US 12,291,344 B2
Aircraft performance optimization based on engine performance monitoring
Mehdi M. Baladi, Cincinnati, OH (US); Aniello Esposito, Turin (IT); Sridhar Adibhatla, Glendale, OH (US); and Kathleen K. Collins, Lynn, MA (US)
Assigned to GE Avio S.r.l., Rivalta di Torino (IT)
Filed by GE Avio S.r.l., Rivalta di Torino (IT)
Filed on Jan. 11, 2024, as Appl. No. 18/410,493.
Application 18/410,493 is a division of application No. 17/471,774, filed on Sep. 10, 2021, abandoned.
Claims priority of application No. 102020000023104 (IT), filed on Sep. 30, 2020.
Prior Publication US 2024/0208660 A1, Jun. 27, 2024
Int. Cl. B64D 31/06 (2024.01); B64D 33/02 (2006.01); B64D 45/00 (2006.01); F02C 9/00 (2006.01); G08G 5/00 (2006.01)
CPC B64D 31/06 (2013.01) [B64D 33/02 (2013.01); B64D 45/00 (2013.01); F02C 9/00 (2013.01); G08G 5/003 (2013.01); B64D 2033/0273 (2013.01); B64D 2221/00 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A computer-readable, non-transitory storage medium storing instructions that, when executed by a digital controller of an aircraft comprising a turbine engine causes the aircraft to execute a method comprising:
storing in a memory of the digital controller an operating log of engine performance over an engine degradation time, the engine degradation time being a time period when the turbine engine is predicted to have reduced engine thrust or power because of engine degradation;
calculating from the operating log a change in engine performance of the turbine engine over the engine degradation time;
determining an allowed maximum operating power for the turbine engine in response to the change in engine performance of the turbine engine over the engine degradation time;
determining changes in performance of the turbine engine over the engine degradation time based on changes in performance of a compressor of the turbine engine over the engine degradation time;
determining changes in performance of the compressor based on changes in constant efficiency islands of performance on a stall map of performance of the compressor over time;
determining at the digital controller, based on data received from the turbine engine during flight, that a load on the turbine engine exceeds the allowed maximum operating power; and
upon determining that the load on the turbine engine exceeds the allowed maximum operating power, issuing a control command to an aircraft system other than the turbine engine (ASOTE) to rebalance a power load on the turbine engine.