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:
Oct. 21, 2025

Filed:

Oct. 09, 2024
Applicants:

General Electric Company, Evendale, OH (US);

GE Avio S.r.l., Rivalta di Torino, IT;

Inventors:

Bugra H. Ertas, Niskayuna, NY (US);

Ravindra Shankar Ganiger, Bengaluru, IN;

Andrea Piazza, Turin, IT;

Brandon W. Miller, Middletown, OH (US);

Assignees:

GENERAL ELECTRIC COMPANY, Evendale, OH (US);

GE AVIO S.R.L., Rivalta di Torino, IT;

Attorneys:
Primary Examiner:
Int. Cl.
CPC ...
F16H 57/025 (2012.01); F02C 7/36 (2006.01); F16H 1/28 (2006.01); F16H 57/02 (2012.01); F16H 57/023 (2012.01);
U.S. Cl.
CPC ...
F16H 57/025 (2013.01); F02C 7/36 (2013.01); F16H 1/2818 (2013.01); F16H 1/2827 (2013.01); F16H 1/2845 (2013.01); F16H 57/023 (2013.01); F16H 2057/02039 (2013.01);
Abstract

A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gear includes a first gear that is a split sun gear including a forward sun gear and an aft sun gear separate from the forward sun gear. The forward sun gear and the aft sun gear are each rotationally coupled to a rotating shaft of the gas turbine engine.


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