Adjustable-trim centrifugal compressor for a turbocharger

Patent metadata

Field	Value
Publication number	US-10465706-B2
Application number	US-201715446054-A
Country	US
Kind code	B2
Filing date	Mar 1, 2017
Priority date	Apr 19, 2016
Publication date	Nov 5, 2019
Grant date	Nov 5, 2019

Abstract

A centrifugal 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 in the air inlet. The inlet-adjustment mechanism includes a plurality of blades disposed about the air inlet and each pivotable about one end of the blade, the blades extending through a slot in the air inlet wall 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. Movement of the inlet-adjustment mechanism from the open position to the closed position is effective to shift the compressor's surge line to lower flow rates.

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 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; and
a compressor inlet-adjustment mechanism disposed in the air inlet of the compressor housing and pivotable radially inwardly and radially outwardly between an open position and a closed position, the inlet-adjustment mechanism comprising a plurality of blades disposed about the air inlet and each pivotable about one end of the blade, the blades pivoting radially inwardly through a slot in the air inlet wall 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, wherein the blades are coplanar and respective edge portions of adjacent blades have complementing shapes configured to allow said adjacent blades to partially overlap when the blades are pivoted radially inwardly from the closed position to a super-closed position in which the blades form an orifice of further-reduced diameter relative to that of the closed position.

2. The turbocharger of claim 1 , wherein each blade includes a radially inner edge having a circular-arc shape, the blades being configured so that said radially inner edges collectively form the orifice as substantially circular in a selected position of the inlet-adjustment mechanism.

3. The turbocharger of claim 2 , wherein said selected position in which said radially inner edges form the orifice as substantially circular is the closed position.

4. The turbocharger of claim 1 , wherein each blade includes a radially inner edge having a circular-arc shape, the blades being configured so that said radially inner edges collectively form the orifice as substantially circular in said super-closed position of the inlet-adjustment mechanism.

5. The turbocharger of claim 1 , wherein the number of said blades is three.

6. The turbocharger of claim 1 , wherein the inlet-adjustment mechanism comprises a cartridge including a pair of annular end plates that are axially spaced apart and wherein the blades are disposed between said end plates, the cartridge being disposed in an annular space defined by the compressor housing.

7. The turbocharger of claim 6 , wherein the end plates are spaced apart by a plurality of pins that pass through holes in the blades, and the blades pivot about said pins.

8. 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.

9. The turbocharger of claim 8 , wherein each blade includes an end portion that engages a slot defined in an inner periphery of the unison ring.

10. The turbocharger of claim 8 , wherein the inlet-adjustment mechanism further comprises a plurality of guides for guiding rotation of the unison ring.

11. The turbocharger of claim 10 , wherein the guides are arranged to limit the amount of radially outward pivoting of the blades to the open position.

Assignees

• Honeywell Int Inc
• Garrett Transportation I Inc

Inventors

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

Classifications

• F04D29/462 Primary

  especially adapted for elastic fluid pumps · CPC title

• F04D27/002

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

• F04D25/04

  the pump being fluid-driven {(pumps driven by exhaust gases F02B37/00, F02B39/00; turbochargers F02C6/12)} · CPC title

• F02B37/16

  by bypassing charging air · CPC title

• F04D29/4213

  suction ports · CPC title