35 results about "Combustion instability" patented technology

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 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 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 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 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.

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.

The invention relates to the field of thermal power plant intelligent control, and provides a thermal power generating unit depth peak regulation coordination method and system, and the method comprises the steps: collecting a video data stream and a broadband sound wave signal, and generating a high-dimensional time sequence data frame sequence through the alignment of acoustic atom dictionary timestamps; extracting visual and acoustic feature embedding vectors, constructing a heterogeneous dynamic graph, and analyzing spatio-temporal evolution to generate a future combustion instability index; an unstable mode code and a future risk index are generated based on an expert rule base, an enhanced state vector is constructed by fusing real-time macroscopic state parameters, and an optimal control instruction set is generated by an intelligent agent through optimization under dynamic constraint; the instruction set is decoded into a control signal sequence through multiple safety verification, a risk index difference value before and after intervention is compared to generate a validity evaluation index, and the validity evaluation index is packaged into an experience playback tuple to update agent parameters. According to the method, multi-mode space-time prediction and self-adaptive control are fused, a combustion instability precursor prediction and look-ahead control closed loop is constructed, and the method is suitable for intelligent monitoring and advanced process control of a thermal power plant.

The invention relates to the technical field of internal combustion engine control, and discloses a combined control system and protection method for a hydrogen-rich gas internal combustion engine, comprising the following steps: acquiring operating parameters of the internal combustion engine in real time, the operating parameters at least comprising a gas source hydrogen concentration value, an average cylinder temperature, a vortex exhaust temperature and a current output power; and through a'priority decoupling 'strategy, after lambda reaches a lean-burn stability limit, the variable is forcibly locked, and seamless switching to EGR combustion speed reduction and ignition phase delay is achieved. The combustion speed of hydrogen-rich gas fuel is reduced through EGR, ignition delay resists the fast combustion characteristic of hydrogen to restrain detonation pressure, a proper ignition advance angle is matched according to different hydrogen concentration values, lambda and EGR rates, and the problems that only by adjusting the excess air coefficient, the system is extremely prone to death under the hydrogen-rich working condition, the lean burn limit can be touched due to the fact that lambda is increased for cooling, and the combustion efficiency is low are solved. And combustion is unstable, and the defect that the combustion speed of hydrogen is too high and knocking occurs due to the fact that lambda is reduced for stable combustion is overcome.

The invention discloses a clean fuel coupling thermal load control method under a low-load working condition of a coal-fired boiler, and belongs to the technical field of flexible peak regulation of the coal-fired boiler. According to the control method, based on multi-point temperature monitoring data in a hearth, areas with unstable combustion and uneven thermal load distribution under low load are dynamically identified; by cooperatively regulating and controlling the blending combustion proportion, the injection momentum and the injection time of hydrogen, ammonia gas, methane or methanol clean fuel at different heights and circumferential positions of the hearth and linkage with graded air distribution, accurate optimization and reconstruction of hearth heat load distribution are achieved. According to the control method, flame pulsation, local overtemperature of the water cooling wall and thermal deviation during low-load operation can be effectively restrained, the flow field structure of four-corner tangential combustion is strengthened and maintained, and the requirements for deep peak regulation and clean operation of the unit are met on the premise that combustion stability and heating surface safety are guaranteed.

This invention discloses a method for identifying the linear growth rate of combustion instability, comprising: establishing a stochastic dynamics model of the combustion system; constructing an identification model based on the stochastic dynamics model of the combustion system; and identifying the linear growth rate, nonlinear saturation coefficient, and noise intensity of the combustion system based on the identification model. This invention aims to solve the problem in traditional methods where the changes in the linear growth rate, nonlinear saturation coefficient, and noise intensity cannot be identified from the data when the units of the experimental data are transformed.

The application discloses a method for impedance mismatch design of a multi-flame tube combined flame system of a gas turbine combustion chamber, comprising the following steps: based on graph theory, 12 flame tubes in a gas turbine are combined through a combined flame pipe to form a combustion chamber, modeling is performed as a cycle graph, and an adjacency matrix and a Laplace matrix are constructed; based on the angular frequency of the flame tube and the coupling strength of the combined flame pipe, a system matrix is constructed; eigenvalues and eigenvectors of the system matrix are calculated, oscillation frequency and vibration mode are determined, and degenerate modes are identified; by modifying the coupling strength of at least one combined flame pipe, the eigenvalues and eigenvectors of the system matrix are recalculated, degenerate frequency splitting is performed, and symmetry is broken; according to the split frequency and mode, the parameters of the combustion chamber are adjusted to optimize the combustion stability. The application simplifies the modeling of a complex system based on a graph theory method, reduces the calculation cost, breaks the symmetry of the system by modifying the coupling strength of the combined flame pipe, splits the degenerate frequency, and relieves the combustion instability.

The utility model provides a kind of hot blast furnace coal powder's injection device, it is related to coal powder injection technology field, including air preheating pipe and fixed on its upper surface coal powder preheating pipe, air preheating pipe one end is equipped with fixed sleeve, fixed sleeve side surface is embedded with filter plate, fixed sleeve inside is provided with fixed assembly, fixed sleeve is fixed in air preheating pipe one end by fixed assembly.The hot blast furnace coal powder's injection device passes through second fan and passes into air preheating pipe in high-temperature waste gas, and the air preheating pipe inside intake pipe is preheated, to preheat external air, avoid because temperature reduces and influence combustion reaction speed, to improve the stability and efficiency of combustion, and utilize waste gas as heat source, realize air preheating while reducing heat energy loss, improve overall thermal efficiency, mix and spray after preheating outside air and coal powder respectively, can avoid the combustion instability caused by preheating uneven or temperature difference too large.

This invention relates to the field of aero-engine technology, and discloses a concave cavity type hydrogen micro-mixing combustor head and its design method. The invention employs a concave cavity combustor endwall design with negative curvature, and directs the airflow direction at the micro-mixing unit outlet towards the focal point of the arc-shaped structure. This allows the radial heat release pulsations of the concave cavity combustor endwall to cancel each other out, reducing the intensity of heat release pulsations and suppressing combustion instability. Furthermore, under the same projected area and micro-mixing unit blockage ratio, the concave cavity combustor endwall can accommodate more micro-mixing units, thereby increasing the volumetric heat release intensity of the combustor head. Moreover, the invention designs the air and fuel nozzles of the micro-mixing unit as oblique cut holes, enabling air and hydrogen to form local swirling flows within the mixing channel and be ejected, thus improving the mixing uniformity of hydrogen and air and combustion efficiency.

The invention discloses a method for predicting combustion instability based on pressure fluctuation change, and relates to a method for predicting combustion instability. The problem that combustion instability cannot be judged through short-time sampling pressure fluctuation data in the prior art is solved. The method comprises the steps that a pressure pulsation time sequence in a combustion chamber is monitored in real time; a rolling window mode is adopted, and a pressure fluctuation arrangement mode with the delay time being 1 and the embedding dimension being 4 in a window is obtained; the arrangement models are further divided into three classes, namely, the class A (arrangement has no turning points), the class B (arrangement has one turning point) and the class C (arrangement has two turning points); and calculating the occurrence probabilities of the A, B and C classes in the rolling window, and predicting the time sequence change development of the pressure pulsation in the combustion chamber based on the probabilities of the A, B and C classes. The invention belongs to the technical field of aerospace propulsion systems.

The invention discloses a garbage power station drying air volume control system and method, and belongs to the technical field of air volume regulation. The garbage power station drying air volume control system comprises an incinerator which comprises a drying area, a combustion area and a burnout area; the sensor system is used for collecting operation parameters including the garbage weight, the water content, the drying area temperature, the hearth temperature, the smoke components and the steam flow in real time. The controller is in communication connection with the sensor system, and the controller is configured to calculate theoretical dry air volume according to a physical and chemical mechanism model based on data collected by the sensor system; inputting the theoretical dry air volume into a trained artificial intelligence optimization model to obtain an optimized dry air volume control instruction; the actuator is connected with the controller and used for adjusting the air volume fed into the drying area according to the optimized drying air volume control instruction. The problems that in the prior art, due to fluctuation of the water content of garbage, combustion is unstable, efficiency is low, and emission is high are solved.

The invention discloses a dual-fuel hypersonic propulsion and power generation integrated system with a chemical energy storage function and a working method, and relates to the field of aero-engine energy management. The problems that an existing scramjet engine is unstable in aviation kerosene conveying and high-Mach-number combustion, thermal management and the like are solved. The system comprises an aviation kerosene tank, an aviation kerosene pump, an aviation kerosene-liquid metal heat exchanger, an ammonia storage tank and the like, the system combines chemical energy storage core characteristics of liquid ammonia, waste heat generated on the wall face of a combustion chamber is subjected to cascade recovery and efficient utilization, specifically, liquid metal serves as a heat conduction medium, redundant heat on the wall face of the combustion chamber is fully absorbed, and the heat conduction efficiency is improved. Liquid ammonia is heated through high-temperature liquid metal, liquid ammonia is promoted to absorb heat, gasify and crack, the liquid metal is further used for aviation fuel preheating, cascade transmission and efficient utilization of system energy are achieved, and the energy utilization rate of the whole system is greatly increased.

The invention relates to the technical field of aero-engines, and discloses a concave cavity type hydrogen micro-mixing combustion chamber head and a design method.The concave cavity type combustion chamber end wall design with the negative curvature is adopted, and the airflow direction of the outlet end of a micro-mixing unit faces the focus of a cambered surface structure; heat release pulsation of the end wall of the concave cavity type combustion chamber in the radial direction is counteracted, the effects of reducing heat release pulsation intensity and restraining combustion instability are achieved, meanwhile, under the condition of the same projection area and the same micro-mixing unit blocking ratio, more micro-mixing units can be arranged on the end wall of the concave cavity type combustion chamber, and the combustion stability is improved. Therefore, the volume heat release intensity of the combustion chamber head is improved. And the air spraying holes and the fuel spraying holes of the micro-mixing unit are designed to be beveled holes, so that air and hydrogen can form local rotational flow in the mixing channel and are sprayed out, and the mixing uniformity and the combustion efficiency of the hydrogen and the air can be improved.

This application belongs to the field of aero-engine combustor design technology, specifically relating to an aero-engine combustor and its control method. By using radially parallel blunt bodies to achieve the low-speed stable recirculation zone required for combustion organization, it can solve the combustion instability phenomenon that is prone to occur in existing high-temperature combustor technology based on the premixed combustion concept. Combined with a multi-point injection nozzle with zoned fuel control, it can achieve a balance between ignition shutdown performance and overall combustion performance at the design point. At the same time, the zoned fuel control function of the injector can realize the shape of the combustor outlet temperature profile.

A tangential unstable acoustic mode feature recognition method for a rocket engine combustion chamber comprises the steps that a pulsating pressure sensor array with the minimum number of 2 is adopted, two orthogonal projection signals are obtained by solving a linear equation set, and finally slow variable parameters corresponding to a tangential acoustic mode are obtained through a quaternion analysis method. Therefore, the mode slow variable of the tangential unstable acoustic mode of the combustion chamber can be better described, the antinode position and the sound pressure peak value of the standing wave mode can be effectively identified, the amplitude and the sound wave rotation rate characteristic of the traveling wave mode can also be identified, and the method is of great significance in understanding the tangential combustion instability characteristic and achieving effective control over the tangential combustion instability.