United Technologies Corporation

Raytheon Technologies Corporation

Corey L Hubbert

Peter V Tomeo

Colin J Kling

Shelton O Duelm

Carney R Anderson

Charles W Brown

Christopher M Quinn

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.

Fan rotor with integrated platform attachment

A fan hub assembly for a gas turbine engine includes a fan hub that is configured to rotate about an axis. The fan hub has an axially extending aperture and a platform. A fastener is received in the aperture in a slip fit relationship to secure the platform to the fan hub.

Gas turbine engine fan spacer platform attachments

A fan section for a gas turbine engine includes a fan hub having blade slots for receiving a root of a fan blade. A lock ring is configured to move rotatably from an unlocked position to a locked position for securing the blade root in the blade slot. A nose cone is secured to the lock ring, and thereby secured to the fan section.

Gas turbine engine nose cone attachment

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Manchester, CT, United States of America

Corey L Hubbert