Method of fabricating a composite material blade having an integrated metal leading edge for a gas turbine aeroengine

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United States of America Patent

PATENT NO 10899051
APP PUB NO 20160167269A1
SERIAL NO

14908321

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Abstract

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A method of fabricating a blade of composite material having an incorporated metal leading edge for a gas turbine aeroengine, the method including in succession placing a metal strip for making the leading edge of a blade in a cavity of an injection mold for making the blade, closing the injection mold, injecting a thermoplastic resin under pressure into the cavity of the mold so as to shape and overmold the metal strip, compacting the assembly, solidifying the resin by regulating the temperature of the injection mold, and unmolding the resulting blade.

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Patent Owner(s)

Patent OwnerAddress
SAFRAN2 BOULEVARD DU GÉNÉRAL MARTIAL VALIN 75015 PARIS 75015

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Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Pautard, Sebastien Palaiseau, FR 9 49

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