Method, device and computer equipment for emission control of water-injected aircraft engine

Abstract

The application relates to a water injection aircraft engine emission control method, device and computer equipment. The method comprises the following steps: acquiring system architecture information of an emission control system of a water injection aircraft engine and flight operation information of the water injection aircraft engine, and constructing an adaptive control model of the emission control system based on the system architecture information; generating simulation stage thrust information of each operation stage based on the flight operation information, and identifying simulation engine operation information of each operation stage based on the simulation stage thrust information of each operation stage; generating simulation operation results of each operation stage by the adaptive control model based on the simulation engine operation information, and identifying system control schemes of each operation stage based on the simulation operation results of each operation stage; and controlling the system operation. The method can improve the nitrogen oxide emission control efficiency of the aircraft engine.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engines, and particularly relates to a water injection aero-engine emission control method and device and computer equipment. BACKGROUND

[0002] The flame combustion temperature is higher than 1516K, which can cause a significant increase in nitrogen oxide emissions. The combustion flame temperature has a significant impact on the speed of nitrogen oxide production in the combustion process. Since the calorific value of hydrogen fuel is high, the combustion temperature of the combustion chamber is higher than that of ordinary kerosene engines. High flame temperature is easy to cause NOx production. However, a large amount of nitrogen oxides can cause environmental pollution. Therefore, how to reduce the NOx emissions of the hydrogen fuel engine is the current research focus.

[0003] The prior art is a dry method, that is, a lean premixed combustion chamber can prevent the emission of NOx. However, the dry method is more prone to flameout and thermal acoustic oscillation. At the same time, the dry method needs to design a control strategy for multiple valves. The controller design is complicated, the cost is high, and the complicated controller design can affect the efficiency conversion ratio of the aero-engine, thereby causing low nitrogen oxide emission control efficiency of the aero-engine. SUMMARY

[0004] Therefore, it is necessary to provide a water injection aero-engine emission control method, device, computer equipment, computer readable storage medium and computer program product in view of the above technical problems.

[0005] In a first aspect, the present application provides a water injection aero-engine emission control method, comprising:

[0006] Obtaining system architecture information of a water injection aero-engine emission control system and flight operation information of the water injection aero-engine, and constructing an adaptive control model of the emission control system based on the system architecture information;

[0007] Based on the flight operation information, generating simulation stage thrust information of each operation stage, and identifying simulation engine operation information of each operation stage based on the simulation stage thrust information of each operation stage;

[0008] Based on the simulation engine operation information, generating simulation operation results of each operation stage through the adaptive control model, and identifying system control schemes of each operation stage based on the simulation operation results of each operation stage;

[0009] Based on the system control schemes of each operation stage, controlling the water injection aero-engine emission control system to perform stage operation tasks of each operation stage.

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

[0011] identifying operation information of each of the device structures and operation association information between the device structures based on the system architecture information, and identifying each operation parameter corresponding to a device operation logic of each of the device structures based on the operation information of each of the device structures;

[0012] constructing a structure operation model of each of the device structures based on each operation parameter corresponding to the device operation logic of each of the device structures, and identifying connection information between the device structures and data interaction logic parameters between the device structures based on the operation association information between the device structures;

[0013] performing structure connection processing on each of the device structures based on the connection information between the device structures to obtain an associated operation model of the emission control system, and adding the data interaction logic parameters between the device structures to the associated operation model to obtain the adaptive control model of the emission control system.

[0014] Optionally, the generating simulation stage thrust information of each of the operation stages based on the flight operation information comprises:

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

[0016] taking the flight thrust information of the operation stage and the duration of the operation stage as simulation stage thrust information of the operation stage.

[0017] Optionally, the identifying simulation engine operation information of each of the operation stages based on the simulation stage thrust information of each of the operation stages comprises:

[0018] querying an engine operation database based on the flight thrust information of each of the operation stages to obtain engine operation degree information of each of the operation stages;

[0019] querying the engine operation database based on the engine operation degree information of each of the operation stages to obtain stage operation data ranges of each of the device structures corresponding to each operation stage and engine input information of the water injection aero-engine corresponding to each operation stage;

[0020] generate each engine simulation running data combination of each running stage based on the stage running data range of each device structure of the running stage, and take each engine simulation running data combination corresponding to each running stage and engine input information of the water injection aero-engine corresponding to each running stage as simulation engine running information of each running stage.

[0021] Optionally, the simulation running results of each running stage are generated based on the simulation engine running information by the adaptive control model, including:

[0022] For each running stage, a stage running process of the running stage is executed based on each engine simulation running data combination of the running stage by the adaptive control model to obtain emission information corresponding to each engine simulation running data combination;

[0023] The emission information corresponding to each simulation running data combination is taken as the simulation running result of the running stage.

[0024] Optionally, the system control scheme of each running stage is identified based on the simulation running result of each running stage, including:

[0025] For each running stage, the correlation distribution information between the stage running data of each device structure and nitrogen and oxygen emission is generated based on the emission information corresponding to each simulation running data combination of the running stage;

[0026] The target stage running data of each device structure corresponding to the lowest emission amount of nitrogen and oxygen emission and the target emission information corresponding to the target stage running data of each device structure are identified based on the correlation distribution information, and the running process of each device structure is simulated based on the target stage running data of each device structure by the adaptive control model to obtain a device running process of each device structure and simulation emission information of the running stage;

[0027] The target emission information corresponding to the target stage running data of each device structure and the simulation emission information of the running stage are taken as emission deviation information of the running stage, and if the emission deviation information is greater than a deviation information threshold, the step of executing a stage running process of the running stage based on each engine simulation running data combination of the running stage by the adaptive control model to obtain stage running data of each device structure corresponding to each engine simulation running data combination and emission information corresponding to each engine simulation running data combination is returned.

[0028] Until the emission deviation information is greater than a deviation information threshold value, a system control scheme of the running stage is generated based on a device running flow of each of the device structures obtained by a last iteration, and target stage running data of each of the device structures obtained by the last iteration.

[0029] In a second aspect, the application further provides an emission control device of a water-injected aero-engine, comprising:

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

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

[0032] A generation module is configured to generate simulated running results of each of the running stages by the adaptive control model based on the simulated engine running information of each of the running stages, and identify system control schemes of each of the running stages based on the simulated running results of each of the running stages;

[0033] A control module is configured to control the emission control system of the water-injected aero-engine to perform stage running tasks of each of the running stages based on the system control schemes of each of the running stages.

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

[0035] Identify running information of each of the device structures, and running association information between each of the device structures based on the system architecture information, and identify each running parameter corresponding to a device running logic of each of the device structures based on the running information of each of the device structures;

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

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

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

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

[0040] use the flight thrust information of the operation phase and the duration of the operation phase as simulation phase thrust information of the operation phase.

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

[0042] query an engine operation database based on the flight thrust information of each operation phase to obtain engine operation degree information of each operation phase;

[0043] query the engine operation database based on the engine operation degree information of each operation phase to obtain phase operation data range of each device structure corresponding to each operation phase and engine input information of the water injection aero-engine corresponding to each operation phase;

[0044] generate each engine simulation operation data combination of the operation phase based on the phase operation data range of each device structure, and use each engine simulation operation data combination corresponding to each operation phase and the engine input information of the water injection aero-engine corresponding to each operation phase as simulation engine operation information of each operation phase.

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

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

[0047] use the emission information corresponding to each simulation operation data combination as simulation operation result of the operation phase.

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

[0049] for each operation phase, generate correlation distribution information between phase operation data of each device structure and nitrogen and oxygen emissions based on the emission information corresponding to each simulation operation data combination of the operation phase;

[0050] Based on the association distribution information, target stage operation data of each device structure corresponding to the lowest nitrogen oxide emission amount is identified, and target emission information corresponding to the target stage operation data of each device structure is identified, and based on the target stage operation data of each device structure, an operation process of each device structure is simulated through the adaptive control model to obtain device operation flow of each device structure and simulation emission information of the operation stage;

[0051] Based on the target emission information corresponding to the target stage operation data of each device structure and the simulation emission information of the operation stage, emission deviation information of the operation stage is obtained, and in a case where the emission deviation information is greater than a deviation information threshold, a step of performing stage operation process of the operation stage through the adaptive control model based on each engine simulation operation data combination of the operation stage is returned to obtain stage operation data of each device structure corresponding to each engine simulation operation data combination and emission information corresponding to each engine simulation operation data combination.

[0052] Until the emission deviation information is greater than the deviation information threshold, a system control scheme of the operation stage is generated based on the device operation flow of each device structure obtained through the last iteration and the target stage operation data of each device structure obtained through the last iteration.

[0053] In a third aspect, a computer device is provided. The computer device includes a memory and a processor, the memory stores a computer program, and the processor implements the steps of the method in any one of the first aspect when executing the computer program.

[0054] In a fourth aspect, a computer readable storage medium is provided. The computer readable storage medium stores a computer program, and the computer program is executed by a processor to implement the steps of the method in any one of the first aspect.

[0055] In a fifth aspect, a computer program product is provided. The computer program product includes a computer program, and the computer program is executed by a processor to implement the steps of the method in any one of the first aspect.

[0056] The water injection aircraft engine emission control method, device and computer equipment, by acquiring the system architecture information of the water injection aircraft engine emission control system and the flight operation information of the water injection aircraft engine, and based on the system architecture information, constructing an adaptive control model of the emission control system; 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; based on each simulation engine operation information, generating simulation operation results of each operation stage through the adaptive control model, and based on the simulation operation results of each operation stage, identifying system control schemes of each operation stage; based on the system control schemes of each operation stage, controlling the water injection aircraft engine emission control system to perform stage operation tasks of each operation stage. The scheme constructs the water injection aircraft engine emission control system, thereby reducing the flame temperature by increasing the injection of water vapor in the aircraft engine to reduce the emission of nitrogen oxides, avoiding the problem of complicated controller design, and in actual control, the scheme constructs the adaptive control model of the system, thereby simulating the engine operation information of the water injection aircraft engine in different operation stages, generating system control schemes of each operation stage, ensuring the lowest nitrogen oxide emission in different operation stages while reducing the flame temperature in the way of injecting water vapor, to improve the control accuracy of the nitrogen oxide emission, and finally, the scheme generates different target system control schemes of different operation stages through simulation analysis, thereby avoiding the complicated design of multiple controllers and the complicated steps of generating multiple control strategies through manual valve control, to adaptively and efficiently generate emission control schemes of the aircraft engine in different operation stages, thereby improving the nitrogen oxide emission control efficiency of the aircraft engine. BRIEF DESCRIPTION OF DRAWINGS

[0057] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the related art, the drawings needed to be used in the embodiments or related art description will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the present application, and those skilled in the art can obtain other drawings according to these drawings without creative labor.

[0058] Figure 1 A system structure diagram of the water injection aircraft engine emission control system in an embodiment;

[0059] Figure 2 A flowchart of the water injection aircraft engine emission control method in an embodiment;

[0060] Figure 3An engine structure diagram of a water-injected aero-engine in an embodiment;

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

[0062] Figure 5 A flow diagram of an emission control example of a water-injected aero-engine in an embodiment;

[0063] Figure 6 A structure block diagram of an emission control device of a water-injected aero-engine in an embodiment;

[0064] Figure 7 An internal structure diagram of a computer device in an embodiment. DETAILED DESCRIPTION

[0065] In order to make the purposes, technical solutions and advantages of the present application clearer, the present application is 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 not used to limit the present application.

[0066] The emission control method of the water-injected aero-engine provided by the embodiments of the present application can be applied to the emission control system of the water-injected aero-engine, such as Figure 1As shown, a system operation structure diagram of an exhaust emission control system of a water injection aero-engine is shown, in which a metering valve, a water vapor injection valve, and a state space prediction model are connected with the water injection aero-engine respectively, and the metering valve, the water vapor injection valve, and the state space prediction model are connected with an adaptive exhaust emission controller respectively. Among them, the hydrogen flow of the system needs to be connected in series with a metering valve in front of the engine to provide hydrogen with a certain flow rate and pressure, and the water vapor needs to be injected into the combustion chamber by the water vapor injection valve to achieve the reduction of the nitrogen oxide emission of the combustion chamber. After receiving the two control quantities, the water injection aero-engine reaches a new operating point, at which the speed sensor obtains a speed measurement value, which is also a 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 exhaust emission controller) uses the predicted state space model to perform internal optimization calculation, so as to obtain water injection command quantity hydrogen command quantity, which is transmitted to the metering valve to generate the actual hydrogen quantity passing to the engine, and is transmitted to the water vapor injection valve to generate the actual water injection quantity passing to the engine. Among them, the system can be applied to a terminal, which can be but is not limited to various aero-engine control computers and the like. Among them, the terminal constructs the adaptive control model of the above-mentioned system, thereby simulating the engine operating information of the water injection aero-engine in different operating stages, thereby generating a system control scheme for each operating stage, so as to ensure that the nitrogen oxide emission quantity in different operating stages is the lowest while meeting the way of injecting water vapor and reducing the flame temperature, so as to improve the control accuracy of the nitrogen oxide emission quantity. Finally, the scheme generates the target system control scheme of different operating stages through simulation analysis, thereby eliminating the cumbersome design of multiple controllers and the cumbersome steps of generating multiple control strategies by manual valve control, so as to adaptively and efficiently generate the exhaust emission control scheme of the aero-engine in different operating stages, thereby comprehensively improving the nitrogen oxide emission control efficiency of the aero-engine.

[0067] In one exemplary embodiment, as shown in Figure 2 An exhaust emission control method of a water injection aero-engine is provided, which is taken as an example for illustration when applied to a terminal, and includes the following steps S201 to S204. Among them:

[0068] In step S201, the system architecture information of the exhaust emission control system of the water injection aero-engine and the flight operating information of the water injection aero-engine are obtained, and an adaptive control model of the exhaust emission control system is constructed based on the system architecture information.

[0069] In this embodiment, the terminal obtains system architecture information of the emission control system of the water-injected aero-engine in response to the information uploading operation of the staff. The system architecture information includes the structures of the devices included in the system, the connection relationship between the structures, the operation mode of the structures, and the association information between the structures. Figure 2 As shown in FIG. 2, the structure of the adaptive emission control unit included in the system is shown. As shown in FIG. 3, the structure of the water-injected aero-engine included in the system is shown. The connection relationship between the structures and the data interaction relationship between the structures are shown in the two diagrams. Figure 3 Then, the terminal obtains the flight operation information of the water-injected aero-engine, wherein the flight operation information includes sub-flight operation information of each operation stage, and the water-injected aero-engine is a single-shaft turbojet engine J85-13. The operation stage is shown in FIG. 4. Figure 4 As shown in FIG. 4, the LTO cycle stage includes approach stage, ground slow stage, take-off stage, and climb stage, and the thrust level and duration of each stage are as follows:

[0070] (1) Take-off: (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 identification process will be described in detail later.

[0075] In step S202, based on the flight operation information, simulation stage thrust information of each operation stage is generated, and based on the simulation stage thrust information of each operation stage, simulation engine operation information of each operation stage is identified.

[0076] In this embodiment, the terminal generates simulation stage thrust information of each operation stage based on the flight operation information, and identifies simulation engine operation information of each operation stage based on the simulation stage thrust information of each operation stage. The simulation stage thrust information includes flight thrust information of the operation stage and duration of the operation stage, and the simulation engine operation information of each operation stage includes each engine simulation operation data combination corresponding to each operation stage and engine input information of the water injection aero-engine corresponding to each operation stage. The engine simulation operation data combination includes single simulation operation data of each device structure. The engine input information includes content information of input air, mass data of liquid hydrogen, and density of water vapor and other input information. The specific identification process will be described in detail below.

[0077] In step S203, the terminal generates simulation operation results of each operation stage by an adaptive control model based on the simulation engine operation information, and identifies system control schemes of each operation stage based on the simulation operation results of each operation stage.

[0078] In this embodiment, the terminal generates simulation operation results of each operation stage by an adaptive control model based on the simulation engine operation information, and identifies system control schemes of each operation stage based on the simulation operation results of each operation stage. The system control scheme of each operation stage is the control scheme with the lowest nitrogen and oxygen emission under the condition of the operation stage. The system control scheme includes device operation processes of each device structure and target stage operation data of each device structure. The specific generation process will be described in detail below.

[0079] In step S204, the terminal controls the emission control system of the water injection aero-engine to perform stage operation tasks of each operation stage based on the system control schemes of each operation stage.

[0080] In this embodiment, the terminal controls the emission control system of the water injection aero-engine to perform stage operation tasks of each operation stage based on the system control schemes of each operation stage. The stage operation task of each operation stage is that the terminal controls the system to perform the system control scheme corresponding to different stages when the system is in different operation stages, thereby controlling the operation process of each device structure.

[0081] Based on the above scheme, by constructing the adaptive control model of the system, the engine operation information of the water injection aero-engine in different operation stages is simulated, the system control scheme of each operation stage is generated, the water vapor injection mode is met, the flame temperature is reduced, and the nitrogen oxide emission amount in different operation stages is ensured to be the lowest, so as to improve the control accuracy of the nitrogen oxide emission amount. Finally, the target system control scheme of different operation stages is adaptively generated by simulation analysis, so as to avoid the complicated design of multiple controllers and the complicated steps of generating multiple control strategies by manual valve control, and to adaptively and efficiently generate the emission control scheme of the aero-engine in different operation stages, thereby comprehensively improving the nitrogen oxide emission control efficiency of the aero-engine.

[0082] Optionally, based on the system architecture information, an adaptive control model of the emission control system is constructed, including: based on the system architecture information, identifying operation information of each device structure and 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 each operation parameter corresponding to each device operation logic, constructing a structure operation model of each device structure, and based on the operation association information between each device structure, identifying connection information between each device structure and data interaction logic parameters between each device structure; based on the connection information between each device structure, performing structure connection processing on each device structure to obtain an associated operation model of the emission control system, and based on the data interaction logic parameters between each device structure, adding the data interaction logic parameters to the associated operation model to obtain the adaptive control model of the emission control system.

[0083] In this embodiment, the terminal identifies operation information of each device structure and operation association information between each device structure based on the system architecture information, and identifies each operation parameter corresponding to the device operation logic of each device structure based on the operation information of each device structure. Specifically, the terminal queries historical operation data of each device structure in the engine operation database of the water injection aero-engine to obtain operation information of each device structure, then queries operation data ranges of each device structure corresponding to different device operation logics in the historical operation data of each device structure, and finally converts each operation data range into operation parameters of each device structure through a parameter conversion strategy. The terminal predefines the parameter conversion strategy for each device structure, which is used to convert operation data of each device structure into operation parameters. The parameter conversion strategy is obtained by simulating the simulation process between operation data of each device structure and model operation parameters of a structure operation model through a large number of simulation of a modeling method by a worker, and the association information between the operation data and the operation parameters of each device structure is obtained, and the association information is used as the parameter conversion strategy.

[0084] The terminal constructs a structure operation model of each device structure based on each operation parameter corresponding to the operation logic of each device, and identifies connection information between each device structure and data interaction logic parameters between each device structure based on operation association information between each device structure. The data interaction logic parameters are associated data corresponding to association information between input data and output data in each data interaction process in the data interaction logic information between each device structure. After parameterization processing, the data interaction logic parameters are obtained, for example, the data interaction logic between the metering valve and the adaptive emission controller is that the adaptive emission controller inputs the hydrogen instruction quantity into the metering valve, and then the metering valve identifies the hydrogen quantity required to be input into the water injection aero-engine based on the hydrogen instruction quantity. The association information is the hydrogen instruction quantity, and the associated data is the conversion of the hydrogen instruction quantity into the hydrogen quantity. Therefore, the terminal presets the conversion program between the hydrogen instruction quantity and the hydrogen quantity in the metering valve, and then the terminal converts the hydrogen instruction quantity into the hydrogen quantity, and after parameterization processing of the hydrogen quantity, obtains the input hydrogen parameter required for model simulation as the data interaction logic parameter.

[0085] The terminal performs structure connection processing on each device structure based on the connection information between each device structure to obtain an associated operation model of the emission control system, and adds 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.

[0086] Based on the above scheme, the adaptive control model of the emission control system is constructed by combining the operation information, operation association information and connection information between each device structure, thereby improving the simulation accuracy and model adaptation degree of constructing the adaptive control model.

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

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

[0089] Based on the above scheme, by splitting each running stage for analysis, the simulation stage thrust information of each running stage is obtained, so as to convert the flight task of the aircraft into the stage thrust task of the engine, thereby improving the analysis pertinence and analysis accuracy of each running stage.

[0090] Optionally, based on the simulation stage thrust information of each running stage, the simulation engine running information of each running stage is identified, including: based on the flight thrust information of each running stage, querying the engine running database to obtain the engine running degree information of each running stage; based on the engine running degree information of each running stage, querying the engine running database to obtain the stage running data range of each equipment structure corresponding to each running stage, and the engine input information of the water injection aircraft engine corresponding to each running stage; based on the stage running data range of each equipment structure, generating each engine simulation running data combination of the running stage, and taking each engine simulation running data combination corresponding to each running stage and the engine input information of the water injection aircraft engine corresponding to each running stage as the simulation engine running information of each running stage.

[0091] In this embodiment, the terminal queries the engine running database based on the flight thrust information of each running stage to obtain the engine running degree information of each running stage. Among them, the engine running database presets the percentage information corresponding to different thrust levels, and the flight thrust information of each running stage obtained above is the thrust level of the aircraft engine, and the terminal identifies the thrust percentage of the aircraft engine of each running stage based on the engine running database and the thrust level of the aircraft engine of each running stage.

[0092] The terminal queries the engine running database based on the engine running degree information of each running stage to obtain the stage running data range of each equipment structure corresponding to each running stage, and the engine input information of the water injection aircraft engine corresponding to each running stage. Among them, in the engine running database, the stage running data range of each equipment structure corresponding to different running degree information and the engine input information corresponding to different running degree information are preset. Among them, the higher the running degree is, the higher the amount and input rate of hydrogen, air and water vapor corresponding to the engine input information are, and the stage running data of each equipment structure is also higher, and the lower the running degree is, the lower the amount and input rate of hydrogen, air and water vapor corresponding to the engine input information are, and the stage running data of each equipment structure is also lower.

[0093] Then, the terminal generates each engine simulation running data combination of each running stage based on the stage running data range of each device structure, and takes each engine simulation running data combination corresponding to each running stage and engine input information of the water injection aero-engine corresponding to each running stage as simulation engine running information of each running stage. Wherein, the way of generating each engine simulation running data combination of each running stage is to perform data allocation processing on the stage running data range of each device structure according to the single variable method principle to obtain each engine simulation running data combination, and each combination includes single stage running data of each device structure.

[0094] Based on the above scheme, the flight thrust information of the aero-engine corresponding to different running stages is refined into the stage running data range of each device structure and the engine input information, so as to generate the simulation engine running information of each running stage, thereby improving the simulation accuracy and simulation comprehensiveness of each running stage.

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

[0096] In this embodiment, the terminal executes the stage running process of each running stage through the adaptive control model based on the engine simulation running data combination of the running stage, so as to obtain the emission information corresponding to each engine simulation running data combination. Wherein, the emission information is nitrogen oxide emission information.

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

[0098] Based on the above scheme, the simulation is performed through the simulation running data combination to obtain the emission information corresponding to each simulation running data combination, thereby improving the recognition accuracy of the correlation between the stage running data of different device structures and the emission information.

[0099] Optionally, based on the simulation running results of each running stage, the system control scheme of each running stage is identified, including: for each running stage, based on the simulation running data of each running stage, the corresponding emission information is combined to generate the correlation distribution information between the stage running data of each device structure and the nitrogen and oxygen emissions; based on the correlation distribution information, the target stage running data of each device structure corresponding to the lowest emission amount of nitrogen and oxygen emissions is identified, and the target stage running data of each device structure corresponding to the target emission information is identified, and based on the target stage running data of each device structure, the running process of each device structure is simulated through the adaptive control model to obtain the device running process of each device structure and the simulation emission information of the running stage; the target emission information corresponding to the target stage running data of each device structure and the simulation emission information of the running stage are taken as the emission deviation information of the running stage, and in the case that the emission deviation information is greater than the deviation information threshold, the step of combining each engine simulation running data set based on the running stage is returned to execute the stage running process of the running stage through the adaptive control model to obtain the stage running data of each device structure corresponding to each engine simulation running data set and the emission information corresponding to each engine simulation running data set is executed; until the emission deviation information is greater than the deviation information threshold, based on the device running process of each device structure obtained by the last iteration and the target stage running data of each device structure obtained by the last iteration, the system control scheme of the running stage is generated.

[0100] In this embodiment, the terminal generates the correlation distribution information between the stage running data of each device structure and the nitrogen and oxygen emissions based on the emission information corresponding to the simulation running data combination of each running stage. Specifically, the terminal screens the target simulation running data combination corresponding to each device structure in each simulation running data combination, and then the terminal constructs the change correlation distribution diagram between the stage running data of each device structure and the nitrogen and oxygen emissions based on the change information of the stage running data in each target simulation running data combination and the change information of the emission information corresponding to each target simulation running data combination to obtain each correlation distribution information. The correlation distribution information can identify the change trend and the change amount of the nitrogen and oxygen emissions when different stage running data changes.

[0101] Then, the terminal identifies target stage operation data of each equipment structure corresponding to the lowest nitrogen oxide emission amount and target emission information corresponding to the target stage operation data of each equipment structure based on the association distribution information. Each association distribution information contains stage operation data corresponding to the lowest nitrogen oxide emission amount as initial stage operation data of each equipment structure. Then, the terminal queries an operation data association range of each equipment structure of the aero-engine during normal operation in the engine operation database. The operation data association range is a range of operation data that each equipment structure can reach during normal operation of the aero-engine. Then, the terminal takes the range of operation data that each equipment structure can reach as a boundary, and filters initial stage operation data that meets the operation data range from the initial stage operation data of each equipment structure as target operation data of each equipment structure. When the initial stage operation data exceeds the operation data range, operation data at a boundary of the operation data range closest to the initial stage operation data is taken as the target operation data of the equipment structure.

[0102] The terminal simulates the operation process of each equipment structure through an adaptive control model based on the target stage operation data of each equipment structure to obtain equipment operation processes of each equipment structure and simulation emission information of the operation stage. Since the target stage operation data of each equipment structure inferred based on the association relationship may not be in the already simulated simulation operation data combination, it needs to be simulated again to identify the feasibility of the filtered target stage operation data of each equipment structure, so as to detect whether the target stage operation data of each equipment structure can reach the lowest emission information.

[0103] Then, the terminal obtains the emission deviation information of the running stage based on the target emission information corresponding to the target stage running data of each device structure and the simulation emission information of the running stage. The terminal presets an emission deviation threshold, and in the case that the emission deviation information is greater than the deviation information threshold, the terminal returns to execute the step of combining each engine simulation running data set based on the running stage, executing the stage running process of the running stage by the adaptive control model to obtain the stage running data of each device structure corresponding to each engine simulation running data set and the emission information corresponding to each engine simulation running data set, so as to re-screen the target stage running data of each device structure until the emission deviation information is greater than the deviation information threshold, and generate the system control scheme of the running stage based on the device running process of each device structure obtained by the last iteration and the target stage running data of each device structure obtained by the last iteration. The system control scheme includes the first system control instruction corresponding to the device running process of each device structure and the second system control instruction corresponding to the target stage running data of each device structure. The terminal presets the corresponding relationship between each system control instruction and the device running process and the stage running data, so as to generate the system control scheme of each running stage.

[0104] Based on the above scheme, the correlation information between the stage running data and the emission information of each device structure is analyzed to screen and detect the target stage running data of each device structure, so as to ensure the realizability of the screened target stage running data of each device structure. Then, the device running process corresponding to the simulation process and each target stage running data are used to generate the system control scheme of the system, which improves the accuracy and comprehensiveness of generating the system control scheme.

[0105] In one exemplary embodiment, as shown in Figure 1 An emission control system of a water-injected aeroengine is provided, which includes a water-injected aeroengine and an adaptive emission control unit. The adaptive emission control unit includes a metering valve, a water vapor injection valve, an engine, an LPV model, and an adaptive MPC controller. The metering valve, the water vapor injection valve, and the state space prediction model are connected to the water-injected aeroengine, respectively. The metering valve, the water vapor injection valve, and the state space prediction model are connected to the adaptive emission controller, respectively.

[0106] Where LPV model is obtained by single shaft turbojet engine J85-13 model multi-point linearization, through small disturbance at engine steady state equilibrium point, multi-step dynamic calculation is carried out by using nonlinear model, when iterative operation converges to flow continuous quasi-equilibrium condition, derivative of initial disturbance state variable, output increment are obtained, then state model matrix is obtained by using their ratio to disturbance quantity. The note aircraft engine is single shaft turbojet engine J85-13, the engine has one state variable, two input quantities, hydrogen flow and water injection into the combustion chamber, three output quantities, engine speed N, turbine inlet temperature T4, Nox, its LPV model can be expressed as:

[0107]

[0108] Then, the LPV model of J85-13 engine has a direct feedthrough item, generally there will be an actuator before the engine, such as the input quantity of hydrogen flow of the engine needs to be connected in series with a hydrogen metering valve before the engine to provide hydrogen with a certain flow and pressure, water vapor needs to be injected into the combustion chamber by the injection valve to realize the reduction of Nox emission of the combustion chamber. After connecting the two actuators in series, the augmented system model obtained by connecting the engine model can be expressed as:

[0109]

[0110] Then the adaptive MPC controller is designed, model predictive control contains three steps, by predicting future dynamics, solving optimization problem, the first element of the solution is applied to the system, following the rolling horizon, the mechanism of repeated solving control law.

[0111] The prediction equation is as follows:

[0112]

[0113] Where,

[0114]

[0115] Then solve the optimization problem, the selection of optimization index can comprehensively consider the tracking performance of output and the size of input amplitude, the generated controlled output at the terminal is close to the reference input, and the control amplitude is low, that is:

[0116]

[0117] Where, The jth component of the given reference input sequence is Is the weighting factor of the jth predicted control output error, Indicates that the tracking performance is more important, is a weighting factor for the jth component of the control increment at the prediction time i, It is desirable to control the amplitude as small as possible.

[0118] The first element of the solution is then applied to the system to obtain:

[0119]

[0120] Where, adaptive MPC control only needs to design a MPC controller at the nominal point to meet the performance index, if the number of state variables and constraints of the remaining steady-state points of the object is unchanged, the solution of the remaining steady-state point optimization problem is the same as the nominal point. Adaptive MPC can adjust the controller parameters according to the model difference, and the object runs at different working points. Then, the adaptive MPC controller updates the internal prediction model in each control interval using the LPV system to realize nonlinear control.

[0121] The adaptive emission controller is configured to send a hydrogen instruction quantity to the metering valve and send a water injection instruction quantity to the water vapor injection valve; the metering valve is configured to identify a hydrogen quantity of the water injection aero-engine based on the hydrogen instruction quantity of the adaptive emission controller, and send the hydrogen quantity to the water injection aero-engine; the water vapor injection valve is configured to identify a water injection quantity of the water injection aero-engine based on the water injection instruction quantity of the adaptive emission controller, and send the water injection quantity to the water injection aero-engine; the water injection aero-engine is configured 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 configured to identify a scheduling parameter of the state space prediction model based on the rotational speed measurement value sent by the water injection aero-engine, and generate a new state space prediction model based on the scheduling parameter; the new state space prediction model is sent to the adaptive emission controller; the adaptive emission controller is further configured to generate a new hydrogen instruction quantity of the metering valve and a new water injection instruction quantity of the water vapor injection valve based on the new state space prediction model, replace the hydrogen instruction quantity with the new hydrogen instruction quantity, and replace the water injection instruction quantity with the new water injection instruction quantity; and return to the step of sending the hydrogen instruction quantity to the metering valve and sending the water injection instruction quantity to the water vapor injection valve.

[0122] In one embodiment, as Figure 3As shown, the water injection aero-engine includes an air inlet, a compressor, a combustion chamber, a turbine, a heat exchanger, a nozzle, and an evaporator, etc., wherein the air inlet is connected with the compressor, the compressor, the evaporator, the heat exchanger, and the turbine are connected with the combustion chamber respectively, the turbine, the evaporator, and the nozzle are connected with the heat exchanger respectively, 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 inlet is used to transmit air to the compressor, the compressor is used to compress the air transmitted by the air inlet and transmit the compressed air 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 a 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 rapidly transmit the first water vapor, the oxygen, and the nitrogen to the heat exchanger, the heat exchanger is further used to perform a cooling process on the first water vapor to obtain second water vapor and liquid water and transmit the liquid water to the evaporator, and the heat exchanger is further used to transmit the second water vapor, the oxygen, and the nitrogen to the nozzle, and the nozzle is used to perform an injection discharge process on the environment by using the second water vapor, the oxygen, and the nitrogen.

[0123] Specifically, the hydrogen flow needs to be connected with a hydrogen metering valve in series in front of the engine to provide hydrogen with a certain flow rate and pressure, and the water vapor needs to be injected into the combustion chamber by using the water vapor injection valve to achieve the reduction of the NOx emission of the combustion chamber. After the engine receives the two control quantities, a new working condition point is reached, at which time the speed sensor obtains a speed measurement value, which is also a 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 calculation, so as to obtain the water injection instruction quantity and the hydrogen instruction quantity, which are transmitted to the metering valve and the water vapor injection valve to generate the actual hydrogen quantity and the actual water injection quantity that are transmitted to the engine.

[0124] The application also provides an emission control example of a water injection aero-engine, as shown in the accompanying drawings. Figure 5 The specific processing process includes the following steps:

[0125] In step S501, system architecture information of an emission control system of a water injection aero-engine and flight operation information of the water injection aero-engine are obtained.

[0126] In step S502, based on the system architecture information, operation information of each device structure and operation association information between each device structure are identified, and based on the operation information of each device structure, each operation parameter corresponding to the device operation logic of each device structure is identified.

[0127] Step S503, based on each device running logic corresponding to each running parameter, construct the structure running model of each device structure, and based on the running 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 structure connection processing on each device structure to obtain the associated running model of the emission control system, and based on the data interaction logic parameters between each device structure, add them to the associated running model to obtain the adaptive control model of the emission control system.

[0129] Step S505, split the flight running information into sub-flight running information of each running phase, and for each running phase, based on the sub-flight running information of the running phase, identify the flight thrust information of the running phase and the duration of the running phase.

[0130] Step S506, the flight thrust information of the running phase and the duration of the running phase are used as the simulation phase thrust information of the running phase.

[0131] Step S507, based on the flight thrust information of each running phase, query the engine running database to obtain the engine running degree information of each running phase.

[0132] Step S508, based on the engine running degree information of each running phase, query the engine running database to obtain the stage running data range of each device structure corresponding to each running phase and the engine input information of the water injection aero-engine corresponding to each running phase.

[0133] Step S509, based on the stage running data range of each device structure, generate each engine simulation running data combination of the running phase, and use each engine simulation running data combination corresponding to each running phase and the engine input information of the water injection aero-engine corresponding to each running phase as the simulation engine running information of each running phase.

[0134] Step S510, for each running phase, based on the engine simulation running data combination of the running phase, execute the stage running process of the running phase through the adaptive control model to obtain the emission information corresponding to each engine simulation running data combination.

[0135] Step S511, the emission information corresponding to each simulation running data combination is used as the simulation running result of the running phase.

[0136] Step S512, for each operating stage, based on the corresponding emission information of each simulation running data set of the operating stage, generate the correlation distribution information between the stage running data of each device structure and the nitrogen and oxygen emissions.

[0137] Step S513, based on the correlation distribution information, identify the target stage running data of each device structure corresponding to the lowest emission amount of nitrogen and oxygen emissions, and the target emission information corresponding to the target stage running data of each device structure, and based on the target stage running data of each device structure, simulate the running process of each device structure through the adaptive control model, to obtain the device running process of each device structure and the simulation emission information of the operating stage.

[0138] Step S514, based on the target emission information corresponding to the target stage running data of each device structure and the simulation emission information of the operating stage, as the emission deviation information of the operating stage, and in the case that the emission deviation information is greater than the deviation information threshold, return to execute the step of combining each engine simulation running data set based on the running stage, and executing the stage running process of the operating stage through the adaptive control model, to obtain the stage running data of each device structure corresponding to each engine simulation running data set and the emission information corresponding to each engine simulation running data set.

[0139] Step S515, until the emission deviation information is greater than the deviation information threshold, based on the device running process of each device structure obtained by the last iteration and the target stage running data of each device structure obtained by the last iteration, generate the system control scheme of the operating stage.

[0140] Step S516, based on the system control scheme of each operating stage, control the emission control system of the water injection aero-engine to execute the stage running task of each operating stage.

[0141] It should be understood that although each step in the flowchart involved in each embodiment as described above is displayed in sequence according to the direction of the arrow, these steps are not necessarily executed in sequence according to the direction of the arrow. Unless otherwise specified herein, the execution of these steps is not strictly limited in sequence, and these steps can be executed in other sequences. Moreover, at least part of the steps in the flowchart involved in each embodiment as described above can include multiple steps or multiple stages, which are not necessarily executed at the same time, but can be executed at different times, and the execution sequence of these steps or stages is not necessarily sequential, but can be executed alternately or alternately with at least part of other steps or steps or stages in other steps.

[0142] Based on the same inventive concept, the application further provides an injection water aircraft engine emission control device for implementing the injection water aircraft engine emission control method.

[0143] In one exemplary embodiment, as shown in Figure 6 An injection water aircraft engine emission control device is provided, comprising: an acquisition module 610, an identification module 620, a generation module 630 and a control module 640, wherein:

[0144] The acquisition module 610 is configured to acquire system architecture information of an injection water aircraft engine emission control system and flight operation information of the injection water aircraft engine, and construct an adaptive control model of the emission control system based on the system architecture information.

[0145] The identification module 620 is configured to generate simulated stage thrust information of each operation stage based on the flight operation information, and identify 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 simulated operation results of each operation stage by the adaptive control model based on the simulated engine operation information, and identify system control schemes of each operation stage based on the simulated operation results of each operation stage.

[0147] The control module 640 is configured to control the injection water aircraft engine emission control system to perform stage operation tasks of each operation stage based on the system control schemes of each operation stage.

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

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

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

[0151] Based on the connection information between each of the device structures, the device structures are connected to obtain a correlation operation model of the emission control system, and based on the data interaction logic parameters between each of the device structures, the correlation operation model is added to obtain an adaptive control model of the emission control system.

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

[0153] The flight operation information is split into sub-flight operation information of each operation phase, and for each operation phase, flight thrust information of the operation phase and duration of the operation phase are identified based on the sub-flight operation information of the operation phase.

[0154] The flight thrust information of the operation phase and the duration of the operation phase are taken as simulation phase thrust information of the operation phase.

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

[0156] Based on the flight thrust information of each of the operation phases, an engine operation database is queried to obtain engine operation degree information of each of the operation phases.

[0157] Based on the engine operation degree information of each of the operation phases, the engine operation database is queried to obtain phase operation data ranges of each device structure corresponding to each operation phase and engine input information of the water injection aero-engine corresponding to each operation phase.

[0158] Based on the phase operation data ranges of each of the device structures, each engine simulation operation data combination of the operation phase is generated, and each engine simulation operation data combination corresponding to each operation phase and the engine input information of the water injection aero-engine corresponding to each operation phase are taken as simulation engine operation information of each operation phase.

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

[0160] For each operation phase, based on each engine simulation operation data combination of the operation phase, a phase operation process of the operation phase is executed through the adaptive control model to obtain emission information corresponding to each engine simulation operation data combination.

[0161] The emission information corresponding to each of the simulation operation data combinations is taken as a simulation operation result of the operation phase.

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

[0163] For each operating stage, based on the corresponding emission information of each simulation running data set of the operating stage, generate the correlation distribution information between the stage running data of each device structure and the nitrogen and oxygen emissions;

[0164] Based on the correlation distribution information, identify the target stage running data of each device structure corresponding to the lowest emission amount of nitrogen and oxygen emissions, and the target emission information corresponding to the target stage running data of each device structure, and based on the target stage running data of each device structure, simulate the running process of each device structure through the adaptive control model to obtain the device running process of each device structure and the simulation emission information of the operating stage;

[0165] Based on the target emission information corresponding to the target stage running data of each device structure and the simulation emission information of the operating stage, as the emission deviation information of the operating stage, and in the case that the emission deviation information is greater than the deviation information threshold, return to execute the stage running process of the operating stage based on each engine simulation running data set of the operating stage through the adaptive control model to obtain the stage running data of each device structure corresponding to each engine simulation running data set and the emission information corresponding to each engine simulation running data set.

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

[0167] Each module in the above water injection aero-engine emission control device can be realized by software, hardware and their combination in whole or in part. Each module can be embedded in or independent of the processor in the computer device in hardware form, or stored in the memory in the computer device in software form, so as to call and execute the operation corresponding to each module by the processor.

[0168] In an exemplary embodiment, a computer device is provided, which can be a terminal, and its internal structure diagram can be as follows 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 the 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 ability. 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 operating system and the computer program in the non-volatile storage medium to run. The input / output interface of the computer device is used to exchange information between the processor and the external device. The communication interface of the computer device is used to communicate with the external terminal in a wired or wireless manner. The wireless manner can be realized by WIFI, mobile cellular network, NFC or other technologies. The computer program is executed by the processor to realize a water injection aero-engine emission control method. 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 overlaid on the display screen, or a key, trackball or touchpad arranged on the shell 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 part of the structure related to the scheme of the present application, and does not constitute a limitation on the computer device to which the scheme of the present application is applied. The specific computer device can include more or fewer components than those shown in the figure, or combine certain components, or have a different component arrangement.

[0170] In one exemplary embodiment, a computer device is provided, including a memory and a processor, the memory storing a computer program, and the processor executing the computer program to realize the steps of the water injection aero-engine emission control method.

[0171] In one embodiment, a computer readable storage medium is provided, which stores a computer program, and the computer program is executed by the processor to realize the steps of the water injection aero-engine emission control method.

[0172] In one embodiment, a computer program product is provided, including a computer program, and the computer program is executed by the processor to realize the steps of the water injection aero-engine emission control method.

[0173] It should be noted that the user information and data involved in the present application are all information and data authorized by the user or authorized by all parties, and the collection, use and processing of related data need to comply with relevant regulations.

[0174] It can be understood by those skilled in the art that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing related hardware through a computer program, and 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 above-mentioned embodiments of each method. Among them, any reference to memory, database or other medium used in each embodiment provided by the present application can include at least one of non-volatile and volatile memory. Non-volatile memory can include read-only memory, magnetic tape, floppy disk, flash memory, optical storage, high-density embedded non-volatile memory, resistive memory, magnetic variable memory, ferroelectric memory, phase change memory, graphene memory, etc. Volatile memory can include random access memory or external cache memory, etc. As an illustration but not limitation, RAM can be in various forms, such as static random access memory or dynamic random access memory, etc. The database involved in each embodiment provided by the present application can include at least one of a relational database and a non-relational database. The non-relational database can include a distributed database based on a block chain, etc., without being limited thereto. The processor involved in each embodiment provided by the present application can be a general-purpose processor, a central processing unit, a graphics processing unit, a digital signal processor, a programmable logic device, a data processing logic device based on quantum computing, etc., without being limited thereto.

[0175] The technical features of the above embodiments can be combined in any way. In order to make the description simple, not all possible combinations of technical features in the above embodiments are described, but as long as the combination of technical features does not exist contradictory, it should be considered as the scope of the present application.

[0176] The above embodiments only express several implementation manners of the present application, and the description is more specific and detailed, but it should not be understood as a limitation on the scope of the patent of the present application. It should be noted that for those skilled in the art, without departing from the concept of the present application, some modifications and improvements can be made, which are all within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the appended claims.

Claims

1. A method of emissions control for a water-injected aircraft engine, characterized by, The method comprises: obtaining system architecture information of an emission control system of a water injection aero-engine, and flight operation information of the water injection aero-engine; based on the system architecture information, identifying operation information of each device structure and operation association information between each of the device structures, and based on the operation information of each of the device structures, identifying each operation parameter corresponding to a device operation logic of each of the device structures; based on each operation parameter corresponding to the device operation logic, constructing a structure operation model of each of the device structures, and based on the operation association information between each of the device structures, identifying connection information between each of the device structures and data interaction logic parameters between each of the device structures; based on the connection information between each of the device structures, performing structure connection processing on each of the device structures to obtain an associated operation model of the emission control system, and based on the data interaction logic parameters between each of the device structures, adding the data interaction logic parameters to the associated operation model to obtain an adaptive control model of the emission control system; splitting the flight operation information into sub-flight operation information of each operation stage, and for each operation stage, based on the sub-flight operation information of the operation stage, identifying flight thrust information of the operation stage and duration of the operation stage; taking the flight thrust information of the operation stage and the duration of the operation stage as simulation stage thrust information of the operation stage; based on the simulation stage thrust information of each of the operation stages, identifying simulation engine operation information of each of the operation stages; based on each of the simulation engine operation information, generating simulation operation results of each of the operation stages through the adaptive control model, and based on the simulation operation results of each of the operation stages, identifying system control schemes of each of the operation stages; based on the system control schemes of each of the operation stages, controlling the emission control system of the water injection aero-engine to perform stage operation tasks of each of the operation stages.

2. The method of claim 1, wherein, The method comprises: based on the flight thrust information of each of the operation stages, querying an engine operation database to obtain engine operation degree information of each of the operation stages; based on the engine operation degree information of each of the operation stages, querying the engine operation database to obtain stage operation data ranges of each of the device structures corresponding to each operation stage and engine input information of the water injection aero-engine corresponding to each operation stage; based on the stage operation data ranges of each of the device structures, generating each engine simulation operation data combination of the operation stage, and taking each engine simulation operation data combination corresponding to each operation stage and the engine input information of the water injection aero-engine corresponding to each operation stage as simulation engine operation information of each operation stage.

3. The method of claim 2, wherein, The method comprises: based on the simulation engine operation information of each of the operation stages, generating simulation operation results of each of the operation stages through the adaptive control model, comprising: For each operating stage, based on each engine simulation running data combination of the operating stage, a stage running process of the operating stage is performed through the adaptive control model to obtain emission information corresponding to each engine simulation running data combination; The emission information corresponding to each simulation running data combination is taken as a simulation running result of the operating stage.

4. The method of claim 3, wherein, The simulation running result of each operating stage is used to identify a system control scheme of each operating stage, including: For each operating stage, based on the emission information corresponding to each simulation running data combination of the operating stage, correlation distribution information between stage running data of each equipment structure and nitrogen oxide emission is generated; Based on the correlation distribution information, target stage running data of each equipment structure corresponding to the lowest nitrogen oxide emission amount and target emission information corresponding to the target stage running data of each equipment structure are identified, and a running process of each equipment structure is simulated through the adaptive control model based on the target stage running data of each equipment structure to obtain an equipment running process of each equipment structure and simulation emission information of the operating stage; The target emission information corresponding to the target stage running data of each equipment structure and the simulation emission information of the operating stage are taken as emission deviation information of the operating stage, and in a case where the emission deviation information is greater than a deviation information threshold, each engine simulation running data combination of the operating stage is used to perform a stage running process of the operating stage through the adaptive control model to obtain stage running data of each equipment structure corresponding to each engine simulation running data combination and emission information corresponding to each engine simulation running data combination; Until the emission deviation information is greater than the deviation information threshold, the equipment running process of each equipment structure obtained through the last iteration and the target stage running data of each equipment structure obtained through the last iteration are used to generate a system control scheme of the operating stage.

5. An emissions control system for a water-injected aircraft engine, characterized by, The system includes a water-injected aero-engine and an adaptive emission 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 water vapor injection valve, and the state space prediction model are respectively connected with the water-injected aero-engine, and the metering valve, the water vapor injection valve, and the state space prediction model are respectively connected with the adaptive emission controller; The adaptive emission controller is configured to send a hydrogen instruction amount to the metering valve and send a water injection instruction amount to the water vapor injection valve; The metering valve is configured to identify a hydrogen amount of the water-injected aero-engine based on the hydrogen instruction amount of the adaptive emission controller, and send the hydrogen amount to the water-injected aero-engine; The water injection valve is configured to identify an injection amount of the water injection aero-engine based on an injection instruction amount of the adaptive emission controller, and send the injection amount to the water injection aero-engine. The water injection aero-engine is configured to generate a rotation speed measurement value, and send the rotation speed measurement value to the state space prediction model. The state space prediction model is configured to identify a scheduling parameter of the state space prediction model based on the rotation speed measurement value sent by the water injection aero-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 emission controller. The adaptive emission controller is further configured to generate a new hydrogen instruction amount of the metering valve and a new water injection instruction amount of the water injection valve based on the new state space prediction model, replace the hydrogen instruction amount with the new hydrogen instruction amount, and replace the water injection instruction amount with the new water injection instruction amount; and return to the step of sending the hydrogen instruction amount to the metering valve and sending the water injection instruction amount to the water injection valve.

6. The system of claim 5, wherein, The water injection aero-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, and the turbine are connected to the combustion chamber respectively, and the turbine, the evaporator, and the nozzle are connected to the heat exchanger respectively; The water 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 configured to transmit air to the compressor, and the compressor is configured to compress the air transmitted by the air inlet and transmit the compressed air to the combustion chamber; The heat exchanger is configured to convert liquid hydrogen into gaseous hydrogen, and transmit the gaseous hydrogen to the combustion chamber; The evaporator is configured to convert liquid water into water vapor, and transmit the water vapor to the combustion chamber; The combustion chamber is configured to perform a 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; and the turbine is configured to rapidly transmit the first water vapor, the oxygen, and the nitrogen to the heat exchanger; The heat exchanger is further configured to cool the first water vapor to obtain second water vapor and liquid water, and transmit the liquid water to the evaporator; and the heat exchanger is further configured to transmit the second water vapor, the oxygen, and the nitrogen to the nozzle; The nozzle is configured to perform water injection and emission treatment on the environment by using the second water vapor, the oxygen, and the nitrogen.

7. An emissions control device for a water-injected aircraft engine, characterized by, The device comprises an acquisition module, an identification module, a generation module, and a control module, and when the device is executed, the steps of the method in any one of claims 1 to 4 are implemented. An acquisition module is configured to acquire system architecture information of an emission control system of a water-injected aero-engine and flight operation information of the water-injected aero-engine, and construct an adaptive control model of the emission control system based on the system architecture information; An identification module is configured to generate simulated stage thrust information of each operation stage based on the flight operation information, and identify simulated engine operation information of each operation stage based on the simulated stage thrust information of each operation stage; A generation module is configured to generate simulated operation results of each operation stage by the adaptive control model based on the simulated engine operation information of each operation stage, and identify system control schemes of each operation stage based on the simulated operation results of each operation stage; A control module is configured to control the emission control system of the water-injected aero-engine to perform stage operation tasks of each operation stage based on the system control schemes of each operation stage.

8. A computer device comprising a memory and a processor, the memory storing a computer program, characterized in that, The computer program is executed by the processor to implement the steps of the method in any one of claims 1 to 4.

9. A computer readable storage medium having stored thereon a computer program, characterized in that, The computer program is executed by the processor to implement the steps of the method in any one of claims 1 to 4.

10. A computer program product comprising a computer program, characterized in that, The computer program is executed by the processor to implement the steps of the method in any one of claims 1 to 4.

Images