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: Variable geometry turbines having new configurations of vanes are disclosed. New methods for designing new configurations of vanes for geometry turbines having are also disclosed.

Abstract: Variable geometry turbines having new configurations of vanes are disclosed. New methods for designing new configurations of vanes for geometry turbines having are also disclosed.

Abstract: A turbine comprises a turbine wheel for rotation within a turbine housing, the turbine housing including at least one volute arranged to deliver a fluid to the turbine wheel via the turbine nozzle. A method for determining a width of a turbine nozzle for the turbine, comprises selecting from a relationship between a turbine stage efficiency and an effective nozzle area, at least one target effective nozzle area. As used here, the effective nozzle area is dependent on both the width of the turbine nozzle and a whirl angle induced by the at least one volute. The method further comprises determining, in dependence on the whirl angle, the width of the turbine nozzle as a width that will achieve the at least one target effective nozzle area.

Abstract: A turbine for a turbo-machine is proposed in which, at a gas inlet, vanes, extending from a nozzle ring though slots in a shroud, are shaped on one side to as to substantially conform to the profile of the surface of the slot, whereby a close connection can be formed between the vane and the slot to inhibit leakage of gas between the vane and the slot surface.

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 turbine with multiple gas inlets is designed by a process of, for a given engine, obtaining time series data characterizing the power bias of the engine, obtaining an isentropic power associated with each data point of the time series, and using the isentropic powers to obtain a design point. The turbine is then designed based on the design point, such as by optimising one or more design parameters of the turbine based on the design point.

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 comprises a housing defining a turbine chamber with a turbine wheel supported for rotation about an axis. The housing further defines first and second inlet volutes which each spiral radially inwards and extend from a respective inlet to adjoin the turbine chamber and a volute tongue for each inlet volute. The tongue of the first volute radially separating a downstream portion of the first volute adjacent the chamber from an upstream portion of the first volute adjacent said inlet of the first volute, and the tongue of the second volute radially separating a downstream portion of the second volute adjacent the chamber from an upstream portion of the second volute adjacent said inlet of the second volute. The tongues having a turbine scroll tongue overlap which is substantially zero or positive; and the first volute tongue is angularly spaced about the axis from the second volute tongue.

Abstract: A turbine with multiple gas inlets is designed by a process of, for a given engine, obtaining time series data characterizing the power bias of the engine, obtaining an isentropic power associated with each data point of the time series, and using the isentropic powers to obtain a design point. The turbine is then designed based on the design point, such as by optimising one or more design parameters of the turbine based on the design point.

Abstract: A turbine comprises a housing defining a turbine chamber with a turbine wheel supported for rotation about an axis. The housing further defines first and second inlet volutes which each spiral radially inwards and extend from a respective inlet to adjoin the turbine chamber and a volute tongue for each inlet volute. The tongue of the first volute radially separating a downstream portion of the first volute adjacent the chamber from an upstream portion of the first volute adjacent said inlet of the first volute, and the tongue of the second volute radially separating a downstream portion of the second volute adjacent the chamber from an upstream portion of the second volute adjacent said inlet of the second volute. The tongues having a turbine scroll tongue overlap which is substantially zero or positive; and the first volute tongue is angularly spaced about the axis from the second volute tongue.

Abstract: A turbine comprises a turbine wheel for rotation within a turbine housing, the turbine housing including at least one volute arranged to deliver a fluid to the turbine wheel via the turbine nozzle. A method for determining a width of a turbine nozzle for the turbine, comprises selecting from a relationship between a turbine stage efficiency and an effective nozzle area, at least one target effective nozzle area. As used here, the effective nozzle area is dependent on both the width of the turbine nozzle and a whirl angle induced by the at least one volute. The method further comprises determining, in dependence on the whirl angle, the width of the turbine nozzle as a width that will achieve the at least one target effective nozzle area.

Abstract: A turbine for a turbo-machine is proposed in which, at a gas inlet, vanes, extending from a nozzle ring though slots in a shroud, are shaped on one side to as to substantially conform to the profile of the surface of the slot, whereby a close connection can be formed between the vane and the slot to inhibit leakage of gas between the vane and the slot surface.