Turbocharger compressor having adjustable trim mechanism including vortex reducers

Patent metadata

Field	Value
Publication number	US-10544808-B2
Application number	US-201815907420-A
Country	US
Kind code	B2
Filing date	Feb 28, 2018
Priority date	Feb 28, 2018
Publication date	Jan 28, 2020
Grant date	Jan 28, 2020

Abstract

A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism operable to move between an open position and a closed position. The inlet-adjustment mechanism includes a plurality of blades disposed about the compressor air inlet and located within an annular space within the air inlet wall. The blades are pivotable about respective pivot points such that the blades extend radially inward from the annular space into the air inlet when the blades are in the closed position so as to form an orifice of reduced diameter relative to a nominal diameter of the inlet. Downstream surfaces of the blades include vortex reducers that are structured and arranged to reduce a strength of an unsteady vortex generated from the radially inner edges of the blades.

First claim

What is claimed is:

1. A turbocharger, comprising:
a turbine housing and a turbine wheel mounted in the turbine housing and connected to a rotatable shaft for rotation therewith, the turbine housing receiving exhaust gas and supplying the exhaust gas to the turbine wheel;
a centrifugal compressor assembly comprising a compressor housing and a compressor wheel mounted in the compressor housing and connected to the 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 compressor housing further defining a volute for receiving compressed air discharged generally radially outwardly from the compressor wheel, the air inlet wall defining an annular space surrounding the air inlet and open to the air inlet at a radially inner end of the annular space; and
a compressor inlet-adjustment mechanism disposed in the annular space of the air inlet wall and movable between an open position and a closed position, the inlet-adjustment mechanism comprising a plurality of blades disposed within the annular space, the blades collectively circumscribing an orifice, each blade having an upstream surface relatively farther from and facing away from the compressor wheel and a downstream surface relatively closer to and facing toward the compressor wheel, the blades pivoting about respective pivots radially inwardly from the annular space 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;
wherein the downstream surface of each of the blades includes a plurality of circumferentially spaced vortex reducers that are structured and arranged to reduce a strength of a vortex shed from the orifice of the inlet-adjustment mechanism.

2. The turbocharger of claim 1 , wherein the vortex reducers comprise cavities in the downstream surface of each blade.

3. The turbocharger of claim 2 , wherein the vortex reducers comprise a series of cavities in the downstream surface of each blade, the cavities being spaced apart along a length of the blade.

4. The turbocharger of claim 3 , wherein a separating wall is defined between each pair of adjacent cavities, the separating walls being oriented at a non-zero angle with respect to a radial direction of the compressor.

5. The turbocharger of claim 4 , wherein the cavities are generally triangular shaped, and the separating walls between the cavities alternate between positive and negative angles with respect to the radial direction.

6. The turbocharger of claim 4 , wherein the cavities are generally rectangular shaped, and the angles of the separating walls between the cavities all have the same sign.

7. The turbocharger of claim 1 , wherein the inlet-adjustment mechanism further comprises a unison ring, the unison ring being rotatable about a rotational axis of the turbocharger, wherein each of the blades is engaged with the unison ring such that rotation of the unison ring causes the blades to pivot.

8. The turbocharger of claim 7 , wherein each blade includes an end portion that engages an outer periphery of the unison ring.

Assignees

• Honeywell Int Inc
• Garrett Transportation I Inc

Inventors

• Mohtar Hani
• Pees Stephane
• Doise Stephane
• Lombard Alain

Classifications

• F05D2220/40

  in turbochargers · CPC title

• F02B37/00

  Engines characterised by provision of pumps driven at least for part of the time by exhaust · CPC title

• F02B37/225

  air passages · CPC title

• F04D29/464

  adjusting flow cross-section, otherwise than by using adjustable stator blades · CPC title

• F04D27/0246

  by varying geometry within the pumps, e.g. by adjusting vanes · CPC title