Abstract: An airfoil for a gas turbine engine comprises a cooling circuit defined within the airfoil providing a flow of cooling fluid within the airfoil. The cooling circuit exhausts the flow of cooling fluid out a slot opening comprising an airfoil element. The slot opening further defines an acceleration zone and a deceleration zone to meter the flow of cooling fluid within the airfoil.

Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can further comprise a leading edge cooling circuit defined by a supply passage, a pin bank passage divided into one or more sub-circuits by pin banks disposed within the pin bank passage, and at least first and second cooling passages. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.

Abstract: A blade assembly includes a blade and a blade platform secured to the blade. The blade extends radially from the blade platform. The blade platform includes at least one platform airflow passage located therein. A gusset extends from the blade to the blade platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage. a gas turbine engine includes a combustor and a plurality of gas turbine engine components located in fluid communication with the combustor. The gas turbine engine component includes an airfoil portion and a platform secured to the airfoil portion. The platform includes at least one platform airflow passage positioned therein. A gusset extends from the airfoil portion to the platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage.

Abstract: An article and method of cooling an article are provided. The article includes a body portion having an inner surface and an outer surface, the inner surface defining an inner region, at least one up-pass cavity formed within the inner region and extending from a base of the body portion towards a tip of the body portion, and a cap formed in each up-pass cavity, each cap being adjacent to the tip of the body portion, having at least one aperture formed therein, and being arranged and disposed to direct fluid towards the tip of the body potion. The method includes directing a fluid into the first up-pass cavity, passing the fluid through at least one aperture in the cap, contacting the tip of the article with the fluid, receiving the post-impingement fluid within a down-pass cavity, and directing the post-impingement fluid through the down-pass cavity.

Abstract: A bladed disk for a gas turbine engine is provided. The bladed disk includes a rotor disk, a plurality of rotor blades, and an interlocking transition zone. The rotor disk includes a plurality of fused layers of a first material formed via additive manufacturing and defines an outer rim. The plurality of rotor blades includes a plurality of fused layers of a second material formed via additive manufacturing. The interlocking transition zone includes a plurality of projections alternately extending from the outer rim of the rotor disk and the plurality of rotor blades, respectively, to undetachably couple the rotor disk and the plurality of rotor blades.

Abstract: A gas turbine engine having a combustor, turbine and transition duct to channel hot gas from combustor to turbine. The transition duct has an internal surface on which the hot gas impinges causing a varying temperature profile. A thermal barrier coating is located on the internal surface having a first and second thermal barrier coating patch. The first patch having a first thickness located on the internal surface and within a first area subject to a higher temperature than an uncoated part and bounded by a first isotherm of a first temperature. The second patch having a second thickness located on the internal surface and within a second area subject to a higher temperature than the uncoated part and bounded by a second isotherm of a second temperature. The second temperature is higher than the first temperature and the second thickness is thicker than the first thickness.

Abstract: A nozzle assembly for a gas turbine engine includes at least one pair of fixed vanes to define a nozzle between the pair of fixed vanes. The vanes can have an interior chamber defining a cooling circuit with a particle separator located within the interior chamber. The particle separator, which can comprise a virtual impactor, can have an accelerator for accelerating fluid moving through the virtual impactor such that the flow path is divided into a major flow moving into the interior chamber and a minor flow moving into a particle collector defined within the virtual impactor. The accelerator accelerates the fluid such that particles within the fluid are carried by their momentum into the particle collector with the minor flow, removing the particles from the major flow of fluid moving into the interior chamber.

Abstract: A turbine nozzle configured to be disposed in a turbine includes a suction side, a pressure side, and a bulge disposed on the suction side. The suction side extends between a leading edge and a trailing edge in an axial direction and transverse to a longitudinal axis of the turbine nozzle, and extends a height of the turbine nozzle in a radial direction along the longitudinal axis. The pressure side is disposed opposite the suction side and extends between the leading edge of the turbine nozzle and the trailing edge of the turbine nozzle in the axial direction, and extends the height of the turbine nozzle in the radial direction. The bulge is disposed on the suction side protruding relative to the other portion of the suction side in a direction transverse to both the radial and axial directions. The turbine nozzle has a first periphery defined at a first cross-section at a first location along the height of the turbine nozzle by selected coordinate sets listed in Table 1.

Abstract: Turbine nozzles are provided for gas turbine engines. The turbine nozzle includes an arcuate inner band; an arcuate outer band; and a nozzle vane disposed between the arcuate inner band and the arcuate outer band. The radially inner end of the nozzle vane is attached to the arcuate inner band through an interlocking transition zone comprising a plurality of projections alternately extending from the radially inner end of the nozzle vane and the arcuate inner band, respectively, to undetachably couple the nozzle vane and the arcuate inner band. Optionally, the radially outer end of each nozzle vane is also attached to the arcuate outer band through an interlocking transition zone.

Abstract: A gas turbine engine arcuate leaf seal assembly includes arcuate leaf seal extending radially and circumferentially between adjacent first and second turbine components. Upper and lower leaf seal portions of leaf seal are in radially spaced apart arcuate upper and lower grooves in the first and second turbine components respectfully. The seal includes an arcuate body and a circumferential retention tab extending radially away from body and disposed in a notch in a wall of grooves. Seal may have a thickness between 3 mils and 35 mils and/or torsional stiffness between 0.015 and 0.15 lb/in. Turbine components may be radially adjacent turbine nozzle upper and lower components. The upper or lower component may be made of a ceramic matrix composite material. Annular cooling air plenum including flow cavities in inner support ring segments may be in lower component and in flow communication with hollow fairing airfoils.

Abstract: Aspects of the disclosure are directed to a gas turbine engine, comprising a sealing assembly that includes a non-contacting HALO seal, a ring constructed as a full ring and configured as a carrier of the seal, a sealing land configured to rotate and interface to the seal. In some embodiments, the engine further comprises a vane, where the ring is coupled to the vane.

Abstract: Aspects of the disclosure are directed to an engine of an aircraft comprising: a first seal located forward of a disk of a turbine section of the engine, a second seal located forward of the disk of the turbine section and radially inward of the first seal relative to an axial centerline of the engine, where the first and second seals are floating, non-contact seals.

Abstract: Shrouds and methods for forming turbine components are provided. A shroud includes a shroud body which includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a forward flange extending from the outer surface of the shroud body, and a rear flange extending from the outer surface of the shroud body, the rear flange axially spaced from the forward flange. The shroud further includes a cooling passage defined in the shroud, the cooling passage extending generally circumferentially through the shroud.

Abstract: According to various embodiments, disclosed is a blade outer air seal assembly for a turbine engine comprising a main body portion that extends generally axially, with respect to a central axis of the turbine engine, from a leading edge portion of the main body to a trailing edge portion of the main body, wherein the leading edge portion includes a leading edge wall having a undercut profile along at least a portion of the leading edge wall, wherein the main body portion comprises cooling passages comprising a leading edge cooling passage adjacent to the leading edge wall, having a leading edge periphery on a side of the leading edge cooling passage adjacent to the leading edge wall, which generally conforms to the undercut profile of the leading edge wall.

Abstract: An assembly for mounting a circumferential shroud to a casing, including a plurality of arcuate shroud segments collectively forming the circumferential shroud. Each segment includes a circumferentially extending wall and a channel extending from the wall. The channel is receivable in a hole passing through a circumferential casing and has a first connector. A fastener has a head and a shank, which is receivable in the channel and has a second connector that engages with the first connector. A first spacer receives the channel and a second spacer receives the shank and sit adjacent the head of the fastener on either side of the casing. The spacers can be selected to adjust for optimal radial positioning of the shroud and of probes received within a space defined between the casing and the shroud for monitoring rotor speed and the tip air gap of a turbine rotor contained in the casing.

Abstract: The invention relates to a module for a gas turbine comprising a rotationally symmetrical outer casing of a first material having a first linear thermal expansion coefficient, a rotationally symmetrical component for guiding hot gas of a second material having a linear thermal expansion coefficient which is lower than the first coefficient, at least one annular structure arranged radially within the component, and at least three struts having a radially inner end secured on the outer casing and a radially outer end secured on the annular structure. The component also comprises at least one first fixing which is free in radial direction and fixed in axial direction and arranged between the component and the outer casing and/or the annular structure, as well as at least three second fixings having an elastic effect in radial, axial and/or circumferential direction and being arranged between the component and the strut and/or the annular structure.

Abstract: A bypass valve assembly for use in turbine generators includes a valve body defining a central bore and a plurality of passageways. Each passageway has a smaller area at an inlet portion and a larger area at an outlet portion to define a flared passageway. A plurality of bypass valves is disposed within the plurality of passageways within the valve body. Each bypass valve includes a base portion and a nose portion, with each nose portion defining a predefined contoured surface area. At least a portion of the contoured surface area includes a wear coating disposed thereon. Optionally, the wear coating includes a plasma enhanced magnetron sputtering nanocoating.

Abstract: A gas turbine engine system includes a gas turbine engine with a rotating element, at least one primary rotor shaft coupled to the rotating element, and a primary generator coupled to the at least one primary rotor shaft. The system further includes at least one auxiliary rotor shaft coupled to the at least one primary rotor shaft, such that rotation of the at least one primary rotor shaft causes rotation of the at least one auxiliary rotor shaft. The at least one auxiliary rotor shaft is oriented substantially perpendicularly to the at least one primary rotor shaft. An auxiliary generator is coupled to the at least one auxiliary rotor shaft, such that the auxiliary generator is in parallel configuration to the primary generator.

Abstract: Specific operation is executable in a Rankine-cycle power-generating apparatus. In the Rankine-cycle power-generating apparatus, a) in the specific operation, the control device adjusts the degree of opening of the opening/closing device so that the direct-current electric power absorbed by the electric power absorber approaches first electric power, or b) in the specific operation, the degree of opening of the opening/closing device is increased to the predetermined intermediate degree of opening so that the direct-current electric power absorbed by the electric power absorber falls within a predetermined range.

Abstract: A method for assisting with the detection of damage to a duct, the duct being designed such as to convey a pressurised air flow collected at the outlet of a high pressure compressor of a turbine engine to a first pressure sensor and a second pressure sensor of a computer, the method including: (A) measuring a first air pressure at the first pressure sensor; (B) measuring a second air pressure at the second pressure sensor; (C) determining a theoretical pressure of the air flow at the outlet of the high-pressure compressor; (D) performing a first test regarding the difference between the first value and the theoretical pressure; (E) performing a second test regarding the difference between the second value and the theoretical pressure; and performing a final test, which is positive if the first difference test and the second difference test are positive, and negative otherwise.

Abstract: Methods for retrofitting a turbomachine are provided. A first trip cup of the turbomachine may be replaced with a second trip cup. The first trip cup may include a throw-out arm connected to a first trip cup spring. The second trip cup may include a plunger disposed in a hole defined by the second trip cup and a plunger spring encircling the plunger in the hole. The first trip cup may be removed from the turbomachine and the second trip cup installed such that a location of the plunger in the turbomachine is the same as a location of the throw-out arm in the turbomachine when the first trip cup was installed on the turbomachine. The tension in the plunger spring may be adjusted such that, when a speed of the turbomachine exceeds a predetermined value, the plunger actuates a trip paddle located adjacent the second trip cup.

Abstract: An airfoil for an axial flow machine includes: an airfoil body extending in a radial direction; a platform (an end wall) provided at an end portion of the airfoil body in the radial direction, the end wall being formed into a plate shape as a wall of a channel in which the airfoil body is installed and which supports the airfoil body; and at least one convex portion formed so as to protrude from a back surface of the platform in a direction away from the airfoil body. The convex portion is formed integrally with a portion for generating a node of a primary vibration mode when an edge portion of the platform vibrates as a free end of the primary vibration mode.

Abstract: Cooling air extracted from a gas turbine engine compressor is sent to a nozzle vane cooling passage inlet, through the cooling passage, and to a purge tube of the vane. A mixing chamber formed in a diaphragm cavity receives fluid from the purge tube and directs it through exit passage(s) formed through a side wall of the mixing chamber and/or diaphragm cavity to a diametral surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the diametral surface and/or in a rotation direction of a turbine wheel adjacent the diaphragm.

Abstract: A mid-turbine frame module comprises an outer structural ring, an inner structural ring and a plurality of circumferentially spaced-apart spokes structurally interconnecting the inner structural ring to the outer structural ring. At least one of the tubular spokes accommodates a service line. The remaining spokes with no service line have an internal architecture which mimics an air cooling scheme of the at least one spoke housing a service line in order to provide temperature uniformity across all spokes.

Abstract: A shroud assembly for a gas turbine engine includes a shroud, hanger, and a hanger support mounted adjacent to a plurality of blades. The hanger can have an interior chamber defining a cooling circuit with a particle separator located within the interior chamber. The particle separator can have an inlet for accepting a flow of cooling fluid, such that a the flow of cooling fluid separates into a major flow and a minor flow carrying particles or particulate matter along the minor flow into a particle collector comprising at least a portion of the particle separator. Particles become constrained to the minor flow and pass into the particle collector, while the major flow is separated into the remaining area of the interior chamber to remove the particles from the flow of cooling fluid passing into the interior chamber.

Abstract: Cooling air extracted from a gas turbine engine compressor is sent to nozzle vane cooling passage inlets, through the cooling passages, and to purge tubes of a set of two or more vanes. A mixing chamber formed between the purge tubes in a diaphragm cavity receives fluid from the purge tubes and directs it through exit passage(s) formed through a wall of the mixing chamber to a surface of the diaphragm. The exit passage(s) can be inclined to induce a fluid velocity component substantially parallel to the surface and/or in a rotation direction of a turbine wheel.

Abstract: A jet engine with a bearing chamber, a sealing chamber, a de-aeration chamber and a bearing chamber support, the support delimiting the bearing chamber comprising at least one bearing appliance in certain areas. The bearing chamber is separated from the sealing chamber via a sealing appliance, with the sealing chamber being separated via a further sealing appliance from the de-aeration chamber that is arranged at the side of the sealing chamber facing away from the bearing chamber. The sealing chamber is connected to a sealing air conduit, by which the bearing chamber can be supplied with a sealing air volume flow. The de-aeration chamber is connected to a de-airing appliance via which a volume flow can be discharged from the de-aeration chamber into a core flow channel of the jet engine. The de-airing appliance is embodied as at least one air extraction duct with a tubular flow cross-section.

Abstract: A turbine bypass housing is provided. The housing includes a body having an inlet end and an outlet end and defining an interior, an outlet flange is configured at the outlet end and has a rim diameter, and an inlet flange is configured at the inlet end and has a flange thickness. An interior wall of the body has a first fillet radius proximal to the inlet flange and at least one boss is configured on an exterior of the body, wherein the boss defines a boss aperture therein, the boss aperture extending from an exterior of the body to the interior of the body. The flange thickness is 0.200±0.005 inches (0.508±0.013 cm).

Abstract: A mid-turbine frame of a gas turbine engine has a structural ring assembly comprising an outer ring, an inner ring having a plurality of threaded bosses extending from a radially outer surface thereof, and a corresponding number of structural spokes interconnecting the inner ring to the outer ring. Each spoke has a radially inner threaded end threadably engaged in an associated one of the threaded bosses on the inner ring.

Abstract: A spoke locking arrangement comprising a washer seated in a seat defined in a structural ring of a gas turbine engine, the washer having a portion thereof plastically deformed into an anti-rotation notch defined in the structural ring, thereby locking the washer against rotation in the seat, the washer further comprising a set of holes for receiving corresponding bolts, and wherein the washer further has at least one anti-rotation tab at each hole, the anti-rotation tabs being deformable in engagement with the bolts to individually lock the same against rotation.

Abstract: A horizontal support tool for an engine build stand, the horizontal support tool includes a support tube along an axis and a tie shaft between a handle and a puck assembly, said puck assembly including a puck selectively extendable and retractable transverse to the axis in response to rotation of the handle. A method of horizontally assembling a portion of a gas turbine engine including mounting a first module to an engine build stand; installing a horizontal support tool into the first module, the horizontal support tool supported in a spherical bearing supported by the engine build stand; and installing a second module to the first module, the horizontal support tool operable to at least partially support second module.

Abstract: An apparatus for supporting a tool in an assembled apparatus. The apparatus includes a support structure, the support structure having a central member and a plurality of support members pivotally mounted on the central member. The support members are movable between a non-deployed position in which the support members extend a minimum distance from the central member and a deployed position in which the support members extend a maximum distance from the central member.

Abstract: A supercritical CO2 generation system using plural heat sources, includes: a pump configured to circulate a working fluid; heat exchangers configured to heat the working fluid using an external heat source; turbines configured to be driven by the working fluid heated by passing through the heat exchanger; and recuperators configured to exchange heat between the working fluid passing through the turbine and the working fluid passing through the pump to cool the working fluid passing through the turbine, in which the heat exchanger includes constrained heat exchangers having an emission regulation condition of an outlet end and heat exchangers without the emission regulation condition.

Abstract: Apparatus for utilizing heat wasted from an engine includes first pressure detecting means (73) and first temperature detecting means (81) for detecting a pressure and a temperature in a refrigerant passage extending from a condenser (38) to a refrigerant pump (32), second pressure detecting means (72) and second temperature detecting means (82) for detecting a pressure and a temperature in a refrigerant passage extending from a heat exchanger (36) to an expansion device (37), and control means (71) responsive to these four detecting means when operating a Rankine cycle (31). Means (71) is for diagnosing whether or not an electromagnetic clutch (35) is stuck responsive to either the first pressure detecting means (73) and the first temperature detecting means (81), or the second pressure detecting means (72) and the second temperature detecting means (82).

Abstract: A device for expanding steam, whereby this device comprises an expander with an inlet that is connected to an inlet pipe and an outlet that is connected to an outlet pipe, whereby the inlet pipe is provided with an inlet valve and the outlet pipe is provided with an outlet valve for isolating the space between the valves, by closing these valves when the expander is not operating, whereby the device is provided with a steam supply that conditions the space between the valves when the expander is not operating, such that no air can penetrate into the space.

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 present invention relates to a variable camshaft adjuster (VVT) for an internal combustion engine with a VVT component, preferably a locking disc, composed of material produced from powder metal with a locking bore, which extends from a first surface of the VVT component, preferably the locking disc, into this, wherein a locking bolt of a variable valve control engages into the locking bore and the locking bore has a connected oil duct which also extends from the first surface into the VVT component and discharges radially into the locking bore, wherein a base of the locking bore has an elevation, preferably in the form of an elevated shoulder which serves as a bearing surface of the locking bolt and the oil duct has a depth which is smaller than that of the locking bore. A VVT component, in particular a locking disc as well as a method for producing the locking disc or the camshaft adjuster are furthermore claimed.

Abstract: The present invention provides a seal ring, for a variable valve timing system, which is resistant to breakage when the seal ring is expanded at a seal ring mounting time even in a case where the seal ring is thick and allowed to have a complicated configuration by performing injection molding and achieve a small oil leak, a low degree of friction, and improved wear resistance. In the variable valve timing system having a camshaft (5) for driving an intake valve of an internal combustion engine and an exhaust valve thereof, an inner rotational body (3) fixed to the camshaft (5), an outer rotational body (4) making a rotational motion relative to the inner rotational body (3) by supply of hydraulic oil at a time of altering opening and closing timings of the intake valve and the exhaust valve, and a shaft body (2) mounted on rotational body (3).

Abstract: A variable valve duration system may include a camshaft, a first cam portion including a first cam, into which the camshaft is inserted and of which a relative phase angle of the first cam with respect to the camshaft is variable, an inner bracket transmitting rotation of the camshaft to the first cam portion, a slider housing into which the inner bracket is rotatably inserted, a first rocker arm having a first end contacting the first cam and a second end connected to a first valve, a rocker shaft to which the first rocker arm is rotatably connected, a solenoid valve to selectively supply hydraulic pressure, and a position controller to selectively change a position of the slider housing according to the selective supplying of the hydraulic pressure from the solenoid valve.

Abstract: An adjustable camshaft may include an inner shaft and an outer shaft arranged coaxially thereto. The camshaft may also include a camshaft adjuster having a stator connected to the outer shaft in a torque-proof manner, and a rotor connected to the inner shaft. The camshaft may further include an integral first connection contour provided at an end of the inner shaft, and an integral second connection contour complementary to the integral first connection contour and provided on the rotor. The connection contours may directly or indirectly enable an interlocking connection between the inner shaft and the rotor.

Abstract: A hydraulic camshaft adjuster (1) having a rotor (2) with at least two parts is provided. The at least two-part rotor (2) is mounted such that it can rotate about an axis (A) and consists of a first rotor element (4) and a second rotor element (6). At least one first, second and/or a third drainage recess (8, 10, 12) is formed in the first and/or second rotor element (4, 6), such that oil can be discharged from a contact surface (14) of the first and second rotor elements (4, 6) of the camshaft adjuster (1) to the outer side (16) of the first and/or second rotor elements (4, 6).

Abstract: A camshaft adjuster for an internal combustion engine, having a stator, a rotor mounted rotatably in the interior of the stator, and a locking cover connected to the stator. A hydraulically actuatable locking element is received in the rotor and engages into the locking cover in at least one blocking position, so as to block a rotation of the rotor relative to the stator, and is arranged in at least one unlocking position so that the rotor can be rotated relative to the stator.

Abstract: Methods and systems are described for an engine with a cam torque actuated variable cam timing phaser. Phaser positioning control is improved by reducing inaccuracies resulting from inadvertent spool valve and/or phaser movement when the spool valve is commanded between regions. In addition, improved spool valve mapping is used to render phaser commands more consistent and robust.

Abstract: A variable valve duration/variable valve lift system may include a camshaft, a first cam portion including a first cam, into which the camshaft is inserted and of which a relative phase angle of the first cam with respect to the camshaft is variable, an inner bracket transmitting rotation of the camshaft to the first cam portion, a slider housing into which the inner bracket is rotatably inserted, a first rocker arm having a first end contacting the first cam, a rocker shaft to which the first rocker arm is rotatably connected, a solenoid valve configured to selectively supply hydraulic pressure, a position controller configured to selectively change a position of the slider housing, a first bridge connected to a second end of the first rocker arm and to which a first valve is connected, and a valve lift disposed within the first bridge.

Abstract: A fluid pump includes a housing defining a cavity. An end plate is disposed within the cavity and divides the cavity into a gear section and an end section. A gear set is disposed within the gear section and comprises at least one gear rotatable about an axis. The end plate is movable longitudinally along the axis for compressing the gear set. A channel is in fluidic communication with the end section for supplying a fluid to the end section to force the plate toward the gear set.

Abstract: In some embodiments, there is provided a method of controlling a pressure gradient between a combustion chamber and a crankcase of an engine, the method having: receiving, at a control device, a signal indicating that a lubricant container is coupled to a lubricant circulation system associated with the engine, in response to the received signal, providing data to cause operation of a suction control device for facilitating control of the pressure gradient.

Abstract: The oil filter device is disposed on a side portion of one side of a cylinder body in a width direction in a cylinder head side with respect to an engine case in a space between center lines of main lubricating oil passages and a cylinder axis line of the cylinder body, and includes an oil pump disposed on the engine case and further lubricating oil passages that connect to the main lubricating oil passage.

Abstract: An exhaust valve for a muffler which is mounted inside the muffler includes: a mounting bracket having an arc shape; a shaft which is rotatably connected to the mounting bracket; a flap which is fixed to the shaft and rotates together with the shaft; and an elastic member which elastically support the flap with respect to the mounting bracket.

Abstract: A system in a vehicle including at least one sound quality valve arranged in an exhaust system of the vehicle includes a sound quality valve control module that determines whether one or more criteria for opening the sound quality valve are met, selectively actuates the sound quality valve to an open position if the one or more criteria for opening the sound quality valve are met, and maintains the sound quality valve in a closed position if a required one of the one or more criteria for opening the sound quality valve is not met. A downshift detection module determines whether aggressive driving behavior is detected. If the aggressive driving behavior is detected, the sound quality valve control module actuates the sound quality valve to the open position regardless of whether the required one of the one or more criteria for opening the sound quality valve is met.

Abstract: A method for reducing reductant deposits in an exhaust conduit fluidly coupled to an engine comprises operating the engine to produce an exhaust gas. The exhaust gas is communicated into the exhaust conduit which has an initial cross-sectional area. An initial flow rate corresponding to an initial flow velocity of the exhaust gas entering the exhaust conduit is determined. The initial flow rate and, thereby the initial flow velocity of the exhaust gas, increases or decreases based on an operating condition of the engine. The initial flow rate of the exhaust gas is compared with a predetermined threshold. If the initial flow rate of the exhaust gas is lower than the predetermined threshold, a cross-sectional area of the exhaust conduit is reduced. The reducing of the cross-sectional area causes the exhaust gas to have an adjusted flow velocity greater than the initial flow velocity.