Tailoring aircraft powerplant split line parameter with inflatable bladder

An assembly for an aircraft propulsion system, comprising:

• a bladed rotor rotatable about an axis, the bladed rotor comprising a fan rotor;
• an inner flowpath comprising a core flowpath and including a core flowpath inlet downstream of the bladed rotor;
• an outer flowpath comprising a bypass flowpath and including a bypass flowpath inlet downstream of the bladed rotor, the bypass flowpath inlet radially outboard of the core flowpath inlet;
• a flowpath wall downstream of the bladed rotor, the flowpath wall disposed radially between and partially forming the core flowpath inlet and the bypass flowpath inlet, the flowpath wall comprising an inflatable bladder and a radial outer surface that forms a radial inner peripheral boundary of the outer flowpath, and the inflatable bladder located at the bypass flowpath inlet;
• the inflatable bladder configured to deform the radial outer surface such that, when viewed in a reference plane parallel with the axis,
• at least a portion of the radial outer surface is convex during a first mode;
• and
• at least the portion of the radial outer surface is concave during a second mode.

An assembly for an aircraft propulsion system, comprising:

• a propulsor rotor;
• an engine core configured to drive rotation of the propulsor rotor about an axis, the engine core including a core inlet;
• an outer flowpath downstream of the propulsor rotor and disposed outside of the engine core;
• and
• a flowpath wall forming a radial inner peripheral boundary of the outer flowpath, the flowpath wall forming a radial outer peripheral boundary of a core flowpath, the flowpath wall comprising an inflatable bladder and a radial outer surface, the inflatable bladder configured to deform the radial outer surface, the inflatable bladder disposed adjacent a bypass inlet, and the inflatable bladder disposed radially outward of the core inlet.