a propulsor for providing air into a core engine housing, and for providing air as propulsion air radially outwardly of the core engine housing;

the core engine housing surrounding a compressor section, a combustor positioned downstream of the compressor section and a turbine section positioned downstream of the combustor;

an aircraft fluid moving within an inlet to the gas turbine engine, the inlet receives the air from the propulsor as inlet air, and there being a first temperature sensor for sensing a first temperature of the aircraft fluid at a first location and a second temperature sensor for sensing a second temperature of the aircraft fluid at a second location, the first location radially outward of the second location; and

a control configured to:

determine that an icing condition exists based on a temperature difference between the first temperature and the second temperature exceeding a predefined threshold, and

based on the determination that the icing condition exists, take a corrective action,

wherein the core engine housing includes an outer engine core housing and an inner engine core housing, a strut extends between the outer engine core housing and the inner engine core housing, and the aircraft fluid passes through the strut,

wherein the strut is exposed to the inlet air at the inlet, and

wherein to take the corrective action, the control is configured to execute a pilot notification or actuate an anti-icing system.