Two-speed epicyclic gearbox with clutch for aircraft propulsion system

An aircraft propulsion system, comprising:

• a gas turbine engine;
• a gearbox that includes an input shaft extending along a first rotational axis, an output shaft extending along a second rotational axis, an epicyclic gear arrangement, a drive gear rotatable about the second rotational axis, and a first layshaft assembly, wherein the input shaft is driven by the gas turbine engine;
• and
• a multiplate clutch engaged with the first layshaft assembly, the multiplate clutch including a first carriage, a second carriage, a plurality of clutch discs, a plurality of clutch plates, and a linear actuator;
• wherein the epicyclic gear arrangement includes a sun gear, a plurality of planet gears, and a ring gear, wherein the sun gear is connected with the drive gear and is rotatable about the second rotational axis;
• wherein the first layshaft assembly extends along a first layshaft rotational axis and includes a first layshaft, a first layshaft input gear, and a first layshaft ring engagement gear, wherein the first layshaft ring engagement gear is engaged with the ring gear, and the first layshaft input gear is engaged with the drive gear and the input shaft;
• wherein the multiplate clutch is disposable in a disengaged configuration wherein the first layshaft ring engagement gear is uncoupled with the first layshaft input gear, and in an engaged configuration wherein the first layshaft ring engagement gear is coupled with the first layshaft input gear;
• wherein the first rotational axis, the second rotational axis, and the first layshaft rotational axis are each offset from each other;
• and
• wherein an engine oil is used to hydraulically power the linear actuator.