US 12,421,904 B2
Mounting assembly for a gearbox assembly
Bugra H. Ertas, Niskayuna, NY (US); Ravindra Shankar Ganiger, Bengaluru (IN); Andrea Piazza, Turin (IT); and Arthur W. Sibbach, Boxford, MA (US)
Assigned to GENERAL ELECTRIC COMPANY, Evendale, OH (US); and GE AVIO S.R.L., Rivalta di Torino (IT)
Filed by General Electric Company, Evendale, OH (US); and GE Avio S.r.l., Rivalta di Torino (IT)
Filed on Apr. 21, 2025, as Appl. No. 19/184,773.
Application 19/184,773 is a continuation of application No. 18/910,905, filed on Oct. 9, 2024, granted, now 12,281,618.
Application 18/910,905 is a continuation in part of application No. 17/929,105, filed on Sep. 1, 2022, granted, now 12,203,418, issued on Jan. 21, 2025.
Claims priority of application No. 202211024200 (IN), filed on Apr. 25, 2022.
Prior Publication US 2025/0243814 A1, Jul. 31, 2025
This patent is subject to a terminal disclaimer.
Int. Cl. F02C 7/36 (2006.01); F01D 15/10 (2006.01); F16H 57/02 (2012.01); F16H 57/025 (2012.01); H02M 1/00 (2007.01); H02M 1/32 (2007.01); H02M 7/00 (2006.01)
CPC F02C 7/36 (2013.01) [F01D 15/10 (2013.01); F16H 57/025 (2013.01); F05D 2220/76 (2013.01); F05D 2260/4031 (2013.01); F16H 2057/02026 (2013.01); F16H 2057/02034 (2013.01); F16H 2057/02039 (2013.01); H02M 1/0067 (2021.05); H02M 1/327 (2021.05); H02M 7/003 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a fan, a compressor section, a turbine section that includes a rotating shaft, and a combustion section in flow communication with the compressor section and the turbine section;
an engine static structure;
an electric power system comprising:
at least one electric machine drivingly coupled to the rotating shaft and generating electricity as a first type of current;
at least one power converter electrically coupled with the at least one electric machine, the at least one power converter converting the electricity as the first type of current from the at least one electric machine to a second type of current; and
at least one power distribution management unit electrically coupled with the at least one power converter, the at least one power distribution management unit supplying the electricity as the second type of current to at least one of the gas turbine engine or one or more aircraft systems of an aircraft,
wherein the at least one power converter is integrated together with the at least one power distribution management unit in a power distribution management unit housing;
a gearbox assembly configured to transfer rotational energy from the turbine section to the fan; and
a mounting assembly for coupling the gearbox assembly to the gas turbine engine, the mounting assembly having:
a flex coupling configured to mount a first gear of the gearbox assembly to the rotating shaft of the gas turbine engine;
a flex mount configured to mount a second gear of the gearbox assembly to the engine static structure; and
a fan frame configured to mount a third gear of the gearbox assembly to the engine static structure,
wherein each of the flex coupling and the flex mount is characterized by a lateral impedance parameter ratio, a bending impedance parameter ratio, and a torsional impedance parameter ratio, and
wherein the lateral impedance parameter ratio of the flex coupling, the flex mount, or both is less than or equal to 0.5,
wherein the bending impedance parameter ratio of the flex coupling, the flex mount, or both is less than or equal to 0.5, and
wherein the torsional impedance parameter ratio of the flex coupling, the flex mount, or both is greater than or equal to 0.1.