Abstract: The present application of the invention aims at improving knot strength of a twisted yarn without compromising circularity, with respect to various yarns including a fishing line. For such purpose, the present application of the invention provides a yarn including a multifilament subjected to two twisting processes in different directions, and a coating resin that covers a surface of the multifilament; wherein the multifilament is subjected to a first twist in one direction, and then to a second twist in a direction opposite to that of the first twist, without being doubled with another yarn.

Abstract: Plasma-Based Waste-to-Energy (PBWTE) facility/systems, including plasma-assisted gasification systems, are described that can be integrated into a single system which when fed a steam of municipal solid waste, discarded tires, or electronic wastes, organic or inorganic, which have been shredded to a uniform size produces a synthesis gas (syngas) and a molten slag, and/or electricity.

Abstract: A combined cycle power plant includes a gas turbine, a steam turbine, a generator coupled to the gas turbine and a generator coupled to the steam turbine, and an auxiliary boiler operatively coupled to the steam turbine. The power plant is continuously operated in a combined cycle mode during operating of the gas turbine by starting the steam turbine first.

Abstract: A method includes blending a first fuel with a second fuel in a ratio to produce a third mixed fuel. The first fuel has a first heating value, the second fuel has a second heating value, and the third mixed fuel has a third heating value. In addition, the first heating value is different than the second heating value. The method also includes feedforward controlling the third heating value of the third mixed fuel via prediction and correction of a fuel flow rate of the first and/or second fuels to adjust the ratio of the first and second fuels based at least in part on a comparison between a measurement and a target for the third heating value.

Abstract: A turbine combustion air system includes a recuperator and a multi-zone combustor for accepting multiple combustion air streams at multiple temperatures.

Abstract: The present invention relates to a nacelle (1) for a jet engine (4) comprising a forward air inlet section (5), a mid-section (6) intended to surround a jet engine fan, and an aft section (9), at least one portion forming the aft section being connected to the mid-section via an at least partially peripheral radial knife-edge (31) capable of engaging by complementarity of shape with a corresponding groove (32) belonging to a portion (6a) of the mid-section, characterized in that the knife-edge comprises at least one reinforcing segment (35, 36) situated in a region for accommodating high loads, said reinforcing segment being made from a material which is stronger than the remainder of the knife-edge and tailored to the loads which are to be borne by said segment in this region.

Abstract: A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating nozzle segment having a forward edge and a first end. The nozzle segment is movably disposed behind the aft edge such that an upstream bypass flow exit is defined between the aft edge and the forward edge when the nozzle segment is in a deployed position. A deflector is disposed between the aft edge and the forward edge proximate to the first end. The deflector substantially prevents bypass flow from exiting the upstream bypass flow exit in a region that is proximate to the first end.

Abstract: A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating thrust reverser sleeve with a trailing edge. The thrust reverser sleeve is movably disposed aft of the nacelle's aft edge and is movable between a forward position and an aft position. A translating fan nozzle having a forward edge is movably disposed behind the trailing edge, and is movable between a stowed position and a deployed position. An upstream bypass flow exit is defined between the trailing edge and the forward edge when the fan nozzle is in the deployed position. An extendable actuation system is configured to move the fan nozzle between the stowed position and the deployed position.

Abstract: An engine timing input system is described for pulse detonation engines that allows for accurate engine timing when rotary or cylindrical valves are used to distribute an air/fuel mixture for combustion. The invention uses a profile disk having a predetermined circumferential edge corresponding to valve position to provide for accurate engine timing. A frequency wheel is used in conjunction with the profile disk to provide a more accurate representation of valve position by partitioning the valve position into multiple pulses during each rotation of the rotary or cylindrical valve. The profile disk and frequency wheel when used with programmable timing circuitry signal fuel valve timing and ignition relative to the rotating valve.

Abstract: There are provided a control device and a control method for an exhaust gas purification apparatus that can prevent the actual adsorption amount from becoming excessively lower than the saturated adsorption amount and can prevent the reduction efficiency of the reduction catalyst from degrading even when the temperature of catalyst continues to shift to a low temperature side for a predetermined time or longer.

Abstract: According to one representative embodiment, an apparatus for controlling reductant dosing in an SCR catalyst system having a reductant injection system configured to inject reductant into an exhaust gas stream includes a controller, an actual reductant dosing rate module, and a reductant doser compensation module. The controller is configured to determine a reductant dosing rate command representing a desired reductant dosing rate. The actual reductant dosing rate module is configured to determine a predicted actual reductant dosing rate based at least partially on the reductant dosing rate command. The reductant doser compensation module is configured to determine a modified reductant dosing rate command based at least partially on the predicted actual reductant dosing rate. The reductant injection system injects reductant into the exhaust gas stream at a rate corresponding to the modified reductant dosing rate command.

Abstract: There are provided a control unit and a control method for a reductant supply system, which are capable of reducing energy consumption by immediately stopping heating means in the case of entering an idling stop mode. A control unit which performs control of a reductant supply system includes an idling stop determination portion that determines whether an internal combustion engine is stopped by idling stop control that automatically stops the internal combustion engine, a heating means operation determination portion that determines whether the heating means provided in the reductant supply route that supplies the liquid reductant to the reductant injection valve is in operation, and a heating means control portion that stops operation of the heating means in a state where the internal combustion engine is automatically stopped and the heating means is in operation.

Abstract: An exhaust aftertreatment system for a lean-burn engine may include a lean NOx trap that comprises a catalyst material. The catalyst material may remove NOx gases from the engine-out exhaust emitted from the lean-burn engine. The catalyst material may include a NOx oxidation catalyst that comprises a perovskite compound.

Abstract: To suppress clogging of an injection nozzle that supplies fuel to an exhaust passage of an engine, a controller executes intermittent addition of fuel from the injection nozzle. In executing the intermittent addition, the controller calculates a particulate discharge amount within the exhaust passage based on the engine operation state, and multiplies the exhaust gas temperature by the intake air rate to calculate the exhaust energy. Then, based on the particulate discharge amount and the exhaust energy, the controller calculates the amount of fuel to be added.

Abstract: A method for remediating a NOx-containing lean diesel emission includes providing a LNT/SCR catalyst system including a SCR catalyst and a first and second LNT. The SCR catalyst is disposed downstream of the second LNT which is disposed downstream of the first LNT. The lean NOx-containing diesel emission is introduced to the first LNT with the NOx being absorbed on to the first LNT forming a substantially NOx-free lean diesel emission. An exotherm generating agent is introduced to the substantially NOx-free diesel emission between the first LNT and the second LNT to form a reactive lean diesel emission. The reactive lean diesel emission is introduced to the second LNT generating a quantity of heat effective for desorbing absorbed NOx. A reducing agent is introduced into the desorbed NOx between the second LNT and SCR catalyst. The desorbed NOx diesel emission is remediated in the SCR catalyst.

Abstract: Disclosed is a technology that enables better reduction of NOx stored in an NOx catalyst in an exhaust gas purification system for an internal combustion engine. When NOx stored in an NOx catalyst is to be reduced, the air-fuel ratio of the ambient atmosphere around the NOx catalyst is decreased to a target air-fuel ratio by decreasing the air-fuel ratio of the exhaust gas discharged from the internal combustion engine. In doing so, if the temperature of the NOx catalyst is not lower than a specific temperature, the air-fuel ratio of the ambient atmosphere around the NOx catalyst is decreased to the target air-fuel ratio while bringing the combustion state into low temperature combustion.

Abstract: A system for venting crankcase emissions from an engine is disclosed generally comprising a crankcase emissions conduit that communicates blow-by gases from the crankcase into the exhaust flow of an exhaust conduit, which includes a venturi, via an inlet located upstream of the minimum inner diameter of the venturi in order to pump the crankcase emissions therethrough. In certain embodiments, the gases are then directed to a filter assembly, which may include a particulate filter and may include a catalyst for facilitating redox of harmful substances to create harmless compounds prior to venting them or recirculating them in the system. In certain advantageous embodiments, an auxiliary oxygen supply is provided to facilitate these burning processes.

Abstract: An after-treatment device that includes a diesel particulate filter (DPF) requiring periodic regeneration includes a sensor providing a signal indicative of a soot accumulation and at least one device providing an operating parameter indicative of a work mode of the machine. A controller determines a soot level and a readiness level based on the work mode of the machine, and further classifies the soot level relative to a desired range for initiating a regeneration event and initiates the regeneration event when the soot level falls within the desired range.

Abstract: An engine exhaust aftertreatment system including a selective catalytic reduction (SCR) device. The system contains no significant amount of catalyzed material upstream of the SCR device.

Abstract: An exhaust system for a marine engine comprising liquid cooled manifold and catalytic converter assemblies. Each assembly uses a separate cooling system to cool either the exhaust manifold or a shell inside which resides the catalytic converter. The housing or shell containing the catalytic converter uses water to cool an exterior surface of a water jacket to an acceptable temperature conforming to federal regulations. The liquid-cooled manifold assembly may use either water or glycol to cool a jacket surrounding tubes extending from the engine block to the catalytic converter assembly.

Abstract: A method for operating an internal combustion engine of a motor vehicle is provided, wherein at least one SCR catalytic converter for the after-treatment of exhaust gases of the internal combustion engine is present. The method serves to assure that a sufficient quantity of reducing agent is supplied for the operation of the SCR catalytic converter. The motor vehicle has a fuel tank (10) with a fill level sensor A (11) and a reducing agent tank (12) with a fill level sensor B (13). Signals from the fill level sensor B (13) or signals from the fill level sensor A (11) and the fill level sensor B (13) are acquired and evaluated by a navigation unit (16).

Abstract: A structure for the purification of a polluted gas comprising a porous matrix of an inorganic material, in the form of interconnected grains and an electrochemical system for the treatment of said gas, formed by a reduction catalyst A for reducing the polluting species of the NOx type, an oxidation catalyst B for oxidizing the polluting species of the hydrocarbon HC type or CO type, an electron-conductive compound C and an ion-conductive compound D, said structure being characterized in that catalysts A and B are placed in the pores of the inorganic material, in that the grains and possibly the grain boundaries of the inorganic material constituting the matrix are covered over at least part of their surface with a texturizing material, and in that said texturizing material is an ionic, electronic or ionic/electronic conductor and constitutes, respectively, the element C, the element D or the elements C and D of the electrochemical gas treatment system.

Abstract: A device for influencing an exhaust gas flow, in particular for controlling sound emission in an exhaust branch of an engine, has a closure member that is driven by a motor in the exhaust pipe. The closure member produces pressure pulsations in the exhaust gas, so that a so-called “sound design” is possible. A force-transmitting, thermal decoupling member is integrated into a force transmission member located between the drive motor and the closure member to interrupt the heat transfer between the closure member and the drive motor.

Abstract: Generally, the invention relates to power generation and energy storage. In particular, to systems and methods for providing constant power from hydraulic inputs having widely-varying pressures. More particularly, the invention relates to hydraulic-pneumatic energy storage and recovery systems that include either a fixed or variable displacement hydraulic motor and control systems that allow a user to maintain constant power from the fixed or variable displacement hydraulic motor.

Abstract: A method and apparatus for extracting energy from wind and wave motion using a common floating platform comprising a ship hull (10) which is moored in an offshore location and which supports wind turbines (27) for extracting energy from wind and wave energy extraction devices (12) positioned at least at one side of the hull (10) for extracting energy from wave motion relative to the hull (10). The method and apparatus may also use water current energy extraction devices. The hull (10) may also support a desalination plant (45) which uses the energy generated from the wind, wave and water current energy extraction devices.

Abstract: A heat engine has four oscillating pistons which lie at a right angle to one another are located in four cylinders. The pistons and the cylinders are of wedge-shaped configuration and have the shape of a cone section. The pistons rest with their lower tip on a piston bearing. The four cylinders are connected to one another by means of channels; compression chamber to displacement chamber and displacement chamber to compression chamber. The crank rotates in this method of operation counter to the gas flow. The engine is applied in the stationary area, preferably in order to generate electricity and heat decentrally in the context of power/heat cogeneration with the use of renewable resources. It is to be possible, inter alia, to also use the heat engine for the low and medium temperature range and to make few demands of the quality of the fuels.

Abstract: Hydraulic fluid is supplied from a hydraulic fluid supply opening to a hydraulic fluid supply portion. The hydraulic fluid in the hydraulic fluid supply portion is supplied to a primary hydraulic fluid storage chamber and to a secondary hydraulic fluid storage chamber via a hydraulic fluid supply passage. An oblong cylinder-shaped portion that has a chamber is formed between the hydraulic fluid supply opening and the hydraulic fluid supply portion. Further, a volume-augmented chamber forming portion that has a volume-augmented chamber that is communicated with the chamber is disposed in this oblong cylinder-shaped portion. In that case, at least part of the volume-augmented chamber is positioned above a MAX line of the hydraulic fluid.

Abstract: A cooler device for a motor vehicle includes a charge air cooler with a first cooler element, an EGR cooler with a second cooler element, the first and second cooler elements are arranged beside and substantially in plane with one another. The cooler elements each comprise pipelines for the respective medium to be cooled. Air passages for a cooling air flow are arranged between the pipelines. A screening device is arranged in front of or behind the cooler elements to regulate the air flow through elements. A control mechanism switches the screening device to and from between an open position in which the screening device does not, or at least does not appreciably, limit air flow through the air passages of the cooler elements, and a closed position in which the screening device limits the air flow through the air passages between all of the pipelines of the second cooler element and the air flow through the air passages between only some of said pipelines of the first cooler.

Abstract: A system for separating and dispersing condensate formed in a charge air cooler of a turbocharged engine system. The system includes a drain tube on the charge air cooler lower surface that is plumbed to a reservoir, with a charge air recirculation tube plumbed from the reservoir to the turbocharger compressor inlet duct. The pressure difference between the charge air cooler and the compressor inlet draws any condensate formed in the charge air cooler back into the reservoir. A valve at the bottom of the condensate reservoir will open under predetermined vehicle operating conditions to drain the stored condensate out from the reservoir. The condensate could be simply drained to the ground, or a spray bar could be connected to the reservoir outlet to spay the condensate on to the outside surface of the charge air cooler, providing additional performance for brief periods of high engine load operation.

Abstract: In an internal combustion engine comprising an exhaust gas turbocharger, including a turbine with at least two inlet passages arranged in the exhaust gas tract of the internal combustion engine, via which exhaust gas from the internal combustion engine can be supplied to a turbine wheel of the turbine, and a valve arrangement being arranged in to the exhaust gas tract to the turbocharger to control the supply of exhaust gas to the inlet passages of the turbine, a valve and turbine inlet passage configuration is selectable providing for a maximum braking power with low thermal load.

Abstract: A turbine housing for a turbocharger for use in a reciprocating internal combustion engine includes a housing having a housing axis and configured to house a rotatable shaft having a turbine wheel disposed thereon. The housing includes a volute having a volute chamber disposed around the housing axis for receiving the turbine wheel. The volute has a first volute inlet providing a first flow path in fluid communication with the volute chamber and second volute inlet providing a second flow path in fluid communication with the volute chamber. The first volute inlet is circumferentially spaced about the housing axis from the second volute inlet by a phase angle ?. The first volute inlet is also radially spaced about the housing axis from the second volute inlet, and may also be axially spaced from the second volute inlet along the housing axis.

Abstract: The present invention relates to a device comprising: a first container and a second container, a capillary device arranged between the first container and the second container with one or more capillaries, each of the one or more capillaries connecting the first container to the second container, and each of the one or more capillaries tapering at least in sections from the second container in the direction towards the first container, means for generating and/or maintaining a temperature gradient T1st container>T2nd container between the first container and the second container.

Abstract: A condenser is provided and includes a body into and through which steam turbine discharge is able to flow, and first and second cooling members disposed in the body, wherein the first and second cooling members are each independently receptive of first and second coolant, respectively, the first cooling member, being receptive of the first coolant, is configured to cool the discharge during at least a first cooling operation, and the second cooling member, being receptive of the second coolant, is configured to cool the discharge during a second cooling operation.

Abstract: The conventional automobile is powered solely by gasoline. Recent automobiles have been produced which incorporate electric motors either in tandem with a gasoline-powered engine or alone. This improvement aims to add an external-combustion steam engine to the mix. The envisioned automobile can be thought of as a gas-electric-steam power trihybrid automobile. By utilizing steam power, the fuel efficiency of the current state of automotive technology can be significantly augmented. The envisioned automobile is powered primarily by a steam engine along with an electric motor and a gasoline-powered boiler. The automobile uses the electric motor to start and after warming-up utilizes a steam powered external combustion engine whose steam is produced by a boiler which utilizes gasoline or other hydrocarbon as a fuel source.

Abstract: A fuel conveying member of a gas turbine engine fuel system conducting pressurized fluid flow is provided. The fuel conveying member comprises a body defining an L-shaped fuel flow passage therein, the L-shaped passage including an elbow. The elbow portion provides a substantially smooth fluid-dynamic transition between portions of the passage upstream and downstream thereof.

Abstract: In one embodiment, a system includes a turbine engine fuel nozzle having an air path, a fuel path, and a surface along the air path. The fuel path may be directed toward the surface. The turbine engine fuel nozzle also may include a heating element configured to heat the surface.

Abstract: This invention provides a gas turbine combustor including: a main burner at a head portion of a combustor cylinder; and a pre-mixing type supplemental burner at a downstream portion of the combustor cylinder and extending through a circumferential wall thereof. The supplemental burner includes: an introducing passage configured to deflect a part of the compressed air radially inward, the compressed air flowing from an air passage between the circumferential wall of the combustor cylinder and a housing surrounding the circumferential wall toward the head portion of the combustor cylinder, and introduce the compressed air into the combustor cylinder; and a fuel nozzle configured to supply the fuel from fuel injection holes to the compressed air introduced into the introducing passage to produce a pre-mixed gas in the introducing passage.

Abstract: Embodiments of methods and apparatus for providing a sacrificial shield for a fuel injector are provided. According to one example embodiment, a method for shielding a fuel injector associated with a combustion device is provided. The method can include providing at least one shield support device operable to mount to a tip of a fuel injector. The method can also include mounting a plurality of shields to the at least one support device, wherein each of the plurality of shields is spaced apart from each respective adjacent shield by at least one segmentation, and wherein each of the plurality of shields is operable to reduce heat exposure to the tip of the fuel injector.

Abstract: Turbomachine, comprising a combustion chamber provided with systems (132, 132?) for injecting fuel into the chamber, and with at least one spark plug (144), the injection system (132) located as close as possible to the spark plug being configured in order to produce a pool (166) of fuel having an angle of opening (?) of a greater value than that (?) of the pools (166?) produced by the other injection systems (132?), and having a flow of fuel greater than that of the other injection systems (132?).

Abstract: A small gas turbine engine for use in an UAV such as a cruise missile, the gas turbine having a combustor forming a primary burn zone and a secondary burn zone, and in which fuel is injected into both the primary and the secondary burn zones by either a rotary cup injector or a plurality of fuel injector nozzles. The secondary burn zone with separate fuel injection allows for the diameter of the engine to be reduced in size but still allow for adequate power and efficiency to be reached for powering the vehicle. Air flow from the compressor is used to cool the combustor walls before being injected into the combustor, and to pass through and cool the guide nozzles and a main bearing located near the hot section of the combustor prior to being introduced into the combustor.

Abstract: A combustion apparatus and duct structure for a gas turbine engine are provided. The combustion apparatus comprises a combustion system to receive fuel and air, ignite at least a portion of the fuel and air and output a stream of first combustion products and any remaining fuel and air. The combustion apparatus further comprises structure positioned adjacent to the combustion system for receiving and accelerating the first combustion products and any remaining fuel and air from the combustion system. The duct structure receives the first combustion products and any remaining fuel and air from the combustion apparatus, allows any remaining fuel and air to combust to generate second combustion products, accelerates the first and second combustion products and outputs the first and second combustion products to a first row blade assembly.

Abstract: A gas turbine engine combustor includes a plurality of main fuel injector assemblies, and a plurality of pilot fuel injector assemblies, that are arranged and configured to reduce exhaust gas emissions during engine operation. The plurality of main fuel injector assemblies are arranged in a substantially circular pattern of a first radius, and each includes an outlet port having a first divergence angle. The plurality of pilot fuel injector assemblies are arranged in a substantially circular pattern of a second radius. Each pilot fuel injector assembly is disposed between at least two main fuel injector assemblies, and each includes an outlet port having a second divergence angle.

Abstract: The invention relates to a wall element for a wall structure of a gas turbine engine combustor. The wall element has an inner, in use, hot surface, and an outer, in use, cooler surface. A plurality of projections is provided on the outer surface to facilitate heat transfer to a coolant flow. The wall element comprises a means to direct more coolant flow at a hot-spot on an adjacent tile than the remainder of the adjacent tile and thereby reducing the thermal gradient across the adjacent tile.

Abstract: A system, in one embodiment, includes a turbine engine. The turbine engine includes a combustor that includes a hollow annular wall having a combustor liner. The turbine engine also includes first flow path in a first direction through the hollow annular wall. The turbine engine further includes a second flow path in a second direction that is opposite the first direction through the hollow annular wall. The second flow path may include one or more film holes configured to supply a cooling film to a downstream end portion of the combustor liner.

Abstract: A wall configured to withstand a high thermal load, said wall having a surface that is turned away from a heat source and provided with at least one strengthening element that, from a base portion thereof, protrudes from said surface. Said at least one strengthening element presents a decreasing width from its base portion towards a top portion thereof. The wall is an engine wall of a thrust nozzle of a rocket engine.

Abstract: Disclosed herein is a highly-reliable two-shaft gas turbine system in which the rotational speed of a compressor exceeds its rated rotational speed when the combustion temperature during rated operation is set to the rated combustion temperature of a simple-cycle gas turbine system and in which the drive force for the compressor can be balanced with the output from a high-pressure turbine without turbine efficiency being compromised. When the rotational speed of a compressor 1 exceeds its rated rotational speed on the condition that the combustion temperature during rated operation is set to the rated combustion temperature of a simple-cycle gas turbine system, part of the working fluid that drives turbines is diverged from a flow path that guides the working fluid to gas paths and used as a coolant.

Abstract: A turbine engine arrangement incorporates an electrical machine combination which can act as a generator or motor. Thus, the combination during initial turbine engine arrangement start-up acts through this motor to drive shaft rotation. This shaft rotation creates core compressed air which is bled through a valve to an air turbine such that the electrical machine when acting as a motor or generator at low engine loads is appropriately cooled. The arrangement also includes a compressor fan which generates an airflow utilised by the air turbine in order to drive the electrical machine as a generator of electrical power when engine conditions dictate. A duct is provided to direct airflow exhausted from the air turbine to a heat exchanger arranged to exchange heat with a bypass flow from the compressor fan.

Abstract: A gas turbine engine is disclosed having a compressor, a combustion chamber downstream of the compressor, and a turbine downstream of the combustion chamber. The compressor includes a first group of compressor blade wheels and a second group of compressor blade wheels downstream of the first group of compressor blade wheels and rotating in an opposite direction such that a deviation of a performance, defined as air mass flow per second between the first group of compressor blade wheels and the second group of compressor blade wheels, is minimized, and a detachment of the air mass flow from blades of a first blade wheel of the second group of compressor blade wheels is substantially eliminated. A bypass enables the air mass flow flowing from the first group of the compressor blade wheels to substantially serve all of the second group of compressor blade wheels substantially simultaneously.

Abstract: An exhaust system for an aircraft has a primary exhaust duct for communicating exhaust gas from an engine exhaust exit and is configured for movement with the engine. A secondary exhaust duct is in fluid communication with the primary exhaust duct and is movably mounted to the airframe. The system has means for maintaining a generally consistent relative alignment between the primary duct and the secondary duct.

Abstract: The burner (1) for a gas turbine includes a duct (2) housing a plurality of tetrahedron shaped vortex generators (3) and a lance (4) to inject a fuel to be combusted. Within the duct (2), a plurality of vortex generators (3) are provided with a plurality of holes (9) for injecting cooling air. The cooling holes (9) define passing through areas that are non-uniformly distributed on a top wall (11) of the vortex generators (3). A method for locally cooling a hot gases flow passing through a burner includes non-uniformly injecting cooling air from a vortex generator into the hot gas flow in the duct, which can reduce the occurrence of flashback in the burner.