United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Douglas Michael Berczik

Gabriel L Suciu

Timothy Coons

Brian D Merry

Michael G McCaffrey

Wayde R Schmidt

Christopher Marc Dye

Paul Sheedy

David A Litton

Kevin W Schlichting

Mario P Bochiechio

Ioannis Alvanos

Steven Lawrence Suib

Melvin Freling

Russell Albert Beers

Tania Bhatia Kashyap

John D Riehl

Mark F Bartholomew

Brendan M Lenz

Lea Kennard Castle

Imelda P Smyth

Michael A Kmetz

Andi M Limarga

Kevin L Rugg

Allan A Noetzel

Shiela R Woodard

Kirk C Newton

Thomas E O'Connell

James F Myers

Justin Reutenauer

George Brodi

Alvanos Ioannis

Mark A Hermann

Steve Lawrence Suib

Rafael Raban

William John Bajorek

Mark Thomas Ucasz

An article includes a substrate formed of a molybdenum-based alloy. A barrier layer is disposed on the substrate. The barrier layer is formed of at least one noble metal.

Molybdenum-silicon-boron with noble metal barrier layer

Disclosed is a method for fabricating a ceramic material from a preceramic polymer material. The method includes providing a preceramic polymer material that has a preceramic polymer and an electromagnetic radiation-responsive component. The electromagnetic radiation-responsive component is selected from cobalt, titanium, zirconium, hafnium, tantalum, tungsten, rhenium, and combinations thereof. An electromagnetic radiation is applied to the preceramic polymer material. The electromagnetic radiation interacts with the electromagnetic radiation-responsive component to generate heat that converts the preceramic polymer to a ceramic material.

Method for pyrolyzing preceramic polymer material using electromagnetic radiation

An article includes a substrate formed of a molybdenum-based alloy. The molybdenum-based alloy has a composition that includes molybdenum, silicon, and boron. A barrier layer is disposed on the substrate. The barrier layer is formed of at least one noble metal.

A method of densifying a CMC article includes the steps of pyrolyzing a CMC article until a desired initial porosity is achieved, coating CMC pores within the CMC article with carbon, pyrolyzing the carbon to form carbon pores, coating the carbon pores with silicon, and heat treating the CMC article to create a silicon carbide filled pore integrated with silicon carbide of the CMC article to densify the CMC article.

Densified polymer infiltrated and pyrolysis-based CMC articles

A Ceramic Matrix Composite (CMC) airfoil segment for a gas turbine engine includes a box-shape fiber geometry which defines a rectilinear pressure side bond line and a rectilinear suction side bond line.

Ceramic matrix composite airfoil structures for a gas turbine engine

Disclosed is a method for providing a crystalline ceramic material. In an example, the method includes providing a silicon-containing preceramic polymer material that can be thermally converted to one or more crystalline polymorphs. The silicon-containing preceramic polymer material includes dispersed therein an effective amount of dopant particles. The silicon-containing preceramic polymer material is then thermally converted to the silicon-containing ceramic material. The effective amount of dopant particles enhance the formation of at least one of the one or more crystalline polymorphs, relative to the silicon-containing preceramic polymer without the dopant particles, with respect to at least one of formation of a selected polymorph of the one or more crystalline polymorphs formed, an amount formed of a selected polymorph of the one or more crystalline polymorphs formed, and a temperature of formation of the one or more crystalline polymorphs.

Method for providing crystalline silicon-containing ceramic material

Disclosed is a method of fabricating a preceramic polymer for making a ceramic material including a metal boride. The method includes providing a starting preceramic polymer that includes a silicon-containing backbone chain and first and second reactive side groups extending off of the silicon-containing backbone chain, reacting a boron-containing material with the first reactive side group to bond a boron moiety to the silicon-containing backbone chain, and reacting a metal-containing material with the second reactive side group to bond a metal moiety to the silicon-containing backbone chain such that the preceramic polymer includes the boron moiety and the metal moiety extending as side groups off of the silicon-containing backbone chain. Also disclosed is a preceramic polymer composition and a metal-boride-containing ceramic article fabricated from the preceramic polymer.

Preceramic polymer for ceramic including metal boride

Disclosed is a method for fabricating a ceramic material from a preceramic polymer material. The method includes providing a preceramic polymer material that has a preceramic polymer and an electromagnetic radiation-responsive component. The electromagnetic radiation-responsive component is selected from boron-containing compounds, cobalt, titanium, zirconium, hafnium, tantalum, tungsten, rhenium, nitrides of aluminum, nitrides of titanium, nitrides of zirconium, nitrides of hafnium, nitrides of tantalum, nitrides of tungsten, nitrides of rhenium, carbides of aluminum, carbides of titanium, carbides of zirconium, carbides of hafnium, carbides of tantalum, carbides of tungsten, carbides of rhenium and combinations thereof. An electromagnetic radiation is applied to the preceramic polymer material. The electromagnetic radiation interacts with the electromagnetic radiation-responsive component to generate heat that converts the preceramic polymer to a ceramic material.

A Ceramic Matrix Composites (CMC) airfoil for a gas turbine engine includes a first multiple of CMC plies which define a suction side, a first airfoil portion of the first multiple of CMC plies at least partially parallel to an airfoil axis. A second multiple of CMC plies define a pressure side, a second airfoil portion of the second multiple of CMC plies at least partially parallel to the airfoil axis and bonded to the first airfoil portion.

Ceramic matrix composite airfoil for a gas turbine engine

A ceramic composite article includes ceramic carbide fibers and a ceramic matrix in which the ceramic carbide fibers are embedded. The ceramic matrix includes a laminar structure with at least one layer of a first ceramic material and at least one layer of a second, different ceramic material.

Ceramic composite article having laminar ceramic matrix

A coated article includes an article having at least one surface and composed of a molybdenum based refractory metal alloy base substrate, a niobium based refractory metal alloy base substrate or a silicon base substrate. A bond coat layer is disposed upon the surface. The bond coat layer includes a molybdenum disilicide base compound and at least one of the following: silicon nitride, silicon carbide or tantalum oxide. A process for coating the article includes the steps of applying upon the article's surface the aforementioned bond coat layer. A functionally graded material layer is applied upon the bond coat layer. The functionally graded material layer comprising molybdenum disilicide, mullite and at least one of the following: silicon nitride, silicon carbide or tantalum oxide. A thermal barrier coating layer is then applied upon the functionally graded material layer.

Bond coating and thermal barrier compositions, processes for applying both, and their coated articles

Mo&mdash;Si&mdash;B alloys having additions of a transition element selected from the group consisting of Fe, Ni, Co, Cu and mixtures thereof.

Oxidation resistant molybdenum

Molybdenum alloys are provided with enhanced oxidation resistance. The alloys are prepared by the addition of silicon and boron in amounts defined by the area of a ternary system phase diagram bounded by the points Mo-1.0% Si-0.5% B, Mo-1.0% Si-4.0% B, Mo-4.5% Si-0.5% B, and Mo-4.5% Si-4.0 B. The resultant alloys have mechanical properties similar to other high temperature molybdenum alloys while possessing a greatly enhanced resistance to oxidation at high temperature. The alloys are composed of a matrix of body centered cubic molybdenum surrounding discrete intermetallic phases. A variety of alloying elements are added to the base composition to modify the alloy properties.

Oxidation resistant molybdenum alloy

Methods of enhancing oxidation resistance and methods of making molybdenum alloys are provided. In these methods, alloys are prepared by the addition of silicon and boron in amounts defined by the area of a ternary system phase diagram bounded by the points Mo-1.0%Si-0.5%B, Mo-1.0%Si-4.0%B, Mo-4.5%Si-0.5%B, and Mo-4.5%Si-4.0 B. The methods utilize rapid solidification followed by consolidation at below the melting point. The resultant alloys have mechanical properties similar to other high temperature molybdenum alloys while possessing a greatly enhanced resistance to oxidation at high temperature.

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Manchester, CT, United States of America

Douglas Michael Berczik