The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Jun. 20, 2017

Filed:

Apr. 11, 2013
Applicant:

Borgwarner Inc., Auburn Hills, MI (US);

Inventors:

Stephanie Dextraze, Bristol, CT (US);

David G. Grabowska, Asheville, NC (US);

Assignee:

BorgWarner Inc., Auburn Hills, MI (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F04D 25/04 (2006.01); F01D 5/14 (2006.01); F01D 5/20 (2006.01); F01D 11/02 (2006.01); F04D 29/16 (2006.01); F04D 29/42 (2006.01); F04D 29/68 (2006.01); F01D 5/04 (2006.01); F04D 17/10 (2006.01); F04D 29/28 (2006.01); F04D 29/52 (2006.01);
U.S. Cl.
CPC ...
F01D 5/143 (2013.01); F01D 5/048 (2013.01); F01D 5/145 (2013.01); F01D 5/146 (2013.01); F01D 5/20 (2013.01); F01D 11/02 (2013.01); F04D 17/10 (2013.01); F04D 25/04 (2013.01); F04D 29/162 (2013.01); F04D 29/284 (2013.01); F04D 29/4206 (2013.01); F04D 29/685 (2013.01); F04D 29/526 (2013.01); F05D 2220/40 (2013.01); Y10S 415/914 (2013.01);
Abstract

A turbocharger () comprising a housing () including a compressor shroud () and a turbine shroud (). A compressor wheel () is disposed in the compressor shroud () and includes a plurality of compressor blades (). Each compressor blade () includes a leading edge () and a compressor shroud contour edge (), wherein each compressor shroud contour edge () is in close confronting relation to the compressor shroud (). A turbine wheel () is disposed in the turbine shroud () and includes a plurality of turbine blades (). Each turbine blade () includes a leading edge () and a turbine shroud contour edge (), wherein each turbine shroud contour edge () is in close confronting relation to the turbine shroud (). At least one of the compressor shroud () and turbine shroud () includes a plurality of grooves () extending cross-wise with respect to the corresponding compressor or turbine shroud contour edges ().


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