Passive and semi-passive inlet-adjustment mechanisms for compressor, and turbocharger having same

Patent metadata

Field	Value
Publication number	US-9822698-B2
Application number	US-201514615428-A
Country	US
Kind code	B2
Filing date	Feb 6, 2015
Priority date	Feb 6, 2015
Publication date	Nov 21, 2017
Grant date	Nov 21, 2017

Abstract

A centrifugal compressor for a turbocharger includes a passive or semi-passive inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position solely by aerodynamic forces on the mechanism. The inlet-adjustment mechanism includes a plurality of flexible vanes collectively forming a duct, and an effective diameter of the air inlet at the inducer portion of the compressor wheel is determined by a trailing edge inside diameter of the duct. The vanes are movable solely or in part by aerodynamic forces exerted on the vanes by the air flowing to the compressor wheel. The duct has a tapering configuration when the vanes are in a relaxed state, but under aerodynamic force the vanes flex outwardly and increase the trailing edge inside diameter of the duct, thereby increasing an effective diameter of the air inlet.

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 defining an air inlet for leading air generally axially into the inducer portion of 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 having an inner surface that extends for an axial length along a downstream direction, followed by an inlet-adjustment mechanism disposed in the air inlet, followed by a shroud surface that is adjacent to outer tips of the blades of the compressor wheel;
the inlet-adjustment mechanism comprising a plurality of vanes constructed of a flexible material, the vanes having leading edges joined to a ring mounted in the air inlet and the vanes being distributed circumferentially about the ring such that the ring and the vanes collectively form a duct, wherein an effective diameter of the air inlet at the inducer portion is determined by a trailing edge inside diameter of the duct, the vanes being movable in a radially outward direction by aerodynamic forces exerted on the vanes by the air flowing to the compressor wheel, the duct having a tapering configuration when the vanes are in a relaxed state such that the trailing edge inside diameter of the duct is smaller than that of the shroud surface, said aerodynamic forces exerted radially outwardly on the vanes causing the vanes to flex generally radially outwardly and increase the trailing edge inside diameter of the duct at the inducer portion, thereby increasing the effective diameter of the air inlet;
a metal biasing member encircling the duct adjacent the trailing edge thereof, the biasing member exerting a generally radially inward biasing force on the vanes; and
an electromagnet disposed radially outward of the metal biasing member, the electromagnet, when energized, exerting a radially outward magnetic attraction force on the metal biasing member for urging the vanes radially outwardly.

2. The turbocharger of claim 1 , wherein the ring is formed separately from the compressor housing and is affixed within the air inlet of the compressor housing.

3. The turbocharger of claim 2 , wherein the ring is formed of a different material from the flexible material of the vanes.

4. The turbocharger of claim 3 , wherein the ring is formed of metal.

5. The turbocharger of claim 2 , wherein the ring is formed of the same flexible material as the vanes.

6. The turbocharger of claim 1 , wherein in the relaxed state of the vanes there are gaps in a circumferential direction between side edges of adjacent vanes.

7. The turbocharger of claim 1 , wherein in the relaxed state the vanes partially overlap in a circumferential direction.

Assignees

• Honeywell Int Inc

Inventors

• Mohtar Hani
• Pees Stephane
• Delapierre Pascal
• Smith William Joseph
• Villemin Pascal

Classifications

• F05D2250/51

  Inlet · CPC title

• F04D29/4213 Primary

  suction ports · CPC title

• F05D2270/101

  Compressor surge or stall · CPC title

• F05D2220/40

  in turbochargers · CPC title

• F04D17/10

  for compressing or evacuating · CPC title