초록 ▼

A turbocharger is disclosed for use with an engine. The turbocharger may include a housing at least partially defining a compressor shroud and a turbine shroud. The turbine shroud may form a volute having an inlet configured to receive exhaust from an exhaust manifold of the engine in a tangential d

A turbocharger is disclosed for use with an engine. The turbocharger may include a housing at least partially defining a compressor shroud and a turbine shroud. The turbine shroud may form a volute having an inlet configured to receive exhaust from an exhaust manifold of the engine in a tangential direction. The volute may also include an axial channel disposed downstream of the inlet. The turbocharger may also include a turbine wheel disposed within the turbine shroud that may be configured to receive exhaust from the axial channel. The turbocharger may also include a compressor wheel disposed within the compressor shroud, and a shaft connecting the turbine wheel to the compressor wheel. The turbocharger may also include a nozzle ring disposed within the axial channel at a location upstream of the turbine wheel.

대표청구항 ▼

1. A turbocharger for an engine, comprising: a housing at least partially defining a compressor shroud and a turbine shroud, the turbine shroud forming a volute having:an inlet configured to receive exhaust from an exhaust manifold of the engine in a tangential direction; andan axial channel dispose

1. A turbocharger for an engine, comprising: a housing at least partially defining a compressor shroud and a turbine shroud, the turbine shroud forming a volute having:an inlet configured to receive exhaust from an exhaust manifold of the engine in a tangential direction; andan axial channel disposed downstream of the inlet;a turbine wheel disposed within the turbine shroud and configured to receive exhaust from the axial channel;a compressor wheel disposed within the compressor shroud;a shaft connecting the turbine wheel to the compressor wheel;a nozzle ring disposed within the axial channel at a location upstream of the turbine wheel;an inner annular surface; anda tongue disposed coaxially outward of the inner annular surface;wherein the axial channel is formed between the inner annular surface and the tongue; andwherein a geometry of the volute is based in part on a ratio of a length of the tongue to a height of the axial channel;wherein:the ratio of the length of the tongue to the height of the axial channel is about 0.8 to 1.6;the ratio is greatest at an inlet of the volute; andthe ratio converges to about zero as the interior surface winds tangentially inward. 2. The turbocharger of claim 1, wherein: the compressor shroud further includes an net located at a first axial end of the turbocharger;the turbine shroud further includes an outlet located at a second axial end of the turbocharger; andthe net of the volute is located between the first and second axial ends of the turbocharger. 3. The turbocharger of claim 2, wherein the compressor shroud further includes an outlet volute located between the net of the compressor shroud and the inlet of the volute. 4. The turbocharger of claim 1, wherein the nozzle ring further includes: an inner annular hub;an outer annular flange; anda plurality of vanes disposed between the inner annular hub and the outer annular flange. 5. The turbocharger of claim 4, wherein each of the plurality of vanes includes: a leading edge;a vane inlet angle defined by a tangent to a camber line of the vane at the leading edge and an axial direction of the turbocharger;a trailing edge;a vane outlet angle defined by a tangent to a camber line of the vane at the trailing edge and an axial direction of the turbocharger; anda vane turning angle defined by a difference between the vane inlet angle and the vane outlet angle, wherein the vane turning angle is equal to or lesser than 60 degrees. 6. The turbocharger of claim 4, wherein a ratio of an inner annular hub radius to an outer annular flange radius is about 0.55 to 0.77. 7. The turbocharger of claim 4, wherein a solidity ratio of the plurality of vanes is about 0.90 to 1.35 at vane midspan. 8. The turbocharger of claim 1, wherein the turbine wheel further includes: an annular hub; anda plurality of blades extending outward in from the annular hub. 9. The turbocharger of claim 8, wherein each of the plurality of blades includes: a leading edge;a blade inlet angle defined by a tangent to a camber line of the blade at the leading edge and an axial direction of the turbocharger;a trailing edge;a blade outlet angle defined by a tangent to a camber line of the vane at the trailing edge and an axial direction of the turbocharger; anda blade turning angle defined by a difference between the blade inlet angle and the blade outlet angle, wherein the blade turning angle is equal to or lesser than 135 degrees. 10. The turbocharger of claim 8, wherein a solidity ratio of the plurality of blades is about 1.1 to 1.5 at blade midspan. 11. The turbocharger of claim 8, wherein a ratio of an annular hub radius to a distance from a center of the turbine wheel to an outer end of the plurality of blades is about 0.55 to 0.77. 12. The turbocharger of claim 1, wherein a centroid of the volute is radially and axially off-center from a vane of the nozzle ring. 13. The turbocharger of claim 1, wherein: the inlet of the volute further includes an inlet flange; anda ratio between a cross-sectional area of the volute and a radius of the volute at the inlet flange is about 100-140 mm. 14. The turbocharger of claim 13, wherein: the ratio between the cross-sectional area of the volute and the radius of the volute at a 0 azimuth angle is about 110-150 mm;the ratio between the cross-sectional area of the volute and the radius of the volute at a 360 azimuth angle is about 10-40 mm; andthe 0 azimuth angle is located at a position corresponding to a plane that is parallel to a face of the inlet flange that also intersects a center of the volute disposed on a rotation axis of the volute. 15. A method of handling exhaust from an engine, the method comprising; receiving exhaust from an exhaust manifold of the engine at a volute inlet of a turbine in a tangential direction;directing exhaust from the volute inlet through an axial channel;directing exhaust from the axial channel through a nozzle ring; anddirecting exhaust from the nozzle ring through a turbine wheel to drive a compressor wheel connected to the turbine wheel by a shaft;wherein the volute is formed in part based on a ratio of a length of a tongue of the volute, disposed coaxially outward of an inner annular surface of the volute, to a height of an axial channel of the volute; andwherein:the ratio of the length of the tongue to the height of the axial channel is about 0.8 to 1.6;the ratio is greatest at an inlet of the volute; andthe ratio converges to about zero as the interior surface winds tangentially inward. 16. The method of claim 15, further including directing exhaust through an axial outlet disposed at a first axial end of the turbine, wherein the volute has a 45-75 degree tangential component through the axial channel upstream of the nozzle ring. 17. The method of claim 16, wherein exhaust is received at the volute inlet at a location between the first axial end of the turbine and an axial end of a compressor. 18. A power system, comprising: an engine;an exhaust manifold fluidly connected to the engine;a turbocharger fluidly connected to the exhaust manifold, the turbocharger including:a housing at least partially defining a compressor shroud and a turbine shroud, the turbine shroud forming a volute having:an inlet configured to receive exhaust from the exhaust manifold in a tangential direction; andan axial channel disposed downstream of the inlet;a turbine wheel disposed within the turbine shroud and configured to receive exhaust from the axial channel;a compressor wheel disposed within the compressor shroud;a shaft connecting the turbine wheel to the compressor wheel;a nozzle ring disposed within the axial channel at a location upstream of the turbine wheel;an inner annular surface; anda tongue disposed coaxially outward of the inner annular surface;wherein the axial channel is formed between the inner annular surface and the tongue;wherein a geometry of the volute is based in part on a ratio of a length of the tongue to a height of the axial channel; andwherein:the ratio of the length of the tongue to the height of the axial channel is about 0.8 to 1.6;the ratio is greatest at an inlet of the volute; andthe ratio converges to about zero as the interior surface winds tangentially inward.