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filingDate 2013-10-24^^<http://www.w3.org/2001/XMLSchema#date>
grantDate 2017-07-25^^<http://www.w3.org/2001/XMLSchema#date>
inventor http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_d7af0d50db41f5eb10ff26ebfacdd559
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publicationDate 2017-07-25^^<http://www.w3.org/2001/XMLSchema#date>
publicationNumber US-9714577-B2
titleOfInvention Gas turbine engine rotors including intra-hub stress relief features and methods for the manufacture thereof
abstract Embodiments of a gas turbine engine rotor including stress relief features are provided, as are embodiments of method for producing a gas turbine engine rotor. In one embodiment, the method includes producing a hub preform in which a plurality of elongated sacrificial cores are embedded. Blades are attached to an outer circumference of the hub preform by, for example, bonding a blade ring to the outer circumference of the preform. The blades are spaced about the rotational axis of the gas turbine engine rotor and circumferentially interspersed with the plurality of elongated sacrificial cores. The plurality of elongated sacrificial cores are then removed from the hub preform to yield a plurality of stress distribution tunnels extending in the hub preform.
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