Abstract: An apparatus for communicating signals across a wellbore barrier defined by a first flow completion system component positioned at an upper end of the wellbore and a second flow completion system component mounted within the first flow completion system component includes a first wireless node which is mounted on the first flow completion system component on a first side of the wellbore barrier, the first wireless node being configured to be connected to an external device, and a second wireless node which is mounted on the second flow completion system component on a second side of the wellbore barrier, the second wireless node being located generally opposite the first wireless node and being configured to be connected to a downhole device. The first and second wireless nodes are configured to communicate wirelessly through the wellbore barrier using near field magnetic induction (NFMI) communications.

Abstract: An inground housing supports a transmitter for receiving electrical power from a battery. The transmitter transmits at least one signal using at least two different transmit power levels for at least one of locating the transmitter and characterizing an orientation of the transmitter. Based on detecting the battery voltage, the transmitter selects one of the transmit power levels. Transmitter output power can be controlled based on one or both of signal gain and duty cycle.

Abstract: The flow control device includes a flow path, a compensation chamber and a regulator assembly defining a first surface exposed to the flow path and an opposing second surface which is exposed to the compensation chamber. A drive arrangement is provided for moving the regulator assembly to vary the flow path. Fluid flowing through the flow path establishes a pressure which varies across the first surface of the regulator assembly. The compensation chamber is in pressure communication with a localised region of the first surface which is selected to establish a compensation chamber pressure which acts against the second surface of the regulator assembly to bias the regulator assembly in a desired direction. The first surface of the regulator assembly may define a profile configured to minimise the variation in pressure applied over the first surface by action of fluid flowing through the flow path.

Abstract: Systems and methods for subterranean formation testing. A method may include: lowering a formation testing tool into a subterranean formation, wherein the formation testing tool may include memory, a pump, a formation probe, at least two sample chambers, wherein the at least two sample chambers may include probes to measure pressure and temperature; extracting a fluid from the subterranean formation with the pump and the formation probe; flowing the fluid into the at least two sample chambers with the pump; storing pressure and temperature data of the fluid in the memory; and removing the at least two sample chambers from the formation testing tool.

Abstract: A method of estimating one or more properties of an earth formation includes acquiring formation fluid data indicative of a qualitative property of a formation fluid in a near-field region of an earth formation surrounding a borehole, the near field region including a surface of the borehole, and acquiring acoustic data based on acoustic signals transmitted into a far-field region of the formation, and estimating a property of one or more fractures in the far-field region based on the acoustic data. The method also includes combining the formation fluid data and the acoustic data, and estimating, by a processing device, at least one fracture characteristic of the formation in the near-field region and the far-field region based on the combined data.

Abstract: Embodiments of the invention are directed to cutting tool assemblies, cutting tool mounting assemblies, material-removing machines that include cutting tool assemblies and/or cutting tool mounting assemblies, and methods of use and operation thereof. In some embodiments, the various assemblies described herein may be used in material-removing machines that may remove target material.

Abstract: A method of moving waste material from a mining site using at least one excavator and a plurality of dozers, including excavating material with the at least one excavator from a dig area, said at least one excavator moving along an excavator path that is parallel with the dig area, transferring the excavated material to a plurality of slots, each of said slots are positioned at an angle to the excavator path, and pushing the transferred material by one of said plurality of dozers along the slot and away from the excavator path; wherein each slot allows each of the plurality of dozers to move between a proximal position and a distal position relative to the excavator path.

Abstract: This invention relates to an injection tool which comprises a longer smaller diameter pipe assembled movable inside a shorter larger diameter pipe, a connection piece assembled at the first end of the smaller diameter pipe, a projecting part connected to the smaller diameter pipe near the connecting piece, the projecting part having an opening or groove for a bolt, a projecting part connected near to the first end of the larger diameter pipe the projecting part having threaded opening for the bolt, the bolt connecting the projecting parts and the bolt having a fixed stopper plate, a nose piece assembled to the second end of the smaller diameter pipe, a press plate assembled to the second end of the larger diameter pipe and a sealing rubber around the smaller diameter pipe situated between the nose piece and the press plate.

Abstract: Disclosed is a mixing and guniting device of a new type for a TBM, wherein the device comprises a concrete inlet pipe (1), a four-way pipe (15), a nozzle (4), an agitator motor (5), a longitudinal swing oil cylinder (6), a flow mixer, a lateral swing oil cylinder (16), a telescopic oil cylinder (7) connected to a big arm, and a controller, one end of the telescopic oil cylinder (7) being provided with a connection plate (12), the four-way pipe (15) being fixed on the upper part of the connecting plate (12), two interfaces in the upper part of the four-way pipe (15) being respectively provided with an air inlet pipe (2) and an accelerator inlet pipe, a measuring sensor connected to the controller being provided in the air inlet pipe (2), two interfaces in the lower part of the four-way pipe (15) being respectively provided with bent pipes (8), the other ends of the bent pipes (8) being in communication with the flow mixer, the nozzle (4) being provided in the upper part of the flow mixer, the concrete inlet pi

Abstract: A laser-assisted tunnel boring machine and a rock fragmenting method thereof belong to the technical field of tunnel engineering. Two rock fragmenting modes exist: a laser-cutter rock fragmenting mode and a cutter rock fragmenting mode, wherein the two rock fragmenting modes are switched by an intelligent control system; and for the laser-assisted rock fragmenting mode, hot fragmenting is mainly performed using lasers which assisted by water spray systems, to achieve the purposes of auxiliary rock fragmenting by laser radiation for hot cracking and water spray for quick cooling, and mechanical rock fragmenting for excavation.

Abstract: A trailer of a backup train of a tunnel boring machine includes a rolling means configured to allow movement of the trailer on a circulation route, a chassis including a lower portion including the rolling means and an upper portion, opposite to the rolling means, conveying means, fixed in the lower portion of the chassis, the conveying means being configured to move at least one support along the trailer, the support being configured to transport at least one arch segment along the chassis.

Abstract: Disclosed is a physical-chemical composite inhibitor for controlling spontaneous combustion of low-rank coal, and methods of preparing and using the same. The composite inhibitor consists of a chelate and attapulgite, the chelate is generated by chelation of proanthocyanidin with calcium chloride. The composite inhibitor has moisture-absorbing and moisture-retaining effect, and can reduce water dissipation at low temperature. A stable oxide insulating layer such as MgO and Al2O3 insulating layer can be formed at high temperature, which can block a coal body from contacting with oxygen. In addition, the composite inhibitor can capture hydroxyl free radicals generated during the chain-cycle reaction and destroy peroxide free radicals, and can also interact with an active moiety in coal to form a stable structure such as ether linkage and hydrogen bonding, thereby achieving permanent inhibition of low-rank coal.

Abstract: The invention relates to an eccentric screw pump, comprising at least one stator (1) composed of an elastic material and a rotor (2) that can be rotated in the stator (1), the stator (1) being surrounded by a stator casing (3) at least in some regions. The stator casing (3) consists of at least two casing segments (19) as a longitudinally divided casing and forms a stator clamping device, by means of which the stator (2) can be clamped against the rotor (1) in the radial direction.

Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

Abstract: A blade/vane cascade segment for a blade/vane cascade of a turbomachine includes a stage and at least two blade/vane elements that define a blade/vane intermediate strip with an axial cascade span on the stage surface by their leading and trailing edges. A stage edge on the inflow side has a contour with a depression. In the axial direction, this depression extends at most by 10% of the cascade span into the blade/vane intermediate strip. Also provided is a corresponding stage, a blade/vane cascade, a blade/vane channel, and a turbomachine.

Abstract: A composite spar having an upper and lower wall region connected by leading and trailing edge regions is provided including a plurality of first laminates and a plurality of second laminates. The plurality of first laminates includes one or more intermediate modulus graphite plies having an intermediate modulus. The plurality of first laminates is arranged in one or more intermediate modulus layers to form at least a portion of the upper wall region, lower wall region, leading edge region and trailing edge region. The plurality of second laminates includes one or more high modulus graphite plies having a high modulus. The plurality of second laminates is arranged in one or more high modulus layers. The high modulus layers are generally interposed between intermediate modulus layers.

Abstract: An airfoil including a spar and a cover sheet. Standoffs, a leading edge wall, and a separator wall extend away from an outer surface of the spar. The standoffs are arranged to define leading grooves disposed at the pressure side of the leading edge. The cover sheet is coupled to the leading edge wall and the standoffs over the leading grooves to define cooling passageways. The cooling passageways are in communication with one or more inlet ports formed in the spar, which are in communication with a plenum disposed within the spar. The cover sheet is arranged to define outlet ports or a slot in communication with the cooling passageway. Cooling air is delivered from the cooling air plenum through the inlet port for impingement cooling at the cover sheet, and traverses downstream through the cooling passageway to the outlet ports or slot for film cooling of the leading edge.

Abstract: An apparatus and method an airfoil for a turbine engine, the airfoil comprising an outer wall defining an interior bound by a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction. The airfoil further includes at least one cooling hole including a diffusing section and fluidly coupling an exterior of the engine component to an exterior of the engine component.

Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A main-body core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a platform. An airfoil skin cooling passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The airfoil skin cooling passage extends to a platform skin cooling passage arranged in the platform. A resupply hole fluidly connects the main-body core cooling passage and at least one of the airfoil skin cooling passage and the platform skin cooling passage.

Abstract: A vane cooling system for a gas turbine engine comprises a vane (20a) arranged on a stator and having a chamber (27,28) extending continuously from a radially inner end to a radially outer end of the vane. The vane (20a) has a first inlet (41) and a second inlet (42). A first cooling fluid feed (54) in communication with the first inlet (41) and a second cooling fluid feed (43) in communication with the second inlet (42). The first cooling fluid feed (54) has a higher pressure than the second cooling fluid feed (43). A flow adjustment device (45) is arranged for adjusting a flow of the second cooling fluid feed (43) into the second inlet (42). The chamber is divided by a restrictor plate (25, 26) to provide an inner chamber (27) and a wall-side chamber (28) bordering the inner chamber (27). The first inlet (41) enters the wall-side chamber (28) and the second inlet (42) enters the central chamber (27).

Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a tip. A skin passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The core passage and the skin passage are configured to have a same direction of fluid flow. A resupply hole fluidly interconnects the core and skin passages. The resupply hole has a single inlet that is fluidly connected to multiple discrete outlet apertures.

Abstract: A turbine rotor blade that includes a tip shroud attached to the outboard tip of the airfoil. The tip shroud may include an axially and circumferentially extending planar component in which an inboard surface opposes an outboard surface, and a shroud edge that connects the inboard surface to the outboard surface and defines an outboard profile of the tip shroud. The tip shroud may include a seal rail protruding from the outboard surface of the tip shroud and a cutter tooth disposed on the seal rail. The cutter tooth may be formed as a circumferential section of the seal rail that is axially thickened. The seal rail may further include a leakage gap formed therethrough that is configured to increase a leakage level during operation.

Abstract: A rotor assembly includes plural blades and damping inserts. The blades include a carrier shroud and a lid shroud extending from an airfoil of the respective blade in generally opposite directions. The carrier shrouds define pockets at distal ends thereof. The damping inserts are disposed in the pockets of the carrier shrouds of the blades and free-floating within the pockets. The damping inserts are configured to dampen vibrations of the blades during rotation of the blades and the rotor disk via engaging an interior surface within the corresponding pocket of the carrier shroud and engaging a distal end of the lid shroud of the neighboring blade. A contact force applied by each damping insert on the distal end of the lid shroud of the neighboring blade is based on a rotational speed of the blades and the rotor disk.

Abstract: A coated ceramic matrix composite component and a gas turbine assembly are provided. The coated ceramic matrix composite component comprises a substrate comprising an endface surface and a hot gas path surface. The hot gas path surface is arranged and disposed to contact a hot gas path when the component is installed in the gas turbine assembly. The endface surface is disposed at an endface angle to the hot gas path surface and opposing at least one adjacent component when the component is installed in the gas turbine assembly. The coated ceramic matrix composite component further comprises an environmental barrier coating on at least a portion of the endface surface.

Abstract: A method of manufacturing a coated turbine vane (34) comprises manufacturing a turbine vane (34) having a platform (44) and an aerofoil (42) extending from the platform (44), a curved transition (60) connects the platform (44) to the aerofoil (42) and a recess (64) is provided in the curved transition (60) from the platform (44) to the aerofoil (42). A bond coating (70) is deposited on the platform (44), the aerofoil (42), the curved transition (60) and the recess (64). A ceramic thermal barrier coating (72) is deposited on the platform (44), the recess (64) and the curved transition (60) by plasma spraying. The recess (64) reduces the size of the step due to the ceramic thermal barrier coating (72) and hence improves the aerodynamics of the turbine vane (34).

Abstract: A retainer for a gas turbine blade that inhibits deviation of a rotating blade mounted on a rotor of a gas turbine, can include: a retainer frame disposed at one side of the rotating blade and configured to form an inside chamber through which cooled air is introduced, between the retainer frame and the rotating blade; a barrier wall formed between the retainer frame and the rotating blade and configured to divide the inside chamber into a plurality of cooling chambers; and a fixing unit disposed at one side of the retainer frame and configured to fix the retainer frame to the rotor.

Abstract: A component for a gas turbine engine includes a platform that has a gas path side and a non-gas path side. At least one airfoil extends from the gas path side of the platform. At least one airfoil includes an internal cavity that has an inlet on the non-gas path side of the platform. A cover plate is located adjacent the non-gas path side of the platform. The cover plate includes a first plurality of fluid openings that extend through the cover plate. At least one bulge is at least partially aligned with the inlet.

Abstract: A turbine blade sealing structure for a ceramic matrix composite component is provided. The turbine sealing structure includes at least one top ply abutting a top portion of a shank. The at least one top ply extends out over the top portion of the shank. The turbine sealing structure includes at least one side ply abutting a side portion of the shank. The at least one side ply extends along a side portion of the shank. The at least one top ply and at least one side ply form an angel wing and a skirt with on the shank of the ceramic matrix composite component.

Abstract: An airfoil stage of a turbine engine includes an upstream airfoil assembly, a downstream airfoil assembly in rotational relationship to the upstream airfoil assembly and a rim seal assembly integrated therebetween. The rim seal assembly may include a sloped downstream portion of a platform of the upstream airfoil assembly, an upstream segment of a platform of the downstream airfoil assembly and a nub that projects radially outward from the upstream segment. The downstream portion and the upstream segment are spaced from one-another defining a cooling cavity therebetween for the flow of cooling air. The portion and segment overlap axially such that the nub is axially aligned to the downstream portion for improved cooling effectiveness and a reduction of core airflow into the cooling cavity.

Abstract: Turbine wheels, turbine engines, and methods of forming the turbine wheels are provided herein. In an embodiment, a turbine wheel includes a rotor disk and a plurality of turbine blades. Each turbine blade is operatively connected to the rotor disk through a blade mount, which is bonded to the rotor disk. The blade mount and the rotor disk have a fore surface on a higher pressure side thereof and an aft surface on a lower pressure side thereof. The blade mount includes a blade attachment surface that extends between and connects the fore surface and the aft surface. The turbine blade extends from the blade attachment surface. A gap is defined between adjacent blade mounts. The gap separates the blade mounts and extends into the rotor disk. The gap includes a pocket that has a fore opening in the fore surface. A pocket seal is disposed in the pocket.

Abstract: The invention relates to a turbine, in particular a combustion gas turbine, which drives a high-speed generator for generating electricity, said turbine having a high efficiency. The turbine has at least one combustion chamber (6), which is provided with a fuel injection means (7) and an ignition device (8) and which supplies the turbine with a combustion gas. An external compressor (3) is associated with the turbine. Said compressor has a separate electric drive and is not connected to the turbine by means of a drive shaft. Furthermore, at least two combustion chambers (5) are provided for discontinuous, pulsed combustion and supply of the turbine.

Abstract: A bypass turbine engine is described. The engine includes a system for bleeding gas from a primary stream to a secondary stream. The system may include two coaxial rings extending one around the other. A perforated internal first ring may be situated at the level of an outer casing and may extend substantially in a continuation of the outer casing. A perforated external second ring may be mounted such that it slides circumferentially on the first ring between a first position in which the perforations of the rings do not communicate with one another and a second bleed position in which the perforations of the rings communicate with one another.

Abstract: A pneumatic trip system for a turbine includes a valve member; a valve stem connected to the valve member; and an actuator assembly connected to the valve stem. The actuator assembly includes a cylinder; a piston connected to the valve stem, the piston dividing the cylinder into a first chamber and a second chamber; a biasing element disposed in the second chamber of the cylinder; and a pneumatic circuit in communication with the second chamber of the cylinder. The pneumatic circuit is configured to pressurize the second chamber of the cylinder to actuate the piston to move the valve stem and the valve member to an exercised position between the open position and the closed position while the first chamber is pressurized.

Abstract: Systems and methods for protecting a turbomachine may include a trip throttle valve having a throttle valve assembly and a trip valve assembly. The trip valve assembly may include a plurality of trip valves fluidly coupled to a hydraulic cylinder of the throttle valve assembly via a first flow path and a second flow path in parallel with one another. The trip valve assembly may also include a plurality of isolation valves fluidly coupled to the hydraulic cylinder via the first flow path and the second flow path. The plurality of isolation valves may be configured to selectively prevent fluid communication between the plurality of trip valves and the hydraulic cylinder to allow testing of one or more of the plurality of trip valves during operation of the turbomachine.

Abstract: The invention relates to a system for controlling variable-setting blades (14) for a turbine engine, which includes at least one control ring (36) mounted rotatably mobile about an annular casing (16) with axis of revolution A, at least one annular row of variable-setting blades (14) extending substantially radially relative to said axis A and connected to said at least one control ring so that a rotation of the ring about the casing rotates the blades about substantially radial axes B, and means (40) for actuating said at least one ring in order to rotate same about the casing, characterised in that said actuation means are connected to said at least one ring by linking means comprising a shaft (52) extending along an axis C which is substantially radial relative to said axis A and mounted rotatably mobile about said axis C on the housing.

Abstract: A turbocharger can include a center housing; a bearing disposed in a through bore of the center housing where the through bore of the center housing defines a longitudinal axis; a shaft rotatably supported by the bearing; a compressor wheel operatively coupled to the shaft; a turbine wheel operatively coupled to the shaft; and a turbine housing assembly operatively coupled to the center housing where the turbine housing assembly includes: a turbine housing; and a cartridge that includes a nozzle wall component and a plate component that are spaced axially by spacers, where the nozzle wall component includes spacer bores for the spacers and where the nozzle wall component has a non-circular outer perimeter defined at least in part by arcs where adjacent arcs intersect at intersection points, and where each of the intersection points is radially outwardly from a respective one of the spacer bores.

Abstract: A debris monitoring system has a first sensor configured to generate a first signal indicating a presence of a metallic particle in a lubrication system. A second sensor is configured to generate a second signal indicating the presence of a metallic particle in the lubrication system. A signal processor is configured to determine a presence of a metallic particle in a fluid passage based on a comparison of at least the first signal and the second signal; the second signal being used to verify accuracy of the first signal. A gas turbine engine and a method for monitoring a fluid passage for debris are also disclosed.

Abstract: A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.

Abstract: A vane includes a pair of airfoils having a plurality of film cooling holes that extend through an exterior surface of the airfoils, the plurality of film cooling holes including at least a first subset of film cooling holes, wherein the first subset of film cooling holes break through the exterior surface at geometric coordinates set forth herein. Each of the geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.

Abstract: A turbocharger, including a turbine with a turbine rotor, a compressor with a compressor rotor coupled to the turbine rotor via a shaft. At least one bearing, via which the shaft is mounted in the bearing housing, wherein the respective bearing comprises a bearing bush mounted in the bearing housing in a rotationally fixed manner, wherein between the bearing bush and the bearing housing a radially outer lubricating gap and between the bearing bush and the shaft a radially inner lubricating gap is formed. The radially inner lubricating gap is suppliable with lubricating oil via at least one line introduced into the bearing bush, wherein the or each line introduced into the bearing bush, which serves for the oil supply of the radially inner lubricating gap, leads into a lubricating oil pocket of the bearing bush each, which based on the axial length of the bearing bush is placed off-center.

Abstract: A gas turbine engine having a core engine. The core engine includes an inlet, a compressor section, a combustion section, a turbine section, and an exhaust. The gas turbine engine also includes a bearing sump arranged in the core engine for containing lubrication, the bearing sump and lubrication having an operational range between at least about 0° F. and about 550° F.

Abstract: The invention relates to an exhaust casing for a turbine engine of an aircraft, including: a collar (4), a hub (5), hollow arms (63) connecting said collar (4) to said hub (5), and an opening piece (3) which is located on the collar (4) and is suitable for being connected to an outlet tube (30) of a transient-operation valve of the turbine engine. In said exhaust casing, said opening piece (3) is attached onto the collar (4) and forms an extension of a hollow arm (63) such that an air flow (7) leaving the outlet tube (30) of the transient-operation valve penetrates the hollow arm (63) and flows into the hub (5).

Abstract: A steam turbine drain structure includes a drain pocket for collecting drain water generated in a steam turbine, and a drain hole communicating with the lower side of the drain pocket. The steam turbine drain structure further includes a drain pan arranged below the exit of the drain hole and configured to collect drain water discharged from the drain hole, and a connection pipe one end of which is connected to the bottom portion of the drain pan and the other end of which is connectable to piping laid outside the steam turbine.

Abstract: A drive assembly for a gas turbine engine according to an exemplary embodiment includes, among other things, an epicyclic gear train having an input and an output, the input coupled to a first turbine, the output coupled to an accessory drive shaft, and at least one engagement feature on a component of the gear train. An actuator is engageable with the at least one engagement feature to cause the accessory drive shaft to rotate. A method of driving a section of a gas turbine engine is also disclosed.

Abstract: Modular cooling water assemblies for combined cycle power plant systems are disclosed. Each of the assemblies may include a pump and a heat exchanger, both positioned on a support structure. Additionally, each of the assemblies may include a closed cooling water system supported by the support structure. The closed cooling water system may include a return header fluidly coupled to a return conduit for receiving cooling water previously utilized by the combined cycle power plant system. The closed cooling water system may also include a supply header positioned adjacent the return header, and fluidly coupled to a supply conduit for supplying the cooling water to the combined cycle power plant system. Additionally, the closed cooling water system may include a closed cooling water circuit fluidly coupling the return header to the supply header. The closed cooling water circuit may be fluidly coupled to the heat exchanger and the pump.

Abstract: Disclosed are a power plant that uses a synchronous generator using a working fluid for generation of electric power, and a method of controlling the power plant, the power plant and the control method having an advantage of preventing damage to the power plant during synchronization with an electrical grid. The power plant comprises a pump for compressing a working fluid, a heat exchanger for heat transfer from an external heat source to the working fluid transferred from the pump, and a power turbine generator for generating a rotational force by using the working fluid heated by the heat exchanger, generating electricity using the rotational force, and supplying the electricity to an electrical grid.

Abstract: A system for actuating engine valves may include a valve bridge having a main event rocker interface portion, a first valve interface portion and a second valve interface portion extending in generally opposite directions from the main event rocker interface portion. The second valve interface portion may include an open end including a slot for receiving a bridge pin. The slot permits the valve bridge to be removed from the actuation system without removal of the main event rocker or other actuating components, such as an auxiliary rocker. The valve bridge can be removed from the valve train without requiring removal of other actuation system components, such as auxiliary rockers or main event rockers. A single valve bridge configuration can be used with different valve spans, which may occur among different cylinder sizes in a given engine family, or across different engine families.

Abstract: A sliding cam system for an internal combustion engine. The sliding cam system includes a cam shaft and a cam carrier, arranged rotationally fixedly and axially movably on the cam shaft. The cam carrier including a first shifting gate and a second shifting gate. The sliding cam system includes a first actuator with an element able to move along a longitudinal axis of the cam shaft, especially a pin, which can be brought into contact with the first shifting gate for the axial movement of the cam carrier in a first direction. The sliding cam system includes a second actuator with an element able to move along the longitudinal axis of the cam shaft, especially a pin, which can be brought into contact with the second shifting gate for the axial movement of the cam carrier in a second direction which is opposite to the first direction.

Abstract: A device for actuating at least one valve in an internal combustion engine includes a camshaft arrangement including a hollow outer shaft and an inner shaft, which is concentrically mounted inside of the outer shaft to be pivotable relative to the outer shaft. A first cam lobe is mounted on one of the inner shaft and the outer shaft in a rotationally fixed manner and a second cam lobe is mounted on the other of the inner shaft and the outer shaft in a rotationally fixed manner. The device further includes a rocker arm arrangement including a first primary rocker arm, which is arranged to follow the first cam lobe and arranged to actuate a first valve when it follows the first cam lobe. The rocker arm arrangement further includes an auxiliary rocker arm, which is arranged to follow the second cam lobe. The auxiliary rocker arm is adapted to actuate the first primary rocker arm so that an opening tune of the first valve may be extended by the auxiliary rocker arm following the second cam lobe.

Abstract: A spark-ignited gas engine system comprises a combustion chamber defined by a piston, a head with a spark plug mechanism, and a cylinder having an associated intake valve and an associated exhaust valve, into which a mixture of combustible gas and air is entered via an intake manifold of the engine to drive a crankshaft. The system further comprises at least one turbocharger to compress the mixture. The system further comprises at least one camshaft, driven by the crankshaft via a gear assembly connected to the crankshaft, that comprises at least one cam that actuates the intake valve and the exhaust valve, at least one camphaser, coupled to the crankshaft via the gear assembly, and a controller to adjust a cam angle operation of the intake valve and the exhaust valve by adjusting the camphaser to a desired phase position to meet a target rotational phase of the camshaft.