US 12,228,085 B2
System and method for thrust linearization with thrust lever angle
Jeffrey Poissant, Brossard (CA); Robert Pontarelli, Brossard (CA); and Cristina Crainic, Longueuil (CA)
Assigned to Pratt & Whitney Canada Corp., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Oct. 28, 2022, as Appl. No. 17/976,509.
Prior Publication US 2024/0141839 A1, May 2, 2024
Int. Cl. F02C 9/16 (2006.01); F02C 9/28 (2006.01); F02C 9/44 (2006.01)
CPC F02C 9/28 (2013.01) [F02C 9/16 (2013.01); F02C 9/44 (2013.01); F05D 2220/323 (2013.01); F05D 2270/051 (2013.01); F05D 2270/304 (2013.01); F05D 2270/311 (2013.01); F05D 2270/313 (2013.01); F05D 2270/708 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A method for operating a gas turbine engine powered aircraft by correlating engine thrust and engine thrust lever angle (TLA) during operation of the gas turbine engine powered aircraft, said method comprising:
(a) determining initial flight conditions during operation of the aircraft, said initial flight conditions including an initial Mach number of the aircraft, an initial altitude of the aircraft, and an initial TLA, and reporting said initial flight conditions to an onboard controller within the aircraft;
(b) determining a corrected maximum fan speed value based on an initial sensed fan speed and the initial flight conditions determined in step (a);
(c) providing a stored data structure containing a range of corrected fan speed values and corrected net thrust values as functions of Mach number values, and determining a first corrected net thrust value based on said stored data structure;
(d) performing a reverse lookup of the stored data structure to determine a reverse corrected maximum fan speed value, and determining a compensation factor based on the corrected maximum fan speed value determined in step (b) and the reverse corrected maximum fan speed value;
(e) determining a second corrected net thrust value as a function of the initial TLA and the first corrected net thrust value determined in step (c); and
(f) correlating 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 determined in step (d), and determining a corrected maximum rated fan speed value as a function of the initial TLA; and
(g) operating the gas turbine engine at the corrected maximum rated fan speed value as a function of the initial TLA determined in step (f).