Nozzle ring for a radial turbine, exhaust turbine, and turbocharger
AssigneeAccelleron Switzerland Ltd.
InventorsNico Geist, Florian Maurer, Davide Pinzi
Life of this patent
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Abstract
The invention relates to a nozzle ring for a radial turbine. The nozzle ring comprises a first ring element, a second ring element, and a plurality of guide vanes arranged between the first ring element and the second ring element. The second ring element comprises an end region, which extends inwards exclusively in the radial direction and has a convex curvature on a side facing the first ring element. The invention also relates to an exhaust turbine and to a turbocharger.
Claims18
A nozzle ring for a radial turbine, wherein the nozzle ring comprises a first annular element, a second annular element, and a plurality of guide vanes which are arranged between the first annular element and the second annular element, wherein an intermediate space between the first annular element and the second annular element provides a flow duct, wherein, when the nozzle ring is installed, the first annular element defines the flow duct on a bearing-housing side and the second annular element defines the flow duct on a turbine-housing side, wherein the second annular element comprises an axial extension that extends axially parallel to a central axis of rotation of the radial turbine and a prolongation, said prolongation separate and axially spaced apart from a gas inlet housing of the radial turbine, said gas inlet housing having an inner radius about a shaft having the central axis of rotation wherein said inner radius comprises a convex curvature in an axial direction, and said prolongation extending radially inward from the axial extension towards the central axis of rotation of the radial turbine, wherein the prolongation has a radially inner end region closest to the central axis of rotation that has a convex curvature on a side facing the first annular element, said convex curvature of the radially inner end region matching the convex curvature of the inner radius of the gas inlet housing.
An exhaust turbine, comprising:
- a turbine housing having a gas inlet housing,
- a radial gas inflow duct arranged in the gas inlet housing, and
- a nozzle ring arranged in the radial gas inflow duct, the nozzle ring comprising a first annular element, a second annular element, and a plurality of guide vanes which are arranged between the first annular element and the second annular element, wherein an intermediate space between the first annular element and the second annular element provides a flow duct, wherein the first annular element defines the flow duct on a bearing-housing side and the second annular element defines the flow duct on a turbine-housing side, wherein the second annular element comprises an axial extension that extends axially parallel to a central axis of rotation of the exhaust turbine and a prolongation, said prolongation separate and axially spaced apart from the gas inlet housing of the exhaust turbine, said gas inlet housing having an inner radius about a shaft having the central axis of rotation wherein said inner radius comprises a convex curvature in an axial direction, and said prolongation extending radially inward from the axial extension towards the central axis of rotation of the exhaust turbine, wherein the prolongation has a radially inner end region closest to the central axis of rotation that has a convex curvature on a side facing the first annular element, said convex curvature of the radially inner end region matching the convex curvature of the inner radius of the gas inlet housing.
A turbocharger comprising an exhaust turbine, the exhaust turbine comprising:
- a turbine housing having a gas inlet housing,
- a radial gas inflow duct arranged in the gas inlet housing, and
- a nozzle ring arranged in the radial gas inflow duct, the nozzle ring comprising a first annular element, a second annular element, and a plurality of guide vanes which are arranged between the first annular element and the second annular element, wherein an intermediate space between the first annular element and the second annular element provides a flow duct, wherein the first annular element defines the flow duct on a bearing-housing side and the second annular element defines the flow duct on a turbine-housing side, wherein the second annular element comprises an axial extension that extends axially parallel to a central axis of rotation of the exhaust turbine and a prolongation, said prolongation separate and axially spaced apart from the gas inlet housing of the exhaust turbine, said gas inlet housing having an inner radius about a shaft having the central axis of rotation wherein said inner radius comprises a convex curvature in an axial direction, and said prolongation extending radially inward from the axial extension towards the central axis of rotation of the exhaust turbine, wherein the prolongation has a radially inner end region closest to the central axis of rotation that has a convex curvature on a side facing the first annular element, said convex curvature of the radially inner end region matching the convex curvature of the inner radius of the gas inlet housing.
Dependencies are inferred from the claim text.