Open rotor aircraft propulsion system with offset geartrain

An assembly for an aircraft, comprising:

• an open propulsor rotor configured to rotate about a first axis;
• an open guide vane structure disposed aft of the open propulsor rotor along a second axis that is at least laterally offset from the first axis, the open guide vane structure including a plurality of open guide vanes arranged circumferentially about the second axis, and the plurality of open guide vanes comprising a first open guide vane;
• a turbine engine including a flowpath, a compressor section, a combustor section, a turbine section and a rotating assembly, the flowpath extending through the compressor section, the combustor section and the turbine section from an airflow inlet into the flowpath to a combustion products exhaust from the flowpath, the airflow inlet comprising a non-annular inlet opening wherein an inner end of the first open guide vane is circumferentially aligned with and radially outboard of the non-annular inlet opening, the rotating assembly comprising a turbine rotor disposed in the turbine section, and the rotating assembly configured to rotate about the second axis;
• and
• a drivetrain comprising an offset geartrain, the rotating assembly configured to drive rotation of the open propulsor rotor through the offset geartrain.

An assembly for an aircraft, comprising:

• an open propulsor rotor configured to rotate about a first axis;
• an open guide vane structure disposed downstream of the open propulsor rotor along a second axis that is at least laterally offset from the first axis, the open guide vane structure including a plurality of open guide vanes arranged and non-equispaced circumferentially about the second axis;
• a turbine engine including a flowpath, a compressor section, a combustor section, a turbine section and a rotating assembly, the flowpath extending through the compressor section, the combustor section and the turbine section from an airflow inlet into the flowpath to a combustion products exhaust from the flowpath, the airflow inlet comprising a non-annular inlet opening, the rotating assembly comprising a turbine rotor disposed in the turbine section, and the rotating assembly configured to rotate about the second axis;
• and
• a drivetrain comprising an offset geartrain, the rotating assembly configured to drive rotation of the open propulsor rotor through the offset geartrain.