Abstract: The present invention relates to a method of determining present-day horizontal stresses in geological formations. The method comprises dividing the received well data in a plurality of contiguous sets of data i, a set of data For each set of data i in the plurality of sets of data, determining, at least parameters Pi, a pressure in subsoil i, bi, a Biot coefficient i, ?i, a Poisson's ratio i, ??i, a vertical constraints in subsoil i, Ei, a Young's modulus i, ?i, a thermal expansion coefficient, and Ti, and a subsoil temperature. The method further comprises, i, computing and outputting the horizontal constraints.

Abstract: The present invention is a hydraulically operated splitting device with a piston cylinder unit comprising an extending chamber and a retracting chamber in which a piston is supported, displaceable in an extending direction and a retracting direction, allowing the extending chamber and the retracting chamber to be impinged with pressurized hydraulic medium for moving the piston at a displacement speed, a cylinder housing at which a plurality of pressure pads is supported, displaceable perpendicular to the extending direction and the retracting direction, a wedged lance connected to a piston rod of the piston and mobile with said piston, which engages wedge-shaped pressure areas of the pressure pads complementary to the wedged lance, and moves the pressure pads perpendicular to the extending direction and the retracting direction, a lubrication unit by which lubricant can be inserted from a lubricant reservoir to an area between the wedged lance and the pressure pads, with the splitting device comprising a prot

Abstract: A load bearing support includes a cylindrical drum. A top portion, a bottom portion, a tapered cylindrical sidewall extends between the top and bottom portions. A core member extends between the top and bottom portions, and a load-bearing material is disposed between the sidewall and the core member. An opening extends through the top portion of the drum to receive load-bearing material. Each of the top portion and the bottom portions has a reinforcing chime. The core member includes a lateral transfer zone defined at one or more points along a vertical axis of the core member. The lateral transfer zone distributes an axial load on the drum to the cylindrical sidewall. The cylindrical sidewall provides a radial expansion area for compression of the core member and the load-bearing material.

Abstract: A feed apparatus for feeding cement to a cement silo of a mining machine includes a receptacle for receiving cement, a transfer tube connected at a first end of the receptacle for guiding the cement from the receptacle to the cement silo connectable at a second end of the transfer tube and transfer means arranged in connection with the transfer tube and arranged to move cement within the transfer tube from the receptacle to the cement silo. The transfer tube includes at least one transfer tube section having a tube-like inner space for cement to be transferred.

Abstract: Disclosed herein is a method comprising mixing a carrier liquid with particles and/or with a particle precursor to form a suspension or solution respectively; where the particles comprise a metal oxide; and where the particle precursor comprises a metal salt; injecting the suspension or solution through a plasma flame; and depositing the particles and/or the particle precursor onto a substrate to form an first abradable coating; where the first abradable coating comprises a plurality of cracks or voids that are substantially perpendicular to the substrate surface, where the substrate is a hub surface of a gas turbine engine or where the substrate is a cantilever stator.

Abstract: A gas turbine rotor includes a first rotor and a second rotor. The first rotor includes a compressor impeller, a turbine wheel, and a shaft. The turbine wheel has a common rotational axis with the compressor impellor. The shaft connects the compressor impeller to the turbine wheel. The second rotor is an electric generator rotor and defines an inner hollow space. The shaft includes an insertable portion disposed in the inner hollow space of the second rotor.

Abstract: The invention relates to the field of turbomachine blades, and more specifically to a leading-edge shield (32) for a turbomachine blade (16), said leading-edge shield (32) having a pressure-side wing (34) and a suction-side wing (36), each extending along a height and along a length, the wings being connected together over their height, the pressure-side wing (34) presenting a greater length than the suction-side wing (36) over a first segment (S1) of the leading-edge shield (32), and an equal or smaller length than the suction-side wing (36) over a second segment (S2) of the leading-edge shield (32).

Abstract: An airfoil for a turbine engine can include a body having an outer wall defining a pressure side and a suction side, and the body can extend axially between a truncated nose and a trailing edge. A shield can be positioned upstream of the nose to define a leading edge for the airfoil.

Abstract: Airfoils and airfoil cores for airfoils of gas turbine engines are provided. The airfoils include an airfoil body having a leading edge and a trailing edge, at least two serpentine flow cavities formed within the airfoil body, a resupply cavity fluidly connected to one serpentine flow cavity of the at least two serpentine flow cavities and arranged to supply a resupply air to the one serpentine flow cavity through a resupply bypass hole, a junction defined at a location where the resupply cavity fluidly connect to the one serpentine flow cavity, a separator rib within the airfoil body and fluidly separating part of the at least two serpentine flow cavities, at least one crossover rib located between the resupply bypass hole and the separator rib, and at least one crossover aperture located between the at least one crossover rib and the separator rib.

Abstract: A turbine airfoil (10) includes a flow displacement element (26A-B, 26A?-B?) positioned in an interior portion (11) of an airfoil body (12) between a pair of adjacent partition walls (24) and comprising a radially extending elongated main body (28). The main body (28) is spaced from the pressure and suction side walls (16, 18) and further spaced from one or both of the adjacent partition walls (24), whereby a first near wall passage (72) is defined between the main body (28) and the pressure side wall (16), a second near wall passage (74) is defined between the main body (28) and the pressure side wall (18) and a central channel (76) is defined between the main body (28) and a respective one of the adjacent partition walls (24). The central channel (76) is connected to the near wall passages (72, 74) along a radial extent.

Abstract: A gas turbine engine assembly includes a supporting component and a supported component. The supporting component includes features engaged by the supported component. The supported component comprises ceramic-containing materials.

Abstract: A stationary-blade-type rotating machine is provided with a rotational shaft, an impeller, an impeller housing having a scroll passage formed on an outer peripheral side of the impeller, a bearing housing connected to the impeller housing in an axial direction of the rotational shaft, a stationary blade disposed in a radial passage formed between the scroll passage and the impeller and defined by an impeller-housing-side member and a bearing-housing-side member which face each other in the axial direction of the rotational shaft. The fixation unit includes an annular circumferential groove formed in an inner peripheral surface of the impeller housing and a ring-shaped fitting member subjected to a force for expanding in a radial direction while being fitted into the circumferential groove. The fitting member is configured to press the stationary blade to the impeller housing via at least one of the impeller-housing-side member or the bearing-housing-side member.

Abstract: A nozzle assembly group for a combustion chamber of an engine, with multiple nozzles for introducing fuel into the combustion chamber that are arranged next to each other, wherein each nozzle has a nozzle outlet opening and a fuel channel for conveying fuel in the direction of the nozzle outlet opening. According to the invention, it is provided that at least two different types of nozzles are provided, wherein the nozzles of different types have nozzle outlet openings with an identical cross section, and for predetermining different flow rates of fuel through the fuel channels of the nozzles of different types, a cross section of a fuel channel of one type of nozzle is different from a cross section of a fuel channel of another type of nozzle.

Abstract: The present disclosure is directed to a turbomachine airfoil including an exterior wall having a trailing edge. The exterior wall defines a radially-extending cooling cavity and one or more trailing edge cooling passages extending through the exterior wall. Each trailing edge cooling passage includes an inlet in fluid communication with the cooling cavity and a first portion in fluid communication with the inlet. Each trailing edge cooling passage also includes a second portion in fluid communication with the first portion. The second portion includes a first outlet defined by the exterior wall at the trailing edge. Each trailing edge cooling passage further includes a third portion in fluid communication with the first portion. The third portion includes a second outlet defined by the exterior wall at the trailing edge. The second and third portions are separated by a rib extending upstream from the trailing edge.

Abstract: A gas turbine engine vane or blade comprises a plurality of micro-structures disposed on an internal surface of the outer wall. The micro-structures may comprise an array of fins having a thickness of less than 0.002?, for example. Cooling air may be impinged upon the surface and routed through at least one flow channel to convectively cool the outer wall. Additionally or alternatively, micro-channels may be disposed along a suction side wall and pressure side wall of the vane or blade to convectively cool the respective walls. An embodiment of a vane or blade in accordance with the present invention may be constructed from a plurality of thin metal foils, stacked and bonded together.

Abstract: The invention relates to a flow arrangement for placing in the hot gas duct of a turbomachine, having a first surrounding-flow structure and a second surrounding-flow structure, the surrounding-flow structures each having, in reference to the surrounding flow in the hot gas duct, a leading edge and, downstream thereof, a trailing edge, wherein the second surrounding-flow structure is provided as a deflecting blade with a suction side and a pressure side and has a lesser profile thickness than the first surrounding-flow structure, which is arranged on the suction side of the second surrounding-flow structure, and wherein, although the second surrounding-flow structure has a partial axial overlap with the first surrounding-flow structure referred to a longitudinal axis of the turbomachine, the trailing edge of the second surrounding-flow structure is, at the same time, displaced axially downstream relative to the trailing edge of the first surrounding-flow structure.

Abstract: A seal device includes a plurality of seal shoes, a seal base, a plurality of spring elements and a resilient biasing element. The seal shoes are arranged around an axis. The seal base circumscribes the seal shoes. Each of the spring elements is radially between and connects a respective one of the seal shoes and the seal base. A first of the spring elements includes a first mount, a second mount and a spring beam. The first mount is connected to a first of the seal shoes. The second mount is connected to the seal base. The spring beam connects the first mount to the second mount. The resilient biasing element is radially between and engaged with first and second components of the seal device, where the first component is configured as or otherwise includes the first mount or the second mount.

Abstract: A gas turbine engine may include a liftoff carbon seal assembly. Liftoff carbon seal assembly may include a static seal support structure, a magnetic carrier spring assembly coupled to the static seal support structure, a nonferrous metal slab magnetically associated with the magnetic carrier spring assembly and coupled to the static seal support structure. In various embodiments, a combination of the magnetic carrier spring assembly and the nonferrous metal slab create a counter-force using an eddy current to oppose a motion of the magnetic carrier spring assembly.

Abstract: A method for reducing the leakage of an organic working fluid operating within a turbine (10) of an Organic Rankine Cycle system, the method comprising the injection of a fluid flow rate (Q) into a volume (I) at a static pressure lower than the total pressure (P1) upstream of the turbine and located near of at least one labyrinth seal (L1, L11) of at least one stage of the turbine (10), said fluid flow rate (Q) having an initial exergetic content lower than the initial exergetic content of the organic working fluid located inside the turbine and flowing through said labyrinth seal (L1, L11).

Abstract: A disclosed gas turbine engine includes a shroud block including a mounting slot, a blade outer air seal supported within the mounting slot and a seal disposed within the mounting slot providing a seal between the blade outer air seal and the mounting slot. An anti-rotation tab is attached to the shroud block within the mounting slot for constraining movement of the seal within the mounting slot.

Abstract: A seal assembly includes a seal arc segment defining first and second seal supports. A carriage defines first and second support members with the first support member supporting the seal arc segment in a first ramped interface and the second support member supporting the seal arc segment in a second ramped interface such that the seal arc segment is circumferentially moveable with respect to the carriage. The seal assembly includes an anti-rotation interface in which the seal arc segment and the carriage are engaged. The anti-rotation interface restricts circumferential movement of the seal arc segment.

Abstract: A gas turbine engine includes a turbine and a rotor tip clearance control system. The rotor tip clearance control system is configured to actively manage a clearance formed between a rotor of the turbine and a case structure of the turbine.

Abstract: A method for operating start-up of a compressor train is disclosed. The train includes a driver machine and at least a centrifugal compressor drivingly coupled to the driver machine. The centrifugal compressor in turn includes a plurality of compressor stages and at least a first set of variable inlet guide vanes at an inlet of one of the compressor stages. The method includes at least partly closing the first set of variable inlet guide vanes; when the first set of variable inlet guide vanes is at least partly closed, starting rotation of the centrifugal compressor and accelerating the centrifugal compressor up to a minimum operating speed; opening the at least one set of variable inlet guide vanes to increase the gas flow through the centrifugal compressor once the minimum operating speed has been achieved.

Abstract: In one embodiment, a plant control apparatus controls a power plant that includes a combustor to burn fuel with oxygen introduced from an inlet guide vane to generate gas, a gas turbine driven by the gas from the combustor, a heat recovery steam generator to generate steam using heat of an exhaust gas from the gas turbine, and a steam turbine driven by the steam from the heat recovery steam generator. The apparatus controls an angle of the inlet guide vane before a start of the steam turbine to a first angle, controls the angle of the inlet guide vane after the start of the steam turbine to a second angle larger than the first angle, and reduce the angle of the inlet guide vane from the second angle to the first angle or more during the predetermined period.

Abstract: A variable-pitch vane assembly for a gas turbine engine includes a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin. A turbine section of a gas turbine engine includes a turbine rotor and a turbine stator. The turbine stator includes one or more variable-pitch vane assemblies including a sync ring, a vane having a vane arm, and a pin installed through the sync ring and through the vane arm. The pin includes an anti-rotation notch located along a pin shaft. An anti-rotation spacer is engaged with the pin at the anti-rotation notch to prevent rotation of the pin.

Abstract: A unison ring assembly for a gas turbine engine has a unison ring and a plurality of levers extending from the unison ring. Each lever has a pin at one end that inserts through a bore of a respective bush mounted in the unison ring. Each bush is formed as separate first and second parts which are mounted to their through-hole by inserting the first part into the through-hole from one side of the unison ring and the second part into the through-hole from the opposing side of the unison ring. Each part has a respective stop which prevents that part from inserting into the through-hole by more than a predetermined amount. When both parts are inserted by their predetermined amounts, their ends join together to form the bush and prevent the parts being retracted from the through-hole.

Abstract: In combination a wear indication sensor and a component of a gas turbine engine is provided. The wear indication sensor is secured to a first surface of the component of the gas turbine engine. The wear indication sensor comprises: a first terminal; a second terminal electrically connected to the first terminal; two or more of resistors electrically connecting the first terminal to the second terminal, each of the two or more resistors including a first end electrically connected to the first terminal and a second end electrically connected to the second terminal, wherein each of the two or more resistors has a known resistance; and a first electrode electrically connecting the first terminal to the first end of each of the two or more resistors; wherein the first end of each of the two or more resistors is electrically connected to the first electrode through primary conductive lines.

Abstract: A deicer device deices both a splitter nose and inlet guide vanes of an aviation turbine engine. The device includes a splitter nose to split a stream coming from the fan into primary and secondary stream flow channels of annular shape and an inner shroud to which inlet guide vanes are fastened and including a hook that holds the inner shroud axially at its upstream end against the inner annular wall. An outer surface facing of the hook forms an angle of less than 90° with an injection orifice such that the outer surface comes progressively closer to the outer annular wall on going away from the injection orifice. The outer surface of the hook presents a minimum amount of clearance J relative to the outer annular wall such that 0.2?J/D?0.6 where D is the hydraulic diameter of an injection orifice.

Abstract: An acoustic damper includes a housing with an inlet aperture and an outlet aperture. The housing is configured to receive a gas flow that enters via the inlet aperture and that exits via the outlet aperture. The acoustic damper also includes a barrier member that is disposed within the housing. The barrier member is configured to be disposed within the gas flow and to dampen acoustic energy that propagates in an upstream direction generally from the outlet aperture toward the inlet aperture. The barrier member includes an outer structure that defines an interior volume of the barrier member. The interior volume is oriented toward the outlet aperture.

Abstract: A vibration absorber which, in the broadest sense, is based on a pendulum device for dampening undesirable vibrations which occur in a very slender structure, such as a wind turbine. The undesirable vibrations are caused by an acting force, in particular wind force. The invention thereby relates to vibration absorbers in which the pendulum mass can be temporarily stopped or braked, either entirely or partially, by an electromagnetic brake. The power supply or the current regulation of the electromagnetic brake correspondingly controls the braking function of the electromagnetic brake.

Abstract: Provided is a structure in which nozzles of a turbine of a gas turbine and a shroud of the turbine are supported by a turbine casing. Each nozzle includes an outer circumferential flange having a front end portion and a rear end portion respectively engaged with an inner circumferential portion of the turbine casing, a front end portion of the shroud is engaged with the rear end portion of the outer circumferential flange located frontward thereof, a rear end portion of the shroud is engaged with the front end portion of the outer circumferential flange located rearward thereof, and the nozzle and the shroud are supported by the turbine casing through a support pin penetrating a superposition engagement portion at which engagement portions of the turbine casing, the outer circumferential flange, and the shroud are radially superposed on each other.

Abstract: Methods and apparatus to adjust hydrodynamic designs of a hydrokinetic turbine are disclosed herein. An example turbine to be placed in a body of water includes a generator having a frame, an inlet, a first set of vanes disposed in the inlet, a second set of vanes, and a shroud. The inlet, the first set of vanes, the second set of vanes, and the shroud are removably coupled to the frame. The first set of vanes in removably coupled to the inlet.

Abstract: A combined heat and power system is provided with a Rankine cycle passage, a heat medium passage, an evaporator, an expander, a condenser, a pump, a temperature sensor, a sensor, and a controller. The evaporator receives the heat from the heat medium to heat a working fluid. The temperature sensor detects the temperature of the heat medium after radiating heat for heating the working fluid. The sensor detects the pressure of the working fluid flowing between the outlet of the evaporator and the inlet of the expander. The controller adjusts the rotation speed of the pump based on the temperature detected by the temperature sensor, and in addition, adjusts the rotation speed of the expander based on the pressure detected by the sensor.

Abstract: There is disclosed an energy storage system. In particular, there is disclosed a chemisorption based energy storage system, able to provide electricity, heating or cooling depending on the desired energy output. The energy storage system includes a first chemical reactor containing a first sorbent material and a second chemical reactor containing a second sorbent material. The first and second chemical reactors are in mutual fluid connection such that a refrigerant fluid can flow from the first chemical reactor to the second chemical reactor, and from the second chemical reactor to the first chemical reactor. The first and second chemical reactors are further provided with means for putting heat in to, or taking heat out of, the first and/or the second chemical reactors. A heat exchanger module is also provided.

Abstract: The present disclosure relates to a hybrid power generating system comprising a power generating system using supercritical CO2 configured to use the supercritical CO2 as a working fluid and a liquefied natural gas (LNG) treatment system configured to vaporize LNG, where the working fluid is cooled in at least one of the power generating system using supercritical CO2 and the LNG treatment system and is re-circulated to the power generating system using supercritical CO2.

Abstract: Provided is a metering plate for a poppet-style valve in which the metering plate includes a peripheral edge structure that reduces the impact of edge variation as a result of typical manufacturing tolerances. The peripheral edge structure is located at the sealing surface and extends from the peripheral surface of the metering plate so as to avoid a sharp edge at the outer diameter of the metering plate. In embodiments, the peripheral edge structure is a chamfered surface or a curved surface. Small dimensional deviations from these surfaces resulting from typical manufacturing tolerances do not have a significant effect on the discharge coefficient of the metering plate. In this way, the discharge coefficients of poppet-style valves across a fluid admission system are contained in a much tighter range, thereby enhancing the efficiency of and control over the fluid admission system.

Abstract: A continuously variable valve lift system includes a driving swing arm, a camshaft, a valve structure, a control shaft and an adjusting swing arm. The valve structure includes a roller rocker arm and a valve connected to the roller rocker arm. The driving swing arm has a driving arc surface. The driving arc surface contacts with the roller rocker arm to drive the valve to perform a reciprocating movement. The driving swing arm is sleeved on the control shaft and is capable of swinging around the control shaft. The control shaft is provided with a mounting part. The adjusting swing arm is connected to the mounting part and is capable of swinging relative to the mounting part. The adjusting swing arm is disposed between the camshaft and the driving swing arm. Two sides of the adjusting swing arm are contacted respectively with the camshaft and the driving swing arm.

Abstract: A lubrication system in a machine includes a sump to collect a bulk portion of lubricant and a pump adapted to circulate the lubricant from the sump through a lubricant line to an area of the machine for lubrication. The lubrication system also includes an oil filter disposed along the lubrication line adapted to filer the lubricant flowing through the lubricant line. The lubrication further includes an additive fixture in fluid flow communication with the oil filter adapted to house at least one additive material section and distribute the additive material in a lubrication flow circulation.

Abstract: A lubrication system for a machine includes a sump to collect a bulk portion of a fluid lubricant and a pump adapted to circulate the lubricant from the sump through a lubricant line to a lubrication target area of the machine. The lubrication system also includes a dip stick defining a first end outside of the machine, a second end immersed in the bulk portion of lubricant, and a lubricant level indicator between the first end and the second end. The lubrication system further includes an additive fixture coupled to the second end of the dip stick. The additive fixture includes at least one additive material section adapted to dissolve in the lubricant to distribute an additive chemical in lubricant circulating through the machine.

Abstract: A lubricant additive dispensing system includes a cartridge defining an inner cavity to house at least one additive material section and a release opening in communication with a lubrication circulation system of a machine. The lubricant additive dispensing system also includes a spring element arranged to bias the at least one additive material section towards the release opening and a release lever arranged to selectively retain the at least one additive material sections within the cartridge. The lubricant additive dispensing system further includes an actuator coupled to the release lever wherein actuation of the release lever ejects a next one of the at least one additive material sections into the lubrication circulation system.

Abstract: A mechanical fluid clearing device for clearing a mechanical device of remaining trapped fluids using an air compressor with a coupled first air hose terminating in a coupling. A second air hos connects to the first air hose and terminates in an airflow interface. The airflow interface mates to a fluid fill hole of a mechanical device providing for airflow to enter the device and blow trapped fluid out through an opening. The airflow interface includes a multi-tiered mating for attaching to multiple types of fluid fill holes.

Abstract: The lubricant level within a reservoir is difficult to monitor, leading to the reservoir being refilled more often than necessary to ensure that the reservoir always contains lubricant. A lubricant level sensing system is connected to and monitors various aspects of the pump assembly that draws lubricant from the reservoir. The pump assembly displaces a known volume of lubricant with each pump stroke. A lubricant-level estimator calculates an estimated lubricant level remaining in the reservoir based on a stroke-count value as sensed from the pump assembly and on a reference value stored in a memory. The estimated lubricant level provides the lubricant remaining and the rate of usage such that maintenance can be scheduled ahead of time to prevent the reservoir running dry.

Abstract: A muffler devised particularly for a small, reciprocating-piston two-stroke internal combustion engine of the type used on unmanned aerial vehicles. The muffler comprises a body incorporating an inlet, an outlet, and a plurality of chambers for exhaust gas flow from the inlet to the outlet. The body is configured to present a compact profile for installation on the engine. The chambers are so configured that adjacent chambers communicate to facilitate exhaust gas flow from the inlet to the outlet via flow passages. The various chambers comprise an inner chamber, an outer chamber, and one or more intervening chambers disposed between the inner and outer chambers. The various chambers are disposed one about another in annular formation. This arrangement creates a long flow path from the inlet to the outlet incorporating various directional changes.

Abstract: Method for forming a collar in a muffler shell including: providing a muffler shell made of a metal sheet and forming a muffler housing, the muffler shell having an exhaust gas opening, providing a collar forming head having a rotational axis and at least two movable expanders, introducing a collar forming head into a muffler housing, moving the expanders of the collar forming head introduced into the muffler shell radially away from the rotational axis of the collar forming head from a retracted position to an expanded position rotating the collar forming head around the of the collar forming head, bringing the rotating expanded collar forming head in contact with the metal sheet forming an outwardly projecting collar around the exhaust gas opening by flaring the edge of the metal sheet.

Abstract: A condensate separator for separating condensate from a gas stream, the condensate separator may include a housing having a condensate drain at a bottom end, a swirl generator provided at an inlet end of the housing, the swirl generator placing the gas stream in a rotational movement, and an impact element situated downstream from the swirl generator.

Abstract: A honeycomb structure provided with cell walls which partition the inside of a cylindrical outer skin having openings at both ends, and a large number of cells which are surrounded by the cell walls and provided in parallel in an axial direction of the cylindrical outer skin. At least part of the large number of cells include a protruding piece. The protruding piece forms a through-hole which penetrates the cell wall, and a protruding wall which protrudes inward of the cell at an angle from an edge of the through-hole.

Abstract: Methods and systems are provided for adjusting engine compression ratio (CR) and spark timing to attain particulate filter (PF) regeneration temperature. In one example, a method may include, in response to PF load reaching a threshold and PF temperature being lower than the PF regeneration temperature, lowering the CR and then selectively adjusting spark timing based on an estimated residual gas fraction (RGF) at the lower CR.

Abstract: An exhaust gas purification system for a construction machine prevents deterioration of an aqueous urea solution remaining in a conduit of an aqueous urea solution replenishing circuit after replenishment. An aqueous urea solution return circuit returns, to an aqueous urea solution tank, an excessive aqueous urea solution that has not been injected from an aqueous urea solution injection device into the exhaust gas, and is provided with a first return conduit that connects the aqueous urea solution injection device to the aqueous urea solution tank and a second return conduit that connects the aqueous urea solution injection device to a conduit of an aqueous urea solution replenishing circuit. An injection valve opening pressure of a first check valve provided in the first return conduit is set higher than an injection valve opening pressure of a second check valve provided in the second return conduit.

Abstract: A method of adjusting reductant injection for a selective catalyst reduction device with a soot filter (SCRF) includes calculating, through a processor, an amount of soot in the SCRF, determining, through the processor, a shrinking core model of the SCRF based on the amount of soot, calculating, with the processor using the shrinking core model, an amount of reductant to inject into the SCRF, and injecting the amount of reductant into the SCRF.

Abstract: An exhaust purification system includes an exhaust passage. Exhaust gas flows through the exhaust passage. A burner is arranged in the exhaust passage. A combustion space for fuel in the burner is a part inside the exhaust passage. A NOx adsorbent is located downstream of the combustion space in the exhaust passage. The NOx adsorbent adsorbs nitrogen oxide contained in the exhaust gas. A selective reduction catalyst is located downstream of the NOx adsorbent in the exhaust passage. An adding valve is located between the selective reduction catalyst and the combustion space in the exhaust passage. A connection passage is connected to the adding valve. Urea water flows through the connection passage toward the adding valve. A part of the connection passage runs through the combustion space.