Gas turbine engine fan

A gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising:

• a core turbine engine;
• and
• a fan mechanically coupled to the core turbine engine, the fan comprising
• a plurality of fan blades, each fan blade defining a base at an inner end along the radial direction, the plurality of fan blades rotatable about the axial direction at a maximum rotational speed of less than 9,350 revolutions per minute (RPM) during operation of the fan;
• a hub configured to direct an airflow through the plurality of fan blades and covering the base of each of the plurality of fan blades, wherein the hub defines a hub radius along the radial direction between a longitudinal axis and an outermost point of the hub along the radial direction;
• and
• one or more bearings for supporting rotation of the plurality of fan blades about the longitudinal axis, the one or more bearings defining a DN value during rotation of the plurality of fan blades about the axial direction at the maximum rotational speed of at least 0.54 million and up to 1.65 million, and the one or more bearings including a ball bearing defining a fan bearing radius along the radial direction, a ratio of the hub radius to the fan bearing radius being less than 1.75;
• and
• a power gearbox, wherein the fan is driven by the core turbine engine through the Power gearbox.

A gas turbine engine defining a radial direction and a longitudinal axis, the gas turbine engine comprising:

• a core turbine engine;
• and
• a fan mechanically coupled to the core turbine engine, the fan comprising
• a plurality of fan blades, each fan blade defining a base at an inner end along the radial direction;
• a hub configured to direct an airflow through the plurality of fan blades and covering the base of each of the plurality of fan blades, the hub defining a hub radius along the radial direction between the longitudinal axis and an outermost point of the hub along the radial direction;
• and
• one or more bearings for supporting rotation of the plurality of fan blades about the longitudinal axis, the one or more bearings including a ball bearing defining a fan bearing radius along the radial direction, a ratio of the hub radius to the fan bearing radius being less than 1.75;
• and
• a power gearbox, wherein the fan is driven by the core turbine engine through the power gearbox,
• wherein the gas turbine engine is configured to generate a maximum takeoff thrust, and wherein the maximum takeoff thrust is greater than 10,000 pounds and less than 30,000 pounds.