A generator apparatus (1) capable of preventing an increase in the frontal area of an aircraft engine is provided with: a transmission (22) connected to a rotating shaft of the engine; a generator (34) driven by output from the transmission (22); an input shaft (27) connected to the rotating shaft and having a shaft center extending in a direction perpendicular to the rotating shaft; and a transmission mechanism (21) connected to the input shaft (27) and configured to drive the transmission (22) about the shaft center perpendicular to the input shaft (27). The transmission (22) and the generator (34) are spaced apart from each other in the circumferential direction of the rotating shaft.
