Aircraft with symmetric propulsion system rotating patterns

An aircraft system, comprising:

• a first open propulsor rotor;
• a first open guide vane structure next to the first open propulsor rotor;
• and
• a first turbine engine including a first core compressor section, a first core combustor section, a first core turbine section, a first power turbine section, a first flowpath, a first core turbine rotor and a first power turbine rotor, the first flowpath extending through the first core compressor section, the first core combustor section, the first core turbine section and the first power turbine section from an inlet into the first flowpath to an exhaust from the first flowpath, the first core turbine rotor disposed in the first core turbine section and configured to rotate in a first rotational direction, the first power turbine rotor disposed in the first power turbine section and configured to rotate in the first rotational direction, and the first power turbine rotor further configured to drive rotation of the first open propulsor rotor in a first propulsor rotational direction about a first axis;
• wherein the first power turbine rotor is disposed axially between the first open propulsor rotor and the first core turbine rotor along the first axis, and the first open guide vane structure is selectively rotationally fixed or rotatable about the first axis.

An aircraft system, comprising:

• a first propulsion system including a first open propulsor rotor, a first core compressor section, a first core combustor section, a first core turbine section, a first power turbine section, a first flowpath, a first core turbine rotor and a first power turbine rotor, the first flowpath extending through the first core compressor section, the first core combustor section, the first core turbine section and the first power turbine section from an inlet into the first flowpath to an exhaust from the first flowpath, the first core turbine rotor disposed in the first core turbine section and configured to rotate in a first rotational direction, the first power turbine rotor disposed in the first power turbine section and configured to rotate in the first rotational direction, and the first power turbine rotor operatively coupled to the first open propulsor rotor;
• and
• a second propulsion system including a second open propulsor rotor, a second core compressor section, a second core combustor section, a second core turbine section, a second power turbine section, a second flowpath, a second core turbine rotor and a second power turbine rotor, the second flowpath extending through the second core compressor section, the second core combustor section, the second core turbine section and the second power turbine section from an inlet into the second flowpath to an exhaust from the second flowpath, the second core turbine rotor disposed in the second core turbine section and configured to rotate in the first rotational direction, the second power turbine rotor disposed in the second power turbine section and configured to rotate in a second rotational direction that is opposite the first rotational direction, and the second power turbine rotor operatively coupled to the second open propulsor rotor;
• wherein at least one of
• the first open propulsor rotor is rotatable about a first axis, and the first core turbine rotor is located axially between the first open propulsor rotor and the first power turbine rotor along the first axis;
• or
• the second open propulsor rotor is rotatable about a second axis, and the second core turbine rotor is located axially between the second open propulsor rotor and the second power turbine rotor along the second axis.