US 11,952,948 B2
Turbomachine and gear assembly
Juraj Hrubec, Prague (CZ); and Davide Lauria, Turin (IT)
Assigned to GE AVIO S.R.L., Rivalta di Torino (IT)
Filed by GE Avio S.r.l., Rivalta di Torino (IT)
Filed on Jul. 19, 2022, as Appl. No. 17/813,453.
Application 17/813,453 is a continuation of application No. 17/150,136, filed on Jan. 15, 2021, granted, now 11,408,355.
Claims priority of application No. 102020000000652 (IT), filed on Jan. 15, 2020.
Prior Publication US 2022/0349350 A1, Nov. 3, 2022
Int. Cl. F02C 7/36 (2006.01); F02C 7/06 (2006.01)
CPC F02C 7/36 (2013.01) [F02C 7/06 (2013.01); F05D 2260/40311 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A turbomachine engine comprising:
a fan assembly comprising a plurality of fan blades; and
a core engine surrounded by an outer casing, wherein the core engine comprises:
a power output component operably connected to the fan assembly, the power output component including a planet gear;
a first input power source and a second input power source, wherein the first input power source is counter-rotatable relative to the second input power source; and
a gear assembly operably connected to the power output component and configured to receive power from the first input power source and the second input power source, the gear assembly comprising a ring gear that rotates circumferentially about a gear assembly centerline axis, wherein the planet gear rotates circumferentially about the gear assembly centerline axis, and wherein one of the first input power source or the second input power source is coupled to the planet gear through the gear assembly, rotation of the one of the first input power source or the second input power source causes the ring gear to rotate, and the ring gear is coupled to the other one of the first input power source or the second input power source.