System and method for thrust linearization with thrust lever angle

A system for correlating engine thrust and engine thrust lever angle (TLA) during operation of an aircraft, the aircraft having a gas turbine engine and a thrust lever in communication with the gas turbine engine, the system comprising:

• a first sensor operable to determine an initial Mach number of the aircraft;
• a second sensor operable to determine an initial thrust lever angle (TLA) of the thrust lever and to provide a signal representative of the initial thrust lever angle;
• a third sensor operable to sense an initial fan speed value and provide a signal representative of the initial fan speed;
• and
• an onboard controller in communication with the first, second, and third sensors, and a memory device storing instructions, which instructions when executed cause the onboard controller to:
• determine a corrected maximum fan speed value based on the fan speed sensed using signals from the third sensor and one or more initial flight conditions;
• determine a first corrected net thrust value based on the corrected maximum fan speed value and the initial Mach number;
• determine a compensation factor based on the corrected maximum fan speed value and a reverse corrected maximum fan speed value, the reverse corrected maximum fan speed value determined based on a stored data structure containing a range of corrected fan speed values and corrected net thrust values as functions of Mach number values;
• determine a second corrected net thrust value as a function of the initial TLA and the first corrected net thrust value;
• correlate an engine fan speed to the initial TLA using the second corrected net thrust value as a function of the initial TLA and the compensation factor, and determine a corrected maximum rated fan speed value as a function of the initial TLA;
• and
• operate the gas turbine engine at said corrected maximum rated fan speed value as a function of the initial TLA.