Symmetric open propulsor rotating patterns for aircraft

An assembly for an aircraft, comprising:

• a first propulsion system and a second propulsion system;
• each of the first propulsion system and the second propulsion system including an open propulsor rotor and a turbine engine configured to drive rotation of the open propulsor rotor, the open propulsor rotor comprising a plurality of open propulsor blades, the turbine engine including a compressor section, a combustor section, a turbine section, a first rotating structure, a second rotating structure and a flowpath, the first rotating structure comprising a first bladed rotor, the second rotating structure comprising a second bladed rotor and operable to rotate independent of the first rotating structure, and the flowpath extending through the compressor section, the combustor section and the turbine section with the first bladed rotor disposed between the second bladed rotor and the combustor section along the flowpath;
• wherein the open propulsor rotor of the first propulsion system is configured to rotate a first rotational direction and has a first propulsor rotation parameter equal to positive one;
• wherein the open propulsor rotor of the second propulsion system is configured to rotate a second rotational direction, that is opposite the first rotational direction, and has a second propulsor rotation parameter equal to negative one;
• wherein the first bladed rotor of the first propulsion system has a first system first rotor rotation parameter equal to positive one where the first bladed rotor of the first propulsion system is configured to rotate in the first rotational direction or negative one where the first bladed rotor of the first propulsion system is configured to rotate in the second rotational direction;
• wherein the first bladed rotor of the second propulsion system has a second system first rotor rotation parameter equal to positive one where the first bladed rotor of the second propulsion system is configured to rotate in the first rotational direction or negative one where the first bladed rotor of the second propulsion system is configured to rotate in the second rotational direction;
• wherein the second bladed rotor of the first propulsion system has a first system second rotor rotation parameter equal to positive one where the second bladed rotor of the first propulsion system is configured to rotate in the first rotational direction or negative one where the second bladed rotor of the first propulsion system is configured to rotate in the second rotational direction;
• wherein the second bladed rotor of the second propulsion system has a second system second rotor rotation parameter equal to positive one where the second bladed rotor of the second propulsion system is configured to rotate in the first rotational direction or negative one where the second bladed rotor of the second propulsion system is configured to rotate in the second rotational direction;
• wherein a product of the first propulsor rotation parameter, the first system first rotor rotation parameter and the first system second rotor rotation parameter is equal to a first value;
• wherein a product of the second propulsor rotation parameter, the second system first rotor rotation parameter and the second system second rotor rotation parameter is equal to a second value;
• and
• wherein a sum of the first value and the second value is equal to zero.

An assembly for an aircraft, comprising:

• a first propulsion system and a second propulsion system;
• each of the first propulsion system and the second propulsion system including an open propulsor rotor and a turbine engine configured to drive rotation of the open propulsor rotor, the turbine engine including a compressor section, a combustor section, a turbine section, a first rotating structure, a second rotating structure and a flowpath, the first rotating structure comprising a first bladed rotor, the second rotating structure comprising a second bladed rotor and operable to rotate independent of the first rotating structure, and the flowpath extending through the compressor section, the combustor section and the turbine section with the first bladed rotor disposed between the second bladed rotor and the combustor section along the flowpath;
• wherein the open propulsor rotor of the first propulsion system is configured to rotate a first rotational direction and has a first propulsor rotation parameter equal to positive one;
• wherein the open propulsor rotor of the second propulsion system is configured to rotate a second rotational direction, that is opposite the first rotational direction, and has a second propulsor rotation parameter equal to negative one;
• wherein the first bladed rotor of the first propulsion system has a first system first rotor rotation parameter equal to positive one where the first bladed rotor of the first propulsion system is configured to rotate in the first rotational direction or negative one where the first bladed rotor of the first propulsion system is configured to rotate in the second rotational direction;
• wherein the first bladed rotor of the second propulsion system has a second system first rotor rotation parameter equal to positive one where the first bladed rotor of the second propulsion system is configured to rotate in the first rotational direction or negative one where the first bladed rotor of the second propulsion system is configured to rotate in the second rotational direction;
• wherein the second bladed rotor of the first propulsion system has a first system second rotor rotation parameter equal to positive one where the second bladed rotor of the first propulsion system is configured to rotate in the first rotational direction or negative one where the second bladed rotor of the first propulsion system is configured to rotate in the second rotational direction;
• wherein the second bladed rotor of the second propulsion system has a second system second rotation parameter equal to positive one where the second bladed rotor of the second propulsion system is configured to rotate in the first rotational direction or negative one where the second bladed rotor of the second propulsion system is configured to rotate in the second rotational direction;
• wherein an absolute value of a sum of the first propulsor rotation parameter, the second propulsor rotation parameter, the first system first rotor rotation parameter, the second system first rotor rotation parameter, the first system second rotor rotation parameter and the second system second rotor rotation parameter is equal to or less than two;
• wherein a product of the first propulsor rotation parameter, the first system first rotor rotation parameter and the first system second rotor rotation parameter is equal to a first value;
• wherein a product of the second propulsor rotation parameter, the second system first rotor rotation parameter and the second system second rotor rotation parameter is equal to a second value;
• and
• wherein a sum of the first value and the second value is equal to zero.