Abstract: A structural duct apparatus includes a cross flow turbine for use in a fluid flow. The turbine has at least one straight vertical aerofoil blade and at least one helical aerofoil blade slanted toward the direction of rotation. Inner and outer walls of the duct apparatus provide an inner diffuser flow passageway that houses turbine power take off modules with the outer surfaces of the duct influencing flow direction so that where there are at least two ducts an open flow barrage is advantageously formed.

Abstract: An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas flow and a cooling surface facing a cooling fluid flow. A film hole extends through the substrate to an outlet on the hot surface. A flow conditioning structure is provided downstream of the outlet.

Abstract: An integrally bladed rotor with an axial bore having either an inward dishing shape or an axial straight shape with an annular inward projection in which radial cooling holes having an elliptical cross sectional shape are formed, where the radial cooling holes have an elliptical cross sectional shape with a major axis perpendicular to the axial bore in order to reduce stress near an inlet opening of the radial holes in order to increase the LCF life of the IBR. The radial cooling holes discharge into a circumferential channel that is connected to cooling holes extending in the rotor blades.

Abstract: An article and method of cooling an article are provided. The article includes a body portion, a plurality of partitions within the body portion, and at least one aperture in each of the partitions, the at least one aperture arranged and disposed to direct fluid towards an inner surface of the body portion. The plurality of partitions form at least one up-pass cavity and at least one re-use cavity arranged and disposed to receive the fluid from the at least one aperture in one of the partitions. The method includes providing the article having an up-pass partition and a re-use partition, generating a first fluid flow through the at least one aperture in the up-pass partition, receiving a post-impingement fluid within the re-use cavity, and generating a re-use fluid flow through the at least one aperture in the re-use partition, the re-use fluid flow being generated from the post-impingement fluid.

Abstract: An airfoil includes an airfoil wall including an exterior airfoil surface and at least partially defines an airfoil cavity. A fillet is on the exterior airfoil surface. A recess is in an interior surface of the airfoil wall adjacent the fillet. A baffle tube is located in the airfoil cavity spaced from the recess.

Abstract: A method of forming a component for use in a gas turbine engine includes the steps of forming an airfoil/root assembly; creating a platform assembly structure having an opening; inserting the airfoil/root assembly into the opening; and bonding the platform assembly structure to the airfoil/root assembly to form the component.

Abstract: It is an objective of the invention to provide a low cost Ni-based casting superalloy suitable for casting articles having a far better balance among a high-temperature mechanical strength, a grain boundary strength and a oxidation resistance than conventional Ni-based superalloy cast articles. There is provided an Ni-base casting super alloy including: in mass %, 0.03 to 0.15% of C; 0.005 to 0.04% of B; 0.01 to 1% of Hf; 0.05% or less of Zr; 3.5 to 4.9% of Al; 4.4 to 8% of Ta; 2.6 to 3.9% of Ti; 0.05 to 1% of Nb; 8 to 12% of Cr; 1 to 6.9% of Co; 4 to 10% of W; 0.1 to 0.95% of Mo; 0.02 to 1.1% of Si and/or 0.1 to 3% of Fe; and the balance including Ni and incidental impurities.

Abstract: A method for forming a hole in a ceramic matrix composite (CMC) component may be provided. A sacrificial fiber having an environmental barrier coating on an outer surface thereof may be inserted into a porous ceramic preform that includes ceramic fibers. The ceramic preform may be formed into a ceramic matrix composite body. The sacrificial fiber may be removed from the ceramic matrix composite body, the environmental barrier coating of the sacrificial fiber defining an opening in the ceramic matrix composite body. A ceramic matrix composite component may be provided. The ceramic matrix composite component may include an environmental barrier coating of a sacrificial fiber, where the environmental barrier coating forms a lining of a hole passing partly or entirely through a thickness of the ceramic matrix composite body.

Abstract: A turbine engine rotor blade having a trailing edge (20A) with a modified surface state (22, 28) enabling the flow speed passing around the blade to be altered so as to modify the acoustic interaction against structural elements (12) that interact with the flow downstream from the rotor blade.

Abstract: A fan section for a gas turbine engine includes a hub. A fan blade is secured to the hub. A platform is removably secured to the hub and is arranged adjacent to the fan blade. The platform has a body with lateral sides that each include a channel. A seal is removably received in each of the channels, with one of the seals abutting the fan blade. A method of repairing the fan blade platform includes the steps of removing a nose cone to provide access to a hub, detaching a platform from the hub, and pulling the seal from a groove in the platform.

Abstract: A device for chocking and retaining a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc, the root being mounted in the slot by insertion of a leading end of the root into a proximal end of the slot and then sliding the root towards a distal end of the slot. The device includes a first wedging body having a key portion receivable in a keyway formed at the distal end of the slot. The keyway restrains the first wedging body against movement in the axial direction. The first wedging body further has a first angled surface over which a correspondingly angled leading end surface of the root slides when the root is inserted in the slot to urge the leading end of the root radially outwardly.

Abstract: The invention relates to a fixed diffuser vanes assembly (10) for guiding flow through a turbomachine, comprising an internal annular platform (12) and a plurality of fixed vanes (11) which are mounted on this platform, the internal platform comprising a support plate (121) forming the base of said vanes, a radial annular partition (120) extending from the support plate toward an axis of the vanes assembly, and an internal ring (122) attached to the radial annular partition and having an internal surface on which an abradable material (123) is arranged, the vanes assembly being characterized in that the internal ring comprises at least one cut-out (1223) delimiting a tongue (1226), the tongue being bent to press against the radial annular partition (120). The invention also relates to a method of manufacturing such a vanes assembly and to a turbomachine incorporating such vanes.

Abstract: An arrangement for a gas turbine engine includes a combustor for producing a working medium by combustion of a mixture of fuel and an oxidant, a turbine section comprising a stationary vane carrier on which a first row of stationary vanes is arranged, and a transition duct for leading the working medium from the combustor to the turbine section. The transition duct has a forward end that adjoins the combustor and an aft end that adjoins the stationary vane carrier. The transition duct has a transition duct axis extending from the forward end to the aft end along a straight line. The transition duct axis is normal to a vane axis of a stationary vane in the first row of stationary vanes.

Abstract: A casting mold assembly includes an airfoil defining section and a casting core. The airfoil defining section includes an outer mold wall and a direct-shelled inner mold wall. The direct-shelled inner mold wall is disposed within a forward chordwise portion of the airfoil defining section. The direct-shelled inner mold wall includes an aft end having an external radius measuring more than about 0.075 in. (1.9 mm). The casting core is secured within an aft chordwise portion of the airfoil defining section, and includes an aft end with an external radius measuring less than about 0.075 in. (1.9 mm). A cast component and a method for making the casting mold assembly are also disclosed.

Abstract: A laminated sheet for a gas turbine component, the laminated sheet has a first cover layer, a second cover layer and a first intermediate layer, wherein the first cover layer, the second cover layer and the first intermediate layer are stacked together on top of each other. The first intermediate layer is located between the first cover layer and the second cover layer. The first intermediate layer has at least one first elongated through hole, wherein a cooling fluid is flowable through the first elongated through hole.

Abstract: A disk-seal arrangement for a gas turbine engine rotor includes a blade retention disk having a longitudinally opening slot therein and a seal disk juxtaposed to said blade retention disk and a single anti-rotation tab received within the blade retention disk slot. The seal disk also includes a pair of balance slots disposed immediately adjacent the antirotation tab to offset the weight thereof for preserving rotor balance. A split ring is disposed longitudinally between the blade retention and seal disks for reacting longitudinal loading therebetween. The ends of the split ring seat against side surfaces of the antirotation between the split ring and the blade retention and seal disks.

Abstract: A Variable Turbine Geometry (VTG) turbine turbocharger comprises a turbine wheel in a housing, and a compressor wheel coupled to the turbine wheel with a main shaft. The turbocharger additionally includes a VTG assembly in the housing, an actuator outside the housing, and an actuation pivot shaft that extends through an opening of the housing and connects the VTG assembly to the actuator. A face seal assembly seals the opening, and includes an inner ring member rotationally fixed on the pivot shaft, a disc member, and a spring seal. The disc member includes a first face that forms a seal with a surface of the housing, and is rotationally fixed to, while being movable axially relative to, the inner ring member. The spring seal seals the inner ring member and the disc member, and applies a seating force against the disc member.

Abstract: A braze gel includes a braze powder, a braze binder, and a viscosity reducer. The braze gel has a gel viscosity sufficiently low to permit dip coating of a component with the braze gel to apply a braze coating of the braze gel to the component. A brazing process includes applying the braze gel to a portion of a component. The brazing process also includes drying the braze gel to form a braze coating on the component to form a braze-coated component. A brazing article includes a component and a braze coating over a portion of the component. The component may have structural features having a spacing of less than about 5 mm and a depth of at least about 1 mm, which may be honeycomb cells. The component may be a turbine component.

Abstract: A variable stator vane for a compressor guide vane is provided. The vane includes a blade and a pivot. The pivot includes an internal pivot element and a pivot cap. The blade and the internal pivot element are each made from a composite material. At least one contact surface of the pivot cap is metallic.

Abstract: A method is provided for determining an updated engine health factor of an aircraft engine. The method includes determining an engine health condition indicative of an engine health during operation of the aircraft engine. The method also includes determining a baseline engine power model for the aircraft engine and modifying the baseline engine power model using the determined engine condition. The method also determines an engine health factor based on a modified engine power model.

Abstract: An inner fixed structure for an aircraft nacelle may comprise a nanoreinforced polyimide composite skin. The nanomaterials may increase thermal conductivity and decrease microcracking in the inner fixed structure. The inner fixed structure may comprise an inner polyimide composite skin, an acoustic core, and an outer polyimide composite skin. The inner fixed structure may be blanketless.

Abstract: A turbine casing includes at least one shell adapted to enclose one or more turbine stages in a gas turbine engine; an air inlet in the at least one shell; a flow sleeve secured to an inside surface of the at least one shell, the flow sleeve comprising at least two arcuate segments. Each arcuate segment includes an arcuate base, a pair of sidewalls extending radially outwardly of the base thereby forming a circumferentially-extending flow channel defined by the base, the sidewalls and the inside surface. The air inlet is aligned with the flow channel and the sleeve is configured to distribute air flowing in the channel into spaces proximate the one or more turbine stages in circumferential, radial and axial directions, including along the inside surface of the at least one shell.

Abstract: A ceramic core used to cast and cooling circuit in a thin wall turbine airfoil, where the ceramic core includes a row of metering and impingement forming pieces that discharge into a radial plenum, followed by a row of pedestals and a row of diffusion channels that then flow into a single discharge slot. The ceramic core has bumpers of both sides to position the core in a wax mold. The metering and impingement holes are offset from the cooling passage in the airfoil wall so that impingement of the hot surface of the wall occurs.

Abstract: A containment system for a gas turbine engine includes a fan track assembly for use with a containment case. The fan track assembly includes a body of collapsible material that is positioned within a cavity of the fan case, and voids are provided for providing space in the event of a catastrophic blade failure. Various configurations of the fan track liner assembly are provided along with various mounting methodologies for securing the track liner assembly to the fan case of a gas turbine engine.

Abstract: A ceramic component for a turbomachine, the ceramic component (1) being configured to be destroyed in response to a contacting with another component (2) of the turbomachine that moves relative to the ceramic component (1). A turbomachine component pairing and a turbomachine including such a ceramic component.

Abstract: The present disclosure is directed to a component for a gas turbine. The component includes a component wall having a radially inner surface, a radially outer surface, a first circumferential surface, and a second circumferential surface. A first boss extends radially outwardly from the radially outer surface, includes a first circumferentially outer surface, and defines a first aperture extending axially therethrough. A second boss extends radially outwardly from the radially outer surface and is circumferentially spaced apart from the first boss. The second boss includes a second circumferentially outer surface and defines a second aperture extending axially therethrough. The first circumferentially outer surface of the first boss and the second circumferentially outer surface of the second boss form a pair of angles with respect to the radially inner surface.

Abstract: A diverter damper for controlling a gas flow in a gas duct of large cross section. The diverter damper includes a housing having an inlet and two outlets, a pivotable flap which in a first extreme position closes a first outlet and in a second extreme position closes a second outlet. The damper further includes a drive shaft connected to the pivotable flap, wherein the drive shaft extends at least partly between two opposite housing walls and through at least one of the two opposite housing walls, and at least one actuator mechanism that is located outside the housing near or against the at least one housing wall through which the drive shaft extends. The actuator mechanism includes at least one cylinder piston unit connected to the drive shaft for pivoting the flap into one of the extreme positions or into a position between the extreme positions.

Abstract: A system including an engine and a heat exchanger coupled to the engine is provided. The engine includes an engine fluid and at least one of a compressor section configured to compress a gas, a lubricant path configured to circulate a lubricant, or a coolant path configured to circulate a coolant. The engine fluid comprises at least one of the gas, the lubricant, or the coolant, and the engine fluid is a source of heat derived from one or more operations of the engine. The heat exchanger is configured to receive the engine fluid from the engine and exchange heat between the engine fluid and a working fluid to produce a heated working fluid and a cooled engine fluid, and the heat exchanger is configured to export the heated working fluid to a steam system.

Abstract: The invention relates to a method for lubricating an expansion machine (30) in a thermodynamic cycle device, wherein the thermodynamic cycle device comprises the expansion machine, a feed pump (50), a lubricant separator (10) and a working medium containing a lubricant, and wherein the method comprises the following steps: The working medium is subjected to pressure by means of the feed pump. The pressurized working medium is delivered by the feed pump to the lubricant separator. At least part of the lubricant is separated from the working medium by means of the lubricant separator. At least part of the separated lubricant is delivered by the lubricant separator to the expansion machine.

Abstract: A power generation system may include a generator, and a gas turbine system for powering the generator, the gas turbine system including a turbine component, an integral compressor and a combustor to which air from the integral compressor and fuel are supplied, the combustor arranged to supply hot combustion gases to the turbine component, and the integral compressor having a flow capacity greater than an intake capacity of at least one of the combustor and the turbine component, creating an excess air flow. A turbo-expander may also power the generator. A first control valve control flow of the excess air flow along an excess air flow path to an inlet of the turbo-expander. An educator may be positioned in the excess air flow path for using the excess air flow as a motive force to augment the excess air flow with additional air. A discharge of the turbo-expander is supplied to an inlet of the integral compressor.

Abstract: A heat engine system and a method for cooling a fluid stream in thermal communication with the heat engine system are provided. The heat engine system may include a working fluid circuit configured to flow a working fluid therethrough, and a cooling circuit in fluid communication with the working fluid circuit and configured to flow the working fluid therethrough. The cooling circuit may include an evaporator in fluid communication with the working fluid circuit and configured to be in fluid communication with the fluid stream. The evaporator may be further configured to receive a second portion of the working fluid from the working fluid circuit and to transfer thermal energy from the fluid stream to the second portion of the working fluid.

Abstract: The present invention provides a variable valve mechanism of an internal combustion engine, which includes an input member, an output member, a slider and a variable device. The output member has internal space formed therein and has a first cutout and a second cutout which are formed at two positions separated from each other in the swing direction so as to extend from an outer periphery of the output member to the internal space, and the input member is mounted in the internal space so as to extend through both inner sides of the first and second cutouts, and is brought into contact with inner side surfaces of the cutouts from both sides in the thrust direction, whereby relative displacement of the input member together with the slider in the thrust direction with respect to the output member is restricted at two positions by the first and second cutouts.

Abstract: A roller tappet for a fuel unit pump of an internal combustion engine is provided with a roller tappet bore for inserting the roller tappet within the internal combustion engine. The roller tappet includes a roller tappet body having a body longitudinal axis for connecting the roller tappet to a reciprocating element of the fuel unit pump. A cam roller contacts a cam lobe of a rotatable shaft of the internal combustion engine. The cam roller is rotatably mounted to the roller tappet body around a cam roller rotation axis. The external surface of the roller tappet body is configured to allow tilting of the roller tappet within the roller tappet bore for aligning the roller tappet with respect to the cam lobe of the rotatable shaft.

Abstract: The cam follower roller device provides a tappet body extending along an axis, an insert mounted in the tappet body, a pin mounted at least on the insert and a roller mounted on the pin. The device further provides a spacer having a body mounted axially against the insert and with retaining means, cooperating with the insert for fixing the spacer to the insert.

Abstract: The cam follower roller device provides a tappet body extending along an axis, an insert 18 mounted in the tappet body, a pin 14 mounted at least on the insert and a roller mounted on the pin. The device further provides a removable retaining plug carried by the tappet body and adapted to retain the insert relative to the body. A radial interference fit is provided between the retaining plug and the tappet body.

Abstract: A wedge clutch for a camshaft phaser is disclosed. The wedge clutch includes a stator including a pressure plate. The wedge clutch further includes a wedge plate including a notch. The notch includes a pulling surface. The wedge clutch further includes a rotor including a pin inside of a chamber. The pin is configured to rotate the wedge plate in a first circumferential direction relative to the rotor by sliding along the pulling surface as the pin extends out of the chamber to disengage the wedge clutch from the pressure plate.

Abstract: A hydraulic camshaft adjuster (1), in particular a vane-type hydraulic camshaft adjuster, including a rotor (2) and a stator (3) which are mounted to rotate with respect to each other, a cover (10) fixed on the stator (3), including a locking receiver and at least one locking pin (11, 12) accommodated in the rotor (2), the locking pin being slidable in the axial direction and prestressed in the direction of the locking receiver, and a hydraulic channel (27, 28, 29) to apply pressure of the locking pin (11, 12) against the prestress of same, the hydraulic channel being able to be filled and emptied with a hydraulic medium via a central screw, wherein in the rotor (2) at least one additional discharge channel (37, 38, 39, 40) fluidically connected to the hydraulic channel (27, 28, 29) is formed with a discharge valve (33, 34, 35, 36), wherein preferably the discharge valve (33, 34, 35, 36) closes the discharge channel (37, 38, 39, 40) when the locking pin (11, 12) is pressurized and opens the discharge channel

Abstract: The invention relates to a hydraulic valve for phaser. In the hydraulic valve according to the invention a seal element is arranged so that a risk of a transition of oil from an oil cycle or a lubricant cycle of an internal combustion engine or a risk of hydraulic fluid from the hydraulic valve entering a coil of an actuator is avoided.

Abstract: A sliding camshaft is provided which may include a base shaft, an over-molded trigger wheel, and a distal axially movable structure. The distal axially movable structure may further include a distal journal in addition to at least one standard journal and lobe packs. A control groove is defined in the distal axially movable structure. The over-molded trigger wheel is mounted on the distal axially movable structure. The over-molded trigger wheel is operatively configured to move between at least a first position and a second position together with the distal axially movable structure via engagement between the control groove and an actuator. The over-molded trigger wheel may be press fitted on distal axially movable structure and is adapted to accurately communicate with a sensor regardless of the position of the distal axially movable structure.

Abstract: A lubricant pump comprises a shiftable control ring, a pump rotor rotating in the control ring, a pump outlet, and a pressure control system. The pressure control system comprises a pressure control chamber which pushes the control ring into a high pumping volume direction, an engine pressure input port connected to an engine pressure output port of an engine, a pilot chamber connected to the engine pressure input port which pushes the control ring into a low pumping volume direction, and a pressure control valve which controls a pressure in the pressure control chamber. The pressure control valve comprises a control valve plunger which opens/closes a control port to connect/disconnect the pressure control chamber to the atmospheric. The control valve plunger is fluidically connected to the engine pressure input port so that the control valve plunger is pushed by a lubricant pressure of the engine into an open position.

Abstract: A work vehicle includes a vehicle body frame supported on a ground surface by wheels, a reinforcing plate provided in the vehicle body frame, an oil equipment using oil, and a drain pan configured to receive and discharge the oil discharged from the oil equipment. The reinforcing plate defines a drain hole extending vertically therethrough. A tilted face is provided in a face of the reinforcing plate. The tilted face extends with a downward inclination from a dropping point on the reinforcing plate for the oil discharged from the drain pan to the drain hole.

Abstract: An exhaust gas purification filter includes: a honeycomb structure body having partition walls for defining a plurality of cells that extend from an inflow end face to an outflow end face; an inflow side plugging portion; an outflow side plugging portion; and a porous surface trapping layer which is disposed on an inflow surface which is a surface on an inflow cell side which is the cell in which the outflow side plugging portion is disposed, among surfaces of the partition walls, in which the surface trapping layer has a thickness of 10 to 60 ?m and an average pore diameter of 0.3 to 5 ?m, and in a section which is parallel to a cell extending direction.

Abstract: Exhaust aftertreatment assemblies and methods of manufacturing and operating exhaust aftertreatment assemblies. The exhaust aftertreatment assembly includes a reductant delivery device, a reductant source fluidly coupled to the reductant delivery device, a mixing chamber positioned between the reductant delivery device and the reductant source and thereby fluidly coupling the reductant source to the reductant delivery device, and a compressed air source fluidly coupled to the mixing chamber upstream of the mixing chamber with respect to the reductant delivery device. The compressed air source provides compressed air to mix with reductant in the mixing chamber.

Abstract: An aftertreatment system comprises a SCR system. The SCR system includes a housing having an inlet, an outlet and defining an internal volume. At least one catalyst can be positioned within the internal volume. A mounting support is positioned around at least a portion of a perimeter of the housing. A heat shield is positioned around the perimeter of the housing such that the housing is positioned substantially within the heat shield. A portion of the heat shield is disposed on and in contact with the mounting support. A clamp is positioned around a heat shield perimeter. The clamp is positioned on the portion of the heat shield disposed on and in contact with the mounting support. The mounting support is configured to transmit a clamping force of the clamp on the heat shield to the housing to prevent buckling of the heat shield from the clamping force.

Abstract: The reducing agent tank has a tank main body and a feed pipe. The tank main body stores a reducing agent to be supplied to an exhaust gas treatment device. The feed pipe protrudes from the tank main body. The feed pipe is provided to replenish the tank main body with the reducing agent. A support base supports a vessel for the reducing agent for replenishment of the reducing agent tank. The support base is variable in position between a developed position in which the support base is arranged at a greater distance from the tank main body than from the feed pipe in a direction of protrusion of the feed pipe from the tank main body in a plan view and a stored position in which the support base is stored in an exterior cover.

Abstract: One form of the present application is an apparatus including an internal combustion engine structured to produce an exhaust flow, an exhaust system structured to receive the exhaust flow, and a reductant injector structured to inject reductant into a primary passage of the exhaust system upstream of a catalyst. The apparatus further includes an injector passage structured to receive a portion of exhaust upstream of the injector and further structured to flow the exhaust into the primary passage around the injector in a manner such that deposit formation is reduced.

Abstract: An SCR device for a motor vehicle, comprising a tank for storing reducing liquid, an injection device for injection of the reducing liquid into an exhaust gas system of a motor vehicle, a liquid conduit for delivering reducing liquid from the tank to the injection device, a feed pump for conveying reducing liquid in the conduit, and a valve arrangement in the conduit, the valve arrangement designed to interrupt an injection flow in the conduit when the tank-side pressure is greater, than the injection device-side pressure in the conduit by less than an injection threshold value, and to allow the injection flow to pass when the tank-side pressure is greater by at least the injection threshold, the valve arrangement designed to interrupt a return flow in the conduit from the injection device to the tank when the injection device-side pressure is greater than the tank-side pressure by less than a return threshold value, and to allow the return flow to pass through when the injection device-side pressure is great

Abstract: An inorganic fiber-formed article, composed of a mat-shaped inorganic fiber assembly, the inorganic fiber-formed article including needle marks that extend in a direction including a thickness direction of the mat-shaped inorganic fiber assembly, where the needle marks include needle marks A and needle marks B having a diameter smaller than that of the needle marks A, dense portions in which a plurality of the needle marks A lie densely are arranged apart, non-dense portions in which a needle mark density of the needle marks A is lower than that in the dense portions are present between the dense portions in both a first direction which is any mat-surface direction extending through the dense portions and a second direction orthogonal to the first direction, and the needle marks B are present at least in the non-dense portions.

Abstract: A retention system for use with an aftertreatment module is disclosed. The retention system may include a first support mat disposed on at least one surface of the at least one catalyst substrate. The retention system may also include at least one support plate having a corrugated portion disposed on the first support mat. The retention system may further include a second support mat disposed on the corrugated portion.

Abstract: A decomposition reactor for an exhaust system includes an exterior component defining an internal volume and having an inlet and an outlet with the inlet and outlet are formed on a same side of the exterior component. A flow divider is positioned within the internal volume and defines a thermal management chamber and a main flow chamber. A first flow path of exhaust flows from the inlet into the main flow chamber to mix with dosed, and a second flow path of exhaust flows from the inlet into the thermal management chamber to control a temperature of a portion of the flow divider. In some implementations, one or more swirling diverters can be coupled to the flow divider and positioned proximate the outlet of the exterior component to impart a vortical motion to a combined reductant and exhaust gas flow exiting out the outlet.