383 results about "Staged combustion" patented technology

The invention discloses a digital twinning method and system for staged combustion of a coal-biomass fluidized bed. The method comprises the following steps: establishing a comprehensive database comprising three-dimensional simulation data and operation data of a coal-biomass fluidized bed boiler; modeling and coupling the gas phase and the particle phase by using a neural network to obtain a coal-biomass combustion model which is used for predicting a temperature field, a pressure field and a velocity field of the coal-biomass fluidized bed boiler; and finally, integrating the coal-biomass combustion model with a boiler PLC system of the coal-biomass fluidized bed to realize data transmission, so as to obtain a coal-biomass combustion digital twinborn model and realize real-time control and dynamic optimization. On-line real-time prediction of the boiler is achieved, and long-term updating of the model and continuous improvement of the intelligent level are achieved through continuous accumulation and dynamic training of operation data.

The invention discloses a flue gas compensation type pulverized coal wide-load stable combustion system based on staged combustion and intelligent regulation and control and a control method, and belongs to the technical field of coal-fired power generation. The system is composed of a combustor, an intelligent control module and a flue gas backflow module, the combustor adopts a double-ring fuel channel design, an inner ring injects high-concentration pulverized coal and is provided with an adjustable swirler, and pulverized coal-flue gas mixed airflow is introduced into an outer ring; the intelligent control module predicts a load through an LSTM neural network, and realizes accurate matching of air and coal in combination with PID adjustment; and the flue gas backflow module adopts an oxygen concentration adjustable technology to maintain the combustion intensity. Under the working condition of 30%-40% low load, the system achieves the stable combustion effect that the flame center temperature is stabilized at 920 + / -20 DEG C by means of optimizing the proportion of inner ring pulverized coal to 75%-85%, increasing the primary air temperature to 145-170 DEG C, compressing the proportion of secondary air to 20%-30%, strengthening a swirling flow field to 45 degrees and the like in cooperation with flue gas backflow with the oxygen concentration of 23%-25%, and has the advantages of efficient combustion and low emission.

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.

The invention provides a low-pollution combustion organization method and system for a combustion chamber of a natural gas turbine. Relates to the field of combustion chamber design, and solves the problem that reliable ignition cross flame and efficient combustion cannot be realized in a small and short space under a low working condition. The method comprises a low-resistance gas distribution step, a rapid premixing step, a wide boundary concentration difference staged combustion step, a fuel escape prevention staged combustion step, a near wall surface streamline control step, a characteristic area pollutant prediction and inhibition step, an outlet temperature distribution regulation and control step and a head scaling / increasing and decreasing stage adaptation step, and determining a corresponding combustion chamber head size and a combustion chamber classification number. On the premise that the rotational flow strength is guaranteed, the flow resistance loss of the head is remarkably reduced, tempering is prevented, and the efficiency of the combustion chamber is improved.

The invention discloses a liquid fuel vaporizing and mixing multi-stage combustion system which comprises an air bellow and a fuel conveying pipe, a flow guide combined barrel is arranged in a lining barrel of the air bellow and is formed by combining an air combing flow guide barrel and a conical flow guide base up and down, and the conical flow guide base is formed by forming an included angle between an air guide annular inclined plate and a transverse bottom plate. A mixing chamber is formed between the flow guide combined cylinder and the lining cylinder, and the oil outlet end of the fuel conveying pipe is arranged in the mixing chamber; a plurality of air grooves are formed in the air combing guide cylinder, and a plurality of air guide grooves are formed in an air guide annular inclined plate of the conical guide seat; the top of the lining cylinder is connected with a combustion cylinder A in a sealed mode, the combustion cylinder A is sleeved with a porous ceramic silencing cylinder, fire distribution fins are installed on the top of the porous ceramic silencing cylinder, and a combustion cavity C is formed between the cylinder wall of the combustion cylinder A and the cylinder wall of the porous ceramic silencing cylinder. According to the invention, liquid fuel can be fully mixed, vaporized and gradually combusted, the fuel is fully combusted, and flame and heat are gathered and are subjected to fire distribution operation through the fire distribution fins.

A main injector can include multiple sub-element mixers. A first sub-element mixer includes a first main air nozzle circumscribing a first main fuel nozzle. A second sub-element mixer includes a second main air nozzle circumscribing a second main fuel nozzle. An annular combustor can include a circumferential array of main injectors disposed proximate a pilot injector. Each main injector of the array of main injectors can be oriented with first sub-element mixers proximate to the pilot injector and second sub-element mixers spaced axially downstream relative to first sub-element mixers in a staged configuration.

The invention discloses an aero-engine acceleration control method with an interstage combustion function. In the acceleration process, the fuel flow of the main combustion chamber and the fuel flow of the interstage combustion chamber are generated through the main control loop and the additional control loop correspondingly, and then the finally-output fuel flow of the main combustion chamber and the finally-output fuel flow of the interstage combustion chamber are obtained in a low selection mode. Adjusting each variable geometry adjusting mechanism according to an acceleration adjusting plan generated by the additional control loop; the additional control loop uses the following oil supply continuing control strategy that in the acceleration process, the main combustion chamber supplies oil to accelerate firstly, after the rotating speed of a low-pressure rotor of the engine reaches a preset threshold value, the interstage combustion chamber supplies oil to ignite, and meanwhile the variable geometry adjusting mechanism is adjusted according to a pre-optimized adjusting plan. The invention further discloses an aero-engine acceleration control device with the interstage combustion function. According to the technical scheme, safe and quick response of the double-combustion-chamber acceleration process can be achieved.

The present invention discloses a coaxial staged burner for a low-pollution combustion chamber of a gas-liquid dual-fuel gas turbine, which relates to the technical field of gas turbine combustion chambers and solves the problem that existing coaxial staged burners are difficult to achieve stable combustion using a single liquid or gas fuel under any load working conditions. The coaxial staged burner comprises: a mounting flange, a main fuel sleeve and a swirler; a fuel supply interface is provided on the mounting flange; four-stage fuel sleeves are coaxially nested in the main fuel sleeve; the swirler consists of a central duty class, a first-stage premixing stage, a second-stage premixing stage, a first-stage hub and a second-stage hub; when liquid fuel works alone, the fuel enters the swirl channel through the duty class liquid fuel nozzle and the second-stage blade liquid fuel hole to achieve premixing and evaporation processes; when gas fuel works alone, the fuel enters the swirl channel through the first-stage blade fuel hole and the second-stage blade gas fuel hole to be mixed.

The invention discloses an ammonia burner based on plasma catalytic ammonia cracking and zoning regulation and control, and relates to the field of aero-engine combustion chamber structures. The head is combined with a staged combustion technology and a plasma and ammonia catalytic cracking concept, and is one of effective methods for keeping the combustion chamber to work stably, reliably and effectively with low emission. Comprising a flame tube casing serving as a burner body, a first-stage swirler, a second-stage swirler and a third-stage swirler are arranged on the front portion of the flame tube casing, an ammonia gas supply nozzle is arranged in the first-stage swirler, a metal cracker is arranged on the periphery of the ammonia gas supply nozzle, and therefore a plasma discharge area is formed between the ammonia gas supply nozzle and the metal cracker; a plurality of main combustion holes and a plurality of mixing holes are formed in the middle of the side wall of the flame tube case. The stability, ignition performance and temperature uniformity of the ammonia combustor are improved, and the ammonia combustor has the advantages of being high in ignition and flameout capacity, low in emission, reliable in structure and the like and is suitable for efficient clean combustion systems in the fields of aviation, energy and the like.

The invention discloses a combined air inlet two-stage combustion six-stroke engine, and relates to the field of power energy. In order to overcome the defects that in the prior art, a six-stroke engine is insufficient in gas inlet in the secondary combustion stage, poor in oil-gas mixing quality and low in combustion efficiency, according to the technical scheme, the six-stroke engine comprises a combustion chamber assembly, a fuel injector, a transmission mechanism and a gas distribution mechanism; the gas distribution mechanism comprises a gas inlet pipeline, an exhaust pipeline, a gas storage cavity, a gas inlet pipeline valve, a scavenging duct and a scavenging duct one-way valve, the working cycle of the engine comprises two times of gas inlet and two times of oil injection combustion acting, and the gas storage cavity releases gas to supplement fresh air in the combustion chamber in the second time of gas inlet. The combustion chamber assembly comprises a cylinder, a piston and a cylinder cover, the piston reciprocates in the cylinder, and the cylinder and the cylinder cover are closed to form a combustion chamber. The invention is suitable for improving the heat efficiency and output performance of the engine, especially for an internal combustion engine power system requiring multiple combustion work.

An alternative fuel vertical pre-combustion furnace comprises a vertical combustion chamber furnace body, a multi-stage stepped furnace hearth arranged on the side wall of the pre-combustion furnace body and a pneumatic pulse injection device arranged on the furnace hearth, and castable is arranged on the inner wall of the whole furnace body. Light flammable substances are completely incinerated under the driving of high-speed airflow, heavier flame-retardant substances fall into the next step to be continuously incinerated, the burn-off rate of the alternative fuel is greatly improved after the alternative fuel stays, is scattered and is pre-combusted, and completely-combusted material residues are dispersed by strong injection of compressed air of an air cannon system; therefore, the influence on the cement kiln caused by sedimentation of the material slag agglomerated in the decomposing furnace is solved. And materials on the uppermost combustion platform sequentially slide to the second-stage combustion step platform and then slide to the next-stage combustion platform layer by layer, and the process is repeated. And waste gas and ash after incineration are discharged from the bottom of the pre-combustion furnace and enter a kiln tail decomposing furnace system, when the material slag is harmful to the kiln system, the material slag can be discharged, and high-temperature airflow enters the decomposing furnace.

The invention discloses a low-nitrogen gas burner suitable for various working conditions and a using method of the low-nitrogen gas burner. The low-nitrogen gas burner comprises an assembly cylinder, an outer-layer fire pan, a central fire pan, an inner-layer gas gun, an outer-layer gas gun and an oxygen gun. The height of the center fire pan is adjusted through the lifting assembly, and switching of three modes of air combustion supporting, oxygen-enriched combustion supporting and pure oxygen combustion supporting is achieved. The air adjusting assembly controls the combustion-supporting air flow; the flow comprehensive adjusting assembly adjusts fuel gas supply and oxygen supply in a linkage mode. The combustor adopts a staged combustion design, the inner-layer gas gun forms first-stage flame at a fire pan gap, the outer-layer gas gun and a combustion-supporting medium ejected from the central fire pan form second-stage combustion, and the temperature of the flame is reduced by ejecting hearth smoke. Cooperative control over all the executing mechanisms is achieved through the driving motor and the speed setting assembly, the beneficial effects that combustion modes are automatically switched, the flame temperature is accurately regulated and controlled, and emission of oxynitride is low are achieved, and the clean combustion requirements of different industrial furnaces can be met.

The invention discloses a multi-angle micro-pipe staged combustion rotational flow gas burner, and relates to the technical field of industrial burners and low-nitrogen combustion. According to the low-nitrogen combustor, the problem that the combustion stability and the nitrogen oxide emission control level are difficult to optimize at the same time due to the fact that an existing low-nitrogen combustor cannot achieve fuel uniform distribution on the microscale is solved. The device comprises an on-duty flame system, a main flame system, an air supply channel and a flue gas recirculation structure, the on-duty flame system realizes multi-angle uniform injection of fuel through a multi-angle fuel distribution device to form stable central on-duty flame; the main flame system realizes fuel grading through an inner and outer ring mixing pipe; the flue gas recirculation structure introduces backflow flue gas into the combustion area through the flaring of the mixing pipe and the entrainment opening of the arc-shaped air sleeve, the backflow flue gas is mixed with air or fuel gas, and the combustion temperature and the oxygen concentration are effectively reduced. Through the synergistic effect of staged combustion and flue gas recirculation, the effects of stable combustion, uniform flame and low NOx emission are achieved.

The invention discloses a control method of a combustion system and the combustion system, and belongs to the technical field of combustion control. The control method of the combustion system comprises the steps that fuel gas is controlled to be input into the first-stage combustion module, so that the fuel gas and air in the first-stage combustion module are subjected to mixed combustion, and gas which is not fully combusted enters the second-stage combustion module through flow guide fins; and gas is controlled to be input into the second-stage combustion module, so that the gas is mixed with gas which is not fully combusted in the second-stage combustion module and air in the second-stage combustion module for combustion. According to the control method of the combustion system, the emission amount of harmful gas is reduced, and the combustion heat efficiency of the system is improved.

The invention relates to the technical field of boiler combustion control, in particular to a through-flow boiler ultra-low nitrogen combustion control system based on multistage flue gas recirculation. Comprising a flue gas grading circulation unit; the low-nitrogen combustion regulation and control unit is used for realizing staged mixed combustion of fuel and circulating flue gas, and a staged combustion structure is matched with an air-fuel ratio dynamic regulation technology; the working condition parameter sensing unit is used for acquiring boiler combustion and flue gas state parameters in real time, integrating a multi-source sensor module and constructing a multi-dimensional operation parameter set; and the intelligent cooperative control unit is used for coordinating dynamic control of the ultra-low nitrogen combustion process. High-temperature and low-temperature independent flue gas circulation branches are arranged through the flue gas staged circulation unit, and a staged combustion structure of a main combustion section and a re-combustion section of the low-nitrogen combustion regulation and control unit is combined, so that the problem of non-uniform distribution of a hearth temperature field caused by compact combustion space and dramatic change of a flow field of the through-flow boiler can be solved; therefore, the generation of thermal nitrogen oxides is inhibited.

The invention discloses a plasma ignition and combustion-supporting cooperated cavity stable combustion ammonia burner which comprises a three-stage plasma ignition and combustion-supporting device and a three-stage fuel and air supply system, and the three-stage plasma ignition and combustion-supporting device comprises a first-stage plasma ignition and combustion-supporting device, a second-stage plasma ignition and combustion-supporting device and a third-stage fuel and air supply system. The second-stage plasma ignition and combustion-supporting device, the third-stage plasma ignition and combustion-supporting device and the three-stage fuel and air supply system are respectively a first-stage fuel and air supply system, a second-stage fuel and air supply system and a third-stage fuel and air supply system. The problems of low flame propagation speed, high ignition energy and the like existing in ammonia fuel combustion at present are solved, stable combustion of pure ammonia can be realized under the condition that hydrogen or other fossil fuels are not doped into ammonia gas by adopting a multi-stage plasma ignition and combustion-supporting device, assisting ammonia combustion and combining a bluff body combustion stabilizer, and a three-stage combustion stabilizing technology is adopted, so that stable combustion of pure ammonia is realized. And the stable combustion range of ammonia gas can be greatly expanded.

The invention discloses a biomass gas staged combustion system and a control method, the system comprises a staged combustor, a gas induced draft fan and an air blower, the gas induced draft fan is connected with the staged combustor through a gas main pipeline, a first-stage gas branch pipeline and a second-stage gas branch pipeline, the first-stage gas branch pipeline and the second-stage gas branch pipeline are connected in parallel, and the air blower is connected with the staged combustor. A first-stage fuel gas electric control valve is mounted on the first-stage fuel gas branch pipeline, and a second-stage fuel gas electric control valve is mounted on the second-stage fuel gas branch pipeline; the air blower is connected with the grading combustor through an air main pipeline, a first-stage air branch pipeline and a second-stage air branch pipeline, the first-stage air branch pipeline and the second-stage air branch pipeline are connected in parallel, and a first-stage air electric control valve is installed on the first-stage air branch pipeline; and a second-stage air electric control valve is mounted on the second-stage air branch pipeline. According to the invention, high-efficiency combustion and low-nitrogen emission are realized in a relatively wide load range.

The invention discloses flue gas recirculation and oxygen-enriched combustion collaborative denitration equipment for a pulverized coal fired boiler, and belongs to the technical field of collaborative denitration. The pulverized coal boiler comprises a heat exchange tank, and a combustion tank and a smoke return pipe are arranged in the heat exchange tank. One side of the smoke return machine shell communicates with a combustor shell, and the combustor shell communicates with the combustion tank. An igniter and a graded oxygen-enriched combustor are arranged in the combustor shell, and the graded oxygen-enriched combustor comprises a central oxygen channel structure, a pulverized coal air channel structure and a compensation oxygen channel structure; core flames of pulverized coal air are ignited through the central oxygen channel structure, then the pulverized coal air with low oxygen content sprayed out of the pulverized coal air channel structure is ignited through the core flames, and a low-oxygen combustion section close to the root of the fire tongue is formed. Oxygen is sprayed out through the compensation oxygen channel structure, so that pulverized coal air is subjected to oxidation reaction and is fully combusted; according to the invention, a staged combustion effect can be formed, nitrate substances generated by a pulverized coal oxidation reaction are greatly reduced, and the capability of denitration of combustion flue gas is improved.

The application discloses a low-NOx ammonia fuel combustion system based on plasma combustion support X The generated staged ammonia gas combustion system comprises a high-frequency high-voltage power supply, a dielectric barrier plasma generator, a gas distribution system (a blower and an ammonia storage tank), a combustion chamber and a swirler; the dielectric barrier plasma generator comprises a high-voltage electrode, an insulating medium, a swirler and a ground electrode; and the gas distribution system comprises a blower and an ammonia storage tank. The application utilizes dielectric barrier to generate ammonia gas plasma discharge, reduces the difficulty of ammonia gas combustion and improves the stability of ammonia gas combustion; utilizes the swirler to generate rotating airflow and improves the combustion efficiency; utilizes ammonia gas staged combustion to further reduce NOx emission; and the ideal staged ratio is that the volume ratio of ammonia gas plasma to side wall ammonia gas is 20% (10%-30%), so that the ammonia gas plasma can be fully discharged, and the ammonia sprayed from the side wall can also be fully combusted.

The invention discloses a natural gas hydrogen-doped gas burner, which adopts a two-stage gas and three-stage air distribution structure, first-stage mixed gas pipes are uniformly arranged on an inner ring in a multi-ring manner, the first-stage mixed gas and first-stage air are subjected to micro-mixing combustion, and second-stage combustion devices are uniformly arranged on the peripheries of the first-stage mixed gas pipes; secondary fuel and secondary air are subjected to diffusive combustion, and a third-stage over fire air channel is arranged on the same ring, so that air classification is enhanced; two-stage fuel gas can be evenly mixed with air through the multi-stage micro-mixing device, multiple strands of evenly-combusted small flames are formed at an outlet of the combustor, ignition and stable combustion of the fuel gas are guaranteed, local high temperature is avoided, air classification is combined, multi-stage combustion is achieved, generation of thermal NOx is reduced, high-power efficient mixed combustion of hydrogen and natural gas can be achieved, and the combustion efficiency is improved. The application range is wide.

A gas turbine unit includes a compressor (2), a turbine (5), a combustor assembly (3), and a fuel supply assembly (4); the combustor assembly (3) includes at least one combustor unit (7); the combustor unit (7) includes a first-stage combustor (8) and a second-stage combustor (9); the first-stage combustor (8) includes a first-stage incinerator (11) and a first-stage combustion chamber (12); the first-stage fuel is an amino fuel; wherein the second-stage combustor (9) includes a second-stage incinerator (13) and a second-stage combustion chamber (14); the fuel supply assembly (4) is configured to supply at least one first-stage fuel to the first-stage incinerator (11) such that the combustion stoichiometry of the first-stage incinerator (11) is unbalanced and there is an excess of first-stage fuel in the first-stage incinerator (11) to obtain unburned first-stage fuel reaching the second-stage incinerator (13).

The present application relates to the technical field of combustor, in particular to a kind of low-nitrogen combustor of roasting furnace natural gas based on cyclone and staged combustion, solve the problem that more nitrogen oxides can be produced in the combustor in the prior art;It includes outer sleeve, inner sleeve and inner core tube, the outer sleeve is sleeved on the outside of inner sleeve, air flow channel is formed between the outer sleeve and inner sleeve, the inner core tube is connected to the inside of inner sleeve, the inner sleeve is formed with natural gas flow channel through inner core tube, the inner wall of outer sleeve is formed with first rifling, the inner wall of inner sleeve is formed with second rifling, spiral groove is formed on the inner core tube and penetrates both ends;The scheme utilizes multiple rifling structures to make air and gas produce cyclone, improve mixing effect, enhance the radiation heat transfer effect of combustion in the furnace on furnace wall, increase the thermal efficiency of equipment, reduce energy waste, compared with conventional direct injection type combustor, NOx is reduced by 40.7%, and flame length is nearly 2 times of conventional direct injection type.

A aircraft gas turbine engine and operation method, the engine including: a staged combustion system having pilot and main fuel injectors, and operates in a pilot-only range wherein fuel delivers to pilot fuel injectors, and a pilot-and-main operation range wherein fuel is delivered to at least the main fuel injectors. The engine further includes a fuel delivery regulator to pilot and main fuel injectors, which receives fuel from a first and second source containing fuels each with different characteristics. The staged combustion system switches between pilot-only and pilot-and-main range operation when in steady cruise mode, the mode defining a boundary between first and second engine cruise operation range. The fuel delivery regulator delivers fuel to pilot fuel injectors during at least part of the first engine cruise operation with different fuel characteristics from fuel delivered to one or both pilot and main fuel injectors the second engine cruise operation range.

The application relates to the technical field of hydrogen fuel engines and discloses a hydrogen fuel staged combustion unit, a full-ring combustion chamber and an aero-engine. The hydrogen fuel staged combustion unit comprises a shell and a nozzle. An air flow cavity is formed in the shell. A combustion cavity is formed by the shell. The air flow cavity is communicated with the combustion cavity. The nozzle is provided with at least two nozzles. The at least two nozzles are arranged at intervals along the engine axis direction. The nozzle is arranged on the shell. A hydrogen fuel cavity is formed in the nozzle. The first end of the nozzle is adapted to communicate with hydrogen fuel. The second end of the nozzle is arranged in the combustion cavity. A group of injection holes are arranged on the nozzle. The group of injection holes is arranged close to the second end of the nozzle. The group of injection holes penetrates the nozzle to communicate the hydrogen fuel cavity with the combustion cavity. At least two nozzles are arranged along the engine axis direction. The hydrogen gas entering the combustion cavity is mixed with the air in the combustion cavity more sufficiently. The mixing uniformity of the hydrogen gas is improved. The temperature of the combustion cavity is reduced. The emission is reduced.

A combustor assembly (3) for a gas turbine unit (1) comprises at least one combustor unit (7) provided with a liner (16) extending substantially along a combustor axis (B); the combustor unit (7) comprising a first-stage combustor (8) and a second-stage combustor (9), which is arranged downstream the first-stage combustor (8) along the gas flow direction (G); the first-stage combustor (8) comprising a first-stage burner (11), fed with first-stage fuel and first-stage air, and a first-stage combustion chamber (12), where the first-stage fuel is burned; wherein the second-stage combustor (9) comprises a second-stage burner (13) and a second-stage combustion chamber (14); the second-stage burner (13) being arranged downstream of the first-stage combustion chamber (12); the second-stage combustion chamber (14) being fed with hot gas leaving the first-stage combustion chamber (12) and passing through the second-stage burner (13), with dilution air and with a second-stage fuel; wherein the dilution air and the second-stage fuel are injected simultaneously within the second-stage burner (13).

A hydrogen combustion-supporting liquid ammonia gas turbine combustor comprises a liquid ammonia fuel pipeline located at a center main shaft, a first-stage axial swirler and a first-stage radial swirler coaxially arranged outside the liquid ammonia fuel pipeline, and the swirler directions are the same and used for stabilizing the liquid ammonia flame. A pre-evaporation pipeline is arranged outside to form a hydrogen gas collecting chamber, and a center space of the pre-evaporation pipeline forms a primary air channel for completing pre-mixing swirl of liquid ammonia, hydrogen and air to stabilize the liquid ammonia flame. The pre-evaporated ammonia gas in the pre-evaporation pipeline enters a secondary air channel and completes pre-mixing swirl with air through a second-stage axial swirler. Secondary air holes are formed on a wall surface of a flame tube, a large amount of air enters to burn the fuel completely and improve combustion efficiency, and simultaneously dilutes tail gas to reduce NOx emission. The present application uses liquid ammonia as fuel, realizes stable liquid ammonia flame and reduces NOx emission through liquid ammonia fuel staging, hydrogen combustion-supporting, multi-stage swirl pre-mixing and staged combustion.

The application discloses a multi-layer dispersion combustion, high-efficiency energy-saving yellow phosphorus tail gas low-nitrogen burner and a multi-stage combustion method, and belongs to the technical field of energy saving and environmental protection. The mounting flange of the burner is connected with a furnace chamber. The burner comprises a cylinder body, the cylinder body is divided into a fuel cavity and a combustion-supporting cavity which are relatively independent through a transverse partition plate, the fuel cavity is used for conveying yellow phosphorus tail gas, and the combustion-supporting cavity is used for conveying high-pressure and high-speed combustion-supporting air. A center gun is arranged at the center of the cylinder body, an inlet end of the center gun is communicated with the fuel cavity, a plurality of layers of spray gun pipes are arranged, nozzles of a part of the spray gun pipes are staggered in height, and the nozzles of the spray gun pipes are oriented in different directions; a part of the spray gun pipes are provided with rotating blades; an air automatic rotating assembly is arranged at the outer periphery of an outlet end of the center gun and is communicated with the combustion-supporting cavity, and the air automatic rotating assembly is used for automatically and rapidly rotating the combustion-supporting air, so that the combustion-supporting air and the yellow phosphorus tail gas are fully mixed. The application solves the problems of yellow phosphorus tail gas ultra-low NOx and CO emission and yellow phosphorus tail gas blockage.

The dual-fuel engine piston capable of reducing methane emission comprises a piston body, a concave pit is formed in the top face of the piston body to serve as a combustion chamber, the top face of the piston body is connected with the side face of the piston body through a flow guide face, and the combustion chamber is communicated with the flow guide face through a plurality of vortex grooves. A set included angle is formed between the vortex groove and the tangent line of the outer circumference of the combustion chamber; according to the utility model, the flow guide surface is arranged between the piston top surface and the piston side surface, so that natural gas in the backlash can be guided into the combustion chamber for combustion, and methane emission is further reduced. A vortex groove is formed in the top face of the piston, natural gas in a side gap passes through a flow guide face to a motion chamber in a combustion chamber and inevitably passes through the vortex groove, airflow is guided by the vortex groove to form a certain vortex in a cylinder, later-stage combustion is accelerated, combustion is more sufficient, and methane emission is further reduced.

A natural gas ammonia-doped optimized combustion device comprises an inner center pipe, a primary air pipe assembly, a natural gas pipe assembly, an ammonia gas pipe assembly, a secondary air pipe assembly and a recirculation pipe assembly, the primary air pipe assembly, the natural gas pipe assembly, the ammonia gas pipe assembly, the secondary air pipe assembly and the recirculation pipe assembly are sequentially arranged outside the inner center pipe, the design of the ammonia center pipe is adopted, ammonia fuel is divided into two parts to be introduced into a combustion chamber, staged combustion of the ammonia fuel is formed, and the combustion efficiency is improved; the flexible and adjustable large-proportion ammonia doping working condition is realized. Fuel is divided into direct-flow air and rotational-flow air to be fed into the combustion chamber, the rotational-flow air enters the combustion device through a tangential channel, is tightly attached to the wall face, forms rotational flow under the action of inertia and centrifugal force and enters the combustion chamber, and therefore rotational-flow air with certain strength is obtained, and the rotational-flow strength is flexible and adjustable by changing the air inflow of the two channels. The multi-stage combustion of fuel can be realized, the stability of ammonia-doped combustion is improved, and the emission of NOx can be greatly reduced while the emission of CO2 is reduced.

The pyrolysis incinerator comprises a pyrolysis chamber provided with a conveying device, the input end of the conveying device is located below a feeding port, and the output end of the conveying device extends to the output end of the pyrolysis chamber; an inner cavity of the multi-stage combustion chamber is divided into a falling combustion chamber, a movable combustion chamber and a gas combustion chamber, the top of the falling combustion chamber is communicated with the output end of the pyrolysis chamber, the bottom of the falling combustion chamber is communicated with the gas combustion chamber through the movable combustion chamber, an inclined plane is arranged in the movable combustion chamber, and the top end of the inclined plane is located below the falling combustion chamber; the bottom end of the inclined surface obliquely extends downwards to the slag discharging opening; and the air distribution mechanism is communicated with the multi-stage combustion chamber. According to the invention, pyrolyzed products can be combusted more sufficiently, residues are less, the requirement for subsequent treatment of the residues is reduced, generation of harmful gases can be reduced, the garbage treatment efficiency can be effectively improved, the structure is compact, and the operation is simple.