MULTI CORE GEARED GAS TURBINE ENGINE

An aircraft propulsion system (12) includes a fan section (14) that includes a fan shaft (16) that is rotatable about a fan axis (26) and that includes a fan gear (24). The aircraft propulsion system (12) also includes a boost turbine engine (28) that includes a first output shaft (32) that includes a first gear (34) that is coupled to the fan gear (24) and has a first maximum power capacity. The aircraft propulsion system (12) further includes a cruise gas turbine engine (30) that includes a second output shaft (58) that includes a second gear (60) that is coupled to the fan gear (34) and has a second maximum power capacity that is less than the first maximum power. The fan section (14) produces a thrust that corresponds to power input through the fan gear (34) from the boost turbine engine (28) and the cruise turbine engine (30).