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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.

Patent No.:

US 10934934 B1

PDFFull Text
Date of Patent:
Mar. 02, 2021

Filed:

Sep. 27, 2018

Reverse core gear turbofan

Applicant:

Raytheon Technologies Corporation, Farmington, CT (US);

Inventors:

Daniel Bernard Kupratis, Wallingford, CT (US);

Francis R. Moon, Granby, CT (US);

Assignee:

Raytheon Technologies Corporation, Waltham, MA (US);

Attorney:

Carlson, Gaskey & Olds, P.C.

Primary Examiner:

Arun Goyal

Int. Cl.
CPC ...
F02C 7/36 (2006.01); F02C 6/02 (2006.01); F02C 3/10 (2006.01); F02C 3/14 (2006.01); F02C 3/05 (2006.01); F02K 3/06 (2006.01); F01D 17/14 (2006.01); F02K 3/075 (2006.01); F02C 3/13 (2006.01); F02C 9/18 (2006.01); F02K 3/065 (2006.01); F02C 3/107 (2006.01);
U.S. Cl.
CPC ...
F02C 6/02 (2013.01); F01D 17/141 (2013.01); F02C 3/05 (2013.01); F02C 3/10 (2013.01); F02C 3/107 (2013.01); F02C 3/13 (2013.01); F02C 3/145 (2013.01); F02C 7/36 (2013.01); F02C 9/18 (2013.01); F02K 3/06 (2013.01); F02K 3/065 (2013.01); F02K 3/075 (2013.01); F05D 2220/32 (2013.01); F05D 2220/323 (2013.01); F05D 2250/36 (2013.01); F05D 2260/4023 (2013.01); F05D 2260/4031 (2013.01); F05D 2270/053 (2013.01);
Abstract

A gas turbine engine comprises a fan at an axially outer location, the fan rotating about an axis of rotation, delivering air into an outer bypass duct, a radially middle duct, and a radially inner core duct. Air from the inner core duct is directed into a compressor, and then flows axially in a direction back toward the fan through a combustor section, and across a core turbine section, and is then directed into the middle duct. A gear reduction drives the fan from a fan drive turbine section. A method of operating a gas turbine engine is also disclosed.

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