A turbine assembly (500, 600) for a turbocharger comprising: a turbine wheel (540, 640) that comprises a base, a nose, a rotational axis extending from the base to the nose, an inducer portion and an exducer portion; a turbine housing (562, 662) that comprises a lower turbine housing surface that extends to a cylindrical surface (568, 668) that defines an upper portion of a turbine wheel space having an axis; a shroud component (552, 652) that comprises a lower shroud component surface, an upper shroud component surface, and a contoured surface (558, 658) that extends between the lower shroud component surface and the upper shroud component surface and that defines a lower portion of the turbine wheel space, wherein the turbine housing (562, 662) receives the shroud component (552, 652) and forms an axial gap (Δz(t)) between a lower axial position of the cylindrical surface (568, 668) and an upper axial position of the contoured surface (558, 658); and a seal that comprises a lower edge, a sloped annular portion that extends from the lower edge, a lower bend that extends from the sloped annular portion, a cylindrical portion that extends from the lower bend, and an upper bend that extends from the cylindrical portion to an upper edge, wherein the seal contacts the lower turbine housing surface of the turbine housing (562, 662) and contacts the upper shroud component surface of the shroud component (552, 652) to axially overlap at least a portion of the cylindrical portion of the seal and the axial gap (Δz(t)) and characterized in that the axial gap (Δz(t)) is axially positioned between an axial position of the inducer portion of the turbine wheel (540, 640) and an axial position of the exducer portion of the turbine wheel (540, 640) and wherein the turbine housing (562,662) defines in part a volute (570, 670) wherein, in absence of the seal, a line-of-sight of exists between the volute (570, 670) and the axial gap (Δz(t)). a turbine wheel (540, 640) that comprises a base, a nose, a rotational axis extending from the base to the nose, an inducer portion and an exducer portion; a turbine housing (562, 662) that comprises a lower turbine housing surface that extends to a cylindrical surface (568, 668) that defines an upper portion of a turbine wheel space having an axis; a shroud component (552, 652) that comprises a lower shroud component surface, an upper shroud component surface, and a contoured surface (558, 658) that extends between the lower shroud component surface and the upper shroud component surface and that defines a lower portion of the turbine wheel space, wherein the turbine housing (562, 662) receives the shroud component (552, 652) and forms an axial gap (Δz(t)) between a lower axial position of the cylindrical surface (568, 668) and an upper axial position of the contoured surface (558, 658); and a seal that comprises a lower edge, a sloped annular portion that extends from the lower edge, a lower bend that extends from the sloped annular portion, a cylindrical portion that extends from the lower bend, and an upper bend that extends from the cylindrical portion to an upper edge, wherein the seal contacts the lower turbine housing surface of the turbine housing (562, 662) and contacts the upper shroud component surface of the shroud component (552, 652) to axially overlap at least a portion of the cylindrical portion of the seal and the axial gap (Δz(t)) and characterized in that the axial gap (Δz(t)) is axially positioned between an axial position of the inducer portion of the turbine wheel (540, 640) and an axial position of the exducer portion of the turbine wheel (540, 640) and wherein the turbine housing (562,662) defines in part a volute (570, 670) wherein, in absence of the seal, a line-of-sight of exists between the volute (570, 670) and the axial gap (Δz(t)).