Aerofoil blades with improved impact resistance
An aerofoil blade for a gas turbine engine, the blade having a metallic core defining a number of cavities that contain a foamed material. The cavities are shaped such that the force of an impact on one surface of the blade is dissipated through the foam and transmitted to the metallic core. A fibro...
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Main Authors | , |
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Format | Patent |
Language | English |
Published |
14.09.2010
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Subjects | |
Online Access | Get full text |
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Summary: | An aerofoil blade for a gas turbine engine, the blade having a metallic core defining a number of cavities that contain a foamed material. The cavities are shaped such that the force of an impact on one surface of the blade is dissipated through the foam and transmitted to the metallic core. A fibrous internal containment device allows the blade to fragment progressively thereby spreading the load imparted by the blade to a casing should the blade fragment upon impact. |
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Bibliography: | Application Number: US20060484728 |