Open rotor aircraft propulsion system with anti-icing system

An assembly for an aircraft propulsion system, comprising:

• a propulsion module comprising an open propulsor rotor, a nose cone and a plurality of open guide vanes arranged circumferentially about an axis, the plurality of open guide vanes including a first open guide vane;
• a gas generator configured to drive rotation of the open propulsor rotor about the axis, the gas generator including a flowpath, a compressor section, a combustor section, a turbine section and an exhaust section, the flowpath extending through the compressor section, the combustor section, the turbine section and the exhaust section from an inlet into the flowpath to an exhaust from the flowpath, and the turbine section axially between the combustor section and the open propulsor rotor along the axis;
• and
• an anti-icing system configured to bleed gas from the flowpath in the exhaust section to provide heated gas, and the anti-icing system configured to direct the heated gas to the propulsion module to reduce or prevent ice accumulation on an exterior surface of the propulsion module;
• wherein the exterior surface of the propulsion module comprises at least one of the nose cone, the first open guide vane or the open propulsor rotor.