Abstract: An oil-lubricated slide vane rotary vacuum pump with a slide vane unit, and with an oil separating and reconditioning device, wherein oil and gas are separated by separating devices, possibly complemented by oil coolers and/or oil pumps. One or more monitoring and/or servicing devices are provided, and the oil separating and reconditioning device is installed in an oil separating and reconditioning housing. Side walls extend transversely to a plane of rotation of a slide vane rotor, and define a longitudinal extent of the oil separating and reconditioning housing. The one or more monitoring and/or servicing devices are arranged only in one or more cover parts which are attached to one or both end walls of the oil separating and reconditioning housing. The oil separating and reconditioning housing is formed with the side walls, the bottom wall and the top wall without being configured for a monitoring and/or servicing device.

Abstract: A method for designing and building a wheel that is simultaneously a turbine and an impeller with a plurality of impeller blades, wherein each impeller blade of the plurality of impeller blades is hollow along an entire length of the impeller blade and which leads into a peripheral circular chamber that operates as a fueled engine (THRA). The method includes building an evolving section of an inner channel of the impeller blades with a plurality of strips each having a neutral axis, wherein each impeller blade rests on a profile of a plurality of profiles of a corresponding neutral axis, the profile built for an inlet to the turbine and for inlets to each impeller blade.

Abstract: A rotor has a rotor body having: a flange with a circumferential array of discontiguous apertures; and a surface spaced apart from the flange. One or more rotor balance weight assemblies each have a weight and a fastener. The weight has: a passageway having a first end and a second end; an internal thread along the passageway; and a boss at the first end of the passageway. The boss is in a respective one of the apertures. The fastener has: a shank having a first end and a second end and an external thread engaged to the passageway internal thread; an engagement feature at the shank first end for engagement by a tool to turn the fastener; and a head at the second end contacts the surface.

Abstract: A turbine engine can include an airfoil comprising an outer wall bounding an interior, as well as an airfoil cooling circuit located within the interior and including a feed tube separating into at least first and second branches. A flow divider can be included in the airfoil and positioned to confront the feed tube.

Abstract: An aerofoil member that extends between radially inner and radially outer endwalls which define a gas annulus of the compressor. Aerofoil member has a leading edge, a trailing edge, a pressure surface and a suction surface such that successive cross-sections through the aerofoil member transverse to the radial direction provide respective aerofoil sections. The external shape of the aerofoil member is defined by the stacking of the aerofoil sections on a stacking axis which passes through a reference point common to each aerofoil section. The aerofoil member has lean produced by the projection of the stacking axis onto a plane normal to the engine axis intersecting a first one of the endwalls at an angle of from 5° to 25° to the circumferential direction direction such that the pressure surface faces the first endwall.

Abstract: An airfoiled component comprises: a root section, an airfoil section, a damper pocket enclosed within a portion of the airfoil section, and a damper. The airfoil section includes a suction sidewall and a pressure sidewall each extending chordwise between a leading edge and a trailing edge, and extending spanwise between the root section and an airfoil tip. The damper includes a fixed end unified with a damper mounting surface, and a free end extending into the damper pocket from the damper mounting surface.

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 1.03-1.13 inch (26.2-28.7 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.93-1.03 inch (23.6-26.2 mm). The airfoil element includes at least two of a first mode with a frequency of 2182±10% Hz, a second mode with a frequency of 4966±10% Hz, a third mode with a frequency of 9675±10% Hz, a fourth mode with a frequency of 13154±10% Hz and a fifth mode with a frequency of 14056±10% Hz.

Abstract: This invention relates to a product and a method of preparing ceramic and/or ceramic hybrid materials through the construction of a printed die. The printed die being made by three dimensional printing or additive manufacturing processes possesses both an external geometry and an internal geometry.

Abstract: A core structure (10) includes a first core element (16) including a leading edge section (30), a tip section (32), and a turn section (34) joining the leading edge and tip sections (30, 32). The first core element (16) is adapted to be used to form a leading edge cooling circuit (102) in a gas turbine engine airfoil (100). The leading edge cooling circuit (102) includes a cooling fluid passage (104) having a leading edge portion (106) formed by the first core element leading edge section (30), a tip portion (108) formed by the first core element tip section (32), and a turn portion (110) formed by the first core element turn section (34). Each of the leading edge portion (106), the tip portion (108), and the turn portion (110) of the cooling fluid passage (104) are formed concurrently in the airfoil (100) by the first core element (16).

Abstract: Airfoils for gas turbine engines are provided. The airfoils include an airfoil body extending between a first platform and a second platform, a first platform feed cavity defined by the first platform, a second platform exit cavity defined by the second platform, a first hybrid skin core cooling cavity passage formed within the airfoil body and fluidly connecting the first platform feed cavity to the second platform exit cavity, and at least one purge aperture formed in the second platform and fluidly connecting the second platform exit cavity to an exterior of the second platform. The airfoil body does not include any apertures fluidly connecting the first hybrid skin core cooling cavity passage to an exterior of the airfoil body.

Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge; and a tip shroud connected with a second end of the airfoil along the suction side, the pressure side, the trailing edge and the leading edge, the tip shroud including a tip shroud fillet connecting the airfoil and the tip shroud and having a non-uniform thickness across an axial length of the airfoil.

Abstract: Components for gas turbine engines are provided. The components include a platform, a first airfoil extending from the platform, a first cavity located within the first airfoil, the first cavity includes a forward portion and an aft portion separated by a divider, a cover plate attached to the platform on a side opposite the airfoil, wherein a platform cavity is defined between the cover plate and the platform and wherein the first cavity is fluidly connected to the platform cavity through a first cavity inlet, and a first cavity separating rail dividing the platform cavity into a first platform forward cavity and a first platform aft cavity, wherein the first platform forward cavity is fluidly connected to the aft portion of the first cavity and the first platform aft cavity is fluidly connected to the forward portion of the first cavity.

Abstract: Partitioned baffles and components for installation within gas turbine engines are provided. The partitioned baffles include a baffle body defining a first cavity, the baffle body having a first inlet and at least one first impingement hole arranged for flow to pass through the first cavity from the first inlet to the at least one first impingement hole and a partitioned channel installed within the baffle body and defining a second cavity, wherein the partitioned channel has a second inlet and at least one second impingement hole, wherein a flow through the second cavity flows from the second inlet to the at least one second impingement hole. The baffle body is configured to receive cooling air from a first source and the partitioned channel is configured to receive cooling air from a second source, wherein the first source is different from the second source.

Abstract: A turbine rotor blade includes an airfoil portion having an airfoil defined by a pressure surface and a suction surface; and a squealer rib on a tip surface of the turbine rotor blade, the squealer rib extending from a leading-edge side (toward a trailing-edge side. The squealer rib has a ridge extending in an extending direction of the squealer rib. The turbine rotor blade is configured to provide a clearance between the tip surface of the turbine rotor blade and an inner wall surface of a casing of a turbine such that the inner wall surface of the casing of the turbine faces the tip surface of the turbine rotor blade and the clearance has a local minimum value on the ridge. The clearance is greater than the local minimum value at both sides of the ridge in a width direction of the squealer rib.

Abstract: A guide vane for a twin-spool aircraft turbomachine has an aerodynamic part that includes an internal lubricant cooling passage extending along a principal lubricant flow direction. The aerodynamic part is made in a single piece and also includes heat transfer fins arranged in the passage connecting the intrados and extrados walls and extending approximately parallel to the direction, these fins being distributed in successive rows along the principal direction and made such that for two rows of staggered directly consecutive fins, a first row includes fins forming a positive acute angle A1 with a dummy reference plane, while a second row includes fins forming a negative acute angle A2 with this plane.

Abstract: A component for a turbine engine comprises a wall with a surface along which a hot airflow passes, a second surface along which a cooling airflow passes, and an insert mounted to the wall wherein the material used for the insert can have a higher temperature capability than that of the wall.

Abstract: A turbine shroud assembly of a gas turbine engine for combustion of fuel mixed with air to produce exhaust products includes a blade track having an I-beam construction including ceramic materials and defining a flow surface to guide exhaust products through a turbine section of the gas turbine engine to expand the exhaust products across the turbine section to produce force.

Abstract: A blade track used in gas turbine engines to define an outer boundary of the primary gas path through a turbine section of a gas turbine engine is disclosed. The blade track includes segments comprising ceramic matrix composite materials that are assembled such that the blade track segments keystone against one another to provide a self-supporting full hoop assembly. Circumferentially-extending splines may be used to couple adjacent segments to one. Also disclosed are other heat shielding assemblies used in gas turbine engines that share features with the illustratively disclosed blade track.

Abstract: A temperature sensing device for a turbine of an engine and a method for measuring the temperature of the turbine are disclosed. The turbine includes a turbine stage coupled to a rotatable shaft and an outer casing. First and second sensor holders are disposed between the rotatable shaft and the outer casing, and first and second temperature sensors disposed on the first and second sensor holders, respectively. Each of the first and second sensor holders has only one temperature sensor disposed thereon, the first and second temperature sensors are disposed at first and second distances from the rotatable shaft respectively, and the first and second distances are different.

Abstract: A gas turbine engine having an optical imaging system with a housing configured for mounting to a wall of the turbine engine, a hollow probe extending from the housing and having a longitudinal axis, and an image receiving device at an end of the hollow probe configured to receive at least one of a perspective or image.

Abstract: A non-transitory computer readable medium stores instructions that are executed by a processor of a monitoring that when executed, the processor receives a state of at least one operational parameter of the turbomachinery. Then, the processor determines whether the state is within a region of accuracy of a stored record of a stored state stored in the memory. When the state is within the region of accuracy, the processor determines at least one operating condition from the stored record. Alternatively, when the state is not within the first region of accuracy, the processor stores the state as a new record in the memory.

Abstract: A washing system is described for a gas turbine engine with an axial compressor, comprising: an inlet screen at the air flow inlet of the compressor to protect the compressor from foreign object damage, an arrangement of nozzles and manifolds for spraying the washing liquid, and a washing liquid supply system connected to the arrangement; the inlet screen comprises a supporting structure and a filtering net fixed to the supporting structure; the arrangement of nozzles and manifolds is integrated in the supporting structure of the inlet screen.

Abstract: A gas turbine engine assembly includes a static component and a rotatable component configured to rotate about a central axis of the gas turbine engine assembly relative to the static component. The gas turbine engine assembly further includes a vibration-dampening system configured to dampen vibration of the gas turbine engine assembly.

Abstract: An on-board injector that delivers discharge air toward a turbine rotor of a gas turbine engine includes a second wall spaced form a first wall to define an annular inlet about an engine longitudinal axis and a multiple of airfoil shapes between the first wall and the second wall to segregate discharge air from the annular inlet, and a multiple of bypass apertures each along a radial axis transverse to the engine longitudinal axis through each of the multiple of airfoil shapes and the respective first wall, the second wall.

Abstract: A turbocharger having a rotatable shaft, a stationary housing, a turbine wheel mounted on one end of shaft, a compressor wheel mounted onto an opposite end of shaft, and at least one rolling bearing disposed between the shaft and the housing. The rolling bearing includes a stationary outer ring fixed to the housing, a rotatable inner ring fixed to the shaft, at least one row of balls disposed in a rolling chamber defined between the outer ring and inner ring, and an annular non-deformable cage providing circumferentially a plurality of through holes forming pockets where the balls are housed. The pockets being axially delimited between annular cage heels. Each pocket of cage is extended by a slot through one of cage heels, the cage heel provided with the slots being axially oriented towards the interior side of turbocharger.

Abstract: Aspects of the disclosure are directed to an engine oil damper comprising: a bearing support, and a housing radially outward from the bearing support and co-axial with the bearing support, where at least one oil flow restrictor is formed with respect to at least one of the bearing support and the housing, where the at least one oil flow restrictor is configured to at least partially interrupt a flow of oil in an annulus radially defined between the bearing support and the housing.

Abstract: A method of manufacturing a superalloy part including a first portion including a majority by weight of a first superalloy and a second portion including a majority by weight of a second superalloy, the second portion extending from the first portion, the method including depositing the second portion on the first portion by a direct metal deposition method, deposition of the second portion including depositing a first layer, then depositing a second layer on the first layer, the first layer including the first and second superalloys, the first layer presenting a content by weight of the first superalloy that is strictly greater than that content by weight of the second layer and strictly less than that content by weight of the first portion, the second layer presenting a content by weight of the second superalloy that is strictly greater than that content by weight of the first layer.

Abstract: A thermal barrier attachment seal for a gas turbine engine component includes a spine having a first surface and a second surface facing opposite the first surface. A first layer of insulation is provided on the first surface. A second layer of insulation is provided on the second surface to provide a thermal barrier seal between a first gas turbine engine component and a second gas turbine engine component. A fan section for a gas turbine engine is also disclosed.

Abstract: A turbine component assembly is disclosed, including a first component, a second component, and a cantilever spring. The first component is arranged to be disposed adjacent to a hot gas path, and includes a ceramic matrix composite composition. The second component is adjacent to the first component and arranged to be disposed distal from the hot gas path across the first component. The cantilever spring is attached directly to the second component as a compliant contact interface between the first component and the second component. The cantilever spring provides a radial spring compliance between the first component and the second component. During operation, the cantilever spring directly contacts and supports the first component.

Abstract: The invention relates to the field of support interfaces, and in particular to such a support interface (30a, 30b) for an engine casing (90) and comprising a coupling part (50), a first plurality of bolts (80), and a plurality of pegs (70). The coupling part (50) has an outer face (52) presenting a cavity (42) suitable for receiving a support arm (20a, 20b), and an inner face (51) suitable for being mounted on an outer face (93) of the engine casing (90), together with a first plurality of orifices (53) between the outer face (52) and the inner face (51) of the coupling part (50). Each bolt (80) has a threaded shank (82) received in an orifice (53) of the first plurality of orifices (53), and a head (81) suitable for bearing against the outer face (52) of the coupling part (50).

Abstract: A separator for separating at least a part of particles from an air flow flowing inside a conduit comprises at least one separating unit. Each separating unit comprises: a protrusion, extending inwardly from an inner surface of the conduit and configured to direct at least a part of the particles towards a wall of the conduit. The separating unit further comprises a hole throughout a thickness of the wall, positioned downstream of and adjacent to the protrusion, and configured to pass the particles moving towards the wall to an outer side of the conduit.

Abstract: A drainage system for a stage of a turbine. The drainage system may include at least one annular recess defined in the inner surface of the casing of the turbine and configured to accumulate liquid therein. An axial slot and a radial slot may be formed in a diaphragm of the turbine, the axial slot extending between the upstream and downstream faces of the diaphragm. The drainage system may further include a tubular member including an axially extending tubular portion disposed in the axial slot and a radially extending tubular portion disposed in the radial slot. The radially extending tubular portion may be sized and configured to fluidly couple the at least one annular recess and the axially extending tubular portion, such that liquid in the at least one annular recess may be drained therefrom and discharged from the stage of the turbine via the axially extending tubular portion.

Abstract: A valve train device, in particular for an internal combustion engine, includes a support element and a cam element which can be moved axially relative to the support element. The valve train device further includes a switch unit for axially moving the cam element, which switch unit includes a displacer that is intended to be at least operatively inserted between the support element and the cam element in order to axially move the cam element.

Abstract: A retention device for interconnecting a lash adjuster and a finger follower that supports a bearing of a valve actuating mechanism for an internal combustion engine, wherein the retention device includes a body having a lower member, an upper member spaced from the lower member, and an intermediate member interconnecting the lower and upper members. The lower member includes an aperture that is adapted to be received in a groove of the lash adjuster. The intermediate member is secured to the finger follower such that the retention device interconnects the lash adjuster and the finger follower. The upper member includes a bearing retention mechanism that limits movement of the bearing of the finger follower and retains the bearing relative to the finger follower prior to mounting the finger follower and lash adjuster as a part of the valve actuating mechanism of the internal combustion engine.

Abstract: A valve train assembly (16) includes a fuel injector (1), an intake rocker lever assembly (10), and an exhaust rocker lever assembly (14). The intake and exhaust rocker lever assemblies (10) can include an eccentric hydraulic lash adjuster (11) that is located in the nose (31) of the respective rocker lever assemblies (10). The rocker lever assemblies (10) are configured to allow a clearance area between a nose (31) of the intake rocker lever assembly (10) and the nose (31) of the exhaust rocker lever assembly (14). As such, the fuel injector (1) can be positioned in the clearance area, while still allowing the eccentric hydraulic lash adjusters to apply a load onto a corresponding valve bridge (2). For example, the eccentric hydraulic lash adjuster (11) can include an outer housing (20) and a pivot ball (21), wherein the pivot ball (21) is positioned at an offset (23) from a lateral centerline of the outer housing (20).

Abstract: A camshaft phaser assembly, including: an axis of rotation; a first hydraulic camshaft phaser including a stator arranged to receive rotational torque and including a plurality of radially inwardly extending protrusions, a rotor including a plurality of radially outwardly extending protrusions circumferentially interleaved with the plurality of radially inwardly extending protrusions, and a plurality of phaser chambers, each phaser chamber circumferentially bounded by a respective radially inwardly extending protrusion included in the plurality of radially inwardly extending protrusions and a respective radially outwardly extending protrusion included in the plurality of radially outwardly extending protrusions; a second hydraulic camshaft phaser; a cap; and a fluid chamber bounded in part by the cap and in fluid communication with a phaser chamber included in the plurality of phaser chambers; and a bolt arranged to non-rotatably connect the rotor and the cap to a camshaft.

Abstract: A driving rotor is configured to rotate about a rotational shaft center in conjunction with a crankshaft. A driven rotor is configured to rotate about the rotational shaft center in conjunction with the camshaft. A deceleration mechanism is configured to change a relative rotational phase between the driving rotor and the driven rotor by using a driving force of an electric motor. The deceleration mechanism includes an internal gear portion, which includes an internal tooth extending radially inward, and an external gear portion, which includes an external tooth extending radially outward and engaging with the internal tooth. A linear expansion coefficient of the external gear portion is greater than a linear expansion coefficient of the internal gear portion.

Abstract: The present invention relates to an oil filtration system for off-line filtering of contaminated oil from diesel machinery (1), the oil filtration system comprising a system inlet (4) for receiving an inlet flow of contaminated oil from the diesel machinery (1), a system outlet (5) for releasing an outlet flow of filtered oil to the diesel machinery (1), an oil filtration unit which is in fluid communication with the system inlet (4) and the system outlet (5), the oil filtration unit comprising an oil filter (6) which is adapted to receive the contaminated oil and to release the filtered oil, a pumping unit (7) which is arranged upstream of the oil filtration unit, the pumping unit (7) being adapted to provide a flow of contaminated oil in a direction from the system inlet (4) to the oil filtration unit, a temperature sensor (13) for measuring an oil temperature, the temperature sensor (13) comprising a signal transmitter adapted to transmit a first electrical signal reflecting the measured oil temperature, a

Abstract: In one embodiment, there is provided a dock for a replaceable fluid container for an engine, the fluid container having: a fluid reservoir; and at least one fluid port having a coupling adapted to couple with a fluid circulation system associated with the engine; the dock having: a fastening mechanism configured to cooperate with the container such that, as the container is inserted into the dock, the fastening mechanism acts first to seat the fluid container in the dock but in an undocked condition and then, as the container is inserted further into the dock, acts to bring the fluid container into an engaged condition in which the fluid container is docked with a docking interface of the dock.

Abstract: Various systems and methods are provided for a lubricant filter. In one example, a method for a lubricant filter comprises indicating a condition of the filter based on a difference between a measured pressure differential and an expected pressure differential during select conditions in which all lubricant pumped by a pump upstream of the filter flows into the filter.

Abstract: An exhaust system for an internal combustion engine, especially diesel internal combustion engine, includes an exhaust gas flow duct (12). At least one exhaust gas treatment unit (23, 26, 28, 30) is provided in an exhaust gas treatment duct area (16) of the exhaust gas flow duct (12). The exhaust gas treatment duct area (16) of the exhaust gas flow duct (12) extends, in at least some areas, in an insulation volume (20), through which exhaust gas discharged from the exhaust gas treatment duct area (16) can flow.

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: An after treatment method for a lean-burn engine is disclosed. The after treatment method is configured to control an after treatment system sequentially equipped with an ammonia production catalyst module, a selective catalytic reduction catalyst, and a CO clean-up catalyst on an exhaust pipe through which an exhaust gas flows. In the after treatment method, the engine is operated sequentially at a stoichiometric air/fuel ratio (AFR) and a lean AFR prior to entering a rich AFR.

Abstract: A reducing agent dosing valve (24) on an exhaust system (12) of an internal combustion engine (10), having a pump (32) which generates an injection pressure (p_24), and having a control unit (14) which actuates the reducing agent dosing valve (24) with actuation signals is presented, wherein the actuation signals are formed in a manner dependent on a reducing agent pressure (p_36) prevailing at the pump side. The method is distinguished by the fact that the actuation signals are formed additionally in a manner dependent on at least one estimated value for an influence of a drop in the injection pressure (p_24), which occurs upon the opening of the reducing agent dosing valve (24), on the injected reducing agent quantity.

Abstract: An aftertreatment system includes: a selective catalytic reduction system including at least one catalyst for decomposing constituents of an exhaust gas produced by an engine, the exhaust gas having a pressure pulsation frequency; an exhaust conduit fluidly coupled to the selective catalytic reduction system and structured to deliver the exhaust gas to the selective catalytic reduction system from the engine; at least one mixer positioned in the exhaust conduit; and a reductant insertion assembly fluidly coupled to the exhaust conduit and structured to insert a reductant into the exhaust conduit upstream of the at least one mixer. The at least one mixer is structured to have a natural frequency matching the pressure pulsation frequency so as to cause resonant vibration in the at least one mixer, the resonant vibration causing reductant deposits to be removed from the at least one mixer.

Abstract: Methods and systems are provided for using thermoelectric generators to recover waste heat from and diagnose turbocharger systems. In one example, a method may include adjusting one or more engine operating parameters based on an amount of current generated from one or more thermoelectric generators coupled to a turbocharger.

Abstract: An aftertreatment system comprises a housing defining an internal volume. A filter is disposed in the housing and configured to remove particulate matter included in the exhaust gas. A delta pressure sensor configured to measure an inlet apparent pressure value upstream of the filter. An ambient pressure sensor separate from the delta pressure sensor is configured to measure an ambient pressure value of an ambient environment in which the aftertreatment system is located. A controller is configured to receive the inlet apparent pressure value, receive the ambient pressure value from the ambient pressure sensor, determine a relative inlet exhaust pressure value based upon the inlet apparent pressure value and the ambient pressure value, and adjust an exhaust flow rate of the exhaust gas based at least on the relative inlet exhaust pressure value.

Abstract: A method to determine the actual quantity of metal powders or ashes trapped in a particulate filter, which involves determining an estimated value of the quantity of metal powders trapped in the particulate filter based on an estimation model; determining a measured value of the quantity of metal powders trapped in the particulate filter; updating the estimated value of the quantity of metal powders trapped in the particulate filter as a function of the measured value; and determining the actual quantity of metal powders or ashes trapped in a particulate filter as a function of the update of the estimated value of the quantity of metal powders trapped in the particulate filter.

Abstract: A flexible tube system having an end section formed from an inner rigid tube and an outer shell, and the end section is joined to a central flexible portion having an inner decoupler tube, and an outer shell bridge is joined to the outer shell and the flexible central portion to define an insulation space.

Abstract: An internal combustion engine exhaust system mixer includes a mixer body (12) with deflection elements (16) extending radially outwards from a mixer body center (14). A ring-shaped carrier area (22) adjoins the mixer body radially on the outside and encloses a mixer longitudinal axis. The carrier area includes a mixer connection area (24) for connecting the mixer (10) to an exhaust system component. A pipe connection wall (30) adjoins the mixer connection area and has a wall inner surface (32). A mixer body carrier wall (34) adjoins the mixer connection area, carries the mixer body, and is enclosed by the pipe connection wall. A first transition surface (40) adjoins the wall and is arched essentially continuously concavely between the wall inner surface and the wall outer surface, and axially defines a ring-shaped pipe-mounting intermediate space (38) between the pipe connection wall and the mixer body carrier wall.