A gas turbine engine (20) typically includes a fan section, 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 section such that the fan section may rotate at a speed different than the turbine section (28) so as to increase the overall propulsive efficiency of the engine (20). In such engine architectures, a shaft (40) driven by one of the turbine sections (28) provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section (28) such that both the turbine section (28) and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine (20).
GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE
ARCHITEKTUR FÜR EINEN GASTURBINENMOTOR MIT EINEM GETRIEBETURBOLÜFTER
ARCHITECTURE DE MOTEUR À TURBINE À GAZ À DOUBLE FLUX ET À ENGRENAGES
2015-11-18
Patent
Elektronische Ressource
Englisch
IPC: | B63H Schiffsantrieb oder Steuerung der Schiffe , MARINE PROPULSION OR STEERING / B64C AEROPLANES , Flugzeuge / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke |