Geared turbofan with improved gear system maintainability
Abstract:
A disclosed gas turbine engine includes a fan section including a hub supporting a plurality of fan blades rotatable about an axis, and a bearing assembly supporting rotation of the hub about the axis. A compressor section is in fluid communication with a combustor and a turbine is in fluid communication with the compressor section. A speed reduction device driven by the turbine section for rotating the fan about the axis is mounted forward of the bearing assembly supporting rotation of the hub.
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