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.

Abstract: A gas turbine engine includes a controller configured for controlling combustor lean flameout. The engine includes a compressor joined to a turbine by a core rotor, with a combustor disposed therebetween for receiving compressed air and fuel for generating combustion gas discharged to the turbine. The controller is configured for reducing fuel flow to the combustor in response to speed of the core rotor and pressure of compressed air entering the combustor to decelerate the core rotor while preventing lean flameout in the combustor.

Abstract: A method and system are provided to bias a control subsystem of a gas turbine engine having a fan and compressor. The method includes the steps of measuring an operating parameter of the engine and differentiating this parameter over time to obtain a derivative thereof. A bias signal is generated in a predetermined bias schedule in response to the parameter derivative, and provided to the control subsystem for biasing the subsystem. The bias signal has a zero value for values of the parameter derivative from zero to a first value thereof at a first time. The bias signal has a maximum value for values of the parameter derivative between second and third values thereof corresponding with second and third times. And, the bias signal returns to a value of zero after a fourth time greater than the third time.