An aircraft gas turbine engine (10) comprises an engine core (11) comprising a turbine (19), a compressor (14), a core shaft (26) connecting the turbine (19) to the compressor (14), and a core casing (50) surrounding the engine core (11). A fan (23) is located upstream of the engine core (11) and a fan casing (52) surrounds the fan (23). A gearbox (30) receives input from the core shaft (26) and outputs drive to rotate the fan (23). A single plane support structure (54) connects the core casing (50) and the fan casing (52). The support structure (54) comprises an inner ring (56), an outer ring (58) and a plurality of circumferentially spaced radially extending struts (60) connecting the inner ring (56) and the outer ring (58). The inner ring (56) comprising a torsion box (66, 68, 70) and a gearbox and fan support structure (24) is connected to the torsion box (66, 68, 70. A front mount (62) and a rear mount (64) are configured to connect the gas turbine engine (10) to the aircraft, wherein the front mount (62) is coupled to the torque box (66, 68, 70) and the rear mount (64) is coupled to the core casing (50).
A geared turbofan bas turbine engine mounting arrangement
2018-08-29
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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