6800 results about "Combustion chamber" patented technology

A combustor includes a combustion liner that defines a combustion chamber and an outer sleeve spaced apart from the combustion liner, such that an annulus is defined between the combustion liner and the outer sleeve. The combustor further includes a fuel injection assembly having a boss coupled to at least one of the combustion liner and the outer sleeve. The boss includes an inner flange coupled to the combustion liner, an outer flange, and a body extending between the outer flange and the inner flange. The boss defines a cooling circuit having a post-impingement plenum defined in the inner flange between an inner wall of the inner flange and an impingement plate in cooling proximity to the inner wall; and a plurality of film cooling channels that are defined in the inner flange and fluidly couple the post-impingement plenum to the combustion chamber.

A method is provided for operating a powerplant. During this method, a hydrocarbon fuel is delivered to a turbine engine for combustion within a combustion chamber of the turbine engine during initial startup operation of the turbine engine. Ammonia is at least partially cracked into hydrogen gas and nitrogen gas. A non-hydrocarbon fuel is delivered to the turbine engine for combustion within the combustion chamber of the turbine engine during post-startup operation of the turbine engine. The non-hydrocarbon fuel is or otherwise includes the hydrogen gas or a combination of the hydrogen gas and the nitrogen gas.

The embodiment of the invention provides a prediction method and device for the outlet temperature of an aero-engine combustion chamber, computer equipment and a medium, and relates to the technical field of performance evaluation and prediction.The method comprises the following steps that input parameters related to combustion chamber operation and combustion chamber structure are collected in batches, an optimal parameter set is generated, and the optimal parameter set is stored; working condition vectors are constructed through combustion chamber working conditions; constructing a stable parameter set through the optimized parameter set and the working condition vector, screening all parameters in the stable parameter set, and adjusting weights corresponding to the parameters in the working condition vector through an adaptive weight model; and constructing a physical constraint coupling prediction model, training the physical constraint coupling prediction model based on the physical constraint, generating a trained physical constraint coupling prediction model, and outputting the unevenness of the temperature distribution of the outlet of the combustion chamber through the model. According to the scheme, high-precision prediction of the temperature distribution unevenness of the outlet of the combustion chamber can be realized under the conditions of different pressures, temperatures, equivalence ratios and the like.

The invention provides a pyrolysis recovery method of a plastic packaging bag, and belongs to the technical field of plastic packaging bag recovery, the pyrolysis recovery method of the plastic packaging bag comprises the following steps: removing impurities from the waste plastic packaging bag, cleaning and drying, and controlling the moisture to be below 5%; the packaging bag is crushed into small blocks with the diameter smaller than 20 mm, so that the pyrolysis efficiency is improved; feeding the crushed plastic into a pyrolyzing furnace through a spiral feeder, adding an auxiliary pyrolyzing component, heating to 300-600 DEG C under an oxygen-free or oxygen-deficient condition, and carrying out thermal cracking; oil gas obtained after pyrolysis is condensed through a cooling system and classified, and solid residues are subjected to tempering treatment; flue gas generated after combustion is subjected to high-temperature degradation through a secondary combustion chamber and then subjected to multistage treatment through a quench tower, dust removal, alkali spraying and activated carbon adsorption, and it is ensured that the flue gas reaches the standard and is discharged; the problems that in the existing pyrolysis recycling process of the plastic packaging bags, the treatment efficiency is low, and the environment is still polluted can be solved.

The invention belongs to the field of engines, and particularly relates to a dual-fuel regenerative cooling system and method. The cooling system comprises a combustion chamber, an ammonia supply device and a kerosene supply device; three layers of cooling flow channels are arranged in the wall face of the combustion chamber, the output ends of the three layers of cooling flow channels are arranged in the combustion chamber, and the three layers of cooling flow channels comprise a first cooling channel, a second cooling channel and a third cooling channel which are sequentially arranged from inside to outside. The ammonia supply device is connected with the input ends of the first cooling channel and the second cooling channel; the kerosene supply device is connected with the input ends of the third cooling channel and the second cooling channel; and ammonia or kerosene is introduced into the second cooling channel in a time-sharing manner. Through the three-layer cooling channel design and the fuel switchable function, the effects of fuel cooling, thermal protection, cracking hydrogen production and combustion organization are improved at the same time.

The invention discloses a modeling method and device for a soft measurement model of the flue gas oxygen content of a gas turbine, and the modeling method comprises the following steps: obtaining multi-source operation data of the gas turbine, including a gas turbine combustion chamber pressure pulsation original signal, an operation parameter and an environment parameter; carrying out time-frequency domain feature extraction on the pressure pulsation original signal to obtain a time domain statistical feature and a frequency domain spectrum feature, fusing the time domain statistical feature and the frequency domain spectrum feature with the operation parameters and the environment parameters, and then screening key input variables through variable importance analysis; constructing a cascade hybrid model based on the screened key input variables; and jointly optimizing model parameters of a time sequence feature learning layer, a static feature mapping layer and a dynamic fusion layer in the hybrid model through a gradient descent method until the model converges, and generating a soft measurement model capable of outputting an effective flue gas oxygen content predicted value.

The invention discloses an aero-engine combustion chamber ignition state prediction method and system based on deep learning. The method comprises the steps that a combustion chamber ignition parameter data set is collected; analyzing sample distribution to determine an augmentation amount, generating a new sample based on KNN interpolation, injecting adaptive Gaussian noise, and referring to physical relevance between a fuel-air ratio and a temperature-pressure ratio of a real sample during augmentation of a special working condition; an AttResVGG deep neural network is constructed, gradient disappearance is prevented by adopting residual connection, a multi-head self-attention mechanism is embedded to capture a long-range dependency relationship among parameters, and multi-scale features are integrated through a global feature fusion module; double classifier training is designed, a main classifier adopts category weighted cross entropy loss, an auxiliary classifier adopts label smooth loss, and model parameters are jointly optimized; and inputting working condition parameters for real-time prediction. According to the invention, parameter dependence of a traditional empirical model is broken through, and adaptive prediction of complex working conditions is realized; the calculation time consumption is reduced, and the real-time decision demand is met; and the device adapts to various combustion chamber structures, and re-modeling is not needed.

The invention belongs to the technical field of aero-engine high-temperature part test, and particularly relates to a thermal mechanical composite fatigue test device in a turbine blade rotation environment, which comprises a high-temperature gas system, a stator system, a rotor system, a support system, a test system, an auxiliary system and a turbine rotor blade test piece, the high-temperature fuel gas system is used for providing a fuel gas environment for a turbine rotor blade test piece and controlling the high-low temperature circulation state of fuel gas, a combustion chamber is arranged at the front end of the high-temperature fuel gas system and provided with a double-oil-way nozzle, a fuel gas flowing system is arranged at the rear end of the high-temperature fuel gas system, and a blade grid structure is designed for the fuel gas flowing system according to the geometrical shape of a turbine rotor blade. And a spray cooling section is arranged at the rear part of the test section. The device is composed of six core systems including a high-temperature fuel gas system, a stator system, a rotor system, a supporting system, a testing system and an auxiliary system, all the systems work cooperatively, and integrated simulation of the high-temperature fuel gas environment, rotating centrifugal loads and heat-force synchronous circulation is achieved.

The invention discloses a combustion chamber and turbine guider integrated composite flow channel outlet flow field uniformity evaluation method, and belongs to the technical field of gas turbine pneumatic design. The method comprises the steps that a geometric model of a combustion chamber and turbine guider integrated composite flow channel is built, a combustion chamber function section and a guider pneumatic section are fused through integral pneumatic modeling to form a continuous flow channel, a front section adopts a diffusion structure to form a low-speed combustion area, and a rear section adopts a gradually-shrinking channel to achieve gas accelerated expansion; performing three-dimensional cold-state flow field numerical simulation by adopting a structured grid division and delay separation vortex simulation technology; flow parameters including total pressure, Mach number, airflow angle and vorticity are extracted from the cross section of a flow channel outlet, conversion from a Cartesian coordinate system to a polar coordinate system is carried out, and a uniformly distributed aerodynamic parameter field is reconstructed by using an interpolation algorithm; the directional coupling degree is calculated based on the spatial correlation of the pressure gradient vector and the vorticity vector, and the vortex-pressure coupling entropy production index representing the overall aerodynamic loss of the flow channel is established in combination with the pressure pulsation intensity and the vorticity concentration ratio. According to the method, a three-dimensional evaluation system is constructed by integrating circumferential and radial non-uniformity and entropy production parameters, and accurate quantitative evaluation of flow characteristics and uniformity of the combustion chamber and turbine integrated structure is realized.

The invention provides a coke oven automatic heating control method and system, and belongs to the technical field of coke oven control, the method is applied to a coke oven temperature control system, and the method comprises the following steps: based on each temperature detection device, obtaining the temperature of a carbonization chamber corresponding to the temperature detection device, and obtaining the actual temperature of each carbonization chamber; determining a standard temperature range of each carbonization chamber based on the heating duration of the coke cake in each carbonization chamber; determining whether each carbonization chamber needs to execute temperature control or not based on the actual temperature of each carbonization chamber and the standard temperature range of each carbonization chamber; in response to existence of a target carbonization chamber in the carbonization chambers, determining a target combustion chamber based on the temperature deviation degree of the target carbonization chamber; the target carbonization chamber is the carbonization chamber needing temperature control in the carbonization chambers; and controlling a gas flow valve and an air flow valve in the target combustion chamber based on the temperature deviation degree of the target carbonization chamber. According to the invention, accurate adaptation and dynamic optimization of heating control of the coke oven to complex working conditions can be realized.

The invention provides a regenerative cooling channel structure and an engine, and relates to the technical field of engine thermal protection, the regenerative cooling channel structure comprises a first channel and a second channel which are arranged between the outer wall face and the inner wall face of a combustion chamber at intervals in the radial direction, and an inlet and an outlet of the first channel are located at the inlet end and the outlet end of the combustion chamber correspondingly; an inlet and an outlet of the second channel are located at the outlet end and the inlet end of the combustion chamber respectively. An outlet of the first channel communicates with an inlet of the second channel, and a coolant flows into the first channel through the inlet of the first channel, then flows into the second channel through an outlet of the first channel and the inlet of the second channel in sequence and then flows into the combustion chamber through an outlet of the second channel. The flowing direction of the coolant in the first channel is consistent with the flowing direction of gas in the combustion chamber to form downstream cooling, the flowing direction of the coolant in the second channel is opposite to the flowing direction of the gas in the combustion chamber to form countercurrent cooling, the flowing speed and flow distribution of the coolant are improved, the heat transfer deterioration phenomenon is restrained, and the cooling effect is effectively improved.

The invention discloses a DCS (Distributed Control System)-based ignition and temperature rise mode of a copper anode slime roasting rotary kiln, which specifically comprises the following steps of: setting initial control conditions, drawing a temperature rise curve according to a target temperature, a temperature rise period and a temperature rise gradient, and then starting ignition preparation. Before natural gas is introduced into the combustion chamber for combustion, rotary kiln operation and combustion-supporting air purging are carried out, after purging is carried out for a period of time, combustion-supporting air and natural gas are introduced for ignition at the same time, and meanwhile the ignition condition is judged through a monitor. And if ignition fails, under the condition of no abnormity, purging can be repeated, and natural gas is introduced for re-ignition. According to the method, the natural gas flow and the combustion-supporting air volume are automatically controlled by the DCS according to the drawn temperature rise curve. The system has the beneficial effects that multiple ignition conditions can be controlled at the same time, remote automatic ignition is achieved, the ignition condition is fed back in time, the natural gas flow is flexibly controlled, the combustion temperature is controlled, the ignition effect of the rotary kiln is guaranteed, and meanwhile production operation safety of the rotary kiln is guaranteed.

The present application provides a dynamics analysis method for an ammonia combustion refrigeration system in large park cooling. The method comprises: on the basis of a geometric structure of an ammonia combustion chamber and a fuel supply amount, calculating the heat generated by ammonia combustion and analyzing the heat transfer mode between the combustion chamber and a desorption tower, the heat transfer mode comprising direct contact type heat transfer and partition type heat transfer, and simulating the heat transfer process to obtain and draw the heat flux distribution of the tower wall surface; on the basis of the flow state and a relationship curve between the pressure drop and the flow velocity, analyzing the desorption process of a refrigerant in a solution, and on the basis of the concentration of the solution, a boiling point of the refrigerant, and the vapor pressure, calculating local desorption rates at different positions in the desorption tower and the refrigerant vapor generation amount; and on the basis of the heat flux distribution, calculating the temperature distribution of the solution, and analyzing the heat transfer and mass transfer processes in the desorption tower to obtain a local heat transfer coefficient and the mass transfer efficiency distribution of the surface of a filler.

The utility model discloses a combustion control assembly of a wall-hanging stove, which relates to the technical field of combustion control of wall-hanging stoves and comprises a combustion chamber, a mixer, a gas valve and a gas calorific value instrument, the mixer is provided with a first input end, a second input end and an output end, the first input end is connected with a combustion-supporting gas pipeline, and the second input end is connected with a gas pipeline. The output end is connected with the combustion chamber; the gas valve is arranged on the gas pipeline; the gas calorific value instrument is connected with the second input end or the output end, and obtains gas calorific value components before the gas and the combustion-supporting gas are mixed or calorific value components of mixed gas formed after the gas and the combustion-supporting gas are mixed in real time; therefore, the calorific value components are obtained through real-time measurement by arranging the gas calorific value instrument, then rapid and accurate self-adaptive adjustment of the air-fuel ratio is achieved, the gas flow / gas volume and / or the combustion-supporting gas flow / combustion-supporting gas volume are adjusted / determined in real time, the influence of gas component difference on the heat efficiency can be well adapted, and it is ensured that the wall-hanging stove is in the optimal combustion condition in real time.

An ammonia-rich combustion coupled dual-mode prechamber ammonia-fueled engine control system is provided, including an ammonia-fueled engine and an electronic control unit. The ammonia-fueled engine includes a combustion chamber, a dual-mode jet ignition device, and an ammonia injector. The dual-mode jet ignition device includes a prechamber, an air injector, and a fuel injector. When the engine operates, ammonia fuel is firstly injected into the combustion chamber by the ammonia injector to form a rich ammonia-air mixture with air in the combustion chamber. During a compression stroke of the engine, the rich ammonia-air mixture in the combustion chamber is entered into the prechamber through a jet hole. The air injector performs scavenging in the prechamber until a equivalence ratio of prechamber gas mixture is less than 1.0, and then the fuel injector injects fuel into the prechamber forming target mixture. Finally, the target mixture is ignited by the spark plug.

The invention provides a CNN-PINN-based gas turbine combustion chamber performance prediction method, belongs to the technical field of combustion chamber combustion, and aims to solve the problems of high resource consumption and high grid dependence of the conventional CFD calculation at present, and the method comprises the steps: S1, collecting historical operation data of a combustion chamber, generating simulation data through numerical simulation, and carrying out the calculation of the simulation data; performing comparative analysis on the simulation data and the collected experimental operation data to prepare a data set; s2, preprocessing the data set; s3, establishing a CNN-PINN neural network prediction model according to the data characteristics and the target; s4, establishing a loss function containing a data error term and a physical information error term; s5, training and evaluating the established model by using the preprocessed data; and S6, performing performance prediction on target data by using the trained model, and performing reverse normalization on a prediction result to obtain prediction data corresponding to multiple targets.

The invention belongs to the field of aero-engine anti-icing system design, and discloses an aero-engine anti-icing system and a design method. The system comprises an anti-icing component, a heat supply structure, a control assembly and a monitoring assembly, wherein the anti-icing component selects an air inlet support plate and a rectification cover hood; the heat supply structure introduces air from two air flows of the combustion chamber and conveys hot air through a pipeline and an air collection cavity; the control assembly adopts intermittent control, and system management and control are achieved through a pressure reducing valve and a digital electronic controller; the monitoring assembly comprises a pressure sensor and a thermocouple. The design method sequentially comprises the steps of anti-icing component and type determination, anti-icing structure design, control scheme design, simulation analysis, test verification and the like. A complete forward design path is provided, the anti-icing efficiency is improved, the structure is simplified, safe and stable operation of the engine is guaranteed, and the method can be widely applied to design and improvement of an anti-icing system of the aero-engine.

The invention discloses a liquid engine ignition device. The liquid engine ignition device comprises a storage tank used for storing an ignition agent required by preset ignition times and an ignition tube used for storing the ignition agent required by single ignition; the ignition tube is communicated with the storage tank through a communicating tube; a one-way valve for preventing an ignition agent in the ignition pipe from flowing back into the storage tank is arranged on the communicating pipe; the ignition tube is configured to be capable of extruding an ignition agent which is stored in the ignition tube and is used for single ignition into an engine combustion chamber under the extrusion effect; the storage tank is configured to be capable of automatically filling the ignition tube with the discharged ignition agent with the ignition agent stored in the storage tank under the extrusion effect. According to the method for sharing the storage tank and the ignition tube, the reliability of the ignition tube and the multi-time ignition characteristic of the storage tank are combined, automatic quantitative ignition agent filling is achieved, and an efficient ignition scheme is provided for multi-time ignition of a rocket engine.

The invention discloses a virtual sensing method for thermal characteristics of an internal combustion engine. The method comprises the following steps: S1, acquiring temperature distribution data; s2, time sequence temperature data mapping; s3, acquiring fusion temperature data; s4, obtaining thermal characteristics; and S5, abnormal judgment of a combustion chamber, an exhaust pipeline and a cooling system. According to the method, the comprehensiveness and the accuracy of thermal state analysis are remarkably improved by constructing a global sensing system of a three-dimensional space temperature field of the internal combustion engine and combining a multi-source sensor collaborative acquisition and deep learning feature fusion mechanism. Through closed-loop coupling of time-space sequence temperature data and a thermodynamic mechanism model, quantitative correlation between thermal characteristics and combustion efficiency, heat energy loss and cooling efficiency core performance parameters is established. According to the LSTM-CNN-MLP collaborative framework, the spatio-temporal evolution law of a temperature field is extracted in a self-adaptive mode, and the robustness of thermodynamic state perception is remarkably enhanced.

The invention discloses a high-pressure combustion combined heat and power generation energy storage system and method for hydrogen and oxygen production through electrolysis, and relates to the field of hydrogen energy storage. After the electrolytic cell produces high-pressure hydrogen and oxygen, the high-pressure hydrogen and oxygen are stored in the hydrogen / oxygen storage tank, the system can operate in a hydrogen / oxygen mode, and in the oxygen mode operation, the hydrogen and oxygen steam mixed gas from the oxygen storage tank and the hydrogen / oxygen evaporation compressor are combusted in the high-pressure combustion chamber to generate superheated steam, and then the superheated steam enters the expansion turbine to do work; due to excessive oxygen, dead steam after acting is separated into two working media through a gas-liquid separator, that is, gas enters a cooler to be cooled and then returns to a combustion chamber through a hydrogen / oxygen evaporation compressor, drainage water generated after liquid enters a heat supply heat exchanger is pressurized through a water pump and then enters a high-temperature combustion chamber, and therefore clean utilization of hydrogen energy and cyclic regeneration of the working media are achieved. The system can realize high power generation efficiency and excellent environmental protection performance, and is suitable for regions requiring stable consumption of fluctuating renewable energy sources, power and heat supply and the like.

The utility model provides a high-enthalpy pure air heating device which is used for solving the technical problem that according to an existing heating mode, the attributes of incoming flow air and real air are different. The heating device comprises a gas inlet unit, a heating unit and a gas collecting unit, the air inlet unit is connected with the heating unit; the heating unit comprises a shell, and a heat transfer chamber and a combustion chamber which are arranged in the shell; the heat transfer chamber is coaxially installed in the shell, the radial section of the heat transfer chamber is of a circular ring structure, and the combustion chamber is axially installed in the center of the circular ring structure. A plurality of radial channels and axial channels which are mutually independent are arranged in the heat transfer chamber; the two ends of each radial channel communicate with the combustion chamber and the residual gas outlet correspondingly, and the radial channels are used for conveying high-temperature gas. The two ends of each axial channel communicate with the air inlet and the air outlet correspondingly, and the axial channels are used for conveying incoming flow air. And the gas collection unit is used for collecting the high-enthalpy air and transmitting the high-enthalpy air to external test equipment. The device is high in heating speed, and pure high-enthalpy air can be obtained.

The invention relates to a two-stage combustor and an axial staged combustion chamber. The secondary combustor comprises a fuel main pipe, a fuel branch pipe, an inner cylinder and an outer cylinder; an inner airflow channel is formed between the inner cylinder and the fuel main pipe; an inner jet hole is formed in one end, close to the outlet of the inner cylinder, of the side wall of the fuel main pipe; an outer airflow channel is formed between the outer cylinder and the inner cylinder, and the outer cylinder comprises a main cylinder section and a conical cylinder section; the conical barrel section sleeves the inlet end of the inner barrel, and at least part of the conical barrel section extends into the main barrel section; the inner diameter of the conical barrel section is gradually reduced from the first end to the second end; the axial direction of the fuel branch pipe is arranged along the radial direction of the fuel main pipe, one end of the fuel branch pipe is connected to the side wall of the fuel main pipe, and the other end penetrates through the side wall of the inner cylinder and extends into the conical cylinder section; an outer jet hole is formed in the end, stretching into the conical barrel section, of the side wall of the fuel branch pipe. The secondary combustor can effectively isolate direct coupling of secondary fuel and primary flame, and avoids unstable combustion and over-high temperature caused by combustion superposition in a coupling area.

A gas turbine engine, comprising a compressor section, combustion section, and turbine section in serial flow arrangement, with the combustion section comprising: a combustor liner at least partially defining a combustion chamber; a wall coupled to the combustor liner; a first fuel supply to supply a first fuel; a gaseous fuel supply to supply a gaseous hydrogen fuel; and a fuel nozzle assembly coupled to the wall and fluidly coupled to the first fuel supply and the gaseous hydrogen fuel supply, the fuel nozzle assembly comprising: a main mixer; and a fuel nozzle comprising an outer wall defining a pilot channel and an outer wall fuel orifice to emit at least one of the first fuel or the gaseous fuel radially outward into the main mixer; and a secondary mixer disposed in the pilot channel.

The invention discloses a combustion chamber nonlinear stability prediction method based on multi-input thermo-acoustic disturbance modeling. The method is used for evaluating thermo-acoustic stability of combustion chambers of aero-engines, gas turbines and the like. According to the method, geometric, operation and analysis parameters are input, and cooling flow distribution is calculated; solving an effective equivalence ratio, a heat release rate and a temperature field, and calculating an acoustic modal frequency; constructing an equivalence ratio and inlet flow double-disturbance MISO transfer function, and generating an FTF curve; and judging oscillation through a limit cycle detection algorithm, calling a Tanh / PowerLaw model to calculate a saturated heat release rate, and finally visually outputting a result. Multi-factor coupling accurate modeling is achieved, intervention can be conducted in the initial stage of design, calculation only needs several minutes, the prediction precision and efficiency are improved, the research and development cost is reduced, and the safety of the combustion chamber is guaranteed.

The invention discloses a numerical simulation method for aero-engine combustion chamber spray combustion, and belongs to the technical field of aero-engine combustion chamber spray combustion simulation. According to the numerical simulation method, external circulation is carried out based on a self-adaptive matching iteration solution control mechanism of liquid drops and flow field motion scales; the method comprises the following steps: starting from the definition of a mixed fraction and component transportation, deducing a mixed fraction source item and a component transportation equation source item under different definitions, establishing a coupling relationship between fuel evaporation and combustion, and having a flow-spray-combustion high-fidelity coupling simulation capability; an RCCE method is introduced to establish a flame surface database, a large number of components in a chemical reaction mechanism are mapped to a limited number of constraint variables for dimensionality reduction solution, a constraint equilibrium state is obtained according to a maximum entropy principle, and finally the concentration of each component is reconstructed by using constraint potential energy. The generation efficiency of the complex fuel chemical reaction database is improved while the key chemical thermodynamic coupling precision is ensured.

The invention discloses a steam boiler with a steam waste heat recovery function, which comprises a steam boiler body, a combustion chamber, a box body, a combustor, a steam pipe, a smoke exhaust pipe, a drainage mechanism, a connecting pipe, a water inlet pipe and a heat exchanger, the combustion chamber is arranged in the steam boiler body, and the combustor is arranged on one side of the combustion chamber; and a steam pipe is arranged at the top of the steam boiler body. According to the steam boiler with the steam waste heat recovery function, in the aspect of waste heat recovery, the heat exchanger of a composite structure of the heat conduction pipe and the spiral pipe is adopted, sensible heat and latent heat of high-temperature smoke in the smoke exhaust pipe are efficiently captured, and heat is rapidly transferred to a water inlet system through low-boiling-point heat conduction liquid; the waste heat of the flue gas which is directly discharged originally is fully recycled, and the energy loss is greatly reduced.

The invention discloses a supercharged SOFC / GT combined cycle system and a starting method, and relates to an SOFC / GT combined cycle system and a starting method. The invention aims to solve the problem that the requirements of short starting time and high energy utilization rate cannot be met in the prior art. The system comprises a gas compressor, the gas compressor is coaxially connected with a turbine and a permanent magnet synchronous motor, an outlet of the gas compressor is connected with an inlet of a first flow divider, one outlet of the first flow divider is connected with a first battery assembly, and the other outlet of the first flow divider is connected with an inlet of a second flow divider; one outlet of the second shunt is connected with a heat exchanger assembly, the other outlet of the second shunt is connected with a combustion chamber, an outlet of the combustion chamber is connected with a turbine, an outlet of the turbine is connected with a heat exchange assembly, the heat exchange assembly is connected with the combustion chamber, the permanent magnet synchronous motor is connected with a power grid bus, and the power grid bus is connected with a second battery assembly. The first battery assembly is connected with the power grid bus. The invention belongs to the technical field of energy power equipment.

The invention discloses an amino mixed fuel explosion characteristic visualization and explosion suppression coordinated regulation and control system and method, and the system comprises an explosion suppression device which is disposed in a combustion chamber and is in communication connection with a holographic monitoring device and an explosion overpressure real-time prediction model. A graded explosion suppression scheme is set according to the safety early warning grade, so that active intervention of explosion suppression intensity and mode matched with combustion or explosion development stages with different intensities in the combustion cavity is implemented. Therefore, visualization of the mixed gas combustion and explosion dynamic process under the multi-parameter coupling condition can be achieved, and the comprehensiveness and reliability of combustion and explosion research are remarkably improved; through real-time monitoring and intelligent prediction of the explosion process, the explosion process in the device can be rapidly started, the explosion suppression response can be optimized, the explosion development can be suppressed, the integrity and operation safety of an experiment system can be guaranteed, and the intrinsic safety and the system protection capability of the experiment process can be effectively enhanced.

The invention belongs to the technical field of engine air pipe network valve adjustment, and provides a combustion chamber air pipe network valve opening prediction model construction method and system, and the method comprises the steps: generating a test working condition set comprising a plurality of valve opening combinations for an established air pipe network system model; the test working condition set serves as input, and a mapping data set of gas parameters and valve opening degrees of an inlet and an outlet of each network management node is obtained through simulation of the air pipe network system model; and training the mapping data set by adopting a Kriging algorithm, and establishing a prediction model taking gas parameters of an inlet and an outlet of a network management node as input and valve opening as output under a test working condition. According to the prediction model constructed through the method, all valve opening strategies can be rapidly predicted for inputting the target flow and pressure, and the target state can be rapidly achieved through a small number of personnel control actions in the experiment process.

The invention relates to the technical field of steel sintering processes, in particular to a biomass gasification coupling system for a steel sintering process, which comprises a biomass gasification system, a circular cooler waste heat utilization system and a waste heat power generation system, the biomass gasification system comprises a biomass drying system, a raw material conveying belt system, a biomass gasification furnace, a biomass gas heat insulation combustion chamber, a sintered coke powder preparation system and a biomass gas purification system, and the biomass drying system is used for drying biomass raw materials; and the dried biomass raw materials are conveyed to the biomass gasification furnace through the raw material conveying belt system. According to the coupling system for biomass gasification for the steel sintering process and the control method, biomass serves as zero-carbon energy, and biomass charcoal obtained after biomass gasification can replace part of solid fuel to achieve the carbon reduction effect. Meanwhile, the biomass gasified gas can replace a part of coal gas, and the carbon reduction effect can also be achieved.