight operation information into sub-flight operation information for each operation stage, and for each operation stage, based on the sub-flight operation information of the operation stage, identifying the flight thrust information of the operation stage and the duration of the operation stage; using the flight thrust information of the operation stage and the duration of the operation stage as the simulated stage thrust information for the operation stage.

[0088] In this embodiment, the terminal splits the flight operation information into sub-flight operation information for each operation stage, and for each operation stage, based on the sub-flight operation information of the operation stage, identifies the flight thrust information of the operation stage and the duration of the operation stage. Finally, the terminal uses the flight thrust information of the operation stage and the duration of the operation stage as the simulated stage thrust information for the operation stage.

[0089] Based on the above solution, by splitting and analyzing each operation stage, the thrust information of the simulation stage in each operation stage is obtained, so that the flight mission of the aircraft is transformed into the stage thrust mission of the engine, thereby improving the analysis pertinence and accuracy of each operation stage.

[0090] Optionally, based on the thrust information of the simulation stage in each operation stage, the simulated engine operation information in each operation stage is identified, including: based on the flight thrust information in each operation stage, querying the engine operation database to obtain the engine operation degree information in each operation stage; based on the engine operation degree information in each operation stage, querying the engine operation database to obtain the stage operation data range of each equipment structure corresponding to each operation stage, and the engine input information of the water-injected aero-engine corresponding to each operation stage; based on the stage operation data range of each equipment structure, generating the combined simulated operation data of each engine in the operation stage, and taking the combined simulated operation data of each engine corresponding to each operation stage and the engine input information of the water-injected aero-engine corresponding to each operation stage as the simulated engine operation information in each operation stage.

[0091] In this embodiment, the terminal queries the engine operation database based on the flight thrust information in each operation stage to obtain the engine operation degree information in each operation stage. Among them, the engine operation database presets the percentage information corresponding to different thrust levels, and the flight thrust information obtained above is the thrust level of the aero-engine. The terminal is based on this engine operation database and the flight thrust information in each operation stage as the thrust level of the aero-engine, so as to identify the thrust percentage of the aero-engine in each operation stage.

[0092] The terminal queries the engine operation database based on the engine operation degree information in each operation stage to obtain the stage operation data range of each equipment structure corresponding to each operation stage, and the engine input information of the water-injected aero-engine corresponding to each operation stage. Among them, in the engine operation database, the stage operation data range of each equipment structure corresponding to different operation degree information and the engine input information corresponding to different operation degree information are preset. Among them, the higher the operation degree, the higher the amount and input rate of hydrogen, air, and water vapor corresponding to the engine input information, and the higher the stage operation data of each equipment structure. On the contrary, the lower the operation degree, the lower the amount and input rate of hydrogen, air, and water vapor corresponding to the engine input information, and the lower the stage operation data of each equipment structure.

[0093] Then, based on the stage operation data ranges of each equipment structure, the terminal generates combinations of simulated operation data of each engine in the operation stage, and takes the combinations of simulated operation data of each engine corresponding to each operation stage and the engine input information of the water-injected aero-engine corresponding to each operation stage as the simulated engine operation information for each operation stage. Among them, the method of generating combinations of simulated operation data of each engine in the operation stage is to perform data allocation processing on the stage operation data ranges of each equipment structure according to the principle of the single-variable method to obtain combinations of simulated operation data of each engine. Each combination includes the single-stage operation data of each equipment structure.

[0094] Based on the above solution, through the flight thrust information of the aero-engines corresponding to different operation stages, it is refined into the stage operation data ranges of each equipment structure and the engine input information, thereby generating the simulated engine operation information for each operation stage, improving the simulation accuracy and comprehensiveness for each operation stage.

[0095] Optionally, based on the simulated engine operation information of each operation stage, through an adaptive control model, simulated operation results for each operation stage are generated, including: for each operation stage, based on the combinations of simulated operation data of each engine in the operation stage, through the adaptive control model, the stage operation process of the operation stage is executed to obtain the emission information corresponding to each combination of simulated operation data of each engine; taking the emission information corresponding to each combination of simulated operation data as the simulated operation result of the operation stage.

[0096] In this embodiment, for each operation stage, the terminal executes the stage operation process of the operation stage based on the combinations of simulated operation data of each engine in the operation stage through the adaptive control model to obtain the emission information corresponding to each combination of simulated operation data of each engine. Among them, the emission information is nitrogen oxide emission information.

[0097] Finally, the terminal takes the emission information corresponding to all combinations of simulated operation data as the simulated operation result of the operation stage.

[0098] Based on the above solution, by performing simulations on separate combinations of simulated operation data to obtain the emission information corresponding to each combination of simulated operation data, the recognition accuracy of the correlation between the stage operation data of different equipment structures and the emission information is improved.

[0099] Optionally, based on the simulation operation results of each operation stage, identify the system control scheme for each operation stage, including: for each operation stage, generate the association distribution information between the stage operation data of each equipment structure and nitrogen oxides emissions based on the emission information corresponding to each combination of simulation operation data in the operation stage; based on the association distribution information, identify the target stage operation data of each equipment structure corresponding to the minimum nitrogen oxides emissions, and the target emission information corresponding to the target stage operation data of each equipment structure, and based on the target stage operation data of each equipment structure, simulate the operation process of each equipment structure through an adaptive control model to obtain the equipment operation process of each equipment structure and the simulated emission information of the operation stage; based on the target emission information corresponding to the target stage operation data of each equipment structure and the simulated emission information of the operation stage as the emission deviation information of the operation stage, and in the case where the emission deviation information is greater than the deviation information threshold, return to execute each combination of engine simulation operation data in the operation stage, and through the adaptive control model, execute the stage operation process of the operation stage to obtain the stage operation data of each equipment structure corresponding to each combination of engine simulation operation data and the emission information corresponding to each combination of engine simulation operation data; until the emission deviation information is greater than the deviation information threshold, generate the system control scheme for the operation stage based on the equipment operation process of each equipment structure obtained in the last iteration and the target stage operation data of each equipment structure obtained in the last iteration.

[0100] In this embodiment, the terminal generates the association distribution information between the stage operation data of each equipment structure and nitrogen oxides emissions based on the emission information corresponding to each combination of simulation operation data in the operation stage for each operation stage. Specifically, the terminal screens each target simulation operation data combination corresponding to each equipment structure in each combination of simulation operation data, and then the terminal constructs the change association distribution diagram between the stage operation data of each equipment structure and nitrogen oxides emissions based on the change information of the stage operation data in each target simulation operation data combination and the change information of the emission information corresponding to each target simulation operation data combination to obtain each association distribution information. Among them, the association distribution information can identify the change trend and the change amount of nitrogen oxides emissions when the different stage operation data changes.

[0101] Then, based on the associated distribution information, the terminal identifies the target stage operation data of each equipment structure corresponding to the emissions of the lowest nitrogen oxides, as well as the target emission information corresponding to the target stage operation data of each equipment structure. Among them, each associated distribution information contains the stage operation data corresponding to the lowest nitrogen oxide emissions as the initial stage operation data of each equipment structure. Then, the terminal queries the operation data association range of each equipment structure when the aero-engine is operating normally in the engine operation database. The operation data association range is the range of operation data that each equipment structure can reach when the aero-engine is operating normally. Then, with the range of operation data that each equipment structure can reach as the boundary, the terminal screens the initial stage operation data that meets the operation data range from the initial stage operation data of each equipment structure as the target operation data of each equipment structure. When the initial stage operation data exceeds the operation data range, the boundary operation data of the operation data range closest to the initial stage operation data is used as the target operation data of the equipment structure.

[0102] Based on the target stage operation data of each equipment structure, the terminal simulates the operation process of each equipment structure through an adaptive control model to obtain the equipment operation process of each equipment structure and the simulated emission information of the operation stage. Among them, since the target stage operation data of each equipment structure inferred based on the association relationship may not be in the simulated operation data combinations that have been simulated, it is necessary to simulate again to identify the feasibility of the target stage operation data of each equipment structure screened, so as to detect whether the target stage operation data of each equipment structure can achieve the lowest emission information.

[0103] Then, the terminal uses the target emission information corresponding to the target stage operation data of each equipment structure and the simulated emission information of the operation stage as the emission deviation information of the operation stage. The terminal presets an emission deviation threshold, and when the emission deviation information is greater than the deviation information threshold, it returns to execute the combined simulated operation data of each engine in the operation stage. Through the adaptive control model, it executes the stage operation process in the operation stage to obtain the stage operation data of each equipment structure corresponding to each combined simulated operation data of the engine and the emission information corresponding to each combined simulated operation data of the engine. Thus, it re-screen the target stage operation data of each equipment structure until the emission deviation information is greater than the deviation information threshold. Based on the equipment operation process of each equipment structure obtained from the last iteration and the target stage operation data of each equipment structure obtained from the last iteration, it generates a system control plan for the operation stage. Among them, the system control plan includes the first system control instruction corresponding to the equipment operation process of each equipment structure and the second system control instruction corresponding to the target stage operation data of each equipment structure. The terminal presets the corresponding relationship between each system control instruction and the equipment operation process and stage operation data, so as to generate the system control plan for each operation stage.

[0104] Based on the above solution, by analyzing the correlation information between the stage operation data and the emission information of each equipment structure, the target stage operation data of each equipment structure is screened and detected to ensure the feasibility of the screened target stage operation data of each equipment structure. Then, the equipment operation process corresponding to the simulation process and the target stage operation data are used to generate the system control plan of the system, improving the accuracy and comprehensiveness of generating the system control plan.

[0105] In an exemplary embodiment, as Figure 1 shown, an emissions control system for a water-injected aeroengine is provided. The system includes a water-injected aeroengine and an adaptive emissions control unit, where: the adaptive emissions control unit includes a metering valve, a water vapor injection valve, an engine, an LPV model, and an adaptive MPC controller, etc.; the metering valve, the water vapor injection valve, and the state space prediction model are respectively connected to the water-injected aeroengine, and the metering valve, the water vapor injection valve, and the state space prediction model are respectively connected to the adaptive emissions controller.

[0106] Among them, the LPV model is obtained by multi-point linearization of the single-spool turbojet engine J85-13 model. By applying small perturbations at the steady-state equilibrium point of the engine and performing multi-step dynamic calculations using the non-linear model, when the convergence index of the flow continuity quasi-equilibrium condition is satisfied after iterative operations, the derivatives of the state variables and the increments of the output quantities at the initial perturbation are obtained. Then, the state model matrix is calculated by taking the ratio of them to the perturbation quantities. The annotated aero-engine is the single-spool turbojet engine J85-13, which has one state variable, two input quantities, namely the hydrogen flow rate and the water quantity injected into the combustion chamber, and three output quantities, namely the engine speed N, the turbine inlet temperature T4, and Nox. Its LPV model can be expressed as:

[0107]

[0108] Then, the LPV model of the J85-13 engine has a direct feedthrough term. Generally, there are actuators in front of the engine. For example, a hydrogen metering valve needs to be connected in series in front of the engine for the input quantity of hydrogen flow rate to provide hydrogen with a certain flow rate and pressure, and a steam injection valve is required to inject a certain mass of steam into the combustion chamber for the water vapor to reduce the Nox emission in the combustion chamber. After connecting two actuators in series, the augmented series system model obtained by augmenting the engine model can be expressed as:

[0109]

[0110] Then, the design of the adaptive MPC controller is carried out. Model predictive control consists of three steps. By predicting the future dynamics, solving the optimization problem, and applying the first element of the solution to the system, following the mechanism of the rolling time domain and repeating the process to solve the control law.

[0111] The prediction equation is shown as follows:

[0112]

[0113] Among them,

[0114]

[0115] Then, the optimization problem is solved. The selection of the optimization index can comprehensively consider the tracking performance of the output and the magnitude of the input. The generated controlled output at the terminal is close to the reference input, while the control magnitude is relatively low, that is:

[0116]

[0117] Among them, is the j-th component of the given reference input sequence, is the weighting factor for the j-th predicted control output error, indicating that the more emphasis is placed on the tracking performance, is the weighting factor for the j-th component of the control increment at the prediction time i, indicating that it is desired that the control amplitude be as small as possible.

[0118] Then, the first element of the solution is applied to the system to obtain:

[0119]

[0120] Among them, for adaptive MPC control, it only needs to design an MPC controller that meets the performance index at the nominal point. If the state variables and the number of constraint conditions at the remaining steady-state points of the object remain unchanged, then the solution of the optimization problem at the remaining steady-state points is the same as that at the nominal point. Adaptive MPC can adjust the controller parameters according to the model differences. When the object operates at different operating points, then, the adaptive MPC controller updates the internal prediction model in each control interval using the LPV system to achieve nonlinear control.

[0121] An adaptive emissions controller for sending a hydrogen command quantity to a metering valve and a water injection command quantity to a steam injection valve; a metering valve for identifying the hydrogen quantity of a water injection aeroengine based on the hydrogen command quantity of the adaptive emissions controller and sending the hydrogen quantity to the water injection aeroengine; a steam injection valve for identifying the water injection quantity of the water injection aeroengine based on the water injection command quantity of the adaptive emissions controller and sending the water injection quantity to the water injection aeroengine; a water injection aeroengine for generating a rotational speed measurement value and sending the rotational speed measurement value to a state-space prediction model; a state-space prediction model for identifying the scheduling parameter of the state-space prediction model based on the rotational speed measurement value sent by the water injection aeroengine and generating a new state-space prediction model based on the scheduling parameter; sending the new state-space prediction model to the adaptive emissions controller; the adaptive emissions controller is further configured to generate a new hydrogen command quantity for the metering valve and a new water injection command quantity for the steam injection valve based on the new state-space prediction model, replace the hydrogen command quantity with the new hydrogen command quantity, and replace the water injection command quantity with the new water injection command quantity; return to execute the step of sending the hydrogen command quantity to the metering valve and sending the water injection command quantity to the steam injection valve.

[0122] In one embodiment, as Figure 3As shown in the figure, the water-injected aeroengine includes an air intake, a compressor, a combustion chamber, a turbine, a heat exchanger, a nozzle, an evaporator, etc. Among them, the air intake is connected to the compressor, and the compressor, the evaporator, the heat exchanger, and the turbine are respectively connected to the combustion chamber; the turbine, the evaporator, and the nozzle are respectively connected to the heat exchanger; a water vapor injection valve is arranged between the evaporator and the combustion chamber; a metering valve is arranged between the heat exchanger and the combustion chamber; the air intake is used for transmitting air to the compressor; the compressor is used for compressing the gas transmitted by the air intake and then transmitting it to the combustion chamber; the heat exchanger is used for converting liquid hydrogen into gaseous hydrogen and transmitting the gaseous hydrogen to the combustion chamber; the evaporator is used for converting liquid water into water vapor and transmitting the water vapor to the combustion chamber; the combustion chamber is used for performing a combustion reaction on the gaseous hydrogen, water vapor, and air to generate first water vapor, oxygen, and nitrogen, and transmitting the first water vapor, oxygen, and nitrogen to the turbine; the turbine is used for quickly transmitting the first water vapor, oxygen, and nitrogen to the heat exchanger; the heat exchanger is further used for cooling the first water vapor to obtain second water vapor and liquid water, and transmitting the liquid water to the evaporator; the heat exchanger is further used for transmitting the second water vapor, oxygen, and nitrogen to the nozzle; the nozzle is used for jetting and discharging the second water vapor, oxygen, and nitrogen to the environment.

[0123] Specifically, a hydrogen metering valve needs to be connected in series in front of the engine to provide hydrogen with a certain flow rate and pressure. Water vapor requires an injection valve to inject a certain mass of water vapor into the combustion chamber to reduce the NOx emissions of the combustion chamber. After the engine receives two control variables, it will reach a new operating point. At this time, the speed sensor will obtain a speed measurement value, which is also the scheduling parameter of the LPV model, so as to obtain a new predicted state space model. The adaptive MPC controller uses the predicted state space model to perform internal optimization calculations, and will obtain a water injection command quantity and a hydrogen command quantity, which are transmitted to the metering valve to generate the actual hydrogen quantity that reaches the engine, and are transmitted to the water vapor injection valve to generate the actual water injection quantity that reaches the engine.

[0124] This application also provides an example of emissions control for a water-injected aeroengine, as Figure 5 shown. The specific processing process includes the following steps:

[0125] Step S501, obtain the system architecture information of the emissions control system of the water-injected aeroengine and the flight operation information of the water-injected aeroengine.

[0126] Step S502, based on the system architecture information, identify the operation information of each equipment structure and the operation correlation information between each equipment structure, and based on the operation information of each equipment structure, identify each operation parameter corresponding to the equipment operation logic of each equipment structure.

[0127] Step S503: Based on the operating parameters corresponding to the operating logics of each device, construct the structural operation models of each device structure, and based on the operating association information between each device structure, identify the connection information between each device structure and the data interaction logic parameters between each device structure.

[0128] Step S504: Based on the connection information between each device structure, perform structural connection processing on each device structure to obtain the associated operation model of the emission control system, and add the data interaction logic parameters between each device structure to the associated operation model to obtain the adaptive control model of the emission control system.

[0129] Step S505: Split the flight operation information into sub-flight operation information for each operation stage, and for each operation stage, based on the sub-flight operation information of the operation stage, identify the flight thrust information of the operation stage and the duration of the operation stage.

[0130] Step S506: Use the flight thrust information of the operation stage and the duration of the operation stage as the simulated stage thrust information of the operation stage.

[0131] Step S507: Based on the flight thrust information of each operation stage, query the engine operation database to obtain the engine operation degree information of each operation stage.

[0132] Step S508: Based on the engine operation degree information of each operation stage, query the engine operation database to obtain the stage operation data range of each device structure corresponding to each operation stage and the engine input information of the water injection aeroengine corresponding to each operation stage.

[0133] Step S509: Based on the stage operation data range of each device structure, generate the combined simulated operation data of each engine for the operation stage, and use the combined simulated operation data of each engine corresponding to each operation stage and the engine input information of the water injection aeroengine corresponding to each operation stage as the simulated engine operation information for each operation stage.

[0134] Step S510: For each operation stage, based on the combined simulated operation data of each engine for the operation stage, execute the stage operation process of the operation stage through the adaptive control model to obtain the emission information corresponding to each combined simulated operation data of the engine.

[0135] Step S511: Use the emission information corresponding to each combined simulated operation data as the simulated operation result of the operation stage.

[0136] Step S512: For each operation stage, based on the emission information corresponding to each combination of simulated operation data in the operation stage, generate the correlation distribution information between the stage operation data of each equipment structure and the nitrogen oxide emissions.

[0137] Step S513: Based on the correlation distribution information, identify the target stage operation data of each equipment structure corresponding to the emission amount of the lowest nitrogen oxide emissions, and the target emission information corresponding to the target stage operation data of each equipment structure. Then, based on the target stage operation data of each equipment structure, simulate the operation process of each equipment structure through the adaptive control model to obtain the equipment operation process of each equipment structure and the simulated emission information of the operation stage.

[0138] Step S514: Use the target emission information corresponding to the target stage operation data of each equipment structure and the simulated emission information of the operation stage as the emission deviation information of the operation stage. When the emission deviation information is greater than the deviation information threshold, return to execute the combination of each engine simulated operation data in the operation stage, and through the adaptive control model, execute the stage operation process of the operation stage to obtain the stage operation data of each equipment structure corresponding to each engine simulated operation data combination and the emission information corresponding to each engine simulated operation data combination.

[0139] Step S515: Until the emission deviation information is greater than the deviation information threshold, generate the system control scheme for the operation stage based on the equipment operation process of each equipment structure obtained from the last iteration and the target stage operation data of each equipment structure obtained from the last iteration.

[0140] Step S516: Based on the system control scheme for each operation stage, control the emission control system of the water-injected aeroengine to execute the stage operation tasks of each operation stage.

[0141] It should be understood that although the steps in the flowcharts involved in the above-described embodiments are displayed in sequence according to the arrows, these steps are not necessarily executed in the order indicated by the arrows. Unless otherwise clearly stated in this article, the execution of these steps has no strict order limit, and these steps can be executed in other orders. Moreover, at least a part of the steps in the flowcharts involved in the above-described embodiments may include multiple steps or multiple stages. These steps or stages are not necessarily executed 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 executed alternately or in turn with at least a part of other steps or steps or stages in other steps.

[0142] Based on the same inventive concept, an embodiment of the present application further provides an emissions control device for a water-injected aeroengine for implementing the emissions control method of the water-injected aeroengine involved above. The solution provided by this device to solve the problem is similar to the solution recorded in the above method. Therefore, the specific limitations in one or more embodiments of the emissions control device for the water-injected aeroengine provided below can refer to the limitations on the emissions control method of the water-injected aeroengine in the above text, and will not be repeated here.

[0143] In an exemplary embodiment, as Figure 6 shown, an emissions control device for a water-injected aeroengine is provided, including: an acquisition module 610, an identification module 620, a generation module 630, and a control module 640, where:

[0144] The acquisition module 610 is configured to acquire the system architecture information of the emissions control system of the water-injected aeroengine and the flight operation information of the water-injected aeroengine, and based on the system architecture information, construct an adaptive control model of the emissions control system;

[0145] The identification module 620 is configured to generate the simulated stage thrust information of each operation stage based on the flight operation information, and identify the simulated engine operation information of each operation stage based on the simulated stage thrust information of each operation stage;

[0146] The generation module 630 is configured to generate the simulated operation results of each operation stage through the adaptive control model based on the simulated engine operation information of each operation stage, and identify the system control scheme of each operation stage based on the simulated operation results of each operation stage;

[0147] The control module 640 is configured to control the emissions control system of the water-injected aeroengine to execute the stage operation tasks of each operation stage based on the system control scheme of each operation stage.

[0148] Optionally, the acquisition module 610 is specifically configured to:

[0149] Based on the system architecture information, identify the operation information of each device structure and the operation association information between each device structure, and based on the operation information of each device structure, identify each operation parameter corresponding to the device operation logic of each device structure;

[0150] Based on each operation parameter corresponding to the device operation logic, construct a structure operation model of each device structure, and based on the operation association information between each device structure, identify the connection information between each device structure and the data interaction logic parameters between each device structure;

[0151] Based on the connection information between each of the device structures, perform structural connection processing on each of the device structures to obtain the associated operation model of the emission control system, and add the data interaction logic parameters between each of the device structures to the associated operation model to obtain the adaptive control model of the emission control system.

[0152] Optionally, the recognition module 620 is specifically configured to:

[0153] Split the flight operation information into sub-flight operation information for each operation stage, and for each operation stage, based on the sub-flight operation information of the operation stage, identify the flight thrust information of the operation stage and the duration of the operation stage;

[0154] Use the flight thrust information of the operation stage and the duration of the operation stage as the simulated stage thrust information of the operation stage.

[0155] Optionally, the recognition module 620 is specifically configured to:

[0156] Query the engine operation database based on the flight thrust information of each of the operation stages to obtain the engine operation degree information of each of the operation stages;

[0157] Query the engine operation database based on the engine operation degree information of each of the operation stages to obtain the stage operation data range of each device structure corresponding to each operation stage and the engine input information of the water injection aeroengine corresponding to each operation stage;

[0158] Generate the combined simulated operation data of the engines for the operation stage based on the stage operation data range of each device structure, and use the combined simulated operation data of the engines corresponding to each operation stage and the engine input information of the water injection aeroengine corresponding to each operation stage as the simulated engine operation information for each operation stage.

[0159] Optionally, the generation module 630 is specifically configured to:

[0160] For each operation stage, based on the combined simulated operation data of the engines for the operation stage, execute the stage operation process of the operation stage through the adaptive control model to obtain the emission information corresponding to each combined simulated operation data of the engines;

[0161] Use the emission information corresponding to each of the combined simulated operation data as the simulated operation result of the operation stage.

[0162] Optionally, the generation module 630 is specifically configured to:

[0163] For each operation stage, based on the emission information corresponding to each simulated operation data combination of the operation stage, generate the association distribution information between the stage operation data of each device structure and the nitrogen oxide emissions.

[0164] Based on the association distribution information, identify the target stage operation data of each device structure corresponding to the emission amount of the lowest nitrogen oxide emissions, and the target emission information corresponding to the target stage operation data of each device structure, and based on the target stage operation data of each device structure, through the adaptive control model, simulate the operation process of each device structure to obtain the device operation process of each device structure and the simulated emission information of the operation stage.

[0165] Based on the target emission information corresponding to the target stage operation data of each device structure and the simulated emission information of the operation stage, as the emission deviation information of the operation stage, and when the emission deviation information is greater than the deviation information threshold, return to execute the step of obtaining the stage operation data of each device structure corresponding to each engine simulated operation data combination and the emission information corresponding to each engine simulated operation data combination by executing the stage operation process of the operation stage through the adaptive control model based on each engine simulated operation data combination of the operation stage.

[0166] Until the emission deviation information is greater than the deviation information threshold, generate the system control scheme of the operation stage based on the device operation process of each device structure obtained from the last iteration and the target stage operation data of each device structure obtained from the last iteration.

[0167] Each module in the above emission control device of the water-injected aeroengine can be implemented in whole or in part by software, hardware and their combination. The above modules can be embedded in the processor of the computer device in hardware form or independent of it, or stored in the memory of the computer device in software form, so as to facilitate the processor to call and execute the operations corresponding to the above modules.

[0168] In an exemplary embodiment, a computer device is provided. The computer device can be a terminal, and its internal structure diagram can be as Figure 7As shown in the figure. The computer device includes a processor, a memory, an input / output interface, a communication interface, a display unit, and an input device. Among them, the processor, the memory, and the input / output interface are connected through a system bus, and the communication interface, the display unit, and the input device are connected to the system bus through the input / output interface. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The input / output interface of the computer device is used to exchange information between the processor and external devices. The communication interface of the computer device is used to communicate with external terminals in a wired or wireless manner, and the wireless manner can be achieved through WIFI, a mobile cellular network, NFC, or other technologies. When the computer program is executed by the processor, it implements a method for controlling emissions of a water-injected aeroengine. The display unit of the computer device is used to form a visually visible picture, which can be a display screen, a projection device, or a virtual reality imaging device. The display screen can be a liquid crystal display screen or an electronic ink display screen. The input device of the computer device can be a touch layer covering the display screen, or a button, a trackball, or a touchpad provided on the housing of the computer device, or an external keyboard, touchpad, or mouse, etc.

[0169] Those skilled in the art can understand that Figure 7 the structure shown in the figure is only a block diagram of some structures related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine some components, or have different component arrangements.

[0170] In an exemplary embodiment, a computer device is provided, including a memory and a processor. A computer program is stored in the memory, and when the processor executes the computer program, it implements the steps of a method for controlling emissions of a water-injected aeroengine.

[0171] In an embodiment, a computer-readable storage medium is provided, on which a computer program is stored. When the computer program is executed by the processor, it implements the steps of a method for controlling emissions of a water-injected aeroengine.

[0172] In an embodiment, a computer program product is provided, including a computer program. When the computer program is executed by the processor, it implements the steps of a method for controlling emissions of a water-injected aeroengine.

[0173] It should be noted that the user information and data 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 relevant data need to comply with relevant regulations.

[0174] Those of ordinary skill in the art can understand that all or part of the processes in the methods of the above embodiments can be completed by instructing relevant hardware through a computer program. The computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above methods. Among them, any reference to a memory, database, or other medium used in the embodiments provided in this application can include at least one of non-volatile and volatile memories. Non-volatile memories can include read-only memories, magnetic tapes, floppy disks, flash memories, optical memories, high-density embedded non-volatile memories, resistive random-access memories, magnetoresistive random-access memories, ferroelectric memories, phase-change memories, graphene memories, etc. Volatile memories can include random-access memories or external cache memories, etc. By way of illustration and not limitation, RAM can be in various forms, such as static random-access memory or dynamic random-access memory, etc. The databases involved in the embodiments provided in this application can include at least one of relational databases and non-relational databases. Non-relational databases can include distributed databases based on blockchain, etc., without limitation. The processors involved in the embodiments provided in this application can be general-purpose processors, central processing units, graphics processing units, digital signal processors, programmable logics, data processing logics based on quantum computing, etc., without limitation.

[0175] The technical features of the above embodiments can be combined arbitrarily. For the sake of brevity of description, 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, it should be considered as the scope recorded in this specification.

[0176] The above-described embodiments merely represent several implementation manners of this application. Their descriptions are relatively specific and detailed, but they should not be construed as limiting the patent scope of this application. It should be noted that for those of ordinary skill in the art, without departing from the concept of this application, several modifications and improvements can still be made, and these all belong to the protection scope of this application. Therefore, the protection scope of this application should be subject to the appended claims.

Claims

1. A method for controlling emissions from a water-injected aircraft engine, characterized in that: The method comprises: Acquiring system architecture information of an emission control system of a water-injected aircraft engine and flight operation information of the water-injected aircraft engine, and constructing an adaptive control model of the emission control system based on the system architecture information; generating simulated stage thrust information for each operation phase based on the flight operation information, and identifying simulated engine operation information for each operation phase based on the simulated stage thrust information for each operation phase; Based on each of the simulated engine operation information, generating simulated operation results of each of the operation stages through the adaptive control model, and identifying the system control scheme of each of the operation stages based on the simulated operation results of each of the operation stages; Based on the system control scheme of each operation stage, the emission control system of the water-injected aircraft engine is controlled to perform the stage operation tasks of each operation stage.

2. The method according to claim 1, characterized in that The step of constructing the adaptive control model of the emission control system based on the system architecture information includes: Based on the system architecture information, identifying the operation information of each device structure and the operation association information between each device structure, and based on the operation information of each device structure, identifying each operation parameter corresponding to the device operation logic of each device structure; Based on the operation parameters corresponding to the operation logic of each device, a structural operation model of each device structure is constructed, and based on the operation association information between each device structure, connection information between each device structure and data interaction logic parameters between each device structure are identified; Based on the connection information between each of the device structures, each of the device structures is structurally connected to obtain an associated operation model of the emission control system, and the data interaction logic parameters between each of the device structures are added to the associated operation model to obtain an adaptive control model of the emission control system.

3. The method according to claim 1, characterized in that The generating, based on the flight operation information, the simulation stage thrust information of each operation stage comprises: Splitting the flight operation information into sub-flight operation information of each operation phase, and for each operation phase, identifying flight thrust information of the operation phase and duration of the operation phase based on the sub-flight operation information of the operation phase; The flight thrust information of the operation phase and the duration of the operation phase are used as the simulation phase thrust information of the operation phase.

4. The method according to claim 3, characterized in that The identifying the simulated engine operation information of each operation stage based on the simulated stage thrust information of each operation stage comprises: Based on the flight thrust information of each operation stage, querying the engine operation database to obtain the engine operation degree information of each operation stage; Based on the engine operation degree information of each operation stage, query the engine operation database to obtain the stage operation data range of each equipment structure corresponding to each operation stage, and the engine input information of the water-injected aircraft engine corresponding to each operation stage; Based on the stage operation data range of each of the equipment structures, the simulated operation data combinations of each engine in the operation stage are generated, and the simulated operation data combinations of each engine corresponding to each operation stage and the engine input information of the water-injected aircraft engine corresponding to each operation stage are used as the simulated engine operation information of each operation stage.

5. The method according to claim 4, characterized in that The generating of the simulated operation results of each operation stage through the adaptive control model based on each simulated engine operation information includes: For each operation stage, based on the combination of simulated operation data of each engine in the operation stage, the stage operation process of the operation stage is executed through the adaptive control model to obtain emission information corresponding to each combination of simulated operation data of the engine; The emission information corresponding to each of the simulation operation data combinations is used as the simulation operation result of the operation stage.

6. The method according to claim 5, characterized in that The identifying of the system control scheme of each operation stage based on the simulation operation results of each operation stage includes: For each operation stage, generating correlation distribution information between the stage operation data of each of the equipment structures and nitrogen oxide emissions based on the emission information corresponding to each combination of simulated operation data of the operation stage; Based on the associated distribution information, target phase operation data of each of the equipment structures corresponding to the emission of the lowest nitrogen oxide emission and target emission information corresponding to the target phase operation data of each of the equipment structures are identified, and based on the target phase operation data of each of the equipment structures, the operation process of each of the equipment structures is simulated through the adaptive control model to obtain the equipment operation process of each of the equipment structures and the simulated emission information of the operation phase; Based on the target emission information corresponding to the target stage operation data of each of the equipment structures and the simulated emission information of the operation stage, as the emission deviation information of the operation stage, and when the emission deviation information is greater than the deviation information threshold, returning to execute the simulated operation data combination of each engine based on the operation stage, executing the stage operation process of the operation stage through the adaptive control model, and obtaining the stage operation data of each equipment structure corresponding to each engine simulated operation data combination and the emission information corresponding to each engine simulated operation data combination; Until the emission deviation information is greater than the deviation information threshold, a system control plan for the operation phase is generated based on the equipment operation process of each equipment structure obtained in the last iteration and the target phase operation data of each equipment structure obtained in the last iteration.

7. An emission control system for a water-injected aircraft engine, characterized in that: The system comprises a water-injected aircraft engine, and an adaptive emissions control unit, wherein: The adaptive emission control unit includes a metering valve, a water vapor injection valve, a state space prediction model, and an adaptive emission controller; The metering valve, the steam injection valve, and the state-space prediction model are respectively connected to the water-injected aircraft engine, and the metering valve, the steam injection valve, and the state-space prediction model are respectively connected to the adaptive emission controller; The adaptive emission controller is used to send a hydrogen command amount to the metering valve and send a water injection command amount to the steam injection valve; The metering valve is used to identify the amount of hydrogen of the water-injected aircraft engine based on the hydrogen command amount of the adaptive emissions controller, and send the amount of hydrogen to the water-injected aircraft engine; The water vapor injection valve is used to identify the water injection amount of the water-injected aircraft engine based on the water injection instruction amount of the adaptive emissions controller, and send the water injection amount to the water-injected aircraft engine; The water-injected aircraft engine is used to generate a rotational speed measurement value and send the rotational speed measurement value to the state-space prediction model; The state-space prediction model is used to identify a scheduling parameter of the state-space prediction model based on the speed measurement value sent by the water-injected aircraft engine, and generate a new state-space prediction model based on the scheduling parameter; and send the new state-space prediction model to the adaptive emissions controller; The adaptive emission controller is also used to generate a new hydrogen command amount for the metering valve and a new water injection command amount for the steam injection valve based on the new state-space prediction model, and replace the hydrogen command amount with the new hydrogen command amount, and replace the water injection command amount with the new water injection command amount; return to execute the steps of sending the hydrogen command amount to the metering valve and sending the water injection command amount to the steam injection valve.

8. The system according to claim 7, characterized in that The water-injected aircraft engine comprises an air inlet, a compressor, a combustion chamber, a turbine, a heat exchanger, a nozzle, and an evaporator, wherein; The air inlet is connected to the compressor, the compressor, the evaporator, the heat exchanger, and the turbine are respectively connected to the combustion chamber; the turbine, the evaporator, and the nozzle are respectively connected to the heat exchanger; The water vapor injection valve is arranged between the evaporator and the combustion chamber; The metering valve is arranged between the heat exchanger and the combustion chamber; The air inlet is used to transmit air to the compressor; the compressor is used to compress the gas transmitted by the air inlet and transmit it to the combustion chamber; The heat exchanger is used to convert liquid hydrogen into gaseous hydrogen and transmit the gaseous hydrogen to the combustion chamber; The evaporator is used to convert liquid water into water vapor and transmit the water vapor to the combustion chamber; The combustion chamber is used to perform combustion reaction on the gaseous hydrogen, the water vapor, and the air to generate first water vapor, oxygen, and nitrogen, and transmit the first water vapor, the oxygen, and the nitrogen to the turbine; the turbine is used to quickly transmit the first water vapor, the oxygen, and the nitrogen to the heat exchanger; The heat exchanger is further used to cool the first water vapor to obtain second water vapor and liquid water, and transmit the liquid water to the evaporator; the heat exchanger is further used to transmit the second water vapor, the oxygen, and the nitrogen to the nozzle; The nozzle is used for spraying and discharging the second water vapor, the oxygen, and the nitrogen to the environment.

9. An emission control device for a water-injected aircraft engine, characterized in that: The device comprises: An acquisition module, used to acquire system architecture information of an emission control system of a water-injected aircraft engine and flight operation information of the water-injected aircraft engine, and to construct an adaptive control model of the emission control system based on the system architecture information; an identification module, configured to generate simulated stage thrust information of each of the operation stages based on the flight operation information, and to identify simulated engine operation information of each of the operation stages based on the simulated stage thrust information of each of the operation stages; A generating module, configured to generate, based on each of the simulated engine operation information and through the adaptive control model, a simulated operation result of each of the operation stages, and to identify a system control scheme of each of the operation stages based on the simulated operation result of each of the operation stages; The control module is used to control the emission control system of the water-injected aircraft engine to perform the stage operation tasks of each operation stage based on the system control plan of each operation stage.

10. 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, the steps of the method according to any one of claims 1 to 6 are implemented.

11. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 6 are implemented.

12. A computer program product, comprising a computer program, characterized in that When the computer program is executed by a processor, the steps of the method according to any one of claims 1 to 6 are implemented.

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