370 results about "Fuel line" patented technology

A fuel rail and a method for producing the fuel rail for a pressure vessel system are provided. The method provides a fuel line and configures a plurality of rail connectors. The rail connectors have a cross-sectional area that is enlarged in comparison to the provided fuel line, and the rail connectors are configured so as to be integral to the fuel line.

A fuel system for a hydrogen fueled aircraft propulsion system comprises first and second hydrogen fuel tanks configured to store liquid hydrogen, first fuel line and second fuel lines configured to supply hydrogen from the first hydrogen fuel tank to a combustor of a first gas turbine engine and from the second hydrogen fuel tank to a combustor of a second gas turbine engine respectively. First and second fuel pumps are provided, each being configured to pump fuel in a respective first and second fuel line. First and second fuel heaters are provided, each being configured to heat fuel in a respective first and second fuel line. A fuel cross-feed fuel line is provided, which is configured to transfer fuel between the first and second fuel lines. The fuel cross-feed line is provided downstream in fuel flow of the first and second fuel heaters.

Embodiments of systems and methods for supplying fuel, enabling communications, and conveying electric power associated with operation of a hydraulic fracturing unit of a plurality of hydraulic fracturing units are disclosed and may include a fuel line connection assembly configured to be connected to the first hydraulic fracturing unit and to supply fuel from a fuel source to a gas turbine engine connected to the hydraulic fracturing unit. A system also may include a communications cable assembly configured to be connected to the hydraulic fracturing unit and to enable data communications between the hydraulic fracturing unit and a data center or another hydraulic fracturing unit. A system further may include a power cable assembly configured to be connected to the hydraulic fracturing unit and to convey electric power between the hydraulic fracturing unit and a remote electrical power source or the plurality of hydraulic fracturing units.

Embodiments of system and methods for supplying fuel, enabling communications, and conveying electric power associated with operation of a hydraulic fracturing unit of a plurality of hydraulic fracturing units are disclosed and may include a fuel line connection assembly configured to be connected to the first hydraulic fracturing unit and to supply fuel from a fuel source to a gas turbine engine connected to the hydraulic fracturing unit. A system also may include a communications cable assembly configured to be connected to the hydraulic fracturing unit and to enable data communications between the hydraulic fracturing unit and a data center or another hydraulic fracturing unit. A system further may include a power cable assembly configured to be connected to the hydraulic fracturing unit and to convey electric power between the hydraulic fracturing unit and a remote electrical power source or the plurality of hydraulic fracturing units.

A propulsion system comprises a propulsive hydrogen-burning gas turbine engine, a fuel cell stack auxiliary power unit (APU) and a first tank arranged to store liquid hydrogen with an ullage. A first fuel line includes a first pump and a first vaporiser and transports hydrogen from the first tank to combustion apparatus of the engine during operation of the propulsion system. A second fuel line includes a second fuel pump and a second vaporiser and transports hydrogen from the first tank to the fuel cell stack APU. A duct connects the second fuel line at a position thereon between the second vaporiser and the fuel cell stack to the ullage of the first tank, providing for pressure in the first tank to be maintained therein as liquid hydrogen within the first tank is depleted, thus avoiding cavitation of liquid hydrogen within the first fuel pump.

A fuel line, terminating in a refuel connector, is used to fuel / defuel an aircraft, for example with liquid hydrogen. A barrier is disposed around the area where the refuel connector connects to an aircraft fuel port, and is sealed against the aircraft wing with a seal. A gas line runs generally parallel to the aircraft fuel line, and supplies inert gas, for example nitrogen, into the volume defined by the barrier. The inert gas flushes out air present around the refuel connector such that the oxygen concentration in that area is significantly lowered. This prevents ignition of fuel in the event of a fuel leak from the fuel line structure.

This invention discloses an electric heat tracing laying device and its usage method for marine fuel oil pipelines, belonging to the field of electric heat tracing technology. The electric heat tracing laying device for marine fuel oil pipelines includes a traveling frame, and further includes: a traveling assembly mounted on the traveling frame for driving the traveling frame to move axially along the pipeline; the bottom of the traveling frame has an opening for the pipeline to enter; a rotating seat rotatably mounted on the traveling frame, on which an electric heating tape shell is mounted, and the electric heating tape shell releases the electric heat tracing tape outward through a discharge port; and a driving unit mounted on the traveling frame and connected to the traveling assembly. This invention replaces manual labor with mechanical automation, realizing the entire process of spiral winding of the electric heating tape, laying of the aluminum foil tape heat-conducting layer, and segmented fixing of the pressure-sensitive tape, solving the problems of low efficiency and insecure fixing in traditional methods, and significantly improving the safety and maintenance efficiency of marine fuel oil pipelines in low-temperature environments.

A propulsion system comprises a propulsive hydrogen-burning gas turbine engine, a first tank storing liquid hydrogen with an ullage and a first fuel line including a fuel pump and a vaporiser, the first fuel line providing gaseous hydrogen to the engine during operation of the system. A second tank storing gaseous hydrogen is coupled by a second fuel line to the first fuel line at a position thereon between the vaporiser and the engine, providing for engine start-up (when the vaporiser is inoperative) and power-boosting during operation of the system. A duct connects gaseous hydrogen within the second tank to the ullage in the first tank in order maintain pressure in the first tank as liquid hydrogen within it is depleted, preventing cavitation of liquid hydrogen within the fuel pump.

A propulsion system comprises a propulsive hydrogen-burning gas turbine engine, a first tank storing liquid hydrogen with an ullage and a first fuel line including a fuel pump and a vaporiser, the first fuel line providing gaseous hydrogen to the engine during operation of the system. A second tank storing gaseous hydrogen is coupled by a second fuel line to the first fuel line at a position thereon between the vaporiser and the engine, providing for engine start-up (when the vaporiser is inoperative) and power-boosting during operation of the system. A duct connects gaseous hydrogen within the second tank to the ullage in the first tank in order maintain pressure in the first tank as liquid hydrogen within it is depleted, preventing cavitation of liquid hydrogen within the fuel pump.

The invention belongs to the technical field of aero-engine cooling, and particularly relates to an aero-engine lubricating oil and fuel oil collaborative cooling system which is characterized in that lubricating oil in an engine lubricating oil tank circularly flows through a lubricating oil system pipeline; the lubricating oil circulation path is sequentially connected in series with a lubricating oil pump, a fuel and lubricating oil radiator, an internal flow channel of an engine air inlet structure, an internal flow channel of a fan stator blade, a bearing cavity, a casing and a transmission accessory to form a closed loop; the fuel oil system comprises a fuel oil tank, a fuel oil pump and a fuel oil and lubricating oil radiator. Fuel oil is conveyed to the fuel oil and lubricating oil radiator through a fuel oil pipeline to be injected into an engine combustion chamber after exchanging heat with lubricating oil. The system is provided with a temperature closed-loop control module, the temperature of lubricating oil is monitored in real time through a temperature sensor arranged in a lubricating oil tank, a temperature signal is transmitted to an engine control unit through an engine cable, and a lubricating oil pump is driven to execute variable-frequency speed regulation to achieve dynamic regulation of the flow of the lubricating oil.

In another aspect, a method for fueling an aircraft, the method including storing liquified gas fuel using a fuel tank, wherein the fuel tank is configured to store liquified gas fuel, fueling an aircraft using a fuel line. Fueling the aircraft may additionally include the fuel tank with liquified gas fuel to a desired level, wherein a desired level comprises fuel for a plurality of flights plus reserves. Filling may also include removing the fuel line as a function of the desired level. The method may additionally include venting the fuel tank using a vent line in fluid connection to the fuel tank. The fuel tank may then be prepared for flight as a function of a desired level. Finally, the method includes flying a plurality of flights using the aircraft.

A hydrogen fuel system for a work machine is disclosed. The hydrogen fuel system comprises a hydrogen storage tank containing hydrogen, the hydrogen being at least one of a liquid hydrogen or a gaseous hydrogen; a hydrogen power unit configured to consume the hydrogen from the hydrogen storage tank, the hydrogen power unit including at least one of a plurality of fuel cells or a hydrogen combustion engine; a boil-off pressure relief valve in fluid communication with the hydrogen storage tank; and a tank pressure sensor in communication with the boil-off pressure relief valve. The boil-off pressure relief valve is configured to, when the tank pressure sensor detects a pressure inside the hydrogen storage tank that exceeds a boil-off pressure threshold, vent the gaseous hydrogen to a boil-off fuel line fluidly connected to the hydrogen power unit.

The utility model relates to the technical field of agricultural machinery, in particular to a rear frame fuel tank and a tractor. The rear frame fuel tank comprises a rear frame, a main fuel tank is formed, and the main fuel tank is provided with a first oil filling port and a first oil suction port; the auxiliary fuel tank is arranged on the side of the rear frame, the auxiliary fuel tank is provided with a second oil filling port, a ventilation pipeline and a fuel pipeline, the ventilation pipeline and the fuel pipeline are communicated with the main fuel tank, and at least one of the main fuel tank and the auxiliary fuel tank can supply oil; the fuel oil pipeline can be disconnected from the main fuel oil tank to form a second oil suction port for the auxiliary fuel oil tank to supply and convey fuel oil to the outside; when the fuel oil pipeline is communicated, fuel oil in the main fuel oil tank and the auxiliary fuel oil tank can be supplied outwards from the first oil suction port. According to the utility model, the main fuel tank and the auxiliary fuel tank are arranged, so that the requirement of a high-horsepower tractor for acting fuel for a long time can be met, and at least one of the main fuel tank and the auxiliary fuel tank can supply oil to meet different working conditions and the requirement for adjusting the weight of the whole tractor.

A second layer of physical protection against failure for a fuel line of a vehicle for use with high pressure and cryogenic fuels increases safety. The primary fuel line can be assembled from one or more components. The secondary protection is a single outer sleeve that includes a selectively permeable or impermeable membrane and may be reinforced. The sleeve and enclosed volume can also be used to protect against oxygen liquification in cryogenic applications. A means to detect failure of the primary fuel line and optional means to vent leaking fuel depend on the application. Clamp designs may be used to mount and clamp such assemblies in a vehicle structure.

A seaplane float frame apparatus with extra fuel storage, and a method of installing, comprising: 1) a middle section housing at least one auxiliary fuel storage tank; and 2) two opposing side panels affixed to the middle section, extending outward from about 45-60-degrees from the parallel, each of the two opposing side panels comprising a bottom flat edge fit-able to a float (e.g., carbon composite). The middle section further comprises a fuel pump and a fuel line attached to the auxiliary fuel storage tank(s) and to a main fuel tank within an airplane fuselage-engine. Electrical components enable the pilot, or automatedly as needed, to pump fuel from the frame's tanks. The two opposing side panels comprise triangular shaped cutouts to reduce the float frame's weight and drag, and a built-in steps, a bar, and non-skid coating on the floats to assist in climbing safely into / out of the cockpit.

A method for discharging water from a fuel cell system (100), wherein the fuel cell system (100) has at least one fuel cell stack (101), an air path (10) in fluid communication with a cathode (105) of the fuel cell stack (101), an exhaust line (12), and a fuel line (20) in fluid communication with an anode (103) of the fuel cell stack (101), wherein at least one controllable valve (46) is arranged in the air path (10) and / or the exhaust line (12). The at least one controllable valve (46) is controlled by a control unit (60) in order to generate pressure oscillations.

A fuel system for an engine comprising a source of liquid ammonia; a fuel injector; an ammonia fuel line extending between the source of liquid ammonia and fuel injector for transferring ammonia from the source of liquid ammonia to the fuel injector; an ammonia pump arranged in series in the ammonia fuel line; an ammonia cracker; an ammonia cracker line extending between the source of liquid ammonia and ammonia cracker for the transfer of ammonia from the source of liquid ammonia to the ammonia cracker; a cooling jacket arranged in series in the ammonia cracker line; and, a pressure reducing valve arranged in series in the ammonia cracker line between the source of liquid ammonia and the cooling jacket; the cooling jacket extending through or at least par ally surrounding the ammonia pump and being in thermal contact therewith.

In accordance with at least one aspect of this disclosure, a system includes a fuel line, an electrically driven fuel pump configured to supply fuel to a first fuel line branch and a second fuel line branch, and a selector valve disposed in the fuel line at a juncture of a first fuel line branch and a second fuel line branch configured to communicate the electrically driven fuel pump with the first fuel line branch or the second fuel line branch based on a position of the selector valve. In a first position, the selector valve is configured to fluidly connect the electrically driven fuel pump with the first fuel line branch to supply fuel to a combustor of the engine and drive a high pressure shaft at a first speed. In a second position, the selector valve is configured to fluidly connect the electrically driven fuel pump with the second fuel line branch to drive a hydraulic rotation unit configured to drive the high pressure spool of the engine at a second speed different from the first speed.

This invention belongs to the field of ramjet technology and provides a wide-speed range ramjet fuel supply system and method driven by a pyrolysis oil-gas turbine. The system comprises a fuel tank, a centrifugal pump, a motor, an oil-gas turbine, a battery, an electromagnetic control module, fuel lines, a pyrolysis fuel vapor line, a combustion chamber, and a regenerative cooling channel on the outer wall of the combustion chamber. Through the connection between the centrifugal pump, the regenerative cooling channel, and the oil-gas turbine, the system utilizes the cracking of hydrocarbon fuel into small-molecule pyrolysis kerosene vapor to drive the turbine rotor to produce work. The motor then assists in starting the ramjet, thereby resolving the power generation challenges of the ramjet mode and alleviating thermal protection issues.

The invention relates to a diagnostic method (100) for diagnosing the state of tank valves (203) in a tank system (200), the tank system (200) having a plurality of fuel tanks (201), each having a tank valve (203), and a fuel line arrangement (207) for guiding fuel out of the fuel tanks (201).

The invention discloses an intelligent control method for a multi-fuel-tank fuel system of an agricultural tractor, and relates to the technical field of agricultural machinery fuel control, and the method comprises the following steps: under the control of a processor, taking an ignition switch state as a trigger: obtaining a first environment temperature during power-on, and outputting a fuel pipeline switching valve opening / closing signal in combination with the fuel quantity of a low-grade fuel tank; pre-selecting an oil path; after starting, the heating electromagnetic valve is opened and closed according to the temperature of cooling liquid, and the high-grade fuel tank is switched back based on the temperature of fuel oil, so that heating and closed-loop management of an oil path are realized; and when the power is off, taking a second environment temperature, forcibly switching to a low-grade oil way when the temperature is less than or equal to 4 DEG C, operating for a set time, and then flameout, so that the system retains low-grade fuel oil. By automatically switching fuel oil and heating control, reliable starting and economical operation of the tractor in a low-temperature environment can be ensured, low-grade fuel oil is reserved in a pipeline after flameout, and difficulty in restarting is avoided.

The present invention relates to a system for mixing hydrogen into fuels, characterized in that it comprises a gas-in-liquid mixing valve which is supplied with gaseous hydrogen via a line originating from a hydrogen storage tank with a compressor controlled by an operating panel, wherein the outlet of the mixing valve is connected to the fuel line which supplies the boiler, engine, burner or the like.

Drive device (1) for driving a machine, in particular a commercial vehicle, with a motor unit (2) for generating mechanical energy, characterized by an energy unit (3) for providing electrical energy, an electrolyzer system (4) for producing a fuel, in particular hydrogen, wherein the electrolyzer system (4) is connected to the energy unit (3) for energy transmission and a fuel line (5) for conducting the fuel, wherein the fuel line (5) connects the electrolyzer system (4) to the engine unit (2).

A hydrogen fuel system for a work machine is disclosed. The hydrogen fuel system comprises a hydrogen storage tank containing hydrogen, the hydrogen being at least one of a liquid hydrogen or a gaseous hydrogen; a hydrogen power unit configured to consume the hydrogen from the hydrogen storage tank, the hydrogen power unit including at least one of a plurality of fuel cells or a hydrogen combustion engine; a boil-off pressure relief valve in fluid communication with the hydrogen storage tank; and a tank pressure sensor in communication with the boil-off pressure relief valve. The boil-off pressure relief valve is configured to, when the tank pressure sensor detects a pressure inside the hydrogen storage tank that exceeds a boil-off pressure threshold, vent the gaseous hydrogen to a boil-off fuel line fluidly connected to the hydrogen power unit.

The invention provides a self-adaptive starting method and system for a fire-fighting vehicle in a low-temperature environment, and the method comprises the steps: S1, obtaining real-time temperature data from the environment and each key part of the fire-fighting vehicle through a sensor array, judging whether the fire-fighting vehicle is in a low-temperature state or not through a threshold comparison method according to the collected temperature distribution, and obtaining a low-temperature activation signal; s3, if any element in the deviation matrix exceeds a preset deviation threshold value, integrating the elements of the deviation matrix to generate a power adjusting instruction, and obtaining a dynamic power output sequence; s4, a dynamic power output sequence is adopted to drive multiple heaters to conduct parallel heating on an engine cylinder body and a fuel oil pipeline, meanwhile, the temperature change rate in the heating process is monitored, and the heating balance degree is judged; and S7, acquiring a starting preparation signal from the vehicle control unit according to the coordination completion mark, releasing the starting sequence if the temperature coordination index reaches a preset index threshold value, and judging the response capability of the vehicle. According to the invention, the quick response capability of the vehicle in an extreme environment is obviously improved.

Aspects herein describe performing analysis of electromagnetic effects (EME) on a structure (e.g., a wing of an aircraft) to identify routes for a link that extends along a length of the structure. With metallic links, it is easier to identify safe regions since EME is typically limited to simply simulating the voltage along the fuel line when a harmful EM event occurs, e.g., a lightning strike. However, for non-metallic links, the system can also determine the energy along the link, which depends on the electric field, the voltage potential, and the properties of the link. The potential energy can determine whether, a hazardous EM event could occur. Thus, the aspects herein can apply to both metallic and non-metallic links. After determining the potential energy, the system can output a GUI that indicates to the designer safe zones for routing the link in the structure.

A system and method for fueling an aircraft using a plurality of fuel tanks are disclosed. The method includes conditioning a plurality of fuel tanks, wherein the plurality of fuel tanks includes at least a first fuel tank and at least a second fuel tank, fueling, using at least a fuel line, the aircraft, wherein fueling further includes filling the at least a first fuel tank with a first fuel and the at least a second fuel tank with a second fuel to a desired level, combining, using at least a fuel cell, the first fuel with oxygen to produce electricity, propelling, using at least a flight component, the aircraft, consuming the first fuel during a first flight mode of the aircraft and consuming the second fuel during a second flight mode of the aircraft.

The application relates to the technical field of aerospace equipment, in particular to a stretchable release mechanism for separating a lunar soil penetration projectile communication antenna, which comprises a main body, the main body comprising a first mounting surface and a second mounting surface, the first mounting surface being arranged obliquely to the second mounting surface; an antenna oscillator arranged on the first mounting surface and provided with a locking ring for locking the antenna oscillator; a super-elastic conductive member sleeved on the second mounting surface; and a fuel line release mechanism arranged on the super-elastic conductive member, one end of the fuel line release mechanism being connected with the locking ring and the other end being connected with one end of the second mounting surface away from the first mounting surface. The arrangement of the fuel line release mechanism avoids the risk of failure of the stretchable release mechanism for separating the lunar soil penetration projectile communication antenna.

The invention concerns a fuel injection nozzle (24.7) for a combustion chamber (24.1) of a gas turbine assembly (20). The fuel injection nozzle (24.7) comprises a central fuel duct (24.7.1) having a distal end provided with a fuel nozzle (24.7.3). The central fuel duct (24.7.1) is configured for feeding fuel from a proximal end of the fuel duct to the fuel nozzle (24.7.3) at the distal end of the fuel duct (24.7.1). The fuel injection nozzle (24.7) further comprises a fuel intake connector (24.7.4) and a fuel return connector (24.7.5) that both are connected to the proximal end of the fuel duct (24.7.1) for feeding pressurized fuel into the fuel duct and allowing the fuel to circulate in an external fuel line. The fuel injection nozzle (24.7) further comprises a coaxial air duct (24.7.2) coaxially surrounding the fuel duct (24.7.1) and being configured for providing that fuel exiting at the fuel nozzle (24.7.3) at the distal end of the fuel duct (24.7.1) is surrounded by an air stream that prevents the fuel from sticking to parts of the fuel injection nozzle (24.7). According to the invention, the fuel injection nozzle (24.7) is provided with a Venturi nozzle (24.7.6) formed at the distal end of the air duct (24.7.2) surrounding the fuel nozzle 24.7.3 of the fuel duct (24.7.1). The Venturi nozzle (24.7.6) has an inner diameter that varies over the length of the Venturi nozzle (24.7.6), i.e. in the longitudinal direction of the fuel injection nozzle, and that is larger at the beginning of the Venturi nozzle (24.7.6) and at the end of the Venturi nozzle (24.7.6) than in the middle of the Venturi nozzle (24.7.6).