Axial turbine wheel with curved leading edge
View Patent ↗A turbocharger including a turbine wheel having a hub-to-tip ratio of no more than 60% and blades with a high turning angle and a curved leading edge, a turbine housing forming an inwardly spiraling primary-scroll passageway that significantly converges to produce highly accelerated airflow into the turbine at high circumferential angles, and a two-sided parallel compressor. The compressor and turbine each produce substantially no axial force, allowing the use of minimal axial thrust bearings.
1. A turbocharger configured to receive an exhaust gas stream from an engine configured to operate over a range of standard operating conditions, and to compress input air into a pressurized air stream, comprising:
a turbocharger housing including a turbine housing; and
a rotor configured to rotate within the turbocharger housing along an axis of rotation, the rotor including an axial turbine wheel, a compressor wheel, and a shaft extending along the axis of rotation and connecting the turbine wheel to the compressor wheel;
wherein the turbine wheel is configured with a hub, and with a plurality of axial turbine blades configured to drive the rotor in rotation around the axis of rotation when the turbocharger receives the exhaust gas stream from the engine, each blade having an axial leading edge, an axial trailing edge, a hub end, and a tip end opposite the hub end;
wherein the axial leading edge of each blade is characterized by a leading edge curvature near the hub end, the leading edge curvature including a downstream curvature component;
wherein the turbine housing forms an inwardly spiraling turbine primary-scroll passageway that turns in an axial direction, the primary-scroll passageway being configured to provide the exhaust gas stream to the blade axial leading edges at an inlet angle distribution during a design condition of the standard operating conditions;
wherein the axial leading edge of each blade is characterized by a distribution of leading edge blade angles that match the inlet angle distribution across the leading edge of the blade;
wherein the axial leading edge of each blade is characterized by a leading-edge direction angle, and wherein the leading-edge direction angle varies by at least 20 degrees over the span of each blade; and
wherein the axially leading edge forms a straight line from a leading edge hub end to a 50% span.
2. A turbocharger configured to receive an exhaust gas stream from an engine configured to operate over a range of standard operating conditions, and to compress input air into a pressurized air stream, comprising:
a turbocharger housing including a turbine housing; and
a rotor configured to rotate within the turbocharger housing along an axis of rotation, the rotor including an axial turbine wheel, a compressor wheel, and a shaft extending along the axis of rotation and connecting the turbine wheel to the compressor wheel;
wherein the turbine wheel is configured with a hub, and with a plurality of axial turbine blades configured to drive the rotor in rotation around the axis of rotation when the turbocharger receives the exhaust gas stream from the engine, each blade having an axial leading edge, an axial trailing edge, a hub end, and a tip end opposite the hub end;
wherein the axial leading edge of each blade is characterized by a leading edge curvature near the hub end, the leading edge curvature including a downstream curvature component;
wherein the leading edge curvature includes a circumferential curvature component;
wherein the turbine housing forms an inwardly spiraling turbine primary-scroll passageway that turns in an axial direction, the primary-scroll passageway being configured to provide the exhaust gas stream to the blade axial leading edges at an inlet angle distribution during a design condition of the standard operating conditions;
wherein the axial leading edge of each blade is characterized by a distribution of leading edge blade angles that match the inlet angle distribution across the leading edge of the blade;
wherein the axial leading edge of each blade is characterized by a leading-edge direction angle, and wherein the leading-edge direction angle varies by at least 20 degrees over the span of each blade; and
wherein the axially leading edge forms a straight line from a leading edge hub end to a 50% span.
3. A turbocharger configured to receive an exhaust gas stream from an engine configured to operate over a range of standard operating conditions, and to compress input air into a pressurized air stream, comprising:
a turbocharger housing including a turbine housing; and
a rotor configured to rotate within the turbocharger housing along an axis of rotation, the rotor including an axial turbine wheel, a compressor wheel, and a shaft extending along the axis of rotation and connecting the turbine wheel to the compressor wheel;
wherein the turbine wheel is configured with a hub, and with a plurality of axial turbine blades configured to drive the rotor in rotation around the axis of rotation when the turbocharger receives the exhaust gas stream from the engine, each blade having an axial leading edge, an axial trailing edge, a hub end, and a tip end opposite the hub end;
wherein the axial leading edge of each blade is characterized by a leading edge curvature near the hub end, the leading edge curvature including a downstream curvature component;
wherein each blade's leading edge curvature is configured to provide adequate clearance between the blade and adjacent blades such that casting molds configured to cast the blades can be pulled from between the blades without deforming the casting molds;
wherein the turbine housing forms an inwardly spiraling turbine primary-scroll passageway that turns in an axial direction, the primary-scroll passageway being configured to provide the exhaust gas stream to the blade axial leading edges at an inlet angle distribution during a design condition of the standard operating conditions;
wherein the axial leading edge of each blade is characterized by a distribution of leading edge blade angles that match the inlet angle distribution across the leading edge of the blade;
wherein the axial leading edge of each blade is characterized by a leading-edge direction angle, and wherein the leading-edge direction angle varies by at least 20 degrees over the span of each blade; and
wherein the axially leading edge forms a straight line from a leading edge hub end to a 50% span.
4. A turbocharger configured to receive an exhaust gas stream from an engine configured to operate over a range of standard operating conditions, and to compress input air into a pressurized air stream, comprising:
a turbocharger housing including a turbine housing; and
a rotor configured to rotate within the turbocharger housing along an axis of rotation, the rotor including an axial turbine wheel, a compressor wheel, and a shaft extending along the axis of rotation and connecting the turbine wheel to the compressor wheel;
wherein the turbine wheel is configured with a hub, and with a plurality of axial turbine blades configured to drive the rotor in rotation around the axis of rotation when the turbocharger receives the exhaust gas stream from the engine, each blade having an axial leading edge, an axial trailing edge, a hub end, and a tip end opposite the hub end;
wherein the axial leading edge of each blade is characterized by a leading edge curvature near the hub end, the leading edge curvature including a downstream curvature component;
wherein the leading edge curvature includes a circumferential curvature component;
wherein each blade's leading edge curvature is configured to provide adequate clearance between the blade and adjacent blades such that casting molds configured to cast the blades can be pulled from between the blades without deforming the casting molds;
wherein the turbine housing forms an inwardly spiraling turbine primary-scroll passageway that turns in an axial direction, the primary-scroll passageway being configured to provide the exhaust gas stream to the blade axial leading edges at an inlet angle distribution during a design condition of the standard operating conditions;
wherein the axial leading edge of each blade is characterized by a distribution of leading edge blade angles that match the inlet angle distribution across the leading edge of the blade;
wherein the axial leading edge of each blade is characterized by a leading-edge direction angle, and wherein the leading-edge direction angle varies by at least 20 degrees over the span of each blade; and
wherein the axially leading edge forms a straight line from a leading edge hub end to a 50% span.