Abstract: The invention relates to a radially compressible and expandable rotor (13, 13a, 13b) for a pump having at least one impeller blade (20, 22, 36, 36a, 36b, 36c, 36d, 36e, 36f, 36g, 37, 37a, 37b, 37c, 37d, 37e, 37f, 74, 88, 89, 90), wherein the impeller blade has an impeller blade body whose material is elastically deformable as well as at least one stiffening strut (25, 26, 27, 30, 31, 32, 52, 53, 57, 58, 62, 63, 67, 95) which is at least partially embedded in the material of the impeller blade body. The struts are designed suitably in size, shape and arrangement and are integrated in suitable hollow spaces of the impeller blade body for stabilizing the impeller blade. Elements with tensile strength can additionally be provided.

Abstract: Airfoils bodies having a first end, a second end, a leading edge, and a trailing edge with a leading edge channel having a first channel wall and a second channel wall that join at a channel base to define the leading edge channel. The leading edge channel extends in a radial direction along the leading edge. A first leading edge impingement cavity is located proximate the leading edge and the first channel wall defines a portion of the first leading edge impingement cavity and a second leading edge impingement cavity with the second channel wall forming a portion of the second leading edge impingement cavity. A first leading edge impingement hole is formed in the first channel wall and angled such that air flowing from the first leading edge impingement cavity and through the first leading edge impingement hole impinges upon a portion of the second channel wall.

Abstract: An airfoil may include an airfoil body that defines a skin chamber, a skin chamber outlet opening, and a tip flag chamber. In various embodiments, the skin chamber is in fluidic communication with the tip flag chamber via the skin chamber outlet opening. In various embodiments, the airfoil body further defines an outlet hole disposed on at least one of a trailing edge and a pressure side of the airfoil. The tip flag chamber may be in fluidic communication with the outlet hole (e.g., cooling circuit air in the tip flag chamber may exit the airfoil via the outlet hole). In various embodiments, the tip flag chamber extends parallel and directly adjacent to the outermost tip of the airfoil.

Abstract: A turbine blade can shorten the assembly time of a multistage turbine section of a gas turbine and reduce assembly errors such as misalignment between adjacent turbine blades, while minimizing the occurrence of a secondary vortex. The turbine blade includes a main end wall; a first turbine airfoil that is connected on a hub side to the main end wall and has a leading edge and a trailing edge; and a second turbine airfoil that is connected on a hub side to the main end wall and has a leading edge and a trailing edge, wherein the main wall is integrally formed with each of the first and second turbine airfoils. The second turbine airfoil is disposed on the main end wall so as to face the first turbine airfoil, and the main end wall is disposed between the first turbine airfoil and the second turbine airfoil.

Abstract: A blade airfoil for an internally cooled turbine rotor blade has suction-side and pressure-side side walls, which, extending from a common leading edge to a common trailing edge and in a span direction from a root-side end to a tip-side end, at least partially enclose a cavity. The tip-side end includes a tip wall which delimits the cavity at the tip side. At least one cooling hole for the discharge of cooling fluid that can be caused to flow in the interior is provided. In the cavity, at least one rib which extends from the tip wall in the direction of the root-side end projects from the inner surface, surrounding the rib, of the suction-side side wall and/or from the inner surface of the pressure-side side wall. An inflow-side end, in relation to the cooling fluid, of the at least one cooling hole opens out laterally in the respective rib.

Abstract: An airfoil may include an airfoil body that defines a central chamber, a skin chamber, and an impingement hole extending between the central chamber and the skin chamber. The central chamber may be in fluidic communication with the skin chamber via the impingement hole. In various embodiments, a first cross-sectional area of the impingement hole is greater than about 25% of a second cross-sectional area of the skin chamber. In various embodiments, the impingement hole is positioned and configured to deliver cooling circuit air to a predicted position of a hotspot on a surface of the airfoil. In various embodiments, the airfoil body further defines at least one structural hole formed from at least one structural core tie, wherein a first cross-sectional area of the impingement hole is at least twice a second cross-sectional area of the at least one structural hole.

Abstract: A guide vane for a turbomachine having an outer platform, a blade airfoil protruding from the outer platform, extending in a longitudinal direction and defining a cavity in its interior, an inner platform arranged opposite the outer platform and connected to the blade airfoil, and a connecting tube which passes through the cavity of the blade airfoil in the longitudinal direction. The first free end of the tube is inserted into a through-opening formed in the inner platform and materially bonded to the inner platform, and the second free end of the tube is arranged in a cooling fluid inlet opening formed on the outer platform, away from the edge thereof, and projecting outward from the outer platform. At least one guide is attached to the outer platform and designed to guide the connecting tube in the longitudinal direction in the event of a thermal change in length.

Abstract: A turbine engine including: rotor blades circumferentially arrayed about a rotor wheel; a connection assembly by which each of the rotor blades connects to the rotor wheel, the connection assembly including: an axially oriented slot formed through a perimeter face of the rotor wheel; a root of the rotor blade installed within the slot, the root being shaped in relation to the slot such that the installation therein forms an axially extending shim cavity between opposing exterior surfaces of the root and the slot; and a shim installed within the shim cavity for restraining movement of the rotor blade relative to the rotor wheel in a radial direction.

Abstract: According to an embodiment, a turbine comprises: a cylindrical casing; and turbine stator blades arranged in the casing along a circumferential direction. The turbine stator blades each includes: a blade effective part; a coolant flow path through which a coolant flows in the blade effective part to cool the blade effective part; an outer ring sidewall provided on an outer periphery of the blade effective part; an inner ring sidewall provided on an inner periphery of the blade effective part; and a contact part provided at an end part of the inner ring sidewall with at least part thereof being along a flow direction of a working fluid, coming into contact with the inner ring sidewall of the adjacent blade during operation, and separating from the inner ring sidewall of the adjacent blade when the operation is stopped.

Abstract: The invention relates to a straightening assembly (28) comprising two radially inner and outer coaxial shells (34) between which extend vanes (36) made of composite material, fixed to a first end portion on the radially inner shell and to a second end portion on the radially outer shell, characterized in that: for each vane (36), in a plane perpendicular to the axis of the radially inner and outer shells (34), a straight line passing through a junction between said first and second end portions and the useful part forms an angle ? with a radius of the radially inner shell, passing through the junction between said first end portion and the useful part of said vane (36), such that 0°<??30°; the radially inner shell has a diameter ranging from 1,000 mm to 1,600 mm; and in that the radially outer shell has a diameter ranging from 2,000 to 2,800 mm; the number of vanes (36) ranges from twenty-five to forty-five.

Abstract: Systems and methods for reducing heat exposure of a turbine casing in a gas turbine engine may be provided. The system may include blade track segments. The blade track segments may include a cavity formed at a circumferential end of the blade track segment. The blade track segments may further include an assembly groove configured to provide a clearance for axial insertion of an inter-segment strip seal. An inter-segment strip seal may be axially inserted past the assembly grooves and into the cavity. The inter-segment strip seal may cover a gap between adjacent blade track segments, thus blocking hot, high pressure fluid from contacting the turbine casing.

Abstract: A sealing assembly for a gas turbine includes a plurality of sealing housings interposed between adjacent turbine disks of a multistage turbine, each sealing housing coupled to a turbine vane of a corresponding stage; and a sealing plate unit installed between adjacent sealing housings to seal a gap between the adjacent sealing housings. Each sealing housing includes a horizontal housing segment and a pair of vertical housing segments each having a lower end connected to horizontal housing segment. The sealing plate unit includes a horizontal plate installed in the horizontal housing segment, and a pair of vertical plates respectively installed in the pair of vertical housing segments. The horizontal housing segment includes a horizontal slot facing an adjacent sealing housing to receive the horizontal plate, and each vertical housing segment includes a vertical slot facing an adjacent sealing housing to receive a corresponding vertical plate.

Abstract: The invention relates to a blade (16), in particular a fan blade, for resurfacing an abradable coating (26) on an internal surface of a turbine engine case (18) intended to surround the blade. The comprises a root (20) and an airfoil (24) having a tip opposite the root, said root comprising a housing (32) for the storage or passage of a polymerisable refill resin. The airfoil comprises longitudinal channels (34), the first ends of said channels being connected to the housing and the opposite ends opening at the aforementioned tip.

Abstract: A method of manufacturing a net shaped seal comprising depositing a first layer of powder material on a substrate; the powder material comprising an abradable feedstock material comprising matrix alloy clad filler particles, wherein the matrix alloy cladding includes Al, Cu, Ni, Co, Cr, Fe, Si and Y; guiding a heat source over the powder material layer; laser sintering the powder material, the matrix alloy clad filler particles sinter in the absence of the filler particles melting; depositing a second layer of powder material over the first layer; laser sintering the second layer of powder material with a second laser pass at predetermined locations; wherein at least one of the matrix alloy clad filler particles sinter, and in the absence of the filler particles melting; and repeating the depositing step and laser sintering step to form subsequent layers to form an abradable seal on the substrate.

Abstract: An adjustable blade outer air seal apparatus includes a case that extends circumferentially around an axis, a support ring non-rigidly mounted to the case on spring connections radially inwards of the case, whereby the support ring floats with respect to the case, and at least one blade outer air seal segment that is radially adjustable relative to the support ring.

Abstract: A convertible ducted fan engine having a shroud, a drive shaft connected to a mechanical fan, and a rotational drive motor configured to rotate the mechanical fan. An embodiment includes a linear drive motor configured to translate the drive shaft and mechanical fan in a direction parallel to a longitudinal axis of the shroud. The convertible ducted fan engine includes a fluid-propulsion configuration in which the mechanical fan rotates freely with respect to the shroud to produce thrust through fluid flow, and a drive-wheel configuration in which the shroud rotates about the rotational axis.

Abstract: A drive system of a gas turbine engine includes at least one drive shaft operable to rotate within the gas turbine engine, a phonic wheel coupled to the at least one drive shaft, a speed sensor operable to detect rotation of the phonic wheel indicative of rotation of the at least one drive shaft, and a processing system coupled to the speed sensor. The processing system is operable to detect a phonic wheel pulse train indicative of rotation of the at least one drive shaft via the speed sensor, determine a torsional mode of the at least one drive shaft based on the phonic wheel pulse train, and record one or more trends of the torsional mode indicative of a health status of the drive system.

Abstract: A performance measurement system of an inlet of a gas turbine engine includes a probe strut configured for installation to a case strut of an inlet case of a gas turbine engine. The probe strut includes one or more probes extending therefrom configured to measure one or more characteristics of an airflow past the one or more probes, a first attachment point configured to secure the probe strut to a hub portion of the inlet case, and a second attachment point configured to secure the probe strut to an outer case portion of the inlet case. A data acquisition module is located at a central longitudinal axis of the inlet and is operably connected to the probe to collect sensed data therefrom. The probe strut and the data acquisition module are configured to be installed, removed, and/or relocated without removal of the inlet case from the gas turbine engine.

Abstract: A gas turbine engine component formed of material having phononic regions. The phononic regions are formed of void nanostructures. The phononic regions modify the behavior of the phonons and manage heat conduction.

Abstract: Disclosed are a blade ring segment for a turbine section, a turbine section having the blade ring segment, and a gas turbine having the turbine section. Multiple blade ring segments is installed in a turbine casing accommodating turbine blades rotated by combustion gas from a combustor. The blade ring segment includes an inner panel provided in the turbine casing and having multiple air holes through which cooling air fed from the outside of the turbine casing flows, an outer panel disposed on one side of the inner panel, and a cooling structure protruding from one side of the outer panel so as to form a flowing channel in a zigzag pattern so that cooling air fed through the air holes flows therethrough.

Abstract: A turbomachine of bypass type comprising a nacelle defining a fan duct with an interduct. The turbomachine comprises at least one compartment created in the thickness of the interduct or of the nacelle. The compartment is separated from the fan duct by a cold wall and comprises at least one heat-sensitive element. The compartment further is equipped with a ventilation assembly comprising at least one ventilation opening made in the cold wall in order, in use, to cause air from the fan duct to enter the compartment. Each ventilation opening comprises a passive-opening system arranged in the compartment, the system comprising a flap able to move between an open position in which the flap uncovers the opening and a closing-off position in which the flap closes off the opening, and a passive-actuation device of the flap for moving the flap between the two positions.

Abstract: A turbo-engine module comprises a turbo-engine housing, and a thermal protection shell of the housing. The thermal protection shell is configured to cover at least partially the housing in order to protect same thermally. The module comprises a wear protection strip which is situated between the housing and the thermal protection shell, in a junction region of the housing and the thermal protection shell.

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan, and an outer housing surrounding the fan to define a bypass flow path, a compressor, a turbine section including a fan drive turbine and a second turbine, an epicyclic gear system with a gear reduction, the fan drive turbine driving the fan through the gear system, and the gear system straddle-mounted by first and second bearings. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.

Abstract: A lubricant scoop is disclosed. The lubricant scoop includes an annular body configured for engagement with a shaft rotating about a central axis. The annular body includes a first annular portion and a second annular portion disposed adjacent the first annular portion. The first annular portion includes a radially oriented entrance surface and a first axially oriented transition surface. The second annular portion includes a second axially oriented transition surface, a primary redirection member spaced radially outward from the second axially oriented transition surface, a radially oriented exit surface and an exit conduit having an opening positioned on the radially oriented exit surface.

Abstract: Oil console equipment includes: a lubrication oil tank in which a lubrication oil is stored; a lubrication oil supply line which is connected to the lubrication oil tank and through which a liquid lubrication oil stored in the lubrication oil tank is supplied to a bearing supporting a rotor; a first cooler which is provided in the lubrication oil supply line and cools the liquid lubrication oil supplied to the bearing; a lubrication oil recovery line which is connected to the lubrication oil tank and through which the lubrication oil recovered from the bearing is introduced into the lubrication oil tank; a first atmosphere discharge pipe which is connected to the lubrication oil tank and through which a lubrication oil mist which exists in a gas phase in the lubrication oil tank and is a misted lubrication oil and a first exhaust gas containing a gas are introduced out.

Abstract: A method for assisting with the management of a pumping device capable of supplying a circuit of a power production facility with water taken from a natural watercourse is disclosed here. In particular, at least some parameters relating to a watercourse and having an influence on the quantity of materials liable to clog filters are collected. A statistical model is developed that is at least based on historical data for said parameters relating to the watercourse for which clogging of the filters has been observed. Current parameters relating to at least the watercourse are collected and said statistical model is used in conjunction with said current parameters to assess the risk of an influx of clogging materials, and an alert signal for deactivating the pumping device at a selected time is generated on the basis of the assessed risk.

Abstract: A heat recovery system arranged to be used together with a first closed loop system (S1) configured as a first closed-loop thermodynamic Rankine cycle system, to convert heat from a heat generating unit (1) into electrical energy (E). Said heat recovery system comprising a second closed loop system (S2) comprising a second system working medium (W2) configured as a second closed-loop thermodynamic Rankine cycle system arranged to convert the heat in at least one heat stream (HS1) generated by the heat generating unit (1) into a first batch (E1) of electrical energy (E) and a third closed loop system (S3) comprising a circulating third system working medium (W3).

Abstract: A variable valve train is provided with cylindrical cam carriers axially slidably and co-rotatably supported on camshafts. The cam carriers have thereon, respectively, plural cam lobes different in cam profile and axially adjacent to each other. Cam changeover mechanisms are provided for axially shifting the cam carriers and for changing over the cam lobes for operating on engine valves. At least one of the cam changeover mechanisms is disposed between axes of the two camshafts and on the side of an engine crankshaft relative to the axes.

Abstract: A valve train assembly includes: a first group of one or more dual body rocker arms and a second group of one or more dual body rocker arms, the first group for controlling one or more valves of a first cylinder and the second group for controlling one or more valves of a second cylinder, each of the dual body rocker arms including a first body, a second body, and a latching arrangement for latching and unlatching the first body and the second body; and an actuator arrangement external to the dual body rocker arms for controlling the latching arrangement, the actuator arrangement including a shaft having a first set of one or more cams for controlling the latching arrangements of the first group of one or more dual body rocker arms and a second set of one or more cams for controlling the latching arrangements of the second group.

Abstract: A driven rotational body rotates relative to a driving rotational body to change a rotational phase therebetween and brings its driven-side stopper wall into contact with a driving-side stopper wall of the driving rotational body in the relative rotational direction. The planetary gear performs a planetary motion while being meshed with the driving rotational body and the driven rotational body to change the rotational phase. The driving rotational body includes a gear member, a cover member, and a fastening member. The gear member has the driving-side stopper wall and is meshed with the planetary gear. The cover member covers an accommodation space, in which the driven rotational body and the planetary gear are accommodated, together with the gear member. The fastening member axially fastens the gear member with the cover member.

Abstract: A joint includes a rotation transmitting portion and a stopper portion. The rotation transmitting portion abuts on a relative rotating portion in a circumferential direction. The stopper portion is capable of abutting on the relative rotating portion to restrict an axial position of the relative rotating portion. The stopper portion of the joint which rotates at the same speed as the relative rotating portion restricts an axial position of the relative rotating portion, whereby a sliding movement does not occur between the relative rotating portion and the stopper portion. It can be restricted that a power transmission efficiency is decreased and an abrasive wear is generated.

Abstract: A valve train for the variable actuation of an inlet valve and an outlet valve of a combustion chamber of an internal combustion engine, having a first operative connection between a valve actuating device and the inlet valve and a second operative connection between the valve actuating device and the outlet valve. The first operative connection and the second operative connection are assigned an interrupting element which is set up to temporarily interrupt the operative connections. The first operative connection and the second operative connection are connected to the same interrupting element in such a way that the first operative connection and the second operative connection can be interrupted temporarily by way of the interrupting element.

Abstract: A deactivating rocker arm can include an outer arm extending between a first end and a second end. The outer arm can have a first outer side arm and a second outer side arm. The first and second outer side arms can define outer pivot axle apertures and axle slots. The inner arm can be disposed between the first and second outer side arms. The inner arm can have a first inner side arm and a second inner side arm. The first and second inner side arms can define bearing apertures. A bearing can be mounted in the bearing apertures of the inner arm and the axle slots of the outer arm. The axle slots can be configured to permit lost motion movement of the bearing. A first biasing member can be disposed on the second end of the outer arm and in biasing contact with the bearing.

Abstract: An engine variable valve train is provided with a cylindrical cam carrier fitted on a camshaft in a manner axially slidable to and co-rotatable with the camshaft. The cam carrier has therearound mutually adjoining low-speed and high-speed cam lobes selectively acting on the engine valve and being different in cam profile. The cam carrier has therearound lead grooves to be engaged with or disengaged from changeover pins for axial shift of the cam carrier. The lead grooves include a speed-increasing lead groove for changeover from the low-speed to the high-speed cam lobe and a speed-decreasing lead grooves for changeover from the high-speed to the low-speed cam lobe. The speed-increasing and speed-decreasing lead grooves are different in groove contour. This enables the cam carrier to axially shift smoothly and to improve the durability of the lead grooves.

Abstract: Methods and systems are provided for indicating degradation of a variable displacement oil pump. In one example, an engine method comprises indicating degradation of the oil pump based on a fuel usage change of the engine, responsive to a commanded change in displacement of the variable oil pump. In response to an indicated degradation, engine wear may be avoided and fuel economy may be improved by adjusting engine operation.

Abstract: In the oil lubrication structure that supplies lubricating oil to the transmission device, the oil lubrication structure includes an oil passage formed above a transmission device. The oil passage is formed by an oil groove portion and a plate member. The oil groove portion is integrally formed in a crankcase. The plate member is arranged in the crankcase so as to cover the oil groove portion. The plate member has oil dripping holes formed therein, and the oil dripping holes are opened at positions directly above the transmission device.

Abstract: A valve, an oil separator, and a ventilation system are described. These are used particularly in internal combustion engines, for example for separating oil mist or oil droplets from blow-by gases (crankcase gases). In particular a valve which can be used for example as a bypass valve in a ventilation system is described.

Abstract: A valve component is provided with a unit for regulating or controlling a fluid pressure and is further provided with an expansion chamber. The unit has a valve housing with a first housing part and a second housing part, between which a switching element is arranged. The first housing part has an inlet and an outlet for a fluid. The switching element is arranged between the inlet and the outlet for regulating, releasing or shutting of a flow of the fluid. The switching element separates two chambers in the valve housing from each other. In open switching position of the switching element, the inlet and the outlet are connected by one of the chambers, and at least one first venting bore opens from the other one of the chambers into the expansion chamber.

Abstract: An apparatus and a method are provided for a crankcase breather vent assembly to direct blow-by gases out of an engine crankcase. A vent base comprising a generally cylindrical vessel communicates received blow-by gases into an interior cavity of a breather vent that comprises a filter medium. Baffles disposed within an interior cavity of the vent base capture oil carried along with the blow-by gases. The captured oil is directed to an oil sump of the engine by way of a suitable hose. A bonnet fastenably receives the breather vent and is configured to reduce a buildup of oil residue on nearby engine components. An outer profile of the breather vent is tapered along a longitudinal dimension of the filter medium to facilitate unrestricted air flow through the filter medium when the bonnet is installed onto the breather vent.

Abstract: Methods and systems are provided for adjusting and troubleshooting an adjustable exhaust valve of a variable exhaust tuning system. In one example, a method may include comparing engine startup conditions to engine conditions of a last engine off event, adjusting a position of the adjustable exhaust valve, and providing a diagnostic summary to a vehicle operator based upon the results of the comparison and adjustment.

Abstract: A muffler valve device for a vehicle may include a chamber fixed at a surface of the wall, a guide rod provided in the chamber and attached at the surface of the wall, a fixing member attached at one end portion of the guide rod and fixing the chamber, a valve disposed slidably on the guide rod between the surface of the wall and the fixing member, and an elastic member located between the valve and the fixing member to provide an elastic force to the valve.

Abstract: Methods and systems are provided for a heat exchanger phase change material installed as a component of a variable exhaust tuning system. In one example, a method may include absorbing excess heat energy from exhaust gases during and after an engine-on event within a heat exchanger material, releasing heat energy stored in the heat exchanger material during and after an engine-off event, and heating an adjustable exhaust valve with the heat energy stored in the heat exchanger material.

Abstract: An exhaust gas purification device includes: a substrate of wall-flow structure having an inlet cell, an outlet cell and a porous partition wall; an upstream catalyst layer provided inside the partition wall and disposed in an upstream portion, including an exhaust gas inflow end section, of the substrate; and a downstream catalyst layer provided inside the partition wall and disposed in a downstream portion, including an exhaust gas outflow end section, of the substrate. The downstream catalyst layer contains a carrier, and Rh supported on the carrier. The upstream catalyst layer contains a carrier, and Pd and/or Pt supported on the carrier.

Abstract: An exhaust purifying device provided in an exhaust passage of an internal combustion engine comprises: a column-shaped honeycomb carrier; a cylindrical case member adapted to house the honeycomb carrier; a holding member provided between the honeycomb carrier and the case member to surround the outer circumference of the honeycomb carrier; buffer members provided on a peripheral edge of the edge surface of at least one side of an inflow side edge surface and an outflow side edge surface of the honeycomb carrier so as to regulate the movement of the honeycomb carrier in the central axis X direction; and setting members secured to the case member to regulate the movement of the buffer members by allowing their position regulation parts to contact the buffer members; wherein the buffer members are provided, on the outer circumferential sides, with recesses into which the position regulation parts of the setting members are fitted.

Abstract: Systems and methods for capturing carbon dioxide (CO2) in exhaust gases of a vehicle include delivering the exhaust gas to a cooled section of a rotary contactor, the rotary contactor including openings that extend from a first side of the rotary contactor to a second side of the rotary contactor. The CO2 of the exhaust gas is adsorbed with a sorbent of the cooled section of the rotary contactor, where the non-CO2 components of the exhaust gas pass through the openings. The cooled section of the rotary contactor is heated with a hot fluid of the vehicle to release the adsorbed CO2 and convert the cooled section of the rotary contactor to a heated section of the rotary contactor. The heated section of the rotary contactor is cooled to convert the heated section of the rotary contactor back to the cooled section of the rotary contactor.

Abstract: An exhaust purification system comprises a catalyst 20, an upstream side air-fuel ratio sensor 40, a downstream side air-fuel ratio sensor 41, and an air-fuel ratio control device. The air-fuel ratio control device alternately switches a target air-fuel ratio between a rich set air-fuel ratio and a lean set air-fuel ratio, calculates an oxygen storage amount and an oxygen discharge amount, updates a learning value, and corrects an air-fuel ratio-related parameter based on the learning value. The air-fuel ratio control device changes a condition for switching the target air-fuel, stores the learning value at the time when the operating state of the internal combustion engine changes from the first state to the second state as a first state value, and updates the learning value to the first state value when the operating state of the internal combustion engine returns from the second state to the first state.

Abstract: A system includes an exhaust conduit coupled, at least first end of the exhaust conduit, to an internal combustion; a catalytic converter coupled to a second end of the exhaust conduit; and electromagnetic wave source configured to emit electromagnetic energy; and a wave guide, coupled at a first end to the electromagnetic wave source and at a second end to the exhaust conduit, and extending between the electromagnetic wave source and the exhaust conduit. The electromagnetic wave source is configured to provide the electromagnetic energy, via the wave guide, to exhaust gas traveling through the exhaust conduit.

Abstract: The present invention relates to a catalyst comprising a carrier substrate of the length L, a passive nitrogen oxide adsorber and means to control the temperature of the carrier substrate, as well as a process for cleaning of an exhaust gas emitted from a lean burn engine.

Abstract: An exhaust purification system is equipped with: a linear exhaust pipe through which exhaust gas emitted from an engine passes; an injection nozzle that injects a reducing agent into the exhaust pipe at an oblique angle with respect to the axial direction of the pipe; a reduction catalyst that is provided in the exhaust system downstream from the injection nozzle, and that purifies the exhaust gas by causing the exhaust gas to react with the reducing agent; and a mixer member that is provided inside the exhaust pipe 13, downstream from the injection nozzle, and that causes the reducing agent to mix with the exhaust gas and diffuse. The mixer member includes multiple fins protruding downstream, and is arranged inclined inside the exhaust pipe such that the upstream surface thereof faces the injection opening surface of the injection nozzle.

Abstract: An assembly includes a heat exchanger, a bypass conduit defining a path for passage for the exhaust gases and bypassing the heat exchanger, and a valve adjusting the amounts of exhaust gases circulating through the heat exchanger and through the bypass conduit respectively. The valve has a driving shaft, and the assembly further comprises a fluid box that is in fluid communication with a heat transfer fluid circulation side of the heat exchanger and arranged around the driving shaft to cool the driving shaft.