公开(公告)号：SG102661A1

公开(公告)日：2004-03-26

申请号：SG200201296

申请日：2002-03-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WILLIAM P ALLEN ,  WILLIAM A VERONESI ,  ROBERT J HALL ,  MICHAEL J MALONEY ,  JOHN W APPLEBY ,  DOUGLAS C HAGUE ,  ABDUS S KHAN

IPC: C04B41/87 ,  C23C14/06 ,  C23C28/00 ,  B32B7/02 ,  B32B15/04

Abstract: An article has a protective ceramic coating 26 which reduces radiation heat transport through the ceramic coating. The protective ceramic coating 26 includes one or more embedded reflective metallic layers 30', 30'', 30''' for reducing the radiation heat transport. The article may be a turbine component and the coating 26 may be a thermal barrier coating.

公开(公告)号：SG114762A1

公开(公告)日：2005-09-28

申请号：SG200501174

申请日：2005-03-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DILIP M SHAH ,  ALAN D CETEL ,  ALAN W STONER ,  WILLIAM P ALLEN

IPC: C22C19/05 ,  F01D5/28 ,  F01D25/00 ,  F02C7/00

Abstract: A high modulus component, such as an aircraft engine turbine blade, is formed from a base metal that has a high modulus crystallographic orientation that is aligned with the primary, i.e. radial, direction of the turbine blade. The base metal is Ni, Fe, Ti, Co, Al, Nb, or Mo based alloy. Alignment of a high modulus direction of the base metal with the primary direction provides enhanced high cycle fatigue life.