초록 ▼

The flow path of exhaust gas to the turbine wheel (70) of a turbocharger is influenced by relative motion between two rings of vanes, at least one of which being provided on a vane ring. The outer ring of vanes contains a plurality of vanes (92, 122), the inner ring of vanes contains a plurality of

The flow path of exhaust gas to the turbine wheel (70) of a turbocharger is influenced by relative motion between two rings of vanes, at least one of which being provided on a vane ring. The outer ring of vanes contains a plurality of vanes (92, 122), the inner ring of vanes contains a plurality of vanes (93, 121), and the inner and outer vanes in registry forming a single generic vane shape. The aerodynamic effect of relative displacement of the outer ring of vanes to the inner ring of vanes produces a modulate-able control of exhaust flow to the turbine wheel.

대표청구항 ▼

1. A turbocharger, comprising: a turbine wheel (70) rotatable about a central axis;a housing (2) configured to enclose said turbine wheel and having a volute,an inner ring of vanes (93) and an outer ring of vanes (92) provided between said volute and said turbine wheel,wherein at least one of said i

1. A turbocharger, comprising: a turbine wheel (70) rotatable about a central axis;a housing (2) configured to enclose said turbine wheel and having a volute,an inner ring of vanes (93) and an outer ring of vanes (92) provided between said volute and said turbine wheel,wherein at least one of said inner ring of vanes and said outer ring of vanes is provided on a rotatable vane ring (90, 91), andone of said inner and outer vanes are pivotably mounted, and wherein said inner and outer vanes are connected such that rotation of one vane ring relative to the other vane ring results in pivoting of said pivotably mounted vanes. 2. The turbocharger as in claim 1, wherein one of said outer vanes (92) and one of said inner vanes (93) when in registry form a general airfoil shape, with the outer vane forming the leading edge of said general airfoil shape, and said inner vane forming the trailing edge of said general airfoil shape. 3. The turbocharger as in claim 2, wherein said inner ring of vanes and outer ring of vanes are segregated along a circular boundary line. 4. The turbocharger as in claim 3, wherein said circular boundary line defines an arc through each of said general airfoil shapes separating each of said outer and inner vanes. 5. The turbocharger as in claim 1, wherein said inner ring of vanes and outer ring of vanes are segregated along a circular boundary line, and the area between outer vanes defines nozzles through which exhaust gas flows, and wherein a ratio of nozzle space at said circular boundary line to an area blocked by said outer vane at said circular boundary line is from 3:1 to 1:1. 6. The turbocharger as in claim 5, wherein said ratio is from 2:1 to 1:1. 7. The turbocharger as in claim 5, wherein said ratio is from 1.5:1 to 1:1. 8. The turbocharger as in claim 1, wherein said outer ring of vanes (92) is provided on said rotatable vane ring (90). 9. The turbocharger as in claim 1, wherein said inner ring of vanes (93) is provided on said rotatable vane ring (91). 10. The turbocharger as in claim 1, wherein said outer and inner ring of vanes (92, 93) are provided on rotatable vane rings (90, 91). 11. A turbocharger, comprising: a turbine wheel (70) rotatable about a central axis;a housing (2) configured to enclose said turbine wheel and having a volute,an inner ring of vanes (93) and an outer ring of vanes (92) provided between said volute and said turbine wheel,wherein at least one of said inner ring of vanes and said outer ring of vanes is provided on a rotatable vane ring (90, 91), andsaid inner ring of vanes and outer ring of vanes are segregated along a circular boundary line, said outer vanes include a projection extending across said circular boundary line, whereby relative movement between inner and outer vanes causes said inner vane and said projection to form a nozzle with varying flow through area.