In some embodiments, apparatuses are provided herein useful to sealing a gap between a movable flap and stationary structure, such as a gap between a gas turbine engine nozzle flap and sidewall. An apparatus for sealing such a gap may be a plunger seal which may include a plurality of plunger segments connected together using at least one flexure. When positioned in the gap, the flexures within the plunger segments pivot allowing rotation of each of the plurality of plunger segments about their respective pivot point, such that the plunger assembly seals and contours against the movable surface.

A gas turbine engine and combustor assembly are provided, the combustor assembly including a first liner and a second liner together defining at least in part a combustion chamber, wherein the first liner and the second liner are separated by a gap along the longitudinal direction, and wherein the first liner is forward of the second liner relative to a flow of fluid through the combustion chamber along the longitudinal direction, and wherein the gap is extended along the circumferential direction.

An airfoil assembly defines an axial direction, a radial direction, and a circumferential direction, and includes an airfoil and an outer band disposed on an outer end of the airfoil in the radial direction. The outer band includes an outer attachment structure configured to secure the outer band to an outer support structure on an outer side of the outer band.

A method of forming a ceramic matrix composite component having an internal cooling circuit includes wrapping at least a first sheet around a first mandrel, wrapping at least a second sheet around a second mandrel, creating a first plurality of holes in the first sheet corresponding to a plurality of openings in the first mandrel, creating a second plurality of holes in the second sheet corresponding to a plurality of openings in the second mandrel, aligning the first mandrel and the second mandrel such that the first plurality of holes face and are aligned with the second plurality of holes, wrapping at least a third sheet around both the first mandrel and second mandrel to form a preform, the preform comprising each of the first sheet, the second sheet, and the third sheet, and densifying the preform. The first sheet, second sheet, and third sheet are formed from a ceramic fiber material.

A method for making a ceramic matrix composite component includes densifying a fibrous preform of the component with a ceramic matrix to form an intermediate component; infiltrating a hole in the intermediate component with an infiltrate material comprising a solid and a metallic alloy whose reaction forms a carbide, silicide, boride or combination thereof, heating the infiltrate material to a temperature in excess of a melting point of the metallic alloy; and sequentially cooling regions of the hole starting from an interior end of the hole to the outer surface of the intermediate component to form a solidified through-thickness reinforcement element. The hole extends in a through-thickness direction and is open to an exterior surface of the intermediate component.

A vertical member, which is preferably a support post used in a molten metal pump, includes a ceramic tube and tensioning structures to add a compressive load to the tube along its longitudinal axis. This makes the tube less prone to breakage. A device, such as a pump, used in a molten metal bath includes one or more of such vertical members.

A rim-rotor assembly has an annular structure including a composite rim and a hub. Blades project from the hub, tips of the blades contacting the annular structure, the blades configured to be loaded in compression against the annular structure. A thermal barrier is in the annular structure, the thermal barrier defining at least part of a radially inward surface of the annular structure. The tips of the blades contact the thermal barrier, the thermal barrier being a thermal barrier coating.

An assembly for a gas turbine engine includes, among other things, an end wall including a main body extending between a first end portion and a second end portion to establish a seal face. The end wall includes a first attachment portion dimensioned to fixedly attach the main body to a static structure at a first attachment point. An airfoil extends radially inwardly from the end wall relative to an assembly axis. The airfoil includes an inner cavity extending between a first end portion and a second end portion, the first end portion adjacent the end wall of the airfoil. A spar member includes a spar body extending between a first end portion and a second end portion. The spar body extends at least partially through the inner cavity. The first end portion of the end wall is cantilevered from the first attachment point.

A gas turbine engine includes a ceramic wall for bounding an engine core gas path. The ceramic wall has a ceramic wall first side that faces the engine core gas path and a ceramic wall second side that faces away from the engine core gas path. There is a metallic wall adjacent the ceramic wall second side. The metallic wall has a metallic wall first side that faces the ceramic wall and a metallic wall second side that faces away from the ceramic wall. The metallic wall and the ceramic wall are spaced apart such that there is a channel there between. There is a seal on the ceramic wall second side, and the metallic wall has at least one cooling hole adjacent the seal for emitting cooling air to cool the seal.

A component for a gas turbine engine includes a component body formed of ceramic matrix composite lamina and has at least one hook. The at least one hook has an attachment region radially inward of the at least one hook. The attachment region is radially thinner from a hook end of the at least one hook to a remote end, and then becomes radially thicker. A slot is formed through a radial thickness of the at least one hook from the hook end in a remote direction, such that there are two sections of the attachment region. A gas turbine engine is also disclosed.