Air system for open rotor aircraft propulsion system

A propulsion system for an aircraft, comprising:

• a turbine engine including a first engine rotor, a second engine rotor, a first shroud and a second shroud, the first engine rotor including a first rotor base and a plurality of first rotor blades arranged circumferentially around the first rotor base in a first rotor blade array, the first shroud next to and circumscribing the first rotor blade array, the second engine rotor including a second rotor base and a plurality of second rotor blades arranged circumferentially around the second rotor base in a second rotor blade array, and the second shroud next to and circumscribing the second rotor blade array;
• and
• an air system including an electric boost compressor, an air circuit, a first clearance control device and a second clearance control device, the air circuit extending longitudinally through the electric boost compressor from an air source to the first clearance control device and the second clearance control device, the first clearance control device aligned with and circumscribing the first shroud, the second clearance control device aligned with and circumscribing the second shroud, and the air system configured to selectively direct air received from an airflow inlet into the air circuit to at least one of the first clearance control device or the second clearance control device.