868 results about "Fuel delivery" patented technology

An aircraft system is provided. The aircraft system includes: a gas turbine engine; a fuel system having a fuel tank and a fuel delivery system fluidly connecting the fuel tank to the gas turbine engine; an electric drive assembly including a component module; and a thermal management system including: a thermal fluid loop; a heat source heat exchanger in thermal communication with the component module and the thermal fluid loop; an airflow heat sink heat exchanger in thermal communication with the thermal fluid loop and further configured to be in thermal communication with a cooling airflow during operation of the gas turbine engine; and a fuel heat sink heat exchanger in selective thermal communication with the thermal fluid loop, the fuel tank, or both, the fuel heat sink heat exchanger in fluid communication with the fuel tank independently of the fuel delivery system during at least a first operating condition.

A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, and given byVGVG⁢B.VG is a gutter volume of the gutter and VGB is a gearbox volume. A gas turbine engine includes a combustion section and the gearbox assembly. A fuel delivery system includes a fuel supply line for delivering fuel to the combustion section. A lubrication system includes a lubricant supply line for delivering lubricant to the gearbox assembly. A thermal management system includes a fuel-lubricant heat exchanger for cooling the lubricant with the fuel. The thermal management system selectively directs the fuel through fuel bypass lines or the lubricant through lubricant bypass lines to bypass the fuel-lubricant heat exchanger based on a fuel temperature or a lubricant temperature.

The invention relates to a liquid hydrogen power aircraft, comprising: a liquid hydrogen storage system comprising a liquid hydrogen storage tank for storing liquid hydrogen, a liquid hydrogen pump arranged in the liquid hydrogen storage tank and used for conveying the liquid hydrogen to a liquid hydrogen vaporization device; the liquid hydrogen vaporization device is used for converting liquid hydrogen into normal-temperature high-pressure hydrogen; the fuel conveying and control system is used for conveying the normal-temperature high-pressure hydrogen to the combustion system; the combustion system comprises an engine which is provided with a combustion chamber, and combustion of hydrogen is conducted in the combustion chamber to generate thrust; heat generated during combustion is obtained through an air entraining pipe or an exhaust nozzle to serve as a heat source of the liquid hydrogen vaporization device; and under the action of the heat source, the liquid hydrogen is vaporized after passing through the liquid hydrogen vaporizing device and reaches a combustible state. The liquid hydrogen power system can be used for an aircraft in which liquid hydrogen fuel generates power through combustion, the number of needed devices is small, the overall weight of the liquid hydrogen power system is low, and the reliability of the overall framework of the liquid hydrogen power system is improved.

This invention concerns a fuel delivery system for an aircraft engine, comprising a fuel delivery regulator configured to receive fuel from a plurality of fuel sources for supply to the engine. An engine operating condition sensor reading is received by a control unit configured to control operation of the regulator. The control unit is configured to actuate the regulator based on a received signal from the engine operating condition sensor in order to vary the volume of fuels from the plurality of fuel sources supplied to the engine during at least a portion of a cruise phase relative to a further portion of an aircraft flight. The different fuels may comprise kerosene and an alternative fuel, such as a biofuel.

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

A gas turbine engine for an aircraft, including: staged combustion system having pilot fuel injectors and main fuel injectors, staged combustion system being operable in pilot-only range of operation and pilot-and-main range of operation; and fuel delivery regulator arranged to control delivery of fuel to pilot and main fuel injectors. Fuel delivery regulator arranged to receive fuel from a first fuel source containing a first fuel having a first fuel characteristic and a second fuel source containing a second fuel having a different second fuel characteristic. The fuel delivery regulator is arranged to deliver fuel to the pilot fuel injectors during at least part of the pilot-only range of operation having a different fuel characteristic from fuel delivered to one or both of the pilot and main fuel injectors during at least part of the pilot-and-main range of operation. A method of operating a gas turbine engine is also disclosed.

The present invention relates to a fuel oil theft prevention tool configured to prevent theft or siphoning of fuel oil from a fuel tank. The tool is compact and lightweight and includes a metal female×female reduced coupling, a heavy-duty metal screen having a plurality of holes disposed therein, the screen is positioned inside the reduced coupling and is secured / biased and held tight by a torsional spring, a male×female hex bushing having a hexagonal head is positioned inside the reduced coupling over the screen for further securing of the screen. The tool is positioned between the fuel delivery pipe and the supply pipe and is configured to allow flow of fuel oil in only one direction.

A fuel leak detection system for hydrogen fuel system including a monitored component. The fuel leak detection system including a sensor and controller communicatively coupled to the sensor. The sensor is positioned to monitor at least a portion of the monitored component. The sensor is configured (i) to sense a parameter corresponding to a hydrogen fuel leak of the monitored component and (ii) to generate an output. The controller is configured (i) to receive the output of the sensor, (ii) to determine, based on the output of the sensor, if a leak has occurred in the monitored component, and (iii) to generate an output indicating a fuel system leak when the controller determines that the leak has occurred in the monitored component. The monitored component may be a component of one of a fuel tank, a power generator, and a fuel delivery assembly.

A method of operating a gas turbine engine is disclosed, the gas turbine engine comprising a fuel delivery system arranged to provide fuel; a combustor arranged to combust at least a proportion of the fuel; a primary fuel-oil heat exchanger arranged to have up to 100% of the fuel provided by the fuel delivery system flow therethrough; and a secondary fuel-oil heat exchanger arranged to have a proportion of the fuel from the primary fuel-oil heat exchanger flow therethrough. Fuel is arranged to flow from the primary fuel-oil heat exchanger to the secondary fuel-oil heat exchanger and oil is arranged to flow from the secondary fuel-oil heat exchanger to the primary fuel-oil heat exchanger. The method comprises transferring 200-600 KJ / m3 of heat to the fuel from the oil in the primary fuel-oil heat exchanger at cruise conditions.

The present application discloses a method of determining one or more fuel characteristics of an aviation fuel suitable for powering a gas turbine engine of an aircraft, the gas turbine engine having a combustor supplied with fuel from a fuel system, the method comprising: determining a mass of the fuel being supplied to the combustor; determining a corresponding volume of the fuel being supplied to the combustor; and determining one or more fuel characteristics based on the determined mass and volume. Also disclosed is a fuel characteristic determination system, a method of operating an aircraft, and an aircraft.

A system includes a hydrogen fuel delivery system for an engine. The hydrogen fuel delivery system includes a pump configured to pump hydrogen from a tank storing the hydrogen in a liquid state through the hydrogen fuel delivery system, and an evaporator configured to convert at least some of the hydrogen in the liquid state to a gaseous state. The system also includes a heat source thermally coupled with the hydrogen fuel delivery system and fluidly uncoupled from the hydrogen fuel delivery system. The hydrogen fuel delivery system is configured to supply the hydrogen to the engine for combustion and cool the heat source using the hydrogen.

A system includes a hydrogen fuel delivery system for an engine. The hydrogen fuel delivery system includes a pump configured to pump hydrogen from a tank storing the hydrogen in a liquid state through the hydrogen fuel delivery system, and an evaporator configured to convert at least some of the hydrogen in the liquid state to a gaseous state. The system also includes a heat source thermally coupled with the hydrogen fuel delivery system and fluidly uncoupled from the hydrogen fuel delivery system. The hydrogen fuel delivery system is configured to supply the hydrogen to the engine for combustion and cool the heat source using the hydrogen.

A power system for a vehicle comprising: a gas-fuelled power plant, one or more fuel delivery devices 26 for delivering fuel to the power plant, a fuel tank 34 configured to provide gaseous fuel to th

An apparatus can be arranged and configured so that after a gas turbine is shut down due to a detected condition, a higher autoignition temperature fuel can be utilized to purge a fuel delivery system and facilitate a quicker restart of the turbine. Embodiments can utilize conduits, valves, and a control system for detection of a fault condition warranting a shut down, purging of a lower autoignition temperature fuel via venting and use of a higher autoignition temperature fuel for purging to facilitate subsequent restarting of the turbine. Embodiments can be configured so an inert gas purge is not needed for venting and purging of the fuel delivery system.

The invention discloses a storage and supply system for enhancing flexible operation of a coal power unit by a pulverized coal bunker, particularly relates to the field of thermal power generation, and is used for solving the problem that fuel conveying and combustion are asynchronous during rapid load adjustment of the coal power unit. Coordination control is carried out with the unified fuel demand as the center, the lag effect of pulverized coal storage and release is accurately predicted and counteracted before pulverized coal enters a boiler, and the pulverized coal conveying rhythm is closely aligned with the actual coal use demand. In this way, the oxygen amount and temperature fluctuation in the boiler combustion process are greatly reduced, and the problems that due to the fact that fuel supply is fast and slow, combustion in the boiler is not stable, and pollutant emission is increased are solved; meanwhile, the whole control method can automatically learn and adjust, frequent human intervention is not needed, operation is simpler, more convenient and safer, the capacity of a power plant for rapidly adapting to power grid load changes is remarkably improved, and the flexible advantage of pulverized coal storage and supply is fully played.

Disclosed is n engine system 2 for a vehicle, the engine system comprising a fuel injector 26 for delivering fuel directly into an associated engine cylinder 12, the associated cylinder having a cylin

The invention provides a hydrocarbon fuel cell aero-engine, a gas compressor and a fan in the engine are driven by a motor and can also be driven by a turbine shaft, a fuel cell system is located behind a turbine, and a partial oxidation reforming reactor, a combustion chamber, a fuel delivery pump and an exhaust nozzle are sequentially connected. Tail gas of the fuel cell system and gas which does not react completely are used for driving the turbine to rotate, the main shaft is driven to drive the gas compressor and the fan to work, electric energy generated by electrochemical reaction in the fuel cell system can also be used for driving the generator to work, and two working modes of driving the gas compressor and the fan are adopted; the problem of poor economical efficiency caused by the fact that a turbine is used for driving the gas compressor in the high altitude is solved; through the working modes of the dual-drive air compressor and the fan, the engine can be freely switched between the high altitude and the low altitude according to requirements in the using process. The advantages of cleanness and high efficiency of the fuel cell are utilized, and the problem that a traditional aero-engine is high in oil consumption rate is solved.

The invention discloses a metal product surface sealing device based on an underwater explosion cladding technology, and belongs to the technical field of metal surface treatment. A pressure-resistant cavity is formed in the sealing box body, a buffer supporting structure is arranged at the bottom of the sealing box body, and a fuel tank and a combustion-supporting gas input connector are arranged at the top of the sealing box body; the two oppositely-arranged fixing assemblies are arranged in the pressure-resistant cavity, and a base plate and a covering plate are arranged between the two fixing assemblies; the ignition assembly comprises a mounting shell, a pulse igniter, a safety interlocking module and a power management unit are integrally mounted in the mounting shell, and the gas circuit control system comprises a fuel conveying pipeline and a combustion-supporting gas input pipeline which communicate with a fuel tank. According to the device, efficient and safe operation of underwater explosion compounding is achieved through collaborative innovation of multiple assemblies, the adjustable fixing assembly guarantees the positioning precision of the base plate / covering plate, the intelligent ignition system avoids the ignition failure risk, gas path closed-loop control optimizes the explosion energy stability, and the service life of the device is prolonged through a buffer supporting structure.

An apparatus can be arranged and configured so that after a gas turbine is shut down due to a detected condition, a higher autoignition temperature fuel can be utilized to purge a fuel delivery system and facilitate a quicker restart of the turbine. Embodiments can utilize conduits, valves, and a control system for detection of a fault condition warranting a shut down, purging of a lower autoignition temperature fuel via venting and use of a higher autoignition temperature fuel for purging to facilitate subsequent restarting of the turbine. Embodiments can be configured so an inert gas purge is not needed for venting and purging of the fuel delivery system.

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.

The RDF fuel conveying and crushing all-in-one machine comprises a crushing box and a crushing roller which is arranged on the crushing box and used for crushing cloth and is of a hollow structure, a longitudinal cutting structure for driving the crushing roller to rotate and preventing cloth fibers from winding a shaft on the crushing roller is arranged on the crushing box, and the longitudinal cutting structure comprises a base plate fixedly connected to the crushing box; the base plate is provided with a spline shaft which is driven by a motor and freely rotates in the vertical direction, and the crushing box is provided with a shaft cutting assembly which allows the multiple sets of cutter bodies and the crushing roller to synchronously rotate and reciprocates along the diameter section of the crushing roller in an L-shaped track. Through the multiple sets of cutter bodies which rotate synchronously with the smashing roller and reciprocate in the horizontal direction, cloth fibers wound around the smashing roller can be cut in time, the shaft winding phenomenon is prevented, and therefore the continuity and stability of the cloth smashing process are guaranteed, the downtime is shortened, the maintenance cost is reduced, and the cloth smashing efficiency is improved.

Disclosed is an engine system for a vehicle, comprising a rail volume 28 for receiving gaseous fuel; a shut off valve 38 for controlling the supply of fuel to the rail volume ; an injector assembly in

The utility model relates to the technical field of hydrogen preparation devices, and specifically to an integrated methanol catalytic reforming reaction device, comprising a shell, wherein a reaction chamber is arranged on the upper part of the shell, a combustion chamber is arranged on the lower part, a circulation pipeline for circulating a heating medium is arranged between the reaction chamber and the combustion chamber; a heating tube array for providing heat to the heating medium is arranged in the combustion chamber, a fuel delivery module connected to a feed end of the heating tube array is arranged on the outside of the shell, the overall structure is compact, and no open flame heating is required during use, thereby improving production safety.

Disclosed is a power system for a vehicle comprising a gas-fuelled power plant, one or more fuel delivery devices 26 for delivering fuel to the power plant, a fuel tank 34 configured to provide fuel t

Disclosed in the present invention is an integrated reforming power generation test system having wide-range fuel adaptability, comprising a fuel supply subsystem, a catalytic reforming subsystem, a hydrogen purification subsystem, a power generation subsystem, and a test monitoring subsystem. A fuel pump and a fuel delivery pump are connected to a water-gas shift reactor by means of an evaporator and a reformer, the water-gas shift reactor is connected to a pressure swing adsorption device by means of a first gas-liquid separator, the pressure swing adsorption device is connected to a fuel cell stack by means of a hydrogen buffer tank, and a gas chromatograph is connected to the reformer by means of a third gas-liquid separator and to the water-gas shift reactor by means of a second gas-liquid separator. By using a variety of fuel resources to produce electricity, the present invention breaks through the limitation of the scope of traditional single-fuel reforming power generation systems, ensures the reliability of electricity supply, gets rid of the dependence on specific fuels, enhances regional energy safety, and improves the flexibility of energy supply.

A control system for a fuel cell electric vehicle (FCEV) includes a controller that is configured to control a fuel delivery system to release fuel via an injector with a selected fuel tank valve among a plurality of fuel tank valves controlled to be in an open state and with the other fuel tank valves controlled to be in a closed state. The control is further configured to cause a corrective action in response to a fuel characteristic indicating the selected fuel tank valve is stuck closed.

The invention relates to the technical field of aviation aircraft power systems, and discloses an aero-engine liquid hydrogen fuel conveying system and a control method thereof, which adopt multi-branch high-precision metering to realize wide-range high-precision flow regulation requirements, determine branch through-flow capability by a root order method, and realize high-precision flow regulation of the aero-engine liquid hydrogen fuel conveying system. The number of hydrogen supply branches, the available regulation ratio of the regulating valve and the total flow regulation ratio demand are matched, and the problem of high-precision fuel conveying in an extremely wide flow regulation range is solved. The circulating coupling heat exchanger is adopted to reasonably utilize waste heat of the system to raise the temperature of hydrogen fuel to the level suitable for combustion, reasonable optimization of heat / energy utilization of the system is achieved, fuel consumption is reduced, and circulating heat efficiency is improved. The hydrogen temporary storage tank is adopted to solve the problem that the supply flow of an upstream liquid hydrogen pump and a heat exchanger is not matched with the flow required by a downstream regulating valve due to hysteresis in the heat exchange process in the fuel flow regulation transient process.

The invention discloses an intelligent fuel system and method based on multi-machine cooperation and control of artificial intelligence, and relates to the technical field of intelligent fuel processing, and the method comprises the steps that coal is unloaded to a belt through a ship unloader; coal is conveyed to a bucket wheel machine through a belt; coal is conveyed to a coal bunker through a bucket wheel machine; and the running states of the belt and the bucket wheel machine are monitored through wireless diagnosis. According to the remote full-automatic intelligent control system for the ship unloader, the coal unloading efficiency is greatly improved, and the risk of operation accidents is reduced; according to the full-automatic unattended control system of the bucket wheel machine, the continuity and automation of storage yard operation are realized, and the labor cost is obviously reduced; the wireless equipment diagnosis and monitoring platform improves the equipment maintenance efficiency and the response speed, and reduces the downtime; the image recognition-based coal conveying belt coal blockage and overflow recognition and early warning system effectively prevents the blockage and overflow problems in the fuel conveying process, and ensures the stable operation of a production line.

To provide a burner capable of suppressing combustion deterioration of pulverized fuel when pulverized fuel and ammonia are mixed and burned, a boiler, and a combustion method.SOLUTION: A burner comprises: a pulverized fuel supply pipe that guides pulverized fuel and primary air for transporting the pulverized fuel to a furnace; a first gaseous ammonia supply pipe that supplies gaseous ammonia to the pulverized fuel supply pipe; and a mixed fuel nozzle that ejects a mixture of the pulverized fuel, the gaseous ammonia, and the primary air from the pulverized fuel supply pipe into the furnace. The burner is configured such that a ratio of an amount of the gaseous ammonia to a total amount of the pulverized fuel and the gaseous ammonia supplied to the furnace through the mixed fuel nozzle is 10% or less on a calorific value basis.SELECTED DRAWING: Figure 3