A method for depositing a coating of a source material onto a panel is disclosed. The method includes providing a cathodic arc, the cathodic arc including a target surface, the target surface disposed along a target deposition axis and able to emit the source material as a generally cloud of source material vapor and a generally conical stream of liquid particles of the source material. The method further includes positioning the panel relative to the target surface based on a deposition angle, the deposition angle being between the target surface and an outer limit of the generally conical stream of liquid particles o the source material. The method may further include emitting the source material from the target surface as the generally conical cloud of source material vapor and coating the edge with the cloud of source material vapor to provide an edge coating.

A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform with an opening, forming a fiber fastener, inserting the fiber fastener into the opening, and infiltrating a matrix material into the fiber preform and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

A treatment composition is disclosed including a carrier and a sacrificial oxide-forming material suspended within the carrier. The sacrificial oxide-forming material is selected from the group consisting of tin oxide, magnesium oxide, antimony pentaoxide, and combinations thereof. A treatment process for a gas turbine component including an abradable ceramic coating is disclosed. The process includes contacting the abradable ceramic coating with the treatment composition. The sacrificial oxide-forming material is infused into the abradable ceramic coating to form sacrificial oxide-forming deposits within the abradable ceramic coating. A rejuvenation process is disclosed including contacting the hot gas path surface of a gas turbine component with a rinse composition comprising water and the treatment composition to form the sacrificial oxide-forming deposits within the abradable ceramic coating.

The present invention is in the field of a high pressure heating installation and in particular a waste incineration installation comprising an advanced panel design and cladding thereof. Said cladding relates to a cladding to a in particular at least partly curved surface of a membrane panel, which panel is used in a high temperature and high pressure incinerator, such as a waste incinerator.

A viewport for a combustion zone includes an inner casing having a flange extending into the combustion zone. A first layer of ceramic fiber insulation is exterior to the inner casing. A middle casing includes two panes of quartz glass separated by traverse plates. A second layer of ceramic fiber insulation is exterior to the middle casing. An outer casing is positioned to the exterior of the second layer of insulation. The middle casing includes L-shaped ledges having third and fourth layers of ceramic insulation. The panes of glass are each positioned between layers of insulation and the insulation positioned in the L-shaped ledges. The viewport is modular enabling the separation of the first layer of insulation, the middle casing, the second layer of insulation and the outer casing from the combustion zone for maintenance or repair. The viewport minimizes heat migration to the outer casing during use.

A flow element for fluidic contact with a hot gas flow inside an aircraft engine includes: a base material, which has a hot gas surface that faces the gas flow and a remote surface that is remote from the gas flow, the base material being completely surrounded by a chroming layer on the hot gas surface and on the remote surface; an adhesive layer on the chroming layer in first portions; an alitising layer, the alitising layer being arranged on the adhesive layer in the first portions; and a thermal barrier layer being arranged on the alitising layer in the first portions. The alitising layer is arranged on the chroming layer in second portions that do not have an adhesive layer, the chroming layer and the alitising layer forming a chroming-alitising layer in the second portions.

An assembly comprising a ceramic matrix composite component, a monolithic insert, and a polymer char and a method for producing the same. The ceramic matrix composite component may include an exterior surface, with the monolithic insert bonded to the exterior surface of the ceramic matrix composite component. The polymer char may be sandwiched between the monolithic insert and the exterior surface of the ceramic matrix composite that may bond the monolithic insert to the ceramic matrix composite component.

The thermal barrier coating includes reactive gadolinia in its microstructures and the embedded gadolinia effectively reacts with CMAS contaminant reducing the damage from CMAS. Moreover, a method to produce a CMAS resistant thermal barrier coating can include a post-treatment to the thermal barrier coating with the reactive gadolinia suspension in sol-gel state.

A method of forming high strength glass fibers in a refractory-lined glass melter, products made there from and batch compositions suited for use in the method are disclosed. The glass composition for use in the method of the present invention is up to about 64-75 weight percent SiO.sub.2, 16-24 weight percent Al.sub.2O.sub.3, 8-12 weight percent MgO and 0.25-3 weight percent R.sub.2O, where R.sub.2O equals the sum of Li.sub.2O and Na.sub.2O, has a fiberizing temperature less than about 2650 F., and a T of at least 80 F. By using oxide-based refractory-lined furnaces the cost of production of glass fibers is substantially reduced in comparison with the cost of fibers produced using a platinum-lined melting furnace. High strength composite articles including the high strength glass fibers are also disclosed.

A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform, applying a polymer material to the fiber preform to form a rigid preform structure, machining an opening in the rigid preform structure, forming a fiber fastener, inserting the fiber fastener into the opening, removing the polymer material, and infiltrating a matrix material into the rigid preform structure and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.