Abstract: There are provided methods, systems and processes for the utilization of microbial and related genetic information for use in the exploration, determination, production and recovery of natural resources, including energy sources, and the monitoring, control and analysis of processes and activities.

Abstract: A cutting head for a mining machine includes a drum, a vane, and a cutting bit assembly positioned adjacent a surface of the vane. The drum includes a first end, a second end, and an outer surface, and the drum is rotatable about a drum axis. The vane is coupled to the outer surface of the drum and protrudes radially away from the drum axis. In some aspects, the vane includes a planar member extending at least partially around the drum axis and at least partially between the first end of the drum and the second end of the drum. In some aspects, the drum includes a plurality of planar walls extending between the first end and the second end.

Abstract: A method for expanding a mature brine well cavern includes determining the position and depth of an insoluble deposit and the volume and depth of a salt formation in the well. An outer drill casing is used to penetrate the soluble deposit and the salt underneath the insoluble deposit. The method further includes drilling continuously through the insoluble deposit and drilling into the salt formation.

Abstract: A rotor assembly for a gas turbine engine includes a turbine shaft disposed about a longitudinal axis, a first rotor and a second rotor configured for rotation about the longitudinal axis, and an intermediate shaft positioned radially between the turbine shaft and the second rotor. The second rotor is mounted to and axially adjacent the first rotor. The intermediate shaft is mounted to the turbine shaft on an inner radial side of the intermediate shaft. The intermediate shaft is mounted to the second rotor on an outer radial side of the intermediate shaft.

Abstract: A tie rod assembly structure, a gas turbine having the same, and a method of assembling tie rod are provided. The tie rod assembly structure includes a tie rod on which a plurality of rotor disks are mounted, a bearing support shaft mounted to the tie rod to support the rotor disks and on which a bearing is mounted, a first nut mounted on the tie rod on one side of the bearing support shaft, and a second nut that is fastened to the first nut to tension the tie rod and then is in close contact with the bearing support shaft to support the bearing support shaft.

Abstract: A blade damage evaluation apparatus includes: a registration unit for design information of a turbine and maintenance information; an acquisition processor for detection data of sensors; a first discrimination processor for first facility states of the turbine at a plurality of past time points; a classification processor for classes Cn of a plurality of first facility states; a first determination processor for first operating state values of the turbine; another registration unit for first damage rates at past time points; a setting processor of a characteristic function for each of the classes Cn; a second discrimination processor for a second facility state of the turbine at the current time point; a second determination processor for a second operating state value of the turbine at the current time point; and an analyzer for a second damage rate at the current time point.

Abstract: A turbomachine defines an axial direction, a radial direction perpendicular to the axial direction, and a circumferential direction extending concentrically around the axial direction. The turbomachine includes a nozzle having an inner platform, an outer platform, and an airfoil. The airfoil includes a leading edge, a trailing edge downstream of the leading edge, a pressure side surface, and a suction side surface opposite the pressure side surface. The trailing edge is orthogonal with the outer platform in an axial-radial plane and the trailing edge is oblique to the inner platform in the axial-radial plane.

Abstract: An airfoil member having a root end, a tip end, a leading edge, and a trailing edge, the airfoil member including an upper skin; a lower skin; and a support network having a plurality of interconnected support members in a lattice arrangement and/or a reticulated arrangement, the support network being configured to provide tailored characteristics of the airfoil member. Also provided are methods and systems for repairing an airfoil member.

Abstract: A rotor blade for a turbomachine is provided. The rotor blade includes a platform, an airfoil extending from the platform, and a cooling circuit extending within the platform and the airfoil. The cooling circuit includes a plurality of cooling passages defined by a plurality of ribs. The plurality of ribs includes an offset rib.

Abstract: Airfoil for gas turbine engines are described. The airfoils have internal walls and internal cavities. A leading edge cavity is defined within the airfoil body along a leading edge and a leading edge feed cavity is arranged aft of the leading edge cavity. A bent leading edge rib is arranged between the leading edge cavity and the leading edge feed cavity. A main body cavity is arranged aft of the leading edge feed cavity and defined at least in part by two interior ribs that define a part of the leading edge feed cavity. The main body cavity is fluidly connected to the leading edge feed cavity by an interior fluid connection through the intersection of the two interior ribs. A shield cavity is arranged to thermally shield the leading edge feed cavity from heat pickup along the suction side of the airfoil body.

Abstract: An airfoil includes a root and a tip, which define a span of the airfoil therebetween. The airfoil also includes a leading edge and a trailing edge downstream of the leading edge along a flow direction. The leading edge and the trailing edge each extend across the span of the airfoil from the root to the tip. The airfoil further includes a pressure side surface and a suction side surface. The airfoil also includes a thermal barrier coating on the pressure side surface and the suction side surface. The thermal barrier coating includes a base layer and a top coat. A thickness of the base layer varies across each of the pressure side surface and the suction side surface with a maximum thickness of the base layer at the leading edge.

Abstract: A structure for assembling turbine blade seals, a gas turbine including the same, and a method of assembling turbine blade seals are provided. The structure for assembling turbine blade seals includes a turbine blade including an airfoil, a platform, and a root, a turbine rotor disk to which the root of the turbine blade is mounted, a seal plate mounted between the platform and one side of the turbine rotor disk to seal a cooling channel defined within the root and the platform, an insertion pin inserted through the turbine rotor disk and the seal plate to fix the seal plate to the turbine rotor disk, and a retainer configured to fix the insertion pin and to prevent the insertion pin from falling out.

Abstract: A turbine wheel consists of a first shroud component and a second bladed disc component. The shroud component comprises a shroud structure, a hub structure and a spoke formed integrally therewith and extending between the shroud structure and the hub structure. The bladed disc component comprises a hub member having inner and outer rims, turbine blades disposed on the outer rim, and at least one receiving zone for receiving the spoke, said at least one receiving zone extending radially between the inner and outer rims. The shroud component and the bladed disc component are connected and thus provide the turbine wheel with a shrouded portion. A shrouded turbine wheel can therefore be conveniently assembled starting from at least two components. Further, these components have simplified geometries for easy manufacture, for example using a casting technique, while the overall mechanical performance of the turbine is preserved or improved.

Abstract: A compressor section includes a compressor casing that has an upper casing portion coupled to a lower casing portion such that a split-line is defined between the upper casing portion and the lower casing portion. A split-line stator vane assembly includes a first split-line stator vane that has a first shank with a first platform portion and a first mounting portion extends radially outward of the first platform portion. A first airfoil extends radially inward of the platform portion. The first platform portion includes a protrusion that extends circumferentially beyond the split-line. A second split-line stator vane having second shank with a second platform portion and a second mounting portion extends radially outward of the second platform portion. A second airfoil extends radially inward of the second platform portion. The second platform portion includes a recess that extends circumferentially away from the split-line.

Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment and a carrier. The shroud segment extends circumferentially partway around an axis to define a gas path boundary of the turbine shroud assembly. The carrier is configured to support the shroud segment in position radially relative to the axis.

Abstract: To provide an axial flow turbine that can reduce circumferential pressure differences to reduce loss. The axial flow turbine includes: stator blades arrayed in the circumferential direction; and a diaphragm inner ring having an outer circumferential surface that interconnects the stator blades on their inner-circumference side and constitutes a wall surface of a main flow path. The outer circumferential surface of the diaphragm inner ring has depressed portions. Each depressed portion is formed in an area that is on the downstream side of a throat where the distance between a suction surface of one stator blade of a pair of adjacent blades and a pressure surface of other stator blade of the pair of adjacent blades becomes the shortest, and that lies in the circumferential direction within a range of a throat position on the suction surface of the one stator blade to a downstream edge position of the one stator blade.

Abstract: The invention concerns a gas turbine having a picture frame, a first vane, and a sealing arrangement to seal a gap between the picture frame and the first vane, the sealing arrangement including two seals arranged in series between the picture frame and the first vane. In exemplary embodiments, one of the seals is a honeycomb seal, a dogbone seal, a hula seal or a piston seal and the other seal is a honeycomb seal, a dogbone seal, a hula seal or a piston seal. A method of supplying cooling fluid to the gap between the picture frame and the first vane is also disclosed.

Abstract: A rotating machine includes a casing having a hollow shape; a rotator rotatably supported in the casing; a stator blade fixed to an inner peripheral portion of the casing; a rotor blade fixed to an outer peripheral portion of the rotator while being displaced from the stator blade in an axial direction of the rotator; a sealing device disposed between the inner peripheral portion of the casing and a tip of the rotor blade; a swirling flow generation chamber provided along a circumferential direction of the rotator on a downstream side of the sealing device in the casing in a fluid flow direction; and guiding members provided at predetermined intervals in the swirling flow generation chamber in the circumferential direction of the rotator. The guiding members each include a first guiding surface that is inclined in the circumferential direction with respect to the axial direction of the rotator.

Abstract: A discharge grille of an intermediate casing of a turbomachine includes a peripheral edge and a seal mounted on the peripheral edge via an attachment system, the seal ensuring the sealing between a first turbomachine member and a second member of the turbomachine, and surrounding the discharge grille of the intermediate casing, the seal having a U-shaped cross section and includes a base plate configured to bear against the first member, a sealing lip configured to bear against the second member through deformation of the sealing lip to ensure air tightness and fire proofing through contact.

Abstract: A system for feeding operating gas to a drive (1) of a motor vehicle, including an atmosphere-side suction inlet (2a) for air under atmospheric pressure, and a feed line (2) for the operating gas to the drive (1) under an operating pressure, the operating gas which is conducted to the drive comprising at least part of the air which is sucked in, at least part of the operating gas being conducted through a turbomachine (3) upstream of the drive (1) in a first operating type, the turbomachine (3) comprising an electric generator (4), and the turbomachine (3) being operated in a second operating type as a compressor for the operating gas, an actuable valve arrangement (5) being provided, at least part of the air which is sucked in being conducted in a turbine direction (T) through the turbomachine (3) in a first position of the valve arrangement (5), and at least part of the air which is sucked in being conducted in a reversed compressor direction (V) through the turbomachine (3) in a second position of the valv

Abstract: A method of controlling a gas turbine engine includes the steps of: detecting a shaft break event in a shaft connecting a compressor of the gas turbine engine to a turbine of the gas turbine engine; and in response to this detection, activating a shaft break mitigation system which introduces a fluid into a gas flow of the gas turbine engine downstream of the turbine, or increases an amount of a fluid being provided into the gas flow of the gas turbine engine downstream of the turbine, whereby the fluid reduces an effective area of a nozzle for the gas flow so as to reduce the mass flow rate of the gas flow through the turbine.

Abstract: An exhaust gas turbocharger having a hydrodynamic plain bearing or a hydrodynamic plain bearing, comprising a rotor (10) and a counter-bearing part (50) assigned to the rotor (10), wherein a rotor bearing surface (17.1, 17.2, 17.3) of the rotor (10) and a counter-surface of the counter-bearing part (50) face each other to form a hydrodynamic plain bearing, wherein the rotor bearing surface and/or the counterface, when cut along and through the axis of rotation (R) in sectional view, form(s) a continuous bearing contour forming at least two contour sections (44.1 to 44.3; 53.1 to 53.3) to provide hydrodynamic load capacities in both radial and axial directions, and wherein the counter-bearing part (50) is mounted in a bearing housing (60) or housing part.

Abstract: A turbine exhaust case (TEC) has an outer case and an inner case structurally interconnected by a plurality of circumferentially spaced-apart struts. At least one of the struts has an airfoil body with a hollow core. The airfoil body has opposed pressure and suction sides extending chordwise from a leading edge to a trailing edge and spanwise from a radially inner end to a radially outer end. The radially inner end of the strut has a strut wall extension that extends through the inner case to a location radially inward of the inner case relative to the central axis.

Abstract: A radially flexible connection joint for a gas turbine engine includes an exhaust manifold flange operatively coupling an exhaust cylinder to an exhaust manifold of the gas turbine engine. The exhaust cylinder includes a cylindrical flange that extends radially outwardly from a rotation axis of the gas turbine. The cylindrical flange defines a downstream axial face. The exhaust manifold is positioned downstream from the exhaust cylinder. The exhaust manifold includes an upstream edge. The exhaust cylinder and the exhaust manifold are substantially coaxial with the rotation axis of the gas turbine. The exhaust manifold flange has a bellows portion that extends radially between the cylindrical flange of the exhaust cylinder and the upstream edge of the exhaust manifold. The bellows portion permits relative radial motion of the exhaust cylinder and the exhaust manifold.

Abstract: A gas turbine system includes a compressor section, a turbine section, a combustor section. The combustor section is in fluid communication with a fuel supply via a fuel supply line. The water circuit includes a first water line extending between a first feed water supply line and a return water line. The gas turbine system further includes an extraction-air line that extends between an inlet port on the compressor section and an outlet port on the turbine section. A first heat exchanger thermally couples the first water line to the extraction-air line for transferring heat from a flow of extraction-air within the extraction-air line to a flow of water within the water circuit. A second heat exchanger thermally couples the first water line to the fuel supply line for transferring heat from the flow of water within the water circuit to a flow of fuel within the fuel supply line.

Abstract: A camshaft adjuster is produced that includes a stator and a rotor, which is rotatable relative to the stator, wherein the stator and the rotor are produced with first planar surfaces on a first end face and with second planar surfaces on a second end face, which is formed to be opposite the first end face when viewed in an axial direction and wherein the rotor and/or the stator is or are produced according to a powder-metallurgical method, The first planar surfaces and the second planar surfaces of the stator and the rotor are ground or finished, and the lateral surface of the stator and the lateral surface of the rotor are left uncalibrated.

Abstract: A cylinder head for an internal combustion engine includes a casting and plug. The casting defines a first channel, a second channel, and a bore extending inward from an exterior surface of the casting. The first channel intersects a central portion of the bore. The second channel intersects an opposing end of the bore relative to the exterior surface. The plug is disposed within the bore. The plug has a distal end that engages the casting along the opposing end of the bore via a slip-fit engagement, a proximal end that engages the casting within the bore proximal to the exterior surface via a fixed engagement, and an intermediate portion that is spaced apart from the casting along the central portion of the bore. The plug defines an internal channel that establishes fluid communication between the first and second channels.

Abstract: Systems and methods are provided for a combined spark arrestor and muffler assembly. In one example, a system may include a combined housing, the combined housing including a spark arrestor portion including a plurality of stator fins, and a muffler portion including acoustic packing, the muffler portion fluidically coupled to the spark arrestor portion via a first sliding joint and a second sliding joint. In this way, a single component of a vehicle exhaust system may reduce sparks and/or carbon deposits in exhaust gas, while also reducing exhaust noise.

Abstract: A method for operating an exhaust gas burner (3) downstream of an internal combustion engine (1) and upstream of an exhaust gas catalytic converter (4), comprising controlling an ignition device (12) of the exhaust gas burner (3) during a predeterminable preheating phase without supplying fuel (11) to the exhaust gas burner (3) during the preheating phase and, after completion of the preheating phase, supplying fuel (11) to the exhaust gas burner (3) and burning the supplied fuel (11) in the exhaust gas burner (3). A processor unit and a computer program product for carrying out such a method are furthermore proposed.

Abstract: An exhaust gas treatment system includes an exhaust gas pathway configured to receive exhaust gas from an internal combustion engine. The exhaust gas treatment system further includes a treatment element configured to reduce an emissions component of the exhaust gas, and a sample collector positioned within the exhaust gas pathway downstream of the treatment element. The sample collector includes a plurality of inlet openings spaced about a periphery of the exhaust gas pathway and configured to receive a sample of exhaust gas from the exhaust gas pathway, and an outlet in fluid communication with the plurality of inlet openings. A sensor located at the outlet of the sample collector is configured to measure a characteristic of the sample.

Abstract: A Diesel Emissions Fluid (DEF) Thawing arrangement is provided for use with a vehicle having an engine, an Engine Control Module (ECM), an exhaust system, and an SCR catalytic device. A DEF injection system is connected to the exhaust system and to the ECM. A DEF tank is connected to the DEF injection system. An exhaust pipe branch is connected to the exhaust system. A heat exchanging apparatus is connected to the exhaust pipe branch and is configured to exchange heat from exhaust gas within the exhaust pipe branch to the DEF in the DEF tank. The heat exchanging apparatus may be an exhaust gas to DEF heat exchanger located at least partially within the DEF tank, or may be an exhaust gas to coolant heat exchanger connected to an engine coolant circuit and a coolant to DEF heat exchanger located at least partially within the DEF tank.

Abstract: Engine systems and methods use a dual air injection approach to control exhaust reactions and to maintain temperatures below a maximum limit of exhaust system components during engine enrichment operation conditions. Dual air injectors are disposed in the exhaust system with one upstream from, and another downstream from, the catalytic converter. Providing air injection before and/or after the converter helps convert all HC, CO, and PM emissions while keeping the catalyst temperature below the catalyst protection temperature limit. Air injection quantity may be controlled and diagnosed by monitoring the temperatures before and after the catalytic converter. The catalytic converter may be a three-way catalytic converter for lower cost or a downstream two-way catalytic converter may be added if further emission reduction is necessary.

Abstract: A heat recovery device includes: a honeycomb structure including an outer peripheral wall having at least one outer peripheral surface, and partition walls arranged on an inner side of the outer peripheral wall, the partition walls defining a plurality of cells each extending from a first end face to a second end face to form a flow path for a first fluid; a thermoelectric conversion element arranged to face the outer peripheral surface of the outer peripheral wall; a cylindrical member that circumferentially covers the honeycomb structure in which the thermoelectric conversion element is arranged; a casing arranged at an interval so as to form a flow path for a second fluid, the casing being arrange on a radially outer side of the cylindrical member; and a pressing member being configured to press the cylindrical member against the thermoelectric conversion element. The cylindrical member has one or more slit portions.

Abstract: A catalytic converter system having oxygen storage materials is disclosed and methods for determining whether to reactivate oxygen storage materials and monitoring failure events of the oxygen storage materials are also disclosed.

Abstract: A vehicle that can cool an ignition coil is provided. The vehicle has an engine having a cylinder head and an ignition coil with a first end exposed from the cylinder head, a CVT that varies and outputs rotary power from the engine, and an exhaust duct having a first exhaust port for exhausting a gas within a CVT case to outside of the CVT case, and a second exhaust port for exhausting a part of the gas flowing to the first exhaust port to outside of the CVT case, wherein the second exhaust port is provided for exhausting the gas within the CVT case to at least a part of the first end of the ignition coil.

Abstract: A support assembly for supporting an upright engine exhaust pipe on an exterior wall of a truck cab at a location below an outlet of the exhaust pipe. The support assembly allows limited cab motion relative to the exhaust pipe.

Abstract: A system includes an engine defining a water jacket fluidly coupled to a heat exchanger. An exhaust manifold defines an exhaust manifold cooling passage. A pump is fluidly coupled to the water jacket, and to each of the heat exchanger and the exhaust manifold cooling passage. An engine cooling circuit includes the water jacket, the heat exchanger, and the pump. An exhaust cooling circuit is selectively fluidly coupled to the engine cooling circuit. The exhaust cooling circuit includes the water jacket, the exhaust manifold cooling passage, and the pump. A control valve includes an inlet fluidly coupled to a first portion of the water jacket. A first outlet is fluidly coupled to a second portion of the water jacket. A second outlet is fluidly coupled to the exhaust cooling circuit. The control valve is structured to selectively control flow of coolant fluid through the second outlet.

Abstract: A deaeration valve includes a housing and a ball in fluid communication with housing. The ball can include a body, a seat defining a bleed passage therein, and a deaeration pin slidably disposed within the bleed passage. Further, the deaeration pin may include a head, a retention feature, and a shaft positioned between the head and the retention feature.

Abstract: An engine cooling system is provided, which includes a water jacket through which coolant flows, a heat exchanger that cools the coolant, a first bypass passage that bypasses the heat exchanger and recirculates the coolant to the water jacket, a radiator passage that recirculates the coolant to the water jacket via the heat exchanger, and a flow control device that is installed at a location where a coolant passage branches into the first bypass passage and the radiator passage and performs a water flow control to adjust a coolant amount flowing into the water jacket by adjusting a coolant amount flowing through the first bypass passage. A thermally-actuated valve connected with the radiator passage via a second bypass passage is provided to the first bypass passage, and when this valve opens, the coolant flowing through the first bypass passage flows into the radiator passage through the second bypass passage.

Abstract: An intake system of an engine mounted on a vehicle where a cabin is air-conditioned by an air conditioner, is provided. A heat exchanger of an evaporator of the air conditioner is divided into a first heat exchanger and a second heat exchanger that are mutually independent, and an air passage includes a first division passage and a second division passage. The intake system cools intake air utilizing a part of the air conditioner, and includes a connecting passage that guides first air cooled by passing through the first heat exchanger, a passage switch, and a controller. When the controller determines that a cooling demand for the intake air exists, it controls the first air to flow into an intake passage through the connecting passage, and when the controller determines that there is no cooling demand, it controls the first air to flow into the first division passage.

Abstract: A straddled vehicle having an engine unit supported by a vehicle body frame. The engine unit includes an engine body, a turbocharger, and an exhaust device. The exhaust device includes an exhaust pipe and a muffler that are connected to each other to form a portion of an exhaust passage, to allow the exhaust gas passed through the turbocharger to pass therethrough, and a first catalyst and a second catalyst that are arranged in this order along a direction in which the exhaust gas flows through the exhaust pipe. The exhaust pipe has an upstream end thereof connected to the turbocharger, a downstream end thereof connected to the muffler, and a corner section that is bent in at least a part thereof between a downstream end of the first catalyst and an upstream end of the second catalyst, the catalysts not being arranged in the corner section.

Abstract: Turbo or super charged intake tract diverter valve system, upstream of a throttle valve, includes a closure means (10) for a diversion aperture (4.1) in the intake tract (3) to vent pressurised gases within to a bypass path or atmosphere; the closure means having a transfer aperture (12) facilitating a net force due to a pressure differential on its opposite sides of the closure means (10) so as to close or keep closed the diversion aperture (4.1). When gas pressure on opposite sides of the closure means is equal, and when an upstream side (10.1) of the closure means (10) has a pressure greater than a downstream side (5.1), then it will open the diversion aperture (4.1). An actuation means opens a control aperture (6) to create the necessary pressure differential on the closure means (10) to thereby cause same to open the diversion aperture (4.1).

Abstract: In a rotary electric machine housing, a first bearing and a second bearing are provided for supporting a rotating shaft. A lubricating oil is supplied to the first bearing and the second bearing. Further, a gas is supplied to the first bearing and the second bearing. The lubricating oil and the gas are recovered by a single recovery device.

Abstract: Power generation systems are described. The systems include a shaft, a compressor operably coupled to a first end of the shaft, a turbine operably coupled to a second end of the shaft, a generator operably coupled to the shaft between the compressor and the turbine, and a working fluid arranged in a closed-loop flow path that flows through each of the compressor and the turbine to drive rotation of the shaft. The shaft includes an internal fluid conduit configured to receive a portion of the working fluid at one of the first end and the second end and convey the portion of the working fluid through the generator to the other of the first end and the second end, wherein the portion of the working fluid is rejoined with a primary flow path of the working fluid.

Abstract: A method for operating a pumped thermal energy storage (“PTES”) system includes circulating a working fluid through a working fluid circuit, the working fluid having a mass flow rate and a specific heat capacity and balancing a product of the mass and the specific heat capacity of the working fluid on a high-pressure side of a recuperator and a low side of the recuperator as the working fluid circulates through the working fluid circuit. The PTES system includes a bypass in the working fluid circuit by which a first portion of the working fluid bypasses the high-pressure side of the recuperator while a second portion of the working fluid circulates through the high-pressure side of the recuperator.

Abstract: A deflecting device for protecting a jet engine of an aircraft from damage caused by a bird strike. The bird strike deflection device attaches to an opening in the front of a cowling of the jet engine to shield an engine air intake from ingesting a bird that would otherwise damage the engine. A conically shaped screening portion having an open mesh pattern is attached to the cowling in a convex orientation. A perimeter of the screening portion terminates in a rim sized to fit the engine intake opening in the cowling. The rim may be directly attached to the cowling or an attachment flange may connect the rim to the cowling. The deflecting device may be completely removable from, hingedly attached to, or integrated directly into the cowling.

Abstract: An oil pumping system for use with a gas turbine engine includes an electric machine, an oil pump assembly, and a variable frequency drive controller. The variable frequency drive is connected with the electric machine and the oil pump assembly. The variable frequency drive controller is programmed to control a torque and speed of the pump motor independent of the gas turbine engine speed so that a flow of oil moved by the oil pump assembly is controlled to cool or lubricate components of the gas turbine engine independent of the gas turbine engine speed.

Abstract: Fuel distribution manifolds and combustors are provided. A fuel distribution manifold includes a main body and a fuel circuit that is defined within the main body. The fuel circuit includes an inlet section extending generally axially from an inlet to a first branch section and a second branch section. The first branch section and the second branch section diverge circumferentially away from each other as they extend axially from the inlet section to a respective first outlet and a respective second outlet.

Abstract: A power generation system includes a combustion system, a liquid supply system, and a vapor supply system. The combustion system is configured to generate power by combusting an alternative fuel. The liquid supply system is configured to channel a liquid alternative fuel to the combustion system. The vapor supply system is configured to channel a vapor alternative fuel to the combustion system. The combustion system is ignited by combusting the liquid alternative fuel from the liquid supply system and is operated by combusting the vapor alternative fuel from the vapor supply system.

Abstract: A fuel pump system, comprising an inlet line and a motorized pump, a first selector valve in fluid communication with an inlet line at a first inlet port and in fluid communication with the motorized pump outlet via a first outlet branch at a second inlet port to receive fuel from the motorized pump outlet. The system can also include a main fuel pump in fluid communication with the first selector valve and a second selector valve, wherein the second selector valve can be in fluid communication with the main fuel pump and in fluid communication with the motorized pump outlet.