A method of operating an aircraft hybrid gas turbofan during an idle mode of operation includes reducing a fuel flow to a primary gas turbine engine (12) and boosting a high spool (18) of the primary gas turbine engine (12) using a secondary gas turbine engine (14) via a first power linkage connecting the primary and secondary gas turbine engines (12, 14), such that a net fuel reduction is achieved. The net fuel reduction accounts for fuel flow to the primary gas turbine engine (12) and fuel flow to the secondary gas turbine engine (14).
A METHOD OF OPERATING AN AIRCRAFT HYBRID GAS TURBOFAN AND RELATIVE HYBRID GAS TURBOFAN
VERFAHREN ZUM BETREIBEN EINES HYBRID-TURBOFAN-TRIEBWERKS FÜR FLUGZEUGE UND ZUGEHÖRIGES HYBRID-TURBOFAN-TRIEBWERK
PROCÉDÉ DE FONCTIONNEMENT D'UN TURBORÉACTEUR À DOUBLE FLUX HYBRIDE D'AÉRONEF ET TURBORÉACTEUR À DOUBLE FLUX HYBRIDE ASSOCIÉ
2024-04-17
Patent
Electronic Resource
English
Springer Verlag | 2025
|Tema Archive | 1982
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