237 results about "Fuel distribution" patented technology

The invention relates to the technical field of steam turbine testing, in particular to a testing system for mismatch correction of a wide-load-interval thermal power generating unit speed regulation model, which comprises a thermodynamic system component, a speed regulation system device, a dynamic signal acquisition device and a control device, a dynamic signal processing module analyzes the relevance between main steam pressure sudden change and control valve opening oscillation in real time, a dynamic response database including a time sequence is constructed, and a control valve opening feed-forward compensation instruction and a combustor fuel distribution gradient adjustment signal are generated according to correction parameters. Power over-modulation wave crests caused by sudden load change are suppressed, and primary frequency modulation action delay is reduced; and the simulation verification module compares measured data with model output through an error feedback mechanism, dynamically adjusts high-pressure cylinder flow characteristic curve calibration parameters, optimizes a control strategy in combination with a network-related safety margin evaluation result, and realizes improvement of dynamic response precision in a full peak regulation interval and enhancement of power grid frequency stability.

The invention belongs to the technical field of aircraft control, relates to an aircraft gravity center real-time balancing method and system based on dynamic parameter fusion, and aims to solve the problems of insufficient real-time performance, accuracy and self-adaptability of a gravity center balancing method under complex flight conditions in the prior art. The method comprises the steps that real-time parameters are obtained, and the real-time gravity center position is calculated; if the real-time gravity center position is not within the preset range, calculating a first inertia moment and a first additional moment caused by fuel density change and a second inertia moment and a second additional moment caused by aeroelastic deformation; performing inertia moment correction based on the first inertia moment and the second inertia moment; additional moment correction is carried out based on the first additional moment, the second additional moment and the real-time pitching inertia moment; when the real-time gravity center position is within the preset range, gravity center balancing is completed. The fuel oil density and aeroelastic parameters are estimated in real time through a self-adaptive control algorithm, rudder deflection and fuel oil distribution are cooperatively adjusted, and the problem of center-of-gravity shift under complex disturbance can be effectively solved.

The present application discloses an aircraft configured for vertical take-off and landing and horizontal flight. The aircraft includes (i) a first nacelle fuel tank configured to hold a first fuel supply for a first engine and to selectively provide fuel to the first engine during both (a) a vertical take-off and landing, and (b) horizontal flight; (ii) a fuselage fuel tank, and (iii) a control system configured to redistribute fuel between the first nacelle fuel tank and the fuselage fuel tank.

The utility model discloses a flame-catalysis integrated combustor, which solves the problem that catalytic combustion and flame combustion are not integrated in the prior art, and has the beneficial effects of realizing integrated combustion and improving combustion efficiency, and the specific scheme is as follows: the flame-catalysis integrated combustor comprises a shell, one side of the shell is provided with an air inlet, and the other side of the shell is provided with an air outlet; a fuel-air mixer, a flame tube and a catalytic component are sequentially arranged in the shell from one side of the air inlet to the other side of the shell, the fuel-air mixer comprises a plurality of fuel distribution chambers which are sequentially arranged in a nested mode, and a gas circulation channel is formed between every two adjacent fuel distribution chambers; the fuel distribution chambers are provided with fuel spray holes facing the gas circulation channel, the outlet end of the fuel-air mixer is inserted into the flame tube, the flame tube comprises a shell, the shell and the shell are arranged at an interval, and the catalytic component is fixed to the end, away from the fuel-air mixer, of the shell of the flame tube.

The invention discloses a gas turbine multi-fuel reference real-time voting scheduling method, and relates to the technical field of gas turbine combustion control, and the method comprises the steps: constructing a plurality of fuel control references, carrying out the collection, integration and comparison of the output of each fuel control reference through a real-time voting control loop, and generating a final fuel control reference; according to the real-time monitoring result, intervention and quit of each fuel control reference are dynamically judged; the proportion of diffusion fuel and premixed fuel and the flow of each branch are controlled through a fuel distribution system, and gas turbine multi-fuel reference real-time voting scheduling is achieved. The fuel distribution proportion can be flexibly adjusted under different working conditions, the combustion process is optimized, fine combustion control of the gas turbine under different working conditions is achieved, the comprehensive performance and economical efficiency of the gas turbine are remarkably improved while the combustion efficiency is improved, pollutant emission is reduced, and the equipment safety is enhanced, and the method is suitable for popularization and application. The method has important application value and wide market prospect.

The invention provides a dual-fuel low-nitrogen combustor. The dual-fuel low-nitrogen combustor comprises a central ignition unit, a premixing air duct, a fuel distribution unit and a combustion-supporting air distribution unit. The premixing air cylinder comprises an outer cylinder, a center hole and n premixing cylinders. The center ignition unit penetrates through the center hole, and the n premixing barrels are distributed on the periphery of the center air pipe in an array mode along the circumference, so that the whole fire outlet interface of the premixing air barrels is fully utilized, the uniformity and stability of flames are improved, and generation of nitric oxide is reduced. The fuel distribution barrel is divided into four cavities through axial front-back separation and radial inner-outer separation, the structure is compact, and fuel can be evenly and stably distributed to all the injection pipes. According to the invention, two fuels with high and low calorific values can be adopted, and the two fuels do not interfere with each other, operate independently, can be used at the same time and can also be used independently, so that the selectivity of the fuels is relatively wide. The flame structure can be kept the same, and application occasion adaptability is improved.

The invention discloses a strong-cooling micro-mixing nozzle and belongs to the technical field of advanced combustion. The high-temperature-rise burner solves the problems that an existing high-temperature-rise burner for burning hydrogen-containing fuel is high in flame temperature and high in burning speed, so that tempering is likely to happen, and safe and stable operation of the burner is seriously affected. The air-fuel mixing module is installed on an end cover of the combustor, an air-fuel mixing hole is formed in the air-fuel mixing module, the other end of the fuel rod is inserted into the air-fuel mixing hole, one end of the rod body is installed on a fuel distribution cavity cover plate of the combustor, the connecting plug is of a stepped rod-shaped structure, and the large-diameter section of the connecting plug is fixedly connected with the other end of the rod body. The sealing cover coaxially covers the connecting plug, the opening end of the sealing cover is fixedly connected with the other end of the rod body, an annular channel is formed between the outer wall face of the small-diameter section of the connecting plug and the inner wall face of the sealing cover, and a plurality of fuel holes are formed in the sealing cover. The micro-mixing nozzle is high in flowability and enhanced in cooling and heat exchange performance, can effectively cool a sealing cover of the micro-mixing nozzle, improves the tempering resistance of the micro-mixing nozzle, and ensures safe and stable operation of a combustor.

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 burner nozzle structure capable of improving the fuel distribution characteristic. A bluff body swirl vane comprises a plurality of swirl single pieces, a swirl channel is formed between every two adjacent swirl single pieces, the swirl single pieces form an incident flow face on the incident flow side, and when fluid impacts the incident flow face, streaming is formed, wide wake flow is generated, and the phenomenon that the fluid falls off along with vortexes is achieved; and the fuel supply system comprises a fuel cavity and a fuel pipe, one end of the fuel cavity is connected with the fuel pipe, the fuel pipe is arranged along the central axis of the combustor shell, and the fuel cavity is provided with a fuel spray hole communicated into the rotational flow channel. The design of the trapezoidal cross section and the incident flow surface of each rotational flow single piece is utilized to enable fluid to form streaming, wake flow and vortex shedding, turbulent mixing and high-temperature flue gas backflow are enhanced, meanwhile, accurate fuel distribution is achieved through the fuel cavities, the fuel pipes and the fuel spray holes in one-to-one correspondence with the rotational flow channels, combustion-supporting air distribution is further optimized through the multi-stage radial flow dividing rings in the rotational flow channels, and the combustion-supporting effect is improved. And the mixing uniformity of the fuel and the combustion-supporting air is effectively improved.

The invention discloses a heating furnace operation data analysis and fault prediction method and system, and particularly relates to the technical field of fault prediction. The method comprises the following steps: analyzing correlation characteristics of nozzle state fluctuation and fuel non-uniform mixing through nozzle state parameters and fuel flow data of a heating furnace, and extracting a fuel distribution non-uniformity index; based on the hearth temperature field infrared thermal imaging data, the drift trajectory of the hot spot is identified, and a hot spot drift rate and direction prediction result is obtained; calculating a local overheating risk probability by combining a fuel distribution non-uniformity index, constructing a heating furnace risk grade map, identifying a high-risk region, matching an abnormal working condition type by combining a historical fault database, and generating a fault early warning instruction including hot drift path prediction; and according to the fault early warning instruction, the fuel injection pressure and the nozzle opening degree of the fault nozzle are adjusted in real time, effective identification and risk assessment of the hot spot drift trend are achieved, and the fault prediction precision and the response timeliness of the heating furnace are improved.

The invention relates to the technical field of limited space fire hazard flashover prediction. The invention provides a limited space fire hazard flashover prediction method and system based on a physical information neural network. The method comprises the following steps: acquiring sensor observation data and initial fuel distribution data; inputting the space-time coordinate vector and the initial fuel distribution data into a Mamba neural network to obtain predicted values of temperature, incident radiation and fuel mass fraction; calculating a space-time derivative of the predicted value, and constructing a physical residual term containing energy conservation, radiation transfer and fuel consumption equation residual, a boundary residual term and an observation residual term; weighted combination is carried out on the three types of residual errors to construct a loss function, and network parameters and to-be-learned physical parameters are updated through an optimization algorithm; and predicting a temperature field based on the updated network, and judging the time of detonation when the temperature reaches a detonation critical value. The problems of poor reliability and prediction deviation caused by lack of physical rule constraints of an existing data-driven fire prediction model are solved.

The invention relates to a method and system for predicting the maximum rotating speed of a power turbine after an engine loses load, and belongs to the field of aviation gas turboshaft engines. The method comprises the following steps that a pressure signal of a gas compressor outlet of the engine, a pressure signal of a main oil way of a fuel oil distribution device and a pressure signal of an auxiliary oil way of the fuel oil distribution device are obtained; performing a simulation over-rotation test under the maximum state of the engine, and obtaining a fuel oil rule of the maximum state over-rotation of the engine according to a test result; carrying out segmented iterative calculation on the rotating speeds of the power turbine at different time points in the maximum state over-rotating process of the engine to obtain a relationship between the rotating speeds of the power turbine and time; and according to the relationship between the power turbine rotating speed and time, the maximum power turbine rotating speed in the maximum state overrunning process of the engine is obtained. According to the method, the response time, the fuel attenuation rule and the torque change rule of the over-rotation protection system are fully considered, and the maximum rotating speed under the condition of shaft breakage of the engine can be accurately predicted.

The present invention provides a method, device, apparatus, and readable storage medium for distributing fuel in an ammonia-diesel engine, comprising: determining an engine fuel distribution mode when the engine is at a preset time; determining the required torques of diesel and ammonia at the preset time based on the engine fuel distribution mode; determining the diesel fuel quantity based on the required torque, diesel thermal efficiency, diesel calorific value, and engine displacement at the preset time; and determining the ammonia quantity based on the required torque, ammonia thermal efficiency, ammonia calorific value, and engine displacement at the preset time. This invention can effectively reduce the large amount of carbon emissions generated by diesel combustion, while also effectively addressing the problems of difficult combustion and insufficient reaction of pure ammonia fuel, thereby improving the thermal efficiency and fuel economy of the engine.

1. The name of the design product: superhigh pressure fuel distribution pipe. 2. The use of the design product: used for engine fuel distribution, evenly and equally distributing fuel to each fuel injector. 3. The design points of the design product: in shape. 4. The picture or photo that best shows the design points: perspective view 1.

The invention relates to the technical field of aero-engines, and discloses a bundling branch pipe structure which is characterized in that multiple branch pipe inlets are communicated with a fuel header pipe, and multiple branch pipe outlets are located at different heads of a combustion chamber respectively; the plurality of branch pipes are bundled in the same bundling header pipe; the bundling branch pipe structure distributes fuel to all the branch pipes through the fuel main pipe, and then all the branch pipes directly convey the fuel to different heads. Based on the local mass principle, fuel flow paths entering all the branch pipes are bundled together in a bundling mode, fuel of all the branch pipes is independently distributed at the branch positions, the high independence of work of all the branch pipes can be kept by actively controlling the flow capacity of the front ends of all the branch pipes and separating the work environment of all the branch pipes, and the reliability of fuel distribution is improved. And the branch pipe flow is strictly proportionally distributed according to the preset value, so that the high uniformity of fuel distribution of the fuel header pipe is ensured, and the fuel supply uniformity is improved.

A burner includes a primary input port configured to receive hydrogen-containing fuel and primary oxygen-containing gas. A fuel-distribution element comprises a plurality of distribution openings. A flashback arrestor element comprises a plurality of flashback arrestor element channels with a mean width that is smaller than a critical flame quench diameter of the hydrogen-containing fuel. A burner housing can be provided, and the burner housing, fuel distribution element, and flashback arrestor element can be made of plastic and by 3D printing. A combustion element includes a plurality of combustion element apertures configured to cause the burner to produce a flame and / or infrared heat, wherein a mean width of the combustion element apertures is 2-4 times larger than the mean width of the flashback arrestor element channels. A method of heating and a heating system are also disclosed. The combustion element can also be equipped for resistive heating.

The invention discloses a two-stage supporting plate injector applied to a wide-working-condition scramjet engine combustion chamber, belongs to the technical field of scramjet engines, solves the problem that an existing alternating supporting plate is low in fuel and air mixing efficiency under the conditions of a high Mach number and a high equivalence ratio, and comprises a supporting plate body. One end of the supporting plate body is a wedge-shaped tail edge formed by arranging a plurality of wedge-shaped slopes in a staggered mode, and first-stage fuel oil spraying holes are formed in the staggered points of the wedge-shaped slopes in the wedge-shaped tail edge. The two side faces of the supporting plate body are symmetrically provided with a plurality of second-stage fuel oil spraying holes inclined in the wedge-shaped tail edge direction. The first-stage fuel injection hole and the second-stage fuel injection hole form a two-stage fuel injection system, the fuel input mode is changed fundamentally, and the fuel flow ratio of the two-stage fuel injection system is dynamically adjusted according to different inlet Mach numbers and equivalence ratios, so that the two-stage support plate injector can be used in various working conditions, and the service life of the two-stage support plate injector is prolonged. And the optimal mixing efficiency can be realized through the optimal fuel distribution strategy.

The utility model provides an oil gun atomizing sheet with a double-included-angle atomizing structure, which comprises an atomizing base body component, an outer ring atomizing component and an inner ring atomizing component, the oil gun atomizing sheet can generate two groups of oil mist spraying at different angles through the arrangement of the outer ring atomizing component and the inner ring atomizing component, the atomized oil mist of the two parts can be mutually supplemented, and the atomizing effect is good. Therefore, the coverage range of oil mist is expanded, fuel can be more evenly distributed in a combustion area, the combustion efficiency is improved, due to the synergistic effect of the outer ring atomization component and the inner ring atomization component, it can be guaranteed that the fuel is fully mixed and atomized in the combustion process, the stable combustion process can be achieved through the even fuel distribution, and the combustion efficiency is improved. The possibility of combustion fluctuation and incomplete combustion is reduced, the whole atomizing sheet is compact in structure and easy to mount and dismount, the matching notch is matched with the oil gun in shape, the atomizing sheet can be conveniently mounted on the oil gun through a connecting piece, and maintenance and replacement are facilitated.

The present application relates to a kind of gas turbine fuel nozzles, including duty road gas pipeline, main road gas pipeline, main fuel distribution cavity, duty fuel distribution cavity, swirler blade, main road fuel nozzle and duty fuel air mixing cavity, the upper portion of the outer wall of duty fuel air mixing cavity is provided with multiple air holes, and the bottom of duty fuel air mixing cavity is provided with center nozzle;Duty gas cavity is arranged in duty fuel air mixing cavity, and the bottom of duty gas cavity is provided with multiple center holes;Duty road gas enters duty fuel air mixing cavity through center hole and mixes with the air entering from air hole, and is ignited by igniter, fuel is sprayed through center nozzle, and pencil type flame is formed when gas turbine is in no-load condition.The present application can solve the problem that gas turbine is easily extinguished during acceleration process, especially when reaching no-load condition;At the same time, the fuel air ratio of duty flame reaches reasonable value when gas turbine is in different load conditions, so that the NOx emission of the whole nozzle is greatly reduced.

Embodiments of the present application provide an online water injection system and method for fuel icing test, relating to the field of aero-engine fuel icing test. It aims to improve the problem of unstable water content of fuel distribution in fuel icing test. It includes main oil supply path, steady-state water injection cylinder, steady-state nozzle, transient water injection cylinder, transient nozzle, bypass solenoid valve, oil supply pressure sensor and test piece; the steady-state water injection cylinder is connected with the steady-state nozzle, and the transient water injection cylinder is connected with the transient nozzle; the bypass solenoid valve is connected with the test piece in parallel, and the bypass solenoid valve is connected with the oil supply pressure sensor. Through the parallel connection scheme of the bypass electric control valve and the test piece, the transition state water-containing fuel oil supply is converted into steady-state supply, solving the problem that the water injection flow cannot quickly follow the change of fuel flow during the transition state of the test piece, and further providing stable water-containing fuel oil, realizing the continuous supply of stable water-containing fuel oil under the transition condition.

A compact combustion chamber belongs to the fields of combustion and aerodynamic technologies of aeroengines and gas turbines. The invention solves the problems of large axial dimensions of the existing combustion chamber and turbine, uneven temperature distribution at the outlet of the combustion chamber, and high NOx emissions. The intake passage is communicated with the air distribution cavity. A main fuel distribution outer cavity, a pilot fuel distribution cavity, and a main fuel distribution inner cavity are sequentially separated along the radial direction of the combustion chamber between the cover plate assembly and the fuel pipe base. The front parts of a plurality of micro-mixing nozzles are inserted on the fuel pipe base, and the rear parts of the plurality of micro-mixing nozzles are correspondingly inserted in a plurality of air distribution holes. The fuel and the oxidant are premixed by internal cross-jet under micro-scale conditions, which can improve the premixing degree of the fuel and the oxidant, increase the average temperature and temperature ratio at the outlet of the combustion chamber, and thus reduce the NOx emissions. By controlling the fuel flow rate in different zones, the temperature distribution at the outlet of the combustion chamber can be controlled and adjusted according to the requirements of the thermal stress distribution of the turbine blades and the operating conditions.

The invention relates to the technical field of small aero-engine combustion devices, in particular to a dual-fuel nozzle for a small aero-engine. The device is characterized by comprising a gaseous fuel header pipe and a liquid fuel header pipe, a gaseous fuel inlet pipe and a gaseous fuel branch pipe are arranged on the gaseous fuel header pipe, a liquid fuel inlet pipe and a liquid fuel branch pipe are arranged on the liquid fuel header pipe, and a liquid fuel nozzle is arranged at the end of the liquid fuel branch pipe. And the end part of the gaseous fuel branch pipe is connected with a liquid fuel nozzle through a gaseous fuel adapter. The liquid fuel pipeline and the gaseous fuel pipeline are combined, the engine adopts gaseous fuel and is easy to ignite and start during starting ignition and low working conditions, and the fuel is switched and the liquid fuel is adopted after the engine enters a slow state, so that a fuel distributor is not needed, oxygen supplementation ignition is not needed, and the cost is reduced. The ignition performance of the small aero-engine combustion chamber is improved, and the complexity and the structural weight of an accessory pipeline system are reduced.

Methods and apparatus for hydrogen aircraft with cryogenic compressed storage are disclosed. An example fuel distribution system includes a vacuum vessel, a cryogenic vessel positioned within the vacuum vessel, the cryogenic vessel being part of a cryogenic compressed hydrogen delivery assembly, and at least one of a heater or a thermosyphon loop to maintain pressure of the cryogenic vessel.

The application discloses a high-power pure-ammonia low-nitrogen combustor, which comprises a wind box, a first-stage air distribution air duct, a second-stage air distribution air duct, a third-stage air distribution air duct and a fourth-stage air distribution passage, a point ignition device is arranged in the first-stage air distribution air duct, and a tangential cyclone device is arranged in the fourth-stage air distribution passage; a central cyclone disc is fixedly connected to the front end of the first-stage air distribution air duct, a plurality of annularly-arranged first-stage ammonia fuel nozzles are arranged in the second-stage air distribution air duct, and the first-stage ammonia fuel nozzles are connected with first-stage ammonia fuel distribution rings through connecting pipes; a flue gas entrainment plate with a plurality of through holes is arranged at the front end of the third-stage air distribution air duct, and front ends of a plurality of second-stage tubular ammonia fuel injection guns pass through the flue gas entrainment plate; a plurality of third-stage ammonia fuel injection guns are arranged in the fourth-stage air distribution passage, and each tubular ammonia fuel injection gun is connected with a corresponding ammonia fuel distribution ring; a system cut-off valve and an adjusting valve are arranged on a conveying pipeline of each ammonia fuel distribution ring; the combustor can realize multiple-stage fuel grading and multiple-stage air distribution, and can realize stable combustion through self-entrainment and backflow of multi-stage high-temperature flue gas in a stable combustion area, so that stable combustion of ammonia fuel is realized and a low-NOx emission effect is achieved.

Annular burner (10) for internal centrifugal fiber spinning of glass fibers, comprising a combustion chamber (12), a combustion chamber casing (14), an ejection nozzle (18) and a fuel and oxidizer supply system (20) to the combustion chamber (12) in gaseous state, the fuel comprising dihydrogen and the oxidizer comprising dioxygen, the supply system (20) comprising a plurality of injectors (22) distributed around the combustion chamber (12) and opening into the combustion chamber (12) and a fuel distribution ring (24) into the injectors (22), the fuel distribution ring (24) comprising a fuel inlet conduit (26) into the fuel distribution ring (24) and the distribution ring (24) forming with the casing (14) a fuel distribution chamber (28),the fuel distribution chamber (28) being in direct fluidic communication with at least two injectors (22) of the plurality of injectors. Figure for the abbreviation: Fig. 1,

The invention discloses a high-pressure fuel distribution pump head state monitoring and fault prediction method and system based on deep learning, and the method comprises the steps: obtaining multi-source sensing data of a pump head through an innovative sensor layout scheme corresponding to a subsequent graph neural network (GNN) model node; the data are input into a physical information neural network (PINN) model constructed based on an enhanced physical model, a physical residual error of quantitative data and a physical rule deviation degree is obtained, and the enhanced physical model considers nonlinear characteristics of pressure-compressibility, temperature-viscosity and the like of fuel oil; abstracting the physical structure of the pump head into a GNN model comprising a plurality of component nodes; on the basis of a mapping rule, the physical residual error is updated to the feature of the corresponding component node in the GNN model; reasoning is carried out through the GNN model, and fault diagnosis information is output. The problems that a traditional deep learning method is poor in interpretability, depends on massive fault data and is weak in generalization ability are solved, and diagnosis and prediction of early weak faults of the pump head are achieved.

The utility model discloses an interval type wide-combustion-range multi-fuel gas burner, which belongs to the technical field of gas diffusion combustion and comprises a fuel preheating and distributing cavity, and one end of the fuel preheating and distributing cavity is connected with an air and fuel distributing channel. The air and fuel distribution channel comprises a plurality of fuel and air distribution channels which are arranged at intervals and are not communicated; the fuel preheating and distributing cavity comprises a plurality of fuel and air channels which are arranged at intervals and are not communicated with each other; the fuel channel comprises a plurality of fuel distribution channels which are not communicated with one another, and the fuel distribution channels are connected with the fuel distribution channel; the air channel comprises a plurality of air distribution channels which are not communicated, and the air distribution channels are communicated with the air distribution channel. The air distribution channel and the fuel distribution channel are arranged at intervals and connected with the air distribution channel and the fuel distribution channel respectively, so that air and fuel are in multi-channel jet flow, mixing of the fuel in the combustion process is enhanced, the temperature uniformity is improved, the flame length is shortened, the combustion range is wider, the volume power density is improved, and safety is higher.

The application discloses a kind of experimental sintering cup test systems, including sintering cup, mixing hopper, pipe assembly and cloth assembly, the top of sintering cup is equipped with inlet;Mixing hopper is arranged in the upper portion of sintering cup, and the mixing cavity for material mixing is equipped in the mixing hopper;Pipe assembly is arranged between the mixing hopper and the sintering cup, and is used to guide the material discharged from the mixing hopper to enter the sintering cup, and the pipe assembly is equipped with the discharge port corresponding to the inlet;Cloth assembly is rotatably arranged on the discharge port of the pipe assembly, and the material of the pipe assembly enters the inlet under the guidance of the cloth assembly, and the rotational movement of cloth assembly can dynamically adjust the falling path and distribution density of material, so that the mixed material forms the segregation layer structure in the actual production when entering the inlet of sintering cup, and truly reflects the key influence of segregation on the permeability of material layer and fuel distribution.

The application relates to a control method and device of a combined fuel engine. The method comprises the following steps: obtaining a corrected standard injection parameter when the engine of a vehicle meets a correction condition; wherein the corrected standard injection parameter is determined according to a vehicle driving parameter and a standard injection parameter under a preset working condition; and controlling the engine based on the corrected standard injection parameter. The method can correct the fuel distribution ratio on line in combination with the vehicle driving parameter, reduce the influence of the change of the fuel distribution ratio caused by the aging of the combined fuel injector on the engine performance, make the engine in an optimal working state, and improve the engine performance.

A fuel distribution pipe that distributes fuel supplied from a fuel pipe to a plurality of fuel injection devices is provided with a pipe member that forms a storage space that stores the fuel inside, and a connection member that is inserted into and joined to a front end portion of the pipe member and is formed with a through hole that is connected to the storage space. The connection member has an intermediate diameter portion that is adjacent to the storage space, and a small diameter portion that is disposed at a position on the side opposite the storage space from the intermediate diameter portion. The intermediate diameter portion has an inner diameter that is larger than the inner diameter of the small diameter portion and smaller than the inner diameter of the pipe member.