A turbocharger comprising: a compressor wheel mounted within a compressor housing; a turbine wheel mounted within a turbine housing; the turbine housing defining a meridionally divided scroll comprising first and second scrolls for respectively receiving separate streams of exhaust gas, each of the first and second scrolls extending about substantially a full circumference of the turbine housing, the second scroll succeeding the first scroll in an axial direction of the turbocharger; the turbine housing defining a nozzle for leading exhaust gas from the meridionally divided volute onto the turbine wheel; and a nozzle ring disposed in the nozzle, the nozzle ring comprising a first ring of first vanes circumferentially spaced about a circumference of the nozzle ring and a second ring of second vanes circumferentially spaced about the circumference of the nozzle ring, the first ring defining first vane passages between circumferentially successive first vanes, the second ring defining second vane passages between circumferentially successive second vanes, the nozzle ring further comprising a partition that fluidly isolates the first and second vane passages from each other, ends of the first vanes being joined to one side of the partition and ends of the second vanes being joined to an opposite side of the partition, and comprising a first end wall and a second end wall, wherein the first end wall is spaced from the one side of the partition and opposite ends of the first vanes from the partition are joined to the first end wall, and wherein the second end wall is spaced on the opposite side of the partition, and opposite ends of the second vanes from the partition are joined to the second end wall, wherein the first vane passages are positioned to receive exhaust gas from only the first scroll and wherein respective exits from the first vane passages direct a plurality of first exhaust gas jets on the turbine blade leading edges, wherein the second vane passages are positioned to receive exhaust gas from only the second scroll and wherein respective exits from the second vane passages direct a plurality of second exhaust gas jets on the turbine blade leading edges, wherein the first vane passages are circumferentially staggered relative to the second vane passages such that about a circumference of the turbine wheel, the first exhaust gas jets are interleaved with the second exhaust gas jets, and wherein the first vanes are configured such that each first exhaust gas jet impinges on a full extent of the turbine blade leading edges, and the second vanes are configured such that each second exhaust gas jet impinges on the full extent of the turbine blade leading edges. a compressor wheel mounted within a compressor housing; a turbine wheel mounted within a turbine housing; the turbine housing defining a meridionally divided scroll comprising first and second scrolls for respectively receiving separate streams of exhaust gas, each of the first and second scrolls extending about substantially a full circumference of the turbine housing, the second scroll succeeding the first scroll in an axial direction of the turbocharger; the turbine housing defining a nozzle for leading exhaust gas from the meridionally divided volute onto the turbine wheel; and a nozzle ring disposed in the nozzle, the nozzle ring comprising a first ring of first vanes circumferentially spaced about a circumference of the nozzle ring and a second ring of second vanes circumferentially spaced about the circumference of the nozzle ring, the first ring defining first vane passages between circumferentially successive first vanes, the second ring defining second vane passages between circumferentially successive second vanes, the nozzle ring further comprising a partition that fluidly isolates the first and second vane passages from each other, ends of the first vanes being joined to one side of the partition and ends of the second vanes being joined to an opposite side of the partition, and comprising a first end wall and a second end wall, wherein the first end wall is spaced from the one side of the partition and opposite ends of the first vanes from the partition are joined to the first end wall, and wherein the second end wall is spaced on the opposite side of the partition, and opposite ends of the second vanes from the partition are joined to the second end wall, wherein the first vane passages are positioned to receive exhaust gas from only the first scroll and wherein respective exits from the first vane passages direct a plurality of first exhaust gas jets on the turbine blade leading edges, wherein the second vane passages are positioned to receive exhaust gas from only the second scroll and wherein respective exits from the second vane passages direct a plurality of second exhaust gas jets on the turbine blade leading edges, wherein the first vane passages are circumferentially staggered relative to the second vane passages such that about a circumference of the turbine wheel, the first exhaust gas jets are interleaved with the second exhaust gas jets, and wherein the first vanes are configured such that each first exhaust gas jet impinges on a full extent of the turbine blade leading edges, and the second vanes are configured such that each second exhaust gas jet impinges on the full extent of the turbine blade leading edges.