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US 2016/0252103 A1Published application
Fan rotor with integrated platform attachment
AssigneeUnited Technologies Corporation
InventorsCorey L. Hubbert, Peter V. Tomeo
Life of this patent
Estimating the term…
Abstract
A fan rotor, for an aircraft engine, including at least one blade root attachment lug, each blade root attachment lug including an attachment lug surface, wherein at least one cavity is disposed on each attachment lug surface.
Claims19
A fan rotor for an aircraft engine, the fan rotor comprising:
- at least one blade root attachment lug, including an attachment lug surface, a blade root attachment lug transverse axis, and a blade root attachment lug longitudinal axis;
- wherein the blade root attachment lug transverse axis is substantially perpendicular to the blade root attachment lug longitudinal axis;
- wherein the attachment lug surface includes a proximal end and a distal end;
- and at least one cavity disposed in the attachment lug surface.
1 more element
A gas turbine engine comprising:
- at least one fan blade platform operably coupled to a fan rotor;
- the fan rotor comprising:
- at least one blade root attachment lug, including an attachment lug surface, a blade root attachment lug transverse axis, and a blade root attachment lug longitudinal axis;
- wherein the blade root attachment lug transverse axis is substantially perpendicular to the blade root attachment lug longitudinal axis;
- wherein the attachment lug surface includes a proximal end and a distal end;
- and at least one cavity disposed in the attachment lug surface.
3 more elements
16-27. (canceled)
Dependencies are inferred from the claim text.