Turbocharger compressor with inlet-adjustment mechanism having pivoting blades forming adjustable uninterrupted blade ring

Patent metadata

Field	Value
Publication number	US-11401948-B2
Application number	US-202017247511-A
Country	US
Kind code	B2
Filing date	Dec 15, 2020
Priority date	Dec 15, 2020
Publication date	Aug 2, 2022
Grant date	Aug 2, 2022

Abstract

A turbocharger includes a compressor equipped with an inlet-adjustment mechanism disposed in the air inlet of the compressor, the inlet-adjustment mechanism including a plurality of arcuate blades distributed about a circumference of a circle and partially overlapping one another so as to form an uninterrupted 360-degree blade ring. Each blade is pivotable about a respective fixed pivot point such that the ring is adjustable between a maximum-open position and a minimum-open position, the ring being adjustable via simultaneous coordinated pivoting of the blades about the respective fixed pivot points. The blades are structured and arranged to form said uninterrupted 360-degree blade ring in the maximum-open position and the minimum-open position and any intermediate position therebetween.

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 comprising impeller 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 contour disposed adjacent to radially outer tips of the impeller blades and defining a volute for receiving compressed air discharged generally radially outwardly from the compressor wheel, the compressor housing defining an annular space bounded between an upstream wall and a downstream wall spaced axially therefrom, the annular space surrounding the air inlet and being 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 compressor housing, the inlet-adjustment mechanism comprising a plurality of coplanar, arcuate blades distributed about a circumference of a circle and partially overlapping one another so as to form an uninterrupted 360 degree blade ring, wherein each blade includes a flow-guiding portion at one end of the blade, a lever arm at an opposite end of the blade, and a mounting portion disposed intermediate the lever arm and the flow-guiding portion, the mounting portions of the blades defining respective fixed pivot points for the blades about which the blades are pivotable such that the blade ring is adjustable between a maximum-open position in which an inner diameter of the blade ring has a maximum value and a minimum-open position in which the inner diameter of the blade ring has a minimum value, the blade ring being adjustable via simultaneous coordinated pivoting of the blades about the respective fixed pivot points, the flow-guiding portions of the blades collectively circumscribing and forming the inner diameter of the blade ring, the blades entirely residing within the annular space in the maximum-open position of the blade ring, the blades pivoting radially inwardly from the annular space into the air inlet when the blade ring is in any of the intermediate- and minimum-open positions such that an effective diameter of the air inlet is reduced to that delimited by the inner diameter of the blade ring, and wherein the blades are structured and arranged to form said uninterrupted 360 degree blade ring in the maximum-open position and the minimum-open position and any intermediate-open position therebetween.

2. The turbocharger of claim 1 , wherein the blades are at least 5 in number.

3. The turbocharger of claim 2 , further comprising:
a unison ring surrounding the blades, the unison ring being rotatable about a rotational axis that is substantially coaxial with a rotation axis of the turbocharger, the unison ring defining a plurality of circumferentially spaced notches defined in one of a radially inner periphery and a radially outer periphery of the unison ring, one said notch for each said blade,
each blade being supported by a pivot pin connected to the mounting portion and engaged in a bore in the compressor housing such that the blade pivots about an axis defined by the pivot pin, the mounting portions of the blades being disposed radially inward from the radially inner periphery of the unison ring, the lever arm of each blade including a hook portion at a radially outer end of the lever arm that is engaged in a respective one of the notches in the unison ring,
whereby rotation of the unison ring imparts pivotal movement to the blades via engagement of the hook portions of the lever arms in the notches in the unison ring.

4. The turbocharger of claim 3 , wherein the notches are defined in the radially outer periphery of the unison ring.

5. The turbocharger of claim 4 , the mounting portion of each blade including a support pad on which a downstream face of the unison ring is axially supported.

6. The turbocharger of claim 3 , wherein a proximal end of the flow-guiding portion of each blade defines an underlying ledge extending radially inwardly from the inner periphery of the unison ring and extending circumferentially toward a distal end of the flow-guiding portion of an adjacent one of the blades, and wherein the distal end of the flow-guiding portion of said adjacent one of the blades defines a stepped portion having an overlying ledge overlapping said underlying ledge, and wherein said underlying and overlying ledges are structured and arranged to at least partially overlap one another in all positions of the blade ring, thereby forming said uninterrupted 360-degree blade ring.

7. The turbocharger of claim 6 , wherein said overlying ledges are respectively disposed adjacent to axially upstream faces of said underlying ledges.

8. The turbocharger of claim 6 , each blade defining an arcuate duct portion integrally formed on the blade, the duct portions of the blades coming together end-to-end circumferentially about the annular space when the blade ring is adjusted to the minimum-open position so as to form a cylindrical duct adjacent the radially inner end of the annular space in the compressor housing and extending axially within the annular space.

9. The turbocharger of claim 6 , wherein a radially inner peripheral edge of each blade comprises a circular arc, the blades being structured and arranged such that the radially inner peripheral edges of the blades collectively form a substantially circular orifice in the minimum-open position of the blade ring.

10. The turbocharger of claim 6 , wherein the compressor housing comprises a main housing portion that defines the volute and the contour, and a separately formed cover portion that defines the air inlet, the cover portion being axially received into a receptacle defined by an upstream side of the main housing portion and being affixed to the main housing portion by fasteners, the upstream wall of the annular space being defined by the cover portion and the downstream wall of the annular space being defined by the main housing portion.

11. The turbocharger of claim 10 , wherein the cover portion defines contact pads that confront an upstream face of the blades of the inlet-adjustment mechanism and constrain axially upstream movement of the blades.

12. The turbocharger of claim 11 , wherein the compressor housing defines a diffuser leading from an exducer portion of the compressor wheel to the volute, and wherein the diffuser is a diverging diffuser.

13. The turbocharger of claim 12 , wherein the diffuser is defined between an upstream diffuser wall and a downstream diffuser wall, and the upstream diffuser wall is inclined with respect to a radial direction such that an axial width of the diffuser increases with increasing radius from the rotation axis of the turbocharger.

14. The turbocharger of claim 13 , wherein the upstream diffuser wall is conical.

Assignees

• Garrett Transportation I Inc

Inventors

• Lombard Alain
• Mohtar Hani
• Colombier Dominique
• Pees Stephane
• Blaise Renaud

Classifications

• F05D2220/40

  in turbochargers · CPC title

• F04D27/0246 Primary

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

• F04D29/464 Primary

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

• F04D17/10 Primary

  for compressing or evacuating · CPC title

• F02C6/12

  Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure · CPC title