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:
Jun. 09, 2020

Filed:

Dec. 29, 2015
Applicant:

General Electric Company, Schenectady, NY (US);

Inventors:

Brandon Wayne Miller, Middletown, OH (US);

Narendra Digamber Joshi, Guilderland, NY (US);

Ian Francis Prentice, Cincinnati, OH (US);

Kurt David Murrow, Liberty Township, OH (US);

Assignee:

General Electric Company, Schenectady, NY (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02C 3/107 (2006.01); F02K 3/065 (2006.01); F02K 3/077 (2006.01); F01D 5/02 (2006.01); F01D 25/30 (2006.01); F02C 7/04 (2006.01); F02C 7/36 (2006.01); F04D 29/32 (2006.01); F02K 3/062 (2006.01); F02K 3/06 (2006.01);
U.S. Cl.
CPC ...
F02C 3/107 (2013.01); F01D 5/02 (2013.01); F01D 25/30 (2013.01); F02C 7/04 (2013.01); F02C 7/36 (2013.01); F02K 3/06 (2013.01); F02K 3/062 (2013.01); F02K 3/065 (2013.01); F02K 3/077 (2013.01); F04D 29/325 (2013.01); F05D 2220/36 (2013.01); F05D 2230/60 (2013.01); F05D 2240/35 (2013.01); F05D 2250/311 (2013.01); F05D 2250/50 (2013.01); Y02T 50/671 (2013.01);
Abstract

A gas turbine engine system and method of operating gas turbine engines are provided. The gas turbine engine assembly includes a gas turbine engine includes a power shaft configured to rotate about an axis of rotation. The gas turbine engine assembly also includes a first fan and a second fan coupled to the power shaft coaxially with the gas turbine engine. The gas turbine engine assembly also includes a first fan duct configured to direct a first stream of air to the first fan. The gas turbine engine assembly also includes a second fan duct configured to direct a second stream of air to the second fan. The gas turbine engine assembly also includes an exhaust duct configured to direct a stream of exhaust gases of the gas turbine engine in a direction of the axis of rotation.


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