公开(公告)号：US20250116243A1

公开(公告)日：2025-04-10

申请号：US18982445

申请日：2024-12-16

Applicant: General Electric Company

Inventor： William Joseph Bowden ,  Keith Edward James Blodgett ,  Mustafa Dindar ,  David Cerra ,  James Hamilton Grooms ,  Brandon Wayne Miller ,  Randy M. Vondrell ,  David Marion Ostdiek ,  Craig Williams Higgins ,  Alexander Kimberely Simpson

IPC: F02K3/065 ,  F02C3/06

Abstract: A gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order. The turbomachine defines an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct. The primary fan is driven by the turbomachine, and a secondary fan is located downstream of the primary fan within the inlet duct. One or more actuation devices operably associated with the fan duct, the one or more actuation devices actuable to increase or decrease an exit area of the fan duct.