Walter Olson

US Patent:

6435826, Aug 20, 2002

Filed:

Apr 16, 2001

Appl. No.:

09/835809

Inventors:

William Patrick Allen - Portland CT
Walter E. Olson - Vernon CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F04D 2944

US Classification:

415200, 416241 R

Abstract:

According to the invention, an article that is exposed to high temperatures, e. g. , over 1000Â 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 noble metal-containing aluminide coating is located on portions of the blade susceptible to corrosion and/or stress corrosion cracking, such as the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blade in these regions.

US Patent:

6435830, Aug 20, 2002

Filed:

Dec 20, 1999

Appl. No.:

09/467516

Inventors:

William Patrick Allen - Portland CT
Walter E. Olson - Vernon CT
Dilip M. Shah - Glastonbury CT
Alan David Cetel - West Hartford CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 522

US Classification:

416193A, 416241 R, 416248

Abstract:

According to the invention, an article that is exposed to high temperatures, e. g. , over 1000Â 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.

US Patent:

6435835, Aug 20, 2002

Filed:

Dec 20, 1999

Appl. No.:

09/467517

Inventors:

William Patrick Allen - Portland CT
Walter E. Olson - Vernon CT

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

F01D 514

US Classification:

416241R

Abstract:

According to the invention, an article that is exposed to high temperatures, e. g. , over 1000Â 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 noble metal-containing aluminide coating is located on portions of the blade susceptible to corrosion and/or stress corrosion cracking, such as the underside of the platform and the neck. The applied coating prevents corrosion and stress corrosion cracking of blade in these regions.

US Patent:

7700154, Apr 20, 2010

Filed:

Nov 22, 2005

Appl. No.:

11/284611

Inventors:

Walter E. Olson - Vernon CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B05D 7/22
C23C 16/06

US Classification:

427239, 427237, 4272481, 427250, 118715

Abstract:

A method for coating internal surfaces of a turbine engine component comprises flowing an aluminide containing gas into passages in the turbine engine component so as to coat the internal surfaces formed by the passages, allowing the aluminide containing gas to flow through the passages and out openings in external surfaces of the turbine engine component, and flowing a volume of a gas selected from the group consisting of argon, hydrogen, and mixtures thereof over the external surfaces to minimize any build-up of an aluminide coating on the external surfaces.

US Patent:

8025730, Sep 27, 2011

Filed:

Jul 9, 2007

Appl. No.:

11/825782

Inventors:

Mark A. Livings - East Windsor CT, US
Walter E. Olson - Buckeye AZ, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

C23C 16/52

US Classification:

118715, 118719, 118728, 427237, 427250

Abstract:

A coating apparatus for coating interior surfaces of internal passages of a workpiece, such as a turbine engine component is provided. The coating apparatus comprises a vessel defining an internal space, a plate dividing the internal space into a first chamber and a second chamber, a divider supporting the plate, and the plate having at least one cut-out for receiving a portion of the workpiece having the internal passages to be coated.

US Patent:

7360678, Apr 22, 2008

Filed:

Jan 27, 2005

Appl. No.:

11/044938

Inventors:

Norman Pietruska - Durham CT, US
Walter E. Olson - Vernon CT, US
Beth K. Abriles - Madison CT, US
David A. Rutz - Glastonbury CT, US

Assignee:

United Technologies Corporation - Hartford CT

International Classification:

B23K 31/00
B23K 35/36

US Classification:

228119, 228226

Abstract:

Novel materials and methods for repairing/reclassifying superalloy components are described herein. These materials are non-traditional blends of materials having a much higher base material content than traditional repair/reclassification materials. In embodiments used to repair/reclassify nickel-based components, these materials may comprise about 5-18. 9 weight percent of a low melting point alloy and about 81. 1-95 weight percent of a base material. In embodiments used to repair/reclassify cobalt-based components, these materials may comprise about 15-30 weight percent of a low melting point alloy and about 70-85 weight percent of a base material. These materials can be used to repair surface defects and/or build up worn or eroded areas of a component to meet precise dimensional and metallurgical requirements. These materials create robust repaired components having a dense, isothermally solidified structure having minimal borides and a high re-melt temperature.

US Patent:

20010004474, Jun 21, 2001

Filed:

Dec 13, 2000

Appl. No.:

09/736074

Inventors:

William Allen - Portland CT, US
Walter Olson - Vernon CT, US
Dilip Shah - Glastonbury CT, US
Alan Cetel - West Hartford CT, US

Assignee:

United Technologies Corporation

International Classification:

B05D003/02

US Classification:

427/446000, 427/248100, 427/383300

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 method 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 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 coated, the airfoil coating may have a composition different from that of the coating on the underplatform surfaces.

US Patent:

20010004475, Jun 21, 2001

Filed:

Dec 13, 2000

Appl. No.:

09/736545

Inventors:

William Allen - Portland CT, US
Walter Olson - Vernon CT, US
Dilip Shah - Glastonbury CT, US
Alan Cetel - West Hartford CT, US

Assignee:

United Technologies Corporation

International Classification:

B05D003/02

US Classification:

427/446000, 427/383300, 427/248100

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 method 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 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 coated, the airfoil coating may have a composition different from that of the coating on the underplatform surfaces.