Abstract: An angular offset apparatus for determining an angular offset, or scribe line offset (SLO), of two objects within a drilling environment. The angular offset apparatus may include a sensing component and a target component located at various locations within the drilling environment. The sensing component may implement one or more sensors configured to collect data associated with the target component and the drilling environment to determine the SLO between the two objects. The angular offset apparatus, along with the calculated SLO, is designed to ensure accuracy and safety during drilling operations.

Abstract: Disclosed are systems and methods for positioning of downhole tools via radioactive tag detection. The method comprises positioning a radiation detector at a first position within a wellbore, logging radiation data while the radiation detector is moved from the first position to a position adjacent to or past a radioactive marker disposed within the wellbore, determining, based on the radiation data, a time at which the radiation detector is adjacent to the radioactive marker, and calculating, based on the time, a distance between the first position of the radiation detector and the radioactive marker.

Abstract: Generally, a sonde, associated components and methods are described which can be used in conjunction with an inground tool having an inground tool housing that defines an inground tool cavity such that the inground tool cavity is exposed to an ambient pressure environment which surrounds the inground tool during an inground operation. A sonde housing assembly includes an exterior configuration that is receivable within the inground tool cavity. The sonde housing assembly at least partially defines a sonde interior and is further configured for receiving the pressure sensor body of a pressure sensor in a pressure sealed engagement. A sonde electronics package is supported within the sonde interior and is at least configured to receive the pressure signal and transfer a corresponding pressure signal from the sonde.

Abstract: A multi-zone monitoring system allowing simultaneous measurement of separate zones of multi-zone wellbore formations comprising a multi-component umbilical containing both electrical lines and a hydraulic fluid lines, an inflatable isolation packer that can traverse through the wellbore and be inflated with hydraulic fluid to seal off a portion of the wellbore wherein the inflatable isolation packer is connected to a hydraulic line of the multi-component umbilical, wherein the inflatable isolation packer further comprises: one or more cable bypass feed throughs for the umbilical's electric and hydraulic fluid lines, wherein the hydraulic line is attached to the inflatable isolation packer with compression fittings.

Abstract: A system to monitor the retrieval of a well tool from a wellbore comprises a deployment member coupled to the well tool to retrievably insert the well tool in the wellbore. At least one first identification transducer is coupled to a top end of the well tool to transmit an identification signal during retrieval of the well tool. At least one second identification transducer is located at at least one axial location along a surface pressure control assembly to detect the identification signal. A controller is in data communication with the at least one second identification transducer to determine the position of the well tool relative to the pressure control assembly, and to output at least one command related to the position of the well tool relative to the pressure control assembly.

Abstract: A repeater system provided in a wellbore including a plurality of communication units spaced at intervals along a length of a wellbore, the communication units being communicatively coupled via a transmission medium. The communication units are configured to relay data from one communication unit to another communication unit selected from the plurality of communication units along the transmission medium, wherein at least one of the communication units is hopped over as data is relayed across the plurality of communication units along the length of the wellbore.

Abstract: A method for recovering data from a downhole tool in a wellbore includes measuring an electromagnetic signal using first and second sensors. At least a portion of the electromagnetic signal is transmitted by a downhole tool positioned in a first wellbore. The first and second sensors are each positioned at a different location along a length of a second wellbore. The electromagnetic signal measured by the first and second sensors is decoded to recover a property measured by the downhole tool.

Abstract: A rotary pulser for transmitting information in a mud pulse telemetry system of a drilling operation. The pulser has two rotors mounted adjacent each other so that obstruction of the passages formed between the blades in one pulser by the blades of the other pulser creates pressure pulses in the drilling fluid. Each rotor is separately controlled and can be rotated continuously in one direction or oscillated. The ability to rotate each rotor separately provides flexibility in the pulser's operating mode, so as to allow more efficient generation of pulses, and also enhances the ability of the pulser to clear debris that would otherwise jam or obstruct the pulser.

Abstract: An apparatus for estimating an ambient environment at which inorganic scale will form in a downhole fluid includes a stress chamber disposed in a borehole in a production zone at a location within a specified range of maximum pressure and configured to receive a sample of the fluid from the production zone and to apply an ambient condition to the sample that causes the formation of inorganic scale. An inorganic scale sensor is configured to sense formation of inorganic scale within the chamber and an ambient environment sensor is configured to sense an ambient environment within the chamber at which the formation of inorganic scale occurs. The apparatus further includes a processor configured to receive measurement data from the inorganic scale sensor and the ambient environment sensor and to identify the ambient environment at which the formation of inorganic scale occurs.

Abstract: An apparatus for estimating an ambient environment at which organic scale will form in a downhole fluid includes a stress chamber disposed in a borehole in a production zone at a location of maximum pressure and configured to receive a sample of the fluid from the production zone and to apply an ambient condition to the sample that causes the formation of organic scale. A sensor is configured to sense formation of organic scale within the chamber and an ambient environment sensor is configured to sense an ambient environment within the chamber at which the formation of organic scale occurs. The apparatus further includes a processor configured to receive measurement data from the organic scaling sensor and the ambient environment sensor and to identify the ambient environment at which the formation of organic scale occurs using the organic scaling sensor measurement data and ambient environment sensor measurement data.

Abstract: This disclosure relates to a system for removing road material. In an embodiment, the system may include a milling drum and at least one pick mounted on the milling drum. Furthermore, the pick may include polycrystalline diamond at least partially forming one or more working surfaces of the pick.

Abstract: A bit holder having a body that includes a forward end that is diametrically smaller than a lower end and a shank depending axially from the lower end of the body. A substantial portion of the body is substantially solid and the shank is generally cylindrical with a bore axially extending from a distal end of the shank towards the lower end of the body. The bit holder also includes an annular sleeve mounted circumferentially around the upper end of the body and is configured protect the upper end of the body and is configured to receive a bit or insert.

Abstract: In a system (3) for the tracking of milling material (26), comprising a milling machine (1) for milling a section (28) of a ground pavement (29) in a milling operation, a truck (14) for loading and transporting away the milling material (26) removed during milling of the section (28) of the ground pavement (29), a deposition site (24) for depositing the milling material (26) transported away by the truck (14), a first detection device (18) for detecting data signals relating to the milling material (26), it is specified for the following features to be achieved: that a second detection device (20) detects position data of the deposition site of the milling material (26), wherein the first and the second detection device (18, 20) transmit the data signals (60) relating to the milling material (26) and the position data of the deposition site (24) to a documentation device (22) which links the position data with the data signals relating to the milling material (26).

Abstract: A rotary engine including a housing and housing head enclosing a combustion chamber, a piston including an output shaft and a piston disk within the housing and rotatable on a piston rotation axis, a quadrant within the housing and around the piston and rotatable on a quadrant rotation axis, wherein the quadrant rotation axis is acutely angled to the piston rotation axis, and a post surrounding a segment of the piston disk. The post pivots relative to the piston about a post-piston rotation axis that is normal to the face of the piston disk. The post pivots relative to the quadrant about a post-quadrant pivot axis that is perpendicular to the quadrant rotation axis. The post rotates about the quadrant rotation axis relative to the housing. Combusting fuel injected into the combustion chamber expands and pushes on the piston disk to rotate the output shaft about the piston rotation axis.

Abstract: A turbocharger impeller is provided with a hub portion with a plurality of vane portions extending outwardly thereof. The hub portion is substantially shaped as a truncated cone with a diameter that gradually increases along a rotation axis. The vane portions are formed on a surface of the hub portion and guide a fluid flowing along the rotation axis radially outward relative to the hub portion. Grooves are formed in and/or on surfaces of the vane portions along a direction of the fluid flowing radially outward during rotation of the impeller. Protruding crest portions are formed between adjacent grooves. Crest portions in a central region near the rotation axis are lower in height than crest portions in an outer region further away from the rotation axis.

Abstract: A rotor disc assembly includes a rotor disc and a minidisc. The rotor disc has a first extension member, a first finger, and a second finger. The first extension member axially extends from a disc body disposed about an axis. The first finger extends axially from the first extension member. The second finger is circumferentially spaced apart from the first finger. The second finger extends axially from the first extension member. Each of the first finger and the second finger has a first portion and a second portion that extends radially from a distal end of the first portion. The minidisc is operatively connected to the rotor disc. The minidisc has an interlocking finger that radially extends from a minidisc body and is disposed between the first finger and the second finger. The interlocking finger, the first portion, and second portion define a ring groove.

Abstract: A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage formed therein that extends from a connection with a coolant source at the root to at least the approximate radial height of the platform. The platform cooling arrangement includes a platform slot formed through at least one of a pressure side slashface and a suction side slashface, the platform slot being in fluid communication with a high-pressure coolant region of the turbine rotor blade. An insert inserted in the platform slot, the insert having a blind channel extending inside the insert. The insert aligns with the platform slot to fluidly connect the channel to the high-pressure coolant region. At least one passage is in fluid communication with the channel and an exterior region of the turbine rotor blade.

Abstract: An airfoil for a gas turbine engine is disclosed. The airfoil may include a first portion including a first slot, a second portion including a second slot, and a biscuit disposed within the first slot and the second slot. The first portion and the second portion may be joined by the biscuit. A method for constructing an airfoil is also disclosed. The method may include making a first slot on a sheath, the first slot sized to fit a first part of a biscuit; making a second slot on a body, the second slot sized to fit a second part of the biscuit; and joining the sheath and the body together through a biscuit joint, the biscuit disposed within the first slot and the second slot.

Abstract: A component for a gas turbine engine includes a gas path wall having a first surface, a second surface exposed to hot gas flow, and a cooling hole extending through the gas path wall. The cooling hole includes an inlet formed in the first surface, an outlet formed in the second surface, cooling hole surfaces that define the cooling hole between the inlet and the outlet, and a longitudinal ridge formed along at least one of the cooling hole surfaces. The longitudinal ridge separates the cooling hole into first and second lobes. The cooling hole diverges through the gas path wall, such that cross-sectional area of the cooling hole increases continuously from the inlet through the cooling hole to the outlet.

Abstract: A blade for a rotor of a gas turbine has: a root, a platform having a lower surface and an upper surface opposite to the lower surface, a hollow aerofoil, an inner cooling passage inside the hollow aerofoil for channelling a first cooling medium to a first plurality of outlet cooling holes on an external surface of the hollow aerofoil, a channel, separated from the first cooling circuit, extending through the platform for channelling a second cooling medium from at least one opening of the channel to a second plurality of outlet cooling holes provided on the upper surface of the platform. The at least one opening of the channel is provided on the lower surface of the platform in order to receive in operation the second cooling medium from an inner cavity of the rotor.

Abstract: A component for use in a turbine engine includes a fore edge connected to an aft edge via a first surface and a second surface. Multiple cooling passages are defined within the turbine engine component. A first skin core passage is defined immediately adjacent one of the first surface and the second surface. At least 80% of coolant entering the first skin core passage is expelled from the turbine engine component at the aft edge.

Abstract: A gas turbine engine component includes a structure having a wall that provides an exterior surface. A first cooling passage is arranged adjacent to and interiorly of the wall. A second cooling passage is arranged in the wall and provides a first fluid flow direction. A resupply channel is arranged in the wall and is fluidly interconnected to the second cooling passage. A resupply hole fluidly interconnects the first cooling passage and the resupply channel. The resupply channel is transverse relative to the second cooling passage to provide a second fluid flow direction that extends from the resupply hole to the second cooling passage.

Abstract: A blade includes a leading edge, a trailing edge, a pressure surface, a suction surface, a root end, a tip end, a tip shroud attached to the tip end, the tip shroud comprising a platform and a fin, wherein the fin having a leading edge side facing towards the leading edge of the blade, a trailing edge side facing towards the trailing edge of the blade, a back end and a front end, the leading edge side and the trailing edge side extending between the back end and the front end, the fin extending across the tip end of the blade at an angle to the chord of the blade at the tip end of the blade. A first platform portion extends from the leading edge side of the fin to the suction surface. A second platform portion extends from the trailing edge side of the fin to the pressure surface at the tip end of the blade.

Abstract: A device such as a drum for positioning at least one guide blade row from a plurality of guide blade groups in a turbomachine, the device on the outer circumferential side including at least one flange for attachment to a housing section of the turbomachine and on the inner circumferential side including a plurality of uniformly distributed receptacles for accommodating holding elements of the guide blade groups and a plurality of recesses, the device having a depth-reduced inner circumferential section, relative to the accommodating grooves, between at least two adjoining receptacles, which extends in each case from the one receptacle to the other receptacle; a blade-device combination; a method for assembling such a blade-device combination; and a turbomachine.

Abstract: A turbine nozzle disposed in a turbine includes a suction side extending between a leading edge of the nozzle and a trailing edge of the turbine nozzle in an axial direction and transverse to a longitudinal axis of the turbine nozzle, and extending a height of the nozzle in a radial direction along the longitudinal axis, a pressure side disposed opposite the suction side and extending between the leading edge of the turbine nozzle and the trailing edge of the turbine nozzle in the axial direction, and extending the height of the nozzle in the radial direction, and a bulge disposed on the suction side of the nozzle protruding relative to the other portion of the suction side in a direction transverse to a both the radial and axial directions.

Abstract: A turbine includes a rotor shaft having a plurality of rotating blades mounted on the rotor shaft, a bearing assembly rotatably supporting the rotor shaft, a casing forming a passage of a fluid and to include a space in which the rotating blades are disposed so that thermal energy of the fluid is converted into mechanical energy by rotation, a foundation fixedly supporting the bearing assembly, and a packing device installed in the rotor shaft for sealing between the casing and the rotor shaft and supported by the foundation. The casing comprises a connection unit extended toward the packing device and fixed to the casing so that a location of the connection unit is relatively changed with respect to the packing device. Accordingly, there is an advantage in that the leakage of a fluid is reduced because a clearance between the packing device and the rotor shaft is reduced.

Abstract: A magnetic seal system adapted for use within a support structure mounted around a rotatable shaft. The magnetic seal system includes two annular seal assemblies configured to be surrounding the shaft to rotate therewith and be axially displaceable along the shaft. Each annular seal assembly includes an annular member adjacent to an annular seal. The magnetic seal system also includes an annular magnet configured to be sealingly connected to the support structure and surrounding the shaft The magnet being disposed between the two annular seals in a non-contacting relationship with the shaft and biasing the two annular members along the shaft towards the magnet, wherein adjacent contacting surfaces between each of the two annular seals and the magnet biasingly mate to form sealing interfaces.

Abstract: An airfoil device for a gas turbine has a root section mountable to an airfoil disc and an airfoil element. The root section has a platform at which the airfoil element is arranged. The root section has a cavity surrounded by an inner surface of the platform, a first and a second edge side of the root section. A seal strip is arranged at the inner surface, wherein the first edge side has a recess into which a first end section of the seal strip is arranged. The root section has a supporting lever extending from the second edge side into the cavity. The supporting lever is formed such that a further cavity is formed between the inner surface, the second edge side and the supporting lever, wherein the second end section of the seal strip is arranged inside the further cavity.

Abstract: The present disclosure generally relates to variable cellular structures, methods of making such cellular structures, and variable cellular flow discouragers for turbine engines for jet aircraft.

Abstract: A thermal barrier coating (TBC) with depth-varying material properties is formed on a turbine component. Exemplary depth-varying material properties include physical ductility, strength and thermal resistivity that vary from the TBC layer inner to outer surface. Exemplary ways to modify physical properties include application of plural separate overlying layers of different material composition or by varying the applied material composition during the application of the TBC layer. Various embodiment described herein also apply a calcium-magnesium-aluminum-silicon (CMAS)-retardant material over the TBC layer to retard reaction with or adhesion of CMAS containing combustion particulates to the TBC layer. In other embodiments the CMAS retardant material is also applied within engineered groove features (EGFs) that are formed in the TBC surface.

Abstract: A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. At least one cooling fin is disposed on the radially outer face between the leading edge portion and the trailing edge portion.

Abstract: A blade tip clearance system includes first and second control rings. The first control ring has a first coefficient of thermal expansion (CTE) and a first thermal response rate. The second control ring is located radially outward of and operatively connected to the first control ring and has a second CTE that is different from the first CTE and a second thermal response rate that is different from the first thermal response rate. Thermal expansion and contraction of the first and the second control rings controls a radial position of the blade tip clearance system relative to a rotating blade component.

Abstract: A system includes a stator assembly including at least one stator airfoil. The system also includes a rotor assembly including at least one rotor airfoil configured to rotate about an axis. The system also includes an actuator coupled to the stator assembly and configured to actuate the stator assembly in an axial direction relative to the rotor assembly, creating an axial movement such that a clearance between the at least one rotor airfoil and the stator assembly varies based on an axial position of the stator assembly.

Abstract: The present disclosure relates to a tip clearance control assembly of a gas turbine including a casing, a plurality of blades, a labyrinth seal, and a shroud. The casing guides a flow of combustion gas. The plurality of blades is located inside the casing in such a manner as to be coupled to a rotary shaft of the gas turbine. The labyrinth seal is located at the front end portion of each blade. The shroud surrounds the front end portion of each blade. The casing includes an outer casing having dove tail slots and an inner ring segment having dove tail coupling portions, so that the dove tail coupling portions moves in an axial direction and a radial direction with respect to the gas turbine.

Abstract: A method of making safe operation of a rotary assembly of a turbomachine including a turbine and a rotary machine, the method anticipating an event of exceeding a predetermined threshold speed by repetitively performing a prediction cycle including: measuring magnitudes relating to operation of the turbomachine, including real speed of rotation of its rotary assembly; based on the magnitudes, estimating driving and resisting torques applied to the rotary assembly; preparing a representative value representative of the difference between these two torques; and calculating a predicted speed of rotation for the rotary assembly at a given time horizon based on the representative value and the real speed of rotation. An action is taken on the operation of the turbomachine to limit an extent to which its rotary assembly exceeds the threshold speed in the event of the predicted speed of rotation exceeding the threshold speed.

Abstract: The present disclosure is directed to a system and method for in-situ (e.g. on-wing) cleaning of gas turbine engine components. The method includes injecting a dry cleaning medium into the gas turbine engine at one or more locations. The dry cleaning medium includes a plurality of abrasive microparticles. Thus, the method also includes circulating the dry cleaning medium through at least a portion of the gas turbine engine such that the abrasive microparticles abrade a surface of the one or more components so as to clean the surface.

Abstract: A fluid cooling system for use in a gas turbine engine including a fan casing circumscribing a core gas turbine engine includes a heat source configured to transfer heat to a heat transfer fluid and a primary heat exchanger coupled in flow communication with the heat source. The primary heat exchanger is configured to channel the heat transfer fluid therethrough and is coupled to the fan casing. The fluid cooling system also includes a secondary heat exchanger coupled in flow communication with the primary heat exchanger. The secondary heat exchanger is configured to channel the heat transfer fluid therethrough and is coupled to the core gas turbine engine. The fluid cooling system also includes a bypass mechanism coupled in flow communication with the secondary heat exchanger. The bypass mechanism is selectively moveable based on a temperature of a fluid medium to control a cooling airflow through the secondary heat exchanger.

Abstract: A housing for retention of the outer race of a bearing of a gas turbine engine includes an arrangement of spring fingers that yields a lightweight housing capable of withstanding very high radial loads combined with very high torsional windup and axial thrust load. Controlled circumferential gaps on both sides of each spring finger limit the deflection and self-arrest the distortion of the housing. The spring fingers define at least one side edge that extends at an angle relative to the axial direction. An axial gap is created on the aft end by a portion of the spring finger beam structure that opposes an axial face of the housing and limits the axial distortion. A radial gap created between interface hardware of the housing and the inner retention housing also acts to retain the spring finger housing under load in a radial direction.

Abstract: An alignment system includes a first visual indicia and a second visual indicia disposed on a first mobile unit, and a third visual indicia and a fourth visual indicia disposed on a second mobile unit. The alignment system also includes a visual inspection area configured to enable collective viewing of the first visual indicia, the second visual indicia, the third visual indicia, and the fourth visual indicia along a single direction. The alignment system is configured to align the first mobile unit with the second mobile unit along a vertical axis, a horizontal axis, and a rotational axis to help align a rotational coupling between the first mobile unit and the second mobile unit.

Abstract: A thermal energy storage system includes one or more components from a Rankine Cycle power plant such as steam turbine and other equipment. The system can include a thermal storage material, a heat source that is heated by running electricity through a heating element for heating the thermal storage material, and a heat exchange for generating steam using the thermal energy stored in the thermal storage material. The system can be configured to store energy during periods of low electricity demand or abundant supply. The system can be configured to generate electricity using the stored thermal energy to generate steam and run one or more turbines.

Abstract: A system and method for supplying an energy grid with energy from an intermittent renewable energy source having a production unit for producing Hydrogen and Nitrogen, a mixing unit configured to receive and mix the Hydrogen and the Nitrogen produced by the production unit, an Ammonia source for receiving and processing the Hydrogen-Nitrogen-mixture, an Ammonia power generator for generating energy for the energy grid, a heat distribution system with one or more heat exchangers, and an Ammonia cracker, which is fluidly connected to the Ammonia storage vessel and to the Ammonia power generator, and which is configured and arranged to receive Ammonia from the Ammonia storage vessel, to effect a partial cracking of the received Ammonia to form an Ammonia-Hydrogen-mixture and to direct the Ammonia-Hydrogen-mixture to the Ammonia power generator for combustion.

Abstract: A method for generating power from a heat source includes mixing a refrigerant in a liquid phase with a lubricating oil, heating the mixture to evaporate the refrigerant, mixing the heated mixture with additional refrigerant in a superheated phase, and atomizing the lubricating oil to disperse the lubricating oil within the refrigerant. The atomized lubricating oil and the refrigerant are passed through a decompressor to generate an electrical current. The refrigerant may be an organic material having a boiling point below about ?35 C. Related systems and heat engines are also disclosed.

Abstract: A method and a device for recovering heat from an engine and for converting the heat into mechanical energy using an expansion machine. A heat accumulator fluid is guided in a primary circuit by means of a primary pump and is firstly heated by the waste heat of the combustion engine by means of a heat exchanger, is transferred into a heat accumulator and recirculated to the first heat exchanger, and, secondly, the heat accumulator fluid is guided in a secondary circuit by said heat accumulator fluid being extracted in the vapor state from the heat accumulator and being supplied to the expansion machine, and being condensed by means of a condenser downstream thereof and being recirculated into the heat accumulator by means of a secondary pump. The primary circuit of the heat accumulator fluid is connected to the secondary circuit exclusively via the heat accumulator.

Abstract: Various embodiments include a system having: at least one computing device configured to perform actions including: measuring at least one of the following parameters: a steam pressure within a steam drum, a load on a GT, a position of a bypass valve bypassing an HRSG, and a steam flow rate through the steam drum; defining a threshold range for each of: a steam pressure within the steam drum, a load on the GT, a position of the bypass valve bypassing the HRSG and a steam flow rate through the steam drum based upon the measured data and a target steam level; and adjusting the steam flow rate through the steam drum in response to at least one of the measured parameters deviating from the corresponding threshold range.

Abstract: A device for recovery of waste heat generated during operation of an internal combustion engine includes a thermodynamic engine, which includes a working fluid circulation circuit and is configured for recovery of the waste heat a first arrangement for providing a first coolant from a first source for heat exchange with the working fluid in the working fluid circulation circuit, and at least one further arrangement for providing a further coolant from a further source for heat exchange with the working fluid in the working fluid circulation circuit, wherein the further source is at different heat level than the first source during operation of the internal combustion engine.

Abstract: A rocker arm may comprise a body defining a pivot aperture and include a pad spaced away from the pivot aperture a predetermined distance. The pad may include a peripheral surface and a top surface that defines a blind aperture, forming an intersection therewith, and the top surface may include a plurality of aligning features disposed around the blind aperture.

Abstract: In variable displacement engines, a portion of the intake valves have deactivatable valve lifters. When the engine conditions are such that some of the cylinders are to be deactivated, the intake and/or exhaust valve lifters in those cylinders are deactivated. Operation of the mechanism inside the lifter that is actuated to deactivate the valves can be harmed when particles in the engine oil get inside. To prevent small particles entering the valve lifter, a small filter is provided just upstream of the orifice into which oil enters the valve lifter. In other embodiments, a wire mesh formed into a coil is inserted into the recess. In some applications, a cage with snap-fitting connectors is installed over the filter to keep the wire mesh in place and properly coiled. The cage also fits into the recess. Such filter may also be applied to a hydraulic lash adjuster feature in a lifter.

Abstract: A method to control a four-stroke combustion engine, comprising at least one cylinder; a piston arranged in each cylinder; at least one inlet valve arranged in each cylinder which is connected with an inlet system; at least one first camshaft which controls each inlet valve; at least one exhaust valve arranged in each cylinder which is connected with an exhaust system; at least one second camshaft which controls each exhaust valve; and a crankshaft which controls each camshaft. At least one phase-shifting device is arranged between the crankshaft and the second camshaft, to phase-shift the second camshaft in relation to the crankshaft to a state, where the exhaust valve is controlled in such a way, that it is opened during the expansion stroke of the engine and closed during the exhaust stroke of the engine, to achieve engine braking through compression in the cylinders during the exhaust stroke.

Abstract: An internal combustion engine having an improved oil treatment system. The internal combustion engine may be a splash lubrication engine in which oil is flowed through an oil circulation circuit by a passive pump. In another aspect, a dipstick tube may be provided that includes a portion of the oil circulation circuit. In a further aspect, the internal combustion engine comprises one or more protuberances that automatically penetrate an oil treatment apparatus upon the oil treatment apparatus being mounted to the internal combustion engine, thereby fluidly coupling the oil treatment apparatus to the oil circulation circuit.

Abstract: An evaporative emission control canister system comprises an initial adsorbent volume having an effective incremental adsorption capacity at 25° C. of greater than 35 grams n-butane/L between vapor concentration of 5 vol % and 50 vol % n-butane, and at least one subsequent adsorbent volume having an effective incremental adsorption capacity at 25° C. of less than 35 grams n-butane/L between vapor concentration of 5 vol % and 50 vol % n-butane, an effective butane working capacity (BWC) of less than 3 g/dL, and a g-total BWC of between 2 grams and 6 grams. The evaporative emission control canister system has a two-day diurnal breathing loss (DBL) emissions of no more than 20 mg at no more than 210 liters of purge applied after the 40 g/hr butane loading step.