Abstract: A control system and method provide thrust droop compensation in a gas turbine engine. A droop compensation signal is generated for increasing turbine exit temperature T.sub.5 based on a predetermined model, and is selectively reduced for limiting the increase in temperature T.sub.5 when the temperature T.sub.5 is above a predetermined threshold temperature for a predetermined time. The reduced droop signal is added as a bias signal into an error signal which effects thrust droop concentration in a variable area exhaust nozzle of the engine.

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.