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公开(公告)号：SG130089A1
公开(公告)日：2007-03-20
申请号：SG2006037378
申请日：2006-06-01
Applicant: UNITED TECHNOLOGIES CORP
Inventor： DUBE BRYAN P , GOLAN JOHN W , BUTCHER RANDALL J , RICHARD M SALZILLO JR
Abstract: A turbine blade is provided for use in a gas turbine engine. The turbine blade has a platform, an airfoil radially extending from the platform, and an attachment portion comprising an asymmetric root neck portion having a higher stress side and a lower stress side. The turbine blade may further have additional material and a compound fillet for dispersing strain in a region where the airfoil overhangs the neck portion.
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