65 results about "Combustion instability" patented technology

The invention relates to the technical field of combustion monitoring, and discloses a combustion instability boundary prediction system based on complex environment condition analysis, and the system comprises a multi-source sensing module, a data fusion module, an anti-interference processing module, an instability feature library, an intelligent decision engine and a digital twinborn body. A dynamic environment interference compensation mechanism is constructed, spectrum correction parameters are configured according to different environment working conditions during real-time prediction of a combustion instability boundary, the problem of spectrum distortion caused by environment disturbance on combustion dynamic parameters is eliminated in real time, spectrum interference deviation of a combustion measurement position can be automatically sensed and corrected, and real-time prediction of the combustion instability boundary is realized. The accuracy of combustion instability sensitive feature extraction is guaranteed, the instability early warning error is reduced, a flame pose real-time tracking system is deployed, fuel control parameter self-adaptive adjustment is triggered immediately when it is detected that the pose is abnormal, autonomous correction of the combustion instability feature recognition position is achieved, and it is guaranteed that the feature capture space is accurately positioned.

The invention discloses a coal-fired boiler combustion instability monitoring method and system based on multi-parameter fusion, and the method comprises the steps: constructing a hearth flame imaging system which comprises an image detector, a lens, a stainless steel cavity and a cooling air channel; the flame image intensity is converted into radiation intensity through blackbody furnace calibration, and the flame temperature and emissivity are calculated based on the Planck law; extracting flame characteristic parameters including average radiation intensity, temperature, emissivity and standard deviation thereof; constructing a load-flame characteristic parameter model, and predicting parameter reference values under different loads through multiple linear regression; and calculating a combustion instability index CII, carrying out weighted fusion on the normalized deviation of the real-time measured value and the predicted value, and judging that CII is equal to 1 when the flame area is 0 or the average temperature is lower than 900 DEG C. The flame radiation image and the unit operation parameters are fused, and the limitation of traditional single-parameter monitoring is solved; combustion instability dynamic quantitative evaluation is achieved through the CII index, and the method is suitable for early warning of the deep peak regulation working condition.

The invention discloses an SVR combustion instability prediction method and system, and relates to the field of energy power and intelligent control, and the method comprises the steps: obtaining a fault combustion flame chemiluminescence signal, and generating a signal data set comprising a training data set and a test data set; establishing a support vector regression model based on the training data set; evaluating the support vector regression model by using the test data set, and adjusting according to an evaluation result to obtain a prediction model; using the prediction model to predict to-be-predicted sample data; the historical flame chemiluminescence signal data of the gas turbine under different working conditions are adopted as data input and can be used for predicting the working state of the gas turbine after a certain time delay, and the model can perform algorithm processing on the flame chemiluminescence signal measured by the gas turbine and predict the change trend of the future moment. The occurrence time of the unstable combustion can be predicted, and enough time is reserved for the control process of the unstable combustion.

The invention relates to the technical field of industrial automation control, in particular to a boiler combustion stability intelligent control method based on a self-adaptive neural network, and the method comprises the steps: collecting multi-source heterogeneous data of a boiler system, the multi-source heterogeneous data comprises a high-frequency vibration data flow and a low-frequency process data flow, carrying out space-time alignment preprocessing on the multi-source heterogeneous data; and calculating a self-adaptive penalty factor based on the current load characteristics and the vibration energy, and performing variational mode decomposition on the high-frequency vibration data stream by using the self-adaptive penalty factor to obtain a combustion characteristic component. According to the method, the gain of the neural network controller is dynamically adjusted through the comprehensive stability risk index, smooth switching of a control strategy between steady-state fine adjustment and fault strong control is achieved, and therefore the fast inhibition capacity for combustion instability is remarkably improved while the steady-state precision of a combustion system is guaranteed.

The invention discloses an impedance mismatch design method for a gas turbine combustion chamber multi-flame-tube cross-flame system, which comprises the following steps: forming a combustion chamber by 12 flame tubes in a gas turbine through cross-flame tubes on the basis of a graph theory, modeling as a cyclic graph, and constructing an adjacent matrix and a Laplacian matrix; constructing a system matrix based on the angular frequency of the flame tube and the coupling strength of the cross flame tube; calculating a characteristic value and a characteristic vector of a system matrix, determining an oscillation frequency and a vibration mode, and identifying a degenerate mode; by modifying the coupling strength of at least one cross flame tube and recalculating the eigenvalue and eigenvector of the system matrix, the degenerate frequency is split, and the symmetry is broken; and according to the frequency and the mode after splitting, parameters of the combustion chamber are adjusted to optimize the combustion stability. Modeling of a complex system is simplified based on a graph theory method, the calculation cost is reduced, the symmetry of the system is broken by modifying the coupling strength of the cross flame tubes, the degenerate frequency is split, and combustion instability is relieved.

The invention discloses a porous medium sweating and cooling combustion chamber based on a ceramic matrix composite material, and relates to the technical fields of gas turbines, new energy and the like. In order to solve the problem of combustion instability such as combustion oscillation of a traditional gas turbine combustion chamber, a ceramic-based porous medium combustion chamber structure is adopted, liquid fuel infiltrates from the outer wall face of a porous medium and is evaporated and gasified on the inner wall, and then combustion occurs. The gasification reaction of the liquid fuel in the porous medium and on the wall surface can take away a large amount of heat, so that the effects of heat insulation, heat protection and wall surface cooling are achieved, and the combustion chamber can be protected from thermal damage. On the other hand, traditional jet flow or rotational flow combustion is replaced by wall face evaporation combustion, and combustion oscillation caused by uneven mixing or jet flow is avoided.

The invention discloses a strong premixing combustion chamber for restraining combustion noise based on a Helmholtz resonant cavity, and relates to the technical field of energy and power. Air and fuel enter the mixing cavity through corresponding connectors to be strongly premixed, premixed gas enters the hearth to be combusted through slit channels among water cooling channel branch pipes, a water cooling channel array can prevent backfire, the Helmholtz resonant cavity is connected with the hearth through a cavity neck and is provided with an air film cooling channel, the size of the Helmholtz resonant cavity needs to measure combustion noise, and a frequency spectrum is analyzed to obtain characteristic frequency. The neck length, the cross section area and the resonant cavity volume are calculated according to a Helmholtz resonance formula, and the sound absorption effect is verified in combination with a low-order thermoacoustic model. Combustion efficiency is improved through the strong premixing and slit water cooling design, tempering is prevented, NOx is reduced, the diffusion combustion problem is solved, the targeted design resonant cavity is matched with air film cooling, the defects that an existing silencing structure is large in size, poor in adaptation and low in high-temperature reliability are overcome, complex active control is not needed, cost is low, applicability is high, and the application range is wide. And cooperative control of high efficiency, low emission and unstable combustion is realized.

The invention discloses a combustion instability control method based on reinforcement learning, which adopts a training mode of combining digital environment pre-training and entity environment retraining, improves the control precision and saves the training time on the premise of guaranteeing the safety. Firstly, a combustion device digital model is constructed based on a mechanism model or experimental data to serve as a reinforcement learning pre-training environment; and then, the intelligent agent performs digital environment pre-training, generates a control action based on state feedback, and realizes strategy optimization through a reward function. And finally, the pre-trained intelligent agent is migrated to an entity combustion device for retraining, key parameters such as pressure pulsation and heat release pulsation are obtained through a state monitoring module, boundary verification is conducted on control actions in combination with a safety function, and an actuator achieves combustion instability self-adaptive control by adjusting fuel / air pulsation parameters. Dynamic pressure and flame heat release rate pulsation of a complex combustion system can be effectively restrained, the service life of a combustion device is prolonged, and the operation safety of the combustion device is improved.

The invention relates to the technical field of efficient clean energy, and discloses a fuel Wobbe number stabilizing system for a chemical regenerative gas turbine and a control method, and the system comprises an exhaust bypass mixing regulation and control component which comprises a regulation and control module, a monitoring module and a control module; the regulation and control module comprises a diverter valve and a bypass flow regulating valve, the inlet end of the diverter valve is connected to an exhaust outlet of the turbine, the outlet end of the diverter valve is sequentially connected with the heat regenerator through a first branch, the bypass flow regulating valve is further connected between the diverter valve and the heat regenerator through a second branch, and the first branch and the second branch are connected to the cracker through a confluence pipeline; the monitoring module comprises a first temperature sensor, a first pressure sensor, a densimeter, a rapid component analyzer and a temperature monitoring unit; the control module generates a control instruction for the mixing temperature of exhaust gas entering the cracker according to the comparison result of the wobbe number estimated value and the wobbe number target reference value, and adjusts the opening degree of the bypass flow adjusting valve so as to solve the technical problem of unstable combustion.

The invention discloses an afterburner adopting a gas-liquid bimodal-cross hole spray rod for oil supply, and relates to the technical field of aero-engines. Comprising a turbine located at the axis position of an inner duct in the air incoming flow direction; the mixer is arranged between the turbine and the inner duct wall body; the rectification support plates are provided with air inlet channels, and the multiple rectification support plates penetrate through the outer duct and are vertically and uniformly arranged in the circumferential direction of the inner duct; the oil injection rod is provided with an air flow channel and a fuel oil channel, and the air inlet channel is communicated with the air flow channel; and the oil injection rod is radially arranged in the rectification support plate. On the basis that the structural complexity of an afterburner of a turbine engine and a combustion chamber of a subsonic combustion ramjet engine is not increased, the atomization performance and the oil-gas mixing uniformity of fuel oil in the afterburner / ramjet combustion chamber are remarkably improved, the combustion efficiency of the engine is improved, and the combustion instability is reduced.

The invention discloses a combustion instability feedforward control method and system based on modal early-stage identification, and belongs to the technical field of combustion control, and the method comprises the steps: S1, collecting a multi-physical field signal in a combustion chamber in real time; s2, based on the multi-physical field signal, identifying a current dominant mode and an amplitude increasing trend of combustion instability in real time; s3, double-condition judgment is carried out, and control is triggered before the oscillation amplitude reaches a preset safety threshold value; s4, matching a corresponding open-loop feedforward control strategy from a preset control strategy library; and S5, generating and applying a modal specific control instruction to drive an execution mechanism to perform intervention. According to the combustion instability feedforward control method and system based on modal early identification, early warning and modal specific control of combustion instability are achieved, the problems of phase mismatch and non-linear inadaptation are effectively avoided, the thermo-acoustic damage risk is remarkably reduced, and the reliability of the system is improved. And the robustness, the real-time performance and the engineering applicability of the control system are improved.

The application discloses a gas turbine regulation and control method and system based on a decentralized control system, and particularly relates to the field of gas turbine regulation and control, and comprises the following steps: S1, synchronously collecting gas turbine operation parameters by using a distributed sensor array; S2, performing feature engineering processing on local perception data by an edge computing node; S3, based on a decentralized control system architecture, adopting an improved model predictive control algorithm to realize control quantity decoupling; S4, after completing each control cycle, evaluating the control effect; S5, establishing a regulation and control threshold, judging the evaluation according to the regulation and control threshold, and issuing a corresponding signal according to the judgment; the application synchronously collects multi-field coupling parameters by using a distributed sensor array and realizes real-time processing of local data through an edge computing node, thereby improving the dynamic response capability of the gas turbine under multi-dimensional working conditions and reducing the occurrence rate of combustion instability events.

This application relates to the field of burner combustion control technology and discloses a burner fuel grading control optimization method. This method calculates the background noise energy during a silent monitoring period and selects the frequency of the minimum energy value as the target micro-perturbation frequency. A sinusoidal micro-perturbation signal is generated based on this frequency and superimposed on the command of the shift fuel regulating valve. Valve displacement and combustion chamber sound pressure signals are simultaneously acquired and orthogonal decoding is performed. Electromechanical transfer gain, thermoacoustic gain, and dynamic transmission phase difference are calculated and obtained. Based on the electromechanical transfer gain, it is determined whether amplitude compensation should be performed. A two-dimensional linkage verification matrix is ​​constructed by combining the time derivatives of the thermoacoustic gain and the dynamic transmission phase difference, thereby distinguishing between pure thermoacoustic mode over-limit and physical spatial anomalies, and executing the corresponding fuel grading closed-loop regulation or safety interlocking procedure. This invention eliminates valve mechanical execution errors, accurately distinguishes combustion instability conditions under strong noise backgrounds, and improves the safety of combustion system operation.

This invention discloses a hydrogen-ammonia fuel injector with a swirling structure. The injector includes a fuel injector housing, an ammonia inlet assembly, an electronic control assembly, a valve assembly, an air intake assembly, and an injection assembly. The injection assembly includes an injector housing, a hydrogen-ammonia interface, a fixed sleeve, a flow pipe, a sliding sleeve, a fixing block, a return spring, and a return assembly. Swirling vanes are installed inside the flow pipe, forcing liquid ammonia and hydrogen into a high-speed swirling state. Centrifugal force and shear force are used to achieve uniform mixing of the two phases, forming a homogeneous hydrogen-ammonia fuel mixture. Combined with the hyperboloidal outlet channel at the bottom of the flow pipe, the injection flow pattern is organized, achieving an integrated function of "hydrogen premixing - forced swirling mixing - injection flow pattern organization." This fundamentally solves the combustion instability problem caused by uneven mixing, significantly improves the uniformity of the hydrogen-ammonia fuel mixture, and, combined with the flow pattern organization effect of the hyperboloidal outlet, effectively improves combustion stability and fuel utilization, reducing NOx emissions and ammonia slip.

The present application relates to the technical field of engine control, in particular to a judgment optimization method and device for residual exhaust gas causing gasoline engine idle speed jitter. Idle speed jitter information is collected and it is judged whether it meets the condition of gasoline engine idle speed jitter caused by combustion instability, if yes, it is judged whether the idle speed jitter is caused by residual exhaust gas according to the gasoline in-cylinder pressure characteristic curve and the maximum peak angle of explosion pressure, if yes, debugging is carried out by increasing the intake pressure of gasoline engine and synchronously retarding the ignition angle, and the optimization process is realized. The present application discriminates the type of idle speed jitter caused by combustion instability, analyzes the cylinder pressure characteristic curve, if the cylinder combustion speed of a gasoline cylinder presents the alternating phenomenon of "low-high-low-high", it can be judged that the residual exhaust gas amount is the key factor affecting the jitter, based on which debugging can be carried out by increasing the intake pressure and synchronously retarding the ignition angle, the judgment optimization method is simple, and the period of consumption is short.

The invention discloses a fuel-rich or oxygen-rich pre-combustion chamber partition combustion method. The method comprises the steps that a pre-combustion chamber is divided into two parts, namely a complete combustion area and an expansion cracking area; a rich propellant is set as a propellant A and comprises a small-flow propellant A and a large-flow propellant A, and the other propellant is set as a propellant B, so that the small-flow propellant A and the propellant B are both sprayed into the complete combustion area and are ignited and fully and completely combusted in the complete combustion area in the form of the optimal mixing ratio, and high-temperature fuel gas is formed; a large-flow propellant A is directly introduced into the expansion cracking area, and when high-temperature fuel gas is cooled, the propellant A absorbs heat and is expanded and decomposed to form high-pressure gas. Partition combustion is adopted, the optimal mixing ratio can be accurately achieved in a complete combustion area, and therefore sufficient and stable combustion of fuel is guaranteed, and the problems that due to the fact that propellants in the pre-combustion chamber greatly deviate from the ideal mixing ratio and mixing is uneven, combustion is unstable are effectively solved.

The present disclosure provides a method for determining parameters of a thermoacoustic panel in an annular combustion chamber and an annular combustion chamber, relating to the field of aeroengine technology. The method comprises: constructing a first scattered acoustic field function formed by the thermoacoustic panel in the combustion chamber, constructing a second scattered acoustic field function formed by the thermoacoustic panel in a back cavity, and constructing a third scattered acoustic field function formed by a heat source in the combustion chamber; processing the first scattered acoustic field function, the second scattered acoustic field function, and the third scattered acoustic field function by Laplace transform to obtain a characteristic equation; if the characteristic solution of the characteristic equation indicates that the current setting parameters of the thermoacoustic panel meet the requirements for suppressing low-frequency modal combustion instabilities, then determining the current setting parameters of the thermoacoustic panel as target setting parameters of the thermoacoustic panel in the annular combustion chamber, wherein the setting parameters include setting position parameters and / or size parameters of the thermoacoustic panel. The present disclosure can effectively suppress low-frequency modal combustion instabilities in an annular combustion chamber.

The present invention provides a method for quantifying the uncertainty of the linear growth rate of combustion instability, including: Step 1, constructing a kinetic process model of the combustion system; Step 2, identifying the linear growth rate; Step 3, identifying the noise intensity; Step 4, quantifying the uncertainty. Based on the linear stochastic dynamics Fokker-Planck equation, the present invention extracts the noise intensity from the limit cycle pressure oscillation data. The Monte Carlo simulation method is used to numerically solve the nonlinear stochastic differential equation to generate more than 100 sets of time series of the growth process from small perturbations to finite amplitudes. Different time intervals are selected, the mean values and standard deviations of the identification results are compared, and the interval with smaller deviation and variance is selected as the linear growth stage. The growth rates of each group in the linear growth stage are identified and the mean value and standard deviation are taken to quantify the uncertainty under this working condition.

The present disclosure relates to a combustion system using carbon-free fuels such as hydrogen or ammonia, and more particularly, to an ammonia-hydrogen co-combustion system that enhances the reactivity of ammonia and reduces nitrogen oxides in exhaust gas after combustion.

The utility model provides a torch head for eliminating smoke by using compressed air, which relates to the technical field of tail gas treatment in the petrochemical industry and comprises a torch cylinder body, an incandescent light ignition device, a compressed gas cylinder, an induced draft fan and an exhaust pipe. According to the torch head for eliminating smoke by using the compressed air, after emptying gas generated in industrial production enters a torch system through the gas inlet cylinder, the emptying gas stably enters the torch cylinder body through the connecting cylinder. And the emptied gas is ignited by the incandescent light in the torch cylinder body for combustion treatment. The induced draft fan is started, negative pressure is formed in the compressed gas cylinder, and external compressed gas enters the compressed gas cylinder and then is sprayed into the torch cylinder in a high-speed jet flow mode through exhaust holes in a hole plate in the side face of the periphery of the exhaust pipe. The compressed gas of the high-speed jet flow is fully mixed with the emptying gas, so that the disturbance of the gas is enhanced, and the emptying gas is more fully combusted. And meanwhile, the supplement of the compressed gas is beneficial to stabilizing the flame, so that the flame is prevented from being extinguished or unstable combustion caused by factors such as strong wind is prevented.

The invention relates to a method for identifying a triggering amplitude of unstable combustion, which belongs to the technical field of aerospace engine evaluation, solves the technical problems of poor applicability, low precision and large deviation of triggering amplitude identification, and comprises the following steps of: acquiring a pressure pulsation time sequence of a combustion chamber, calculating and fitting a pressure time sequence power spectrum, and calculating the triggering amplitude of the combustion chamber. Obtaining peak frequency, noise intensity and linear growth rate; performing Hilbert transformation on the pressure pulsation time sequence, performing modulo, dividing the value range of the amplitude time sequence, substituting peak frequency, noise intensity and linear growth rate as initial values into an analytical solution of an FK equation, and fitting the analytical solution of the FK equation by using a discrete transition probability density function to obtain an analyzed transition probability density function; and logarithm taking, differentiation and operation are carried out on the analyzed transition probability density function to obtain a nonlinear growth rate of pressure oscillation, and fitting is carried out to obtain a combustion instability trigger amplitude.

The invention discloses a marine dual-fuel fire-tube boiler, and relates to the technical field of marine boilers. The problems that in combustion of an ammonia boiler, needed ignition energy is large, the combustible range is narrow, the laminar flow combustion speed is low, combustion is unstable due to natural nitrogen, and nitrogen oxide emission is high are solved. Boiler feed water enters the feed water heating cabin through the feed water heating water inlet, flows out of the feed water heating water outlet after being heated, enters the water inlet of the evaporation cabin, is heated into saturated steam in the evaporation cabin, enters the steam pipeline through the steam outlet and then is supplied to steam supply equipment. The feed water heating cabin is arranged in the fire-tube boiler, so that the smoke exhaust temperature can be greatly reduced, and the smoke exhaust loss is reduced; according to the device, two fuels of No.0 diesel oil and ammonia gas can be combusted together, the clean energy ammonia gas fuel which is easy to store and low in price can be fully utilized, stable combustion of the ammonia fuel can be guaranteed, the heat value of the fuel can be properly improved, and then the heat exchange efficiency is improved to 90%-95%. The invention is suitable for the field of fire-tube boilers.

The application discloses a liquid-liquid coaxial centrifugal nozzle combustion instability active control injection panel, which comprises an upper cover plate, an internal centrifugal nozzle, an external centrifugal nozzle and a pressure measuring device; the upper cover plate comprises a cylindrical cavity A, a cylindrical cavity B and a propellant supply flow channel; the external centrifugal nozzle comprises an outer rotational flow chamber, an outer straight section and a jet base plate; the jet base plate is detachably connected with a combustion chamber in a sealing mode; a plurality of secondary propellant injection holes are uniformly arranged on the jet base plate in a circumferential direction; each secondary propellant injection hole is connected with a secondary propellant collecting cavity and the combustion chamber; the internal centrifugal nozzle comprises an inner rotational flow chamber and an inner straight section coaxially arranged at the bottom of the inner rotational flow chamber. When the liquid-liquid coaxial centrifugal nozzle is in combustion instability, the pressure oscillation amplitude in the combustion chamber is monitored, then the flow of secondary fuel injection is actively and dynamically adjusted, the pressure oscillation amplitude in the combustion chamber is continuously observed, and the active control effect is realized.

The invention discloses a single-nozzle combustion stability evaluation method and a test system, and relates to the technical field of engines, and the method comprises the steps: determining the working time t1 of the single ignition operation of a single-nozzle combustion stability test device according to the moment when the combustion of an engine is unstable; determining a single ignition time sequence according to the working time t1; a plurality of groups of mixing percentages with different percentage values are set, a plurality of groups of working condition percentages with different percentage values are set, the group number of the mixing percentages and the group number of the working condition percentages are the same, and under the condition that one group is selected from the plurality of groups of mixing percentages and the plurality of groups of working condition percentages, a combustion stability test is carried out according to a single ignition time sequence. And testing the combustion stability until each group of the mixing percentage and the working condition percentage is subjected to the combustion stability test, and recording the percentage of the number of times of generating the excitation combustion instability in the number of times of all the combustion stability tests. And transversely comparing the stability of different nozzles by taking the percentage of the combustion instability problem in the test matrix as a quantitative index.

This invention discloses a method and system for adaptive allocation of preheating power for a target drone turbojet engine based on dynamic compensation of environmental parameters. It relates to the field of aero-engine control and thermodynamic process optimization technology, and includes: collecting flight environmental parameters and calculating the mass flow rate of air at the combustion chamber inlet; constructing a multi-condition compensation matrix to determine aerodynamic reference quantities; dividing the combustion chamber into regions based on the reference quantities; establishing a thermodynamic unsteady model and generating a combustion instability sensitivity matrix; calculating the dynamic instability index and performing thermoacoustic risk classification; constructing a preheating energy transfer matrix based on the risk level; introducing an inertia factor to achieve adaptive allocation of preheating power in each region; converting the allocation strategy into injector pulse modulation control commands; and performing dynamic iterative optimization by combining a spatiotemporal evolution model of thermoacoustic parameters and wall temperature. This invention can achieve refined allocation of preheating power, effectively suppress thermoacoustic instability, and improve engine preheating uniformity and operational reliability.

The invention discloses a gas turbine combustion stability online regulation and control method based on deep learning, and aims to solve the problem of combustion instability prevention and control under the scene that fuel components / heat values are variable and are constrained by emission. The method comprises the following steps: firstly, fusing unit load, fuel characteristics and dynamic pressure of a combustion chamber, and constructing a ten-dimensional fuel characteristic package and a 2,000-448-dimensional pressure sequence; then, through a self-adaptive stability margin estimation network containing a stability judgment trunk and a fuel condition calibration layer, in combination with comparison event online calibration, self-adaptive stability margin of cross-fuel alignment is output; matching the risk level with the threshold group, screening regulation and control actions in an emission qualified adjustable range, calculating the amplitude, and generating a regulation and control instruction draft; and finally, through closed-loop verification, outputting a final regulation and control instruction or a rollback instruction according to the stable response quantity. According to the method, online self-adaptive evaluation of the stability margin and closed-loop regulation and control under emission constraint are realized, the combustion instability risk is effectively inhibited, and the operation safety and continuity of the unit are improved.

According to the combustion instability evaluation method and system during low-load operation provided by the invention, the thermal power generation combustion state abnormity analysis model is trained through the comparison result between the second type division result example and the fusion identification example; the trained thermal power generation combustion state abnormity analysis model is used for determining an object type analysis model, and a thermal power generation combustion state instability evaluation result is determined through the object type analysis model. In the process of model updating training, the initial thermal power generation combustion data example does not need to be obtained, only the newly added thermal power generation combustion data example is used for training the initial object type analysis model, the model performance can be improved when new data is learned, and therefore the accuracy and precision of thermal power generation combustion state evaluation can be improved.

The present invention relates to a combustion system using a carbon-free fuel such as hydrogen or ammonia, and more specifically, relates to an ammonia and hydrogen co-combustion system which improves the reactivity of ammonia and reduces nitrogen oxides in the exhaust gas after combustion.

The utility model discloses a gas flow adjusting device for a burner of a sleeve kiln, which relates to the technical field of sleeve kilns and comprises a sleeve kiln body. The installation support is arranged on the front side of the sleeve kiln body, a PIC remote IO station is installed at the front end of the installation support, a gas nozzle is arranged at the right end of the sleeve kiln body, an automatic adjusting valve is arranged above the gas nozzle, and a gas through pipe is arranged on the left side of the automatic adjusting valve. The lower part of the coal gas through pipe is connected with a pneumatic stop valve; connecting discs are arranged at the left end and the right end of the automatic adjusting valve; the problems that the coal gas flow is difficult to accurately control, unstable combustion is easily caused, the heat efficiency and the product quality of the sleeve kiln are influenced, and energy waste and unstable factors in the production process are further aggravated due to the fact that the coal gas flow of a burner in the kiln is controlled by a manual valve and the coal gas flow is difficult to accurately control, and operators are difficult to accurately adjust in time when working conditions change are solved. And meanwhile, the labor amount of workers is increased.

The invention discloses a hearth negative pressure dynamic compensation control method and device, electronic equipment and a storage medium, relates to the technical field of equipment control, and aims to dynamically adjust the proportion and integral coefficient of an induced draft fan regulator in combination with hearth pressure deviation and change rate thereof so as to avoid the limitation that fixed PID parameters are difficult to adapt to dynamic working conditions; in addition, an enhanced feed-forward signal containing an air feeder public instruction and a pressure change rate feed-forward item can be generated, a coupling compensation mechanism under the dynamic working condition is supplemented, meanwhile, the dynamic upper and lower limits of a frequency conversion instruction are calculated according to the load for boundary constraint, and pressure fluctuation caused by instruction abnormity is prevented. The technical problems that combustion instability is caused by hearth pressure fluctuation and improvement of boiler operation efficiency is restricted due to the fact that existing single-loop control adopts fixed PID parameters and a single feedforward signal and lacks a dynamic coupling compensation mechanism can be solved. The technical effects of stabilizing the hearth negative pressure, avoiding combustion instability, improving the boiler operation efficiency and enhancing the hearth pressure control adaptability under the dynamic working condition are achieved.