Abstract: A method of calibrating a gas turbine engine having a propulsive fan, and an engine core, the method including: measuring a total thrust generated by the engine; measuring the thrust generated by the engine core; measuring first and second engine performance parameters; based on the total thrust and engine core thrust, determining a thrust generated by the propulsive fan; providing a first power setting parameter associating the fan thrust with the first engine performance parameter; and providing a second power setting parameter associating the engine core thrust with the second engine performance parameter.

Abstract: A method of controlling a gas turbine engine having a propulsive fan and an engine core, the method includes: measuring a first engine performance parameter indicative of the output of the fan; measuring a second engine performance parameter indicative of the output of the engine core; determining a thrust contribution generated by the fan based on a first power setting parameter and the first engine performance parameter; determining a thrust contribution generated by the engine core based on a second power setting parameter and the second engine performance parameter; determining the total thrust based on the fan thrust and core thrust; and controlling the engine based on the determined total thrust, wherein the total thrust includes the fan thrust and the engine core thrust.

Abstract: A method of calibrating a gas turbine engine having a propulsive fan, and an engine core, the method including: measuring a total thrust generated by the engine; measuring the thrust generated by the engine core; measuring first and second engine performance parameters; based on the total thrust and engine core thrust, determining a thrust generated by the propulsive fan; providing a first power setting parameter associating the fan thrust with the first engine performance parameter; and providing a second power setting parameter associating the engine core thrust with the second engine performance parameter.

Abstract: A fuel control system is provided for a gas turbine engine having a core engine comprising at least one core engine spool in which a compressor and a turbine are interconnected by a shaft. The system includes a first engine sensor which determines a power output of the engine. The system further includes a control unit which is configured to compare the determined power output with a value of a power threshold, and to command a reduction in fuel supplied to the engine when the determined power output exceeds the power threshold value. The system further includes a second engine sensor which measures the rate of change of rotational speed of the core engine spool. The control unit is further configured to adjust the power threshold value as a function of the measured rate of change of speed of the core engine spool.