ATTÉNUATION DE DÉMARRAGE ET RÉDUCTION D'USURE DE ROTOR BOMBÉ D'UN SYSTÈME DE MOTEUR À TURBINE À GAZ

摘要

An engine system (200) for an aircraft (100) includes a first gas turbine engine (20A), a second gas turbine engine (20B), and a control system (202). The control system (202) is configured to operate the first gas turbine engine (20A) with an idle fuel burn schedule in a taxi mode (408) of the aircraft and dry crank the second gas turbine engine (20B) in a first pre-takeoff portion (312A) of the taxi mode to cool the second gas turbine engine (20B) absent fuel burn by the second gas turbine engine. The control system (202) operates the second gas turbine engine with a sub-idle fuel burn schedule in a second pre-takeoff portion (312B) of the taxi mode of the aircraft. The sub-idle fuel burn schedule includes a reduction of the idle fuel burn schedule. A fuel flow of the first gas turbine engine (20A) and the second gas turbine engine (20B) is increased above the idle fuel burn schedule prior to takeoff of the aircraft.