Open rotor aircraft propulsion system with guide vane structure receptacle

An assembly for an aircraft propulsion system, comprising:

• an open propulsor rotor comprising a plurality of open propulsor blades arranged circumferentially around an axis, each of the plurality of open propulsor blades projecting radially out into an environment external to the aircraft propulsion system;
• a housing structure including an engine case, a nacelle structure and a receptacle, the nacelle structure disposed radially outboard of and partially covering the engine case, the nacelle structure forming a first axial section of an exterior flow boundary for the aircraft propulsion system that borders the environment external to the aircraft propulsion system, the receptacle disposed radially outboard of the engine case and axially between the open propulsor rotor and the nacelle structure, and the receptacle configured to receive a structure base of an open guide vane structure;
• a compressor section housed within the engine case;
• a combustor section housed within the engine case;
• a turbine section housed within the engine case, the turbine section comprising a turbine rotor operatively coupled to the open propulsor rotor, and the turbine rotor configured to drive rotation of the open propulsor rotor about the axis;
• and
• a flowpath extending through the compressor section, the combustor section and the turbine section from an inlet into the flowpath to an exhaust from the flowpath.