United Technologies Corporation

Other

William Patrick Allen

Krishan Lal Luthra

Peter Joel Meschter

Hongyu Wang

James L Smialek

Kang Neung Lee

Harry Edwin Eaton, Jr

Nathan S Jacobson

Elizabeth J Opila

Dilip M Shah

Alan David Cetel

Walter E Olson

John W Appleby, Jr

Bangalore Aswatha Nagaraj

Irene T Spitsberg

Michael J Maloney

William A Veronesi

Robert A Miller

Abdus Suttar Khan

Alan W Stoner

Robert J Hall

Donald R Parille

Douglas Charles Hague

Roscoe A Pike

John G Smeggil

David N Duhl

Norman S Bornstein

Stephen Chin

Allan A Noetzel

Abdus S Khan

Michael A DeCrescente

Narottam P Bansal

Maurice L Gell

Richard S Mullin

Richard H Barkalow

James S Brewer

Nanottam P Bansal

John W Appleby

Douglas C Hague

Abdus Khan

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.

High modulus metallic component for high vibratory operation

The present invention relates to a method for forming an article having a protective ceramic coating which reduces radiation heat transport through the ceramic coating. The protective ceramic coating includes one or more embedded reflective metallic layers for reducing the radiation heat transport. The method for forming the protective coating broadly comprises the steps of forming a ceramic coating on a substrate and embedding at least one reflective metallic layer within the ceramic coating.

Reflective coatings to reduce radiation heat transfer

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

Article having corrosion resistant coating

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

A barrier layer for a silicon containing substrate which inhibits the formation of gaseous species of silicon when exposed to a high temperature aqueous environment comprises a barium-strontium alumino silicate.

Silicon based substrate with environmental/ thermal barrier layer

Silicon based substrate with environmental/thermal barrier layer

A barrier layer for a silicon containing substrate which inhibits the formation of gaseous species of silicon when exposed to a high temperature aqueous environment comprises a yttrium silicate.

Silicon based substrate with yttrium silicate environmental/thermal barrier layer

A barrier layer for a silicon containing substrate which inhibits the formation of gaseous species of silicon when exposed to a high temperature aqueous environment comprises a calcium alumino silicate.

Silicon based substrate with calcium aluminosilicate environmental/thermal barrier layer

Silicon based substrate with calcium aluminosilicate/thermal barrier layer

A thermal barrier coating for high temperature applications has improved resistance to heat flow. The coating comprises a large number of these (nanometer scale) layers separated by interfaces which are effective in retarding heat flow. The coating material will typically be oxide based ceramics and the coating has particular applications in gas turbine engines.

Multiple nanolayer coating system

Superalloy articles are made more oxidation resistant by a process which includes heat treating the article in the presence of foreign chemical species, at a temperature at which the foreign chemical species reacts with and modifies any oxide film present on the article surface. The heat treatment is best carried out at a temperature above the gamma prime solvus temperature of the article and below the incipient melting temperature of the article. Alternatively, the heat treatment may be carried out within the range defined by the incipient melting temperature of the article and about 150.degree. C. below the incipient melting temperature of the article. At such temperatures the foreign chemical species reacts with and modifies the oxide film on the article surface. Sulfur is then able to diffuse through such modified film, and a more oxidation resistant component is produced.

Method for removing sulfur from superalloy articles to improve their

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Portland, CT, United States of America

William Patrick Allen