Abstract: Described herein are devices, systems, and methods for analyzing multi-phase fluid flow profile and flow field distribution by utilizing heating wires and thermal sensing arrays to detect transient thermal response and generate a dynamic temperature profile. The thermal sensing arrays include a plurality of thermal sensors disposed linearly along the length of the array. The multi-point dynamic temperature profile is used to determine fluid rate, velocity, flow patterns, and flow field distribution.

Abstract: In one aspect, a wellbore system is disclosed for determining breach of cement section in the wellbore, wherein the system includes a cement section in the wellbore formed to prevent flow of fluids including hydrocarbons through the cement section, nonradioactive tracers that emit radioactive emission when activated by a radiation source , a radioactive source that generates radioactive particles to activate the nonradioactive tracers that have migrated through the cement to cause the nonradioactive tracers to emit radiation, a detector for detecting the radioactive emission from the nonradioactive tracer, and a processor that determines from the detected radioactive emission a fluid leak through the cement section.

Abstract: An optical interface system is disclosed. In accordance with an embodiment, such a system includes an optical interface. A surface control system is coupled to a first end of the optical interface, and a logging tool coupled to an opposite second end of the optical interface. Data and/or power can be exchanged between the logging tool and the optical interface by converting electrical signals into corresponding optical signals which can be transmitted over the optical interface. Corresponding methods are also disclosed herein.

Abstract: A core cutting assembly is disclosed for use with a continuous mining machine having a milling drum. The core cutting assembly may have a drive mechanism configured to rotate about a first axis of the milling drum. The core cutting assembly may also have at least one rotary cutting bit powered by the drive mechanism to rotate about a second axis that is substantially orthogonal to the first axis.

Abstract: A system for determining the position and orientation of a cutter module relative to a frame of a highwall miner is provided. The cutter module is attached to the highwall miner by a string of push beams and moveable relative to the highwall miner. A reel is rotatably mounted to the highwall miner frame and configured to feed out a hose chain that supplies fluid to the cutter module. A fiber optic shape sensing system is associated with the cutter module is configured to receive strain information from the fiber bundle and compute the location of at least one position of the fiber bundle that is associated with the cutter module relative to the reference frame.

Abstract: Polymer Rubber Gel is heated to an elevated temperature and sprayed against the exposed rock to form a generally uniform surface. The Polymer Rubber Gel can be sprayed on the rock surface using a heated want coupled to a heated kettle. Then, a layer of I polyethylene is formed against the polymer rubber gel layer. Finally, a finish layer such as concrete, tile, brick or segmental wall block is placed against the outer side of the polyethylene layer.

Abstract: The present disclosure relates to a mining site comprising an extraction shaft passing through an ore body. Also included in the mining site are a lower shaft intersecting a path of the extraction shaft, a starting station extending from the lower shaft and from a bottom of the path of the extraction shaft, an arrival station overhanging above a top of the extraction shaft, and a upper shaft extending from the arrival station. In a particular aspect, the extraction shaft can be dug at a shallow angle between 10 and 45 degrees from horizontal. A shallow angle mining method for constructing the mining site is also provided. The present disclosure additionally introduces a hydro-electric site having a penstock dug at a shallow angle, and a method of digging a penstock.

Abstract: The invention relates to an artificial lifting system comprising a progressive cavity motor for hydrocarbon's extraction. In the invention's system a pump injects a fluid stored in the surface to the progressive cavity motor, located in the basement; the rotation that occurs by the passage of fluid is transmitted to a progressive cavity pump such that the hydrocarbon is pushed toward the surface.

Abstract: A circumferential airfoil array that provides a total airfoil count for the stage and that includes first and second sets of airfoils with different vibrational frequencies. First and second arcuate regions are arranged opposite one another and third and fourth arcuate regions are arranged opposite one another. The first set of airfoils has first primary, first secondary and first tertiary airfoil groups. The second set of airfoils has second primary, second secondary and second tertiary airfoil groups. The first primary airfoil group and second primary airfoil group are respectively arranged in the first and second arcuate regions. The first secondary airfoil group and second secondary airfoil group are arranged in the third arcuate region. The first tertiary airfoil group and the second tertiary airfoil group are arranged in the fourth arcuate region. The first and second arcuate regions provide greater than 50% of the total airfoil count.

Abstract: A turbomachine rotor blade milling machine system includes a fixture having a body including first and second opposing surfaces and a slot. The fixture is configured and disposed to connect with first and second rotor blade sections mounted in a rotor wheel. A mounting system includes at least one mounting element coupled to one of the first and second opposing surfaces of the body at the slot. A milling machine is coupled to the one of the first and second opposing surfaces through the at least one mounting element. The milling machine includes a cutter and is configured and disposed to form an opening extending axially through a dovetail portion of a third rotor blade section arranged between the first and second rotor blade sections.

Abstract: A compressor impeller assembly is disclosed. The compressor impeller assembly may have a compressor impeller having an impeller bore. The compressor impeller assembly may further have an insert screwed into the impeller bore, the insert having a threaded insert bore. The compressor impeller assembly may also have a shaft having a threaded shaft bore. In addition, the compressor impeller assembly may have a stud. The stud may have a first threaded portion engaged with the threaded insert bore. The stud may also have a second threaded portion engaged with the threaded shaft bore.

Abstract: A disc for a fan rotor (with a pilot to connect to a rotating shaft, a hub and a plurality of blades) includes a flat circular portion connecting to the pilot at an inner edge and to the hub at an outer edge; a plurality of first circular cooling holes of a first diameter located around the inner edge of the disc; and a plurality of second circular cooling holes of a second diameter located around the outer edge of the disc, wherein the second diameter is larger than the first diameter.

Abstract: A cooled gas turbine engine component comprises a wall which has a plurality of effusion cooling apertures extending there-through from a first surface to a second surface. Each aperture has an inlet in the first surface and an outlet in the second surface. Each aperture has a metering portion and a diffusing portion arranged in flow series and each metering portion is elongate and the width is greater than the length of the metering portion. The metering portion of each aperture has a U-shaped bend. The diffusing portion of each aperture is arranged at an angle to the second surface. Each outlet has a rectangular shape in the second surface of the wall. Each inlet has an elongate shape in the first surface of the wall and the inlet in the wall is arranged substantially diagonally with respect to the outlet in the wall.

Abstract: A gas turbine engine component, especially an aerofoil-sectioned nozzle guide vane (NGV), having at least one internal cooling chamber for passage of cooling air, the chamber including leading edge portion and one inlet portion via which cooling air may enter the chamber from feed source, wherein the component includes a partitioning element, e.g. curved or scoop-shaped partitioning plate or wall, provided in the chamber inlet portion and defining within the inlet portion a sub-chamber adjacent the leading edge portion, and wherein partitioning element is configured so the cooling air velocity in the sub-chamber is less than the cooling air velocity in the remainder of inlet portion. The reduced velocity of the cooling air in the sub-chamber adjacent the leading edge serves to increase pressure therein, thereby maintaining desired backflow pressure margin between the feed pressure of the cooling air delivered to the showerhead holes and the gas-path from the combustor.

Abstract: Fan for gas turbine engine includes hub and annular array of fan blades mounted to hub and extending radially outwardly from hub, each fan blade includes blade root. The hub includes plurality of hub grooves having shape complimentary to shape of blade root and each hub groove receives and radially retains one blade root. A slot is provided on the suction side and on the pressure side of each blade root. Plurality of keys is provided, each key engages with slots in one blade root and with corresponding hub groove so as to axially retain fan blade. The key includes two arms and joining member, two arms are received in slots provided on blade root and joining member extends between the arms. Interface is defined between key arms and slots in blade root, and greater or equal percentage of interface is curved than is planar.

Abstract: A lock apparatus securing a blade to a hub, the lock apparatus comprising a planar element having a spring actuable between an expanded position and a compressed position without deviation from the plane of the element, wherein in the expanded position of the spring the planar element is partly located in a slot provided in the blade, the spring being compressible to its compressed position to disengage the planar element from the slot.

Abstract: A slider for chocking a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc. The slider, in use, is slidingly inserted in an axially-extending cavity formed in the base of the root and in the disc at the base of the slot to urge the blade radially outwardly and thereby mate flanks of the root to flanks of the slot. The slider is arc-shaped and the cavity is correspondingly arc-shaped. The normal to the plane of the arc of the arc-shaped cavity is substantially perpendicular to the engine axis such that, when inserted in the cavity, the slider also retains the root axially in the slot.

Abstract: A nacelle for a gas turbine jet engine for an aircraft includes flow disruptors to provide boundary layer turbulence when the engine is exposed to air flow that is obtuse to direction of travel of the engine.

Abstract: A stator assembly includes a platform located on a radially inner end of a plurality of vanes that connects a first vane to a second vane. There is a platform groove on a radially inner side of the platform between the first vane and the second vane.

Abstract: The present invention describes a gas turbine having two shafts, which are rotatably mounted using bearing devices in the area of a casing. An intermediate shaft sealing device is arranged between the bearing devices, which includes a sealing element connected to a first shaft, in which a further sealing element connected to the second shaft radially engages. An operating pressure is applied, in the area limited by the shafts in the axial direction of the shafts, to facing effective areas of the sealing elements, while the pressure prevailing in the area outside the shafts in the axial direction acts on effective areas of the sealing elements facing away from one another. A ratio between the outer diameters limiting the facing effective areas and the inner diameters likewise limiting these effective areas is in each case greater than or equal to 1.25.

Abstract: A compressor seal assembly is disclosed. The compressor seal assembly may have a seal ring having a seal ring bore. The compressor seal assembly may also have a collar. The collar may have a cap portion having a first bore configured to receive an impeller. The cap portion may be disposed in the seal ring bore. The collar may further have a journal portion having a second bore configured to receive a shaft connectable to the impeller. The collar may also have a slinger disposed between the cap portion and the journal portion. The slinger may have a generally cylindrical shape and may have a front face. The slinger may also have a rear face opposite the front face. Further, the slinger may have a cylindrical side surface extending between the front face and the rear face. In addition, the slinger may have a groove disposed on the side surface.

Abstract: A brush seal plate may comprise a flat ring with bristles protruding from an inner diameter of the flat ring. The brush seal plate may have a racetrack slot to allow the flat ring to move in a radial direction relative to a retention pin. The bristles may protrude from the inner diameter of the flat ring at an angle. A slot may be formed through the flat ring, and the slot may be angled. The flat ring may be circumferentially discontinuous. The flat ring may further comprise a retention opening configured to fix the flat ring in place relative to a retention pin.

Abstract: A sealing element for positioning radially outwardly of aerofoil blades of a gas turbine engine is provided. A radially inner surface region of the sealing element includes a seal structure having one or more inwardly projecting walls formed by additive layer, powder fed, laser weld deposition. The walls form a plurality of curved profile shapes which are arranged in a repeating pattern across the radially inner surface region. None of the walls intersects with any other wall. The curved profile shapes have no radii of curvature less than 0.5 mm.

Abstract: A system includes a turbomachine rotor having a shaft and turbomachine blades coupled to the shaft. The system also includes a turbomachine stator having a shroud surrounding the turbomachine blades of the turbomachine rotor. Further, the system includes a cooling channel having at least a first portion of the cooling channel extending upstream of a final stage of a compressor of the system, where the cooling channel is configured to receive cooled compressed air from the compressor and direct the cooled compressed air adjacent to the turbomachine rotor to reduce thermal expansion and/or axial displacement of the turbomachine rotor.

Abstract: A compressor comprising a housing having an axial intake and an annular outlet volute, an impeller mounted for rotation about a shaft axis, the impeller having a plurality of blades, an annular diffuser passage surrounding the impeller extending from a diffuser inlet to a diffuser outlet, the impeller hub being mounted in an annular impeller recess in a first wall member of the diffuser, wherein an annular diffuser recess is provided in the first wall member extending radially outwardly from a first end to a second end, the first end being located at a radially outer end of the impeller recess, the second end being located axially inboard of the first end of the diffuser recess and wherein the depth of the diffuser recess at the first end of the diffuser recess is at least 30% of the maximum depth of the impeller recess.

Abstract: The invention relates to a turbine engine comprising a fixed structure (7), a fan (1) rotor (3), having an axis (XX) of rotation, and emergency braking means (12, 13) of the rotor (3), in particular in the event of the loss of a blade of the fan (1), characterised in that said emergency braking means (12, 13) comprise a first (18) and a second (22) member supported by the fixed structure (7), said members (18, 22) respectively being configured so as to interact frictionally with a first (20) element which is complementary to the rotor (3), by forming a stop of the rotor (3) towards the rear along the axis (XX), and a second (24) element which is complementary to the rotor (3), by forming a stop of the rotor (3) towards the front along the axis (XX), when the emergency braking means (12, 13) are active.

Abstract: A fan track liner assembly for a ducted fan engine which provides for ease of installation and replacement. The assembly includes a plurality of panels; and a plurality of fastening members which are arranged to secure the panels to the fan case of the engine, wherein: each fastening member has a base portion and an elongate arm member, and further wherein: the base portion has an attachment portion which is used to secure the fastening member to the fan case; and the arm member extends from the base portion, and each panel has slotted edge portions on opposing edges at one end of the panel which are each arranged to engage with respective arm members of fastening members on either side of the panel when the panel is assembled with the fastening members by sliding the panel onto the fastening members or vice-versa.

Abstract: A fan track liner assembly for ducted fan engine which provides for reduced strain and deformation of front of fan case in the event of a fan blade off event. Various assemblies are proposed. In one aspect, assembly includes fan track liner panel and plurality of fasteners which are arranged to secure panel to fan case of engine, wherein: a forward portion of panel includes hinged portion which operates as trapdoor to permit blade or blade fragment to pass through, and fasteners are arranged to fail in the event of blade or blade fragment passing through trapdoor causing panel to be displaced rearwards in fan case. Other aspects provide for reduced height of support on fan case for attaching fan track liner and for collapsible comb box.

Abstract: An aircraft gas-turbine engine having a fan mounted on a fan shaft and including several fan blades, where the fan shaft is mounted on an engine structure by means of an upstream fan bearing, when seen in the flow direction, and a downstream bearing, where at least one predetermined breaking point is provided in the area of the fan bearing, characterized in that at least one shock-absorbing element designed as metal fabric damper is arranged at a radial gap to have a parallel effect relative to the predetermined breaking point.

Abstract: A turbine bearing and seal assembly is disclosed. The turbine bearing and seal assembly may have a turbine cartridge. The turbine cartridge may have a compressor end and a turbine end opposite the compressor end. The turbine bearing and seal assembly may also have a bearing attached to the turbine cartridge. The bearing may be disposed between the compressor end and the turbine end. The turbine bearing and seal assembly may further have a seal collar attachable to a shaft. The seal collar may be disposed within the turbine cartridge adjacent the turbine end.

Abstract: A shroud support system with load spreading comprises a shroud hanger having a first wall and a second wall spaced apart in an axial direction by a retainer support wall, a ceramic matrix composite shroud segment disposed in the shroud hanger between the first and second walls and the retainer support wall, a retainer having circumferentially spaced first and second bolt holes, the retainer passing through the shroud, first and second bolts passing through the shroud hanger and engaging the first and second bolt holes of the retainer.

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, and a low spool including a low pressure compressor section and a low pressure turbine. A high spool includes a high pressure compressor section. A gear arrangement is defined along an engine axis. The low spool is operable to drive the fan section through the gear arrangement. A mount system includes an aft mount configured to react at least a portion of a thrust load at an engine case generally parallel to an engine axis.

Abstract: An exhaust system for an engine include a first exhaust system portion that receives exhaust from one or more combustion chambers of the engine. The exhaust system also includes an oxidation catalyst having an inlet and an outlet. The inlet of the oxidation catalyst is in fluid communication with the first exhaust system portion and receives exhaust from the one or more combustion chambers of the engine. The exhaust system also includes a second exhaust system portion that receives exhaust gases downstream from the outlet of the oxidation catalyst. A waste heat recovery system is in thermal communication with the second exhaust system portion that receives exhaust gases from the outlet of the oxidation catalyst. In some instances, the exhaust system may omit other aftertreatment components.

Abstract: A device for a valve train for switching over the lift of gas-exchange valves of an internal combustion engine comprising a camshaft on which at least one cam carrier with at least three different cam profiles is mounted so as to be non-rotatable and axially movable. The device includes an adjustment shaft arranged parallel to the camshaft and on which a first transmission element is mounted so as to be non-rotatable and axially movable, the first transmission element having a guide unit, a housing-fixed first guide element operatively connected to the guide unit, a second guide element operatively connected, on the one hand, to the guide unit and, on the other hand, to the cam carrier via a second transmission element, the second transmission element being connected to the cam carrier so as to be axially unmovable, and a push element operatively connected to the first transmission element.

Abstract: A device for a valve train for switching over the lift of gas-exchange valves of an internal combustion engine, the internal combustion engine including a camshaft on which at least one cam carrier with at least three different cam profiles is mounted so as to be torque-proof and axially movable. The device includes an adjustment shaft arranged parallel to the camshaft and on which a first transmission element is mounted so as to be torque-proof and axially movable, the first transmission element having a guide unit, a housing-fixed first guide element operatively connected to the guide unit, a second guide element that, on the one hand, is operatively connected to the guide unit and, on the other hand, to the cam carrier via a second transmission element, whereby the second transmission element is connected to the cam carrier so as to be axially immovable, and a push element.

Abstract: A ventilation system is disclosed for use with an engine having a crankcase The ventilation system may have a first source of compressed air and a second source of compressed air. The ventilation system may also have a plurality of oil separators, each in separate communication with the crankcase. The ventilation may system further have a distribution manifold in fluid communication with the plurality of oil separators, and a shuttle valve fluidly connected between the distribution manifold and the first and second sources of compressed air.

Abstract: A suppressor for a gaseous fuel system is disclosed. The suppressor may include a cylindrical body having a first end opposite a second end along an axis. A vent opening may be disposed at the second end. A conduit may pass through the first end and may have an inlet disposed outside the cylindrical body and an outlet disposed inside the cylindrical body. The suppressor may include an acoustic core between the outlet of the conduit and the vent opening and configured to reduce a sound level of fluids exiting the conduit. The suppressor may include a thermal mass between the outlet of the conduit and the vent opening, wherein the thermal mass includes fluid channels and is configured to transfer heat energy to fluids exiting the conduit.

Abstract: An exhaust gas purification apparatus for an internal combustion engine, capable of carrying out oxidation removal of PM deposited in a filter as a whole in an efficient manner, includes a filter arranged in an exhaust passage of the internal combustion engine and having an oxidation catalyst supported in at least an upstream side portion thereof, and a heating device arranged so as to be able to heat the upstream side portion of the filter irrespective of oxidation reaction heat of the oxidation catalyst, wherein when filter upstream regeneration processing to oxidize and remove deposition PM in the upstream side portion of the filter is carried out by controlling a heating device, an amount of decrease of the upstream side deposition PM by the filter upstream regeneration processing is reflected on an amount of filter PM deposition in the ordinary filter regeneration processing which oxidizes and removes the deposition PM in the entire filter by means of oxidation reaction heat of unburnt fuel generated by

Abstract: Filter for application in motor vehicles in general, urban or rural use, terrestrial, aquatic or aerial use, such as car, motorcycle, truck, bus, train, boat, ship, vessel, airplane, jet ski, snowmobile, tractor, any vehicle or machine powered by a combustion engine, electric, hybrid, hydrogen, gasoline, methanol, ethanol, butanol, diesel, kerosene, or any other technology or fuel, which can also be applied to any equipment using a combustion engine, like generators or turbines for stationary power generation, large water pump and agricultural equipment use, and aircraft powered by turbo-jets, turbo-fans, turbo propellers, piston engines or others, and may also provide versions for residential, commercial, industrial and hospital use, among others, with the addition of a power supply (transformer) on the power input and a possible adjustment in a cabinet with appropriate design for each use.

Abstract: A method at an exhaust gas cleaning system for an engine (235) in which a reducing agent is added to a passage (290) for exhaust gases from the engine (235) for cleaning the exhaust gases. The exhaust gas cleaning system includes arrangements (270) that require a certain temperature level (Tmax) in order to achieve catalytic exhaust gas cleaning. The method is to distribute and store (s430) a limited amount of reducing agent at temperature level (Tmax); and to use (s440) during a cold start of the exhaust gas cleaning system, the distributed and stored reducing agent to achieve the catalytic exhaust gas cleaning. Also a computer program product (200; 210) to implement the method. Also an arrangement for an exhaust gas cleaning system for an engine (235), and a motor vehicle (100) equipped with the arrangement.

Abstract: In an engine control method for maintaining performance of oxidation catalyst, fuel of a compressed natural gas engine under a lean-burn condition with an air-fuel equivalence ratio less than or equal to 1 is burned. Activation of the oxidation catalyst for purifying an exhaust gas of the engine is determined. Necessity of a regeneration mode for recovering catalytic activation of the oxidation catalyst according to an activation state of the oxidation catalyst and an operating condition of the engine is determined. And, the air-fuel equivalence ratio is increased to a range of from 1.10 to 1.20 when the oxidation catalyst is inactive and an engine speed is lower than a predetermined speed.

Abstract: A system is provided and includes a fuel module that, based on a crankshaft angle of an engine, generates a value indicative of an amount of fuel burned in a cylinder or a change in the amount of fuel burned. A heat release module, based on the value, determines an amount of heat released during a combustion event of the cylinder. A pressure module, based on the amount of heat released, estimates a pressure in the cylinder. A temperature module, based on the pressure, estimates a temperature in the cylinder. A concentration module, based on the pressure or the temperature, estimates nitrogen oxide concentration levels in the cylinder. An output module, based on the nitrogen oxide concentration levels, estimates an amount of nitrogen oxides. A control module, based on the amount of nitrogen oxides out of the cylinder, controls operation of the engine or an exhaust system.

Abstract: A silencer for a motor vehicle and in particular air intake or exhaust gas lines and/or HVAC air passageways is disclosed. The silencer includes a pipe arranged in a housing, which defines a duct and an annular orifice arrangement having a first annular orifice which extends from the pipe to the housing. The housing and pipe form a chamber arrangement with a first chamber and a second chamber, which are separated by the first annular orifice and communicate with the duct through apertures in the pipe. The housing is designed integrally with a first connector and the pipe integrally with a second connector, which communicate with the duct, and in particular merge into the duct.

Abstract: A method for operating a compression ignition engine includes forming a combustible mixture by mixing generally homogeneously a first fuel and air and introducing this mixture into the at least one cylinder, compressing the combustible mixture with the piston in a compression stroke, injecting a second fuel to the combustible mixture at an injection-time of the second fuel during the compression stroke but before start of combustion, and continuing the compression stroke until combustion starts at those locations in the at least one cylinder where concentration of the second fuel is highest and/or the temperature of the mixture is the highest. Emission of the cylinder and/or mechanical stress of the cylinder caused by the combustion are monitored, and if emissions and/or mechanical stress are above respective predetermined thresholds, individually for the cylinder, the amount and/or the timing of the second fuel injected, and/or temperature of the cylinder charge is changed.

Abstract: This disclosure relates to an improved prechamber device for an internal combustion engine. The prechamber device is positioned adjacent to a combustion chamber. The improved prechamber device is configured to improve removal of heat from the prechamber device, particularly in the area adjacent to the combustion chamber.

Abstract: Various methods and systems are provided for adjusting a turbine boost control actuator based on a single common reference value. In one example, a method for an engine includes adjusting a turbine boost control actuator to control an intake manifold pressure to a limit, the limit based at least in part on one or more of peak cylinder pressure, turbine speed, and a pressure difference across a turbine.

Abstract: Upon request for start-up of an engine, a control apparatus controls the opening/closing action of a waste gate valve in accordance with the temperature Te of the engine before cranking and, if the temperature Te of the engine is equal to or lower than a first set temperature Te1, sets the waste gate valve in an open state.

Abstract: A device of a system for air ducting of an internal combustion engine in a motor vehicle with a turbocharger arranged between an exhaust gas line and an intake line. The device includes a high pressure flow pathway with a valve branching from the exhaust gas line between the internal combustion engine and a turbine side of the turbocharger, a low pressure flow pathway with a valve branching in the flow direction of the exhaust gas downstream from the turbine side of the turbocharger, and an exhaust gas heat exchanger. A first flow pathway with a valve and a second flow pathway with a valve merge into a mouth region with a third flow pathway. At least one section of the high pressure flow pathway, the low pressure flow pathway, the flow pathways, and the exhaust gas heat exchanger are integrated inside a housing formed as a continuous compact unit.

Abstract: A process for the crystallisation of a water-soluble compound is disclosed. The process comprises (a) providing, in a crystallisation vessel, a solution of the water-soluble compound in a mixture of water and a solvent in which the water-soluble compound has a lower solubility than in water; (b) passing vapour phase of the mixture through a sorption zone containing a water vapour sorbent to selectively adsorb water from the vapour phase; (c) recycling a part of the vapour phase to the crystallisation vessel or withdrawing vapour phase depleted in water from the process and adding solvent to the crystallisation vessel; (d) allowing solid crystals of the water-soluble compound to precipitate from the solution; and (e) discharging precipitated solid crystals of the water-soluble compound from the crystallisation vessel and discharging a solution of non-crystallised water-soluble compound in water-solvent mixture from the crystallisation vessel.

Abstract: A reciprocating piston internal combustion engine includes at least one first, one second and one third cylinder and has a crank mechanism having a crankshaft, which is rotatably mounted in a crankcase, having a first, a second and a third crankpin. A first connecting rod having a first piston for the first cylinder is allocated to the first crankpin. A second connecting rod having a second piston for the second cylinder is allocated to the second crankpin. A third connecting rod having a third piston for the third cylinder is allocated to the third crankpin. The crankpins are arranged successively in an axial direction of the crankshaft, wherein the cylinders are arranged in a fan shape.