515 results about "Fuel distribution" patented technology

An inerting system provides air with reduced oxygen content by flowing and directing air through an air separation module. Optimal working pressure for the air separation module is obtained with two compressors. A first compressor elevates air from the aircraft cabin to a second pressure. The second pressure is at an intermediate level below the working pressure of the air separation module. A second compressor elevates air from the second pressure to the working pressure. The second compressor is driven by air that is exhausted through a turbine. The pressure difference between air at the working pressure and air required by the fuel distribution system is used to power the turbine and drive the second compressor.

A throttle body fuel injection system and method that is arranged to easily replace four-barrel carburetors includes a throttle body assembly with four main bores, each with a throttle plate and an associated fuel injector. Each injector feeds fuel into a circular fuel distribution ring via a fuel injection conduit, which introduces pressurized fuel into the air stream. The fuel distribution rings and bores have profiles that avoid constrictions for to prevent low pressure zones according to the Venturi effect. Fuel is injected through downward-facing outlets at or near the bottom end of the rings. The fuel injection rings are two-piece, each formed of an insert pressed into an outer housing. The insert includes axial grooves intervaled about its exterior circumference of insert that are joined by a circumferential groove formed about the insert. The grooves are in fluid communication with a conduit that supplies fuel from a fuel injector.

Various methods and systems are provided for regenerating an exhaust gas recirculation cooler. One example method includes, initiating an EGR cooler regeneration mode, wherein the EGR cooler regeneration mode comprises changing a fuel distribution of a donor cylinder group relative to a non-donor cylinder group of an engine, and increasing at least one of engine speed or load of the engine.

A multiple adiabatic bed reforming apparatus and process are disclosed in which stage-wise combustion, in combination with multiple reforming chambers with catalyst, utilize co-flow and cross-flow under laminar flow conditions, to provide a reformer suitable for smaller production situations as well as large scale production. A passive stage by stage fuel distribution network suitable for low pressure fuel is incorporated and the resistances in successive fuel distribution lines control the amount of fuel delivered to each combustion stage. The fuel distribution system allows relatively constant fuel and air flow during turn up or turn down conditions. High efficiency is achieved by capturing heat from reforming syngas product to preheat gases before entering the reformer. Conditions that would produce unwanted coking or metal dusting are also eliminated or localized to locations within the apparatus outside the heat exchangers, but which locations can be cost effectively protected. Also, a chemical reactor is disclosed and which has a core composed of a stack of metal plates that are diffusion bonded in face-to-face relationship. A plurality of reaction zones are located within the core, as are a plurality of catalyst receiving zones, and both the reaction zones and the catalyst receiving zones are defined by respective aligned apertures in the plates. First and second channel arrangements are provided in the plates for transporting first and second reactants to reaction zones. Portions of the first channel arrangement that interconnect the reaction zones are formed as heat exchange channels. A third channel arrangement is provided in the plates for transporting a third reactant to catalyst receiving zones. Portions of the third channel arrangement are formed as heat exchange channels in proximity to the heat exchange channels of the first channel arrangement.

A nozzle has combustion air passages extending from a first, upstream end to a second, downstream end. A fuel distribution manifold is associated with the first, upstream end of the nozzle. Combustion air passages correspond to, and align with the air passages in the nozzle. Fuel distribution grooves are formed in one end of the fuel distribution manifold disk and extend from a central opening to the air passages. A fuel circuit cover closes the fuel distribution grooves to define fuel passages that extend from the central opening to the combustion air passages. A fuel supply conduit communicates with the central opening and the fuel passages for delivery of fuel to the combustion air in the air passages.

A portable fuel cell stack is provided in which the number of components is reduced by reducing the number of flow field plates, cell performance is improved by reducing the number of contact portions to thereby lower internal resistance, and fuel is supplied from the center of an end plate directly to a fuel distribution manifold. The portable fuel cell stack includes two end plates, a plurality of unit cells positioned between the two end plates, a fuel distribution manifold positioned in the center of the unit cell for fuel supply thereto, a tie bolt passed through the centers of the fuel manifold and the unit cell for integration of these members, and fixing nuts threaded to both ends of the tie bolt for integrally clamping the plurality of unit cells together between the end plates via an O-ring, etc. The unit cell includes a polymer electrolyte membrane, an oxygen electrode and a fuel electrode installed on both sides of the polymer electrolyte membrane, a flow field plate adjacent to the oxygen electrode side, and a separator plate on the outside of the flow field plate adjacent in contact therewith and another separator plate on the outside of the fuel electrode side in contact therewith. One of the fixing nuts has a fuel supply port connecting to the fuel distribution manifold.

A system for providing fuel to a combustor of a gas turbine includes an annular fuel distribution manifold that at least partially defines a fuel plenum. The fuel distribution manifold includes a forward end axially separated from an aft end, a flange that extends radially outward and circumferentially around the forward end and an annular support ring that extends downstream from the flange. A LLI assembly extends downstream from the fuel distribution manifold. The LLI assembly includes a unibody liner that at least partially defines a primary combustion zone and a secondary combustion zone within the combustor. A LLI injector extends substantially radially through the unibody liner and provides for fluid communication through the unibody liner into the secondary combustion zone. A fluid conduit in fluid communication with the fuel plenum extends between the LLI injector and the fuel distribution manifold.

A fuel distribution manifold system for a gas turbine engine is disclosed that includes a plurality of interconnected manifold segments, each manifold segment extending between a pair of fittings, each manifold segment including at least one fuel transfer tube and a sealing tube that surrounds the at least one fuel transfer tube, wherein opposed end portions of the at least one fuel transfer tube are dynamically connected to the fittings and opposed end portions of the sealing tube are statically connected to the fittings.

A fuel separator is disclosed having a hollow interior in which a tubular coiled heat exchanger is positioned to receive a coolant liquid therethrough. Fuel is fed into the chamber through a fuel inlet and pumped out of the chamber by a high pressure pump into the fuel distribution system of an internal combustion engine. Heated excess fuel from the fuel distribution system of an internal combustion engine is returned to the chamber through a fuel return inlet at the bottom of the chamber and the heated fuel passes upwardly through the coolant coil thereby cooling the heated return fuel. Fuel vapor that is not condensed as a result of cooling can escape from the chamber through a float needle valve at the top of the chamber. A pressure relief valve is also provided at the top of the chamber to allow the vapor to escape when a predetermined internal pressure is reached.

The present disclosure provides a tuning system for tuning the operation of a gas turbine. The system comprises operational turbine controls for controlling operational control elements of the turbine, including at least one of turbine fuel distribution or the fuel temperature. The system also has a tuning controller communicating with the turbine controls. The tuning controller is configured to tune the operation of the turbine in accordance with the following steps: receiving operational data about the turbine, providing a hierarchy of tuning issues, determining whether sensed operational data is within predetermined operational limits and producing one or more indicators. If the operational data is not within predetermined operational limits, the tuning controller will rank the one or more indicators to determine dominant tuning concern, and tune the operation of the turbine based on dominant tuning concern. Also provided herein are a method and computer readable medium for tuning.

A system and method for controlling multiple fuel injections during a single combustion cycle for a multiple cylinder internal combustion engine having a common rail fuel distribution system determine the beginning of injection for the pilot and main injections based on crankshaft position while post injections are based on the main injection timing and an injector turn off delay determined using actual rail pressure. A rail pressure setpoint is determined based on current engine operating conditions including one or more fluid temperatures and current operating mode to provide more accurate injection control.

A fuel injector assembly for use in a turbine engine having a combustion section and a turbine section downstream from the combustion section. The fuel injector assembly includes a flow sleeve defining a pre-mixing passage of the combustion section and including a sleeve wall having a forward end proximate to a cover plate of the combustion section and an opposed aft end. An annular cavity in fluid communication with a source of fuel is formed in the sleeve wall adjacent the aft end. A fuel dispensing structure is associated with the cavity and includes at least one fuel distribution aperture for distributing fuel from the cavity to the pre-mixing passage.

A system and method for the rapid configuration and connection of a backup controller in a distributed data network such as an automated fuel distribution network. Each service-station site in the network has a site controller that supervises operations of the site components, such as the fuel dispenser and credit-card reader, communicating with them through an on-site router, or hub. The fuel-distribution site also communicates with the central network controller through the same hub. In the event of a site-controller outage, one of several spare controllers, usually co-located with the network controller, is loaded and configured to function as the site controller. It is then placed in communication with the site components via a data-network connection, such as through the Internet. The hub switches communications protocols from serial data to packets suitable for Internet communications.

A fuel distribution tube for a direct injection fuel rail assembly includes an elongate cylindrical conduit, a plurality of first scalloped features that receive fuel injector sockets formed in the conduit, and plurality of second scalloped features that receive mounting bosses formed in the conduit. The scalloped features are designed to closely match the outer radii of the injector sockets and the mounting bosses. The scalloped features provide necessary dimensional control to injector sockets and mounting bosses and fuel passage from the fuel distribution tube to the fuel injector sockets. The scalloped features enable a leak test of the braze joints of the fuel rail assembly. By providing a direct injection fuel rail assembly that includes the fuel distribution tube having scalloped features formed in the conduit, optimization of true position location of fuel injector sockets and improved braze joints are enabled.

Any specific member for fixation is omitted from a fuel injection device so that number of parts is reduced and the fuel injection device is constructed at a reasonable cost. The fuel injection device for use in an internal combustion engine is provided with a fuel distribution pipe 1, plural connecting pipe members 4, and plural fuel injection valves 2, and each of the fuel injection valves 2 is inserted into a connecting pipe member 4. A band-shaped protrusion 7 extends in the radial direction from a flange portion of the connecting pipe member 4 and further extends in parallel to the axis of the fuel injection valve 2. The band-shaped protrusion 7 is provided with a fitting hole 8, and each fuel injection valve 2 is provided with a protrusion 9 fitted into the fitting hole 8.

An apparatus to deliver a fuel into a chamber is provided. In one embodiment, the apparatus includes a fuel inlet and a substantially circular fuel distribution canal communicating with the fuel inlet. A biasing element is coupled to the substantially circular fuel distribution canal, with the biasing element having a plurality of slots arranged to non-uniformly dispense the fuel into the chamber. Another embodiment includes a flange positioned in the substantially circular fuel canal, with the flange structured to perturb a fuel passing into the chamber. This Abstract is provided for the sole purpose of complying with the Abstract requirement rules that allow a reader to quickly ascertain the subject matter of the disclosure contained herein. This Abstract is submitted with the explicit understanding that it will not be used to interpret or to limit the scope or the meaning of the claims.

A fuel control device includes a combustion temperature estimation value calculation unit that calculates a temperature estimation value when a mixture of fuel and inflow air is burned using an atmospheric condition, an opening degree command value of a valve that controls the amount of air that is mixed with the fuel and burned, and an output prediction value calculated on the basis of a fuel control signal command value used for calculation of a total fuel flow rate flowing through a plurality of fuel supply systems, a fuel distribution command value calculation unit that calculates a fuel distribution command value indicating a distribution of fuel output from the fuel supply systems based on the temperature estimation value, and outputs the fuel distribution command value, and a valve opening degree calculation unit that calculates each valve opening degree of a fuel flow rate control valve of the fuel supply systems.

A combustion module for a combustor of a gas turbine includes an annular fuel distribution manifold disposed at an upstream end of the combustion module. The fuel distribution manifold includes an annular support sleeve having an inner surface. The combustion module further includes a fuel injection assembly having an annular combustion liner that extends downstream from the fuel distribution manifold and that terminates at an aft frame, and an annular flow sleeve that circumferentially surrounds the combustion liner. The flow sleeve extends downstream from the fuel distribution manifold and terminates at the aft frame. The flow sleeve extends continuously between the support sleeve and the aft frame. A forward portion of the flow sleeve is positioned concentrically within the support sleeve where the forward portion is slidingly engaged with the inner surface of the support sleeve.