公开(公告)号：SG108232A1

公开(公告)日：2005-01-28

申请号：SG200007303

申请日：2000-12-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WILLIAM PATRICK ALLEN ,  WALTER E OLSON ,  DILIP M SHAH ,  ALAN DAVID CETEL

IPC: C22C19/00 ,  C23C4/00 ,  C23C4/08 ,  C23C30/00 ,  F01D5/28 ,  C23C10/52

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 overlay coating such as an MCrAlY is located on the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blade in these regions. Where the airfoil is also coated, the airfoil coating may have a composition different from that of the coating on the underplatform surfaces.

公开(公告)号：SG96589A1

公开(公告)日：2003-06-16

申请号：SG200007299

申请日：2000-12-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WILLIAM PATRICK ALLEN ,  WALTER E OLSON ,  DILIP M SHAH ,  ALAN DAVID CETEL

IPC: C23C4/00 ,  C23C30/00 ,  F01D5/28 ,  B32B15/00 ,  C22C19/00 ,  C23C16/00

Abstract: According to the invention, an article that is exposed to high temperature e.g., over 1000° C. during operation is disclosed. In one embodiment, a method for a gas turbine engine includes a directionally solidifed 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 overlay coating such as an MCrAlY or a noble metal containing aluminide or corrosion inhibiting ceramic is located on portions or the blade not previously covered with such coatings, e.g., the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blade in these regions. Where the airfoil is also created, the airfoil coating may have a composition different from that of the coating on the underplatform surfaces.

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.