Abstract: There is provided an assembly for a turbocharger, the assembly comprising a turbine housing and a nozzle ring, wherein one of the turbine housing and the nozzle ring comprises a tongue and the other of the turbine housing and the nozzle ring comprises a corresponding slot, the tongue and slot being configured to engage and prevent relative rotation of the turbine housing and the nozzle ring. Also provided is a method of manufacturing a turbine housing, assembly for use in a turbocharger, or a turbocharger.

Abstract: A turbine for a turbo-machine is proposed in which, at a gas inlet for a turbine wheel, vanes extend from a nozzle ring though slots in a shroud. The nozzle ring and shroud are relatively rotatable about a rotational axis of the turbine by at least 0.1 degrees. In use, the nozzle ring and shroud are relatively rotated to bring one side of the vane into close contact with one surface of the slot, to inhibit leakage of gas between the vane and the slot surface. For this purpose the respective surfaces of the nozzle and slot can be configured to closely conform to each other. If there is differential thermal expansion of the shroud and nozzle ring, the nozzle ring and shroud can relatively rotate, to withdraw the vane from the edge of the slot to relieve the pressure between them.

Abstract: An aerodynamic wrap for use with a tank trailer illustratively includes opposing first and second side assemblies. In an illustrative embodiment, each side assembly includes an upper panel pivotably supported by the tank trailer, and a lower panel pivotably supported by the upper panel. A lower connecting member illustratively couples the lower panels of the first and second side assemblies under the belly of the tank trailer.

Abstract: A valve system comprising a valve chamber at a junction of an inlet port, an outlet port and a bypass port, the inlet port configured for fluid communication with exhaust gas, the outlet port configured for fluid communication with an inlet of a turbine, and the bypass port configured for fluid communication with an exhaust aftertreatment device; a rotary valve comprising a valve rotor which rotates about a valve axis within the valve chamber between a first position to permit gas flow through the bypass port and a second position to block gas flow. At least one of the valve rotor and the valve chamber comprises a protrusion and the other comprises a recess, wherein, in the first position, the protrusion and recess are spaced from one another, and, in the second position the recess receives the protrusion such that gas flow between the protrusion and recess is substantially prevented.

Abstract: A rotary turbine bypass valve comprises a valve chamber positioned at a junction of an inlet port, an outlet port and a bypass port, the inlet port configured for fluid communication with a flow of exhaust gas from an engine, the outlet port configured for fluid communication with an inlet of a turbine, and the bypass port configured for fluid communication with an exhaust aftertreatment device; and a valve rotor supported for rotation, about a valve axis, within the valve chamber. The valve rotor is rotatable about the valve axis between a first position in which the valve rotor permits gas flow through the bypass port and a second position in which the valve rotor blocks gas flow through the bypass port.

Abstract: A turbine for a turbo-machine is proposed in which, at a gas inlet for a turbine wheel, vanes extend from a nozzle ring though slots in a shroud. The nozzle ring and shroud are relatively rotatable about a rotational axis of the turbine by at least 0.1 degrees. In use, the nozzle ring and shroud are relatively rotated to bring one side of the vane into close contact with one surface of the slot, to inhibit leakage of gas between the vane and the slot surface. For this purpose the respective surfaces of the nozzle and slot can be configured to closely conform to each other. If there is differential thermal expansion of the shroud and nozzle ring, the nozzle ring and shroud can relatively rotate, to withdraw the vane from the edge of the slot to relieve the pressure between them.

Abstract: A turbine for a turbo-machine is proposed in which, at a gas inlet for a turbine wheel, vanes extend from a nozzle ring though slots in a shroud. The nozzle ring and shroud are relatively rotatable about a rotational axis of the turbine by at least 0.1 degrees. In use, the nozzle ring and shroud are relatively rotated to bring one side of the vane into close contact with one surface of the slot, to inhibit leakage of gas between the vane and the slot surface. For this purpose the respective surfaces of the nozzle and slot can be configured to closely conform to each other. If there is differential thermal expansion of the shroud and nozzle ring, the nozzle ring and shroud can relatively rotate, to withdraw the vane from the edge of the slot to relieve the pressure between them.

Abstract: A valve system comprising a valve chamber at a junction of an inlet port, an outlet port and a bypass port, the inlet port configured for fluid communication with exhaust gas, the outlet port configured for fluid communication with an inlet of a turbine, and the bypass port configured for fluid communication with an exhaust aftertreatment device; a rotary valve comprising a valve rotor which rotates about a valve axis within the valve chamber between a first position to permit gas flow through the bypass port and a second position to block gas flow. At least one of the valve rotor and the valve chamber comprises a protrusion and the other comprises a recess, wherein, in the first position, the protrusion and recess are spaced from one another, and, in the second position the recess receives the protrusion such that gas flow between the protrusion and recess is substantially prevented.

Abstract: An aerodynamic wrap for use with a tank trailer illustratively includes opposing first and second side assemblies. In an illustrative embodiment, each side assembly includes an upper panel pivotably supported by the tank trailer, and a lower panel pivotably supported by the upper panel. A lower connecting member illustratively couples the lower panels of the first and second side assemblies under the belly of the tank trailer.

Abstract: There is provided a turbine comprising: a turbine housing; a turbine wheel; an inlet upstream of the turbine wheel, the inlet defining a first inlet portion and a second inlet portion; an outlet downstream of the turbine wheel, the outlet defining a first outlet portion and a second outlet portion; and a wastegate arrangement configured to selectively vent exhaust gas from the first inlet portion to the first outlet portion via a first bypass passage, and further configured to selectively vent exhaust gas from the second inlet portion to the second outlet portion via a second bypass passage; wherein the first outlet portion and the second outlet portion are separated by a baffle of the turbine housing.

Abstract: An aerodynamic curtain assembly for use with a tank trailer illustratively includes a front nose assembly, and opposing first and second side assemblies. The front nose assembly illustratively includes a front support coupled to the tank trailer, and a flexible air deflector screen coupled to the support and extending arcuately from a first upright supported by a first side of the tank trailer to a second upright supported by a second side of the tank trailer. Each of the side assemblies illustratively includes an upper support member, a lower support member, an upper coupler securing the upper end of a flexible air deflector screen to the upper support member, and a lower coupler securing the lower end of the flexible air deflector screen to the lower support member.

Abstract: A turbine for a turbo-machine is proposed in which, at a gas inlet for a turbine wheel, vanes extend from a nozzle ring though slots in a shroud. The nozzle ring and shroud are relatively rotatable about a rotational axis of the turbine by at least 0.1 degrees. In use, the nozzle ring and shroud are relatively rotated to bring one side of the vane into close contact with one surface of the slot, to inhibit leakage of gas between the vane and the slot surface. For this purpose the respective surfaces of the nozzle and slot can be configured to closely conform to each other. If there is differential thermal expansion of the shroud and nozzle ring, the nozzle ring and shroud can relatively rotate, to withdraw the vane from the edge of the slot to relieve the pressure between them.

Abstract: An aerodynamic wrap for use with a tank trailer illustratively includes opposing first and second side assemblies. In an illustrative embodiment, each side assembly includes an upper panel pivotably supported by the tank trailer, and a lower panel pivotably supported by the upper panel. A lower connecting member illustratively couples the lower panels of the first and second side assemblies under the belly of the tank trailer.

Abstract: An aerodynamic curtain assembly for use with a tank trailer illustratively includes a front nose assembly, and opposing first and second side assemblies. The front nose assembly illustratively includes a front support coupled to the tank trailer, and a flexible air deflector screen coupled to the support and extending arcuately from a first upright supported by a first side of the tank trailer to a second upright supported by a second side of the tank trailer. Each of the side assemblies illustratively includes an upper support member, a lower support member, an upper coupler securing the upper end of a flexible air deflector screen to the upper support member, and a lower coupler securing the lower end of the flexible air deflector screen to the lower support member.

Abstract: There is provided a turbine comprising: a turbine housing; a turbine wheel; an inlet upstream of the turbine wheel, the inlet defining a first inlet portion and a second inlet portion; an outlet downstream of the turbine wheel, the outlet defining a first outlet portion and a second outlet portion; and a wastegate arrangement configured to selectively vent exhaust gas from the first inlet portion to the first outlet portion via a first bypass passage, and further configured to selectively vent exhaust gas from the second inlet portion to the second outlet portion via a second bypass passage; wherein the first outlet portion and the second outlet portion are separated by a baffle of the turbine housing.

Abstract: A rotary turbine bypass valve comprises a valve chamber positioned at a junction of an inlet port, an outlet port and a bypass port, the inlet port configured for fluid communication with a flow of exhaust gas from an engine, the outlet port configured for fluid communication with an inlet of a turbine, and the bypass port configured for fluid communication with an exhaust aftertreatment device; and a valve rotor supported for rotation, about a valve axis, within the valve chamber. The valve rotor is rotatable about the valve axis between a first position in which the valve rotor permits gas flow through the bypass port and a second position in which the valve rotor blocks gas flow through the bypass port.

Abstract: An exhaust throttle valve configured for use with a turbocharger. The exhaust throttle valve comprising a housing defining a duct configured to receive exhaust gas discharged from an outlet of the turbocharger; a valve member disposed within the duct and being movable between an open configuration in which flow of exhaust gas through the duct is permitted and a closed configuration the flow of exhaust gas through the duct is prevented or restricted; and a bearing member received by a bore of the housing and configured to support the valve member for rotation about a valve axis. The bore is closed at one end so as to substantially prevent leakage of exhaust gas through the bore.

Abstract: A valve system comprising a valve chamber at a junction of an inlet port, an outlet port and a bypass port, the inlet port configured for fluid communication with exhaust gas, the outlet port configured for fluid communication with an inlet of a turbine, and the bypass port configured for fluid communication with an exhaust aftertreatment device; a rotary valve comprising a valve rotor which rotates about a valve axis within the valve chamber between a first position to permit gas flow through the bypass port and a second position to block gas flow. At least one of the valve rotor and the valve chamber comprises a protrusion and the other comprises a recess, wherein, in the first position, the protrusion and recess are spaced from one another, and, in the second position the recess receives the protrusion such that gas flow between the protrusion and recess is substantially prevented.