Aeromet Technologies, Inc.

Mt Coatings, LLC

Siemens Aktiengesellschaft

Rolls-royce Corporation

Chromalloy Gas Turbine Corporation

Organic Cautery, LLC

Acromet Technologies Inc.

Siemens Industrial Turbomachinery Gmbh

David C Fairbourn

Max Sorenson

Paul Mathew Walker

Edward A Loeser

Richard Patrick Chesnes

Sunny Chang

Johnny D Grubbs

Xuan Nguyen-Dinh

Ky D Ngo

Paul Walker

A method for removing a coating including a rare earth silicate from a substrate including a ceramic or ceramic matrix composite may include contacting a coating comprising a rare earth silicate with a liquid comprising an active species. The active species may include at least one of a mineral acid or a base. The method also may include working the coating to cause removal of at least a portion of the coating.

Removing coatings from ceramic matrix composite substrates

A titanium electrosurgical instrument, such as a scalpel (), and electrosurgical devices, e.g., needle (), and Bovie tips (), are provided with a silane coating () directly against the solid titanium metal () of the body tissue-contacting distal ends () thereof whereby to impart advantageous non-stick properties thereto.

Silane coating for medical devices and associated methods

Metal components with a protective coating containing silicon and a process for forming such protective coatings. The protective coating is formed by applying a silicon-containing fluid composition to the metal component as a silicon-containing layer and then heating the silicon-containing layer to a temperature exceeding 400&#xb0; F.

Metal components with silicon-containing protective coatings substantially free of chromium and methods of forming such protective coatings

A method of forming a metallic wetting layer on the surface of a metal component is provided, including the steps of placing the component into a chemical vapor deposition furnace, placing a metal-containing salt in the furnace, and heating the component and the metal-containing salt in the furnace to cause the metal from the metal-containing salt to deposit in a coating on the surface of the component forming a metallic wetting layer that improves the metallic bond of a subsequently applied brazing material. The process can be practiced with the addition of a cleaning reagent to both clean and coat in one operation.

Chemical vapor deposition of metal layers for improved brazing

A turbine engine component () with a non-aluminide protective coating () containing silicon and chromium and a process for forming such non-aluminide protective coatings (). The non-aluminide protective coating () is formed by applying a silicon-containing fluid composition to the turbine engine component () as a silicon-containing layer () and heating the silicon-containing layer () to a temperature effective to form the non-aluminide protective coating ().

Turbine engine components with non-aluminide silicon-containing and chromium-containing protective coatings and methods of forming such non-aluminide protective coatings

A chemical vapor deposition (CVD) system and method for applying an aluminide coating constituted by two or more extrinsic metal components on a jet engine component. The aluminide coating is capable of forming a protective complex oxide upon subsequent heating in an oxidizing environment. At least one of the extrinsic metals in the aluminide coating is provided as a first vapor phase reactant from a receptacle coupled by a closed communication path with the reaction chamber of the CVD system and free of a carrier gas. The aluminide coating is formed by the chemical combination of the first vapor phase reactant with a second vapor phase reactant either created in situ in the reaction chamber or supplied by a carrier gas to the reaction chamber from a precursor source.

Simple chemical vapor deposition systems for depositing multiple-metal aluminide coatings

Methods and systems for forming modified metal coatings on a gas turbine engine component (). The gas turbine engine component () is placed inside a container () having a known volume, along with a source material () containing a secondary element. The container (), gas turbine engine component (), and the source material () inside the container are placed into an oxygen-depleted space () inside a reaction chamber (). At least one temperature for the source material () is determined based upon the known volume of the container () and an amount of the source material (). While in the oxygen-depleted space (), the source material () is heated to the at least one temperature sufficient to release a vapor phase reactant () containing the secondary element. The vapor phase reactant () is confined inside the container () at an approximately constant pressure and the secondary element is deposited from the vapor phase reactant () as a layer () on the gas turbine engine component ().

Apparatus and methods for forming modified metal coatings

A MCrAlY alloy, methods to produce a MCrAlY layer and a honeycomb seal are provided. The MCrAlY alloy includes chromium, aluminum, yttrium and iron and optionally titanium, hafnium or silicon. The honeycomb seal includes a substrate, honeycomb cells and a protective coating on side walls of the honeycomb cells or a diffusion area inside side walls of the honeycomb cells, the protective coating or the diffusion area including the MCrAlY alloy.

MCrAlY alloy, methods to produce a MCrAlY layer and a honeycomb seal

A metal component () with a protective coating () containing silicon and a process for forming such protective coatings (). The protective coating () is formed by applying a silicon-containing fluid composition to the metal component () as a silicon-containing layer () and heating the silicon-containing layer () to a temperature exceeding 400&#xb0; F.

Methods for removing coatings from metal components, such as metal components used in aircraft and other aerospace vehicles and the oil industry. The method may include removing an outer layer of a coating with a first stripping operation, removing an inner layer of the coating with a second stripping operation, and specifying an aqueous bath for either the first stripping process based upon an element in the outer layer or the second stripping process based upon an element in the inner layer.

Methods for removing coatings from a metal component

Apparatus and methods for removing coatings from metal components, such as metal components used in aircraft and other aerospace vehicles and the oil industry, as well as aqueous bath compositions. The metal component may be DC coupled with a counter electrode and immersed in an aqueous bath that includes an active oxygen source and a ligand in a composition effective to remove the coating. The aqueous bath may include hydrogen peroxide as the active oxygen source and may be maintained in a specific pH range if the temperature of the aqueous bath is controlled. In an alternative embodiment, the composition of the aqueous bath may include a non-peroxide active oxygen source, such as sodium perborate, and be maintained in a different specific pH range. An oxygen sensor may be provided to periodically monitor the concentration of active oxygen in the aqueous bath.

Apparatus, methods, and compositions for removing coatings from a metal component

A gas turbine engine component () with an aluminide coating () on at least a portion of an airflow surface () that includes a roughening agent () effective to provide a desired surface roughness and a deposition process for forming such aluminide coatings (). A layer () including a binder () and the roughening agent () maybe applied to the superalloy substrate () of the component () and the aluminide coating () formed on the airflow surface portion by exposing the component () and layer () to an appropriate deposition environment. Suitable roughening agents include metal and ceramic particles () that are dispersed on the airflow surface portion before exposure to the deposition environment. The particles (), which are substantially intact after the aluminide coating () is formed, are dispersed in an effective number to supply the desired surface roughness.

Roughened coatings for gas turbine engine components

A turbine engine component () with a protective aluminide coating () that include additions of silicon and a dopant, such as yttrium and/or hafnium, in an amount effective to reduce sulfidation and a deposition process for forming such aluminide coatings (). A silicon-containing layer () may be applied to the superalloy substrate () of the component () and the aluminide coating () formed by exposing component () and layer () to a vapor phase reactant containing the dopant. The aluminide coating (), which contains dopant from the layer (), may operate as a standalone environmental coating or as a bond coating for an optional ceramic thermal barrier layer (). An optional zirconia layer () maybe provided between the aluminide coating () and the ceramic thermal barrier layer (). Alternatively, the dopant may be included in the silicon-containing layer () applied to the component () before the aluminide coating () is formed and no vapor phase reactant containing the dopant is required.

Gas turbine engine components with aluminide coatings and method of forming such aluminide coatings on gas turbine engine components

Methods for cleaning surface deposits, such as sulfidation deposits or dust particles, from a surface bounding an internal passage in a turbine engine component. The surface deposits are cleaned by placing a halogen-containing organic compound, such as a fluorine-containing organic compound, into the internal passage and heating the component and organic compound to chemically react the halogen-containing species in the liquefied and boiling organic compound with the deposits. The temperature is further elevated to vaporize the chemically-modified deposits, which are moved by mass transport through the internal passage and out of the turbine engine component. An optional protective coating, such as a chromium or aluminum coating, may be applied to the cleaned surface of the internal passage.

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Sandy, UT, United States of America

David C Fairbourn