公开(公告)号：SG89356A1

公开(公告)日：2002-06-18

申请号：SG200006280

申请日：2000-11-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DILIP M SHAH ,  ALAN DAVID CETEL

IPC: C23C4/00 ,  C23C4/02 ,  C23C4/10 ,  C23C30/00 ,  F01D5/28 ,  B63H1/26 ,  F01D5/14

Abstract: According to the invention, an article that is exposed to high temperatures, e.g., over 1000° C. during operation is disclosed. In one embodiment, a turbine blade for a gas turbine engine includes a directionally solidified metallic substrate, e.g., a superalloy, which defines an airfoil, a root and a platform located between the blade and root. The platform has an underside adjacent the root, and a corrosion resistant ceramic overlay coating such as a stabilized zirconia is located on the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blades in these regions.