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.

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.

The invention relates to a bladed disk (1) of a fan, comprising: a hub (10) comprising an outer radial platform (13) designed so as to define an inner gas flow stream in the turbomachine, a plurality of blades (20) comprising a root (23) connected to the platform (13), a leading edge (21) and a trailing edge (22), a groove formed in the platform (13) around part of the root (23) of each blade (20) in an area adjacent to the leading edge (21) and/or the trailing edge (22), and a joint (30) placed in the groove (15) in such a way that it extends in the extension of the radially outer face (14) of the platform (13) in order to ensure a continuity of the inner flow stream.

A turbine vane is provided. The turbine vane may include an inner shroud having an upper surface and a lower surface, a seal unit disposed in the lower surface of the inner shroud and defining a first region and a second region in the lower surface of the inner shroud, a first impingement unit arranged in the first region and comprising a first impingement plate facing the inner shroud defining a first impingement chamber therebetween, wherein the first impingement plate is configured to receive cooling air and form impingement jet directed to the first impingement chamber, a second impingement unit arranged in the second region and comprising a second impingement plate facing the inner shroud defining a second impingement chamber therebetween, and at least one connector flow channel configured to direct cooling air from the first impingement chamber to the second region, wherein the second impingement plate is configured to receive cooling air from the at least one connector flow channel and form impingement jet directed to the second impingement chamber.

An impingement insert for an airfoil of a turbomachine component is provided. The insert includes first and second body parts, each having inner and outer surfaces; and first and second contact parts provided on the outer surfaces of the first and the second body parts. The insert includes a flexible mechanical seal part between the body parts. A flow channel for cooling air is defined by the seal part and the inner surfaces of the body parts. One or both of the body parts include impingement holes. The insert has an elastic part connected to the body parts. When the elastic part is subjected to deformation, the elastic part is configured to apply a force, on the first and/or the second body parts, in a direction of increasing a separation between the first contact part and the second contact part.

A seal assembly includes first, second, and third gas turbine engine components, such as vane assemblies, that are successively arranged around an axis. Each component has first and second mate faces such that the first mate face of the first component and the second mate face of the second component define a first mate face gap, and the first mate face of the second component and the second mate face of the third component to define a second mate face gap. A seal arc segment has first and second seal portions and a connector portion that joins the seal portions. The first seal portion bridges the first mate face gap to seal the first mate face gap, the second seal portion bridges the second mate face gap to seal the second mate face gap, and the connector portion spans circumferentially across the second component.

A vane assembly includes an airfoil extending from a platform. The platform has a flange that extends radially outward and circumferentially across the platform. A vane cover is arranged adjacent the platform that defines an impingement gap between the platform and the vane cover. The vane cover has a wall that defines a slot. The flange is arranged at least partially within the slot.

An airfoil assembly includes an airfoil fairing, a spar, a seal plate, and a seal. The airfoil fairing has a fairing platform and a hollow airfoil section that extends from the fairing platform. The spar has a spar leg that extends in the hollow airfoil section. The spar leg defines a spar leg periphery. The seal plate is secured with the fairing platform. The seal plate has an opening, and the opening has an opening periphery that is complementary to the spar leg periphery. The spar leg extends through the opening. The seal is between the seal plate and the spar leg. The seal seals around the spar leg periphery.

A sealing system for a gas turbine engine includes a first surface and a second surface spaced a dimension away from the first surface defining a gap through which a fluid can flow. At least one recess is formed in one of the first surface and the second surface and is oriented such that the fluid flow through the gap crosses the at least one recess. The recess is configured to restrict the fluid flow through the gap in comparison to if the at least one recess were not present, all other things being equal.

A seal includes a ceramic matrix composite ply having woven ceramic-based fibers in a ceramic-based matrix. The ceramic matrix composite ply has at least one bend formed about a bend axis and defines at least one rounded portion. A sealed assembly and a method of making a seal are also disclosed.