Turbine engine airfoil with a crush initiator

A composite fan blade for a turbine engine, the composite fan blade comprising:

• a fan blade core having a deformation threshold;
• an outer wall at least partially surrounding the fan blade core;
• a stiffener at least partially forming one of the fan blade core or the outer wall;
• and
• a crush initiator formed into the stiffener, wherein the crush initiator defines a crush geometry that specifies a geometry for deformation of the composite fan blade in response to a force exceeding the deformation threshold.

A fan blade for a turbine engine, the fan blade comprising:

• a core having a core deformation threshold;
• an outer wall, exterior of the core, having an exterior surface and an interior surface at least partially defining an interior, with the outer wall having a wall deformation threshold;
• and
• a crush initiator at least partially defining at least one of the core or the outer wall;
• wherein the crush initiator defines a crush geometry that specifies a geometry for deformation of at least one of the core or the outer wall in response to a force exceeding the core deformation threshold or the wall deformation threshold.