Methods for forming a sintered bond coat (64) on a silicon-based substrate (14) and articles (50) formed by the methods are disclosed. The methods include applying a bond coat slurry on the silicon-based substrate (14), drying the bond coat slurry on the silicon-based substrate to form a dried bond coat (44), and sintering the dried bond coat (44) in an oxidizing atmosphere to form a sintered bond coat (64) on the silicon-based substrate (14). The bond coat slurry includes a bond coat patching material in a bond coat fluid carrier. The articles (50) include a silicon-based substrate (14), a sintered bond coat (64) formed on the silicon-based substrate (14), and a sintered environmental barrier coating (EBC) (66) formed on the sintered bond coat (64). The sintered bond coat (64) includes a silicon-based phase and an oxide of the silicon-based phase.

A nozzle including a vane and a band, each having defined therein interlocking features. The vane and the band are each formed of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix. The vane and the band include one or more interlocking features. The nozzle further including an interlocking mechanical joint joining the vane and the band to one another. Methods are also provided for joining the vane and the band at the interlocking features to form an interlocking mechanical joint.

A thermal barrier system includes a protective coating on a substrate, and a ceramic feature layer attached to the protective coating via an adhesive spray coat.

A thermal barrier system includes a protective coating on a substrate, and a ceramic feature layer attached to the protective coating via an adhesive spray coat.

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 titanium-based component having a high heat capacity surface. The high heat capacity surface prevents or inhibits titanium fires. The component is titanium-based, forming the substrate, and includes a high heat capacity surface overlying the titanium substrate. A diffusion barrier is intermediate the titanium-based substrate and the high heat capacity surface. The diffusion barrier is non-reactive with both the titanium-based substrate and the high heat capacity surface. The system eliminates the formation of detrimental phases due to diffusion between the applied high heat capacity surface and the titanium substrate. The high heat capacity material has a coefficient of thermal expansion compatible with the coefficient of thermal expansion of the titanium-based substrate. The stresses introduced into the component as a result of differential thermal expansion between the high heat capacity material and the titanium-based substrate do not result in spalling of the substrate at the operational temperatures of the component.

A silencer of a compressor for aspirating air to be compressed, with a housing having a front plate and a rear plate, a circumferential surface extending between the front plate and rear plate and bordering a suction area, via which the air can be aspirated, and a recess in the rear plate, via which the aspirated air can be supplied to the compressor. A flow-carrying metal component, in particular a wire component, is arranged in or adjacent to the suction area as a flame absorber.

A cooling apparatus for a gas turbine engine includes a wall structure defining an air flowpath, the wall structure comprising a thermoplastic material; and a thermal barrier layer surrounding the wall structure.

Turbocharger turbine wheels including nickel-based alloys are disclosed herein. In one exemplary embodiment, a turbocharger turbine wheel includes as, at least part of its constituency, a nickel-based alloy that includes, on a weight basis of the overall alloy: about 10.5% to about 11.5% cobalt, about 9.0% to about 10.0% chromium, about 5.75% to about 6.25% aluminum, about 2.8% to about 3.3% tantalum, about 4.0% to about 4.5% molybdenum, about 2.2% to about 2.4% titanium, about 0.13% to about 0.15% carbon, about 0.03 to about 0.09% zirconium, and a majority of nickel. The nickel-based alloy excludes tungsten except in unavoidable trace amounts. The turbocharger turbine wheel may be configured for operating at about 980 C. to about 1020 C.

Thermal barrier coatings, which may be used in gas turbine engines, comprise or consist of a tantala-niobia-zirconia mixture that is stabilized with two or more stabilizers. An exemplary thermal barrier coating comprises or consists of, by mole percent: about 2% to about 30% YO.sub.1.5; about 8% to about 30% YbO.sub.1.5 or GdO.sub.1.5 or combination thereof; about 6% to about 30% TaO.sub.2.5; about 0.1% to about 10% NbO.sub.2.5; about 0% to about 10% HfO.sub.2; and a balance of ZrO.sub.2.