Axial thrust loading mitigation in a turbocharger

Patent metadata

Field	Value
Publication number	US-10415599-B2
Application number	US-201514928743-A
Country	US
Kind code	B2
Filing date	Oct 30, 2015
Priority date	Oct 30, 2015
Publication date	Sep 17, 2019
Grant date	Sep 17, 2019

Abstract

Methods and systems are provided for a turbocharger system to reduce and balance axial thrust load on the turbine shaft and the associated bearing system and sealing. In one example, a partial back plate compressor may be used in combination with an axial turbine to reduce axial thrust load and to improve turbocharger transient response time. In another example, a regenerative turbocharger system with back-to-back turbo pump may be used to reduce and balance axial thrust load.

First claim

The invention claimed is:

1. A turbocharger system, comprising:
a centrifugal compressor including an impeller having a plurality of radially-arranged blades coupled to a partial back plate, the partial back plate comprising a plurality of cut-out sections, each cut-out section located between two of the blades on an outer circumference of the impeller;
a shaft coupling the impeller of the compressor to a drive unit;
a rotating disk located inside a chamber of a center housing of the shaft, the rotating disk coupled to the shaft, the chamber defined by the center housing of the shaft and chamber walls and enclosing a space that at least partially surrounds the rotating disk; and
a passage connecting an outlet of the compressor to the chamber, the passage fluidly connecting the outlet of the compressor to the space of the chamber, where the chamber is fully closed other than where the chamber connects to the passage.

2. The turbocharger system of claim 1 , wherein the drive unit is an axial turbine including a turbine impeller and a rotor inlet and a rotor outlet, where impinging fluid/air is moved parallel to the turbine impeller, along the entire turbine impeller.

3. The turbocharger system of claim 1 , further comprising thrust bearings mounted on the shaft.

4. The turbocharger system of claim 3 , wherein the rotating disk in the chamber is a sealing ring positioned intermediate the partial back plate and the thrust bearings, the sealing ring a part of a sealing mechanism configured to seal the center housing of the shaft, and wherein the chamber partially surrounds the sealing mechanism.

5. The turbocharger system of claim 1 , wherein the impeller further comprises a plurality of through-holes connecting a back-face of the impeller to a front-face of the compressor.

6. The turbocharger system of claim 1 , wherein the blades of the compressor impeller are full blades.

7. The turbocharger system of claim 1 , wherein the blades of the compressor impeller are splitter blades.

Assignees

• Ford Global Tech Llc

Inventors

• Sun Harold Huimin
• Hu Leon
• Hanna Dave R
• Yi Jianwen James
• Curtis Eric Warren

Classifications

• F04D29/662 Primary

  Balancing of rotors (compensating imbalance G01M1/36) · CPC title

• F04D29/284

  for compressors · CPC title

• F04D29/051

  Axial thrust balancing · CPC title

• F04D25/045

  the pump wheel carrying the fluid driving means, e.g. turbine blades · CPC title

• F04D25/024 Primary

  the driving means being assisted by a power recovery turbine · CPC title