A gas turbine engine (20) includes a fan (42), a compressor section (24), a combustor section (26) and a turbine section (28). A speed reduction device (48), such as an epicyclical gear assembly, may be utilized to drive the fan (42) at a speed different than the turbine section (28) so as to increase the overall propulsive efficiency of the engine (20). A shaft driven (30) by the turbine section (28) provides an input to the epicyclical gear assembly (48) such that both the turbine section (28) and the fan (42) can rotate at closer to optimal speeds providing increased performance attributes and performance.
GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
ARCHITEKTUR FÜR EINEN GASTURBINENMOTOR MIT EINEM GETRIEBETURBOLÜFTER
ARCHITECTURE D'UN MOTEUR À TURBINE À GAZ À TURBORÉACTEUR À DOUBLE FLUX ET À ENGRENAGE
2017-12-20
Patent
Elektronische Ressource
Englisch