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US 10,378,440 B2Granted
Geared turbofan with improved gear system maintainability
AssigneeUnited Technologies Corporation
InventorWilliam G. Sheridan
Life of this patent
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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.
Claims19
A gas turbine engine comprising:
- a fan section including a hub supporting a plurality of fan blades rotatable about an axis;
- a bearing assembly supporting rotation of the hub about the axis;
- a gas generator including a fan drive turbine;
- and
- a speed reduction device driven by the fan drive turbine for rotating the fan about the axis, wherein the speed reduction device is mounted radially inward and axially within an axial width of the plurality of fan blades supported by the hub forward of the bearing assembly supporting rotation of the hub.
2 more elements
A method of removing a geared architecture from a gas turbine engine comprising:
- accessing a geared architecture mounted radially inward and axially within an axial width of blades of the fan section supported by a hub and forward of a bearing assembly at least partially supporting the hub of the fan section;
- decoupling a portion of the geared architecture from a fixed engine structure;
- and
- removing the geared architecture in a direction forward of the fan section.
1 more element
Dependencies are inferred from the claim text.