公开(公告)号：US20250122849A1

公开(公告)日：2025-04-17

申请号：US18991142

申请日：2024-12-20

Applicant: General Electric Company

Inventor： Brandon W. Miller ,  Randy M. Vondrell ,  David M. Ostdiek ,  Craig W. Higgins ,  Alexander Simpson ,  William Bowden

IPC: F02K3/065 ,  F02C3/06

Abstract: A gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct. The gas turbine engine defines a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10. The thrust to power airflow ratio is a ratio of airflow through a bypass passage over the turbomachine plus airflow through the fan duct to airflow through the core duct. The core bypass ratio is a ratio of airflow through the fan duct to airflow through the core duct. The fan duct includes an exhaust nozzle having a plurality of chevrons disposed at its aft end to define an exhaust outlet.