Abstract: 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.

Abstract: A honeycomb seal is provided. The honeycomb seal is in one part with a substrate so that there is no brazing is needed. Furthermore, a better corrosion resistance is gained by the substrate having a coating comprising iron, chromium, aluminum and/or yttrium, especially applied by vapour deposition. A method for producing a honeycomb seal is also provided.

Abstract: 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.

Abstract: A turbine engine component (10) with a non-aluminide protective coating (14) containing silicon and chromium and a process for forming such non-aluminide protective coatings (14). The non-aluminide protective coating (14) is formed by applying a silicon-containing fluid composition to the turbine engine component (10) as a silicon-containing layer (20) and heating the silicon-containing layer (20) to a temperature effective to form the non-aluminide protective coating (14).

Abstract: 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.

Abstract: Apparatus and methods for removing tungsten-containing coatings from metal components, such as metal components used in aircraft and other aerospace vehicles. The metal component is 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 tungsten-containing coating. The aqueous bath may be maintained at a pH greater than about 7.0 and less than or equal to about 8.0. A sensor may be provided to periodically monitor the oxidation reduction potential of the aqueous bath. Another sensor may be provided to periodically monitor the pH of the aqueous bath.

Abstract: Aluminide coatings or layers (14) for jet engine components (10) and a process for forming aluminide layers (14) that include additions of silicon and yttrium. A superalloy substrate (12) of the component (10) is initially coated with a layer of a silicon-containing material. The substrate (12) is then aluminided, for example by a chemical vapor deposition process, and is exposed to a yttrium-containing material during the aluminiding process to form the aluminide layer (14) containing silicon and yttrium. A ceramic thermal barrier layer (24) of yttria-stabilized zirconia may be optionally applied over the aluminide layer (14). Another optional zirconia layer (26) maybe provided between the aluminide layer (14) and the ceramic thermal barrier layer (24). The present invention provides a silicon- and yttrium-containing aluminide layer (14) having improved durability, either as a standalone environmental coating or as a bond coat for a subsequently-applied ceramic thermal barrier layer (24).

Abstract: 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.