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 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 area parameter and a first propulsor flow area, and the first propulsor area parameter is equal to a product of positive one and the first propulsor flow area;
• 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 area parameter and a second propulsor flow area, and the second propulsor area parameter is equal to a product of negative one and the second propulsor flow area;
• wherein the first bladed rotor of the first propulsion system has a first system first rotor area parameter, a first system first rotor flow area and a first system first rotor rotation parameter, the first system first rotor area parameter is equal to a product of the first system first rotor flow area and the first system first rotor rotation parameter, and the first system first rotor rotation parameter is 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 area parameter, a second system first rotor flow area and a second system first rotor rotation parameter, the second system first rotor area parameter is equal to a product of the second system first rotor flow area and the second system first rotor rotation parameter, and the second system first rotor rotation parameter is 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 area parameter, a first system second rotor flow area and a first system second rotor rotation parameter, the first system second rotor area parameter is equal to a product of the first system second rotor flow area and the first system second rotor rotation parameter, and the first system second rotor rotation parameter is 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 area parameter, a second system second rotor flow area and a second system second rotor rotation parameter, the second system second rotor area parameter is equal to a product of the second system second rotor flow area and the second system second rotor rotation parameter, and the second system second rotor rotation parameter is 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 alpha parameter is equal to a sum of the first propulsor area parameter, the first system first rotor area parameter and the first system second rotor area parameter;
• wherein a beta parameter is equal to a sum of the second propulsor area parameter, the second system first rotor area parameter and the second system second rotor area parameter;
• wherein a gamma parameter is equal to a sum of the alpha parameter and the beta parameter;
• wherein an absolute value of a quotient of the gamma parameter divided by the beta parameter is less than 0.2.

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 speed rotating structure, a second speed rotating structure and a flowpath, the first speed rotating structure comprising a first bladed rotor, the second speed rotating structure comprising a second bladed rotor, and the flowpath extending through the compressor section, the combustor section and the turbine section;
• wherein the open propulsor rotor of the first propulsion system is configured to rotate a first rotational direction and has a first propulsor area parameter and a first propulsor flow area, and the first propulsor area parameter is equal to a product of positive one and the first propulsor flow area;
• 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 area parameter and a second propulsor flow area, and the second propulsor area parameter is equal to a product of negative one and the second propulsor flow area;
• wherein the first bladed rotor of the first propulsion system has a first system first rotor area parameter, a first system first rotor flow area and a first system first rotor rotation parameter, the first system first rotor area parameter is equal to a product of the first system first rotor flow area and the first system first rotor rotation parameter, and the first system first rotor rotation parameter is 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 area parameter, a second system first rotor flow area and a second system first rotor rotation parameter, the second system first rotor area parameter is equal to a product of the second system first rotor flow area and the second system first rotor rotation parameter, and the second system first rotor rotation parameter is 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 area parameter, a first system second rotor flow area and a first system second rotor rotation parameter, the first system second rotor area parameter is equal to a product of the first system second rotor flow area and the first system second rotor rotation parameter, and the first system second rotor rotation parameter is 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 area parameter, a second system second rotor flow area and a second system second rotor rotation parameter, the second system second rotor area parameter is equal to a product of the second system second rotor flow area and the second system second rotor rotation parameter, and the second system second rotor rotation parameter is 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 alpha parameter is equal to a sum of the first propulsor area parameter, the first system first rotor area parameter and the first system second rotor area parameter;
• wherein a beta parameter is equal to a sum of the second propulsor area parameter, the second system first rotor area parameter and the second system second rotor area parameter;
• wherein a gamma parameter is equal to a sum of the alpha parameter and the beta parameter;
• wherein an absolute value of a quotient of the gamma parameter divided by an X value is less than 0.2, and the X value is equal to one of the alpha parameter or the beta parameter.