Gas turbine engine with front support arrangement

A gas turbine engine comprising:

• a propulsor section including a propulsor having blades extending from a propulsor hub;
• a propulsor shaft that drives the propulsor hub, the propulsor rotatable about an engine longitudinal axis;
• a compressor section including a first compressor and a second compressor, the first compressor including a plurality of stages and a rotatable compressor hub, and the second compressor having a greater number of stages than the first compressor;
• a speed reduction device including an epicyclic gear system, wherein the epicyclic gear system includes a gear reduction ratio greater than 2.3, wherein the epicyclic gear system includes a sun gear, a plurality of intermediate gears, a carrier supporting the intermediate gears and the propulsor hub, and a ring gear, and wherein the speed reduction device drives the compressor hub and the propulsor through a connection established axially forward of the epicyclic gear system relative to the engine longitudinal axis;
• and
• a turbine section including a first turbine and a second turbine, wherein the second turbine drives the propulsor through the epicyclic gear system;
• wherein the epicyclic gear system is straddled by forward and aft bearings that engage the carrier.