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.

公开(公告)号：SG127708A1

公开(公告)日：2006-12-29

申请号：SG200400363

申请日：2004-01-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CUNHA FRANK J ,  DUBE BRYAN P

IPC: F01D5/08 ,  F01D5/00 ,  F01D5/18 ,  F01D5/30 ,  F02C7/18

Abstract: An improved cooling design and method for cooling airfoils within a gas turbine engine is provided which includes an embedded microcircuit that traverses a tip (36) between a suction sidewall (44) and a pressure sidewall (42) of the airfoil (54). The microcircuit includes at least one inlet (70) disposed proximate to the tip (36) and one of the sidewalls (44) for receiving cooling air from an internal cooling cavity of the airfoil and at least outlet (72) disposed proximate to the tip (36) through which the cooling air ejects into a region outside the airfoil.

公开(公告)号：EP3047108A4

公开(公告)日：2017-04-19

申请号：EP14845469

申请日：2014-08-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZELESKY MARK F ,  DUBE BRYAN P ,  CHRISTOPHEL JESSE R

IPC: F01D5/28 ,  F01D5/18 ,  F01D9/04

CPC classification number: F01D25/005 ,  F01D5/189 ,  F01D5/284 ,  F01D9/041 ,  F01D25/12 ,  F02C3/04 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2260/201 ,  F05D2300/17 ,  F05D2300/176 ,  F05D2300/20 ,  F05D2300/5023