Open rotor propulsion system with exhaust mixer(s)

A propulsion system for an aircraft, comprising:

• a propulsion section including an open propulsor rotor and an open guide vane structure disposed next to the open propulsor rotor;
• and
• a turbine engine configured to drive rotation of the open propulsor rotor about an axis, the turbine engine including an engine core, an inlet section, an exhaust section and a flowpath, the engine core including a compressor section, a combustor section and a turbine section, the inlet section comprising a flowpath inlet, the exhaust section comprising a flowpath exhaust and a mixer at the flowpath exhaust, and the flowpath extending from the flowpath inlet, through the inlet section, the compressor section, the combustor section, the turbine section and the exhaust section, to the flowpath exhaust;
• wherein the mixer is configured to mix combustion products exhausted from the flowpath through the flowpath exhaust with ambient air outside of the propulsion system;
• and
• wherein the flowpath exhaust is axially aligned with the open guide vane structure.

A propulsion system for an aircraft, comprising:

• a propulsion section comprising a propulsor rotor, wherein the propulsor rotor comprises an open propulsor rotor, and the propulsion section further comprises a guide vane structure axially next to and downstream of the propulsor rotor;
• a compressor section;
• a combustor section;
• a first turbine section;
• a second turbine section configured to drive rotation of the propulsor rotor about an axis;
• an exhaust section including a plurality of exhaust outlets and a plurality of mixers, the plurality of exhaust outlets arranged circumferentially about the axis, and each of the plurality of mixers located at a respective one of the plurality of exhaust outlets to mix combustion products exhausted through the respective one of the plurality of exhaust outlets with another flow of air;
• and
• a flowpath extending from a flowpath inlet, through the compressor section, the combustor section, the first turbine section, the second turbine section and the exhaust section, to the plurality of exhaust outlets.