Two-sided turbocharger wheel with differing blade parameters

• US 10,233,756 B2
• Filed: 08/27/2013
• Issued: 03/19/2019
• Est. Priority Date: 08/27/2013
• Status: Active Grant

• Current Assignee: Garrett Transportation I Inc. (Garrett Motion, Inc.)
• Original Assignee: Garrett Transportation I Inc. (Garrett Motion, Inc.)
• Inventors: Chen, Hua, Li, Annie, Zhao, Michael, Dai, Wei, Lazaro Bercianos, Jose Luis, Houst, Vit, Turecek, Daniel, Kares, Vaclav, Nejedly, Milan, Mokos, Michal
• Primary Examiner(s): Laurenzi, Mark
• Assistant Examiner(s): Thiede, Paul
• Application Number:
  US14/011,691
• Publication Number:
  US 20150064002A1
• Time in Patent Office: 2,030 Days
• Field of Search: 415 1, 415 98
• CPC Class Codes: F01D 5/02 Blade-carrying members, e.g. rotors rotors of non-bladed type F01D1/34; stators F01D9/00 ; selecting particular materials F01D5/28
• CPC Class Codes: F04D 17/105 with double suction
• CPC Class Codes: F04D 25/04 the pump being fluid-driven pumps driven by exhaust gases F02B37/00, F02B39/00; turbochargers F02C6/12
• CPC Class Codes: F04D 29/284 for compressors
• CPC Class Codes: F04D 29/285 the compressor wheel comprising a pair of rotatable bladed hub portions axially aligned and clamped together
• CPC Class Codes: F04D 29/441 especially adapted for elastic fluid pumps
• CPC Class Codes: F05D 2220/40 in turbochargers

Abstract

A two-sided turbocharger compressor wheel and a housing forming a diffuser for the compressor. A first side and a second side of the compressor wheel are characterized by different values of a trim and of an annulus area. A first side of the diffuser surrounds the first side of the compressor wheel, and a second side of the diffuser surrounds the second side of the compressor wheel. The first and second sides of the diffuser are characterized by different annulus area ratios. The blades of the first and second sides of the compressor wheel are angularly offset from one another. The compressor wheel is configured for greater flow through the side of the compressor wheel that faces away from a related turbine wheel.

Claims

1. A two-sided turbocharger compressor wheel, comprising:

a hub defining an axial axis of rotation; and

a plurality of blades including a first set of compressor blades attached to a first axial side of the hub; and

a second set of compressor blades attached to a second axial side of the hub, the first set of compressor blades being completely axially separate from the second set of compressor blades;

wherein the first set of compressor blades defines a first inducer;

wherein the second set of compressor blades defines a second inducer, wherein the first inducer opens in a direction away from the second inducer, and wherein the second inducer opens in a direction axially opposite from the direction that the first inducer opens;

wherein the first set of compressor blades are characterized by a first set of blade parameters consisting of a first wheel trim and a first annulus area;

wherein the second set of compressor blades are characterized by a second set of blade parameters consisting of a second wheel trim and a second annulus area; and

wherein the values of the first set of blade parameters are not all identical to the values of the second set of blade parameters.

2. The two-sided turbocharger compressor wheel of claim 1, wherein at least some of the root trailing edges of the blades of the second axial side of the hub are at different circumferential locations than the root trailing edges of any of the blades of the first axial side of the hub.

3. The two-sided turbocharger compressor wheel of claim 2, wherein all of the root trailing edges of the blades of the second axial side of the hub are at different circumferential locations than the root trailing edges of any of the blades of the first axial side of the hub.

4. The two-sided turbocharger compressor wheel of claim 3, wherein the root trailing edge of each of the blades of the second axial side of the hub are at a location that is angularly offset around the axis of rotation from the location of a root trailing edge of a corresponding blade of the first axial side of the hub by a singular angle.

5. The two-sided turbocharger compressor wheel of claim 4, wherein the root trailing edge of each of the blades of the second axial side of the hub are at a location that is angularly half way between two consecutive blades of the first axial side of the hub around the axis of rotation.

6. A turbocharger, comprising:

a turbocharger housing; and

a rotor being mounted for axial rotation within the turbocharger housing, the rotor including a shaft extending axially between a turbine wheel and the two-sided turbocharger compressor wheel of claim 1.

7. The turbocharger of claim 6, wherein:

the housing defines a diffuser for the two-sided turbocharger compressor wheel, the diffuser including a first portion surrounding the first set of compressor blades, and the diffuser including an axially separate second portion surrounding the second set of compressor blades;

the diffuser is characterized by a first annulus area ratio for the diffuser first portion and by a second annulus area ratio for the diffuser second portion; and

the first annulus area ratio is not identical to the second annulus area ratio.