US Patent 10174624 Composite blade root lay-up
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Patent abstract
A blade for a gas turbine engine includes composite layers that include a uni-directional layer and a fabric compliant wedge layer that are arranged adjacent to the uni-directional layer. The fabric compliant wedge layer has a reduced compressive Young's modulus compared to the uni-directional layer.
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Patent Inventor Names
Kevin L. Rugg0
Michael G. Abbott0
Michael G. McCaffrey0
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US Patent 10174624 Composite blade root lay-up
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Is a
Patent applicant
Patent jurisdiction
Patent number
10174624
Date of patent
January 8, 2019
Patent application number
14721393
Date Filed
May 26, 2015
Patent primary examiner
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