Gas Turbine Engine

A gas turbine engine comprising:

• a turbomachine comprising a core engine including at least one compressor section, a combustion section, and at least one turbine section arranged in serial flow order, the 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 including a plurality of variable pitch fan blades and driven by the turbomachine;
• and
• a secondary fan located downstream of the primary fan within the inlet duct,
• the gas turbine engine 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 over the turbomachine plus an airflow through the fan duct to an airflow through the core duct,
• wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core duct,
• wherein the primary fan includes a first VPF parameter and a second VPF parameter,
• wherein the first VPF parameter is within a range of 0.10-0.40 and is defined by a fan blade radius ratio (RR) divided by a fan pressure ratio (FPR) at a static sea-level takeoff operating condition;
• and
• wherein the second VPF parameter is within a range of 1-30 lbf/in2 and is defined by a bearing spanwise force (F_Span) at a redline operating condition measured in pounds force divided by a fan area (F_Area) measured in square inches.