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US 10,119,423 B2Granted
Gas turbine engine fan spacer platform attachments
AssigneeUnited Technologies Corporation
InventorsColin J. Kling, Charles W. Brown, Christopher M. Quinn, Shelton O. Duelm, Peter V. Tomeo, Corey L. Hubbert
Life of this patent
Estimating the term…
Abstract
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.
Claims11
A fan hub assembly for a gas turbine engine comprising:
- a fan hub that includes forward and aft lugs and is configured to rotate about an axis, wherein the forward and aft lugs respectively include an axially extending first and second aperture;
- a platform;
- and
- a first fastener and a second fastener integrally connected with the platform by molding, bonding or threading to the platform, and the first and second fasteners respectively are received in the first and second apertures in a slip fit relationship to secure the platform to the fan hub.
1 more element
A fan hub assembly for a gas turbine engine comprising:
- a fan hub configured to rotate about an axis and including a radially extending aperture;
- a fan blade secured to the fan hub;
- a platform that is separate and discrete from the fan blade and provides an inner flow surface that has a first hole and an axially extending flange is formed integrally with the platform providing an unbroken, unitary structure therewith, the axially extending flange includes a second hole;
- and
- a fastener that is a bolt aligned with the first hole and the fastener extends through the second hole, the fastener threadingly received in the aperture to secure the platform to the fan hub.
2 more elements
Dependencies are inferred from the claim text.