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:
May. 22, 2018

Filed:

Apr. 12, 2015
Applicant:

Honeywell International Inc., Morristown, NJ (US);

Inventors:

Raphaël Hettinger, La Baffe, FR;

Raphaël Boileau, Thaon les Vosges, FR;

Fréderic Daguin, Epinal, FR;

Assignee:

Honeywell International Inc., Morris Plains, NJ (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F02B 39/14 (2006.01); F01D 25/16 (2006.01); F01D 25/18 (2006.01); F16C 25/08 (2006.01); F16C 27/04 (2006.01); F16C 35/077 (2006.01); F16C 19/54 (2006.01);
U.S. Cl.
CPC ...
F02B 39/14 (2013.01); F01D 25/164 (2013.01); F01D 25/166 (2013.01); F01D 25/18 (2013.01); F16C 25/083 (2013.01); F16C 27/045 (2013.01); F05D 2220/40 (2013.01); F05D 2240/53 (2013.01); F05D 2240/54 (2013.01); F16C 19/548 (2013.01); F16C 35/077 (2013.01); F16C 2360/24 (2013.01);
Abstract

An assembly can include a turbocharger center housing that includes a through bore and a counterbore positioned between a compressor end and a turbine end of the through bore where the through bore includes a sleeve mating surface positioned between the compressor end and the counterbore and a turbine side bearing lubricant film formation surface positioned between the counterbore and the turbine end; and a sleeve positioned at least in part in the through bore of the turbocharger center housing between the compressor end and the counterbore where the sleeve includes a locating flange and an axial extension that extends from the locating flange where the axial extension includes an outer mating surface, an inner compressor side bearing lubricant film formation surface, a compressor side axially facing spacer surface and a turbine side axially facing spacer surface.


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