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:
Sep. 19, 2017

Filed:

Apr. 29, 2014
Applicant:

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

Inventors:

Philippe Arnold, Hennecourt, FR;

Denis Jeckel, Thaon les Vosges, FR;

Peter Rhys Davies, Grandvillers, FR;

Christophe Riviere, Aydoilles, FR;

Gregory Do, Aydoilles, FR;

Dominique Petitjean, Julienrupt, FR;

Shankar Pandurangasa Solanki, Karnataka, IN;

Assignee:

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

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02B 37/24 (2006.01); F01D 17/16 (2006.01);
U.S. Cl.
CPC ...
F02B 37/24 (2013.01); F01D 17/165 (2013.01); F05D 2230/54 (2013.01);
Abstract

A turbocharger includes a variable turbine nozzle formed between first and second walls. A variable-vane assembly has a fixed nozzle ring and a plurality of circumferentially spaced vanes disposed in the nozzle and rotatably mounted on the nozzle ring such that the vanes are pivotable. The nozzle ring defines the first wall of the turbine nozzle, each vane having a first end adjacent the first wall and a second end adjacent the second wall. The second wall of the turbine nozzle is formed by a gas pressure-responsive member that is arranged to be axially movable relative to the vanes. A first stop is positioned so that the gas pressure-responsive member is urged against the first stop by a differential gas pressure exerted on the gas pressure-responsive member so that there is a non-zero first value for a clearance between the second ends of the vanes and the second wall of the turbine nozzle.


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