A turbine ring sector made of ceramic matrix composite material has a portion forming an annular base with an inner face for defining the inner face of a turbine ring when the ring sector is mounted on a ring support structure and an outer face from which there extends an attachment portion for attaching the ring sector to the ring support structure, the ring sector further including inter-sector faces, each for facing a neighboring ring sector when the ring sector is mounted on the ring support structure; wherein the inter-sector faces are coated in an environmental barrier that is doped with an electrically-conductive compound and that presents at least one slot.

A system for coating a component is provided. The system includes a feedstock supply, a carrier fluid supply, and a thermal spray gun coupled in flow communication with the feedstock supply and the carrier fluid supply. The feedstock supply contains a substantially homogeneous powder mixture of a first powder and a second powder. The second powder is softer than the first powder and has a percentage by mass of the powder mixture of between about 0.1% and about 3.0%.

A method for joining engine components includes positioning a first plurality of thermal protection structures across a thermal protection space between a first thermal protection surface and a second thermal protection surface. The first and second engine components are locally joined by forming a first plurality of transient liquid phase (TLP) or partial transient liquid phase (PTLP) bonds along corresponding ones of the first plurality of thermal protection structures between the first thermal protection surface and the second thermal protection surface. The second thermal protection surface is formed from a second surface material different from a first surface material of the first thermal protection surface.

A component is provided and includes a core including a ceramic matrix composite material, one or more cooling channels formed about the core, an outer metal shell disposed about the core and the one or more cooling channels and a protective material between the core and the outer metal shell. The one or more cooling channels are formed about the core as an array of cooling channels in the protective material.

A control ring for use in a gas turbine engine includes a control ring segment defining a centerline axis. The control ring segment includes an inner diameter surface and an outer diameter surface. A thermally isolating contact is operatively connected to at least one of the inner diameter surface and the outer diameter surface. The thermally isolating contact has lower thermal conductivity than the control ring.

A gas turbine engine ceramic panel assembly includes a ceramic liner that has a slot and includes a hole. An insert is received in the slot and provides a female fastening element aligned with the hole. A method of manufacturing a ceramic panel assembly includes the steps of forming a ceramic liner with a slot, installing an insert into the slot, and securing the ceramic liner to a structure using a fastening assembly.

Core assemblies for manufacturing airfoils and airfoils made therefrom having an aft flowing serpentine hybrid skin core positioned relative to a plurality of core bodies and configured to define at least one serpentine cavity within the manufactured airfoil. The aft flowing serpentine hybrid skin core extends from a root region toward a tip region in a radial direction of the manufactured airfoil and the plurality of core bodies are positioned about the aft flowing serpentine hybrid skin core to form a shielding structure to thermally shield the aft flowing serpentine hybrid skin core in the manufactured airfoil.

A seal system for a gas turbine vane includes a first seal layer and an optional second seal layer. Each first seal layer includes multiple seal segments, each of which includes a first leg, a second leg, and an intermediate portion between the first leg and the second leg. Each adjacent pair of seal segments of the first seal is separated by a gap. The seal segments define a substantially complete perimeter of a seal slot in which the first seal is installed. The second seal, which is also segmented, may or may not define the substantially complete perimeter of the seal slot. If present, the second seal segments are circumferentially offset from the first seal segments to block the gaps between the first seal segments. A turbine vane including the present seal system is also disclosed.

A process for forming a component is provided. The process includes providing a cooling channel flow definition at least partially about a core including a ceramic matrix composite material. A metal material is cast about the core and the cooling channel flow definition to form an outer metal shell. In addition, a cooling channel is formed from the cooling channel flow definition in the component.

Embodiments of the present disclosure are directed to an article and methods of forming the article. The article includes a thermal barrier coating disposed on a substrate. The thermal barrier coating includes a thermal barrier material and partially filled surface-connected columnar voids. The partially filled surface-connected columnar voids are interspersed with the thermal barrier material in the thermal barrier coating. At least some of the partially filled surface-connected columnar voids include a calcium-magnesium-aluminum-silicon-oxide (CMAS)-reactive material disposed within, such that the CMAS-reactive material is physically separated from the substrate by a columnar cavity having an aspect ratio greater than 3.