公开(公告)号：AU2006202238A1

公开(公告)日：2007-02-22

申请号：AU2006202238

申请日：2006-05-26

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GOLAN JOHN W ,  DUBE BRIAN P ,  SALZILLO RICHARD M JR ,  BUTCHER RANDALL J

IPC: F01D5/30 ,  F01D5/14

Abstract: A turbine blade (100) is provided for use in a gas turbine engine. The turbine blade (100) has a platform (102), an airfoil (104) radially extending from the platform (102), and an attachment portion (108) comprising an asymmetric root neck portion (114) having a higher stress side (126) and a lower stress side. The turbine blade (100) may further have additional material (120) and a compound fillet (124) for dispersing strain in a region where the airfoil (104) overhangs the neck portion (114).

公开(公告)号：SG130114A1

公开(公告)日：2007-03-20

申请号：SG2006052211

申请日：2006-08-02

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DUBE BRYAN P ,  BUTCHER RANDALL J

Abstract: A blade is provided for use in a gas turbine engine. The blade has a platform, an airfoil portion extending radially from a first side of the platform, and an attachment portion extending from a second or underside side of the platform. The attachment portion includes a buttress which abuts the second side of the platform. The blade is provided with additional material on the second side of the platform for redistributing load away from the buttress.

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.