A stack molding pattern and a shell for manufacturing aircraft turbine engine blades via lost wax casting. The stack molding shell includes a plurality of shell blade elements, each intended for producing a blade, wire elements being arranged within the shell blade elements; and a metal feeder including a plurality of metal outlets, each one radially open towards one of the shell blade elements and connected with the second end portion of the element. The shell includes a protective screen, associated with each second end portion and intended to protect a sensitive portion of the wire elements against the direct impact of a flow of metal from the feeder. The sensitive portion is located in the second end portion, downstream from the protective screen.

A turbine intermediate casing for a gas turbine comprising outer and inner wall elements arranged in series in circumferential direction and delimiting a flow passage for exhaust gas; strut fairing elements arranged in radial direction between respective outer and inner wall elements; an outer casing encompassing the outer and inner wall elements; and an annular mounting structure encompassing a bearing region of a shaft of the gas turbine. The strut fairing elements comprise a space for accommodating carrier elements which extend from the annular mounting structure through the flow passage to the outer casing exhaust gas flowing through the flow passage being directed by the strut fairing elements around the carrier elements. The outer and inner wall and strut fairing elements comprise ceramic fiber composite materials, the outer and inner wall elements being connected to the outer casing and the annular mounting structure respectively.

A sealing system including a first component at least partially manufactured from ceramic fiber composite materials, a second component at least partially manufactured from ceramic fiber composite materials, and a sealing element accommodated between the first component and the second component. The sealing element is designed as a sealing strip. It is provided that at least one recess accommodating the sealing element is formed on the first component and/or on the second component, the recess having a cross-sectional profile including an inner section which is concave toward the sealing element, the radius of curvature of the inner section being selected in such a way that it may be formed with the aid of continuous, curved fibers of the ceramic fiber composite material, the fibers being oriented in such a way that they lie essentially in parallel to the cross-sectional plane of the cross-sectional profile.

A turbine airfoil for a gas turbine engine includes a pressure sidewall extending along a spanwise direction, and from a leading edge of the airfoil towards the trailing edge of the airfoil. The turbine airfoil additionally includes a suction sidewall also extending along the spanwise direction, and from the leading edge towards the trailing edge. The pressure sidewall and suction sidewall define a cooling air cavity therebetween, and one or both of the pressure sidewall and suction sidewall define a trailing edge cooling channel extending from the cooling air cavity substantially to the trailing edge. Additionally, one or both of the pressure sidewall and suction sidewall include a plurality of pressure drop members extending partially into the trailing edge cooling channel for reducing an amount of cooling air flowing therethrough from the cooling air cavity.

An airfoil assembly including a composite body having a mounting edge and a trailing edge which is secured to a leading edge element defining a 3-D leading edge geometry with both chord and camber variation.

A vane assembly (10) having: an airfoil (12) and a shroud (14) held together without metallurgical bonding there between; a channel (22) disposed circumferentially about the airfoil (12), between the airfoil (12) and the shroud (14); and a seal (20) disposed in the channel (22), wherein during operation of a turbine engine having the vane assembly (10) the seal (20) has a sufficient ductility such that a force generated on the seal (20) resulting from relative movement of the airfoil (12) and the shroud (14) is sufficient to plastically deform the seal (20).

A rotor for a turbine engine includes a disk having cavities called primary cavities at its periphery; a plurality of blades each having a root of which the lower part is composed of a bulb locked axially in the primary cavities; a plurality of added platforms, each being arranged between two consecutive blades, wherein the platforms have: a substantially straight plate and a bulb extending radially under the plate, the bulb being locked axially in the secondary cavities arranged at the periphery of the disk, the secondary cavities being positioned between two consecutive primary cavities; a spoiler extending in the axial direction, the spoiler forming an annular sector facing at least two consecutive blades,

A method is provided for manufacturing a component. This method includes additively manufacturing a crucible for casting of the component. A metal material is directionally solidified within the crucible to form a metal single crystal material. A sacrificial core is removed to reveal a metal single crystal component with internal passageways. A component is provided for a gas turbine engine that includes a metal single crystal material component with internal passageways. The metal single crystal material component was additively manufactured of a metal material concurrently with a core that forms the internal passageways. The metal material was also remelted and directionally solidified.

A blades outer air seal includes a seal arc segment that defines radially inner and outer sides. The radially outer side includes radially-extending sidewalls and a radially inner surface that joins the radially-extending sidewalls. The radially-extending sidewalls and the radially inner surface define a pocket. A manifold is disposed at least partially in the pocket. The manifold subdivides the pocket such that there is a manifold chamber bounded by the manifold and the radially inner surface. The manifold includes at least one inlet and a plurality of outlets.

A seal assembly includes a seal arc segment that defines radially inner and outer sides with the radially outer side including radially-extending sidewalls. A radially inner surface joins the radially-extending sidewalls. The radially-extending sidewalls and the radially inner surface define a pocket. A rail shield has radially-extending walls lines the radially-extending sidewalls.