A ceramic component is generally provided that includes a silicon-based layer comprising a silicon-containing material (e.g., a silicon metal and/or a silicide) and about 0.001% to about 85% of a Ga-containing compound. For example, the silicon-based layer can be a bond coating directly on the surface of the substrate. Alternatively or additionally, the silicon-based layer can be an outer layer defining a surface of the substrate, with an environmental barrier coating on the surface of the substrate. Gas turbine engines are also generally provided that include such a ceramic component.

An acoustic structure for a gas turbine engine comprising a noise reduction layer and a fire protector layer connected to the noise reduction layer. The noise reduction includes a perforated inner wall adapted to be in contact with a first fluidic environment, and a noise reduction adjacent to the inner wall. The fire protector layer includes a non-perforated outer wall adapted to be in contact with a second fluidic environment having potentially a fire, a fire protector adjacent to the outer wall, and a pressure resisting wall disposed between the fire protector and the noise reduction. The second fluidic environment is under a pressure lower than a pressure of the first fluidic environment. The inner and outer walls are load-bearing walls of the acoustic structure.

An apparatus and method for cooling a fluid within a turbine engine. A fan casing assembly for the turbine engine can include an annular fan casing with a peripheral wall having a flow path defined through the casing. A fan casing cooler includes a body to confront the peripheral wall with at least one conduit configured to carry a flow of heated fluid to convectively cool the heated fluid with a flow of air through the flow path.

A turbine shroud assembly is disclosed including an inner shroud having a surface adjacent to a hot gas path, an outer shroud, a damper block disposed between the inner shroud and the outer shroud, a first biasing apparatus, and a second biasing apparatus. The first biasing apparatus provides a first biasing force to the inner shroud, biasing the inner shroud a first deflection distance in a direction toward the hot gas path and away from the outer shroud. The second biasing apparatus provides a second biasing force to the damper block, biasing the damper block a second deflection distance in a direction toward the hot gas path and away from the outer shroud. The second deflection distance is greater than the first deflection distance.

Provided are a coated member in which damage of a coating film can be suppressed in a high temperature environment and the coating may be performed at low cost, and a method of manufacturing the same. A coated member includes a bond coat and a top coat sequentially laminated on a substrate made of a Si-based ceramic or a SiC fiber-reinforced SiC matrix composite, wherein the top coat includes a layer composed of a mixed phase of a (Y.sub.1-aLn.sub.1a).sub.2Si.sub.2O.sub.7 solid solution (here, Ln.sub.1 is any one of Nd, Sm, Eu, and Gd) and Y.sub.2SiO.sub.5 or a (Y.sub.1-bLn.sub.1b).sub.2SiO.sub.5 solid solution (here, Ln.sub.1 is any one of Nd, Sm, Eu, and Gd), or a mixed phase of a (Y.sub.1-cLn.sub.2c).sub.2Si.sub.2O.sub.7 solid solution (here, Ln.sub.2 is any one of Sc, Yb, and Lu) and Y.sub.2SiO.sub.5 or a (Y.sub.1-dLn.sub.2d).sub.2SiO.sub.5 solid solution (here, Ln.sub.2 is any one of Sc, Yb, and Lu).

An oxide and non-oxide based ceramic matrix composite (CMC) component for a combustion turbine engine has a solidified ceramic core with a three-dimensional preform of ceramic fibers, embedded therein. Engineered surface features (ESFs) are cut into an outer surface of the core and fibers of the preform. A thermal barrier coat (TBC) is applied over and coupled to the core outer surface and the ESFs. The ESFs provide increased surface area and mechanically interlock the TBC, improving adhesion between the ceramic core and the TBC.

A gas turbine engine component includes a metal substrate and a coating system disposed on the metal substrate. The coating system includes at least one layer of aluminum-chromium oxide.

Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arc segment adjacent to a second arc segment, each arc segment including an end surface and radially facing surfaces extending from opposite ends of the end surface; a slot located between the end surfaces of the first arc segment and the second arc segment; and a first seal disposed in the slot, the first seal contacting the first arc segment at the end surface and extending over the radially facing surfaces of the first arc segment, the first seal including: a shim contacting the first arc segment; a laminate material over the shim and covering the shim; and a conforming material coupling the laminate material to the shim.

The present invention relates to a mechanical system that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses an articulating cone. When in a retracted position the articulating cone allows the aircraft to operate in low speed mode as only the turbo jet receives airflow. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face, precluding operation of the turbine engine.

Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arc segment adjacent to a second arc segment, each arc segment including an end surface and radially facing surfaces extending from opposite ends of the end surface; a slot located between the end surfaces of the first arc segment and the second arc segment; and a first seal disposed in the slot, the first seal contacting the first arc segment at the end surface and extending over the radially facing surfaces of the first arc segment, the first seal including: a shim contacting the first arc segment; a laminate material over the shim and covering the shim; and a conforming material coupling the laminate material to the shim.