Abstract: A compressor for a turbine engine includes an annular row of blades including a first blade with an extrados surface and a second blade with an intrados surface; and a connecting surface joining the intrados surface to the extrados surface, the connecting surface having a bulge of volume VB and a recess of volume VC, the bulge and recess forming a contouring 3D. The volume of the bulge VB is greater than four times the volume VC of the recess, the connecting surface includes a flat or axisymmetric band circumferentially separating the bulge from the recess, and the bottom of the recess being formed against the intrados surface.

Abstract: An anti-rotation assembly may include a first shaft, a second shaft, and a locking sprocket. The first shaft may have a first crenelated end rim, the second shaft may have a second crenelated end rim, and the locking sprocket may be configured to engage the first crenelated end rim and the second crenelated end rim to anti-rotatably couple the first shaft to the second shaft. That is, the locking sprocket may be configured to prevent relative rotation between the two shafts. The anti-rotation assembly may further include an axial retaining ring configured to axially retain the locking sprocket.

Abstract: A combination including a seal (36-38) for sealing a gap (s) between blade platforms (11, 21) of two adjacent blades of a turbomachine and a reducer (31; 32-34) for reducing vibrations of at least one of the blades, the seal including at least one rib (36) having a rib thickness and at least one wall (37) having a wall thickness that is smaller than the rib thickness and/or the reducer including a tuning-element guide housing (32) having at least one cavity (33) in which at least one tuning element (34) is disposed with play for impacting contact with the tuning-element guide housing.

Abstract: A low-pressure compressor for an axial-flow turbomachine, such as a jet engine, includes an annular row of vanes and a between-vanes passage with a connecting surface that links the pressure surface of a first vane to the suction surface of a second vane of the row. The connecting surface includes a main protuberance which includes a first elevation and a second elevation that are spaced apart from one another.

Abstract: In an axial turbomachine low-pressure compressor, the compressor, or booster, includes a first vane with an intrados surface, a second vane with an extrados surface, an inter-vane passage with a guiding surface, which connects the intrados surface to the extrados surface delimiting an annular vein, and which has a bulge and a recess forming a so-called 3D contouring geometry, or non-axisymmetric surface. The guiding surface includes an axially symmetrical or substantially flat zone, which axially extends through the inter-vane passage so as to separate the recess from the bulge.

Abstract: An aerofoil having a leading edge and a trailing edge, the leading edge including a plurality of slits extending toward the trailing edge, such that the leading edge is defined by alternating peaks and troughs. Each peak extends in a generally spanwise direction and defines a peak width, each peak being separated from an adjacent peak in the spanwise direction by a trough. Each trough extends in the generally spanwise direction and is spaced in a chordwise direction from the peak, each trough defining a trough width. A ratio of the peak width to the trough width is between 4:1 and 10:1.

Abstract: A modified J-type cantilevered vane reduces rubbing of an airfoil and enhances the vibration stability of a vane hub and the fluidity of fluid. The cantilevered vane includes a root attachment inserted into a slot formed in an inner circumferential surface of a casing of a gas turbine, and an airfoil vertically extending from the root attachment to a predetermined height. The airfoil includes a linear part extending in a radial direction from the inner circumferential surface of the casing toward a rotating shaft of the gas turbine, and a curved part integrally formed with the linear part, the curved part including a bend beginning from one end of the linear part and curving in a circumferential direction of the rotating shaft. Overall, the linear part and the curved part are biased in the circumferential direction, since the airfoil has a J-shaped X-axis profile and a C-shaped Y-axis profile.

Abstract: A power generator for generating power using a liquid that can alternatively flow at a lower flow rate and at a higher flow rate. The power generator includes a conduit and a rotor mounted in the conduit so as to be rotatable about a rotation axis. The rotor includes a top set of blades provided in a conduit top portion and configured for rotating about the rotation axis when the liquid flows at the higher flow rate in the conduit. The rotor also includes a bottom set of blades provided in a conduit bottom portion and configured for rotating about the rotation axis when the liquid flows at the lower flow rate in the conduit. An output shaft protrudes from the conduit and is rotatable by at least one of the top and bottom sets of blades. The top and bottom blades have different configurations.

Abstract: A turbine blisk is provided. The turbine blisk includes an inner rim, a plurality of adjacent rotor blades extending radially outward from said inner rim, a shroud segment integrally coupled to each of the plurality of adjacent rotor blades, thereby forming a plurality of adjacent shroud segments, and a gap defined between each of the adjacent shroud segments. The gap has a geometry that facilitates interlocking the plurality of adjacent shroud segments when a torsional force is applied to the plurality of adjacent rotor blades.

Abstract: A compressor wheel assembly (200) includes a compressor wheel (140) and a coupling member (230). The compressor wheel (140) is formed of a polymeric material. The compressor wheel (140) includes a hub (202), blades (204) extending from a forward surface (210) of the hub (202), and a shaft coupling portion (206) extending axially rearward from a rearward surface of the hub (202). The shaft coupling portion (206) includes a bore (208) extending therethrough and having a polygonal cross-sectional configuration. The coupling member (230) includes a head (232) and a body (234) extending axially from the head (232). The head (232) is received against a forward end (216) of the compressor wheel (140) and the body (234) extends through the bore (208). The body (234) has another polygonal cross-sectional configuration for transferring torque from the coupling member (23) to the compressor wheel (140).

Abstract: Disclosed is a gas turbine including a housing, a rotor rotatably provided in the housing to transfer a rotary force to a compressor, the compressor receiving the rotary force from the rotor and compressing air, a combustor mixing a fuel with the compressed air supplied from the compressor and igniting the mixture of the fuel and the air to generate combustion gas, and a turbine receiving the rotary force caused by the combustion gas generated by the combustor and rotating the rotor by using the received rotary force.

Abstract: The casing assembly comprises a casing comprising a slot defined by a front surface and a rear surface, the front surface and the rear surface being spaced apart by an axial casing gap. A plurality of stator vanes comprising a platform and at least one aerofoil extending from the platform, the platform being received within the slot and having an axial length and a circumferential length. Circumferential lengths of the platforms define a total circumferential length which is less than the circumference of the casing at an outer radial surface of the platforms and so defines a circumferential clearance. Axial length of each of the platforms is less than the axial casing gap and so defines an axial clearance. Circumferential and axial clearances allow the platforms of the stator vanes to rotate within the slot, with rotation of the platforms from an unrotated position reducing the circumferential and axial clearance.

Abstract: A guide vane for a turbomachine is disclosed. The guide vane includes a heat pipe wall that is interpenetrated by a capillary system, which has a continuous material transition from a first surface, which delimits the guide vane toward the outside, to a second surface, which lies opposite to the first surface and delimits an evaporation cavity in the interior of the guide vane. Further disclosed is a method for producing a guide vane having a heat pipe wall, wherein at least the heat pipe wall is formed by additive manufacture.

Abstract: A variable guide vane assembly is provided for a turbine defining a core air flowpath. The variable guide vane assembly includes an airfoil band defining a flowpath surface and a cavity. The variable guide vane assembly further includes an airfoil including a first end extending at least partially into the cavity of the airfoil band and an opposite second end, the airfoil extending generally along an axis between the first end and the second end and being moveable generally about the axis relative to the airfoil band. The variable guide vane assembly further includes a sealing element operable to form a seal between the first end of the airfoil and the airfoil band.

Abstract: A support case for a turbomachine ring sector includes an annular body around a longitudinal axis of the case, and a downstream edge for attachment of the ring sector. The downstream edge extends from the body radially towards the inside of the case. The downstream edge extends circumferentially along a junction region between the body and a fixed vanes stage. The junction region includes a central portion and two lateral portions located on each side of the central portion, along a circumferential direction of the case with respect to its longitudinal axis. The central portion projects radially outwards from the case with respect to the lateral portions.

Abstract: An assembly including a sector of fixed blades for turbomachine distributor including at one circumferential end a protuberance and at another circumferential end a contact surface, such that the protuberance of a sector arrives opposite the contact surface of another adjacent sector, a detachable cap including a surface with anti-wear material, configured to be engaged detachably on the protuberance of the sector, such that the anti-wear material is in contact with the contact surface of the other sector.

Abstract: A blade outer air seal includes a body that extends axially between forward and aft rails and circumferentially between lateral faces. The body has an inner arcuate surface that is configured to seal relative to a blade tip. The body includes a plurality of cooling holes that extend through an exterior surface of the body. Each of the plurality of cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Tables 1, 2 and 3. Each of the geometric coordinates is measured from a reference point on the body.

Abstract: An assembly in a turbine engine having a dynamically moveable flowpath boundary member for encasing a rotatable bladed disc and maintaining a clearance gap between the flowpath boundary member and the blade tips of the bladed disc. The assembly comprises a static casing, a flowpath boundary member carried by the casing, and a refrigeration system configured to remove heat from the flowpath boundary member to thereby thermally expand and contract the flowpath boundary member to control blade tip clearance.

Abstract: A gas turbine engine is provided. The gas turbine engine comprising: a fan section having a fan; and a containment zone encircling the fan, the containment zone comprising: a ballistic liner composed of a plurality of ring segments located radially outward of the fan; wherein each of the plurality of ring segments include two opposing circumferential ends, and wherein the plurality of ring segments are arranged circumferentially around the fan section and the circumferential ends of each of the plurality of ring segments meet at joints to form the ballistic liner.

Abstract: A gas turbine engine including a first rotor assembly is generally provided. The first rotor assembly includes outer drum and an outer drum airfoil. The outer drum airfoil is coupled to the outer drum and extended inward along a radial direction. A damper structure is coupled to one or more of the outer drum or the outer drum airfoil.

Abstract: A turbomachine, with a flow-conducting assembly, which on a first side serves for the flow-conduction of a first medium, which has a first temperature, and which on a second side is coolable with a second medium, which has a second temperature, that is lower than the first temperature, and with an impingement grille including openings which extend spaced from the flow-conducting assembly, wherein via the openings of the impingement grille the second medium is directable onto the second side of the flow-conducting assembly. In the region of at least some of the openings of the impingement grille, flow-conducting elements for the second medium are formed, which emanating from the impingement grille extend in the direction of the second side of the flow-conducting assembly to be cooled.

Abstract: A bearing bush of a turbocharger for radially mounting a shaft of the turbocharger. The bearing bush on an inner surface facing the shaft to be mounted, which forms a running surface of the bearing bush, has a microstructuring of multiple cup-shaped recesses at least in sections. The recesses have a maximum depth.

Abstract: A bearing device for an exhaust gas turbocharger, comprising a first radial bearing and a second radial bearing, the radial bearings radially support a shaft with an axis of rotation of the exhaust gas turbocharger, and wherein a first outflow gap and a second outflow gap, respectively, are formed between the first radial bearing and a radially extending first supporting wall of the turbocharger, which faces a turbine wheel of the exhaust gas turbocharger for axially supporting the first radial bearing, and the second radial bearing and a radially extending second supporting wall of the turbocharger, which faces a compressor wheel of the exhaust gas turbocharger for axially supporting the second radial bearing. The first outflow gap and/or the second outflow gap is configured inclined or curved relative to the axis of rotation for the axial and simultaneously radial support and/or for the backup of the radial support.

Abstract: A starter supplemental lubrication system for a gas turbine engine is provided. The starter supplemental lubrication system includes a pneumatic starter operable to drive rotation of a rotor shaft of a gas turbine engine through an accessory gearbox. The pneumatic starter is configured to receive a primary lubricant flow at a first rotational speed range and receive a supplemental lubricant flow at a second rotational speed range that is less than the first rotational speed range. The starter supplemental lubrication system also includes a supplemental lubricant pump operable to supply the supplemental lubricant flow at the second rotational speed range.

Abstract: An assembly is provided that includes a first component, a second component, a plurality of retainers and a fastener. The first component is configured with a plurality of first apertures. The second component is configured with a plurality of second apertures. Each of the retainers includes a pin and an arm projecting out from an end of the pin. The pin of each of the retainers is mated with a respective one of the first apertures and a respective one of the second apertures. The fastener is configured to fixedly connect the aim of each of the retainers to the first component.

Abstract: A tunable compliant mount structure for an engine such as a turbine engine can include a fluid conduit coupled to a fan casing by a connector. At a junction between the connector and the fluid conduit, a compliant mount structure can provide compliance and can be tuned to operate under variable stresses at the junction. The compliant mount structure can include a set of nested convolutions to provide compliance. The geometry of the convolutions can be used to tune the compliance, stiffness, or directionality. The tunable compliant attachment structure provides for additive in-situ manufacturing at the fluid conduit.

Abstract: Aspects are directed to removing a portion of a component that includes wear to generate a void in the component, where a material of the component has a first microstructure, depositing a filler material in the void, subjecting the filler material to a cold working technique to compress the filler material, and applying a heat treatment to cause the filler material to have a second microstructure that is matched to the first microstructure. Aspects are directed to a case of an engine, including: a first portion with a first material that has a first microstructure, and a second portion with a second material that has a second microstructure, where the second microstructure is matched to the first microstructure, where the second material includes a plurality of layers, and where at least one layer of the plurality of layers includes a compressive residual stress.

Abstract: A support member for supporting a turbine assembly during installation is provided. The support member includes a platform having a plurality of modular platform components oriented to define an upper surface of the platform. The support member also includes a linear actuator selectively positionable on the upper surface of the platform. The support member further includes a column selectively positionable on the linear actuator. The platform, the linear actuator, and the column are sized to support the turbine assembly.

Abstract: A heat cycle system includes a cooling circuit and a Rankine cycle circuit in which an organic medium circulates. The Rankine cycle circuit includes an evaporator, an expander, and a condenser. Before warm-up of an engine, a control device executes a warm-up mode in which the organic medium is circulated through the condenser, the expander and the evaporator in sequence; after the warm-up of the engine, the control device executes a waste heat recovery mode in which the organic medium is circulated through the evaporator, the expander and the condenser in sequence. In the warm-up mode, by supplying energy to the expander, the control device compresses the organic medium passing through the condenser and supplies the compressed organic medium to the evaporator; in the waste heat recovery mode, by depressurizing the organic medium passing through the evaporator by the expander, the control device recovers the energy generated by the expander.

Abstract: A control system for a vehicle comprises a controller (114), with the controller (114) further including a processor and a memory. The memory stores instructions executable by the processor such that the controller is programmed to detect a temperature difference (?TEvap), select a flow ratio, and select a valve opening setting (242, 244, 250, 252, 258, 260). The difference in temperature (?TEvap) is between a working fluid (15) downstream of a first evaporator (16) and a working fluid (15) downstream of a second evaporator (20). The flow ratio is a desired flow ratio based on the difference in temperature (?TEvap). The valve opening setting (242, 244, 250, 252, 258, 260) for each of a first valve (84) regulating flow of the working fluid into the first evaporator (16) and a second valve (86) regulating flow of the working fluid into the second evaporator (20) based on the flow ratio.

Abstract: A method and system enabling the efficient use of thermal energy to provide kinetic energy and/or electrical energy. The method uses at least two heat exchangers for heating the working medium, a heat engine and a condenser. The working medium consists of at least two substances. The working medium is partially condensed on the primary side of the first heat exchanger, wherein heat is transferred to the working medium flowing on the secondary side and, subsequently, further condensation heat is transferred to a cooling circuit in a condensation heat exchanger on the primary side of the condensation heat exchanger. Subsequently, the working medium is redirected to the secondary side of the first heat exchanger. A separation of gaseous fractions of the working medium takes place in the condensation heat exchanger on the primary side.

Abstract: A control valve for use in a cam timing phaser arrangement is disclosed comprising a cylindrical valve body, a rotational shuttle element coaxially located within a recess of the valve body, and a blocking pin. When using in a cam timing phaser arrangement having a first phasing chamber and a second phasing chamber, the control valve when non-actuated acts as a double check valve, preventing flow between chambers. Actuation of the blocking pin limits rotation of the rotational shuttle element and results in the control valve allowing flow in a single flow direction between phasing chambers. The allowed direction of flow can be controlled by controlling the timing of the deployment of the blocking pin. A cam timing phaser arrangement, internal combustion engine, and vehicle comprising such a control valve are also disclosed.

Abstract: A valve for an internal-combustion engine may include a body. The body may include a titanium alloy. At least one region of the body may include a nitrided layer. The nitrided layer may include at least one of titanium nitrides and aluminium-titanium nitrides.

Abstract: A system includes an engine head that mounts to an engine block of a reciprocating engine, and the engine head includes an intake flow path, an exhaust flow path, a coolant flow path, and first and second sealing registers disposed on opposite sides of the coolant flow path. In addition, the first and second sealing registers are configured to receive a valve guide that supports a valve stem of an exhaust valve. Moreover, the first sealing register is disposed in a wall separating the exhaust flow path and the coolant flow path. Also, a first wall portion of the wall extends between the first sealing register and an exhaust valve seat configured to receive a valve head of the exhaust valve, and a second wall portion of the wall extends from the first sealing register away from the first wall portion.

Abstract: A high efficiency variable cutoff uniflow steam engine with piston operated valves has an exhaust valve that is held open by a spring during the exhaust stroke but is closed at an end of the exhaust stroke by the piston compressing steam in a compartment associated to act on the exhaust valve. The piston continues to move in the same direction a short distance toward top dead center (TDC) compressing a small residual quantity of steam in the cylinder above the piston during the remaining fraction of the exhaust stroke with sufficient pressure to open the steam inlet valve by steam pressure without an impact caused by physical contact with the piston.

Abstract: An engine camshaft has a lubricating oil passage formed along the longitudinal axis of the same, a cam communicating oil hole is radially formed from the lubricating oil passage to an outer peripheral surface of the camshaft at the same axial position as an engine valve. Cam lubrication holes are radially formed from the inside to cam surfaces of cam lobes formed around a cam carrier fitted around the camshaft. One of the cam lubrication holes of the cam lobes shifted to a position for operating the valve communicates with the cam communicating oil hole of the camshaft to supply lubricant oil.

Abstract: A fluid supply system with a component includes a first bypass valve arranged in a control channel with a valve body adjustable at least between a first and a second position. The valve body separates the control channel into a first and a second space and has a leakage opening connecting the first space to the second space. The second space is connected to a fluid reservoir via a leakage channel, and a switchable valve is arranged in the leakage channel. A sensing device is configured to sense a property of the fluid and convey the property to a controlling device that is configured to close the valve to block the leakage channel when a predefined property is reached. A second bypass valve is configured to reduce a transient oscillation of the first bypass valve during a starting of the system.

Abstract: The oil pan assembly includes an oil pan and a slideable cover. The oil pan includes a base and a sidewall which surrounds the base wherein the base and the sidewall are configured to retain a pool of oil. The oil pan further includes a peripheral flange operatively configured to be coupled to an engine block. The slideable cover is affixed to the oil pan and is configured to maintain the pool of oil proximate to the base of the oil pan.

Abstract: An engine assembly is provided. The engine assembly comprises a first housing defining a first oil gallery, a second housing defining a second oil gallery, and an alignment dowel configured to be received within the first and second housings to provide an alignment feature for locating first and second housings of an engine assembly relative to one another, wherein the alignment dowel comprises a groove formed in an outer surface of the dowel configured to receive oil from the first oil gallery, and wherein the dowel is configured to provide a flow channel for the received oil to flow to the second oil gallery. An alignment dowel for use in the engine assembly is also provided.

Abstract: Systems and methods are provided for in-situ determination of engine oil viscosity to allow for selection of an engine map by an engine control module (ECM) to match the detected viscosity. The new engine map selected based on the viscosity can correspond to an engine map based on an engine oil with a different HTHS viscosity than the prior engine map. Instead of requiring a reprogramming of an ECM when the engine oil is changed, an ECM can have access to a plurality of engine maps corresponding to different engine oils at a given HTHS viscosity and/or at different HTHS viscosities. The ability of an ECM to select an engine map corresponding to a different HTHS viscosity based on in-situ viscosity detection can allow the oil in an engine to be changed without requiring access to the ECM for reprogramming.

Abstract: A ramjet generator for an intake/exhaust pipe of the present invention includes: a central jet having a predetermined length and disposed in the intake/exhaust pipe; and a vortex generator having two or more blades connected to the central jet at sides and extending outwards with a predetermined area, in which the blades have elasticity to come in contact with an inner side of the intake/exhaust pipe of an internal combustion engine and form an external shape of the vortex generator to correspond to a shape of the inner side of the intake/exhaust pipe of the internal combustion engine. According to the present invention, it is possible to improve intake/exhaust efficiency of an internal combustion engine by generating a vortex using a ramjet that increases the flow speed of air in an intake/exhaust pipe connecting an engine and an air cleaner for an internal combustion engine.

Abstract: This particulate matter (PM) sensor is provided with a porous body that has a partition disposed in a passage for exhaust gas including particulate matter, at least a pair of electrodes that oppose each other in a prescribed direction so as to sandwich the porous body, and a deposition part that includes the surface of the partition on the upstream side of the passage, has the particulate matter deposited thereon, and has, formed therein, pores having an average pore diameter smaller than the average pore diameter of the portion of the partition other than the deposition part.

Abstract: A process of using seawater to scrub and clean exhaust gas of engine in ocean engineering with zero energy consumption includes steps of leading the exhaust gas of engine into a scrubbing tower of a scrubbing and cleaning system, pumping seawater into the scrubbing tower with a seawater pump, scrubbing the exhaust gas of engine with the seawater in the scrubbing tower, and discharging clean exhaust gas and scrubbing seawater out of the scrubbing and cleaning system after scrubbing, wherein a step of recycling thermal energy of the scrubbing seawater is carried out before the scrubbing seawater is discharged out of the scrubbing and cleaning system, and in the step of recycling thermal energy, the thermal energy of the scrubbing seawater is recycled and used as the power of the seawater pump.

Abstract: An exhaust purification system comprises an air-fuel ratio control device. If the air-fuel ratio detected by the downstream side air-fuel ratio sensor 41 reaches a second judged air-fuel ratio, the air-fuel ratio control device sets the target air-fuel ratio to a third set air-fuel ratio when the air-fuel ratio reaches the second judged air-fuel ratio, and switch the target air-fuel ratio from the third set air-fuel ratio to the second set air-fuel ratio when the air-fuel ratio becomes a value at the stoichiometric air-fuel ratio side from the second judged air-fuel ratio. The first set air-fuel ratio, the first judged air-fuel ratio and the second judged air-fuel ratio are an air-fuel ratio in the first region. The second set air-fuel ratio and the third set air-fuel ratio are an air-fuel ratio in a second region at an opposite side from the first region.

Abstract: The present disclosure relates to a control unit (8) for controlling reactivation of a lean NOx trap (LNT) disposed in an exhaust system (3) connected to an internal combustion engine (2), the control unit (8). The control unit (8) has at least one processor (11) configured to generate a reactivate flag (RF) for the LNT (6). A memory device (12) having instructions stored therein is coupled to the at least one processor (11). The at least one processor (11) is configured to generate the reactivate flag (RF) when the exhaust gas supplied to the LNT (6) is lean and an LNT temperature (TLNT) is greater than or equal to a predefined LNT temperature threshold (T1). The present disclosure also relates to a method of controlling reactivation of the LNT (6). The present disclosure also relates to a vehicle comprising reactivation control apparatus.

Abstract: A method for simultaneous optimization of nitrogen oxide emissions and carbon dioxide emissions of a combustion engine with an exhaust gas aftertreatment system of a motor vehicle. The method comprises the following steps: at the start a prediction horizon (PH) is selected (100), then a nitrogen oxide limit value (mNOx_max) is specified (101). Minimisation (102) of a cost function (K) comprising the nitrogen oxide emissions and the carbon dioxide emissions is carried out, wherein the nitrogen oxide limit value (mNOx_max) is complied with. Then actuators of the combustion engine are set (105) to a setpoint value (S) that is determined when minimizing (102) the cost function (K). Finally, the steps of the method are repeated.

Abstract: A dosing module includes a frame assembly, a first manifold, a first dosing tray, and a first rail assembly. The frame assembly includes a plurality of panels. The first manifold is coupled to one of the plurality of panels. The first manifold is configured to separately receive air and reductant. The first manifold includes a first connector extending from the first manifold. The first dosing tray includes a first base panel, a second manifold, and a second connector. The second manifold is coupled to the first base panel. The second manifold is configured to separately receive air and reductant from the first manifold and to provide the air and the reductant back to the first manifold. The second connector extends from the second manifold. The second connector is configured to be selectively coupled to the first connector. The first rail assembly includes a first member and a second member.

Abstract: A controller includes a switching delay circuit structured to determine an open delay time and a close delay time for a reductant injector, each based on battery voltage and reductant injector coil temperature. A dosing circuit is structured to determine an open time that the armature pin must be in the fully open position so as to cause the injector to inject a first quantity of reductant. An actuation time is determined based on each of the open time, the open delay time, and the close delay time. The actuation time relates to a time that the coil must be energized so as to cause the injector to inject the first quantity of reductant. A switching command signal is transmitted to the injector to energize the coil for the calculated actuation time so as to cause the injector to inject the first quantity of reductant into an exhaust gas stream.

Abstract: An exhaust gas purification system and an exhaust gas purification method are disclosed. The exhaust gas purification system is provided with: an injector for injecting urea water, said injector being installed between a combustion device and a selective catalytic reduction (SCR) catalyst; a first gas sensor which is installed downstream of the SCR catalyst, and which detects the NO concentration and the NH3 concentration in exhaust gas outputted from the SCR catalyst; and an opening amount control means for controlling the opening amount of the injector for injecting urea water.

Abstract: An automotive vehicle includes an exhaust aftertreatment system. The exhaust aftertreatment system includes a mixer, a doser that injects a reducing agent into the mixer, and a selective catalytic reduction unit. The exhaust aftertreatment system mixes exhaust gases and the reducing agent for treatment prior to the exhaust gases being discharged into the atmosphere. Some components of the exhaust aftertreatment system are positioned proximate to an associated combustion engine to minimize thermal energy loss from the exhaust gases prior to interaction with the exhaust aftertreatment system.