Aircraft with symmetric open propulsor rotating patterns

An assembly for an aircraft, comprising:

• a first propulsion system disposed laterally to a first side of an aircraft fuselage, the first propulsion system including a first open propulsor rotor, a first engine core and a first geartrain, the first open propulsor rotor disposed at a forward end of the first propulsion system, the first open propulsor rotor configured to rotate in a first rotational direction about a first axis, the first engine core comprising a first rotating structure with a first turbine rotor, and the first rotating structure configured to rotate in the first rotational direction about the first axis and drive rotation of the first open propulsor rotor through the first geartrain;
• and
• a second propulsion system disposed laterally to a second side of the aircraft fuselage, the second propulsion system including a second open propulsor rotor, a second engine core and a second geartrain, the second open propulsor rotor disposed at a forward end of the second propulsion system, the second open propulsor rotor configured to rotate in a second rotational direction about a second axis that is opposite the first rotational direction, the second engine core comprising a second rotating structure with a second turbine rotor, and the second rotating structure configured to rotate in the first rotational direction about the second axis and drive rotation of the second open propulsor rotor through the second geartrain.

An assembly for an aircraft, comprising:

• an open propulsor rotor configured to rotate about an axis;
• an engine core including a flowpath, a compressor section, a combustor section, a turbine section and a rotating structure, the flowpath extending longitudinally 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 rotating structure including a turbine rotor within the turbine section, and the rotating structure configured to rotate about the axis and drive rotation of the open propulsor rotor;
• and
• a geartrain disposed axially between and operatively coupling the rotating structure and the open propulsor rotor, the geartrain including
• a sun gear configured to rotate about the axis;
• a plurality of first intermediate gears arranged circumferentially about the axis and meshed with the sun gear;
• a plurality of second intermediate gears arranged circumferentially about the axis, each of the plurality of second intermediate gears rotatably coupled to a respective one of the plurality of first intermediate gears;
• a ring gear circumscribing and meshed with the plurality of second intermediate gears;
• and
• a carrier, each of the plurality of first intermediate gears and each of the plurality of second intermediate gears rotatably mounted to the carrier.