General Electric Company

Nicholas Edward Antolino

Glen Harold Kirby

Don Mark Lipkin

Herbert Chidsey Roberts

Kevin Paul McEvoy

Anant Achyut Setlur

Venkat Subramaniam Venkataramani

Neelesh Nandkumar Sarawate

Julin Wan

Anthony Yu-Chung Ku

Atanu Saha

Reza Sarrafi-Nour

Stephen Francis Bancheri

Edip Sevincer

Satya Kishore Manepalli

Anthony Christopher Marin

Luc Stephane Leblanc

Nathaniel Patrick Brown

Guruvenket Srinivasan

David Poerschke

Randall Scott Hagerdon

Taryn Elizabeth Hewitt

Kevin Paul Mcevoy

Environmental barrier coatings including a bondcoat layer including silicon and a rare earth silicate-based hermetic layer and rare earth silicate-based non-hermetic layer are provided. The rare earth silicate-based hermetic layer is deposited on the bondcoat via a thermal spray process and has an elastic modulus ranging from 100 GPa to 180 GPa. The at least one rare earth silicate-based non-hermetic layer is deposited on the rare earth silicate-based hermetic layer and has an elastic modulus ranging from 50 GPa to 100 GPa. Coated gas turbine engine components and methods for coating gas turbine engine components are also provided.

Environmental barrier coatings

In one aspect, a method for performing in situ repairs of internal components of a gas turbine engine may generally include inserting a repair tool within an interior of the gas turbine engine such that a tip end of the repair tool is positioned within the gas turbine engine and an exterior end is positioned outside the gas turbine engine. The method may also include positioning the tip end of the repair tool adjacent to a defect of an internal component, wherein the defect defines a fillable volume along a portion of the internal component. In addition, the method may include intermixing two or more constituents of a repair agent within the repair tool at a mixing location defined within the gas turbine engine, and expelling the repair agent from the tip end such that the fillable volume is at least partially filled with the repair agent.

System and method for performing an in situ repair of an internal component of a gas turbine engine

Methods of forming an environmental barrier coating are disclosed. A method includes disposing a powder-based coating on a substrate, heat-treating the powder-based coating at a temperature greater than 800&#xb0; C. and less than 1200&#xb0; C. to form a porous coating that includes surface-connected pores, infiltrating at least some of the surface-connected pores of the porous coating with an infiltrant material to form an infiltrated coating, and sintering the infiltrated coating at a temperature greater than 1200&#xb0; C. and less than 1500&#xb0; C. to form the environmental barrier coating on the substrate.

Environmental barrier coating and methods of preparation

A coating system on a CMC substrate is provided, along with methods of its tape deposition onto a substrate. The coating system can include a bond coat on a surface of the CMC substrate; a first rare earth silicate coating on the bond coat; a first sacrificial coating of a first reinforced rare earth silicate matrix on the at least one rare earth silicate layer; a second rare earth silicate coating on the sacrificial coating; a second sacrificial coating of a second reinforced rare earth silicate matrix on the second rare earth silicate coating; a third rare earth silicate coating on the second sacrificial coating; and an outer layer on the third rare earth silicate coating. The first sacrificial coating and the second sacrificial coating have, independently, a thickness of about 4 mils to about 40 mils.

Compositions and methods of attachment of thick environmental barrier coatings on CMC components

A coated seal slot system for turbomachinery includes a first turbine component comprising a first groove having at least one first coating attached to at least a portion of the first groove of the first turbine component, a second turbine component comprising a second groove having at least one second coating attached to at least a portion of the second groove of the second turbine component. The first and the second turbine components are disposable adjacent to each other with the first groove having the first coating and the second groove having the second coating together forming a coated seal slot extending across a gap between the first turbine component and the second turbine component. A seal is disposable in the coated seal slot and extendable across the gap between the first and the second turbine components and engageable with the first coating and the second coating to inhibit leakage of gas through the gap.

Coated seal slot systems for turbomachinery and methods for forming the same

A rare earth silicate-based hermetic layer includes a thermal sprayed coating including a rare earth silicate having a hermetic microstructure. An environmental barrier coating includes a bond coat layer including silicon; and at least one rare earth silicate-based hermetic layer deposited on the bond coat layer by thermal spraying. The rare earth silicate-based hermetic layer includes a thermal sprayed coating including a rare earth silicate having a hermetic microstructure. An article for service in extreme environments may be provided with such an environmental barrier coating. A thermal spray feedstock for producing a rare earth silicate-based hermetic layer.

Compositions and methods for thermal spraying a hermetic rare earth environmental barrier coating

There is set forth herein a silicon-based patch formulation comprising about 25 to 66 percent by volume of a solvent; about 4 to 10 percent by volume of a silicon-comprising binding material; and about 30 to 65 percent by volume of a patching material, the patching material comprising particles having one or more non-actinide Group IIIA elements, wherein a molar ratio of the one or more non-actinide Group IIIA elements to silicon within the patch formulation is about 0.95 to 1.25.

Silicon-based repair methods and composition

Processes for fabricating ceramic membranes include providing a porous substrate having at least one inner channel extending therethrough and having surfaces defined by porous walls, depositing a coating slurry on surfaces of the inner channel(s), and sintering. Sintering temperatures for the processes range from about 400&#xb0; C. to 800&#xb0; C. Coating slurries for use in the processes include a boehmite sol and a colloidal suspension of porous alumina particles.

Ceramic membranes

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Schenectady, NY, United States of America

Nicholas Edward Antolino