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 EINES GASTURBINENMOTORS MIT GETRIEBETURBOLÜFTER
ARCHITECTURE DE MOTEUR DE TURBINE À GAZ ET TURBORÉACTEUR À ENGRENAGES
2018-04-25
Patent
Electronic Resource
English