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US 2016/0237835 A1Published application
Compressible fan blade with root spacer
AssigneeUnited Technologies Corporation
InventorsLee Drozdenko, William R. Graves
Life of this patent
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Abstract
A spacer for use in a hub and blade assembly of a gas turbine engine including a first layer of a first material forming the spacer body having an elongate shape. The first material has a first stiffness. A second layer of a second material is mechanically attached to the first layer. The second material has a second stiffness different from the first stiffness.
Claims20
A spacer for use in a hub and blade assembly of a gas turbine engine, the spacer comprising:
- a first layer of a first material forming a spacer body having an elongate shape, the first material having a first stiffness;
- and
- a second layer of a second material mechanically attached to the first layer, the second material having a second stiffness different from the first stiffness.
A method of constructing a gas turbine engine fan blade assembly, the method comprising:
- mechanically coupling at least one root of a fan blade to a hub;
- and
- inserting a spacer with a first layer of a first material having a first compressibility and a second layer of a second material having a second compressibility between the at least one root of the fan blade and the hub.
Dependencies are inferred from the claim text.