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. 01, 2020

Filed:

Dec. 29, 2015
Applicant:

General Electric Company, Schenectady, NY (US);

Inventors:

Thomas Ory Moniz, Loveland, OH (US);

Joseph George Rose, Mason, OH (US);

Paul Daniel Kemper, Loveland, OH (US);

Assignee:

General Electric Company, Schenectady, NY (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02K 3/06 (2006.01); F04D 29/54 (2006.01); F01D 9/04 (2006.01); F01D 25/24 (2006.01); F01D 25/16 (2006.01); F02C 3/04 (2006.01); F04D 29/52 (2006.01); F04D 29/64 (2006.01);
U.S. Cl.
CPC ...
F04D 29/542 (2013.01); F01D 9/041 (2013.01); F01D 25/162 (2013.01); F01D 25/243 (2013.01); F01D 25/246 (2013.01); F02C 3/04 (2013.01); F02K 3/06 (2013.01); F04D 29/522 (2013.01); F04D 29/644 (2013.01); F05D 2220/323 (2013.01); F05D 2230/60 (2013.01); F05D 2230/70 (2013.01); F05D 2240/12 (2013.01); F05D 2240/129 (2013.01); F05D 2240/35 (2013.01); F05D 2240/80 (2013.01); F05D 2250/36 (2013.01); Y02T 50/671 (2013.01); Y02T 50/673 (2013.01);
Abstract

A turbofan engine assembly includes a core gas turbine engine with a booster compressor having a radially outer diameter, a fan case assembly, and an outlet guide vane assembly. The outlet guide vane assembly includes a plurality of outlet guide vane segments spaced circumferentially about the core gas turbine engine. Each outlet guide vane segment of the plurality of outlet guide vane segments includes a radially inner fan hub frame flange configured to couple to the core gas turbine engine, a radially outer fan case flange configured to couple to the fan case assembly, and a plurality of outlet guide vanes extending therebetween. The radially inner diameter of the outlet guide vane assembly is smaller than the radially outer diameter of the booster compressor.


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