Patent ID: 11873767
Assignee: GE AVIO S.R.L.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 7:
8. An aircraft comprising:
a first turbofan engine having a first core engine, a first core engine output shaft rotating in a first rotational direction, a first gear assembly, and a first output fan drive shaft rotating in a second rotational direction to drive a first fan assembly in the second rotational direction; and
a second turbofan engine having a second core engine, a second core engine output shaft rotating in the first rotational direction, a second gear assembly, a second output fan drive shaft rotating in the first rotational direction to drive a second fan assembly in the first rotational direction, and a third gear assembly comprising a secondary gear output shaft disposed between the second core engine output shaft and the second gear assembly and rotating in the second rotational direction,
wherein the first gear assembly receives the first core engine output shaft at a first speed and drives the first output shaft at a second speed that is lower than the first speed;
wherein the third gear assembly receives the second core engine output shaft at a third speed and drives a secondary gear output shaft at the third speed,
wherein the second gear assembly receives the secondary gear output shaft at the third speed and drives the second fan drive shaft at a fourth speed that is lower than the third speed,
wherein the second core engine output shaft is axially aligned and in series with the secondary gear output shaft and
wherein a gear ratio of the first gear assembly ranges from 6:1 to 14:1.