Valved airflow passage assembly for adjusting airflow distortion in gas turbine engine

A gas turbine engine system for an aircraft comprising:

• a core engine comprising a compressor section, a combustion section, and a turbine section in series flow and defining at least in part an engine airflow path, the compressor section comprising a compressor;
• a valved airflow passage assembly comprising a duct and a valve, the duct defining an inlet in airflow communication with the engine airflow path at a location downstream of the compressor, an outlet in airflow communication with the engine airflow path at a location upstream of the compressor, and an airflow passage extending between the inlet and the outlet;
• and
• a controller operably connected to the valve of the valved airflow passage assembly, the controller comprising one or more processors and one or more memory devices located on an aircraft, the one or more memory devices storing instructions that when executed by the one or more processors cause the one or more processors to perform operations, the operations comprising:
• determine an airflow distortion condition within the engine airflow path at a location upstream of the compressor;
• and
• control the valve to adjust an airflow through the airflow passage to adjust the determined airflow distortion condition.