Abstract: A gas turbine engine includes a compressor joined to a turbine by a core rotor, with a combustor disposed therebetween for receiving compressed air from the compressor and fuel through a valve for producing combustion gas discharged to the turbine. A speed sensor measures speed of the core rotor, and a pressure sensor measures pressure at an inlet to the compressor. A controller is operatively joined to the sensors and the fuel valve and is configured for limiting fuel flow to the combustor in response to core acceleration rate and compressor inlet pressure to limit transient temperature of the combustor discharge combustion gas.