GAS TURBINE ENGINE WITH THIRD STREAM

A gas turbine engine (100) is provided. The gas turbine engine includes a turbomachine (120, 506) including a compressor section (512), a combustion section (514), and a turbine section (516) arranged in serial flow order, the turbomachine (120, 506) defining an engine inlet (182) to an inlet duct (180), a fan duct inlet (176) to a fan duct (172), and a core inlet (124) to a core duct (142); a primary fan (152) driven by the turbomachine (120, 506); and a secondary fan (184) located downstream of the primary fan (152) within the inlet duct (180), the gas turbine engine (100) defining a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10, wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage (194, 522) over the turbomachine (120, 506) plus an airflow through the fan duct (172) to an airflow through the core duct (142), and wherein the core bypass ratio is a ratio of the airflow through the fan duct (172) to the airflow through the core duct (142).