A system to enable high pressure compressor build clearance reduction in a gas turbine engine, the system comprising: a low compressor of a gas turbine engine; a high compressor of a gas turbine engine having a ratio of a cold-rotor build clearance to a span between 0.7% and 7%, wherein the cold-rotor build clearance is defined for a plurality of rotor blades of the high compressor with respect to an engine casing assembly interior surface of the high compressor, and the span is defined as a gap between a rotor disk of the high compressor and the engine casing assembly interior surface of the high compressor for at least a last two stages of the high compressor closest to a combustor section of the gas turbine engine, and the high compressor is between the low compressor and the combustor section; at least two bowed rotor management systems for the gas turbine engine to prevent damage to the rotor blades for a bowed rotor condition of the high compressor under a plurality of starting and operating conditions, wherein the bowed rotor condition of the high compressor occurring after engine shutoff when thermal expansion causes deflection of the high compressor rotor with respect to the engine casing assembly interior surface of the high compressor, characterized in that the at least two bowed rotor management systems comprise a damper system (41; 600) configured to reduce vibration effects caused by the rotor deflection; the system further comprising: a controller operable to determine a status of the bowed rotor condition of the high compressor, wherein the controller is operable to select between use of the at least two bowed rotor management systems based on the status of the bowed rotor condition of the high compressor or a condition external to the gas turbine engine; and a mitigation monitor operable to sequence use of the at least two bowed rotor management systems, restart use of one or more of the at least two bowed rotor management systems, and trigger a maintenance request based on a detected bowed rotor elimination fault condition. a low compressor of a gas turbine engine; a high compressor of a gas turbine engine having a ratio of a cold-rotor build clearance to a span between 0.7% and 7%, wherein the cold-rotor build clearance is defined for a plurality of rotor blades of the high compressor with respect to an engine casing assembly interior surface of the high compressor, and the span is defined as a gap between a rotor disk of the high compressor and the engine casing assembly interior surface of the high compressor for at least a last two stages of the high compressor closest to a combustor section of the gas turbine engine, and the high compressor is between the low compressor and the combustor section; at least two bowed rotor management systems for the gas turbine engine to prevent damage to the rotor blades for a bowed rotor condition of the high compressor under a plurality of starting and operating conditions, wherein the bowed rotor condition of the high compressor occurring after engine shutoff when thermal expansion causes deflection of the high compressor rotor with respect to the engine casing assembly interior surface of the high compressor, a controller operable to determine a status of the bowed rotor condition of the high compressor, wherein the controller is operable to select between use of the at least two bowed rotor management systems based on the status of the bowed rotor condition of the high compressor or a condition external to the gas turbine engine; and a mitigation monitor operable to sequence use of the at least two bowed rotor management systems, restart use of one or more of the at least two bowed rotor management systems, and trigger a maintenance request based on a detected bowed rotor elimination fault condition.