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:
Aug. 20, 2024

Filed:

Oct. 31, 2022
Applicant:

General Electric Company, Schenectady, NY (US);

Inventors:

David Marion Ostdiek, Liberty Township, OH (US);

William Joseph Solomon, Montgomery, OH (US);

Assignee:

General Electric Company, Cincinnati, OH (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
B64C 11/48 (2006.01); F02K 3/06 (2006.01); B64C 11/00 (2006.01); B64C 11/18 (2006.01); F01D 9/02 (2006.01); F01D 17/10 (2006.01); F01D 17/14 (2006.01); F02C 7/36 (2006.01); F02K 3/065 (2006.01); F02K 3/072 (2006.01); F04D 19/02 (2006.01); F04D 29/34 (2006.01); F04D 29/38 (2006.01);
U.S. Cl.
CPC ...
F02K 3/06 (2013.01); B64C 11/001 (2013.01); B64C 11/18 (2013.01); B64C 11/48 (2013.01); F01D 9/02 (2013.01); F01D 17/105 (2013.01); F01D 17/14 (2013.01); F02C 7/36 (2013.01); F02K 3/065 (2013.01); F02K 3/072 (2013.01); F04D 19/02 (2013.01); F04D 29/34 (2013.01); F04D 29/388 (2013.01); F05D 2200/14 (2013.01); F05D 2200/211 (2013.01); F05D 2220/323 (2013.01);
Abstract

A gas turbine is provided, the gas turbine engine including a turbomachine having an inlet splitter defining in part an inlet to a working gas flowpath and a fan duct splitter defining in part an inlet to a fan duct flowpath. The gas turbine engine also includes a primary fan driven by the turbomachine defining a primary fan tip radius R, a primary fan hub radius R, and a primary fan specific thrust rating TP; and a secondary fan downstream of the primary fan and driven by the turbomachine, the secondary fan defining a secondary fan tip radius R, a secondary fan hub radius R, and a secondary fan specific thrust rating TS; wherein the gas turbine engine defines an Effective Bypass Area, and wherein a ratio of Rto Requals


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