Turbocharger compressor with adjustable-trim mechanism and noise-attenuator
A compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position. The inlet-adjustment mechanism includes a plurality of blades disposed about the air inlet, the blades being movable radially inwardly from an annular space of the air inlet wall, into the air inlet, so as to form an orifice of reduced diameter relative to a nominal diameter of the inlet. A noise-attenuator is disposed in the annular space, downstream of the inlet-adjustment mechanism, for attenuating aerodynamic noise induced by the inlet-adjustment mechanism when it is closed.
1. A turbocharger, comprising:
a turbine including a turbine housing;
a compressor assembly comprising a compressor housing and a compressor wheel mounted in the compressor housing and connected to a rotatable shaft for rotation therewith, the compressor wheel having blades and defining an inducer portion, the compressor housing having an air inlet wall defining an air inlet for leading air generally axially into the compressor wheel, the air inlet wall defining an annular space therein upstream of the compressor wheel, a radially innermost extremity of the annular space being open to the air inlet;
an inlet-adjustment mechanism disposed in the air inlet and adjustable between an open position and a closed position, the inlet-adjustment mechanism comprising a plurality of blades disposed about the air inlet and collectively circumscribing an orifice, the blades being movable radially inwardly into the air inlet when the blades are in the closed position so as to cause the orifice to have a reduced diameter relative to a nominal diameter of the inlet; and
a noise-attenuator disposed in the annular space downstream of the inlet-adjustment mechanism, the noise-attenuator being structured and arranged to define axially consecutive first and second annular cavities each of which is open to the air inlet, the first annular cavity having a radial height h 1 and the second annular cavity having a radial height h 2 .
2. The turbocharger of claim 1 , wherein h 1 and h 2 are not equal.
3. The turbocharger of claim 1 , wherein each of the first and second annular cavities has an axial width that is greater than an axial thickness of the second plate.
4. The turbocharger of claim 1 , wherein h 1 and h 2 are equal.
5. The turbocharger of claim 1 , wherein the noise-attenuator comprises a ring-shaped first plate and a ring-shaped second plate axially abutting the first plate.
6. The turbocharger of claim 5 , wherein the first plate defines a flange at a radially outer periphery thereof, the flange projecting axially upstream from an upstream face of the first plate.
7. The turbocharger of claim 6 , wherein the inlet-adjustment mechanism includes a rotatable unison ring for actuating movement of the blades, the unison ring abutting the flange, the flange forming a bearing surface for the unison ring when the unison ring is rotated.
8. The turbocharger of claim 7 , wherein the blades are pivotally mounted to the first plate, the blades engaging the unison ring such that rotation of the unison ring in one direction or an opposite direction causes the blades to pivot radially inwardly or radially outwardly for adjusting a size of the orifice.
9. A turbocharger, comprising:
a turbine including a turbine housing;
a compressor assembly comprising a compressor housing and a compressor wheel mounted in the compressor housing and connected to a rotatable shaft for rotation therewith, the compressor wheel having blades and defining an inducer portion, the compressor housing having an air inlet wall defining an air inlet for leading air generally axially into the compressor wheel, the air inlet wall defining an annular space therein upstream of the compressor wheel, a radially innermost extremity of the annular space being open to the air inlet;
an inlet-adjustment mechanism disposed in the air inlet and adjustable between an open position and a closed position, the inlet-adjustment mechanism comprising a plurality of blades disposed about the air inlet and collectively circumscribing an orifice, the blades being movable radially inwardly into the air inlet when the blades are in the closed position so as to cause the orifice to have a reduced diameter relative to a nominal diameter of the inlet; and
a noise-attenuator disposed in the annular space of the air inlet wall, downstream of the inlet-adjustment mechanism, the noise-attenuator cooperating with the annular space to define an annular cavity, and the noise-attenuator comprising a plurality of elongate fingers that bridge across from an upstream side to a downstream side of the annular cavity, adjacent a radially inner end thereof, the fingers being non-uniformly circumferentially spaced about an entire circumference of the air inlet.
10. The turbocharger of claim 9 , wherein the noise-attenuator comprises a ring-shaped plate, the fingers projecting axially downstream from a downstream face of the plate adjacent a radially inner periphery thereof.
11. The turbocharger of claim 10 , wherein the plate defines a flange at a radially outer periphery thereof, the flange projecting axially upstream from an upstream face of the plate.
12. The turbocharger of claim 11 , wherein the inlet-adjustment mechanism includes a rotatable unison ring for actuating movement of the blades, the unison ring abutting the flange, the flange forming a bearing surface for the unison ring when the unison ring is rotated.
13. The turbocharger of claim 12 , wherein the blades are pivotally mounted to the plate, the blades engaging the unison ring such that rotation of the unison ring in one direction or an opposite direction causes the blades to pivot radially inwardly or radially outwardly for adjusting a size of the orifice.