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:
Nov. 13, 2018

Filed:

Nov. 24, 2015
Applicant:

United Technologies Corporation, Hartford, CT (US);

Inventor:

John W. Magowan, Longmeadow, MA (US);

Assignee:

United Technologies Corporation, Farmington, CT (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02C 3/107 (2006.01); F02C 7/36 (2006.01); F02K 3/06 (2006.01); F02C 3/067 (2006.01);
U.S. Cl.
CPC ...
F02C 7/36 (2013.01); F02C 3/067 (2013.01); F02C 3/107 (2013.01); F02K 3/06 (2013.01); F05D 2260/40311 (2013.01);
Abstract

A gas turbine engine has a fan section including a fan hub supporting a plurality of fan blades for rotation relative to a fan case. A shaft is rotatable relative to the fan case about an engine center axis. A geared architecture is driven by the shaft and provides driving output to rotate the fan hub. A compressor is driven by the shaft and is positioned forward of the geared architecture. The compressor includes at least first and second stages with the first stage being positioned forward of the plurality of fan blades and the second stage being positioned aft of the plurality of fan blades. The compressor includes at least one set of vanes that rotate in a first direction about the engine center axis and at least one set of compressor blades that rotate in a second direction about the engine center axis. The second direction is opposite of the first direction.


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