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: A method for loading or reloading a decomposition unit of a vehicular system, the vehicular system including a filler pipe in communication with the decomposition unit. The method includes introducing at least one capsule including at least one protein component adapted to decompose ammonia precursor through the filler pipe and which is then guided through the filler pipe towards the decomposition unit.

Abstract: An exhaust gas treatment device, which includes an outer layer, an inner layer that is at least in part disposed within the outer layer, and an insulation material disposed in an enclosed space between the outer layer and the inner layer, where at least one reservoir disposed with the insulation material is connected to the enclosed space and in fluid communication therewith and a manufacturing method that includes placing an insulation material into an enclosed space between an inner layer and an outer layer for an exhaust gas treatment device and placing the insulation material into a reservoir connected to the enclosed space and in fluid communication therewith.

Abstract: Methods and systems are provided for addressing engine cold-start emissions while an exhaust catalyst is activated. In one example, a method for improving exhaust emissions may include flowing ionized air into an engine exhaust, downstream of an exhaust catalyst, to oxidize exhaust emissions left untreated by the catalyst. The approach reduces the PM load of the exhaust as well as of a downstream particulate matter filter.

Abstract: In an exhaust gas purification system provided with a denitration catalyst layer, a reducing agent oxidation catalyst layer is installed together; a reducing agent and air are supplied into the reducing agent oxidation catalyst layer at the time of catalyst regeneration of the denitration catalyst layer; a high-temperature oxidation reaction gas is produced by a reaction heat generated by an oxidation reaction of the reducing agent and the air in this reducing agent oxidation catalyst layer; and this high-temperature oxidation reaction gas is introduced into the denitration catalyst layer to heat the denitration catalyst, thereby recovering a denitration performance of the catalyst.

Abstract: The invention relates to a thermoelectric module (1), comprising at least one thermoelectric element (3) allowing the generation of an electric current from a temperature gradient applied between two of its active faces (4a, 4p), a first so-called hot circuit (2) able to allow the flow of a first fluid in a heat exchange relationship with one of said active faces and a sheath (8) surrounding said thermoelectric elements (3) and said hot circuit (2) such that the sheath (8) is arranged to establish thermal contact between a so-called cold liquid with a temperature lower than that of the first fluid, and the other of said active faces and to hermetically separate said cold liquid on the one hand and said thermoelectric element(s) (3) and said hot circuit (2) on the other hand. The invention also relates to a thermoelectric device comprising at least one module as described and a heat exchanger comprising such a device.

Abstract: A tractor according to an embodiment of the present invention includes a front wheel, a rear wheel, a hood that covers an engine, and an exhaust gas treatment unit. The exhaust gas treatment unit is placed laterally outside right or left side of the hood and behind the front wheel, and purifies exhaust gas from the engine. A circular cylindrical heat shielding plate covers an outer circumferential surface of the exhaust gas treatment unit. A plurality of vent holes are formed in a rear surface of the heat shielding plate, and are not formed in a region that lies on a front surface of the heat shielding plate and faces the front wheel.

Abstract: A cooling system for a vehicle has a first cooling circuit, in which a first pressure prevails, and a second cooling circuit, in which a second pressure prevails. The first cooling circuit and the second cooling circuit share a common equalizing container for ventilating. The cooling system has a passive element that separates the first cooling circuit from the second cooling circuit if the first pressure is lower than the second pressure.

Abstract: A machine engine enclosure arrangement that has sound reducing elements allows for the overall sound rating of the machine to be decreased. The engine enclosure includes a housing that has a housing length and a housing width. The housing defines a housing axis that extends along the housing length and the housing axis defines a vertical reference plane. The vertical reference plane is perpendicular to a ground surface on which machine is resting. The engine enclosure further includes a radiator fan that is configured to provide air flow across the radiator. The radiator fan has a diameter greater than the housing width and defines a fan plane perpendicular to an axis of rotation of the radiator fan. The radiator fan is positioned between the side walls of the housing so that the fan plane is at a non-perpendicular angle with respect to the vertical reference plane.

Abstract: A variable pump for an internal combustion engine incudes a drive wheel, a drive shaft configured to be driven via the drive wheel, a coupling pump impeller comprising pump blades, a coupling turbine wheel comprising turbine blades arranged axially opposite to the pump blades, and an impeller which is fixedly connected with the coupling turbine wheel. The coupling pump impeller is arranged to be rotationally fixed on the drive shaft. The coupling turbine wheel is configured to rotate on the drive shaft. The coupling pump impeller is arranged so as to be axially displaceable with respect to the coupling turbine wheel.

Abstract: The cooling apparatus includes two cooling water circulation system in which the temperatures of the cooling water are different. A low-temperature cooling water circulation system includes an LT radiator that is disposed partway along a circulation circuit and that performs heat exchange between low-temperature cooling water and external air, a temperature sensor that detects the external air temperature, and an adjustment apparatus that adjusts an amount of low-temperature cooling water that is introduced into the LT radiator. The control apparatus adjusts the adjustment apparatus so that the temperature of the low-temperature cooling water approaches a target water temperature, and when the external air temperature is higher than the target water temperature, corrects the target water temperature to a value that is greater than or equal to the external air temperature.

Abstract: In order to provide a method for indicating a risk of corrosion or scuffing of components of a combustion chamber of a turbo charged engine arrangement, in particular for vessels, the turbo charged engine arrangement includes a turbocharger and a charge gas cooler. A first gas stream of an ambient gas enters into the turbocharger, a second gas stream of charge gas flows from the turbocharger to the charge gas cooler, and the second gas stream of charge gas enters into the charge gas cooler. A third gas stream of charge gas flows from the charge gas cooler to the combustion chamber, and the third gas stream of the charge gas enters into the combustion chamber.

Abstract: An internal combustion engine, including a combustion chamber with a first aperture; a compression chamber with a second aperture; and a crossover valve comprising an internal chamber, first and second valve seats, a valve head, and first and second valve faces on the valve head, wherein the first aperture allows fluid communication between the combustion chamber and the internal chamber, the second aperture allows fluid communication between the compression chamber and the internal chamber, the first valve face couples to the first valve seat to occlude the first aperture, and the second valve face couples to the second valve seat to occlude the second aperture.

Abstract: Techniques for learning endstop position(s) of an actuator for a wastegate valve include detecting a learn condition and, in response to detecting the learn condition, performing a learn procedure for the actuator endstop position(s). The learn procedure includes commanding the actuator to a desired position past the endstop position corresponding to a fully-closed wastegate valve while rate-limiting a velocity of the actuator. When the difference reaches its maximum allowed value and the velocity falls below a fraction of its rate limit, the endstop position is learned. When the wastegate valve is requested open, the actuator is then controlled using the learned endstop position. Reference stiffness for a fully-closed wastegate valve could be obtained, and subsequent stiffness checks could then be periodically performed and, if less than the reference stiffness, a duty cycle of the actuator could be increased during open-loop control.

Abstract: An engine system configured to adjust an output torque generated by the engine system in response to anticipated changes in a condition of a load. The engine system includes a load predictor, an air supply system, a fuel supply system, and an electronic control unit. The electronic control unit is configured to adjust the quantity of air and/or exhaust provided to an inlet manifold of an engine and to thereafter adjust the quantity of fuel delivered to the engine for a predetermined period of time. The delivery of the quantity of fuel is delayed from the adjustment to the quantity of air and/or exhaust to provide a torque boost responsive to the anticipated changes in the condition of the load. Fuel costs are reduced and the engine operates more smoothly in response to load changes.

Abstract: The present disclosure describes a supercharging device for an internal combustion engine of a motor vehicle comprising: a planetary mechanism, a first electric machine, a second electric machine, a compressor impeller, and an internal combustion engine attachment for fastening to a drive output shaft of the internal combustion engine. The first electric machine, the second electric machine and the compressor impeller are connected to one another via the planetary mechanism. Along a longitudinal axis of the supercharging device, the compressor impeller is arranged on a first side of one of the electric machines, and the other of the electric machines is arranged on the second side situated opposite said first side.

Abstract: An external cooling fin of a rotary engine is mounted onto the housings of the rotary engine and includes a plurality of cooling teeth for lowering the temperature of the rotary engine, and each cooling fin includes a root and two or more outstretching fin stems, and the root is coupled to the rotary engine housings, so as to achieve a high-efficiency heat dissipation.

Abstract: Disclosed is an outboard motor including an exhaust manifold having a first passage that is provided with a plurality of first openings connected to a plurality of exhaust ports and extends vertically, and a second passage that is arranged under the first passage and has a second opening provided in a lower end portion and connected to a third passage formed in the engine holder. The first and second passages of the exhaust manifold are formed integrally, and the exhaust manifold is formed separately from the cylinder head and the cylinder block and is detachably installed.

Abstract: An engine can include at least one piston, a block, a fluid delivery system, and an output shaft. The block can define at least one cylinder. The piston can be received in the cylinder. The piston can be operable to reciprocally move rectilinearly while positioned in the cylinder. The fluid delivery system can be operable to communicate air and combustible fuel to the cylinder. The piston can be operable to compress the air and combustible fuel. The output shaft can be driven in motion by the piston and extend beyond the block to a distal end. The output shaft is limited to rectilinear movement.

Abstract: The present invention discloses an on-line cleaning control system and method for carbon deposits in a direct injection engine fuel system. The system comprises a cleaner tank, a cleaner input pipeline, an electromagnetic flow controller and a control circuit. A liquid transfer pump is in series connection with a pipeline of the cleaner input pipeline and the cleaner tank; when the conditions that fuel is injected through a fuel injector of the engine, the temperature of a three-way catalytic converter is lower than 800° C., the rotational speed of the engine is greater than 1200 rpm and the cleaning time is shorter than set cleaning time are met, the control circuit starts a cleaning working procedure to inject a cleaner into an intake manifold of the engine.

Abstract: A variable density coating system on a component (e.g., a CMC component) is provided. In one embodiment, the variable density coating system comprises: an external coating on the component, where the external coating has a first density area and a second density area with the first density area being more dense than the second density area. A gas turbine engine is also provided that includes a CMC component with the variable density coating system thereon.

Abstract: Circular propulsion jet compressor-engine, through a circular combustion chambers propellants spheroidal geometry set, generates a tangential push the turning radius and therefore resulting angular momentum about the shaft of the circle in rotation. This impulse is the consequence of the principle of action-reaction, the violent expansion that occurs inside the combustion chamber, when burning mixtures of fuel and oxidizer at high pressure, or by merging a small mass of H2, encapsulated and simultaneously subjected to very high pressure, constant electromagnetic fields and high-frequency electric fields and high peak intensity. The high pressure on the oxidant or H2, is achieved using the force resulting from the centripetal acceleration shaft rotating about a significant mass of a piston, solid or liquid and alternatively or cyclically. The gases and vapors produced are cooled inside the engine.

Abstract: An inlet for an aircraft nacelle may comprise a nanoreinforced polyimide composite lip skin. The nanomaterials may increase thermal conductivity and decrease microcracking in the lip skin. A lip skin for an inlet with an electric heater may comprise a surface layer, an outer composite skin, an electric heater, an inner composite skin, and a thermal barrier coating. A lip skin for an inlet with a pneumatic deicing system may comprise a surface layer, a composite skin, and a thermal barrier coating.

Abstract: The present application relates to a de-icing splitter lip for a low-pressure compressor of a turbofan aircraft engine. The splitter lip surrounds the primary flow and includes an annular splitter wall with a circular leading edge, an outer shroud connected to the splitter wall, and a heating device in an electric ribbon that de-ices the splitter lip. The splitter lip further includes an elastic element made of elastomer, holding the heating device on the inside of the splitter wall. The elastic element is compressed, pre-loaded, in the splitter lip. Thus, the elastic element exerts a force F clamping the heating device against the splitter wall and the outer shroud in order to improve thermal contact. The present application also provides a method for assembling a splitter lip.

Abstract: An oil tank and scavenge pipe assembly of a gas turbine engine comprises a tank, and a scavenge pipe having a discharge portion disposed inside the tank. The discharge portion comprises a first portion having first and second ends. The first end is adapted to connect to an oil return line for receiving a mixture of oil and air. A bend extends from the second end downstream thereof relative to a flow of the mixture of oil and air through the scavenge pipe. The bend is configured to cause stratification of the mixture of oil and air as the mixture of oil and air flows through it. An outlet downstream of the bend delivers the mixture of oil and air to the tank. A method of delivering an oil and air mixture to a rotating oil volume of a tank of a gas turbine engine is also presented.

Abstract: A gas turbine engine includes a first stage compressor, an intercooler in fluid communication with the first stage compressor, and a second stage compressor in fluid communication with the intercooler. The engine also includes a combustor in fluid communication with the second stage compressor and a turbine in fluid communication with the combustor. The intercooler cools an air inflow from the first stage compressor and the recuperator heats the airflow traveling from the second stage compressor to the turbine exhaust. The intercooler and recuperator are arranged radially outward of the combustor.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular body. The body extends laterally between an inner surface and an outer surface. The inner surface defines an igniter aperture in the combustor wall. The outer surface is vertically between the heat shield and the shell. The shell defines a first cooling aperture through which air is directed to impinge against the outer surface.

Abstract: A stationary gas turbine having at least one at least partially annular gas supply line, which is supported by a retainer, wherein the gas turbine has in the interior thereof a main flow direction of the working fluids, and wherein the retainer has at least one floor retainer supported against the floor and a face retainer attached to the housing of the gas turbine on the side opposite the floor retainer, and wherein both the floor retainer and the face retainer support the gas supply line against motion both in the main flow direction and perpendicularly thereto, wherein the face retainer has a spring system, which in particular compensates the change in the extent of the housing during operation of the gas turbine.

Abstract: A fuel nozzle apparatus for a gas turbine engine includes: an annular outer body extending parallel to a centerline axis and having an exterior surface, and having a ring of forward openings passing through the exterior surface, and a ring of aft openings passing through the exterior surface, the aft openings positioned axially aft of the forward openings; an annular main injection ring disposed inside the outer body and including: a forward main fuel gallery extending in a circumferential direction; an aft main fuel gallery extending in a circumferential direction; a ring of forward main fuel orifices communicating with the forward main fuel gallery and each aligned with one of the forward openings; a ring of aft main fuel orifices, communicating with the aft main fuel gallery and each aligned with one of the aft openings; and a pilot fuel injector disposed along the centerline axis.

Abstract: In at least one aspect of this disclosure, a shut off valve for an ecology fuel return system can include an inlet for receiving a fluid, an outlet for effusing the fluid, and a valve member configured to move between an open position such that the valve member allows fluid to effuse from the outlet and a closed position such that the valve member prevents fluid from effusing from the outlet. The valve member can include a pressure deflector configured to prevent fluid flow from biasing the valve member toward the closed position.

Abstract: An apparatus for discriminating ignition in a gas-turbine aeroengine is configured to discriminate that ignition occurred in a combustion chamber upon discriminating that a calculated high-pressure turbine rotational speed change rate at a detected high-pressure turbine rotational speed equal to or greater than a predetermined rotational speed threshold is equal to or greater than a predetermined rotational speed change rate threshold and that the change rate has been equal to or greater than the predetermined rotational speed change rate threshold continuously for a predetermined time period or longer, whereby whether or not ignition of an air-fuel mixture occurred in a combustion chamber can be accurately discriminated or determined without using a dedicated sensor or detector even when an EGT sensor or detector fails.

Abstract: A gas turbine engine including a composite case having a conductive path therein, and a conductive case connected to the composite case. The conductive case is made of a conductive material. A fastener connects the composite case to the conductive case. The fastener is conductively connected to the conductive material of the conductive case and not directly conductively connected to the conductive path. At least one voltage discharge channeling assembly is connected to the fastener and to the conductive case. The at least one voltage discharge channeling assembly has a portion conductively connected to the conductive path. The at least one voltage discharge channeling assembly is conductively connected to the fastener. A method of assembling an engine casing in a gas turbine engine is also provided.

Abstract: An accessory gearbox for a turbomachine, the gearbox being equipped with a pump and including intermeshing pinions, one of which is formed as a single piece with a coaxial shank for driving a rotary part of the pump, wherein said rotary part is directly mounted on the shank.

Abstract: Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective exhaust energy to match a nominal exhaust energy value, and subsequently measuring an actual emissions value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition.

Abstract: Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a nominal power output value, and subsequently measuring an actual exhaust energy value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual exhaust energy value and a nominal exhaust energy value at the ambient condition.

Abstract: Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective exhaust energy to match a nominal exhaust energy value, and subsequently measuring an actual power output value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual power output value and a nominal power output value at the ambient condition.

Abstract: Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective emissions value to match a nominal emissions value, and subsequently measuring an actual exhaust energy value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual exhaust energy value and a nominal exhaust energy value at the ambient condition.

Abstract: An apparatus for estimating operating parameter of a gas-turbine aeroengine is configured to calculate a rotational speed of the low-pressure turbine (N1) by retrieving preset first characteristics by at least a rotational speed of the high-pressure turbine (N2), an engine inlet temperature and a first amount of bled air, to calculate a compensating value (?N1) of the rotational speed of the low-pressure turbine by retrieving preset second characteristics by at least a second amount of bled air, and to calculate the rotational speed of the low-pressure turbine (N1) finally based on the calculated rotational speed of the low-pressure turbine (N1) and the compensating value (?N1) thereof.

Abstract: The present disclosure generally relates to a system with a gas turbine engine. The gas turbine engine includes a first combustor having a first fuel injector and a second combustor having a second fuel injector. The gas turbine engine further includes a first fuel conduit extending from a first orifice to a first fuel outlet of the first fuel injector. The first fuel conduit has a first acoustic volume between the first orifice and the first fuel outlet. The gas turbine engine further includes a second fuel conduit extending from a second orifice to a second fuel outlet of the second fuel injector. The second fuel conduit has a second acoustic volume between the second orifice and the second fuel outlet, and the first acoustic volume and the second acoustic volume are different from one another.

Abstract: A fuel control system according to an exemplary aspect of the present disclosure includes, among other things, a fuel delivery valve selectively moveable to a closed position to shut off a flow of fuel to a downstream location. The system further includes a windmill bypass valve, and a shutoff pressure line between the windmill bypass valve and the fuel delivery valve. The windmill bypass valve is selectively operable to direct fuel to the shutoff pressure line to assist the movement of the fuel delivery valve to the closed position. A method is also disclosed.

Abstract: Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective fuel flow to match a nominal fuel flow value, and subsequently measuring an actual emissions value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition.

Abstract: Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective exhaust energy to match a nominal exhaust energy value, and subsequently measuring an actual fuel flow value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual fuel flow value and a nominal fuel flow value at the ambient condition.

Abstract: Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective power output to match a nominal power output value, and subsequently measuring an actual emissions value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual emissions value and a nominal emissions value at the ambient condition.

Abstract: Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective fuel flow to match a nominal fuel flow value, and subsequently measuring an actual power output value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual power output value and a nominal power output value at the ambient condition.

Abstract: Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective emissions value to match a nominal emissions value, and subsequently measuring an actual fuel flow value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual fuel flow value and a nominal fuel flow value at the ambient condition.

Abstract: Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective fuel flow value to match a nominal fuel flow value, and subsequently measuring an actual exhaust energy value for each GT; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual exhaust energy value and a nominal exhaust energy value at the ambient condition.

Abstract: A control apparatus for a gas-turbine aeroengine having discriminator that discriminates normality of a low-pressure turbine rotational speed sensor adapted to detect the low-pressure turbine rotational speed and a high-pressure turbine rotational speed controller that establish a first value as an upper limit value of a high-pressure turbine rotational speed and controls the high-pressure turbine rotational speed based on the established upper limit value, and is configured to change the upper limit value to a second value lower than the first value when the low-pressure turbine rotational speed sensor is discriminated not to be normal, whereby engine output (thrust) determined by the low-pressure turbine rotational speed can be controlled to a desired value while restraining the high-pressure turbine rotational speed to not greater than the first value, and low-pressure turbine overspeed at the time of a mishap such as engine fan blade breakage can be reliably prevented.

Abstract: An apparatus for controlling a gas-turbine aeroengine is configured to calculate a fuel command to supply fuel based on a calculated desired rotational speed of a low-pressure turbine calculated from an operation angle of a thrust lever installed at an aircraft cockpit pilot's seat, determines whether it is a time point for outputting a command to open/close a bleed-off valve equipped at a high-pressure compressor connected to a high-pressure turbine and to supply the fuel command based on the time point when it is determined to be the time point for outputting the command to open/close the bleed-off valve.

Abstract: A control valve (10) for an exhaust system of a motor vehicle, especially a motorbike, comprising a valve housing (11) in which a shut-off body (12) is movably arranged for changing the cross-section of a flow channel (21) of the exhaust system, wherein expansion play in the radial and axial direction is provided between the shut-off body (12) and the valve housing (11), which allows thermal expansion of the shut-off body (12) within the valve housing (11), wherein the shut-off body (12) comprises a perforated ball (12a).

Abstract: In at least some implementations, a charge forming device includes a main body, a throttle valve and an adjuster. The main body includes a main bore through which fluid flows for delivery to an engine. The throttle valve is carried by the main body and moveable relative to the main bore to control fluid flow through the main bore. And the adjuster is moveable relative to the throttle valve and engageable with the throttle valve to adjust the range of motion of the throttle valve. In at least some implementations, the adjuster limits the range of motion of the throttle valve when the adjuster is engaged with the throttle valve.