Aircraft propulsion system with auxiliary flowpath system

A propulsion system for an aircraft, comprising:

• an open propulsor rotor;
• a turbine engine configured to drive rotation of the open propulsor rotor about an axis, the turbine engine including an engine flowpath, a compressor section, a combustor section and a turbine section, and the engine flowpath extending through the compressor section, the combustor section and the turbine section from an engine flowpath inlet to an engine flowpath exhaust;
• and
• an auxiliary flowpath extending longitudinally along a trajectory from an auxiliary flowpath first orifice to an auxiliary flowpath second orifice, the auxiliary flowpath first orifice disposed along an exterior of the propulsion system that borders an environment external to the propulsion system, and the auxiliary flowpath second orifice disposed along the engine flowpath;
• wherein the trajectory extends circumferentially about the axis as the auxiliary flowpath extends longitudinally between the auxiliary flowpath first orifice and the auxiliary flowpath second orifice.

A propulsion system for an aircraft, comprising:

• an open propulsor rotor;
• a turbine engine configured to drive rotation of the open propulsor rotor about an axis, the turbine engine including an engine flowpath, a compressor section, a combustor section and a turbine section, and the engine flowpath extending through the compressor section, the combustor section and the turbine section from an engine flowpath inlet to an engine flowpath exhaust;
• an auxiliary flowpath extending from an auxiliary flowpath inlet to an auxiliary flowpath outlet, the auxiliary flowpath inlet disposed along an exterior of the propulsion system that borders an environment external to the propulsion system, and the auxiliary flowpath outlet disposed along the engine flowpath;
• and
• a flow regulator configured to open during a reverse thrust operating mode such that the auxiliary flowpath directs air from the environment into the engine flowpath.