37 results about "Fuel distribution" patented technology

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.

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.

This invention provides a combustion chamber head device and ignition method for a pure hydrogen gas turbine. It relates to the field of gas turbine combustion chamber design, solving the problem of unreliable ignition in existing pure hydrogen combustion chambers. The device includes: a fuel distribution component, a multi-cluster burner, and a base; the multi-cluster burner includes a central combustion cluster and multiple interconnected combustion clusters surrounding the central combustion cluster; the multiple interconnected combustion clusters are divided into N-stage combustion chambers; the fuel distribution component includes a central fuel pipe and N-stage interconnected fuel pipes; each stage of interconnected fuel pipes is isolated from each other and from the central fuel pipe; the central fuel pipe is connected to the top of the central combustion cluster; each stage of interconnected fuel pipe is connected to the top of its corresponding combustion chamber; the bottom ends of the central combustion cluster and the N-stage combustion chambers are respectively connected to the base. This invention provides reliable start-up, stable operation, and low emissions over wide loads, achieving multi-cluster interconnection and reliable flame propagation, significantly improving ignition success rate and combustion stability.

Combustion system comprising: an injection device (40) configured to inject fuel into a combustion chamber (38) of an engine (91, 92); a spark plug (50) configured to perform ignition (I) of the fuel in the combustion chamber; and a normal control unit (65) configured to perform normal control (α) to cause the injection device to perform a predetermined normal injection (F), and subsequently to cause the spark plug to perform ignition, wherein in a predetermined delay range (D) in the combustion chamber the propagation of the flame (P) is further delayed than in any other range when normal control is performed, and in a knocking condition auto-ignition occurs in the fuel in the delay range when normal control is performed, the combustion system further comprising: an adjustment control unit (66),which is configured to perform a predetermined adjustment control (β) when the knock condition is established in order to suppress auto-ignition, wherein the adjustment control does the following: cause the injector to perform a predetermined main injection (Fm) and subsequently perform a predetermined partial injection (Fs) in a second half of a compression stroke to adjust fuel distribution in the combustion chamber to facilitate flame propagation (P) into the retardation region further than with normal injection, and subsequently cause the spark plug to perform ignition.

This invention discloses a combustion organization method and combustion chamber head device for a gas turbine combustor, relating to the technical field of gas turbine combustion. It solves the problems of uneven fuel-air mixing, excessive nitrogen oxide emissions, and localized high temperatures in existing combustion chamber head devices. The device consists of a fuel distributor, fuel injection pipe, igniter, and flame tube cover. The fuel distributor internally forms a primary, secondary, and tertiary fuel distribution chamber, which are not interconnected, meaning the fuel is axially distributed in three stages. Each swirl inlet is connected to a fuel distribution chamber via a fuel injection pipe. This invention, employing a multi-stage fuel distribution and swirl inlet structure, improves fuel-air mixing, effectively avoids localized high fuel concentrations, thereby reducing localized high temperatures, lowering nitrogen oxide emissions, and achieving stable combustion of hydrogen fuel across a wide load range.

This technology provides the ability to detect the state of gaseous fuel flowing through the inner pipe and to prevent leakage of gaseous fuel outside the outer pipe. [Solution] The gaseous fuel circulation device is a gaseous fuel circulation device for an engine that burns gaseous fuel, and comprises a double pipe having an inner pipe through which the gaseous fuel flows and an outer pipe positioned at a predetermined gap from the outer surface of the inner pipe. The double pipe is provided with a detection unit for detecting the state of the gaseous fuel. The detection unit includes a state detection sensor positioned from inside the inner pipe to outside the outer pipe, and a cover unit that covers a protruding part of the state detection sensor that protrudes from the outer pipe.

This disclosure provides a micro-mixing unit and a combustion device for a gas turbine, which is disposed in the fuel distribution chamber of the combustion device for a gas turbine. The micro-mixing unit is characterized by being configured as a tubular structure to accommodate air passage; the inner diameter of the micro-mixing unit is configured with a tapering structure along the airflow direction, and includes a first section located upstream and a second section located downstream; the first section is provided with a fuel hole, and the inner wall of the first section is provided with a protruding structure along the circumferential direction, and the inner wall of the second section forms a smooth wall surface.

This invention provides a boiler fuel feeding method, comprising the following steps: collecting raw coal; classifying the raw coal into N types of colored coal; measuring and obtaining the carbon content Sn of each type of colored coal; selecting and verifying the flue gas reference dust content G and the corresponding mass fraction Kn; grinding to obtain colored coal powder with a particle size Mn; and uniformly mixing the N types of colored coal powder according to the mass fraction Kn to obtain mixed coal powder. By employing the technical solution of this invention, the carbon content of the coal is optimized, and various types and particle sizes of coal powder are rationally matched, so that each type of coal can be fully utilized, reducing resource waste, improving the homogeneity of the carbon content and particle size of the mixed coal powder, ensuring that the dust content of the flue gas generated after the combustion of the mixed coal powder meets the expected requirements, and matching the carbon content of the colored coal with its particle size, avoiding over-grinding of low-ash coal, reducing the load on the coal mill, and reducing enterprise production costs.

A radial partition type combined combustion chamber belongs to the technical field of combustion and aerodynamics of aero-engines and gas turbines. The existing gas-liquid dual-fuel combustion chamber adopts circumferential interval partition combustion, and the problems of local turbine air inlet, uneven turbine air inlet and low turbine efficiency are solved. The gas fuel distribution cavity and the second air distribution cavity are sequentially arranged in the radial direction of the combustion chamber between the cover plate assembly and the fuel pipe locator from outside to inside, the first gas separation plate is arranged in the inner part of the flame tube, the second gas separation plate is arranged between the turbine first stage static blades in the circumferential direction, and the first gas separation plate and the second gas separation plate are fixedly connected. By sequentially arranging the gas fuel distribution cavity and the second air distribution cavity in the radial direction of the combustion chamber from outside to inside, and arranging the first gas separation plate and the second gas separation plate, radial partition is realized, and gas-liquid dual-fuel combined combustion and partition combustion can be realized in one combustion chamber structure.

In one aspect, a method includes establishing a first communication channel between a first computing device associated with a fuel dispenser user and a second computing device configured within a fuel dispenser. The method can further include receiving, by the second computing device, first data characterizing a first authorization of the fuel dispenser user of a fuel dispenser. The method also includes determining, by the second computing device, a second authorization of the fuel dispenser user based on the first data. The method further includes controlling, by the second computing device and based on the second authorization, operation of the fuel dispenser to dispense fuel. The method also includes providing, by the second computing device via the first communication channel, second data characterizing the operation of the fuel dispenser to the first computing device. Related apparatus, systems, and articles are also described.

The present application relates to the technical field of combustion chamber design, more particularly to a device and method for testing fuel injection performance of a combustion chamber head, the device comprising a head fixing plate for fixing the combustion chamber head, a fuel supply device connected to the combustion chamber head via a hose for supplying fuel to the combustion chamber head, an image acquisition device for acquiring images of a fuel injection performance test plate, an illumination device for providing illumination to an image acquisition area of the image acquisition device, and a fuel injection performance test plate located directly below the image acquisition device for calibrating a background image and / or collecting injected fuel and displaying fuel distribution, wherein the fuel is added with a fluorescent component. Through detailed calibration, testing and photographing arrangement, combined with fluorescent imaging technology, the fuel injection performance of the combustion chamber head of an aero-engine and each injection position can be effectively verified and analyzed.

This utility model relates to the field of carburetor technology and discloses a precision fuel injection carburetor, including a carburetor body, a fuel injection mechanism on the surface of the carburetor body, a filter mechanism on the surface of the fuel injection mechanism, a motor housing fixedly connected to the surface of the carburetor body, and a torsion spring cover fixedly connected to the surface of the carburetor body. This utility model uses an annular nozzle tube to deliver fuel, ensuring uniform fuel distribution on the surface of the carburetor body. By using nozzles, the fuel inside the annular nozzle tube is separated through the evenly distributed nozzles, allowing for thorough mixing of fuel and air, promoting fuel atomization, improving combustion efficiency, and enhancing the practicality of the device. By using a pressure tube with a relatively small diameter, the fuel flow space is reduced, increasing the fuel flow velocity and allowing the fuel to quickly fill the annular nozzle tube before being sprayed from the nozzles, ensuring uniform fuel spraying.

The application provides an aero-engine fuel metering characteristic monitoring method and system, the monitoring method comprising: collecting FMV opening degree, engine demand flow and flow data of an airborne flowmeter by an airborne computer to obtain a rated metering characteristic line and a measured metering characteristic line respectively, and determining metering accuracy; determining a calibration area of a main nozzle and an auxiliary nozzle, and when the measured metering characteristic line does not meet the metering accuracy, calculating metering flow data according to fuel distribution; judging whether the calculated metering flow data and the measured metering data are offset in the same trend; if so, the fuel metering characteristic drifts, and the fuel metering function is abnormal; otherwise, the airborne flowmeter is measured incorrectly, and the airborne flowmeter is abnormal. The above monitoring method uses the airborne flowmeter, FMV control data and fuel grading proportion data to detect the fuel metering characteristic under different working conditions, compares the detection data with an embedded fuel metering characteristic table, and judges whether the fuel metering characteristic is abnormal.

The invention relates to a fuel dispensing unit (1) for refuelling a vehicle, comprising a breakaway device (3) comprising a first shut-off valve unit (4) connected to a fuel supply line of the fuel dispensing unit (1) and a second shut-off valve unit (5) connected to a first end (6) of a fuel hose (7), the fuel hose (7) comprising a fuel nozzle (2) at a second end of the fuel hose (7). The first shut-off valve unit (4) and the second shut-off valve unit (5) are intended to be disconnected when a predetermined tractive force from the fuel hose (7) is exceeded to separate the fuel hose (7) from the fuel dispensing unit (1). The fuel dispensing unit (1) comprises a tilting means (8) fixed to an outer side portion (9) of the fuel dispensing unit (1) and supporting the breakaway device (3), such that the breakaway device (3) is inclined at a predetermined angle (α) with respect to the outer side portion (9) of the fuel dispensing unit (1).

The application discloses a slanting detonation engine based on a vertical distribution support plate and relates to the technical field of engines.The slanting detonation engine comprises an air inlet section, a mixing section and an ignition section.The air inlet section is used for compressing supersonic airflow to reduce the airflow speed and increase the static temperature and static pressure.The mixing section is connected with the air inlet end and is internally provided with a support plate which is perpendicular to the bottom of the mixing section.The support plate is used for fuel injection, thereby forming fuel distribution in the vertical direction, so as to match the ignition structure which is vertically stable in the three-dimensional direction of the slanting detonation.The ignition section is arranged at the rear end of the mixing section and is used for compressing the supersonic airflow after the fuel injection structure is mixed, thereby forming a slanting detonation wave through self-ignition ignition, and the ignition area and distance can be changed by changing the angle of the support plate.The increase of the angle of the support plate disclosed by the application can strengthen the mixing of hydrogen, and the ignition distance is reduced in a certain range, so that the ignition on the wedge surface is advanced, and a stable slanting detonation wave is formed earlier.

Procedure, comprehensive: Reducing the total number of fuel injections provided to a cylinder in a given cylinder cycle in response to a reduction in pressure in a fuel distributor (222), including reducing the total number of pre-fuel injections during high engine load conditions and reducing the total number of main fuel injections during low engine load conditions.

There is provided a reheat assembly for a gas turbine engine. The reheat assembly comprises a jetpipe casing, a support duct, a plurality of fuel discharge ports, and a fuel distribution passageway. The jetpipe casing comprises a reheat core section and a reheat bypass section. The support duct radially separates the reheat core section and the reheat bypass section. Each fuel discharge port is configured to discharge fuel received from the fuel distribution passageway. The fuel distribution passageway is defined by an interior channel embedded within the support duct.

This invention provides an integrated evaporative flame stabilizer with fuel injection and stabilization, applied to an afterburner. It includes a stabilizer cooling chamber, a stabilizer control structure, and a fuel system. This invention integrates the stabilizer, fuel system, and fuel plate into a single design. The main fuel injection rod is located within the stabilizer cooling chamber. Low-temperature airflow from the outer bypass is introduced to cool the stabilizer and the main fuel injection rod. Furthermore, the evaporative stabilizer and circumferential stabilizer are designed to work together, with high-temperature airflow introduced from the side intake channel of the evaporative stabilizer. This airflow mixes and evaporates with the fuel in the intake manifold and fuel distribution pipe. Additionally, a radial gap is provided between the fuel distribution pipe and the baffle to allow for thermal expansion of the fuel distribution pipe. This invention overcomes the shortcomings of traditional flame stabilizers, offering advantages such as a wider lean-out threshold, lower flow loss, and higher structural reliability under complex operating conditions.

This invention provides a multi-nozzle array staged combustor head for gas turbines, comprising a shift nozzle, a primary main combustion nozzle, a secondary main combustion nozzle, a combustion chamber end cooling plate, a shift fuel distribution chamber, a primary main combustion fuel distribution chamber, and a secondary main combustion fuel distribution chamber. It employs a staged, zoned nozzle arrangement, with the load increasing progressively from the inside out. By controlling the area of ​​the film cooling holes and the area of ​​the lateral air inlets on the combustion chamber end cooling plate, the velocity of the cooling film cooling holes is ensured to be lower than the nozzle velocity, and the inclined opening of the cooling film cooling holes does not affect the combustion flame. Each stage of the fuel pipe has an independent fuel distribution chamber for gas distribution, ensuring uniform gas distribution and flexible fuel adjustment. This invention can achieve the effects of reducing pollutant emissions, suppressing thermoacoustic instability, and widening the range of heat load adjustment.

The present application relates to a kind of engine loses load power turbine maximum speed prediction method and system, belong to aviation gas turbine engine field including the following steps: obtaining the pressure signal of the compressor outlet of engine, the pressure signal of the main oil line of fuel distribution device and the pressure signal of the auxiliary oil line of fuel distribution device;Maximum state simulation overspeed test is carried out to engine, and the fuel law of engine maximum state overspeed is obtained according to test result;The power turbine speed of different time points in the maximum state overspeed process of engine is calculated by section iteration, and the relationship between power turbine speed and time is obtained;According to the relationship between power turbine speed and time, the maximum power turbine speed of engine maximum state overspeed process is obtained.The present application fully considers the response time of overspeed protection system, fuel attenuation law and torque variation law, and can accurately predict the maximum speed of engine broken shaft.

This utility model provides a high-pressure carbon steel fuel distribution pipe, including a main pipe, a fuel inlet seat, an injector seat, and a mounting bracket. The main pipe has several fuel inlets on its wall. The injector seat is welded to the first interface of the fuel inlet seat, and the second interface of the fuel inlet seat corresponds to the fuel inlets and is welded to the main pipe wall. The fuel inlet seat and the mounting bracket are separately manufactured independent components. The mounting bracket is welded to the main pipe wall. This utility model solves the problems of high cost and complex manufacturing process caused by the existing technology of "integral forging of the fuel inlet seat and mounting bracket".

The application discloses a high-pressure fuel distribution pump head state monitoring and fault prediction method and system based on deep learning, and comprises the following steps: acquiring multi-source sensing data of the pump head through an innovative sensor layout scheme corresponding to subsequent graph neural network (GNN) model nodes; inputting the data into a physical information neural network (PINN) model constructed based on an enhanced physical model to obtain physical residuals of the quantitative data and the deviation degree of the physical law, wherein the enhanced physical model considers the nonlinear characteristics of the fuel, such as pressure-compressibility, temperature-viscosity and the like; abstracting the physical structure of the pump head into a GNN model containing multiple component nodes; updating the physical residuals to the features of the corresponding component nodes in the GNN model based on a mapping rule; and performing reasoning through the GNN model to output fault diagnosis information. The application solves the problems of poor interpretability, dependence on massive fault data and weak generalization ability of traditional deep learning methods, and realizes the diagnosis and prediction of early weak faults of the pump head.

The present application discloses an aircraft configured for vertical take-off and landing and horizontal flight. The aircraft includes one or more processors configured to control distribution of fuel among a plurality of aircraft fuel tanks. Controlling the distribution of fuel includes: (a) determining a first fuel level in a first nacelle fuel tank, wherein the first nacelle fuel tank is configured to provide a supply of fuel to a first engine during both (i) a vertical take-off and land operation, and (ii) a horizontal flight operation, (b) determining a fuselage fuel level in a fuselage fuel tank, and (c) determining whether to redistribute fuel across at least the first nacelle fuel tank and the fuselage fuel tank based at least in part on the first fuel level and the fuselage fuel level.

1. The name of the design product: fuel injector. 2. The use of the design product: for supplying fuel in the form of injection, one end of which is connected with fuel distribution pipe, and the other end is connected with intake manifold or cylinder head. 3. The design points of the design product: in shape. 4. The picture or photo that can best show the design points: perspective view.

The application discloses a 6FA gas turbine automatic combustion adjusting method and system, acquires the pressure value of each combustion chamber of the gas turbine in different frequency bands; if the pressure value is higher than an alarm value, calculates the offset amount for adjusting the pressure value each time; judges whether the offset amount is higher than a preset value, if higher than the preset value, turns to manual adjustment; if lower than the preset value, adds the offset amount to a fuel distribution model constructed in advance, adjusts the fuel flow of the nozzle, and until the pressure value of each combustion chamber in different frequency bands is lower than the alarm value. The application is aimed at the 6FA type gas turbine, through the research on the combustion characteristics of the gas turbine and the development of the adjusting strategy, makes the combustion system of the 6FA gas turbine run in the best matching interval at any time, improves the operation stability, and reduces the number of unplanned shutdowns.

A duel-fuel large diesel engine is proposed, comprising at least one cylinder having a combustion chamber, wherein a piston is arranged in the cylinder for a reciprocating movement between a top dead center position and a bottom dead center position, wherein the cylinder is provided with a first fuel injector (10) for injecting a first fuel into the combustion chamber, and a second fuel injector (20) for injecting a second fuel into the combustion chamber, wherein the first fuel is different from the second fuel, the large diesel engine further comprising a first fuel supply system (5) for supplying the first fuel to the cylinder and a second fuel supply system (7) for supplying the second fuel to a fuel distribution system (6), wherein the fuel distribution system (6) is configured to deliver the second fuel from the second fuel supply system (7) to the second fuel injector (20). A purge line (9) is provided connecting the first fuel supply system (5) to the fuel distribution system (6), wherein a switching member (8) is provided for opening and closing a flow connection through the purge line (9). Furthermore, a method for operating such an engine is proposed.

The application relates to the technical field of gas turbine combustion chambers, in particular to a gas turbine combustion chamber layout structure which comprises an air inlet section, a combustion section is arranged on the air inlet section, five groups of burners are arranged in the air inlet section, the burners comprise an outer shell, a middle shell and an inner shell which are coaxially arranged in sequence, a head swirl generator is arranged at the air outlet end of the middle shell, first guide vanes, second guide vanes, a swirl assembly and an assembling mechanism are arranged in the air inlet section. The application can promote the mixing of different components between air and fuel gas flow, improve the reaction efficiency, increase the uniformity of the gas, effectively reduce the dead zone in the gas flow, make the gas flow more uniform in the whole system, avoid local accumulation or retention, optimize the entering direction of the fluid, enhance the rotation effect of the fluid, guide the smooth discharge of the swirl fluid and maintain a certain flow rate, realize multiple combustion organizations such as diffusion, diffusion+premixing and premixing, so that the air organization and fuel distribution of each burner are controllable.