General electric company (20250122849). GAS TURBINE ENGINE WITH THIRD STREAM
GAS TURBINE ENGINE WITH THIRD STREAM
Organization Name
Inventor(s)
Brandon W. Miller of Evendale OH US
Randy M. Vondrell of Evendale OH US
David M. Ostdiek of Evendale OH US
Craig W. Higgins of Evendale OH US
Alexander Simpson of Evendale OH US
William Bowden of Evendale OH US
GAS TURBINE ENGINE WITH THIRD STREAM
This abstract first appeared for US patent application 20250122849 titled 'GAS TURBINE ENGINE WITH THIRD STREAM
Original Abstract Submitted
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.