HYDROGEN POWERED GEARED TURBO FAN ENGINE WITH AN OFF-SET REDUCED CORE

An aircraft propulsion system includes a fan shaft (410) connected to a fan (406) and defining a centerline axis (404) of the aircraft propulsion system (400), one or more offset cores (402) arranged at an angle to the centerline axis (404), the one or more offset cores (402) each comprising a hydrogen burning combustor, a centerline cavity (422) defined along the centerline axis (404), and a heat exchanger (424, 426) arranged within the centerline cavity (422). In operation, a portion of air is directed from the fan (406) into the centerline cavity (422) to provide a first working fluid to the heat exchanger (424, 426) within the centerline cavity.